Axial Internal-Combustion Engines

Also known as barrel engines

Updated: 9 Oct 2014

Text sizes fixed (I hope)

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An axial or barrel engine has multiple cylinders arranged around and parallel to a central shaft, like the chambers in the cylinder of a revolver. The piston thrust is usually converted to rotary motion by a swashplate or Z-crank mechanism. The claimed advantages for this engine format were low frontal area (important for powering aeroplanes) very good balance and great compactness. On the downside there were major problems with the swashplate or wobble-plate mechanisms, and access for maintenance was poor. The axial IC engine was an obvious development of the Axial Steam Engine. No axial IC engines have achieved any sustained success.


AXIAL ENGINE TECHNOLOGY

Wobble-plates and swash-plates are not the same thing:

Left: A wobble plate motor wobbling.

A wobble plate does not go round; it is mounted on the Z-shaped crankshaft by a bearing. It is articulated to the connecting rods by ball-joints, and clearly if it did go round would tie these rods in knots. As you can see here, it does not need to be a plate as such, but can be more of a spider.

One problem with this configuration is that friction between wobble-spider and crankshaft tends to cause rotation of the spider which upsets its alignment with the pistons. Here an arm is shown moving in a channel to constrain the movement of the wobbler, but there are more sophisticated methods of stabilisation, such as those used by Charles Redrup in The Bristol axial engine, which is a good example of the type.

Another fine animation by Bill Todd

Left: A swash plate motor swashing.

A swashplate is rigidly fixed to the crankshaft, and goes round with it as a unit. Therefore the connecting rods are not fixed to the plate in any way, but push on it with rollers or slipper pads that can glide over the surface of the plate as it turns. Note that two rollers are needed, one each side of the swashplate, so it can both pull and push on the pistons.

The only examples of pure swashplate engines on this page are The Michell engine and The Alfaro Engine.

Another fine animation by Bill Todd

A variation on the swashplate engine is the cam-plate engine, in which the plate is not a flat surface, but is given a sinusoidal contour. The pistons can now be made to move back and forth twice or more during one rotation of the main shaft, giving more firing strokes and potentially increasing the power output of an engine of a given size. See The Dynacam Engine below.
There is a whole gallery of non-axial cam engines just around the corner from here.

An engine expert speaks:

"Such cylinder arrangements have serious disadvantages with regard to accessibility and mounting structure, which would make them undesirable for most services even if a reliable mechanism could be developed. There is no likelihood of such engines becoming important competitors to the conventional types."

(Quote from The Internal-Combustion Engine in Theory and Practice by Charles Fayette Taylor, 2nd edition, pub MIT press 1985. This book is a standard work on the subject of IC engines)

While I hesitate to argue with Charles Taylor, I don't see his point about accessibility and mounting structures. Accessibility for adjustments with the engine running would of course be a challenge with one of the rotating-barrel types; doing a compression test would be a most interesting procedure. The doubt about the reliability of wobble & swash mechanisms is more telling. However, I don't doubt that if we really needed axial engines with long-term reliability for some reason, the problem could be solved.


There have been some unconventional engines which have used wobble-plates but are in different galleries of the Museum because they have even more unusual features. One example is: The Selwood-Hughes Engine which had toroidal cylinders.


THE SMALLBONE AXIAL ENGINE: 1906

Above: The Smallbone axial engine patent: US 821,546 of 22nd May 1906.

Four cylinder wobble-plate gas engine; static barrel type. Water cooled.

This design by Harry Eales Smallbone is the first example of an axial IC engine found so far. It was intended to run on town gas, not gasoline/petrol. It is not currently known if it was ever built or if it was successful.

Smallbone took out Canadian patent CA 82570 rather earlier in July 1903. The patent is not viewable on the Canadian Patents Database.


THE MACOMBER AXIAL ENGINE: 1911

The first IC axial engine the indefatigable staff of the Museum have tracked down that was definitely constructed and put into use is the seven-cylinder Macomber, a rotating-barrel wobble-plate type. The ball joints between the connecting rods and the plate make it clear that it is of the wobble-plate persuasion.

Left: The Macomber Axial Engine: 1911.

In 1911 the Macomber Rotary Engine Company of Los Angeles, USA placed one of the first axial internal-combustion engines on the market. It had seven cylinders and a variable compression ratio, altered by changing the wobble-plate angle and hence the length of piston stroke.

It was a rotary engine in the sense that the whole engine rotated apart from the casings at each end.

According to the manufacturer's literature, it was "Guaranteed not to overheat", which given the small amount of finning on the cylinders, and the fact that each cylinder would be moving in the slipstream of its neighbour, seems to me a little optimistic.

Left: The Macomber Axial Engine: publicity material.

The text on the right-hand page is none too clear, so I have reproduced it below. Rather surprisingly, it does not give the engine capacity.

The cylinders were individual iron castings, with inclined valves in the cylinder heads, working in a plane through the axis of the central shaft. The inlet valve was on the inside, and drew the fuel-air mixture through the hollow shaft, from a carburetor mounted on the end of the engine. The exhaust valve was on the outside, and the exhaust goes straight out into the air through the D-shaped apertures visible in the photograph, which suggests that the engine when running would have been surrounded by a ring of exhaust flame. Because of the rotating-barrel there was no possibility of adding a silencing system.

Each pair of valves operated from a single rocker pivoted between them, which much have placed some remarkable restrictions on valve timing. One end of each rocker engaged with a groove in a four-lobe cam mounted on the central shaft. This cam was rotated by gearing.

Ignition was by a Bosch magneto operated by the cam gears. The spark was led through six inch cables to a stationary electrode on the top of the front bearing case, from which sparks jumped to the tops of the spark plugs as they passed within one-sixteenth of an inch of it.

  • MODEL "A"
  • HORSE POWER-- 50-60 Brake
  • SPEED-- 800 to 1400 Revolutions per minute
  • CYLINDERS-- Seven
  • BORE-- 4 1-4 inch.
  • STROKE-- Variable, 4 1-4 inch Maximum
  • AIR COOLED-- Guaranteed not to overheat.
  • VALVES-- Very large. Set in head, operated from single cam sleeve on main shaft. Four cycle movement.
  • IGNITION-- High tension Bosch Magneto. No wiring.
  • CARBURETOR-- Special. Injection system to order only.
  • OILING SYSTEM-- Absolutely positive. Self contained, automatic without a moving part.
  • BEARINGS-- D. W. F. and New Departure Ball Bearings throughout.
  • GREATEST EXTERNAL DIAMETER-- 19 inches.
  • LENGTH OF SHAFT-- 34 inches. Six inches allowed for attachment of propeller.
  • WEIGHT-- 250 lbs. complete with above equipment.
  • PRICE-- $2000.00 F. O. B. Los Angeles.
  • TERMS-- 25% cash with order; Balance C. O. D., or sight draft with bill of lading.

This list raises one or two questions. "Positive lubrication" implies pumped pressure lubrication, and it is not easy to see how that could be done without a pump having some moving parts. It is also difficult to see how fuel injection would have worked, if this means an injector on the cylinder head or in the inlet port.

How many engines were built and sold is currently unknown. It is recorded that it made at least one successful flight in May 1911, in a plane piloted by Charles F Walsh.

Left: Patent drawing of the Macomber Axial Engine: 1912.

This shows a big lever 37 that alters the piston stroke and so the compression ratio, while engine is running. The patent makes it clear that this was a way controlling the power output; this sounds like a pretty poor idea as it would waste a lot of fuel running inefficiently at low compression, compared with simple throttling which reduces the amount of fuel/air drawn in.

The fuel/air reached the cylinders from the right (carburettor not shown) via the hollow central shaft and the annular distributor 57. The breathing arrangements look very inefficient.

The 4-lobed cam 46 operating the valve rockers 44 can be seen; it was driven by gearing so that for each rotation of the engine it went round 7/8 of a rotation; acording to the patent this gave the correct valve timing.

From US patent 1042018, 1912

It is a bit of a mystery why axial rotary engines should have been so popular in the early days of flying; The Trebert engine of 1912 and The Nedoma-Najder of 1924 are two more examples on this page. The snags include the difficulty of getting the fuel/air mixture to the whirling cylinders, the impossibility of using anything but stub exhausts, and all sorts of potential problems with centrifugal force affecting the valvegear, the lubrication, and so on.
On the upside you got a very heavy flywheel for free (ie with no added weight) but then there was already a big propellor attached to the output shaft, and I would have thought that gave quite a bit of flywheel action.

More conventional rotaries such as the well-known Gnome engine were, for a short time, successful at powering early aircraft. Having cylinders arranged radially, they had the advantage of air-cooling of the whirling cylinders; this was an advantage an axial rotary did not enjoy. But... the heavy rotating mass gave rise to interesting gyroscopic effects. It gave the Sopwith Camel remarkable turning power- in one direction. This, in the hands of an expert, could be very useful in combat. To an inexperienced pilot it could all too easily be lethal. The gyroscopic problems, coupled with breathing restrictions due to the convoluted air-fuel delivery path, meant that rotaries fell out of use after the First World War.


THE TREBERT AXIAL ENGINE: 1912

This remarkable rotary axial aeroplane engine was produced by Henry L.F. Trebert, who had an engine works in Rochester, NY.

Left: The Trebert Axial Engine: 1912

The Trebert engine was a rotary; the cylinders and crank case revolved, while the central shaft remaine stationary. This is the only axial engine in this gallery that does not use either a wobble-plate or a swashplate. Instead each axial cylinder drove a small crankshaft, with bevel gears at the inner end of each shaft engaging with a large gear on the central output shaft; power output was taken from the crankcase end. The propeller speed was thus reduced to one-half of crankshaft speed.

The engine was covered by US patent 1215434, 1917.

From: The Airplane Engine Encyclopedia by Glen D Engle, pub 1921, Otterbein Press. Original source

The air-cooled engine had six axial cast-iron cylinders and a central rotary valve, which communicated with the small finned cylinders at the end of the main cylinders, from which the spark plugs protrude. The stationary valve had a one inlet and one outlet port on its periphery, connecting to the radial cylinders as they passed. Since the ports have to open every two revs of the crank the cylinders have to revolve at half engine speed.
Cylinder bore was 3.75in, stroke 4.25in, and the total displacement 4521cc (282 in3) It was rated at 60 HP. It used a Panhard carburetor and Mea magnetos. The weight (fully equipped) was 230lb, giving 3.83 lb/HP. Overall length was 22in, and outside diameter 15.5in.

The Trebert company also produced a barrel-type marine engine.

Left: The Trebert Axial Engine animated

In this animation the engine has been held stationary and the central shaft allowed to revolve, so the action of the multiple crankshafts is clear. In reality the engine went round but the shaft was fixed.

Another brilliant animation by Bill Todd

Left: The Trebert Axial Engine patent

The carburettor L is at extreme left and the magneto M at extreme right; W is the ignition cable, running to a fixed terminal at left, from which the spark jumped to the top of each plug as it went past.

From US patent 1215434, 1917

Left: The Trebert Axial Engine animated

Here the engine is rotating, as it did in real life. Note carburettor & stub exhaust at extreme left.

The rotary valve is just to the right of this. From


THE GNOME AXIAL ENGINE: 1911

Left: Rumours of a Gnome Axial Engine: 1911

This cutting, from "Air Eddies" the gossip column of Flight, describes what is clearly an axial engine. The design is described as a "stationary motor" which I assume means that unlike the Gnome rotary engines, the cylinders stayed still while the crankshaft revolved.

From Flight 23 Dec 1911

The Gnome company of France are best-known for making the Gnome rotary engines, in which the cylinders went round but the crankshaft stayed still; such designs had inherent problems that caused them to disappear after WW1.

I have found no other reference anywhere to such an engine. Perhaps the rumour was groundless.


THE STATAX AXIAL ENGINE: 1913

The first IC axial engine in Europe (sometimes erroneously stated to be the first ever) was a on-off prototype built by Statax-Motor of Zurich, Switzerland in 1913; it was designed by Dr. F.J.M. Hansen who apparently had links with the German air force in WW1. The engine was confiscated after the war by the British authorities and ended up in the Science Museum in London, though it is not, I believe, currently on display.

In 1914 Statax moved to London and planned a series of rotary engines, but apparently only a 5 cylinder version giving 40 HP was ever made. It was put into a Caudron G.II aeroplane to compete in the British 1914 Aerial Derby but was withdrawn. Dr Hansen produced an all-aluminum version of the engine in 1922, but it is not clear if it was produced in any quantity. Much improved versions were introduced by Statax's German division in 1929, giving 42 HP in a sleeve valve version called the 29B.

Left: The Statax Axial Engine.

The joints between the connecting rods and the plate show that it is a wobble-plate engine rather than a swash-plate type.

The carburettor and magneto can be seen at the left of the drawing. Unlike the Macomber, in the Statax the carburettor was at the "wrong end" so the fuel-air mixture had to be drawn thrugh a hollow shaft that ran most of the length of the engine.

Image kindly provided by Richard T Jones.
Original source: The Airplane Engine Encyclopedia by Glen D Angle, published in 1921 by Otterbein Press.


THE SALMSON AXIAL ENGINE: 1913

Left: Salmson Axial Engine: 1911

The Salmson engine was shown at the Paris air salon, which opened in the Grand Palais on 15th December 1911. Despite the visible fins, it was water-cooled.

From Flight 23 Dec 1911

The propellor shaft is at the right, and at the left end of the engine there appears to be some sort of cooling fan for a radiator. Just to the right of the fan is a series of levers of uncertain function- they look to be too far away from the cylinders to be valves. Below this is an auxiliary that is probably a dynamo, driven from the periphery of the fan.

Flight gave the following specs:

Nominal HP
60
Bore (mm)
75
Stroke (mm)
260
RPM
1300
Weight (kg)
100
Price (Francs)
10,000

Left: Salmson Axial Engine: 1913

This axial engine was shown at the Paris air show on 1913; it is obviously different from the 1911 version above.

Salmson had started making aero-engines in 1908, but became famous for making nine-cylinder radials, like the Salmson 9. The recently updated Wikipedia page on Salmson now describes a series of seven axial engines, running from 1908 (Model A) to 1912. (Model K) Model A was only bench-tested, and it is not clear if any of the others were flown. All were water-cooled.

From Popular Mechanics Jan 1913

The casing at right with the offset shaft emerging presumably contained reduction gearing so the engine could turn faster than the propellor. This seems rather advanced for the time.

The Salmson company survived until 1951.


THE RILEY ENGINES: 1914

Percy Riley was one of the men behind the British Riley Motor Manufacturing Company. Riley also began manufacturing aeroplane engines, becoming a key supplier in Britain's buildup for World War I. Early aero engines were of the rotary type, such as the Gnome Monosoupape, in which the whole engine rotated about a stationary crankshaft. Riley thought he could reducing the heavy whirling mass (just one disadvantage of the rotary aero-engine) and became interested in axial engines.

Left: Riley Axial Engine patent, 1914

This drawing comes from British patent 18,204 granted on the First of August, 1914. This patent covered both 2-stroke and 4-stroke designs. Both engines had eight cylinders, unlike other aero engines both radial and rotary, that almost always had an odd number of cylinders to get a good firing order.

Cutaway drawing and information from “Riley- Beyond the Blue Diamond” by David G Styles. This book is currently out of print but may be reprinted if sufficient demand exists. Email davidstyles208@yahoo.com to express your interest.

The version shown above is apparently the liquid-cooled two-stroke version; this was later intended for powering early tanks. Only four of the cylinders produced power, the other four were pumping cylinders for the 2-stroke cycle. This would more than outweight any advantage in specific power that could be gained by 2-stroke operation. The output shaft is on the left. At right is a rotary disc valve that controlled the transfer of the fuel/air mixture.

Above: Cutaway drawing of the Riley 4-stroke axial engine, 1914

This drawing shows the air-cooled, 4-stroke version of the Riley axial engine. This time all eight cylinders were power cylinders, and there appear to have been eight separate camshafts, driven by helical gears from the central shaft. The valves were operated by pushrods and rocking levers.

In a later design (Patent 11933 of August 1915) Riley reduced the number of cylinders to seven, which gave a much better firing order, and introduced compressed-air starting.

Left: Percy Riley: date unknown

It is believed that none of the axial engines planned by Percy Riley ever left the drawing board, allegedly due to lack of enthusiasm on the part of the Ministry of Munitions.

An exhibition of David Styles' drawings, some eighty-odd in number, is planned at the California Automotive Museum in Sacramento for late summer 2012. Examples of a Brooklands Riley Nine and an ERA are planned for exhibit with the drawings.


THE MICHELL AXIAL SWASHPLATE ENGINE: 1920

Above: The Australian Michell swashplate engine: 1927. Eight-cylinder static barrel swashplate-plate type

The swashplate (a seriously thick piece of metal) and part of one of the cylinders can be seen through the open hatch on top.

Anthony Michell (pronounced, but not spelt, Mitchell) is famous for inventing the Michell thrust-bearing in 1905; the unique feature of the bearing is the ring of sector-shaped pads making contact with a fixed shaft collar through a pivot or ball-joint. As the shaft rotates oil is pumped between collar and pads. The load is taken by the wedge-shaped oil film, without metal-to-metal contact, and this allows bearing pressures more than ten times greater than the previous sytem of multiple massive plane-faced collars contacting with fixed shoes. The Michell bearing made possible increases in ship size.
Learn more about it at:
Powerhouse Museum.

Left: Michell slipper pad

The piston C has a socket that which mates with the spherical back of the slipper pad B, which is rigidly fixed to the actual slipper pad A. The line of thrust passing through C and B is set slightly behind the centre of area of A, (much exaggerated in diagram) which causes the pad to tilt very slightly (about one minute of arc, according to Newton & Steeds) and forces a wedge-shaped film of oil W between the pad A and swashplate S.

From The Motor Vehicle by Newton & Steeds, pub Iliffe, date unknown but post 1921, p104.

Michell used his bearing and his knowledge of lubrication to design several swashplate engines. Between the piston and the swashplate is a hemispherical thrust block with a raised and rounded leading edge which helps the oil film get between the thrust block and the swashplate. Michell took out US patent No 1,409,057 for his engine in 1922. This has been mis-referenced as 1,404,057 in other patents referring to it, and as a result it took some tracking down.

Above: Longitudinal section of an 8-cylinder 4-piston Michell engine meant for road vehicles: 1927. Source: NACA

The hemispherical thrust-block and the sliding surface consisted of one piece of steel with a white-metal lining. Despite the ingenious thrust-block mechanism, the swashplate still required copious lubrication. A gear-type scavenge pump at the bottom of the sump pumped the oil up into a tank, from which it flowed by gravity to a pressure oil pump that delivered it at 5 psi to several nozzles that sprayed it against the swashplate and the camshaft drive.

Above: Section through piston and valves of 8-cylinder 4-piston Michell engine for road vehicles: 1927. Source: NACA

Michell established The Crankless Engine Company in 1920 to develop designs, manufacture prototypes and to try to sell licences from overseas manufacturers for large-scale production. From a Fitzroy (Australia) workshop he produced pumps, compressors, automobile engines and aero and gas engines. Serial numbers were assigned to fifty-four machines and of these at least forty-five were built, making the Michell one of the more successful axial engines. The company ceased active operations in Australia in 1928 but design and manufacture carried on in England and the USA. The principal overseas manufacturer, George Waller & Sons of Stroud, Hampshire, England, had by 1971 built 116 engines, mainly gas fuelled, for driving compressors which ranged in capacity up to 500,000 cubic feet (14,160 m³) per hour.

Above: Longitudinal section in front of swashplate, and end view, of 8-cylinder 4-piston Michell engine for road vehicles: 1927. Source: NACA

The left drawing shows the two vertical camshafts at each end of the engine, which also drove the oil and water pumps, connected by a large horizontal gear wheel at bottom centre. Quite how these were driven from the main shaft is not currently clear.

Above: Longitudinal section of a 300HP 8-cylinder 4-piston Michell engine for driving gas compressors: 1927. Source: ME

This illustration comes from a 1927 sales brochure, and in this case it shows two horizontal camshafts at each end. Michell engines of this type are believed to have been used by the Australian Gas Light Company for pipeline pressure boosting. According to one source they were built by the National Gas Engine Company of England, which presumably implies they were fuelled by the gas they were pumping. It does however raise the question of why these unconventional engines were used in an application where their main advantage- low frontal area for aeroplane use- was irrelevant.

Left: Michell engine in the Powerhouse Museum, Sydney, Australia: 1927

This engine (No 37) gave 70 HP at 750 rpm. Length 5', Width 30", Height 33". Weight 10-12 cwt.

By modern standards, not a lot of power from half a ton of engine.

Left: Michell engine in the Powerhouse Museum, Sydney, Australia engine: 1927

The same engine from the other side.

Left: Michell engine in the Powerhouse Museum, Sydney, Australia engine: 1927

A plate on the side of the engine; the function of the lever is unknown. This confirms that some Michell engines were built by the National Gas Engine Company, Ashton-under-Lyme, England.

Left: A single-ended Michell engine: 192?

This single-ended (ie not horizontally opposed) five-cylinder Michell engine is probably an early version.

It demonstrates a problem with swashplates. On the power stroke, the piston pushes the swashplate. On exhaust & compression strokes, the swashplate pushes the piston. But on the induction stroke, the swashplate has to pull the piston, and so there have to be slipper pads on both sides of the plate. and the piston has to be constructed so it hooks round the edge to hold the pad on the rear side. This no doubt why so many of these engines are horizontally opposed; doubling the number of cylinders in this way requires no more slipper pads.

The Dynacam and Michell solve the problem by having the swashplate in the center of the engine, with opposed pistons that are joined up round the edge of the swashplate, so to speak.

From The Motor Vehicle by Newton & Steeds, pub Iliffe, date unknown but post 1921, p105.

The stalk-type piston P is cast integral with the cylindrical yoke which slides in segmental guides concentric with the cylinder bore, the swashplate rim running through the annular gap between the inner and outer guides, as shown in the small drawing below. The swashplate S and the clutch member C (the presence of which seems to indicate that this engine was intended for road use) are attached to a flange on the main shaft. This shaft turns in two self-aligning ball-bearings; there is also a thrust bearing T to take the force of the power strokes on the swashplate. The valves are of the conventional overhead poppet type, actuated by rockers and ball-ended push-rods driven by the face cam F, which is driven at one quarter engine speed through idler pinion and an internal gear ring. The cylinder head at left contains concentric induction and exhaust manifolds at I and E. The auxiliaries were driven by means of spiral bevel gear, with a shaft passing radially between two of the cylinders.

Left: Single-ended Michell engine piston guides: 192?

Note the pegs attached to the slipper pads to prevent them rotating around the cylinder axis. These can be seen in their arc-shaped cavities in the main drawing above.

As with several other engines in this gallery, an odd number of cylinders are used because this gives a uniform firing interval; five cylinders gives an interval of 144 degrees. (720/5)


THE ALMEN A-4 WOBBLE-PLATE ENGINE: 1921

Left: The Almen aero engine: 1921

Eighteen horizontally-opposed cylinders in two sets of nine with a central wobble-plate; static barrel type. Water cooled. Rotary valve disc at each end of the engine.

The A-4 was the fourth experimental barrel engine built by John O Almen of Seattle, Washington State, for testing at McCook Field, Ohio. The engine project began in 1921 and by the mid-1920s, the A-4 had passed its acceptance tests. Despite this success the Almen engine never went into production, because of a growing emphasis by the US Army Air Corps on air-cooled radial engines with large frontal area. European air forces generally preferred water cooled engines.

Like other barrel engines, the Almen had a much smaller frontal area than other water-cooled engines of similar horsepower, promising reduced air resistance when installed in an aeroplane. It was rated at 425 hp but weighed only 749 pounds (a power/weight ratio of 1.76 lb/hp), a significant achievement for the time.

This example is in The National Museum of the USAF at Dayton, Ohio.

Above: The Almen aero engine

This shows the other side of the engine. The propellor mounting flanges are on the left, and the dual distributors to the right. Dual ignition was fitted, calling for 36 spark plugs.

Photograph by kind permission of Phil Callihan. See his remarkable website at http://airpower.callihan.cc/default.htm

Above: The internals of the Almen engine

Below the crankshaft is a sectioned cylinder containing one of the double-ended pistons. The cooling water pump is at bottom right.

Bore 4.25 in
Stroke 5.5 in
Displacement1404 in3 (23,007 cc)
Output 425 HP at 2000rpm
Weight 749 lb
Diameter 20in
The vital statistics of the Almen engine

Above: The Almen engine patent: US1255973 of Feb 12, 1918

The patent described an eleven-cylinder engine with a single wobble-plate at one end.

Fuel/air was fed from the carburetor 30 through the hollow shaft at the left, and entered the cylinder through ports in the rotary valve 31. The wobble plate was fitted with a gear ring 45 that engaged with a fixed gear ring 46 on the casing 11 to prevent the wobble plate from twisting round. Another gear ring 47 drove gear ring 48 on the end of the valve extension piece 49, so that the rotary valve rotated at one tenth of the speed of the main shaft but in the opposite direction. The lower cylinder is shown with a valve port 33 lined up to release the exhaust gases.
The patent was assigned to the Almen-Crosby Motors Company.


THE ALI OUTBOARD ENGINE: 1922

The ALI axial outboard engine was designed by Arvid Lind in Sweden, and reached the market in 1922. It was a popular choice for racing competition, but its general use was limited as it was expensive to produce, costing twice as much as an ordinary engine. The factory in Stockholm was closed when the inventor died 1932.

Lars Eimar owns an Ali engine bearing the number 308, so presumably at least this number were built, making it one of the more sucessful axial engines.

Left: The Ali Engine: 1922

Four-cylinder static barrel wobble-plate type.

The Ali is a two-stroke water-cooled petrol engine with four working cylinders above the wobble-plate and four scavenging pump cylinders below it, intended for use as an outboard engine for boating. The Ali has magneto ignition.

The leftmost drawing is a section through the cylinders. That to the right is a section between the cylinders.

The magneto can be seen at the right of the rightmost drawing, driven from the central shaft by spur gearing and a layshaft. An HT cable can be seen running from here to the top of the engine, where the distributor is mounted at the extreme top of the central shaft, between the spark plugs.

From NACA technical memorandum No 462, translation of Motorwagen Nov 20, 1927
Original source: Zeitschrift Des Vereines Deutscher Ingenieure (The magazine of the Association of German Engineers) p1405, 1925

Left: The Ali Engine in plan view : 1922

The U-shaped thing to the right is the ignition magneto. The rest of the grey area is believed to be the fuel tank(s).

From NACA technical memorandum No 462, translation of Motorwagen Nov 20, 1927
Original source: Zeitschrift Des Vereines Deutscher Ingenieure (The magazine of the Association of German Engineers) p1405, 1925

Left: The Ali Engine: 1922

The engine partly disassembled, showing the working pistons with sculpted tops; the nearest one has been removed to reveal the wobble plate. The scavenge pistons can be seen below the wobble plate. The carburettor is at lower right, at lower left is the tiller arm, with the kickstart mechanism below the arm pivot.

The upper part of the central shaft drives the distributor.

From the Ali instruction book; kindly provided by Lars Eimar.

Left: Ali Engine No 308, owned by Lars Eimar

The tiller functioned as a "kickstart" similar to that on a motor cycle; presumably it was pulled sharply sideways while the engine was fixed in some way. The power output with the standard carburettor was 4 HP at 1400 rpm. The metal dome on the top covered the spark-plugs and kept them dry.

This engine, and engine No 306, in the Tekniska Museet, (The Swedish National Museum of Science and Technology) are believed to be the only remaining examples of this engine.

Below: Ali Engine No 308, with the top cover removed

This exposes the sparkplugs and the central distributor. The yellow HT lead that runs up from the magneto can be seen. There appear to be two fuel tanks, each with a silver filler plug.

Photographs and information kindly provided by Lars Eimar.


THE ROLLS-ROYCE AXIAL ENGINE: 1923

Left: The Rolls-Royce engine: 1923

In 1921 Rolls-Royce had expressed an interest in an axial engine and the following year an Air Ministry contract allowed the design and build of one experimental engine. This was a seven-cylinder arrangement with a cast-iron cylinder block and cast-iron detachable cylinder heads. The bore was 3 inches, but the capacity is currently unknown. Push-rod operated overhead valves were used and a car-type carburettor fitted. Some development work was done, but by 1925 interest had waned and the project passed to Napier's. Nothing appears to be known of its development, if any, after this point.

The engine is mentioned in a well-known book "I Kept No Diary" by F.R. Banks; he says it was probably intended for motorcar use, since it was of only 3 litres cylinder capacity, which is small for an aero engine. This capacity would make the stroke 3.7" which seems a reasonable figure for the era.

Photo: Rolls-Royce Ltd


THE WISHON ROTARY-VALVE AXIAL ENGINE: 1923

Left: The Wishon engine patent: 1923

The Wishon engine was a wobble-plate design patented by Ralph Wishon in 1923. (US patent no 1,476,275) It is unusual as it sought to combine the axial engine principle, using opposed-pistons, with rotary valves. There were nine cylinders, and hence 18 pistons. The rotary valves valves were double-walled sleeves in the central section of the engine, surrounding the combustion spaces, and were driven by a complex train of epicyclic gearing.

Induction is through the left section of the hollow centre shaft.

Drawing from US patent 1,476,275

Left: The Wishon engine rotary-valve gear train

This drawing has a certain beauty to it. Gear 21 on the central shaft drives the wheels 20, which carry pinions 18 that mesh with the inner teeth 16 of wheel 14. The outer teeth 15 on this wheel drive the rotary valves 13. While the teeth on these valves are close together, they do not mesh.

On the downside, all of this complex coggery was mounted in the very centre of the engine, making it somewhat less than accessible.

But was this engine ever built? Certainly the text of the patent appears to show that Mr Wishon knew what he was talking about, but Googling "Wishon engine" yields nothing. The extra difficulties of rotary valves would probably have prevented any prototype from being successful.

Drawing from US patent 1,476,275


THE LAAGE AXIAL CAM ENGINE: 1923

Left: The Laage axial cam aero engine: 1923

The propellor hub is at the left. The engine had 8 double-ended pistons working in 16 air-cooled cylinders, pushing on the cam with rollers. The cam (with apertures in it to reduce weight) can be seen in the top centre of the engine, with a drive roller in place. The Laage engine worked on a six stroke cycle, the details of which are currently obscure; the lower drawing shows that the curve of the cam was not a simple sinusoid, and that no doubt has something to do with it.

The engine was designed in France by E Laage. Although cam drive patents go back farther than the 1920s, the Laage engine was probably the first cam-drive axial engine. According to the source, "the engine has ... disappeared" which does not exactly sound like a commercial triumph.

From NACA technical memorandum No 462, translation of Motorwagen Nov 20, 1927
Original source: Zeitschrift Des Vereines Deutscher Ingenieure (The magazine of the Association of German Engineers) p1405, 1925


THE NEDOMA-NAJDER ENGINE: 1924

Above: The American Nedoma-Najder engine: 1924. Five-cylinder rotating barrel wobble-plate type

From NACA technical memorandum No 462, translation of Motorwagen Nov 20, 1927:

The stationary hollow shaft W rests on bearings A at each end. Around it revolve five cylinders Z, and the housing G carrying flange N for the propellor hub. The housing revolves on hollow shaft W on long bushings and in ball-bearing A at the propeller end. Gear Z1 is screwed to the front end of the revolving housing, and meshes with front planetary gear Z2, which transfers its motion to geared bushing Z3, which revolves at the same speed as housing G but in the opposite direction. The bushing B is keyed to Z3, on which the wobble plate T revolves on two ball bearings, being carried along by arm C which is fixed to housing G.

Due to the opposite motions of the bushing B and wobble plate T, a complete working cycle occurs in each cylinder for each revolution of the housing. The five aluminium cylinders were of 70mm diameter and 68mm stroke, with a single cast iron sleeve valve. The pistons were also of aluminium.
The sleeve valves were actuated by five shafts each carrying a helical groove and a gear meshing with a gear ring on the stationary hollow shaft. Two of these gears also operated two separate oil pumps. The inventor claimed an engine giving 40HP at 1400rpm would weigh 74kg, giving 1.83kg/HP.

The engine was intended for use in light aircraft, where its low frontal area would have reduced drag. It was the subject of United States Patent US1492215 (29 Apr 1924)


CHARLES REDRUP & THE BRISTOL AXIAL ENGINE: 1934

Charles Benjamin Redrup (born in Wales in 1878) had a long association with axial IC engines. Before that he designed unconventional motor cycle egines, such as the rotary Barry engine, which was exhinited in 1904. Later he designed "Reactionless" rotary aircraft engines, in which the engine and crankshaft-propellor assemblies rotated in opposite directions to cancel out the troublesome gyroscopic effect. This did not live lomg or prosper because rotary engines had other inherent problems.

In the 1920s he produced wobble-plate axial engines, used to power a motor launch and a Crossley motorcar.

Left: The Redrup cam engine

At some point Redrup also designed a cam-based axial engine. This demonstration model is in the Manchester Museum of Science and Industry. Regrettably it is in a glass case so you can't turn the handle.

Author's photograph

Charles Redrup was hired by the Bristol Tramways and Carriage Company in 1931 to design the engine below, and several variants were used in Bristol buses during the late 1930s. The engine went through several versions from RR1 to RR4. RR4/2 (ie engine number 2) gave 145 HP at 2900 rpm on the test bench.

Above: The 7-litre Bristol axial engine of the mid-1930s, designed by Charles Redrup. Nine-cylinder static barrel wobble-plate type.

From Some Unusual Engines by LJK Setright, pub Mechanical Engineering Publications Ltd, 1975.

This engine was originally conceived as a power unit for buses and coaches, presumably because its compact format would allow it to be installed below the floor. Note the wobble-plate on the Z-shaped crankshaft, and one of the axial pistons and cylinders at the top. The engine had a single rotary valve to control induction and exhaust, which can be seen between the piston/cylinder and the cooling fan at the right. Some complication were required to make the wobble-plate move correctly, and the resulting vertical stabiliser arm can be seen just below the Z-crank.

  • RR1 Originally poppet valves, modified to rotary valve
  • RR2 Poppet valves
  • RR3 Rotary valve
  • RR4 Rotary valve

A change of management at the Bristol Tramways company caused development to be stopped in October 1936.

Left: The Bristol Axial Engine on a testbed.

I have not been able to determine which version of the engine this is.

From Some Unusual Engines by LJK Setright, pub Mechanical Engineering Publications Ltd, 1975.

Left: The Bristol Axial Engine animated

Showing the crank-driven vertical stabiliser arm designed to give the correct kinematics.

Animation by Bill Todd

During World War Two Redrup worked on top-secret armaments projects for the Avro Lancaster and other aircraft, including the hydraulic drive for the Vickers Type 464 bouncing bomb used in the Dam-Busters operation. He died in 1961.


THE SPAROST CAM ENGINE: 193?

Left: The Russian Sparost Cam Engine: 193?

This axial engine was developed in the 1930's. It had six enormous cylinders, driving a cam roller that fitted in between two sinusoidal ridges. In the photograph the cam roller can be seen at top centre,with its piston rod to the left of it. The Soviet Sparost was rated at 600 HP (how honestly is anyone's guess) and it was expected to reach 1200 HP by the late 1930's. As usual, the goal was a powerful engine with low frontal area.

The cutaway example shown here is in
The Soviet Air Force Museum at Monino.

Image from The Development of Aero Piston engines by Bill Gunston

Left: The Russian Sparost Cam Engine

Another view.

The cutaway example shown here is in
The Soviet Air Force Museum at Monino.

Image from The Soviet Air Force Museum


THE STERLING AXIAL DIESEL ENGINE: 1938

"The Sterling Engine Company manufactures a crankless opposed-piston barrel-type Diesel engine consisting of 4 cylinders arranged in a cross form, Fig. 223. These engines are built in various sizes:

The Sterling engines are of the two cycle type. The inclined disks (wabble plates) are virtually flywheels. Piston-type pumps attached to 4 of the 8 pistons act as compressors forcing air into the ports and combustion chambers. A rotary valve at the end of the shaft distributes the compressed air to the various cylinders. The weight of these engines varies from 13-20 lb per BHP."

The information above is taken from the von Bongart book mentioned below. Notice that it is at one point inaccurate; the rotary valve does not distribute the compressed air, but blocks the air inlet on the compression stroke.

Left: The Sterling Axial Diesel Engine

It appears that the air entrance is on the left, and the output shaft on the right, as in the diagram below.

This engine is unknown to Google, though you do get lots of hits for Stirling hot-air engines.

Source: Diesel Engines by von Bongart. Pub Van Nostrand, 1938

Left: The Sterling Axial Diesel Engine

This swashplate engine was intended to run as a two-stroke Diesel. The scavenge air to blow the exhaust gases from the opposed power cylinders in the centre was compressed by the pistons on the left.

Notice the use of a rotary valve at the air intake.

The von Bongart book is clear that these engines were actually in production, in three sizes. One can only guess at how well they suceeded. I would have thought that Diesel operation would put a lot more stress on the swashplate mechanism, due to the high compression ratio and high cylinder pressures on ignition.

The Sterling Engine Company was based in Buffalo, NY. Most of its output appears to have been conventional engines, some being for marine use. Charles Fayette Taylor, in one edition (1985) of his famous textbook The Internal Combustion Engine in Theory & Practice mentions "Opposed-piston double-swashplate engines briefly put on the market by Sterling Engine Company, Buffalo, NY". That does not sound as if they did well.


THE ALFARO AXIAL SWASHPLATE ENGINE: 1938

Left: The Alfaro swashplate engine: 1938

This is the only engine so far uncovered that has horizontally-opposed cylinders and a swash-plate at each end. This configuration doubles the number of rollers or bearing pads required compared with engines that have a single central swash-plate. Note that rollers rather than slipper-pads are used to contact the swashplates.

It was designed by the Spanish pilot Heraclio Alfaro. (who was knighted at the age of 18 by King Alfonso III for designing, building, and flying the first aeroplane in Spain) The engine was on test at MIT in 1934, where Alfaro was teaching. It had been built in Springfield, Mass, by the Indian Motorcycle Company.

According to Aerofiles, the engine had 4 cylinders and developed 155 HP from 167 cu in. (2737 cc)

Image from Charles Fayette Taylor

The engine had no valve system when operated as a two-stroke. (4-stroke operation was also envisaged) The exhaust ports were uncovered by the piston moving down, while the inlet ports, fed with compressed air from a geared blower, were likewise piston-controlled.

However, according to Wikipedia, the engine had a sleeve valve system based on a rotating cylinder head, an arrangement that never entered production on any engine. The engine was later developed further for use in the Doman helicopter by Stephen duPont, of whom more below. I have however been unable to find any evidence that it was actually flown in a Doman.

Alfaro took out US patent no 2,080,846. A photograph of the engine has now been discovered:

Left: The Alfaro swashplate engine: 1938

The trumpet air-intake at the right suggests that induction took place down the central shaft. The black thing pointing up at an angle is the distributor, while the other auxiliaries are not identified. Note the belt drive at top right.

The photo is from the book "A 1911 Spanish Pilot and MIT AeroEngineer and his 1938 AeroEngine – Upgraded for today by Stephen DuPont" ISBN 0-9777134-0-7. Stephen Dupont was the son of the president of the Indian Motorcycle Company, and worked as a student with Alfaro at MIT on this engine. Stephen is now 93 but still able to recount stories and discuss engines – he only recently quit flying his Pitts Specials at the age of 88 due to failing eyesight.

Image kindly provided by Darren Powell.

References:

Cullom, "The Alfaro Engine," Civil Aeronautical Authority Technical Development Report No. 4, Jan 1939. See also Auto. Ind., Dec. 1, 1939.


THE DYNA-CAM ENGINE: 1941

Left: The Dyna-Cam Engine

This engine has six double-ended pistons working in six cylinders, making it equivalent to a twelve-piston engine. All 12 combustion chambers are fired in a single revolution of the drive shaft. The sinusoidal cam can be seen, together with four of the six pistons and two empty cylinders.

The history of this engine is proving hard to track down, not least because access to the old dynacam.com website in internet archives is blocked; clearly this is part of The General Conspiracy.

However, the story so far: the engine appears to originate from a design by the Blazer brothers, who worked for Studebaker in 1916. They sold the rights to Karl Herrmann, Studebaker's head of engineering. He developed it over many years, taking out a patent in 1941; see US patent 2237989.

Image from The Knife and Fork Man (Biography of Charles Redrup) by Bill Fairney

Left: The Dyna-Cam Engine internals

Note that the thickness of the cam (and it is everywhere very substantial) varies, appearing thinner where it is at a more oblique angle; this is because it runs between two rollers, in each piston, that are at a fixed spacing.

The engne received FAA Type Certificate E-293 on Dec 31, 1981.

By 1961 Herrmann was eighty years old, and sold everything to Dennis Palmer, one of his employees. At this point the Dyna-Cam name was attached to it. Eventually the engine was flown for seven hours in a Piper Arrow in 1987, but Dyna-Cam fell out with Piper in 1988, and things appear to have rested there until recently.

The assets of the Dyna-Cam Engine Corp were acquired by the Axial Vector Engine Corporation in 2006. The engine now has a 92-year history, which I should think must be unique.

Image from Piston Aero Engines

Left: The Dyna-Cam Engine on test

Or is it? The mounting brackets look a bit flimsy, and it doesn't appear to be in a test cell.

Note the exhaust connections running upwards from each end of the engine.

Image from


THE WOOLER AXIAL ENGINE: 1947

This six-cylinder static-barrel wobble-plate engine was designed by John Wooler (?-1955) who was better known as a motorcycle engine designer, for aircraft use. See here for more on John Wooler. (Wikipedia link)

Left: The Wooler Axial Engine: 1947.

This engine is similar to the Bristol axial engine, but has two wobble-plates, the angled discs that can be seen at each end. They were driven by 12 opposed pistons working in six cylinders. Some confusion about this engine has arisen because LJK Setright, in his book Some Unusual Engines, in a moment of uncharacteristic imprecision describes it as a swashplate engine; however it is a wobble-plate engine, not a swashplate engine.

Note SU carburettor at the extreme right. The tall dark thing top right is probably the distributor.

Engine in The Science Museum, London

Left: The Wooler Axial Engine: 1947.

A view of the wobble-plate at the the carburettor end.

The engine is on display in the Aeroplane Gallery of The Science Museum, London. Author's photograph.


THE SEARLE ROTOCOM ENGINE: 1981

The Rotocom engine, invented by Russell Searle of Sunbury, England, was a three-cylinder four-stroke design. The pistons are rigidly fixed to a plate angled at 12 degrees to the central axis. The cylinder block is fixed to the central shaft, while the angled plate turns on a bearing, and causes the barrel-shaped pistons to move in and out of the cylinders. The barrel shape is necessary because the pistons do not slide straight in and out, but their axis moves in a small circle. Each piston has a sealing ring of Du Pont Vespel polymer, machined to a spherical surface. This was claimed to be gas-tight.

Left: The Searle Rotocom Engine: 1981

The central rotary valve is rotated at one and one-half engine speed by two belts (left of drawing) that also drive the ignition contact-breaker H.

Note the ignition electrode K that contacts each spark plug at the appropriate time. Remarkably, the spark plugs are mounted in the top of the piston rather than in the cylinder head; they don't look too accessible.

Popular Science October 1981

Lubrication was by adding oil to the petrol, which doesn't sound like a very reliable method to me. How was the oil supposed to reach some of those internal bearings?

Left: The Searle Rotocom Engine

The cycle of operations.

Popular Science October 1981

The Searle Rotocom Engine is unknown to Google apart from the Popular Science article. Apparently it was never heard of again...


TORPEDO ENGINES

The cylindrical format of the axial engine is ideally suited to fitting in torpedos, and any lack of durability in the swashing/wobbling mechanism is not a problem if the operational life is measured in minutes.

THE US NAVY MARK 37 TORPEDO was designed as as an electrically powered homing torpedo; it was introduced into the US Navy in the 1950s. See Wikipedia. It went out of use from 1972 onwards, the remaining stock being converted to Otto fuel (see below) with the same engine as the Mark 46 torpedo described below, and sold to friendly nations. The conversion not only increased speed by over 40%, but increased endurance by more than 60%, more than doubling the MK 37 run range.
The information on the Mk 37 here comes from the conversion manual, the full text of which can be found here. Time to update those old Mk 37s you have hanging around in the garage...

The engine is described as "a cam-piston" design which presumably means it uses a swashplate rather than a wobble-plate. The diagram is a bit short on detail but it looks as though the engine may use rotary valves.

The Otto fuel burns in a combustion chamber cooled by sea-water. It is not clear if water is sprayed into the hot gases to moderate their temperature and produce an added volume of steam, as is the practice in conventional "heater" torpedos.
Engine start is initiated by an igniter operated by the torpedo's auxiliary power battery. As a safety measure, a water detector, located in the tailcone water inlet, prevents engine ignition prior to submerging the torpedo in water. The igniter sets off a small propellant "starting grain" which pressurizes the combustion chamber system, starts the engine, and opens the fuel interlock valve. The seawater pump supplies cooling water to the combustion chamber and the engine. The fuel pump supplies fuel to the engine from the fuel tank, a rubberized nylon fuel cell with a capacity of 26 gallons. Engine crossover time, the transition from starter grain energy to fuel burn energy, was typically 0.8 second. Fuel consumption rates were about 1.4 gallons-per-minute in tests. The Otto fuel genertates gases at up to 3600 psi. No figures for the horsepower developed have so far been found.

Left: The propulsion sytem of a converted Mark 37 torpedo

The output power is delivered to the propellers by counter-rotating shafts; one driven by the cam and pistons and the other from the reacting housing of the engine which is free to rotate. These two shafts drive counter-rotating propellers. The engine exhaust gases, and perhaps the engine cooling water, exit via the hollow inner shaft. The rotating engine housing also drives the fuel pump and seawater pump by gearing, and apparently also powers the control-surface actuators.

From Mark 37C Torpedo System Technical Description, NVR 73-50, 1973, a Northrop document describing updating the Mk 37 torpedo to the C version.

The MK 46 cam-piston engine is essentially a constant torque output device, with the torque dependent on combustion pressure and back pressure. Fuel pump output pressure (combustion pressure) is controlled by an internal regulator that is referenced to sea pressure to maintain nearly constant shaft output torque as the sea pressure increases with depth. Constant vehicle speed is then maintained at all running depths.

THE US NAVY MARK 46 TORPEDO, designed to attack high-performance submarines, is powered by an axial IC engine. Variations of this torpedo are expected to remain in service until the year 2015, so axial engines are very much with us.
The engine runs on a monopropellant called Otto fuel II. (nothing to do with the Otto cycle) This fearful stuff is a mixture of three synthetic substances: propylene glycol dinitrate (the main component), 2-nitrodiphenylamine, and dibutyl sebacate. It is a red-orange oily liquid and a stable substance until vapourised and heated, when its three components react. The fuel itself is toxic and the products of combustion are also toxic, containing highly poisonous hydrogen cyanide gas. This monopropellant system is unlike earlier "heater" torpedos which carried a tank of highly compressed air for the combustion of paraffin.

There are some details of the Mark 46 torpedo, though not much about the engine, here: Wikipedia (external link)

Details of the Mark 46 engine have, until now, proved impossible to find, and it is not unlikely that even looking for them will land the Museum staff in Guantamo Bay. However, this video claims to show the Mark 46 Torpedo axial engine mechanism in action: Youtube video (external link) It is described as "Mk.46 ASW weapon's swashplate engine mechanism mock-up at US Naval Undersea Museum. Keyport, WA". Hard to see how many cylinders there are, but it looks like there might be nine.

The video is of poor quality but it looks as though the engine uses a wobbleplate rather than a swashplate format.

Left: The back end of a Russian torpedo

The wobbleplate engine can be seen to the left; to the left of that is a thing like a cotton-reel, presumably the heater/combustion chamber.

Image from a special issue of "National Defense" (a Russian arms & military technologies magazine) for EURONAVAL 2008, the leading international trade fair for naval defense that took place in Paris-Le-Bourget exhibition center from 27 to 31 October 2008. This was kindly brought to my attention by Pr. Théodose Lamartre.

This is an unlabelled cut-away drawing of a torpedo produced by the "Sea Thermal Engineering Research and Design Institute" of St. Petersburg (Russia) that features a wobbleplate engine in the 300-1350 kW (heavy multi-purpose torpedo) or 60-200 kW (small torpedo) power output range. The original drawing is titled "Multipurpose depth homing torpedo", but unfortunately it is not currently clear which model it is or what fuel it uses, though it is probably of the kerosene-oxygen wet-heater type.

It's nothing to do with axial engines, but here is a torpedo engine with rotary valves.


CURRENT AXIAL ENGINE DEVELOPMENTS: 2011/

THE AXIAL VECTOR ENGINE CORPORATION
Work continues on axial IC engines. Here is one company:
The Axial Vector Engine Corporation (external link)

There is an animation of their engine on Youtube (external link)

Axial have apparently acquired the assets of the Dyna-Cam Engine Corp; this news item appeared in the Portland Business Journal on Thursday, July 6, 2006:

"Dyna-Cam lawsuit settled.
Axial Vector Engine Corp. said Thursday that is has signed a settlement agreement and mutual release with Dennis Palmer and Patricia Wilks resolving the lawsuit filed by Axial over the purchase of the Dyna-Cam assets.
The agreement was signed May 16, effective June 30. The settlement involved confirmation by Palmer and Wilks of the agreements wherein Axial acquired all rights, titles, assets and interest to Dyna-Cam Engine Corp., including related Web sites and domain names."


GYROSCOPE.COM
Gyroscope.com makes model gas engines. This video shows their 4-cylinder wobbleplate engine. Their website is not explicit but it appears that the fuel is propane. The price is £1,233.75.


THE COAXE ENGINE COMPANY
The CoAxe Engine Company are developing a diesel cam-engine with contra-rotating output shafts.
Their website is here. There is a nice CAD animation to be seen.


THE DUKE ENGINE
Duke Engines are developing a valve-less 5 cylinder, 3 injector Axial internal combustion engine that claims to have zero first-order vibration, significantly reduced size and weight, very high power density and the ability to run on multiple fuels and bio-fuels.

Left: Duke axial engine: 2011

The Duke Engine is said to be already in an advanced state of development; itis claimed that multicylinder engines are operational and have been tested in Australasia and Europe, and are soon to be tested at Mahle Powertrain in the USA.


BIBLIOGRAPHY

  • Some Unusual Engines by L J K Setright, pub Mechanical Engineering Publications Ltd, 1975
  • The Knife and Fork Man (Biography of Charles Redrup) by Bill Fairney, pub Diesel Publishing, 2007

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