Chrysler IV-2220

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Chrysler IV-2220, perhaps a display model (note the cutaway prop). The length of the engine is evident, made even longer by the large accessories section on the left.

The XIV-2220 (XI-2220 from 1944) was an experimental 2,500 hp liquid-cooled inverted-V-16 Aircraft engine designed by Chrysler starting in 1940. Although several aircraft designs had considered using it, by the time it was ready for use in 1945 the war was already over. Only a few engines were built during the program, and it retained its 'X' designation the entire time as the XIV-2220, or simply XI-2220 in Chrysler terminology. The IV-2220 is historically important as it was Chrysler's first Hemi, a design that would re-appear for many years later and is now a Chrysler Trademark.

Contents

Original Design


Chrysler had apparently been carrying out paper studies of a very large engine for a brief period starting in May 1940 and decided to present their work to the United States Army Air Corps. They proposed a large engine to provide 2,500 hp initially, with room for growth upwards. Instead of using advanced features such as Sleeve valve for improved RPM, they instead decided to use a larger number of "normal sized" cylinders in a V-16 arrangement. The Army was interested, and sent them a development contract tender on June 22, 1940, to which Chrysler responded on July 2.

The extremely long profile of the new design meant that the crankshaft would be highly loaded if power was taken off at the propeller end. Chrysler's solution to this problem was unique; power was instead taken from the middle of the engine, placing the propeller reduction gear in a gap between two V-8 cylinder banks and sending power to the front of the engine via a long extension shaft running below the crankshaft. Additionally many of the accessories were driven off the drive shaft instead of the crank shaft. This solution also raised the weight of the engine by the amount of the shaft, but it was apparently a price worth paying.

A single overhead cam drove the two-per-cylinder Poppet valve, arranged at an angle to the piston in a hemi-spherical cylinder head, with the spark plug arranged between the valves. This arrangement allowed for "cross-flow" scavenging of the charge, and had been used on various race and performance car engines for some time. The hemi is actually less efficient than the design being used in most engines of the era, the Penta engine, which improved airflow by allowing three or four valves per cylinder.

Problems and Advantages


One early problem for the design was the lack of high-strength Aluminum alloys; the original supplier, Alcoa, was able to deliver only half the required strength. Chrysler was able to address this through much improved production-line Quality control, but the engine was nevertheless built with considerably more distance between the cylinders than normal, making the engine relatively long. This was not helped by the "gap" holding the propeller gearing in the middle of the engine, or the large accessories section at the end. The IV-2220 was comparatively huge; the Rolls-Royce Griffon of about the same displacement was 77 inches long, while the IV-2220 was 122.

Weight was not greatly affected, however, and the Power-to-weight ratio was certainly competitive at 1.03 hp/lb. Some of this was no doubt due to the use of a Turbocharger in addition to a Supercharger for more continuous boost and less power draw on the engine. Turborchargers are generally "free", powered not by the engine directly as in a supercharger, but by otherwise wasted exhaust energy. The IV-2220 also included a fairly advanced liquid-cooled Intercooler between the turbocharger and supercharger, and an Aftercooler behind the supercharger as well. This complex arrangement resulted in excellent altitude performance, keeping maximum rated power all the way to 25,000 ft.

The engine first flew on 26 July 1945, mounted on a converted P-47D-15-RE which was intended to serve as the prototype for the new P-47H series using this engine. A second example followed, but the war was already over and the need for a new engine in the Jet age was gone. The only other design to select it was one of the many versions of the storied Curtiss P-60 in 1942, but the engine was so delayed that the P-60 had long moved onto other designs.

Specifications (XIV-2220-11)


General characteristics
  • Type: 16-cylinder turbosupercharged liquid-cooled 60° V16 aircraft piston engine
  • Bore: 5.8 in (147.32 mm)
  • Stroke: 5.25 in (133.35 mm)
  • Displacement: 2,219.35 cu in (36.37 L)
  • Length: 122 in (3,100 mm)
  • Dry weight: 2,440 lb (1,015 kg)
<h3>Components
  • Valvetrain: Single Overhead camshaft actuating two valves per cylinder
  • Supercharger: With Intercooler
  • Turbocharger: With water-to-air Intercooler
  • Cooling system: Liquid-cooled
<h3>Performance
  • Power output:
    • 2,500 hp (1,865 kW) at 3,400 rpm for takeoff (bmep=262.4psi)
    • 2,500 hp (1,865 kW) at 25,000 ft METO
    • 2,150 hp (1,605 kW) at 3,200 rpm normal rating (bmep=239.8psi)
    • 1,450 hp (1,080 kW) at 2,800 rpm cruise (bmep=184.8psi)
  • Specific power: 1.13 hp/cu in (51.2 kW/L)
  • Brake specific fuel consumption:
    • 0.54 lb/(hp·h) (0.33 kg/(kW·h)) METO
    • 0.43 lb/(hp·h) (0.26 kg/(kW·h)) normal rating
  • Power-to-weight ratio: 1.02 hp/lb (1.84 kW/kg)

Note: some sources claim the engine delivered 2,300 hp in testing, and that 2,500 was the design power. Chrysler documents specify 2,500 hp, the figure used here.

References

  • Correspondence with Kimble D. McCutcheon, who also provided a Chrysler specification sheet used for the figures above.
  • Gunston, Bill (2006). World Encyclopedia of Aero Engines, 5th Edition. Phoenix Mill, Gloucestershire, England, UK: Sutton Publishing Limited. p. 79. ISBN 0-7509-4479-X. 

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