Ishikawajima Ne-20
Clash Royale CLAN TAG#URR8PPP | Ne-20 | |
|---|---|
 | |
| Ishikawajima Ne-20 | |
| Type | Turbojet |
| Manufacturer | Ishikawajima-Harima Heavy Industries |
| First run | 1945 |
Major applications | Nakajima Kikka |
Number built | c.5 |
The Ishikawajima Ne-20 (Japanese: 石川島 ネ-20) was Japan's first turbojet engine. It was developed during World War II in parallel with the nation's first military jet, the Nakajima Kikka.
Contents
1 Design and development
2 Variants
3 Engines on display
4 Specifications (Ne-20)
4.1 General characteristics
4.2 Components
4.3 Performance
5 See also
6 References
7 External links
Design and development
The decision to manufacture this engine came about because of the unsuitability of two earlier powerplants selected for the Kikka, the Tsu-11 and the Ne-12. The Ne-20 was made possible by Imperial Japanese Navy engineer Eichi Iwaya obtaining photographs and a single cut-away drawing of the German BMW 003 engine.
Only a small number of these engines, perhaps fifty, were produced before the end of the war. Two of them were used to power the Kikka on its only flight on August 7, 1945. Only a few of the engines under construction survived. It was also planned to use the engine to power a version of the Ohka kamikaze weapon, but this was not implemented before the end of the war.
Variants
- Ne-20
- Standard production engines
- Ne-20-Kai
- Up-rated version
Engines on display
Three Ne-20s have been preserved to the present day, one at Ishikawajima-Harima's internal company museum in Tanashi, and two at the Smithsonian's National Air and Space Museum in Washington, DC.
Specifications (Ne-20)
Data from Turbojet History and Development 1930–1960 Volume 2:USSR, USA, Japan, France, Canada, Sweden, Switzerland, Italy and Hungary[1]
General characteristics
Type: Turbojet engine
Length: 2700 mm
Diameter: 620 mm
Dry weight: 470 kg
Components
Compressor: 8-stage Axial compressor
Combustors: Annular combustion chamber
Turbine: 1-stage axial turbine
Performance
Maximum thrust: 475 kgf (4.66 kN, 1,047 lbf) at 11,000 rpm
Specific fuel consumption: 1.5 lb/(lb h)
Thrust-to-weight ratio: 1.01
See also
Comparable engines
- BMW 003
- Junkers Jumo 004
Heinkel HeS 006 — later, more common designation: Heinkel HeS 30
Related lists
- List of aircraft engines
References
^ Kay, Anthony L. (2007). Turbojet History and Development 1930–1960 Volume 2:USSR, USA, Japan, France, Canada, Sweden, Switzerland, Italy and Hungary. Ramsbury: The Crowood Press. p. 258. ISBN 9781861269393.
External links
 | Wikimedia Commons has media related to Ishikawajima Ne-20. |
Kugisho Ne-20, Naval Air Technical Arsenal, Turbojet Engine -National Air and Space Museum
