General Electric YJ101
| YJ101 | |
|---|---|
| |
| YJ101 | |
| Type | Turbojet |
| National origin | United States |
| Manufacturer | General Electric Aircraft Engines |
| Major applications | Northrop YF-17 |
| Developed into | General Electric F404 |
The General Electric YJ101 was an afterburning turbojet engine, as signified by its "J" designation, in the 15,000 lbf class. It was designed for the Northrop P-530 Cobra[1] but its initial application was the Northrop YF-17 entry in the Lightweight Fighter (LWF) competition. It was subsequently developed into the widely used General Electric F404.
Design[edit]
Two essential requirements for the engine were reliability, which can be measured by the number of times a particular engine model has to be shutdown during flight (in-flight shut-down rate), and handling, which means stall-free operation throughout the flight envelope together with allowing the pilot to make unrestricted throttle movements anywhere between idle and maximum afterburner.[2]
The engine used continuous bypass bleed from the compressor to cool the afterburner liner and nozzle. The bypass air was not mixed with hot air from the turbine[3] as the afterburner was a simple turbojet style with no requirement for intentional mixing of the bypass flow with the turbine exhaust.[4] However, mixing is an important requirement for turbofan engines.
General Electric chose to describe the engine differently depending on circumstance. To emphasize simplicity it was a "leaky turbojet". For advanced technology it was "the world's first self-cooled turbojet".[5] This referred to using the compressor bypass air to cool the afterburner instead of using much hotter turbine exhaust gas.
Applications[edit]
Specifications (YJ101)[edit]
Data from Jane's All The World's Aircraft 1975-76 [6]
General characteristics
- Type: Two-shaft afterburning turbojet with continuous bypass bleed
- Length: 145 inches (3,683 mm)
- Diameter: 32.5 inches (826 mm)
- Dry weight: 1,900 pounds (862 kg) (approx)
Components
- Compressor: Three-stage axial LP, seven-stage axial HP
- Combustors: Annular
- Turbine: Single-stage LP, single-stage HP
Performance
- Maximum thrust: 15,000 pounds (6,804 kg) class
- Overall pressure ratio: In excess of 20:1
- Bypass ratio: 0.25:1
- Thrust-to-weight ratio: 7.9:1
See also[edit]
Related development
Related lists
References[edit]
- ^ Jane's All The World's Aircraft 1975-76, ISBN 0 531 03250 7 p.747
- ^ Flight International, 14 April 1984, F404: Fighter pilot's engine, p.1021
- ^ Flight International, 21 August 1978, "F-18: US Navy Air Combat Fighter", p.262
- ^ Patierno, J. (1974). "YF-17 design concepts". 6th Aircraft Design,Flight Test and Operations Meeting. American Institute of Aeronautics and Astronautics. doi:10.2514/6.1974-936.
- ^ The Lightweight Fighter Program:A Successful Approach to Fighter Technology Transition, Aronstein and Piccirillo 1996, ISBN 1 56347 193 0, p.42
- ^ Jane's All The World's Aircraft 1975-76, ISBN 0 531 03250 7 p.748
- Spick, Mike (2000). The Great Book of Modern Warplanes. Osceola, WI: MBI Publishing Company. ISBN 0-7603-0893-4.
External links[edit]
