| 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 shut down during flight (in-flight shutdown rate), and handling. This means stall-free operation throughout the entire flight envelope, 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 the circumstances. 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] NASA Technical Report[7]
General characteristics
- Type: Two-shaft afterburning turbojet with continuous bypass bleed
- Length: 145 inches (3,683 mm)
- Diameter: 32.5 inches (826 mm), 26.32 inches (669 mm) inlet[8]
- Dry weight: 1,870 pounds (848 kg)[9] (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) wet thrust class
- 9,924 pounds (4,501 kg) military thrust
- Overall pressure ratio: 24,[10] LPC: 3.9[11]
- Bypass ratio: 0.25:1
- Air mass flow: 127 pounds per second (57.6 kg/s)
- Turbine inlet temperature: 2,445–2,465 °F (1,341–1,352 °C)[12]
- 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
- ^ "Design definition study of NASA/Navy lift/cruise fan V/STOL aircraft. Volume 1: Summary report of Navy multimission aircraft". NASA Technical Reports Server. p. 40.
- ^ "Boron/aluminum fan blades for SCAR engines". NASA Technical Reports Server. p. 106.
- ^ "YJ101-YF-17 Aircraft Prototype Development Summary". DTIC. p. 28.
- ^ "Conceptual design studies of lift/cruise fans for military transports". NASA Technical Reports Server. p. 7.
- ^ "YJ101-YF-17 Aircraft Prototype Development Summary". DTIC. p. 17.
- ^ "YJ101-YF-17 Aircraft Prototype Development Summary". DTIC. p. 31.
- Spick, Mike (2000). The Great Book of Modern Warplanes. Osceola, WI: MBI Publishing Company. ISBN 0-7603-0893-4.
External links
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