Engineering:Teledyne CAE J69
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Short description: Turbojet aircraft engine series
| J69 / J100 | |
|---|---|
| |
| Teledyne-Continental J69 turbojet at the Museum of Aviation, Warner Robins, Georgia | |
| Type | Turbojet |
| National origin | France /United States |
| Manufacturer | Continental Aviation and Engineering / Teledyne CAE |
| Major applications | BQM-34 Firebee T-37 Tweet Ryan Model 147 |
| Developed from | Turbomeca Marboré |
The Teledyne CAE J69 was a small turbojet engine originally produced by Continental Aviation and Engineering (CAE) under license from Turbomeca. The J69 was a development of the Turbomeca Marboré II. It powered a number of United States drones, missiles and small aircraft. The engine was later produced by Teledyne CAE. The J69 was also developed into the Teledyne CAE J100 turbojet optimized for operation at higher altitudes.
Variants
Data from: Aircraft engines of the World 1957[1]
- J69-T-1
- (Marboré I) 660 lbf (2.9 kN) at 23,000 rpm.[2]
- J69-T-3
- 880 lbf (3.9 kN) at 22,500 rpm for take-off.[2]
- J69-T-6
- J69-T-9
- J69-T-17
- J69-T-19
- J69-T-19A
- J69-T-19B
- J69-T-23
- J69-T-25
- J69-T-27
- J69-T-29
- J69-T-31
- J69-T-33
- J69-T-39
- J69-T-41
- J69-T-41A
- J69-T-406
- J100-CA-100
- 2,800 lbf (12 kN) thrust
- CJ69-1025
- 1,025 lbf (4.56 kN)
- CJ69-1400
- 1,400 lbf (6.2 kN) lb thrust
- Model 352
- Model 352A
- Model 352-5a
- (CJ69-T-1025) 1,025 lbf (4.56 kN) thrust
- Model 354-12
- (J69-T-27) 1,150 lbf (5.1 kN) thrust
- Model 356-7A
- (J69-T-29) 1,705 lbf (7.58 kN) thrust
- Model 356-7D
- (J69-T-29) 1,700 lbf (7.6 kN) thrust
- Model 356-8
- (J69-T-31) 1,025 lbf (4.56 kN) thrust
- Model 356-11
- (J69-T-33) 1,025 lbf (4.56 kN) thrust
- Model 356-16
- Model 356-24
- Model 356-27B
- Model 356-29A
- (J69-T-41A)
Applications
The J69 of a TT-1 Pinto
- J69
- Avro Canada VZ-9 Avrocar
- Cessna T-37 Tweet
- Radioplane Q-1
- Ryan BQM-34 Firebee
- Temco TT Pinto
- J100
Specifications (Marboré IIC)
Data from FAA Type Certificate Data Sheet[3]
General characteristics
- Type: turbojet
- Length: 61.7 in (1,570 mm)
- Diameter: 24.9 in (630 mm)
- Dry weight: 358 lb (162 kg)
Components
- Compressor: single stage centrifugal
- Combustors: single annular combustion chamber
- Turbine: single stage
Performance
- Maximum thrust: 880 lbf (3.9 kN) at 22,600 rpm
- Turbine inlet temperature: 650 °C (1,202 °F)
- Thrust-to-weight ratio: 2.458
See also
Related development
Related lists
References
- ↑ Wilkinson, Paul H. (1957). Aircraft engines of the World 1957 (15th ed.). London: Sir Isaac Pitman & Sons Ltd.. pp. 74–75.
- ↑ 2.0 2.1 Wilkinson, Paul H. (1953). Aircraft engines of the World 1953 (11th ed.). London: Sir Isaac Pitman & Sons Ltd.. pp. 80–81.
- ↑ FAA Type Certificate Data Sheet Retrieved: 2 November 2008
- Gunston, Bill (2006). World Encyclopedia of Aero Engines, 5th Edition. Phoenix Mill, Gloucestershire, England, UK: Sutton Publishing Limited. pp. 79. ISBN 0-7509-4479-X.
- Leyes II, Richard A.; William A. Fleming (1999). The History of North American Small Gas Turbine Aircraft Engines. Washington, DC: Smithsonian Institution. ISBN 1-56347-332-1.
External links
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