Teledyne CAE J69

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 U.S. 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.

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

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

• Ryan Model 147T

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

• Turbomeca Marboré

Related lists

• List of aircraft engines

References

1. Wilkinson, Paul H. (1957). Aircraft engines of the World 1957 (15th ed.). London: Sir Isaac Pitman & Sons Ltd. pp. 74–75.
2. Wilkinson, Paul H. (1953). Aircraft engines of the World 1953 (11th ed.). London: Sir Isaac Pitman & Sons Ltd. pp. 80–81.
3. 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. p. 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

• Aircraft fitted with MARBORE II or VI