• Source: General Electric J85

The General Electric J85 is a small single-shaft turbojet engine. Military versions produce up to 3,500 lbf (16 kN) of thrust dry; afterburning variants can reach up to 5,000 lbf (22 kN). The engine, depending upon additional equipment and specific model, weighs from 300 to 500 pounds (140 to 230 kg). It is one of GE's most successful and longest in service military jet engines, with the civilian versions having logged over 16.5 million hours of operation. The United States Air Force plans to continue using the J85 in aircraft through 2040. Civilian models, known as the CJ610, are similar but supplied without an afterburner and are identical to non-afterburning J85 variants, while the CF700 adds a rear-mounted fan for improved fuel economy.




Design and development


The J85 was originally designed to power a large decoy missile, the McDonnell ADM-20 Quail. The Quail was designed to be released from a B-52 Stratofortress in-flight and fly for long distances in formation with the launch aircraft, multiplying the number of targets facing the SA-2 surface-to-air missile operators on the ground. This mission demanded a small engine that could nevertheless provide enough power to keep up with the jet bomber. Like the similar Armstrong Siddeley Viper being built in the UK, the engine on a Quail drone had no need to last for extended periods of time, so therefore could be built of low-quality materials.
The fit was a success on the Quail, but again like the Viper it was later built with normal grade materials and subsequently used to power small jet aircraft, including the Northrop T-38 Talon, Northrop F-5, Canadair CT-114 Tutor, and Cessna A-37 Dragonfly light attack aircraft. More recently, J85s have powered the Scaled Composites White Knight aircraft, the carrier for the Scaled Composites SpaceShipOne spacecraft, and the Me 262 Project.
The basic engine design is quite small, about 17.7 inches (45 cm) in diameter, and 45.4 inches (115 cm) long. It features an eight-stage axial-flow compressor powered by two turbine stages, and is capable of generating up to 2,100 lbf (9.3 kN) of dry thrust, or more with an afterburner. At full throttle at sea level, this engine, without afterburner, consumes approximately 400 US gallons (1,500 L) of fuel per hour. At cruise altitude and power, it consumes approximately 100 US gal (380 L) per hour.
Several variants were produced.
The most advanced variant in the J85 series is the J85-21 model designed specifically for the F-5E/F during its development process.
The J85-21 design replaces AM 355 chromium nickel molybdenum stainless steel alloy, used by previous J85 models for compressor rotors and blades, with a titanium alloy. Its inlet diameter was increased from 17.7 in (45 cm) to 20.8 in (53 cm), and it included an added stage ahead of the base 8-stage compressor for a total of 9 stages. Its multiple disk rotors were replaced with a single-spool rotor, thus improving dry thrust to 3,600 lbf (16 kN) and wet thrust to 5,000 lbf (22 kN) while reducing mechanical complexity along with the weight gain of the J85-21 model.
More than 12,000 J85 engines had been built by the time production ended in 1988.




= Iranian reverse engineering

=

The Iranian Ministry of Defense constructed a new engine based on the General Electric J85-GE-21B named "OWJ" and presented it at a defense exhibition on 22 August 2016.
The Owj engine has been used in several Iranian products like Kowsar, Saeghe and Azarakhsh fighter jets or Yasin training jet.




Variants



J85-GE-1
1,900–2,100 lbf (8.5–9.3 kN) thrust
J85-GE-2
2,850 lbf (12.7 kN) thrust
J85-GE-3
2,450 lbf (10.9 kN) thrust
J85-GE-4
2,950 lbf (13.1 kN) thrust
J85-GE-4A
2,950 lbf (13.1 kN) thrust
J85-GE-5
2,680 lbf (11.9 kN) dry thrust; 3,850 lbf (17.1 kN) afterburning thrust
J85-GE-5A
2,680 lbf (11.9 kN) dry thrust; 3,850 lbf (17.1 kN) afterburning thrust
J85-GE-7
2,450 lbf (10.9 kN) thrust
J85-GE-12
2,400 lbf (11 kN) thrust
J85-GE-13
2,720 lbf (12.1 kN), dry thrust; 4,080 lbf (18.1 kN) afterburning thrust
J85-GE-13A
License built for the Fiat G.91Y, 2,720 lbf (12.1 kN), dry thrust; 4,080 lbf (18.1 kN) afterburning thrust
J85-GE-15
2,925 lbf (13.01 kN) dry thrust; 4,300 lbf (19 kN) afterburning thrust
J85-CAN-15
Orenda manufactured J85-GE-15 for the Canadair CF-116, 2,925 lbf (13.01 kN) dry thrust; 4,300 lbf (19 kN) afterburning thrust
J85-GE-17
2,850 lbf (12.7 kN) thrust
J85-GE-17A
2,850 lbf (12.7 kN) thrust
J85-GE-17B
2,850 lbf (12.7 kN) thrust
J85-GE-17C
2,850 lbf (12.7 kN) thrust
J85-GE-19
3,015 lbf (13.41 kN) dry thrust
J85-GE-21A
3,500 lbf (16 kN) dry thrust; 5,000 lbf (22 kN) afterburning thrust.
J85-GE-J1A
3,500 lbf (16 kN) dry thrust; 5,000 lbf (22 kN) afterburning thrust
J85-GE-J2
2,850 lbf (12.7 kN) thrust.
J85-GE-J4
2,950 lbf (13.1 kN) thrust.
J85-CAN-40
Manufactured by Orenda for the Canadair CT-114 Tutor, 2,650 lbf (11.8 kN) thrust
J85-GE-100
2,450 lbf (10.9 kN) thrust




Applications



Bell X-14A/B
Boom XB-1 demonstrator
Canadair CT-114 Tutor
Canadair CF-5
Cessna A-37 Dragonfly
HESA Yasin (without afterburner)
HESA Kowsar (with afterburner)
Fairchild C-123 Provider
Fairchild AC-119K
Fiat G.91Y
Lockheed Have Blue
McDonnell ADM-20 Quail decoy missile
North American Rockwell OV-10 Bronco - OV-10B(Z) target tug variant, the engine in addition to its turboprops
North American T-2 Buckeye
Northrop F-5
Northrop T-38 Talon
Republic AP-100
Ryan MQM-34D Mod II target drone
Ryan XV-5 Vertifan
Saab 105Ö
Scaled Composites White Knight




= Other

=
American Challenge water speed record jet-powered boat - Two J85-GE-21s
Hermeus experimental turbine-based combined cycle "Chimera" turboramjet engine - J85-21 turbojet core




Specifications (J85-GE-21)



Data from



General characteristics

Type: afterburning turbojet engine
Length: 112.5 in (286 cm)
Diameter: 20.8 in (53 cm) inlet
Dry weight: 684 lb (310 kg)



Components

Compressor: single-spool 9 axial stages
Combustors: annular
Turbine: 2 stages
Fuel type: jet fuel



Performance

Maximum thrust: 3,600 lbf (16 kN) dry thrust / 5,000 lbf (22 kN) afterburner thrust
Overall pressure ratio: 8.3:1 (J85-21 A~C model)
Air mass flow: 53 lb (24 kg) per second
Turbine inlet temperature: 1,790 °F (980 °C)
Specific fuel consumption: 1.24 lb/(lbf⋅h) or 35 g/(kN⋅s) dry thrust / 2.13 lb/(lbf⋅h) or 60 g/(kN⋅s) afterburner thrust
Thrust-to-weight ratio: 5.25 dry / 7.3 afterburner




See also



Related development

General Electric CJ610
General Electric CF700

Comparable engines

Armstrong Siddeley Viper
Continental J69
Fairchild J83
Rolls-Royce Soar
Related lists

List of aircraft engines




References



Gunston, Bill (2006). World Encyclopedia of Aero Engines, 5th Edition. Phoenix Mill, Gloucestershire, England, UK: Sutton Publishing Limited. ISBN 0-7509-4479-X.




External links



GE J85 product page
J85 picture
"G.E.'s Small Turbojet" a 1959 Flight article

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