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General Electric T64


GE-T64

 

The General Electric T64 is a free-turbine turboshaft engine that was developed for use on helicopters. GE introduced the engine in 1964. The original engine design included technical innovations such as corrosion resistant and high-temperature coatings. The engine features a high pressure ratio, yielding low specific fuel consumption.

Later versions of the engine produce from 3,925 to 4,750 shp (2,927 to 3,542 kW).

The engine was designed to accommodate different gearboxes, or shaft drive for helicopter or turboprop fixed-wing applications. The engine could be operated between 100 degrees upward and 45 degrees downward for STOL or Helicopter applications.

MTU Aero Engines has a 30% share in the program, producing the engine's high-pressure turbine, high-pressure compressor, combustion chamber and gearbox.

Versions:

T64-GE-1
3,080 hp (2,296.76 kW)
T64-GE-2
Turbo-shaft : 2,810 hp (2,095.42 kW) at 5,200 output rpm
T64-GE-4
Turbo-prop, reduction gearbox below centre-line, airscrew brake and bolt-on control unit : 2,850 hp (2,125.24 kW) at 1,160 propeller rpm.
T64-GE-6
Turbo-shaft : 2,850 hp (2,125.24 kW) at 13,600 engine rpm.
T64-GE-7
3,925 hp (2,926.87 kW)
T64-GE-8
Turbo-prop, reduction gearbox above centre-line, airscrew brake and bolt-on control unit : 2,850 hp (2,125.24 kW) at 1,160 propeller rpm.
T64-GE-10
2,970 hp (2,214.73 kW)
T64-GE-16
3,485 hp (2,598.76 kW)
T64-GE-100
4,330 hp (3,228.88 kW)
T64-GE-412
3,695 hp (2,755.36 kW)
T64-GE-413
3,925 hp (2,926.87 kW)
T64-GE-415
4,380 hp (3,266.17 kW)
T64-GE-416
4,380 hp (3,266.17 kW)
T64-GE-419
4,750 hp (3,542.07 kW)
T64-GE-423
3,925 hp (2,926.87 kW)
CT64-820-1
2,850 hp (2,125.24 kW)
CT64-820-3
3,130 hp (2,334.04 kW)
CT64-820-4
3,130 hp (2,334.04 kW)
T64/P4D
3,400 hp (2,535.38 kW)

 

Applications:
Aeritalia G.222
de Havilland Canada DHC-5 Buffalo
Lockheed AH-56 Cheyenne
Kawasaki P-2J
LTV XC-142
ShinMaywa US-1
Sikorsky CH-53 Sea Stallion
Sikorsky CH-53E Super Stallion
Sikorsky HH-53/MH-53

 

Specifications:
T64-GE-100
Type: Turboshaft
Length: 79 in (2,007 mm)
Diameter: 20 in (508 mm)
Dry weight: 720 lb (327 kg)
Compressor: Axial, 14 stage high pressure compressor
Combustors: Annular
Turbine: Axial, 2 stage high pressure turbine, 2 stage low pressure turbine
Fuel type: Aviation kerosene
Oil system: Pressure spray / splash
Maximum power output: 4,330 hp (3,228.88 kW)
Overall pressure ratio: 14.9:1
Turbine inlet temperature: 1,180 °F (638 °C)(-1), 1,325 °F (718 °C)(-413), 1,410 °F (770 °C)(-415)
Specific fuel consumption: 0.48 lb/hp-hr (0.292 kg/kW-hr)
Power-to-weight ratio: 6.014 hp/lb (9.887 kW/kg)

 

 


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