General Electric T64
From Wikipedia, the free encyclopedia
| Type | Turboshaft |
|---|---|
| National origin | United States |
| Manufacturer | GE Aviation |
| Major applications | AH-56 Cheyenne Alenia G.222 DHC-5 Buffalo CH-53 Sea Stallion CH-53E Super Stallion |
|
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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.[1] 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).[2]
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.[3]
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[4]
- 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.[4]
- T64-GE-6
- Turbo-shaft : 2,850 hp (2,125.24 kW) at 13,600 engine rpm.[4]
- 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.[4]
- 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)
Sources: Vectorsite,[5]
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)
Data from Gas Turbine Engines[6]
General characteristics
- Type: Turboshaft
- Length: 79 in (2,007 mm)
- Diameter: 20 in (508 mm)
- Dry weight: 720 lb (327 kg)
Components
- 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
Performance
- 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)[7]
- 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)
Notes
- ↑ GE T64 page, GlobalSecurity.org, accessed October 29, 2007.
- ↑ T64 turboshaft page, GE Aviation, accessed October 29, 2007.
- ↑ Flying Magazine: 68. May 1962.
- ↑ 4.0 4.1 4.2 4.3 Taylor, John W.R. FRHistS. ARAeS (1962). Jane's All the World's Aircraft 1962-63. London: Sampson, Low, Marston & Co Ltd.
- ↑ Sikorsky Giant Helicopters: S-64, S-65, & S-80. Vectorsite, 1 March 2008.
- ↑ Gas Turbine Engines. Aviation Week & Space Technology Source Book 2009. p. 118.
- ↑ "The history of North American small gas turbine aircraft engines".
References
- Taylor, John W.R. FRHistS. ARAeS (1962). Jane's All the World's Aircraft 1962-63. London: Sampson, Low, Marston & Co Ltd.
External links
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