General Electric T64
From Wikipedia, the free encyclopedia
| T64 | |
|---|---|
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| A T64-GE-7 on a CH-53G | |
| Type | Turboshaft |
| National origin | United States |
| Manufacturer | GE Aviation |
| Major applications | AH-56 Cheyenne Alenia G.222 CH-53 Sea Stallion CH-53E Super Stallion |
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 is also used in several turboprop fixed-wing 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.
Contents |
[edit] Versions
Helicopter versions:
- T64-GE-1 - 3,080 shp (2,300 kW)
- T64-GE-6 - 2,850 shp (2,125 kW)
- T64-GE-7 - 3,925 shp (2,930 kW)
- T64-GE-16 - 3,485 shp (2,600 kW)
- T64-GE-412 - 3,695 shp (2,755 kW)
- T64-GE-413 - 3,925 shp (2,930 kW)
- T64-GE-415 - 4,380 shp (3,265 kW)
- T64-GE-416 - 4,380 shp (3,266 kW)
- T64-GE-419 - 4,750 shp (3,543 kW)
- T64-GE-423 - 3,925 shp (2,927 kW)
Turboprop versions:
- T64-GE-10 - 2,970 shp (2,214 kW)
- CT64-820-1 - 2,850 shp (2,125 kW)
- CT64-820-3/-4 - 3130 shp (2,400 kW)
- T64/P4D - 3400 shp (2,600 kW)
Sources: Vectorsite,[3] Aviastar.org[4]
[edit] 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
[edit] Specifications (T64-GE-100)
Data from [5]
General characteristics
- Type: Turboshaft
- Length: 79 in (201 cm)
- Diameter: 20 in (51 cm)
- Dry weight: 720 lbf (327 kg)
Components
- Compressor: Axial, 14 stage high pressure compressor
- Combustors: Annular
- Turbine: Axial, 2 stage high pressure turbine, 2 stage low pressure turbine
Performance
- Maximum power output: 4,330 shp
- Overall pressure ratio: 14.9:1
- Turbine inlet temperature: 1180F(-1), 1325F(-413), 1410F(-415)[6]
- Specific fuel consumption: 0.48 lb/lbf-hr
- Power-to-weight ratio:
[edit] References
- ^ GE T64 page, GlobalSecurity.org, accessed October 29, 2007.
- ^ T64 turboshaft page, GE Aviation, accessed October 29, 2007.
- ^ Sikorsky Giant Helicopters: S-64, S-65, & S-80. Vectorsite, 1 March 2008.
- ^ Sikorsky S-65 / CH-53 Sea Stallion. Aviastar.org.
- ^ Gas Turbine Engines. Aviation Week & Space Technology Source Book 2009. p 118.
- ^ "The history of North American small gas turbine aircraft engines". http://books.google.com/books?id=V0SnFt8JGokC&pg=PA301&lpg=PA301&dq=T64+engine+inlet+temperature&source=bl&ots=N4vW7DoUrL&sig=C792YVytQjmvCQAm-sGG1MMV8jo&hl=en&sa=X&ei=qvfsTrCtCqOpiQKlp83XBA&ved=0CCEQ6AEwAA#v=onepage&q=T64%20engine%20inlet%20temperature&f=false.
[edit] External links
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