| T64 | |
|---|---|
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| |
| Cutaway of a T64-IHI-10E (in turboprop configuration) | |
| Type | Turboshaft |
| National origin | United States |
| Manufacturer | GE Aviation |
| First run | (T64-GE-2) March 1959 |
| Major applications | Lockheed AH-56 Cheyenne Alenia G.222 de Havilland Canada DHC-5 Buffalo Sikorsky CH-53 Sea Stallion Sikorsky CH-53E Super Stallion |
The General Electric T64 is a free-turbine turboshaft engine that was originally developed for use on helicopters, but which was later used on fixed-wing aircraft as well. General Electric 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 overall pressure ratio, yielding a low specific fuel consumption for its time.[2] Although the compressor is all-axial, like the earlier General Electric T58, the power turbine shaft is coaxial with the HP shaft and delivers power to the front of the engine, not rearwards. Fourteen compressor stages are required to deliver the required overall pressure ratio. Compressor handling is facilitated by 4 rows of variable stators. Unlike the T58, the power turbine has 2 stages.
Later versions of the engine produce from 3,925 to 4,750 shp (2,927 to 3,542 kW).[3]
The engine was designed to accommodate different gearboxes or shaft drives, for helicopter or turboprop fixed-wing applications. The engine could be operated continuously at angles between 100 degrees upward and 45 degrees downward for STOL or helicopter applications.[4]
- ^ GE T64 page, GlobalSecurity.org, accessed October 29, 2007.
- ^ Gunston, W.T. (January 13, 1961). "T64: Design philosophy behind GE's new shaft turbine". Flight. pp. 63–64. Archived from the original on January 11, 2019.
- ^ T64 turboshaft page Archived 2011-06-20 at the Wayback Machine, GE Aviation, accessed October 29, 2007.
- ^ "General Electric T-64". Newsreel. Flying. May 1962. p. 68.