General Electric T64

From Wikipedia, the free encyclopedia
Jump to: navigation, search
T64
Helicopter engine CH-53G.jpg
A T64-GE-7 on a CH-53G
Type Turboshaft
National origin United States
Manufacturer GE Aviation
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 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]

Variants[edit]

T64-GE-1
3,080 hp (2,300 kW)
T64-GE-2
Turbo-shaft: 2,810 hp (2,100 kW) at 5,200 rpm output[4]
T64-GE-4
Turbo-prop, reduction gearbox below centerline, airscrew brake and bolt-on control unit: 2,850 hp (2,130 kW) at 1,160 propeller rpm.[4]
T64-GE-6
Turbo-shaft: 2,850 hp (2,130 kW) at 13,600 engine rpm.[4]
T64-GE-7
3,925 hp (2,927 kW)
T64-GE-7A
3,936 hp (2,935 kW)
T64-GE-8
Turbo-prop, reduction gearbox above centerline, airscrew brake and bolt-on control unit: 2,850 hp (2,130 kW) at 1,160 propeller rpm.[4]
T64-GE-10
2,970 hp (2,210 kW)
T64-GE-16
3,485 hp (2,599 kW)
T64-GE-100
4,330 hp (3,230 kW)
T64-GE-412
3,695 hp (2,755 kW)
T64-GE-413
3,925 hp (2,927 kW)
T64-GE-413A
3,936 hp (2,935 kW)
T64-GE-415
4,380 hp (3,270 kW)
T64-GE-416
4,380 hp (3,270 kW) - three on Sikorsky CH-53E Super Stallion[5]
T64-GE-419
4,750 hp (3,540 kW)
T64-GE-423
3,925 hp (2,927 kW)
T64-P4D
Turboprop 3,400 hp (2,500 kW)
CT64-820-1
2,850 hp (2,130 kW)
CT64-820-2
CT64-820-3
3,130 hp (2,330 kW)
CT64-820-4
3,133 hp (2,336 kW)
T64/P4D
3,400 hp (2,500 kW)[6]

Sources: Vectorsite,[7]

Applications[edit]

Specifications (T64-GE-100)[edit]

Data from Gas Turbine Engines[8]

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

Notes[edit]

  1. ^ GE T64 page, GlobalSecurity.org, accessed October 29, 2007.
  2. ^ T64 turboshaft page, GE Aviation, accessed October 29, 2007.
  3. ^ Flying Magazine: 68. May 1962. 
  4. ^ a b c d Taylor, John W.R. FRHistS. ARAeS (1962). Jane's All the World's Aircraft 1962-63. London: Sampson, Low, Marston & Co Ltd. 
  5. ^ "About the GE T64" BGA-aeroweb, May 17, 2012. Accessed: April 10, 2014.
  6. ^ John W.R. Taylor, ed. (1988). Jane's All the World's Aircraft 1988-89. London: Jane's Information Group. ISBN 0 7106 0867 5. 
  7. ^ Sikorsky Giant Helicopters: S-64, S-65, & S-80. Vectorsite, 1 March 2008.
  8. ^ Gas Turbine Engines. Aviation Week & Space Technology Source Book 2009. p. 118.
  9. ^ "The history of North American small gas turbine aircraft engines". 

References[edit]

  • Taylor, John W.R. FRHistS. ARAeS (1962). Jane's All the World's Aircraft 1962-63. London: Sampson, Low, Marston & Co Ltd. 

External links[edit]