General Electric GE38
Gas turbine
From Wikipedia, the free encyclopedia
The General Electric GE38 is a gas turbine developed by GE Aviation for turboprop and turboshaft applications. It powers the Sikorsky CH-53K King Stallion as the T408.[1]
| GE38 / T408 | |
|---|---|
The T408 on a CH-53K King Stallion | |
| Type | Turboshaft |
| National origin | United States |
| Manufacturer | GE Aviation |
| First run | December 26, 1989 |
| Major applications | Sikorsky CH-53K King Stallion (T408) |
| Developed into | CFE CFE738 |
Design and development
The GE27 was developed in the early 1980s under the "Modern Technology Demonstrator Engines" (MTDE) program sponsored by the United States Army Aviation Applied Technology Directorate.[2] Sporting a 22:1 pressure ratio, which was a record for single-spool compressors at the time, the GE27[3] was GE's unsuccessful submission to power the Bell Boeing V-22 Osprey tiltrotor aircraft. The GE27 also had a compressor air flow of 27–28 pounds per second (12–13 kg/s) and a turbine temperature of 2,400–2,500 °F (1,320–1,370 °C; 2,860–2,960 °R; 1,590–1,640 K).[2] The GE27 first ran in late 1984, but it unexpectedly lost the V-22 engine competition to the Allison 501-M80C, which was not a participant in the MTDE program.[4]
In the late 1980s, GE used the GE27 as the basis for the commercial development of turboshafts, turboprops, turbofans, and propfans under the GE38 name. GE formed a 50/50 venture with Garrett (then a division of AlliedSignal) to develop the turbofan variant[5] called the CFE (Commercial Fan Engines) CFE738, which used the GE27's gas generator core.[2] One of a range of advertised GE38 unducted fan (UDF) sizes,[5] the 9,620 lbf (4,360 kgf; 42.8 kN) takeoff thrust GE38-B5 was for a time the baseline engine for the West German-Chinese MPC 75 regional airliner.[6] The GE38 became the T407 military turboprop in partnership with Lycoming Engines for the Lockheed P-7A, with a maximum takeoff power of 6,000 shp (4,475 kW). First run on December 26, 1989,[7] the T407 engine was scheduled to undergo flight testing on a Lockheed P-3 Orion testbed aircraft in the summer of 1990,[8] but the US Navy canceled Lockheed's P-7 contract on July 20, 1990.[9] The commercial version of the T407 was the GLC38 (General Electric/Lycoming Commercial 38), which was unsuccessfully offered for several turboprop airliners in the late 1980s and early 1990s.[2]
The new T408 (GE38-1B) is slated to power the new Sikorsky CH-53K King Stallion three-engined helicopter for the US Marine Corps. It has a power rating of 7,500 shp.[10] The GE38 completed its first round of ground testing in May 2010.[11] Two test engines have completed over 1,000 hours of ground testing by November 2011. Five test engines will be used in the 5,000-hour test program.[12] In September 2019, GE delivered the first production T408 engine to the U.S. Naval Air Systems Command (NAVAIR) for the CH-53K.[13] GE also offered the engine to power the U.S. Navy's Ship-to-Shore Connector air-cushioned landing craft.
The T408 was also tested by the U.S. Army and Boeing as an alternative powerplant on an NCH-47D Chinook testbed helicopter. The helicopter configuration was ground tested beginning in late 2019, followed by an initial flight on September 22, 2020.[14] Conclusion of the test trials was announced on May 12, 2021.[15]
Variants
- T407-GE-400
- T408-GE-400 (GE38-1B)
- Boeing NCH-47D Chinook (flying testbed)[16]
- Sikorsky CH-53K King Stallion
- CFE CFE738
- Turbofan variant of the T407-GE-400, used on the Dassault Falcon
- CPX38
- Proposed turboprop engine variant of the GE38-1B[17]
- GE38-3
- An 8,000 shp (6,000 kW) class derivative engine under consideration by the U.S. military in 2006[18]
- GE38-B5
- A contra-rotating, ungeared, unducted fan (UDF) derivative with a bare engine weight (including the UDF) of 2,395 lb (1,086 kg), a UDF diameter of 85 inches (2.1 meters), and a blade count of 11 on one propeller and 9 on the other; provides a takeoff thrust of 9,644 lbf (4,374 kgf; 42.90 kN) with a thrust-specific fuel consumption (TSFC) of 0.240 lb/(lbf⋅h) (6.8 g/(kN⋅s)), and a cruise thrust of 2,190 lbf (990 kgf; 9.7 kN) with a TSFC of 0.519 lb/(lbf⋅h) (14.7 g/(kN⋅s)); proposed for the MPC 75 German-Chinese regional airliner in the late 1980s[6]
- GLC38
- Proposed turboprop variant of the T407-GE-400
Applications
- Boeing NCH-47D Chinook (flying testbed)
- Sikorsky CH-53K King Stallion
Specifications (T408)
Data from GE Aviation.[19]
General characteristics
- Type: Turboprop/turboshaft
- Length: 57.5 inches (1.46 m)
- Diameter: 27 inches (0.69 m)
- Dry weight: 1,104.7 pounds (501.1 kg)
Components
- Compressor: 5-stage axial + 1-stage centrifugal HP compressor
- Turbine: 2-stage single crystal cooled HP turbine, 3-stage LP turbine
- Oil system: synthetic[vague]
Performance
- Maximum power output: 7,500 shaft horsepower (5,600 kW)
- Overall pressure ratio: 18.6:1
- Specific fuel consumption: About 0.4 lb/(hp⋅h) (0.24 kg/kWh) (estimated)[20]
- Power-to-weight ratio: 6.8 shp/lb (11.2 kW/kg)
See also
Related development
Comparable engines
Related lists