General Electric GE4
Today, General Electric GE4 is a topic that has captured the attention of millions of people around the world. From its emergence until today, General Electric GE4 has been the subject of debate, discussion and analysis in a variety of contexts. Its impact on society, politics, popular culture and everyday life is undeniable, and its relevance continues to grow over time. In this article, we will explore the different facets of General Electric GE4, its evolution over the years and its influence on the world today. From its origins to current trends, General Electric GE4 continues to be a topic of interest for people of all ages and backgrounds.
| GE4 | |
|---|---|
| |
| The General Electric GE4/J5 afterburning turbojet | |
| Type | Turbojet |
| National origin | United States |
| Manufacturer | General Electric |
| First run | 1967 |
| Major applications | Boeing 2707 Lockheed L-2000 |
| Produced | 1967 - 1972 |
| Number built | 3[citation needed] |
| Developed from | General Electric YJ93 |
The General Electric GE4 turbojet engine was designed in the late 1960s as the powerplant for the Boeing 2707 supersonic transport. The GE4 was a nine-stage, single-shaft, axial-flow turbojet based largely on the General Electric YJ93 which powered the North American XB-70 bomber.[1] The GE4 was the most powerful engine of its era, producing 50,000 lbf (220 kN) dry, and 65,000 lbf (290 kN) with afterburner.[2] The Boeing 2707 was cancelled in 1971, putting an end to further work on the GE4.
Specifications (GE4/J5P)
General characteristics
- Type: Afterburning turbojet
- Length: 27ft 4 in (8,331mm)
- Diameter: 5ft 11 in (1,803mm)
- Dry weight: 11,300 lb (5,100 kg)[5]
Components
- Compressor: Nine-stage axial[5]
- Combustors: Annular straight-through-flow[5]
- Turbine: Two-stage axial[5]
- Fuel type: Special high-temperature JP-6 Fuel
Performance
- Maximum thrust: 50,000 lbf (220 kN) (63,200 lbf (281 kN) with afterburner)
- Overall pressure ratio: 12.5:1[5]
- Turbine inlet temperature: 2,200 °F (1,204 °C)[5]
- Thrust-to-weight ratio: 6.02
- Power-to-weight ratio: 6.07[5]
Other Specifications
- Compressor inlet diameter: 60.6 in (1,539 mm)[5]
- Exhaust nozzle diameter: 74.2 in (1,880 mm)
- Core airflow: 620 lb (280 kg) per second
- Noise:
See also
Related development
Comparable engines
Related lists
References
- ^ FLIGHT International. 6 January 1966. p. 33.
- ^ FLIGHT International. 6 January 1972. pp. 16a–17.
- ^ "SUPERSONIC TRANSPORT DEVELOPMENT PROGRAM. PHASE III PROPOSAL. BOEING MODEL 2707". Archived from the original on May 15, 2012. Retrieved 2008-12-29.
- ^ FLIGHT International. 5 January 1967. p. 23.
- ^ a b c d e f g h Aircraft engines of the world, Paul H. Wilkinson, 1970. ISBN 0-911710-24-8