General Electric J87
|Type||Nuclear powered afterburning turbojet|
|National origin||United States|
|Number built||at least 2|
The General Electric J87 was a nuclear-powered turbojet engine designed to power the proposed WS-125 long-range bomber. The program was started in 1955 in conjunction with Convair for a joint engine/airframe proposal for the WS-125. It was one of two nuclear-powered gas turbine projects undertaken by GE, the other one being the X39 project.
Design and development
The J87 was a large turbojet, designed to operate as a paired unit, with a nuclear reactor power section. The complete power-plant was given the project designation X211.
The X211 was a relatively large multiple turbojet engine of conventional layout, save for the combustion chambers being replaced by a nuclear reactor where half of the total air-flow through the turbojet sections was used for direct-cycle cooling of the reactor. The J87 components featured variable-stator compressors and chemically-fuelled afterburners and a single nuclear reactor to supply heat to both J87 engines.
Several arrangements for the X211 were studied but eventually the paired J87 was chosen and development was started at General Electrics Evandale factory. The air by-passed around the XMA-1A nuclear reactor passed through can style combustion chambers arranged around the core, used for starting, burning normal jet fuel to ensure cooling air flow for the reactor as soon as it was started-up. The reactor core sat in the middle of the combustion section, fed with cooling air from a large plenum chamber. Heated exhaust air was collected by another plenum chamber to be fed to the turbine sections. Testing of the X211 was confined to the XJ87 turbojet sections.
In 1956, the United States Air Force (USAF) decided that the proposed WS-125 bomber was unfeasible as an operational strategic aircraft. In spite of this, the X211 program was continued for another 3 years, albeit with no target application. It was finally terminated in mid-1959 and by 1961 all funding for nuclear propulsion was removed.
Specifications (single J87)
- Type: Afterburning direct-cycle nuclear turbojet
- Length: 41 ft (12 m)
- Diameter: 80 in (2,000 mm) +
- Dry weight: 15,745 lb (7,142 kg) turbojet section sans reactor
- Compressor: 16-stage variable stator axial compressor
- Combustors: Direct-cycle air-cooled XMA-1A nuclear reactor
- Turbine: 3-stage axial turbine
- Fuel type: Nuclear (JP-4 to start)
- Maximum thrust: 13,685 lbf (60.87 kN) 17,300 lbf (77 kN) with afterburner
- Overall pressure ratio: 20:1
- Bypass ratio: 50% by-passed reactor
- Air mass flow: 425 lb (193 kg)/s
- Turbine inlet temperature: ca 1,800 °F (980 °C; 1,260 K)
- Power-to-weight ratio:
- Carpenter, David M. (2003). NX-2 (PDF). United States: Jet Pioneers of America. ISBN 9780963338792. Archived from the original (pdf) on 10 November 2014. Retrieved 10 November 2014.
- "Nuclear Powered Aircraft History + Smallest Nuke Power Plants". xenophilius.wordpress.com. Archived from the original on 21 December 2014. Retrieved 10 November 2014.
- Gunston, Bill (2006). The development of jet and turbine aero engines (4. ed.). Sparkford: PSL. p. 156. ISBN 0750944773.