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Using an aerospace engine test stand usually used to precisely test spacecraft engines like ion drives, [17] [56] [57] they reported a maximum thrust of 720 mN at 2,500 W of input power. [57] Yang noted that her results were tentative, and said she "[was] not able to discuss her work until more results are published".
The General Electric XA100 is an American adaptive cycle engine demonstrator being developed by General Electric (GE) for the Lockheed Martin F-35 Lightning II and forms the technological foundation for the company's XA102 propulsion system for the United States Air Force's sixth generation fighter program, the Next Generation Air Dominance (NGAD).
The General Electric YF120, internally designated as GE37, was a variable cycle afterburning turbofan engine designed by General Electric Aircraft Engines in the late 1980s and early 1990s for the United States Air Force's Advanced Tactical Fighter (ATF) program.
The Power and Propulsion Element (PPE) for the Lunar Gateway will have a mass of 8-9 metric tons and will be capable of generating 50 kW [3] of solar electric power for its Hall-effect thrusters for maneuverability, which can be supported by chemical monopropellant thrusters for high-thrust attitude control maneuvers.
The XLR11, company designation RMI 6000C4, was the first liquid-propellant rocket engine developed in the United States for use in aircraft. It was designed and built by Reaction Motors Inc., and used ethyl alcohol and liquid oxygen as propellants to generate a maximum thrust of 6,000 lbf (27 kN).
Learn how to download and install or uninstall the Desktop Gold software and if your computer meets the system requirements.
For the CX-X program GE demonstrated a half-scale engine, the GE1/6, with 15,830 lb thrust and an sfc of 0.336. [8] This was developed into the TF39 with a 97 in diameter fan. By modern standards the Low Pressure Compressor on the TF-39 is fairly unique as a single T-stage is mounted upstream of the fan rotor, rather than behind it.
The PW 300 series has been developed in partnership with MTU who are responsible for the low pressure turbine. The first variant, the PW305A, has the following configuration and was designed with a core flexible enough for engines with take-off thrusts from 20 kN to 31 kN (4,500 to 7,000 lb): a single-stage fan driven by a three-stage low pressure turbine, supercharging a four-stage axial ...