What is the most powerful turbojet engine engine ever made?
I believe General Electric possibly made such an turbojet engine, albeit in prototype form only, that produced in the order 70,000 lbf, if this is so what aircraft was it planned to be used in?
You're probably thinking of this . The mighty GE4
Thanks, that was the engine I was thinking of. I would imagine the noise levels generated by this engine would make the critics of the F35's F135 engine noise levels would think it was positively silent in comparison.
The Boeing SST engines noise level was one of the many reasons which doomed the program .....
I think that the most powerfull engine (TURBO FAN) ever made that is under production is the GE90-115B.
Specifically designed for the Boeing 777, the GE90-115B holds the world record for thrust totalling 127,900 pounds of thrust.
"The most powerful derivative of the GE90, the GE90-115B, is the sole
powerplant for Boeing's longer-range 777-300ER. The GE90-115B certified
at 115,000 lbs. of thrust and has broken a number of aviation records.
GE90-115B derated to 110 lbs. of thrust (GE90-110B) powers the Boeing
777-200LR and the world's largest, most capable twin-engine freighter
-- Boeing's 777 Freighter. The 777 Freighter will offer unsurpassed
efficiency to long-haul markets and provide more capacity than any
other twin-engine freighter."
The Guinness Book of World Records recognized the engine as the
"World's Most Powerful Commercial Jet Engine" in 2001 after it recorded
an amazing 123,000 lbs. of steady-state thrust while undergoing initial
ground testing. In late 2002, the engine shattered its original record
by reaching 127,900 lbs. of thrust during required certification
The GE90 isn't a turboject though.
A. General The micro-turbojet engine HN-40-65(hereafter referred to as the turbojet) is a highly reliable, low-cost, single-shaft turbine jet engine. It consists of centrifugal compressor, bearing lubricating system, annular firebox, radial turbine, simple convergent nozzle and electron fuel controller. The thrust of HN-40-65 is 650N . B. Description The engine HN-40-65 consists of the following six parts: a) Inlet assembly: The S/A consists of an inlet duct which is taken the shape of hyperbola and a center body located at the rear of the inlet duct. The inlet duct conducts the air into the compressor with less pressure drop. The center body is supported by three rods, apart from each other by 120°. The center body contained a starting motor. b) Compressor: The S/A consists of centrifugal rotor, radial diffuser and axial diffuser. The clip bush of the bearings and the bearing lubricating system are fixed at the rear of the diffuser. c) Firebox: The S/A consists of main fuel supply system, starting fuel supply system, igniting device, flame canister and the housing. d) Turbine: The S/A consists of a guided ring and a radial turbine. e) Nozzle: It is a simple convergent nozzle. f) Fuel control system: The S/A consists of Digital Fuel Electronic Control Unit (ECU) and fuel pump. Max. flight height: 7620m Max. flight velocity: 0.8Ma Min. working temperature: -40℃ Max. working temperature: +35℃ The engine HN-40-65 contains a Digital Fuel Electronic Control Unit (ECU). The 12V (or 24V) current is supplied by battery or DC power source. The input signals include the rotate speed of engine (n), the pressure (P2) at the compressor outlet, the exhaust temperature (T4) and order signal (simulation or digital signal). The output signal is the pulsed voltage signal to control the fuel supply.