What is the difference between a turbofan and a turboprop engine . . . In a turbofan, the turbine primarily drives a fan at the front of the engine Most engines drive the fan directly from the turbine Most engines drive the fan directly from the turbine There are usually at least two separate shafts to allow the fan to spin slower than the inner core of the engine
What is the difference between turbojet and turbofan engines? A very low bypass turbofan like 0 3:1 is used in the Gripen supersonic fighter as "an efficiency tweak" according to @J This is technically a turbofan but performance-wise it's very close to a turbojet, just more fuel efficient at lower speeds and thrusts The F-16 uses a turbofan with a 0 71:1 bypass These engines can use an afterburner to
turbofan - Why do we refer to power for turboprop engines and thrust . . . For turbofans vs turboprops, its similar to how piston airplanes with fixed pitch props just measure RPM, like a turbofan, whereas piston planes with constant speed props need to show RPM and manifold pressure (MP being more or less equivalent to torque in a turboprop) Not sure what you mean by the math part
In a turbofan what holds the spinning axis? The supporting structures of a turbofan are two stationary frames with their characteristic struts, located at the ends of the engine core: One is behind the OGV stator of the fan module, the other at the aft end of the turbine module: CFM56 with the two frames visible Stationary frames to spinning shafts
Why dont modern jet engines use forced exhaust mixing? 4: Exhaust mixer of a General Electric GEnx-2B high-bypass turbofan from a Boeing 747-8I (image by Olivier Cleynen at Wikimedia Commons); note the chevrons on both the fan cowling (here opened to appease the peanut gallery), for mixing the bypass airflow with the ambient air, and on the core tailpipe, for mixing the core exhaust with the bypass
turbofan - How does a fan differ from a propeller? - Aviation Stack . . . In the other hand in the turbofan, the additional pressure at the front actually helps the air to be forced trough the nozzle increasing performance At extremely high velocities, however, the drag from the fan becomes very high and the speed is limited again (but at a higher velocity than in the propeller )
turbofan - Why is thrust available constant with speed for turbojet . . . Assuming that the net thrust of a turbojet is constant is not correct It is assumed to be constant (for simplicity by the aircraft performance engineers and usually valid for low subsonic speeds), but in reality, the performance is not constant, and it also varies with altitude
What is the operating temperature of a turbofan engine, and how is it . . . Q1: Assuming that by operating temperature you mean turbine inlet temperature, this article says the Pratt Whitney F135 engine in the F-35 (JSF) has a TIT of 3600 °F (1982 °C 2255 K), but that most high performance aircraft engines do not exceed 3000 °F (1649 °C 1922 K), while non aviation engines are nearer 2700 °F (1482 °C 1755 K) or lower
turbofan - How does the bypass air provide thrust? - Aviation Stack . . . $\begingroup$ "The air coming from the engine core will move even faster, but there is less of it in a high bypass turbofan resulting in less total thrust coming from the core" To expand on that: a jet engine's efficiency is (speaking simply) related to the change in velocity of the airstream The greater the difference in velocity between