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exit pressure ratio

См. также в других словарях:

  • Overall pressure ratio — In aeronautical engineering, the term overall pressure ratio is defined as the ratio of the stagnation pressure as measured at the front and rear of the compressor of a gas turbine engine. Generally speaking, a higher overall pressure ratio… …   Wikipedia

  • Components of jet engines — Diagram of a typical gas turbine jet engine. Air is compressed by the fan blades as it enters the engine, and it is mixed and burned with fuel in the combustion section. The hot exhaust gases provide forward thrust and turn the turbines which… …   Wikipedia

  • Rocket engine — RS 68 being tested at NASA s Stennis Space Center. The nearly transparent exhaust is due to this engine s exhaust being mostly superheated steam (water vapor from its propellants, hydrogen and oxygen) …   Wikipedia

  • Turbofan — [ CFM56 3 turbofan, lower half, side view.] A turbofan is a type of jet engine, similar to a turbojet. It essentially consists of a ducted fan with a smaller diameter turbojet engine mounted behind it that powers the fan. Part of the airstream… …   Wikipedia

  • Centrifugal compressor — Centrifugal compressors, sometimes termed radial compressors, are a sub class of dynamic axisymmetric work absorbing turbomachinery.[1] Centrifugal impeller with a highly polished surface likely to improve performance …   Wikipedia

  • Jet engine performance — This article describes how jet engine performance is estimated during the design phase. Similar techniques are used once the engine has been built and is being tested, except the performance of individual components, rather than being assumed, is …   Wikipedia

  • Afterburner — For other uses of afterburner, see Afterburner (disambiguation). Infobox Aviation name= Afterburner caption= A U.S. Navy F/A 18 Hornet being launched from the catapult on full afterburnerAn afterburner (or reheat) is an additional component added …   Wikipedia

  • Propelling nozzle — A propelling nozzle is a component of a jet engine that is found at the tail of the engine that operates to form an exhaust jet and to maximise the use of the exhaust gas s energy throughout the engine so that the maximum overall thrust is… …   Wikipedia

  • Jet engine — For a general overview of aircraft engines, see Aircraft engine. A Pratt Whitney F100 turbofan engine for the …   Wikipedia

  • Axial compressor — Axial compressors are rotating, aerofoil based compressors in which the working fluid principally flows parallel to the axis of rotation. This is in contrast with centrifugal, axi centrifugal and mixed flow compressors where the air may enter… …   Wikipedia

  • Rocket engine nozzle — A rocket engine nozzle is a propelling nozzle usually of the de Laval type used in a rocket engine to expand and accelerate the combustion gases, from burning propellants, so that the exhaust gases exit the nozzle at hypersonic… …   Wikipedia

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