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  2. Kolesov RD-36 - Wikipedia

    en.wikipedia.org/wiki/Kolesov_RD-36

    This was a modified version of the RD36-51A engine with an unregulated nozzle and oxygen supply to the combustion chamber. The engine provided long-duration operation at an altitude of 26,000 m (85,000 ft) at low flight speed (M = 0.6). P = 7,000 kgf (15,000 lbf; 69,000 N) With beats. vsl. = 0,88 kg / kgf • h.

  3. Components of jet engines - Wikipedia

    en.wikipedia.org/wiki/Components_of_jet_engines

    Diagram of a typical gas turbine jet engine. Air is compressed by the compressor 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 drive the compressor blades. 1. Intake 2. Low pressure compression 3. High pressure compression ...

  4. Turbofan - Wikipedia

    en.wikipedia.org/wiki/Turbofan

    One of the earliest turbofans was a derivative of the General Electric J79 turbojet, known as the CJ805-23, which featured an integrated aft fan/low-pressure (LP) turbine unit located in the turbojet exhaust jetpipe. Hot gas from the turbojet turbine exhaust expanded through the LP turbine, the fan blades being a radial extension of the turbine ...

  5. Category:Low-bypass turbofan engines - Wikipedia

    en.wikipedia.org/wiki/Category:Low-bypass...

    Turbofan engines with a bypass ratio of less than 2 (usually less than 1). These engines were commonly used on narrow body jet airliners of the 1960s and 1970s, some business jets from the same time period, and on modern fighter aircraft.

  6. General Electric CJ805 - Wikipedia

    en.wikipedia.org/wiki/General_Electric_CJ805

    Data from FAA Type Certificate Data Sheet, E-306 General characteristics Type: Single-spool turbojet Length: 188.9 in (4,798 mm) with thrust reverser/suppressor Diameter: 31.6 in (803 mm) Dry weight: 3,213 lb (1,457 kg) with thrust reverser/suppressor Components Compressor: 17-stage axial flow Combustors: can-annular Turbine: 2× gas generator power stages Fuel type: Aviation kerosene Oil ...

  7. Pratt & Whitney PW1120 - Wikipedia

    en.wikipedia.org/wiki/Pratt_&_Whitney_PW1120

    This improved the sustained turn rate by 15 per cent, the climb rate by 36 per cent, medium-level acceleration by 27 per cent and low-level speed with 18 bombs from 1,046 km/h to 1,120 km/h (654 - 700 mph or 565 kn to 605 kn). It was demonstrated at the Paris Air Show in 1987.

  8. Pratt & Whitney J52 - Wikipedia

    en.wikipedia.org/wiki/Pratt_&_Whitney_J52

    The Pratt & Whitney J52 (company designation JT8A) is an axial-flow dual-spool turbojet engine originally designed for the United States Navy, [2] in the 40 kN (9,000 lbf) class. It powered the A-6 Intruder and the AGM-28 Hound Dog cruise missile. As of 2021 the engine was still in use in models of the A-4 Skyhawk.

  9. Turbojet - Wikipedia

    en.wikipedia.org/wiki/Turbojet

    Early turbojet compressors had low pressure ratios up to about 5:1. Aerodynamic improvements including splitting the compressor into two separately rotating parts, incorporating variable blade angles for entry guide vanes and stators, and bleeding air from the compressor enabled later turbojets to have overall pressure ratios of 15:1 or more.