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Jet engines and other gas turbine engines are often uprated by adding a zero-stage, sometimes written '0' stage, [1] to the front of a compressor. [2] At a given core size, adding a stage to the front of the compressor not only increases the cycle overall pressure ratio, but increases the core mass flow.
On civil turbofans, the first stage of the LP compressor is often a single-stage fan. If the HP compressor pressure ratio exceeds about 4.5:1, then the unit will probably have variable geometry (i.e. variable stators) on the first few stages, to make the surge line on the compressor map more shallow, to accommodate the shallow working line.
Data from General characteristics Type: Afterburning turbojet Length: 244 in (6197.6mm) Diameter: 39 in (990.6mm) Dry weight: 5,175 lb (2,347 kg) Components Compressor: all-axial, 9-stage LP compressor, 7-stage HP compressor Combustors: cannular, 8 flame tubes Turbine: all-axial, single stage HP turbine, 2-stage LP turbine Performance Maximum thrust: 11,700 lbf (52.0 kN) dry, 17,200 lbf (76.5 ...
The HP compressor is driven by a single-stage turbine. On the LP spool a three-stage turbine drives a single-stage fan and a four-stage LP compressor. The engine made its first flight August 21, 2000 on a test aircraft flown from Plattsburgh International Airport (KPBG), successfully completing a 1-hour-20-minute flight. [ 1 ]
The Pratt & Whitney J75 (civilian designation: JT4A) is an axial-flow turbojet engine first flown in 1955. A two-spool design in the 17,000 lbf (76 kN) thrust class, the J75 was essentially the bigger brother of the Pratt & Whitney J57 (JT3C).
Compressor performance changes, day to day, with changes in the ambient pressure and temperature. Woolenweber [11] shows the change in performance of a turbocharger compressor when the inlet temperature varies between 70 and 100 deg F. In the case of aircraft compressors, inlet pressure and temperature also change with altitude and airspeed.
Compressor: Two-spool, with low-pressure (LP) and high-pressure (HP) axial compressors: LP compressor with 3 fan stages and transonic blading; HP compressor with 6 stages, including variable inlet guide vanes and first two stators; Combustors: Annular, with dump diffuser and air-blast fuel atomisers; Turbine: 1 LP stage and 1 HP stage
Compressor characteristic is a mathematical curve that shows the behaviour of a fluid going through a dynamic compressor. It shows changes in fluid pressure , temperature , entropy , flow rate etc.) with the compressor operating at different speeds.