compressor stage वाक्य
उदाहरण वाक्य
मोबाइल
- This variant added an additional axial compressor stage ( bringing the total to two axial stages ), which increased the engine length by only 4 in ( 10 cm ), yet increased the thrust to 970 lbf ( 4.3 kN ).
- When used for cabin pressurization, the bleed air from the engine must first be cooled ( as it exits the compressor stage at temperatures as high as 250 �C ) by passing it through an air-to-air heat exchanger cooled by cold outside air.
- Earlier engines generally consisted of a series of compressor stages connected via a shaft to one or more turbine stages, with the burners between them arranged around the shaft . Although this arrangement is mechanically simple, it has the disadvantage of lowering the efficiency of the compressor.
- Pratt & Whitney later announced that core testing was beginning before the end of 2009 . Few details about the design of the engine had been released by the end of 2009, but it had been announced that the high pressure spool of the engine would have eight compressor stages and two turbine stages.
- For the engine optimisation for its intended use, important here is air intake design, overall size, number of compressor stages ( sets of blades ), fuel type, number of exhaust stages, metallurgy of components, amount of bypass air used, where the bypass air is introduced, and many other factors.
- Alternatively, adding a zero ( i . e . front ) stage to the compressor, to increase overall pressure ratio, will require an increase in shaft speed ( to maintain the same blade tip Mach number on each of the original compressor stages, since the delivery temperature of each of these stages will be higher than datum ).
- The Sapphire compressor operated well, free from surging, over its complete RPM range without the need for variable inlet guide vanes ( VIGV ) or bleed ( VIGV on early engines were fixed on the "'ASSa . 6 "'. ) However, early compressor stages suffered from fatigue due to rotating stall at low RPM and various fixes, such as lacing wire, were incorporated.
- It bore considerable similarities in terms of external appearance to the American F-16 fighter, having a similar configuration and several shared design features while being a slightly smaller aircraft . The engine air intake took the form of a plain chin type scoop with a splitter plate, externally resembling that of the F-16, yet internally it was substantially different, not exposing the engine compressor stage forwards ( inverse S-duct ), thus drastically minimizing the frontal cross-sections of IR and radar alike.
- Only the limitations of weight and materials ( e . g ., the strengths and melting points of materials in the turbine ) reduce the efficiency at which a turbofan gas turbine converts this thermal energy into mechanical energy, for while the exhaust gases may still have available energy to be extracted, each additional stator and turbine disk retrieves progressively less mechanical energy per unit of weight, and increasing the compression ratio of the system by adding to the compressor stage to increase overall system efficiency increases temperatures at the turbine face.
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