By Richard T. C. Harman
Fuel Turbine Engineering: functions, Cycles and features
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Extra info for Gas Turbine Engineering: Applications, Cycles and Characteristics
3). 314). 1 ). 25 ~[( 2 mv'Toe --:ti = 'Y A 'Y ePoe J-y+ 1 )/('y- 1 ) /Cp('Y- 1) ] where the pressure is in the consistent units N/m 2 (appendix A). 1753 m This is the effective area of the nozzle.
533 bar if the inlet condition was the International Standard Atmosphere, Sea Level, Static condition (ISASLS). Other parameters also have dimensionless forms. 2), from which the actual values of any parameter can be found by inserting the ambient atmospheric conditions as the reference inlet and outlet data. 2) and heat addition and rejection at constant pressure. This cycle is different from those of the various reciprocating engine types, which work ideally to the Diesel, Otto (petrol engines), Stirling or other cycles.
2) for VTOL. Supersonic flight requires a considerably increased jet velocity. 4) reheats the exhaust gas after the turbines, permitting it to accelerate to an appropriate level above the flight velocity and boosting the thrust to overcome the increased drag. The last aircraft engine type is the auxiliary power unit (APU). It is a small turboshaft engine which provides air-conditioning and electric and hydraulic power while the main engines are stopped, but its main function is to start the main engines without external assistance.
Gas Turbine Engineering: Applications, Cycles and Characteristics by Richard T. C. Harman