Effects of intercooling and recuperation on turbofan engine performance
An overall performance simulation model of the intercooled recuperative aero-engine was built, and an overall performance simulation program was developed. Then, analysis of the effects of intercooling and recuperation on the thermodynamic cycle parameters and performance parameters of the turbofan engine can be carried out. The result indicates that the turbofan engine performance can be improved with the proper use of intercooling and recuperation. With the same thermodynamic cycle parameters, the thermal efficiency and the net thrust is larger, while the specific fuel consumption is lower. To gain the same performance, lower overall pressure ratio and lower bypass ratio can be chosen for the intercooled recuperative aero-engine.
Preliminary analysis of thermodynamic cycle of an intercooled recuperated turbofan engine
Intercooled recuperated aero-engine(IRA) is built based on conventional engine while intercooled and recuperated cycles are incorporated.It can utilize effectively engine's heat,improve the thermal efficiency and reduce the specific fuel consumption.The intercooled recuperated aero engine presents a new concept about "green" engine.On the MATLAB platform,an overall performance simulation model has been developed on the intercooled recuperated tri-spool turbofan engine with split exhaust.Then,performance simulation and thermal cycle analysis was carried out under this model.The result indicates that,with the same thermal cycle parameters and specific thrust,the specific fuel consumption of the IRA is less than that of the conventional turbofan engine.
Experiments in active control of stall on an aeroengine gas turbine
This paper describes work carried out between 1989 and 1994 to investigate the application of ‘Active Stall Control’ to a Rolls-Royce Viper turbojet. The results demonstrate that stall control is feasible and can increase the stable operating range by up to 25% of pressure rise. Stall disturbances were detected using rings of high response pressure transducers positioned at different axial planes along the compressor, and processed using a PC-based data acquisition and control system. Actuation was provided by six hydraulically operated sleeve valves positioned to recirculate air over all or part of the compressor.Stall was artificially induced using combinations of inbleed into the combustor outer casing, fuel spiking, hot gas ingestion and inlet pressure spoiling, thus replicating many of the transient conditions commonly observed to make a compressor prone to stall. Results are compared from a number of stall control strategies including those demonstrated at low speed by Paduano et al [1993] and Day [1993]. Best results were obtained with detection of non-axisymmetric disturbances coupled with axisymmetric control action. A control system of this type is demonstrated to be capable of extending the stable engine operating range at all speeds and with each method of inducing stall.Copyright © 1997 by ASME