Pressure-gain combustion and its potential for gas turbine engine enhancement

Abstract


Despite its simplicity the quasi-isobaric, steady-flow combustion in gas turbines has been identified to have major disadvantages. The highly irreversible heat addition process in conjunction with inevitable loss in stagnation pressure represent an obvious penalty to engine performance and limit the thermodynamic cycle efficiency. This intrinsic drawback of conventional gas turbine combustion can be substantially improved by introduction of pressuregain combustion. The main advantage of pressure gain combustors is their potential for a significant rise in thermal cycle efficiency, its magnitude essentially depending on the specific device chosen. The thermodynamic advantage of pressure-gain combustion is analysed and shown as a function of the combustor pressure ratio for various gas turbine engine setups. Further, the aim of this paper is to summarize the status and important research efforts in this field. A compilation of proposed pressure-gain combustor concepts is presented with regard to its performance, mechanical complexity and suitability for use in gas turbines.


About the authors

E. V. Lutoschkin

Institute of Aircraft Propulsion Systems, University of Stuttgart, Germany

Author for correspondence.
Email: vest@ssau.ru

Russian Federation

M. G. Rose

Institute of Aircraft Propulsion Systems, University of Stuttgart, Germany

Email: vest@ssau.ru

Russian Federation

S. Staudacher

Institute of Aircraft Propulsion Systems, University of Stuttgart, Germany

Email: vest@ssau.ru

Germany

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