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Published January 2009 | public
Book Section - Chapter

Numerical Study on Single-Stage Axial Turbine with Pulse Detonation Combustor

Abstract

Two-dimensional numerical simulations are conducted for a single-stage axial-turbine system with the inlet gas flow provided by a pulse detonation combustor. The objectives of this study are to compute the turbine work output as a function of rotor speed and gain insights into the significant gap between theoretical predictions and experimental results. The turbine work output is evaluated by two approaches. One is an energy balance evaluation method using average stagnation enthalpy at the stage inlet and outlet, and the other is a mechanical method of integrating the force acting on the rotor blade surface. From the results of both approaches, it is confirmed that the turbine work increases with increasing rotor speed up to 150% from the design point. Multi-cycle operation is also conducted at the design point for an initial pressure of 0.15 MPa and turbine adiabatic efficiency is observed to be reduced 5% after the second cycle.

Additional Information

© 2009 by the American Institute of Aeronautics and Astronautics, Inc. Published online: 15 Jun 2012.

Additional details

Created:
August 20, 2023
Modified:
October 18, 2023