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Publications at Chair of Aero Engines

A Fast Approach for Unsteady Compressor Performance Simulation Under Boundary Condition Caused by Pressure Gain Combustion
Citation key 2021_neumann_n_japplthermaleng
Author Neumann, N. and Asli, M. and Garan, N. and Peitsch, D. and Stathopoulos, P.
Pages 117223
Year 2021
ISSN 1359-4311
DOI 10.1016/j.applthermaleng.2021.117223
Location UK
Journal Applied Thermal Engineering
Volume 196
Month 09
Note Technische Universität Berlin:
N. Neumann, M. Asli, N. Garan, D. Peitsch, P. Stathopoulos
Publisher Elsevier Ltd.
Series ScienceDirect
Abstract The constant pressure combustion of the Joule cycle is a dominant source of losses in gas turbines. One possible improvement is pressure gain combustion through pulse detonation combustion. However, the total pressure increase is the result of a transient periodic process that can adversely affect the performance of adjoining turbo components. The thermodynamic benefits of pressure gain combustion can thus be undermined by low efficiencies of compressor and turbine. In order to account for such unsteady effects early in the design process, suitable methods are essential. Given 3D-CFD simulations’ undue computational demands, an approach with low computation resources is required for first-order estimates. This paper introduces such an approach based on a 1D-Euler method and demonstrates its applicability. A compressor is simulated with 3D-CFD, which serves as a reference, as well as with the 1D-Euler code employing unsteady outlet boundary conditions that approximate those encountered with pulse detonation combustion. The findings suggest that the 1D-Euler code is able to accurately capture the transient compressor behaviour. Though the relative pressure amplitude at the compressor outlet of 3.6% is attenuated by 90% up to the compressor inlet, it still results in a compressor isentropic efficiency loss of 0.8 percentage points.
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