NDLI: Investigation of Axial Spacing and Effect of Interface Location in a 1.5 Stage Transonic Axial Compressor

Content Provider	The American Society of Mechanical Engineers (ASME) Digital Collection
Author	Choi, Jaeho Choi, Taewoo
Copyright Year	2015
Abstract	An axial compressor that is used for gas turbines has to meet axial length constraints as well as performance requirements. Therefore, the axial spacing between the stator and the rotor is one of the important design variables in the compressor design. Thus, a 3-dimensional fluid analysis is usually conducted to predict the performance of the compressor and to determine axial spacing in the preliminary design phase. The length of the inlet computational domain, which is influenced by shock waves from the transonic rotor, affects the compressor performance in the computational fluid analysis. This paper deals with a transonic axial compressor stage which consists of an inlet guide vane, a rotor and a stator which are designed as part of a high pressure compressor in a gas turbine. The purpose of this paper is to investigate the axial spacing between an IGV and a rotor, and effects of interface location in the spacing on the performance prediction of the axial compressor with the 3-dimensional fluid analysis. A multi-stage transonic axial compressor with an inlet guide vane was designed. Three dimensional Reynolds-averaged Navier-Stokes equation was used for the numerical analysis and the k-ω SST turbulence model was used to analyze the fluid flow in the transonic axial compressor. Numerical analyses were carried out at three interface locations in the axial spacing between the IGV and the rotor for two axial spacings in order to investigate the effect of interface location limiting the upstream flow of shock waves by the transonic rotor. The results show that the flow characteristics upstream of the rotor depend on the interface location. The detailed results on the performance and the flow fields are shown and discussed in the paper.
Sponsorship	International Gas Turbine Institute
File Format	PDF
ISBN	9780791856635
DOI	10.1115/GT2015-44020
Volume Number	Volume 2A: Turbomachinery
Conference Proceedings	ASME Turbo Expo 2015: Turbine Technical Conference and Exposition
Language	English
Publisher Date	2015-06-15
Publisher Place	Montreal, Quebec, Canada
Access Restriction	Subscribed
Subject Keyword	Turbulence Navier-stokes equations Fluid dynamics Rotors Compressors Flow (dynamics) Design Shock waves High pressure (physics) Fluids Gas turbines Numerical analysis Inlet guide vanes Stators
Content Type	Text
Resource Type	Article

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