Improving aerodynamic matching of axial compressor blading using a 3D multistage inverse design method

M. P.C. Van Rooij, T. Q. Dang, L. M. Larosiliere

Research output: Contribution to conferencePaper

1 Scopus citations

Abstract

Current turbomachinery design systems increasingly rely on multistage CFD as a means to diagnose designs and assess performance potential. However, design weaknesses attributed to improper stage matching are addressed using often ineffective strategies involving a costly iterative loop between blading modification, revision of design intent, and further evaluation of aerodynamic performance. A scheme is proposed herein which greatly simplifies the design point blade row matching process. It is based on a three-dimensional viscous inverse method that has been extended to allow blading analysis and design in a multi-blade row environment. For computational expediency, blade row coupling is achieved through an averaging-plane approximation. The proposed method allows improvement of design point blade row matching by direct regulation of the circulation capacity of the blading within a multistage environment. During the design calculation, blade shapes are adjusted to account for inflow and outflow conditions while producing a prescribed pressure loading. Thus, it is computationally ensured that the intended pressure-loading distribution is consistent with the derived blading geometry operating in a multi-blade row environment that accounts for certain blade row interactions. The viability of the method is explored in design exercises on a 2.5-stage, highly loaded compressor.

Original languageEnglish (US)
Pages1019-1032
Number of pages14
DOIs
StatePublished - Nov 24 2005
EventASME Turbo Expo 2005 - Gas Turbie Technology: Focus for the Future - Reno-Tahoe, NV, United States
Duration: Jun 6 2005Jun 9 2005

Other

OtherASME Turbo Expo 2005 - Gas Turbie Technology: Focus for the Future
CountryUnited States
CityReno-Tahoe, NV
Period6/6/056/9/05

Keywords

  • Compressor stage matching
  • Inverse aerodynamic shape design
  • Multistage turbomachinery CFD

ASJC Scopus subject areas

  • Engineering(all)

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    Van Rooij, M. P. C., Dang, T. Q., & Larosiliere, L. M. (2005). Improving aerodynamic matching of axial compressor blading using a 3D multistage inverse design method. 1019-1032. Paper presented at ASME Turbo Expo 2005 - Gas Turbie Technology: Focus for the Future, Reno-Tahoe, NV, United States. https://doi.org/10.1115/GT2005-68271