A fully three-dimensional inverse method for turbomachinery blading in transonic flows

Research output: Chapter in Book/Report/Conference proceedingConference contribution

2 Scopus citations

Abstract

This paper presents a procedure to extend a recently developed fully three-dimensional inverse method for highly-loaded turbomachine blades into the transonic-flow regime. In this inverse method, the required three-dimensional blade profile to produce a prescribed swirl schedule is determined iteratively using the blade boundary conditions. In the present implementation, the flow is assumed to be inviscid and the blades are assumed to be infinitely thin. The relevant equations are solved in the conservative forms and are discretized in all three directions using a finite-volume technique. Calculations are carried out for the design of high-pressure axial- and centrifugal-compressor rotors. These examples include prescribed swirl schedules that correspond to blade design that are shock-free and blade design that have rapid compression regions in the blade passage.

Original languageEnglish (US)
Title of host publicationTurbomachinery
PublisherAmerican Society of Mechanical Engineers
Volume1
ISBN (Electronic)9780791878934
DOIs
StatePublished - 1992
EventASME 1992 International Gas Turbine and Aeroengine Congress and Exposition, GT 1992 - Cologne, Germany
Duration: Jun 1 1992Jun 4 1992

Other

OtherASME 1992 International Gas Turbine and Aeroengine Congress and Exposition, GT 1992
CountryGermany
CityCologne
Period6/1/926/4/92

ASJC Scopus subject areas

  • Energy Engineering and Power Technology
  • Fuel Technology
  • Nuclear Energy and Engineering
  • Aerospace Engineering
  • Mechanical Engineering

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