Inverse method for turbomachine blades using shock-capturing techniques

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

7 Scopus citations

Abstract

An aerodynamic design method for turbomachine blades using robust time-marching algorithms for the numerical solutions of the Euler equations is proposed. In this inverse method, the blade loading and thickness distributions are prescribed, and the corresponding blade geometry is sought after. A four-stage Runge-Kutta time-stepping scheme is used to march the finite-volume formulation of the unsteady Euler equations to steady-state. The inverse problem is formulated using a pressure-loading boundary condition across the blade surfaces, and modification of the blade geometry is achieved using the flow-tangency conditions along the blade surfaces. The method is demonstrated for the design of two-dimensional cascaded blades ranging from the subsonic to the supersonic flow regimes.

Original languageEnglish (US)
Title of host publication31st Joint Propulsion Conference and Exhibit
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9780000000002
StatePublished - Jan 1 1995
Event31st Joint Propulsion Conference and Exhibit, 1995 - San Diego, United States
Duration: Jul 10 1995Jul 12 1995

Publication series

Name31st Joint Propulsion Conference and Exhibit

Other

Other31st Joint Propulsion Conference and Exhibit, 1995
CountryUnited States
CitySan Diego
Period7/10/957/12/95

ASJC Scopus subject areas

  • Energy Engineering and Power Technology
  • Electrical and Electronic Engineering
  • Mechanical Engineering
  • Control and Systems Engineering
  • Aerospace Engineering

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  • Cite this

    Dang, T. (1995). Inverse method for turbomachine blades using shock-capturing techniques. In 31st Joint Propulsion Conference and Exhibit [AIAA-95-2465] (31st Joint Propulsion Conference and Exhibit). American Institute of Aeronautics and Astronautics Inc, AIAA.