### Abstract

A three-dimensional inverse method for the aerodynamic design of turbomachine blades using robust time-marching algorithms for the numerical solutions of the Euler equations is proposed. In this inverse method, the circumferential mass-averaged tangential velocity is the primary specified flow quantity, and the corresponding blade geometry is sought after. The presence of the blades is represented by a periodic array of discrete body forces which is included in the equations of motion. A four-stage Runge-Kutta time-stepping scheme is used to march a finite volume formulation of the unsteady Euler equations to a steady-state solution. Modification of the blade geometry during this time-marching process is achieved using the flow-tangency conditions along the blade surfaces. The method is demonstrated for the design of two-dimensional infinitely thin cascaded blades ranging from the subsonic to the supersonic flow regimes, including cases with rotational flows and complex shock structures in the flow passage. (Authors)

Original language | English (US) |
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Pages (from-to) | 2309-2315 |

Number of pages | 7 |

Journal | AIAA Journal |

Volume | 33 |

Issue number | 12 |

State | Published - 1995 |

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### ASJC Scopus subject areas

- Aerospace Engineering

### Cite this

*AIAA Journal*,

*33*(12), 2309-2315.