Improved blade profile loss and deviation angle models for advanced transonic compressor bladings. Part 1: A model for subsonic flow
- Technical Univ. of Darmstadt (Germany). Dept. of Flight Propulsion
- Univ. of Munich, Neubiberg (Germany). Inst. for Jet Propulsion
New blading concepts as used in modern transonic axial-flow compressors require improved loss and deviation angle correlations. The new model presented in this paper incorporates several elements and treats blade-row flows having subsonic and supersonic inlet conditions separately. In the first part of this paper two proved and well-established profile loss correlations for subsonic flows are extended to quasi-two-dimensional conditions and to custom-tailored blade designs. Instead of a deviation angle correlation, a simple method based on singularities is utilized. The comparison between the new model and a recently published model demonstrates the improved accuracy in prediction of cascade performance achieved by the new model.
- Sponsoring Organization:
- USDOE
- OSTI ID:
- 194220
- Report Number(s):
- CONF-940626-; ISSN 0889-504X; TRN: IM9611%%61
- Journal Information:
- Journal of Turbomachinery, Vol. 118, Issue 1; Conference: 39. international gas turbine and aeroengine congress and exposition, The Hague (Netherlands), 13-16 Jun 1994; Other Information: PBD: Jan 1996
- Country of Publication:
- United States
- Language:
- English
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