Improved blade profile loss and deviation angle models for advanced transonic compressor bladings. Part 2: A model for supersonic 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. The second part of the present report focuses on the extension of a well-known correlation for cascade losses at supersonic inlet flows. It was originally established for DCA bladings and is now modified to reflect the flow situation in blade rows having low-cambered, arbitrarily designed blades including precompression blades. Finally, the steady loss increase from subsonic to supersonic inlet-flow velocities demonstrates the matched performance of the different correlations of the new model.
- Sponsoring Organization:
- USDOE
- OSTI ID:
- 194221
- Report Number(s):
- CONF-940626-; ISSN 0889-504X; TRN: IM9611%%62
- 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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