Improved blade profile loss and deviation angle models for advanced transonic compressor bladings. Part 2: A model for supersonic flow

Journal Article · Mon Jan 01 04:00:00 EST 1996 · Journal of Turbomachinery

DOI:https://doi.org/10.1115/1.2836610· OSTI ID:194221

Koenig, W M; Hennecke, D K ^[1]; Fottner, L ^[2]

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1. Technical Univ. of Darmstadt (Germany), Dept. of Flight Propulsion
2. 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--
• Journal Information: Journal of Turbomachinery, Journal Name: Journal of Turbomachinery Journal Issue: 1 Vol. 118; ISSN JOTUEI; ISSN 0889-504X
• Country of Publication: United States
• Language: English

Related Subjects

20 FOSSIL-FUELED POWER PLANTS
33 ADVANCED PROPULSION SYSTEMS
COMPRESSOR BLADES
ENERGY EFFICIENCY
ENERGY LOSSES
GAS COMPRESSORS
MATHEMATICAL MODELS
SUBSONIC FLOW