Improved blade profile loss and deviation angle models for advanced transonic compressor bladings. Part 1: A model for subsonic flow

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

DOI:https://doi.org/10.1115/1.2836609· OSTI ID:194220

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

---

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. 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--
• 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