This paper describes the design of a transonic mixed flow compressor stage for an extreme duty, with an extremely high flow coefficient () of 0.25 and a high isentropic pressure rise coefficient (ψ) of 0.56. The impeller design makes use of modern aerodynamic practice from radial and transonic axial compressors, whereby the aerodynamic blade shape involved arbitrary surfaces on several spanwise sections. Some aspects of the aerodynamic optimization of the design were limited by mechanical considerations, but nevertheless the test data obtained on a prototype stage demonstrates that acceptable performance levels can be achieved at these extreme design conditions, although map width enhancement (MWE) devices were needed to obtain an acceptable operating range. The test data are compared with computational fluid dynamics (CFD) predictions to demonstrate the validity of the design methods used.
A Transonic Mixed Flow Compressor for an Extreme Duty
Studio 2, Deepdale Enterprise Park,
Stuttgart 70569, Germany
Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received September 9, 2014; final manuscript received September 17, 2014; published online November 26, 2014. Editor: Ronald Bunker.
- Views Icon Views
- Share Icon Share
- Cite Icon Cite
- Search Site
Hazby, H., Casey, M., Numakura, R., and Tamaki, H. (May 1, 2015). "A Transonic Mixed Flow Compressor for an Extreme Duty." ASME. J. Turbomach. May 2015; 137(5): 051010. https://doi.org/10.1115/1.4028738
Download citation file:
- Ris (Zotero)
- Reference Manager