The experimental investigation of an aspirated fan stage designed to achieve a pressure ratio of 3.4:1 at 1500 ft/s is presented in this paper. The low-energy viscous flow is aspirated from diffusion-limiting locations on the blades and flowpath surfaces of the stage, enabling a very high pressure ratio to be achieved in a single stage. The fan stage performance was mapped at various operating speeds from choke to stall in a compressor facility at fully simulated engine conditions. The experimentally determined stage performance, in terms of pressure ratio and corresponding inlet mass flow rate, was found to be in good agreement with the 3D viscous computational prediction, and in turn close to the design intent. Stage pressure ratios exceeding 3:1 were achieved at design speed, with an aspiration flow fraction of 3.5% of the stage inlet mass flow. The experimental performance of the stage at various operating conditions, including detailed flowfield measurements, are presented and discussed in the context of the computational analyses. The stage performance and operability at reduced aspiration flow rates at design and off-design conditions are also discussed.
Skip Nav Destination
Article navigation
January 2005
Technical Papers
Experimental Investigation of a High Pressure Ratio Aspirated Fan Stage
Ali Merchant,
Ali Merchant
Gas Turbine Laboratory, Massachusetts Institute of Technology, Cambridge, Massachusetts 02139
Search for other works by this author on:
Jack L. Kerrebrock,
Jack L. Kerrebrock
Gas Turbine Laboratory, Massachusetts Institute of Technology, Cambridge, Massachusetts 02139
Search for other works by this author on:
John J. Adamczyk,
John J. Adamczyk
NASA Glenn Research Center, Cleveland, Ohio 44135
Search for other works by this author on:
Edward Braunscheidel
Edward Braunscheidel
NASA Glenn Research Center, Cleveland, Ohio 44135
Search for other works by this author on:
Ali Merchant
Gas Turbine Laboratory, Massachusetts Institute of Technology, Cambridge, Massachusetts 02139
Jack L. Kerrebrock
Gas Turbine Laboratory, Massachusetts Institute of Technology, Cambridge, Massachusetts 02139
John J. Adamczyk
NASA Glenn Research Center, Cleveland, Ohio 44135
Edward Braunscheidel
NASA Glenn Research Center, Cleveland, Ohio 44135
Contributed by the International Gas Turbine Institute (IGTI) of THE AMERICAN SOCIETY OF MECHANICAL ENGINEERS for publication in the ASME JOURNAL OF TURBOMACHINERY. Paper presented at the International Gas Turbine and Aeroengine Congress and Exhibition, Vienna, Austria, June 13–17, 2004, Paper No. 2004-GT-53679. Manuscript received by IGTI, October 1, 2003; final revision, March 1, 2004. IGTI Review Chair: A. J. Strazisar.
J. Turbomach. Jan 2005, 127(1): 43-51 (9 pages)
Published Online: February 9, 2005
Article history
Received:
October 1, 2003
Revised:
March 1, 2004
Online:
February 9, 2005
Citation
Merchant , A., Kerrebrock, J. L., Adamczyk , J. J., and Braunscheidel, E. (February 9, 2005). "Experimental Investigation of a High Pressure Ratio Aspirated Fan Stage ." ASME. J. Turbomach. January 2005; 127(1): 43–51. https://doi.org/10.1115/1.1812323
Download citation file:
Get Email Alerts
Related Articles
The Design of Highly Loaded Axial Compressors
J. Turbomach (July,2011)
Prediction of the Nonuniform Tip Clearance Effect on the Axial Compressor Flow Field
J. Fluids Eng (May,2010)
Impact of Manufacturing Variability and Nonaxisymmetry on High-Pressure Compressor Stage Performance
J. Eng. Gas Turbines Power (March,2012)
Related Proceedings Papers
Related Chapters
Boundary Layer Analysis
Centrifugal Compressors: A Strategy for Aerodynamic Design and Analysis
Other Components and Variations
Axial-Flow Compressors
Pulsation and Vibration Analysis of Compression and Pumping Systems
Pipeline Pumping and Compression Systems: A Practical Approach, Second Edition