A new family of subsonic compressor airfoils, which are characterized by low losses and wide operating ranges, has been designed for use in heavy-duty gas turbines. In particular the influence of the higher airfoil Reynolds numbers compared to aeroengine compressors and the impact of these differences on the location of transition are taken into account. The design process itself is carried out by the combination of a geometric code for the airfoil description, with a blade-to-blade solver and a numerical optimization algorithm. The optimization process includes the design-point losses for a specified Q3D flow problem and the off-design performance for the entire operating range. The family covers a wide range of inlet flow angle, Mach number, flow turning, blade thickness, solidity and AVDR in order to consider the entire range of flow conditions that occur in practical compressor design. The superior performance of the new airfoil family is demonstrated by a comparison with conventional controlled diffusion airfoils (CDA). The advantage in performance has been confirmed by detailed experimental investigations, which will be presented in Part II of the paper. This leads to the conclusion that CDA airfoils that have been primarily developed for aeroengine applications are not the optimum solution, if directly transferred to heavy-duty gas turbines. A significant improvement in compressor efficiency is possible, if the new profiles are used instead of conventional airfoils. [S0889-504X(00)02102-4]
Skip Nav Destination
Article navigation
July 2000
Technical Papers
1999 Turbomachinery Committee Best Paper Award: Development of Advanced Compressor Airfoils for Heavy-Duty Gas Turbines— Part I: Design and Optimization
Ulf Ko¨ller,
Ulf Ko¨ller
Siemens AG, Power Generation (KWU) D-45466 Mu¨lheim a. d. Ruhr, Germany
Search for other works by this author on:
Reinhard Mo¨nig,
Reinhard Mo¨nig
Siemens AG, Power Generation (KWU) D-45466 Mu¨lheim a. d. Ruhr, Germany
Search for other works by this author on:
Bernhard Ku¨sters,
Bernhard Ku¨sters
German Aerospace Center, Institute of Propulsion Technology, D-51170 Ko¨ln, Germany
Search for other works by this author on:
Heinz-Adolf Schreiber
Heinz-Adolf Schreiber
German Aerospace Center, Institute of Propulsion Technology, D-51170 Ko¨ln, Germany
Search for other works by this author on:
Ulf Ko¨ller
Siemens AG, Power Generation (KWU) D-45466 Mu¨lheim a. d. Ruhr, Germany
Reinhard Mo¨nig
Siemens AG, Power Generation (KWU) D-45466 Mu¨lheim a. d. Ruhr, Germany
Bernhard Ku¨sters
German Aerospace Center, Institute of Propulsion Technology, D-51170 Ko¨ln, Germany
Heinz-Adolf Schreiber
German Aerospace Center, Institute of Propulsion Technology, D-51170 Ko¨ln, Germany
Contributed by the International Gas Turbine Institute and presented at the 44th International Gas Turbine and Aeroengine Congress and Exhibition, Indianapolis, Indiana, June 7–10, 1999. Manuscript received by the International Gas Turbine Institute February 1999. Paper No. 99-GT-95. Review Chair: D. C. Wisler.
J. Turbomach. Jul 2000, 122(3): 397-405 (9 pages)
Published Online: February 1, 1999
Article history
Received:
February 1, 1999
Citation
Ko¨ller , U., Mo¨nig, R., Ku¨sters , B., and Schreiber, H. (February 1, 1999). "1999 Turbomachinery Committee Best Paper Award: Development of Advanced Compressor Airfoils for Heavy-Duty Gas Turbines— Part I: Design and Optimization ." ASME. J. Turbomach. July 2000; 122(3): 397–405. https://doi.org/10.1115/1.1302296
Download citation file:
Get Email Alerts
Evaluating Thin-Film Thermocouple Performance on Additively Manufactured Turbine Airfoils
J. Turbomach (July 2025)
Thermohydraulic Performance and Flow Structures of Diamond Pyramid Arrays
J. Turbomach (July 2025)
Related Articles
1999 Turbomachinery Committee Best Paper Award: Development of Advanced Compressor Airfoils for Heavy-Duty Gas Turbines— Part II: Experimental and Theoretical Analysis
J. Turbomach (July,2000)
Design of Industrial Axial Compressor Blade Sections for Optimal Range and Performance
J. Turbomach (April,2004)
Siemens Westinghouse Advanced Turbine Systems Program Final Summary
J. Eng. Gas Turbines Power (July,2004)
An Integrated System for the Aerodynamic Design of Compression Systems—Part II: Application
J. Turbomach (January,2011)
Related Chapters
Alternative Systems
Turbo/Supercharger Compressors and Turbines for Aircraft Propulsion in WWII: Theory, History and Practice—Guidance from the Past for Modern Engineers and Students
Performance Testing of Combined Cycle Power Plant
Handbook for Cogeneration and Combined Cycle Power Plants, Second Edition
Outlook
Closed-Cycle Gas Turbines: Operating Experience and Future Potential