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]
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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
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Reinhard Mo¨nig,
Reinhard Mo¨nig
Siemens AG, Power Generation (KWU) D-45466 Mu¨lheim a. d. Ruhr, Germany
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Bernhard Ku¨sters,
Bernhard Ku¨sters
German Aerospace Center, Institute of Propulsion Technology, D-51170 Ko¨ln, Germany
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Heinz-Adolf Schreiber
Heinz-Adolf Schreiber
German Aerospace Center, Institute of Propulsion Technology, D-51170 Ko¨ln, Germany
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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
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