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Titolo:
1999 Turbomachinery Committee Best Paper Award - Development of advanced compressor airfoils for heavy-duty gas turbines - Part I: Design and optimization
Autore:
Koller, U; Monig, R; Kusters, B; Schreiber, HAB;
Indirizzi:
Siemens AG, Power Generat KWU, D-45466 Mulheim, Germany Siemens AG Mulheim Germany D-45466 Generat KWU, D-45466 Mulheim, Germany German Aerosp Ctr, Inst Prop Technol, D-51170 Cologne, Germany German Aerosp Ctr Cologne Germany D-51170 hnol, D-51170 Cologne, Germany
Titolo Testata:
JOURNAL OF TURBOMACHINERY-TRANSACTIONS OF THE ASME
fascicolo: 3, volume: 122, anno: 2000,
pagine: 397 - 405
SICI:
0889-504X(200007)122:3<397:1TCBPA>2.0.ZU;2-1
Fonte:
ISI
Lingua:
ENG
Tipo documento:
Article
Natura:
Periodico
Settore Disciplinare:
Engineering, Computing & Technology
Citazioni:
26
Recensione:
Indirizzi per estratti:
Indirizzo: Koller, U Siemens AG, Power Generat KWU, D-45466 Mulheim, Germany Siemens AG Mulheim Germany D-45466 U, D-45466 Mulheim, Germany
Citazione:
U. Koller et al., "1999 Turbomachinery Committee Best Paper Award - Development of advanced compressor airfoils for heavy-duty gas turbines - Part I: Design and optimization", J TURBOMACH, 122(3), 2000, pp. 397-405

Abstract

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 ar taken into account. The design processitself 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 ben 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 application 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. [S0998-504X(00)02102-4].

ASDD Area Sistemi Dipartimentali e Documentali, Università di Bologna, Catalogo delle riviste ed altri periodici
Documento generato il 30/11/20 alle ore 09:40:09