Modern computer simulations can predict some aspects of the unsteady aerodynamic phenomena associated with turbomachinery blade rows. This allows analysts to investigate aeroelastic phenomena, such as flutter, and blade-row interactions, such as forced response and unsteady effects on performance. This paper describes tools and design processes used to numerically investigate unsteady aerodynamic phenomena in heavy-duty gas turbines. A linearized Navier- Stokes method from the DLR has been used to predict the aerodynamic damping of both compressor and turbine airfoils under a variety of operating conditions. Some of these predictions were validated with engine experience. Other CFD codes, including TRACE from the DLR and ITSM3D from the University of Stuttgart, have been used to predict blade-row interaction. This includes the prediction of forced response due to rotor-vane interaction and unsteady effects on performance. The effects of airfoil clocking, including the effects of cooling flow injection, have also been investigated. Advanced CFD modeling has been developed in research institutes and applied in aircraft engine design, and now contributes to heavy-duty gas turbine design as well. Computational analysis of aeromechanics - both flutter and forced response - unsteady aerodynamic and thermal blade row interaction, and airfoil clocking aimed at aerodynamic and thermal performance optimization are demonstrated for heavy-duty gas turbines. These analyses contribute to better understanding of past experience and offer new design opportunities.
Application of unsteady aerodynamics and aeroelasticity in heavy-duty gas turbines
Anwendung der instationären Aerodynamik und Aeroelastizität in Hochleistungs-Gasturbinen
ASME Turbo Expo, 2005 ; 635-649
2005
15 Seiten, 27 Bilder, 4 Tabellen, 41 Quellen
Aufsatz (Konferenz)
Englisch
Aeroelasticity and Unsteady Aerodynamics
AIAA | 1989
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