Numerical analysis of three-dimensional unsteady hot streak migration and shock interaction in a turbine stage
- Swiss Federal Inst. of Technology, Zuerich (Switzerland)
A three-dimensional unsteady flow computation has been performed for a transonic first turbine stage under the influence of streaks of hot gas exiting the combustion chamber. Realistic flow conditions are obtained by using an unequal stator-to-rotor pitch, a single-streak/multistator channel configuration, and periodic boundary conditions. The resulting unsteady shock wave system and the hot streak migration as well as the shock wave/streak interaction are presented and discussed. In addition, the time average of the periodic unsteady solution is analyzed and compared with a steady-state computation. The steady-state solution matches the time-averaged one in terms of the pressure field and the maximum stagnation temperature on the rotor blade surface. However, the rotor blade temperature patterns are different with a stronger radial secondary flow present in the time-averaged solution due to the retention of the circumferential streak variations at the stator/rotor interface.
- Sponsoring Organization:
- USDOE
- OSTI ID:
- 250812
- Report Number(s):
- CONF-940626-; ISSN 0889-504X; TRN: IM9629%%125
- Journal Information:
- Journal of Turbomachinery, Vol. 118, Issue 2; Conference: 39. international gas turbine and aeroengine congress and exposition, The Hague (Netherlands), 13-16 Jun 1994; Other Information: PBD: Apr 1996
- Country of Publication:
- United States
- Language:
- English
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