Loss generation in transonic turbine blading

[+] Author and Article Information
Penghao Duan

Osney Thermo-Fluids Laboratory, University of Oxford, Oxford, England OX1 3PJ, United Kingdom

Choon S. Tan

Department of Aeronautics and Astronautics, Massachusetts Institute of Technology, 77 Massachusetts Avenue, Cambridge, MA 02139

Andrew Scribner

Gas Turbine Engineering, Siemens Energy Inc., Charlotte, NC, 28273

Anthony Malandra

Siemens Energy, Inc., 11842 Corporate Boulevard, Orlando, FL 32817

1Corresponding author.

ASME doi:10.1115/1.4038689 History: Received September 09, 2017; Revised December 05, 2017


The measured loss in a high-speed cascade tunnel of two turbine blades of different designs showed distinctly different trend with exit Mach number ranging from 0.8 to 1.4. Assessments using RANS computation in the two blades, complemented with control volume analyses and loss modelling, elucidate why the measured loss characteristic looks the way it is. The loss model categorizes the total loss in terms of boundary layer loss, trailing edge loss and shock loss; it yields results in good agreement with the experimental data as well as RANS computed results. The measured loss plateau in Blade 1 for Mach number of 1 to 1.4 is due to a balance between a decrease of boundary layer loss and an increase in shock loss with Mach number; this plateau is absent in Blade 2 due to a greater rate in shock loss increase than the corresponding decrease in boundary layer loss. For exit Mach number from 0.85 to 1, the higher loss associated with shock system in Blade 1 is due to the larger divergent angle downstream of the throat than that in Blade 2. However when exit Mach number is between 1.00 and 1.30, Blade 2 has higher shock loss. In transonic to supersonic flow regime, the turbine design can be tailored to yield a shock pattern the loss of which can be mitigated in near equal amount of that from the boundary layer with increasing Mach number, hence yielding a loss plateau.

Siemens AG
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