In a previous study, vane-rotor shock interactions and heat transfer on the rotor blade of a highly loaded transonic turbine stage were simulated. The geometry consists of a high pressure turbine vane and a downstream rotor blade. This study focuses on the physics of flow and heat transfer in the rotor tip, casing, and hub regions. The simulation was performed using the unsteady Reynolds-averaged Navier–Stokes code MSU-TURBO. A low Reynolds number model was utilized to model turbulence. The rotor blade in question has a tip gap height of 2.1% of the blade height. The Reynolds number of the flow is approximately . Unsteadiness was observed at the tip surface that results in intermittent “hot spots.” It is demonstrated that unsteadiness in the tip gap is governed by inviscid effects due to high speed flow and is not strongly dependent on pressure ratio across the tip gap contrary to published observations that have primarily dealt with subsonic tip flows. The high relative Mach numbers in the tip gap lead to a choking of the leakage flow that translates to a relative attenuation of losses at higher loading. The efficacy of new tip geometry is discussed to minimize heat flux at the tip while maintaining choked conditions. In addition, an explanation is provided that shows the mechanism behind the rise in stagnation temperature on the casing to values above the absolute total temperature at the inlet. It is concluded that even in steady (in a computational sense) mode, work transfer to the near tip fluid occurs due to relative shearing by the casing. This is believed to be the first such explanation of the work transfer phenomenon in the open literature. The difference in pattern between steady and time-averaged heat fluxes at the hub is also explained.
Skip Nav Destination
Article navigation
July 2012
Research Papers
Analysis of Unsteady Tip and Endwall Heat Transfer in a Highly Loaded Transonic Turbine Stage
Vikram Shyam,
Vikram Shyam
NASA Glenn Research Center
, Cleveland, OH 44135
Search for other works by this author on:
Ali Ameri,
Ali Ameri
NASA Glenn Research Center
, Cleveland, OH 44135; Ohio State University
, Columbus, OH 44135
Search for other works by this author on:
Jen-Ping Chen
Jen-Ping Chen
Aerospace Engineering,
Ohio State University
, Columbus, OH 44135
Search for other works by this author on:
Vikram Shyam
NASA Glenn Research Center
, Cleveland, OH 44135
Ali Ameri
NASA Glenn Research Center
, Cleveland, OH 44135; Ohio State University
, Columbus, OH 44135
Jen-Ping Chen
Aerospace Engineering,
Ohio State University
, Columbus, OH 44135J. Turbomach. Jul 2012, 134(4): 041022 (9 pages)
Published Online: July 25, 2011
Article history
Revised:
September 12, 2010
Received:
November 2, 2010
Online:
July 25, 2011
Published:
July 25, 2011
Citation
Shyam, V., Ameri, A., and Chen, J. (July 25, 2011). "Analysis of Unsteady Tip and Endwall Heat Transfer in a Highly Loaded Transonic Turbine Stage." ASME. J. Turbomach. July 2012; 134(4): 041022. https://doi.org/10.1115/1.4003719
Download citation file:
Get Email Alerts
The Cooling Effect of Combustor Exit Louver Scheme on a Transonic Nozzle Guide Vane Endwall
J. Turbomach (July 2025)
Aerodynamic Performance Evaluation of Subsonic Compressor Cascade Blade With Leading-Edge Damage
J. Turbomach (July 2025)
Thermohydraulic Performance and Flow Structures of Diamond Pyramid Arrays
J. Turbomach (July 2025)
Related Articles
A Study of Advanced High-Loaded Transonic Turbine Airfoils
J. Turbomach (October,2006)
An Implicit Fluctuation Splitting Scheme for Turbomachinery Flows
J. Turbomach (April,2005)
Inverse Design of and Experimental Measurements in a Double-Passage Transonic Turbine Cascade Model
J. Turbomach (July,2005)
Unsteady Rotor Heat Transfer in a Transonic Turbine Stage
J. Turbomach (October,2002)
Related Proceedings Papers
Related Chapters
Control and Operational Performance
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Introduction
Turbine Aerodynamics: Axial-Flow and Radial-Flow Turbine Design and Analysis
Outlook
Closed-Cycle Gas Turbines: Operating Experience and Future Potential