Effect of turbine endwall contouring on its aerodynamic performance has been widely studied, but only a few studies are available in the open literature investigating its effect on heat transfer performance; especially at transonic exit Mach number conditions. In this paper, we report a study of effect of contouring on endwall heat transfer performance of a high-turning high-pressure (HP) turbine blade passage operating under transonic exit conditions. The paper describes comparison of heat transfer performance of two contoured endwall geometries, one aerodynamically optimized (AO) and the other heat transfer optimized (HTO), with a baseline, noncontoured geometry. The endwall geometries were experimentally investigated at Virginia Tech's transient, blow down, transonic linear cascade facility at three exit Mach numbers, 0.71, 0.88(design) and 0.95, for their heat transfer performance. Endwall surface temperatures were measured using infrared (IR) thermography and local heat transfer coefficient (HTC) values were calculated using measured temperatures. A camera matrix model-based data postprocessing technique was developed to relate the two-dimensional images captured by IR camera to three-dimensional endwall contours. The measurement technique and the methodology for postprocessing of the heat transfer coefficient data have been presented in detail. Discussion and interpretation of experimental results have been augmented using aerodynamic CFD simulations of the geometries. Both the contoured endwalls demonstrated a significant reduction in the overall average heat transfer coefficient values of the order of 10%. The surface Stanton number distributions also indicated a reduction in the level of hot spots for most of the endwall surface. However, at some locations an increase was also observed, especially in the area near the leading edge (LE). The results indicate that the endwall contouring could significantly improve heat transfer performance of turbine passages.
Skip Nav Destination
Article navigation
January 2017
Research-Article
Effect of Endwall Contouring on a Transonic Turbine Blade Passage: Heat Transfer Performance
Santosh Abraham,
Santosh Abraham
Siemens Energy, Inc.,
5101 Westinghouse Boulevard,
Charlotte, NC 28273-9640
e-mail: santosh.abraham@siemens.com
5101 Westinghouse Boulevard,
Charlotte, NC 28273-9640
e-mail: santosh.abraham@siemens.com
Search for other works by this author on:
Srinath V. Ekkad,
Srinath V. Ekkad
Department of Mechanical Engineering,
301 Burruss Hall,
800 Drillfield Drive,
Blacksburg, VA 24061
e-mail: sekkad@vt.edu
301 Burruss Hall,
800 Drillfield Drive,
Blacksburg, VA 24061
e-mail: sekkad@vt.edu
Search for other works by this author on:
Wing Ng,
Wing Ng
Department of Mechanical Engineering,
Virginia Tech,
425 Goodwin Hall (0238),
635 Prices Fork Road,
Blacksburg, VA 24061
e-mail: wng@vt.edu
Virginia Tech,
425 Goodwin Hall (0238),
635 Prices Fork Road,
Blacksburg, VA 24061
e-mail: wng@vt.edu
Search for other works by this author on:
Michael E. Crawford
Michael E. Crawford
Search for other works by this author on:
Kapil V. Panchal
Santosh Abraham
Siemens Energy, Inc.,
5101 Westinghouse Boulevard,
Charlotte, NC 28273-9640
e-mail: santosh.abraham@siemens.com
5101 Westinghouse Boulevard,
Charlotte, NC 28273-9640
e-mail: santosh.abraham@siemens.com
Arnab Roy
Srinath V. Ekkad
Department of Mechanical Engineering,
301 Burruss Hall,
800 Drillfield Drive,
Blacksburg, VA 24061
e-mail: sekkad@vt.edu
301 Burruss Hall,
800 Drillfield Drive,
Blacksburg, VA 24061
e-mail: sekkad@vt.edu
Wing Ng
Department of Mechanical Engineering,
Virginia Tech,
425 Goodwin Hall (0238),
635 Prices Fork Road,
Blacksburg, VA 24061
e-mail: wng@vt.edu
Virginia Tech,
425 Goodwin Hall (0238),
635 Prices Fork Road,
Blacksburg, VA 24061
e-mail: wng@vt.edu
Andrew S. Lohaus
Michael E. Crawford
1Corresponding author.
2Present address: National Energy Technology Laboratory, Morgantown, WV 26507.
Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received March 4, 2016; final manuscript received July 22, 2016; published online September 20, 2016. Assoc. Editor: Jim Downs.
J. Turbomach. Jan 2017, 139(1): 011009 (11 pages)
Published Online: September 20, 2016
Article history
Received:
March 4, 2016
Revised:
July 22, 2016
Citation
Panchal, K. V., Abraham, S., Roy, A., Ekkad, S. V., Ng, W., Lohaus, A. S., and Crawford, M. E. (September 20, 2016). "Effect of Endwall Contouring on a Transonic Turbine Blade Passage: Heat Transfer Performance." ASME. J. Turbomach. January 2017; 139(1): 011009. https://doi.org/10.1115/1.4034411
Download citation file:
Get Email Alerts
Related Articles
Investigation of Unsteady Flow Phenomena in First Vane Caused by Combustor Flow With Swirl
J. Turbomach (April,2017)
EFFECTS OF LOCALIZED NON-GAUSSIAN ROUGHNESS ON HIGH PRESSURE TURBINE AERO-THERMAL PERFORMANCE: CONVECTIVE HEAT TRANSFER, SKIN-FRICTION AND THE REYNOLDS' ANALOGY
J. Turbomach (January,0001)
Advanced Design of a Transition Duct for Supersonic Inlet Turbines in Rotating Detonation Engines
J. Turbomach (January,0001)
ON THE APPLICATION OF BACKGROUND ORIENTED SCHLIEREN TO A TRANSONIC LOW-REYNOLDS TURBINE CASCADE
J. Turbomach (January,0001)
Related Proceedings Papers
Related Chapters
The Special Characteristics of Closed-Cycle Gas Turbines
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Outlook
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Mixed-Up Convection
Hot Air Rises and Heat Sinks: Everything You Know about Cooling Electronics Is Wrong