One of the most critical gas turbine engine components, rotor blade tip and casing, are exposed to high thermal load. It becomes a significant design challenge to protect the turbine materials from this severe situation. As a result of geometric complexity and experimental limitations, Computational Fluid Dynamics (CFD) tools have been used to predict blade tip leakage flow aerodynamics and heat transfer at typical engine operating conditions. In this paper, the effect of turbine inlet temperature on the tip leakage flow structure and heat transfer has been studied numerically. Uniform low (LTIT: 444 K) and high (HTIT: 800 K) turbine inlet temperature have been considered. The results showed the higher turbine inlet temperature yields the higher velocity and temperature variations in the leakage flow aerodynamics and heat transfer. For a given turbine geometry and on-design operating conditions, the turbine power output can be increased by 1.48 times, when the turbine inlet temperature increases 1.80 times. Whereas the averaged heat fluxes on the casing and the blade tip become 2.71 and 2.82 times larger, respectively. Therefore, about 2.8 times larger cooling capacity is required to keep the same turbine material temperature. Furthermore, the maximum heat flux on the blade tip of high turbine inlet temperature case reaches up to 3.348 times larger than that of LTIT case. The effect of the interaction of stator and rotor on heat transfer features is also explored using unsteady simulations.
Skip Nav Destination
ASME Turbo Expo 2009: Power for Land, Sea, and Air
June 8–12, 2009
Orlando, Florida, USA
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
978-0-7918-4888-3
PROCEEDINGS PAPER
Effect of Turbine Inlet Temperature on Blade Tip Leakage Flow and Heat Transfer
Sung In Kim,
Sung In Kim
Concordia University, Montreal, QC, Canada
Search for other works by this author on:
Md Hamidur Rahman,
Md Hamidur Rahman
Concordia University, Montreal, QC, Canada
Search for other works by this author on:
Ibrahim Hassan
Ibrahim Hassan
Concordia University, Montreal, QC, Canada
Search for other works by this author on:
Sung In Kim
Concordia University, Montreal, QC, Canada
Md Hamidur Rahman
Concordia University, Montreal, QC, Canada
Ibrahim Hassan
Concordia University, Montreal, QC, Canada
Paper No:
GT2009-60143, pp. 1773-1782; 10 pages
Published Online:
February 16, 2010
Citation
Kim, SI, Rahman, MH, & Hassan, I. "Effect of Turbine Inlet Temperature on Blade Tip Leakage Flow and Heat Transfer." Proceedings of the ASME Turbo Expo 2009: Power for Land, Sea, and Air. Volume 7: Turbomachinery, Parts A and B. Orlando, Florida, USA. June 8–12, 2009. pp. 1773-1782. ASME. https://doi.org/10.1115/GT2009-60143
Download citation file:
16
Views
Related Proceedings Papers
Related Articles
Effects of Inlet Temperature Uniformity and Nonuniformity on the Tip Leakage Flow and Rotor Blade Tip and Casing Heat Transfer Characteristics
J. Turbomach (March,2012)
Aerodynamics and Heat Transfer for a Cooled One and One-Half Stage High-Pressure Turbine—Part I: Vane Inlet Temperature Profile Generation and Migration
J. Turbomach (January,2012)
Influence of Stator-Rotor Interaction on the Aerothermal Performance of Recess Blade Tips
J. Turbomach (January,2011)
Related Chapters
Control and Operational Performance
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Outlook
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Introduction
Consensus on Operating Practices for Control of Water and Steam Chemistry in Combined Cycle and Cogeneration