In Part 1 of this paper it was shown that discrete jets issuing from a tip platform trench were successful in reducing the total pressure deficit due to tip leakage flow. The specific tip cooling system used in Part 1 had all four injection locations active. This paper examines the effect of the individual location of the injection hole on the tip leakage flow. The investigation was carried out in a large-scale rotating rig. Total pressure downstream of the rotor exit was measured using a Kulite sensor. The measurements were phase-locked and ensemble averaged over 200 rotor revolutions. The injection holes are located at 61%, 71%, 81%, and 91% blade axial chord, in the tip trench of a single blade with a clearance of 1.40% blade height. Individual injection at 61% and 71% chord reduced the leakage vortex size. Coolant injection at 81% chord was the most successful in reducing the total pressure deficit in the leakage vortex. Injection from 91% chord had no effect on the leakage vortex. Injection from combinations of holes had greater effect in reducing the leakage vortex size and the total pressure deficit associated with the vortex. It can be concluded that the individual jets most likely turn the leakage flow towards the trailing edge. Most of the leakage flow that is responsible for the greatest total pressure deficit occurs around 80% chord.
Skip Nav Destination
ASME Turbo Expo 2004: Power for Land, Sea, and Air
June 14–17, 2004
Vienna, Austria
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
0-7918-4170-7
PROCEEDINGS PAPER
Axial Turbine Tip Desensitization by Injection From a Tip Trench: Part 2 — Leakage Flow Sensitivity to Injection Location
Nikhil M. Rao,
Nikhil M. Rao
Pennsylvania State University, University Park, PA
Search for other works by this author on:
Cengiz Camci
Cengiz Camci
Pennsylvania State University, University Park, PA
Search for other works by this author on:
Nikhil M. Rao
Pennsylvania State University, University Park, PA
Cengiz Camci
Pennsylvania State University, University Park, PA
Paper No:
GT2004-53258, pp. 1089-1098; 10 pages
Published Online:
November 24, 2008
Citation
Rao, NM, & Camci, C. "Axial Turbine Tip Desensitization by Injection From a Tip Trench: Part 2 — Leakage Flow Sensitivity to Injection Location." Proceedings of the ASME Turbo Expo 2004: Power for Land, Sea, and Air. Volume 5: Turbo Expo 2004, Parts A and B. Vienna, Austria. June 14–17, 2004. pp. 1089-1098. ASME. https://doi.org/10.1115/GT2004-53258
Download citation file:
44
Views
Related Proceedings Papers
Related Articles
Tip Clearance Effects in a Turbine Rotor: Part II—Velocity Field and Flow Physics
J. Turbomach (April,2001)
Investigation of Three-Dimensional Unsteady Flows in a Two-Stage Shrouded Axial Turbine Using Stereoscopic PIV—Kinematics of Shroud Cavity Flow
J. Turbomach (January,2008)
The Tip Leakage Flow of an Unshrouded High Pressure Turbine Blade With Tip Cooling
J. Turbomach (October,2011)
Related Chapters
Aerodynamic Performance Analysis
Axial-Flow Compressors
Fans and Air Handling Systems
Thermal Management of Telecommunications Equipment
Engineering and Physical Modeling of Power Plant Cooling Systems
Thermal Power Plant Cooling: Context and Engineering