This paper presents a study of the effects of two types of hub coolant injection on the rotor of a high pressure gas turbine stage. The first involves the leakage flow from the hub cavity into the mainstream. The second involves a deliberate injection of coolant from a row of angled holes from the edge of the stator hub. The aim of this study is to improve the distribution of the injected coolant on the rotor hub wall. To achieve this, it is necessary to understand how the coolant and leakage flows interact with the rotor secondary flows. The first part of the paper shows that the hub leakage flow is entrained into the rotor hub secondary flow and the negative incidence of the leakage strengthens the secondary flow and increases its penetration depth. Three-dimensional unsteady calculations were found to agree with fast response pressure probe measurements at the rotor exit of a low speed test turbine. The second part of the paper shows that increasing the injected coolant swirl angle reduced the secondary flow penetration depth, improves the coolant distribution on the rotor hub, and improves stage efficiency. Most of the coolant however, was still found to be entrained into the rotor secondary flow.
Skip Nav Destination
Article navigation
September 2012
Research Papers
The Effect of Coolant Injection on the Endwall Flow of a High Pressure Turbine
Jonathan Ong,
Jonathan Ong
Whittle Laboratory,
University of Cambridge,
1 JJ Thomson Avenue, Cambridge CB3 0DY, England
e-mail:
Search for other works by this author on:
Robert J. Miller,
Robert J. Miller
Whittle Laboratory, 1 JJ Thomson Avenue, Cambridge CB3 0DY,
England
Search for other works by this author on:
Sumiu Uchida
Sumiu Uchida
Mitsubishi Heavy Industries,
Takasago Research and Development Centre,
1-1, Arai-cho Shinhama 2-chome Takasago, Hyogo Prefecture, 676-8686, Japan
Search for other works by this author on:
Jonathan Ong
Whittle Laboratory,
University of Cambridge,
1 JJ Thomson Avenue, Cambridge CB3 0DY, England
e-mail:
Robert J. Miller
Whittle Laboratory, 1 JJ Thomson Avenue, Cambridge CB3 0DY,
England
Sumiu Uchida
Mitsubishi Heavy Industries,
Takasago Research and Development Centre,
1-1, Arai-cho Shinhama 2-chome Takasago, Hyogo Prefecture, 676-8686, Japan
J. Turbomach. Sep 2012, 134(5): 051003 (8 pages)
Published Online: May 7, 2012
Article history
Received:
January 7, 2011
Revised:
January 8, 2011
Online:
May 7, 2012
Published:
May 7, 2012
Citation
Ong, J., Miller, R. J., and Uchida, S. (May 7, 2012). "The Effect of Coolant Injection on the Endwall Flow of a High Pressure Turbine." ASME. J. Turbomach. September 2012; 134(5): 051003. https://doi.org/10.1115/1.4003838
Download citation file:
Get Email Alerts
Related Articles
The Effect of the Combustor-Turbine Slot and Midpassage Gap on Vane Endwall Heat Transfer
J. Turbomach (October,2011)
Aerothermal Investigation of Tip Leakage Flow in a Film Cooled Industrial Turbine Rotor
J. Turbomach (April,2010)
The Tip Leakage Flow of an Unshrouded High Pressure Turbine Blade With Tip Cooling
J. Turbomach (October,2011)
Aerodynamics of Tip Leakage Flows Near Partial Squealer Rims in an Axial Flow Turbine Stage
J. Turbomach (January,2005)
Related Proceedings Papers
Related Chapters
Outlook
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Tip Leakage Flow In a Mixed-flow Pump
Mixed-flow Pumps: Modeling, Simulation, and Measurements
Numerical Simulation of Tip Leakage Flow and Cavitation Observation on Two-Dimensional Hydrofoil
Proceedings of the 10th International Symposium on Cavitation (CAV2018)