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Thermal Performance of Cooled Tips in a High-Pressure Turbine Cascade


Reference:

Zhou, C., Hodson, H. and Lock, G., 2012. Thermal Performance of Cooled Tips in a High-Pressure Turbine Cascade. Journal of Propulsion and Power, 28 (5), pp. 900-911.

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Official URL:

http://dx.doi.org/10.2514/1.B34299

Abstract

The thermal performance of the three turbine tips was investigated. The results are presented in terms of heattransfer coefficient (h), cooling effectiveness (η), net heat-flux reduction (NHFR), and heat load. The calculations were performed using a cooled flat tip, a cooled cavity tip, and a cooled suction-side squealer tip in a cascade at a tip gap of 1.6%C. The results were validated using experimental data where possible. For an uncooled flat tip, the fluid dynamics are dominated by flow separation at the pressure-side edge. A significant benefit of ejecting coolant inside this separation bubble is shown. At the coolant mass-flow ratio M c = 0:52%, both the cooled flat tip and the cooled cavity tip are well-protected by the coolant. For the cooled suction-side squealer tip, the coolant lifts off from the tip floor and leads to not only low cooling effectiveness, but also to high heat-transfer coefficients. The effects of the coolant mass-flow ratio on the thermal performance of the tip were presented. The effects of end-wall motion on the thermal performance of the blade tip are found to be small in the current study.

Details

Item Type Articles
CreatorsZhou, C., Hodson, H. and Lock, G.
DOI10.2514/1.B34299
DepartmentsFaculty of Engineering & Design > Mechanical Engineering
Research CentresAerospace Engineering Research Centre
RefereedYes
StatusPublished
ID Code32114

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