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Dongjie Yan, Hongmei Jiang, Jieling Li, Wenbo Xie, Zhaoguang Wang, Shaopeng Lu and Qiang Zhang
In high-pressure turbines, there is a large difference in temperature between the mainstream and the turbine blade surface. Most of the turbine blade tip heat transfer studies were conducted under the assumption that the Over-Tip-Leakage (OTL) flow field...
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Bogdan C. Cernat and Sergio Lavagnoli
The present research focused on the analysis of the leakage flows developing from advanced blade tip geometries. The aerodynamic field of a contoured blade tip and of a high-performance rimmed blade were investigated against a baseline squealer rotor. Ti...
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Manuel Wilhelm and Heinz-Peter Schiffer
Rotor tip film cooling is investigated at the Large Scale Turbine Rig, which is a 1.5-stage axial turbine rig operating at low speeds. Using pressure sensitive paint, the film cooling effectiveness η" role="presentation">???
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at a squealer-ty...
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Stefano Caloni, Shahrokh Shahpar and Vassili V. Toropov
The turbine tip geometry can significantly alter the performance of the turbine stage; its design represents a challenge for a variety of reasons. Multiple disciplines are involved in its design and their requirements limit the creativity of the designer...
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Song Xue and Wing F. Ng
This article provides an overview of gas turbine blade tip external cooling technologies. It is not the intention to comprehensively review all the publications from past to present. Instead, selected reports, which represent the most recent progress in ...
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Shantanu Mhetras, Diganta Narzary, Zhihong Gao, and Je-Chin Han
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Nicole L. Key and Tony Arts
Pág. 213 - 220
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Cengiz Camci, Debashis Dey, and Levent Kavurmacioglu
Pág. 14 - 24
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Hasan Nasir, Srinath V. Ekkad, David M. Kontrovitz, Ronald S. Bunker, and Chander Prakash
Pág. 221 - 228
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Jae Su Kwak and Je-Chin Han
Pág. 648 - 657
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