Discharge coefficient measurements for film cooling holes on blade surface in a turbine cascade

An Ding Xiang; Hui Ren Zhu; Song Ling Liu; Du Chun Xu; Wen Guo

Discharge coefficient measurements for film cooling holes on blade surface in a turbine cascade

An Ding Xiang, Hui Ren Zhu, Song Ling Liu, Du Chun Xu, Wen Guo

动力与能源学院

科研成果: 期刊稿件 › 文章 › 同行评审

8 引用（Scopus）

摘要

Discharge coefficients of film cooling holes were investigated on the turbine blade surface with a large-scale low speed turbine cascade. Discharge coefficients with coolant injection were determined at different blowing ratio and Reynolds number. Results show that turbine blade surface film holes discharge coefficients are different greatly in different hole array position. The distribution of discharge coefficients is mainly determined by blowing ratio for same geometry.

源语言	英语
页（从-至）	216-218+239
期刊	Tuijin Jishu/Journal of Propulsion Technology
卷	24
期	3
出版状态	已出版 - 6月 2003

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引用此

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title = "Discharge coefficient measurements for film cooling holes on blade surface in a turbine cascade",

abstract = "Discharge coefficients of film cooling holes were investigated on the turbine blade surface with a large-scale low speed turbine cascade. Discharge coefficients with coolant injection were determined at different blowing ratio and Reynolds number. Results show that turbine blade surface film holes discharge coefficients are different greatly in different hole array position. The distribution of discharge coefficients is mainly determined by blowing ratio for same geometry.",

keywords = "Experiment, Film cooling, Flow coefficient, Gas hole, Turbine blade",

author = "Xiang, {An Ding} and Zhu, {Hui Ren} and Liu, {Song Ling} and Xu, {Du Chun} and Wen Guo",

year = "2003",

month = jun,

language = "英语",

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T1 - Discharge coefficient measurements for film cooling holes on blade surface in a turbine cascade

AU - Xiang, An Ding

AU - Zhu, Hui Ren

AU - Liu, Song Ling

AU - Xu, Du Chun

AU - Guo, Wen

PY - 2003/6

Y1 - 2003/6

N2 - Discharge coefficients of film cooling holes were investigated on the turbine blade surface with a large-scale low speed turbine cascade. Discharge coefficients with coolant injection were determined at different blowing ratio and Reynolds number. Results show that turbine blade surface film holes discharge coefficients are different greatly in different hole array position. The distribution of discharge coefficients is mainly determined by blowing ratio for same geometry.

AB - Discharge coefficients of film cooling holes were investigated on the turbine blade surface with a large-scale low speed turbine cascade. Discharge coefficients with coolant injection were determined at different blowing ratio and Reynolds number. Results show that turbine blade surface film holes discharge coefficients are different greatly in different hole array position. The distribution of discharge coefficients is mainly determined by blowing ratio for same geometry.

KW - Experiment

KW - Film cooling

KW - Flow coefficient

KW - Gas hole

KW - Turbine blade

UR - http://www.scopus.com/inward/record.url?scp=0141679381&partnerID=8YFLogxK

M3 - 文章

AN - SCOPUS:0141679381

SN - 1001-4055

VL - 24

SP - 216-218+239

JO - Tuijin Jishu/Journal of Propulsion Technology

JF - Tuijin Jishu/Journal of Propulsion Technology

IS - 3

ER -

Discharge coefficient measurements for film cooling holes on blade surface in a turbine cascade

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