某大折转角压气机静叶分叉改型设计及其尾迹流场

Huanlong Chen; Linxi Li; Huaping Liu; Menghan Yu

doi:10.13224/j.cnki.jasp.2018.06.012

某大折转角压气机静叶分叉改型设计及其尾迹流场

Translated title of the contribution: Redesign and wake flow field for a compressor high-turning stator with bifurcate blade

Huanlong Chen
, Linxi Li
, Huaping Liu
, Menghan Yu

School of Energy Science and Engineering, Harbin Institute of Technology

Research output: Contribution to journal › Article › peer-review

2 Scopus citations

Abstract

For large scale flow separation problem caused by strong adverse pressure gradient in high-loaded fan/compressor cascade passage, a bifurcate blade was designed by using the three-dimensional blade geometry building technology according to increased solidity, so as to abate pressure gradient in passage flow, and numerical simulation method was adopted to predict and discuss aerodynamic performance and wake flow field characteristics for the design. The results indicated that, compared with baseline blade passage, the energy loss and wake loss decreased as well as flow turning capability was enhanced at 0° and positive incidence angles for bifurcate blade passage.

Translated title of the contribution	Redesign and wake flow field for a compressor high-turning stator with bifurcate blade
Original language	Chinese (Traditional)
Pages (from-to)	1381-1392
Number of pages	12
Journal	Hangkong Dongli Xuebao/Journal of Aerospace Power
Volume	33
Issue number	6
DOIs	https://doi.org/10.13224/j.cnki.jasp.2018.06.012
State	Published - 1 Jun 2018
Externally published	Yes

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10.13224/j.cnki.jasp.2018.06.012

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title = "某大折转角压气机静叶分叉改型设计及其尾迹流场",

abstract = "For large scale flow separation problem caused by strong adverse pressure gradient in high-loaded fan/compressor cascade passage, a bifurcate blade was designed by using the three-dimensional blade geometry building technology according to increased solidity, so as to abate pressure gradient in passage flow, and numerical simulation method was adopted to predict and discuss aerodynamic performance and wake flow field characteristics for the design. The results indicated that, compared with baseline blade passage, the energy loss and wake loss decreased as well as flow turning capability was enhanced at 0° and positive incidence angles for bifurcate blade passage.",

keywords = "Bifurcate blade, Compressor cascade, Pressure gradient, Secondary flow, Wake",

author = "Huanlong Chen and Linxi Li and Huaping Liu and Menghan Yu",

year = "2018",

month = jun,

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doi = "10.13224/j.cnki.jasp.2018.06.012",

language = "繁体中文",

volume = "33",

pages = "1381--1392",

journal = "Hangkong Dongli Xuebao/Journal of Aerospace Power",

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TY - JOUR

T1 - 某大折转角压气机静叶分叉改型设计及其尾迹流场

AU - Chen, Huanlong

AU - Li, Linxi

AU - Liu, Huaping

AU - Yu, Menghan

PY - 2018/6/1

Y1 - 2018/6/1

N2 - For large scale flow separation problem caused by strong adverse pressure gradient in high-loaded fan/compressor cascade passage, a bifurcate blade was designed by using the three-dimensional blade geometry building technology according to increased solidity, so as to abate pressure gradient in passage flow, and numerical simulation method was adopted to predict and discuss aerodynamic performance and wake flow field characteristics for the design. The results indicated that, compared with baseline blade passage, the energy loss and wake loss decreased as well as flow turning capability was enhanced at 0° and positive incidence angles for bifurcate blade passage.

AB - For large scale flow separation problem caused by strong adverse pressure gradient in high-loaded fan/compressor cascade passage, a bifurcate blade was designed by using the three-dimensional blade geometry building technology according to increased solidity, so as to abate pressure gradient in passage flow, and numerical simulation method was adopted to predict and discuss aerodynamic performance and wake flow field characteristics for the design. The results indicated that, compared with baseline blade passage, the energy loss and wake loss decreased as well as flow turning capability was enhanced at 0° and positive incidence angles for bifurcate blade passage.

KW - Bifurcate blade

KW - Compressor cascade

KW - Pressure gradient

KW - Secondary flow

KW - Wake

UR - https://www.scopus.com/pages/publications/85052955404

U2 - 10.13224/j.cnki.jasp.2018.06.012

DO - 10.13224/j.cnki.jasp.2018.06.012

M3 - 文章

AN - SCOPUS:85052955404

SN - 1000-8055

VL - 33

SP - 1381

EP - 1392

JO - Hangkong Dongli Xuebao/Journal of Aerospace Power

JF - Hangkong Dongli Xuebao/Journal of Aerospace Power

IS - 6

ER -

某大折转角压气机静叶分叉改型设计及其尾迹流场

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