Control of compressor face total pressure distortion on a high bypass turbofan intake using air-jet vortex generators

William Crowther; S. D. Erbslõh; W. J. Crowthert; J. R. Frutos

doi:10.2514/6.2004-2206

Control of compressor face total pressure distortion on a high bypass turbofan intake using air-jet vortex generators

William Crowther, S. D. Erbslõh, W. J. Crowthert, J. R. Frutos

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

Abstract

The control of turbofan intake duct flow separation and the subsequent control of compressor face distortion have the potential to achieve a relaxation of the maximum crosswind constraint at take off. Wind tunnel tests have been conducted using a 10% axis-symmetric scale model. Air jets, simulating micro-electrical mechanical actuators, have been implemented at the intake lip to reenergize the boundary layer locally. Improvements in distortion of up to 40% could be achieved at a 10% engine bleed. © 2004 by the American Institute of Aeronautics and Astronautics, Inc. All rights recived.

Original language	English
Title of host publication	2nd AIAA Flow Control Conference\|2nd AIAA Flow Contr. Conf.
DOIs	https://doi.org/10.2514/6.2004-2206
Publication status	Published - 2004
Event	2nd AIAA Flow Control Conference 2004 - Portland, United States Duration: 28 Jun 2004 → 1 Jul 2004

Conference

Conference	2nd AIAA Flow Control Conference 2004
Country/Territory	United States
City	Portland
Period	28/06/04 → 1/07/04

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10.2514/6.2004-2206

Cite this

@inproceedings{9b0cbf24d2e6468e9c72c49ddf8fe3ed,

title = "Control of compressor face total pressure distortion on a high bypass turbofan intake using air-jet vortex generators",

abstract = "The control of turbofan intake duct flow separation and the subsequent control of compressor face distortion have the potential to achieve a relaxation of the maximum crosswind constraint at take off. Wind tunnel tests have been conducted using a 10% axis-symmetric scale model. Air jets, simulating micro-electrical mechanical actuators, have been implemented at the intake lip to reenergize the boundary layer locally. Improvements in distortion of up to 40% could be achieved at a 10% engine bleed. {\textcopyright} 2004 by the American Institute of Aeronautics and Astronautics, Inc. All rights recived.",

author = "William Crowther and Erbsl{\~o}h, {S. D.} and Crowthert, {W. J.} and Frutos, {J. R.}",

year = "2004",

doi = "10.2514/6.2004-2206",

language = "English",

isbn = "9781624100307",

booktitle = "2nd AIAA Flow Control Conference|2nd AIAA Flow Contr. Conf.",

note = "2nd AIAA Flow Control Conference 2004 ; Conference date: 28-06-2004 Through 01-07-2004",

}

TY - GEN

T1 - Control of compressor face total pressure distortion on a high bypass turbofan intake using air-jet vortex generators

AU - Crowther, William

AU - Erbslõh, S. D.

AU - Crowthert, W. J.

AU - Frutos, J. R.

PY - 2004

Y1 - 2004

N2 - The control of turbofan intake duct flow separation and the subsequent control of compressor face distortion have the potential to achieve a relaxation of the maximum crosswind constraint at take off. Wind tunnel tests have been conducted using a 10% axis-symmetric scale model. Air jets, simulating micro-electrical mechanical actuators, have been implemented at the intake lip to reenergize the boundary layer locally. Improvements in distortion of up to 40% could be achieved at a 10% engine bleed. © 2004 by the American Institute of Aeronautics and Astronautics, Inc. All rights recived.

AB - The control of turbofan intake duct flow separation and the subsequent control of compressor face distortion have the potential to achieve a relaxation of the maximum crosswind constraint at take off. Wind tunnel tests have been conducted using a 10% axis-symmetric scale model. Air jets, simulating micro-electrical mechanical actuators, have been implemented at the intake lip to reenergize the boundary layer locally. Improvements in distortion of up to 40% could be achieved at a 10% engine bleed. © 2004 by the American Institute of Aeronautics and Astronautics, Inc. All rights recived.

U2 - 10.2514/6.2004-2206

DO - 10.2514/6.2004-2206

M3 - Conference contribution

SN - 9781624100307

BT - 2nd AIAA Flow Control Conference|2nd AIAA Flow Contr. Conf.

T2 - 2nd AIAA Flow Control Conference 2004

Y2 - 28 June 2004 through 1 July 2004

ER -

Control of compressor face total pressure distortion on a high bypass turbofan intake using air-jet vortex generators

Abstract

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