Rotating Stall Control in a High-Speed Stage With Inlet Distortion: Part I—Radial DistortionSource: Journal of Turbomachinery:;1999:;volume( 121 ):;issue: 003::page 510Author:Z. S. Spakovszky
,
C. M. van Schalkwyk
,
K. L. Suder
,
M. M. Bright
,
H. J. Weigl
,
J. D. Paduano
DOI: 10.1115/1.2841345Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: This paper presents the first attempt to stabilize rotating stall in a single-stage transonic axial flow compressor with inlet distortion using active feedback control. The experiments were conducted at the NASA Lewis Research Center on a single-stage transonic core compressor inlet stage. An annular array of 12 jet-injectors located upstream of the rotor tip was used for forced response testing and to extend the compressor stable operating range. Results for radial distortion are reported in this paper. First, the effects of radial distortion on the compressor performance and the dynamic behavior were investigated. Control laws were designed using empirical transfer function estimates determined from forced response results. The transfer functions indicated that the compressor dynamics are decoupled with radial inlet distortion, as they are for the case of undistorted inlet flow. Single-input-single-output (SISO) control strategies were therefore used for the radial distortion controller designs. Steady axisymmetric injection of 4 percent of the compressor mass flow resulted in a reduction in stalling mass flow of 9.7 percent relative to the case with inlet distortion and no injection. Use of a robust H∞ controller with unsteady nonaxisymmetric injection achieved a further reduction in stalling mass flow of 7.5 percent, resulting in a total reduction of 17.2 percent.
keyword(s): Dynamics (Mechanics) , Flow (Dynamics) , Control equipment , Compressors , Transfer functions , Ejectors , Rotors , Testing , Axial flow AND Feedback ,
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contributor author | Z. S. Spakovszky | |
contributor author | C. M. van Schalkwyk | |
contributor author | K. L. Suder | |
contributor author | M. M. Bright | |
contributor author | H. J. Weigl | |
contributor author | J. D. Paduano | |
date accessioned | 2017-05-09T00:01:14Z | |
date available | 2017-05-09T00:01:14Z | |
date copyright | July, 1999 | |
date issued | 1999 | |
identifier issn | 0889-504X | |
identifier other | JOTUEI-28670#510_1.pdf | |
identifier uri | http://yetl.yabesh.ir/yetl/handle/yetl/123007 | |
description abstract | This paper presents the first attempt to stabilize rotating stall in a single-stage transonic axial flow compressor with inlet distortion using active feedback control. The experiments were conducted at the NASA Lewis Research Center on a single-stage transonic core compressor inlet stage. An annular array of 12 jet-injectors located upstream of the rotor tip was used for forced response testing and to extend the compressor stable operating range. Results for radial distortion are reported in this paper. First, the effects of radial distortion on the compressor performance and the dynamic behavior were investigated. Control laws were designed using empirical transfer function estimates determined from forced response results. The transfer functions indicated that the compressor dynamics are decoupled with radial inlet distortion, as they are for the case of undistorted inlet flow. Single-input-single-output (SISO) control strategies were therefore used for the radial distortion controller designs. Steady axisymmetric injection of 4 percent of the compressor mass flow resulted in a reduction in stalling mass flow of 9.7 percent relative to the case with inlet distortion and no injection. Use of a robust H∞ controller with unsteady nonaxisymmetric injection achieved a further reduction in stalling mass flow of 7.5 percent, resulting in a total reduction of 17.2 percent. | |
publisher | The American Society of Mechanical Engineers (ASME) | |
title | Rotating Stall Control in a High-Speed Stage With Inlet Distortion: Part I—Radial Distortion | |
type | Journal Paper | |
journal volume | 121 | |
journal issue | 3 | |
journal title | Journal of Turbomachinery | |
identifier doi | 10.1115/1.2841345 | |
journal fristpage | 510 | |
journal lastpage | 516 | |
identifier eissn | 1528-8900 | |
keywords | Dynamics (Mechanics) | |
keywords | Flow (Dynamics) | |
keywords | Control equipment | |
keywords | Compressors | |
keywords | Transfer functions | |
keywords | Ejectors | |
keywords | Rotors | |
keywords | Testing | |
keywords | Axial flow AND Feedback | |
tree | Journal of Turbomachinery:;1999:;volume( 121 ):;issue: 003 | |
contenttype | Fulltext |