scholarly journals Control of rotating stall in a low-speed axial flow compressor using pulsed air injection: modeling, simulations, and experimental validation

2002 ◽  
Author(s):  
R.L. Behnken ◽  
R. D'Andrea ◽  
R.M. Murray
Keyword(s):  
Experimental Validation ◽  
Axial Flow ◽  
Rotating Stall ◽  
Air Injection ◽  
Low Speed ◽  
Axial Flow Compressor ◽  
Flow Compressor

Rotating Stall Control of an Axial Flow Compressor Using Pulsed Air Injection

1997 ◽  
Vol 119 (4) ◽  
pp. 742-752 ◽  
Author(s):  
R. D’Andrea ◽  
R. L. Behnken ◽  
R. M. Murray
Keyword(s):  
Axial Flow ◽  
Rotating Stall ◽  
Experimental Results ◽  
Air Injection ◽  
Nonlinear Feedback ◽  
Axial Flow Compressor ◽  
Flow Compressor ◽  
Low Dimensional ◽  
Stall Control ◽  
Fidelity Model

This paper presents the use of pulsed air injection to control rotating stall in a low-speed, axial flow compressor. In the first part of the paper, the injection of air is modeled as an unsteady shift of the compressor characteristic, and incorporated into a low dimensional model of the compressor. By observing the change in the bifurcation behavior of this model subject to nonlinear feedback, the viability of various air injection orientations is established. An orientation consistent with this analysis is then used for feedback control. By measuring the unsteady pressures near the rotor face, a control algorithm determines the magnitude and phase of the first mode of rotating stall and controls the injection of air in the front of the rotor face. Experimental results show that this technique eliminates the hysteresis loop normally associated with rotating stall. A parametric study is used to determine the optimal control parameters for suppression of stall. The resulting control strategy is also shown to suppress surge when a plenum is present. Using a high-fidelity model, the main features of the experimental results are duplicated via simulations.

Rotating stall cells in a low-speed axial flow compressor

1985 ◽  
Vol 22 (3) ◽  
pp. 175-181 ◽  
Author(s):  
F. A. E. Breugelmans ◽  
K. Mathioudakis ◽  
F. Casalini
Keyword(s):  
Axial Flow ◽  
Rotating Stall ◽  
Low Speed ◽  
Axial Flow Compressor ◽  
Stall Cells ◽  
Flow Compressor

Optimized Preliminary Design of a Multistage Low-Speed Axial FLow Compressor

2021 ◽  
Author(s):  
AbdelRahman Ahmed Kamal ◽  
Alyaa Abdelnaby Thabet ◽  
Mohamed M. A. Elnabawy
Keyword(s):  
Axial Flow ◽  
Preliminary Design ◽  
Low Speed ◽  
Axial Flow Compressor ◽  
Flow Compressor

Distributed Control of Rotating Stall in an Axial Flow Compressor With Actuator Constraints

2000 ◽  
Author(s):  
Craig A. Buhr ◽  
Matthew A. Franchek ◽  
Sanford Fleeter
Keyword(s):  
Absolute Stability ◽  
Closed Loop ◽  
Axial Flow ◽  
Gain Control ◽  
Rotating Stall ◽  
Control Law ◽  
Circle Criterion ◽  
Axial Flow Compressor ◽  
Flow Compressor ◽  
Stall Control

Abstract Presented in this paper is an analytical study evaluating the closed loop stability of rotating stall control in an axial flow compressor subject to a nonlinear spatial actuation constraint that limits the amplitude of a spatial mode input. Absolute stability of the rotating stall control system is investigated by applying the circle criterion to a linearized model of an axial compressor in series with the saturation element. This stability analysis is then used to design the gain and phase of the ‘classical’ complex gain feedback control law. Resulting is a systematic method for designing the parameters of the complex gain control law which increases the region of absolute stability guaranteed by the circle criterion for the closed-loop system.

Numerical Simulation of Steady Air Injection Flow Control Effects on a Transonic Axial Flow Compressor

2012 ◽  
Vol 224 ◽  
pp. 352-357
Author(s):  
Islem Benhegouga ◽  
Ce Yang
Keyword(s):  
Mass Flow Rate ◽  
Mass Flow ◽  
Flow Rate ◽  
Pressure Ratio ◽  
Axial Flow ◽  
Leading Edge ◽  
Air Injection ◽  
Axial Flow Compressor ◽  
Blade Tip ◽  
Flow Compressor

In this work, steady air injection upstream of the blade leading edge was used in a transonic axial flow compressor, NASA rotor 37. The injectors were placed at 27 % upstream of the axial chord length at blade tip, the injection mass flow rate is 3% of the chock mass flow rate, and 3 yaw angles were used, respectively -20°, -30°, and -40°. Negative yaw angles were measured relative to the compressor face in opposite direction of rotational speeds. To reveal the mechanism, steady numerical simulations were performed using FINE/TURBO software package. The results show that the stall mass flow can be decreased about 2.5 %, and an increase in the total pressure ratio up to 0.5%.

1118 Effect of Tip Clearance on Rotating Stall Inception in an Axial Flow Compressor Rotor

2009 ◽  
Vol 2009 (0) ◽  
pp. 377-378 ◽  
Author(s):  
Hiroaki KIKUTA ◽  
Masato FURUKAWA ◽  
Satoshi GUNJISHIMA ◽  
Kenichiro IWAKIRI ◽  
Takuro KAMEDA
Keyword(s):  
Axial Flow ◽  
Rotating Stall ◽  
Tip Clearance ◽  
Stall Inception ◽  
Axial Flow Compressor ◽  
Compressor Rotor ◽  
Flow Compressor

2415 Effect of Tip Clearance on Structure of Rotating Stall Cell in an Axial Flow Compressor Rotor

2006 ◽  
Vol 2006.2 (0) ◽  
pp. 149-150
Author(s):  
Sho BONKOHARA ◽  
Ken-ichiro IWAKIRI ◽  
Ryusuke OHTAGURO ◽  
Yasuhiro SHIBAMOTO ◽  
Masato FURUKAWA
Keyword(s):  
Axial Flow ◽  
Rotating Stall ◽  
Tip Clearance ◽  
Axial Flow Compressor ◽  
Compressor Rotor ◽  
Flow Compressor

Experimental investigations on instability evolution in a transonic compressor at different rotor speeds

2015 ◽  
Vol 229 (18) ◽  
pp. 3378-3391 ◽  
Author(s):  
Qiushi Li ◽  
Tianyu Pan ◽  
Tailu Sun ◽  
Zhiping Li ◽  
Yifang Gong
Keyword(s):  
Low Frequency ◽  
Axial Flow ◽  
Rotating Stall ◽  
Operating Conditions ◽  
Experimental Investigations ◽  
Rotor Speed ◽  
Axial Flow Compressor ◽  
Transonic Compressor ◽  
New Type ◽  
Flow Compressor

Experimental investigations are conducted to study the instability evolution in a transonic axial flow compressor at four specific rotor speeds covering both subsonic and transonic operating conditions. Two routes of evolution to final instability are observed in the test compressor: at low rotor speeds, a disturbance in the rotor tip region occurs and then leads to rotating stall, while at high rotor speeds, a low-frequency disturbance in the hub region leads the compressor into instability. Different from stall and surge, this new type of compressor instability at high rotor speed is initiated through the development of a low-frequency axisymmetric disturbance at the hub, and we name it “partial surge”. The frequency of this low-frequency disturbance is approximately the Helmholtz frequency of the system and remains constant during instability inception. Finally, a possible mechanism for the occurrence of different instability evolutions and the formation of partial surge are also discussed.

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