Detection of a Rotating Stall Precursor in Isolated Axial Flow Compressor Rotors

1991 ◽  
Vol 113 (2) ◽  
pp. 281-287 ◽  
Author(s):  
M. Inoue ◽  
M. Kuroumaru ◽  
T. Iwamoto ◽  
Y. Ando
Keyword(s):  
Pressure Sensor ◽  
Pressure Fluctuation ◽  
Axial Flow ◽  
Leading Edge ◽  
Rotating Stall ◽  
Statistical Characteristics ◽  
Flow Passage ◽  
Axial Flow Compressor ◽  
Flow Compressor ◽  
Stall Precursor

Statistical characteristics of pressure fluctuation on the casing wall of two axial flow compressor rotors have been investigated experimentally to find a precursor of rotating stall. Near stall, the casing wall pressure across a flow passage near the leading edge is characterized by a highly unsteady region where low-momentum fluid accumulates. The periodicity of the pressure fluctuation with blade spacing disappears and an alternative phenomenon comes into existence, which supports the disturbance propagating at a different speed from the rotor revolution. The precursor of rotating stall can be detected by monitoring collapse of the periodicity in the pressure fluctuation. To represent the periodicity qualitatively, a practical detection parameter has been proposed, which is easily obtained from signals of a single pressure sensor installed at an appropriate position on the casing wall during operation of a 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.

Characteristics of Surge and Rotating Stall in a Three-Stage Axial Flow Compressor Using Shock Tube

2011 ◽  
Author(s):  
Daisuke Morita ◽  
Yutaka Fujita ◽  
Yutaka Ohta ◽  
Eisuke Outa
Keyword(s):  
Plane Wave ◽  
Shock Tube ◽  
Axial Flow ◽  
Stable Condition ◽  
Rotating Stall ◽  
Operating Conditions ◽  
Research Attention ◽  
Axial Flow Compressor ◽  
Wall Pressure Fluctuations ◽  
Flow Compressor

Transient characteristics as well as unsteady cascade flow fields of a three-stage axial flow compressor with compression plane wave injection from the compressor downstream were experimentally investigated by detail measurements of casing wall pressure fluctuations and unsteady velocity. The main feature of tested compressor is a shock tube facility connected in series to the compressor outlet duct in order to supply a compression plane wave which simulates the sudden rise of the compressor back pressure in a gas turbine system. Research attention is mainly focused on the unsteady behavior of surge and rotating stall coexistence phenomenon, and influence of the compression plane wave injection on the compressor operating conditions. When the compressor is connected to the capacity tank, surge and rotating stall occur simultaneously according to the capacitance increment of the whole compression system. The surge cycle changes irregularly with a throttling of the valve installed just behind the compressor and several different types of surge behaviors are observed. Furthermore, even though the compressor is operating under the stable condition, it goes into surge by injecting the compression plane wave.

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