EXPERIMENTAL INVESTIGATION OF UNSTEADY FLOW IN A TRANSONIC UNI-STAGE AXIAL COMPRESSOR

被引:0
作者
Kumar, S. Satish [1 ]
Alone, Dilipkumar Bhanudasji [1 ]
Thimmaiah, Shobhavathy M. [1 ]
Mudipalli, Janaki Rami Reddy [1 ]
Ganguli, Ranjan [2 ]
Kandagal, S. B. [2 ]
Jana, Soumendu [1 ]
机构
[1] CSIR Natl Aerosp Labs, Bangalore, Karnataka, India
[2] Indian Inst Sci, Bangalore 560012, Karnataka, India
来源
PROCEEDINGS OF THE ASME GAS TURBINE INDIA CONFERENCE, 2014 | 2014年
关键词
transonic axial compressor; rotating stall; unsteady flow; FFT; STALL INCEPTION; ROTATING STALL; SPIKE;
D O I
暂无
中图分类号
TH [机械、仪表工业];
学科分类号
0802 ;
摘要
Detailed steady and unsteady experimental measurements and analysis were performed on a Single stage Transonic Axial Compressor with asymmetric rotor tip clearance for studying the compressor stall phenomena. The installed compressor had asymmetric tip clearance around the rotor casing varying from about 0.65mm to 1.25mm. A calibrated 5-hole aerodynamic probe was traversed radially at exit of rotor and showed the characteristics of increased flow angle at lower mass flow rates for all the speeds. Mach number distribution and boundary layer effects were also clearly captured. Unsteady measurements for velocity were carried out to study the stall cell behavior using a single component calibrated hotwire probe oriented in axial and tangential directions for choke/free flow and near stall conditions. The hotwire probe was traversed radially across the annulus at inlet to the compressor and showed that the velocity fluctuations were dissimilar when probe was aligned axial and tangential to the flow. Averaged velocities across the annulus showed the reduction in velocity as stall was approached. Axial mean flow velocity decreased across the annulus for all the speeds investigated. Tangential velocity at free flow condition was higher at the tip region due to larger radius. At stall condition, the tangential velocity showed decreased velocities at the tip and slightly increased velocities at the hub section indicating that the flow has breakdown at the tip region of the blade and fluid is accelerated below the blockage zone. The averaged turbulent intensity in axial and tangential flow directions increased from free flow to stall condition for all compressor rated speeds. Fast Fourier Transform (FFT) of the raw signals at stall flow condition showed stall cell and its corresponding frequency of occurrence. The stalling frequency of about half of rotational speed of the rotor along with large tip clearance suggests that modal type stall inception was occurring.
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页数:8
相关论文
共 17 条
[1]  
Cameron J.D., 2007, THESIS U NOTRE DAME
[2]   A study of spike and modal stall phenomena in a low-speed axial compressor [J].
Camp, TR ;
Day, IJ .
JOURNAL OF TURBOMACHINERY-TRANSACTIONS OF THE ASME, 1998, 120 (03) :393-401
[3]   Prestall behavior of a transonic axial compressor stage via time-accurate numerical simulation [J].
Chen, Jen-Ping ;
Hathaway, Michael D. ;
Herrick, Gregory P. .
JOURNAL OF TURBOMACHINERY-TRANSACTIONS OF THE ASME, 2008, 130 (04)
[4]   Effects of Fan Speed on Rotating Stall Inception and Recovery [J].
Choi, Minsuk ;
Vahdati, Mehdi ;
Imregun, Mehmet .
JOURNAL OF TURBOMACHINERY-TRANSACTIONS OF THE ASME, 2011, 133 (04)
[5]   Stall inception and the prospects for active control in four high-speed compressors [J].
Day, IJ ;
Breuer, T ;
Escuret, J ;
Cherrett, M ;
Wilson, A .
JOURNAL OF TURBOMACHINERY-TRANSACTIONS OF THE ASME, 1999, 121 (01) :18-27
[6]   STALL INCEPTION IN AXIAL-FLOW COMPRESSORS [J].
DAY, IJ .
JOURNAL OF TURBOMACHINERY-TRANSACTIONS OF THE ASME, 1993, 115 (01) :1-9
[7]   The role of tip leakage vortex breakdown in compressor rotor aerodynamics [J].
Furukawa, M ;
Inoue, M ;
Saiki, K ;
Yamada, K .
JOURNAL OF TURBOMACHINERY-TRANSACTIONS OF THE ASME, 1999, 121 (03) :469-480
[8]   Role of blade passage flow structures in axial compressor rotating stall inception [J].
Hoying, DA ;
Tan, CS ;
Vo, HD ;
Greitzer, EM .
JOURNAL OF TURBOMACHINERY-TRANSACTIONS OF THE ASME, 1999, 121 (04) :735-742
[9]   Short and long length-scale disturbances leading to rotating stall in an axial compressor stage with different stator/rotor gaps [J].
Inoue, M ;
Kuroumaru, M ;
Yoshida, S ;
Furukawa, M .
JOURNAL OF TURBOMACHINERY-TRANSACTIONS OF THE ASME, 2002, 124 (03) :376-384
[10]   Endwall blockage in axial compressors [J].
Khalid, SA ;
Khalsa, AS ;
Waitz, IA ;
Tan, CS ;
Greitzer, EM ;
Cumpsty, NA ;
Adamczyk, JJ ;
Marble, FE .
JOURNAL OF TURBOMACHINERY-TRANSACTIONS OF THE ASME, 1999, 121 (03) :499-509