Experimental Investigation of Rotating Stall in a Mismatched Three-Stage Axial Flow Compressor

1989 ◽  
Vol 111 (4) ◽  
pp. 418-425 ◽  
Author(s):  
G. L. Giannissis ◽  
A. B. McKenzie ◽  
R. L. Elder
Keyword(s):  
High Speed ◽  
Measurement Techniques ◽  
Axial Flow ◽  
Fast Response ◽  
Rotating Stall ◽  
Response Measurement ◽  
Stall Inception ◽  
Axial Flow Compressor ◽  
Multistage Compressors ◽  
Flow Compressor

This paper reports on an examination of rotating stall in a low-speed three-stage axial flow compressor operating with various degrees of stage mismatch. The objective of this study was to simulate the mismatching that occurs in high-speed multistage compressors when operating near surge. The study of the stall zones involved the use of fast response measurement techniques. The study clearly shows how stages can operate in an axisymmetric fashion even when heavily stalled, since rotating stall inception requires the stall of more than one stage. The study also compares conditions required for full-span and part-span stall and suggests that the part-span stall structure is more relevant to high-speed multistage compressors.

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

scholarly journals The Numerical Simulation of a High-Speed Axial Flow Compressor

1991 ◽  
Author(s):  
Richard A. Mulac ◽  
John J. Adamczyk
Keyword(s):  
Numerical Simulation ◽  
Data Storage ◽  
High Speed ◽  
Axial Flow ◽  
Equation System ◽  
Axial Flow Compressor ◽  
Code Performance ◽  
Recent Developments ◽  
Multistage Compressors ◽  
Flow Compressor

The advancement of high-speed axial flow multistage compressors is impeded by a lack of detailed flow field information. Recent developments in compressor flow modeling and numerical simulation have the potential to provide needed information in a timely manner. This paper, which consists of two parts, will explore this topic. The first part will address the development of a computer program to solve the viscous form of the average-passage equation system for multistage turbomachinery. Programming issues such as in-core versus out-of-core data storage and CPU utilization (parallelization, vectorization, and chaining) will be addressed. Code performance will be evaluated through the simulation of the first four stages of a five stage, high-speed, axial flow compressor on a CRAY Y-MP8/8128 computer. The second part will address the flow physics which can be obtained from the numerical simulation. In particular, an examination of the endwall flow structure will be made, and its impact on blockage distribution assessed.

J0501-2-2 Effect of Stator on Rotating Stall Inception in Axial Flow Compressor Rotor

2010 ◽  
Vol 2010.7 (0) ◽  
pp. 15-16
Author(s):  
Hiroaki KIKUTA ◽  
Masato FURUKAWA ◽  
Kenichiro IWAKIRI ◽  
Satoshi GUNJISHIMA ◽  
Goki OKADA ◽  
...  
Keyword(s):  
Axial Flow ◽  
Rotating Stall ◽  
Stall Inception ◽  
Axial Flow Compressor ◽  
Compressor Rotor ◽  
Flow Compressor

Stall Inception and Development in an Axial Flow Aeroengine

1994 ◽  
Vol 116 (2) ◽  
pp. 216-225 ◽  
Author(s):  
A. G. Wilson ◽  
C. Freeman
Keyword(s):  
High Speed ◽  
Engine Speed ◽  
Static Pressure ◽  
Flow Instability ◽  
Axial Flow ◽  
Fast Response ◽  
Rotating Stall ◽  
Flow Disturbance ◽  
Stall Inception ◽  
Small Flow

This paper describes the phenomenon of stall and surge in an axial flow aeroengine using fast response static pressure measurements from the compressor of a Rolls-Royce VIPER engine. It details the growth of flow instability at various speeds, from a small zone of stalled fluid involving only a few blades into the violent surge motion of the entire machine. Various observations from earlier theoretical and compressor rig results are confirmed by these new engine measurements. The main findings are as follows: (1) The point of stall inception moves rearward as engine speed increases, and is shown to be simply related to the axial matching of the compressor. (2) The final unstable operation of the machine can be divided into rotating stall at low speed and surge or multiple surge at high speed. (3) The inception process is independent of whether the final unstable operation is rotating stall or multiple surge. (4) Stall/surge always starts as a circumferentially small flow disturbance, rotating around the annulus at some fraction of rotor speed.

An Experimental Study of Rotating Stall in a Multistage Axial-Flow Compressor

1984 ◽  
Vol 106 (3) ◽  
pp. 542-551 ◽  
Author(s):  
D. K. Das ◽  
H. K. Jiang
Keyword(s):  
Axial Flow ◽  
Fast Response ◽  
Critical Discussion ◽  
Rotating Stall ◽  
Digital Data ◽  
Appreciable Amount ◽  
Ensemble Averaging ◽  
Axial Flow Compressor ◽  
Digital Data Acquisition System ◽  
Flow Compressor

The flow field and the distribution of the flow parameters in the rotating stall regime in a three stage axial flow compressor were obtained in detail using three-hole cylindrical probes containing fast response transducers in association with a digital data acquisition system and an ensemble averaging technique. An appreciable amount of experimental data are presented in this paper with a critical discussion on those.

Unsteady Total Pressure Field Downstream of an Embedded Stator in a Multistage Axial Flow Compressor

1997 ◽  
Vol 119 (4) ◽  
pp. 985-994 ◽  
Author(s):  
N. Suryavamshi ◽  
B. Lakshminarayana ◽  
J. Prato ◽  
J. R. Fagan
Keyword(s):  
Total Pressure ◽  
High Speed ◽  
Pressure Field ◽  
Axial Flow ◽  
Temporal Variations ◽  
Pressure Probe ◽  
Peak Efficiency ◽  
Axial Flow Compressor ◽  
Multistage Compressors ◽  
Flow Compressor

The results from measurements of the unsteady total pressure field downstream of an embedded stage of a three stage axial flow compressor are presented in this paper. The measurements include area traverses of a high response kulite total pressure probe and a pneumatic five hole probe downstream of stator 2 at the peak efficiency operating point for the compressor. These data indicate that both the shaft-resolved and unresolved fluctuations contribute to the unsteadiness of the total pressure field in multistage compressors. Specifically, regions associated with high levels of unsteadiness and, consequently, high levels of mixing including both the hub and casing end walls and the airfoil wakes have significant levels of shaft resolved and unresolved unsteadiness. Temporal variations of stator exit flow are influenced by both shaft resolved and unresolved unsteadiness distributions. The limitations of state-of-the-art instrumentation for making measurements in moderate and high speed turbomachinery and the decomposition used to analyze these data are also discussed.

scholarly journals Comparison of Different Stall Conditions in Axial Flow Compressor Using Analytic Wavelet Transform

2017 ◽  
Vol 5 (1) ◽  
pp. 35-42
Author(s):  
Ali Arshad ◽  
Li Qiushi
Keyword(s):  
Wavelet Transform ◽  
Sampling Rate ◽  
Axial Flow ◽  
Rotating Stall ◽  
Data Sampling ◽  
Stall Inception ◽  
Detection Techniques ◽  
Axial Flow Compressor ◽  
Analytic Wavelet ◽  
Flow Compressor

Abstract The rotating stall inception data analysis using Analytic Wavelet Transform (AWT) in a low-speed axial compressor was presented in the authors’ previous studies [1], [2]. These studies focused on the detection of instability inception in an axial flow compressor when it enters into the instability regime due to the modal type of stall perturbation. In this paper, the effectiveness of AWT is further studied by applying it under different testing conditions. In order to examine the results of AWT on highly sampled data, at first, the stall data were acquired at a high sampling frequency and the results were compared with the conventional filtered signals. Secondly, the AWT analysis of stall data was carried out for the condition when compressor experienced a spike type rotating stall disturbance. The stall inception information obtained from the AWT analysis was then compared with the commonly used stall detection techniques. The results show that AWT is equally beneficial for the diagnostic of compressor instability regardless of the data sampling rate and represents an outstanding ability to detect stall disturbance irrespective of the type of stall precursor, i.e. the modal wave or spike.

scholarly journals Stall Inception and Development in an Axial Flow Aeroengine

1993 ◽  
Author(s):  
Alexander G. Wilson ◽  
Chris Freeman
Keyword(s):  
High Speed ◽  
Engine Speed ◽  
Static Pressure ◽  
Flow Instability ◽  
Axial Flow ◽  
Fast Response ◽  
Rotating Stall ◽  
Flow Disturbance ◽  
Stall Inception ◽  
Small Flow

This paper describes the phenomenon of stall and surge in an axial flow aeroengine using fast response static pressure measurements from the compressor of a Rolls-Royce VIPER engine. It details the growth of flow instability at various speeds, from a small zone of stalled fluid involving only a few blades into the violent surge motion of the entire machine. Various observations from earlier theoretical and compressor rig results are confirmed by these new engine measurements. The main findings are as follows: 1. The point of stall inception moves rearwards as engine speed increases, and is shown to be simply related to the axial matching of the compressor. 2. The final unstable operation of the machine can be divided into rotating stall at low speed and surge or multiple surge at high speed. 3. The inception process is independent of whether the final unstable operation is rotating stall or multiple surge. 4. Stall/surge always starts as a circumferentially small flow disturbance, rotating around the annulus at some fraction of rotor speed.

Sign in / Sign up

Export Citation Format

Share Document