Numerical Simulation of Flow Instabilities in High Speed Multistage Compressors

2010 ◽  
Author(s):  
Huan Zhang ◽  
Jun Hu ◽  
Baofeng Tu ◽  
Zhiqiang Wang
Keyword(s):  
High Speed ◽  
Rotating Stall ◽  
Flow Instabilities ◽  
Two Dimensional ◽  
Duct Flow ◽  
Disk Model ◽  
Stall Inception ◽  
Axial Compressors ◽  
Multistage Compressors ◽  
The Stability

In the present paper, a nonlinear multi “actuator disk” model is proposed to analyze the dynamic behavior of flow instabilities, including rotating stall and surge, in high speed multistage axial compressors. The model describes the duct flow fields using two dimensional, compressible and unsteady Euler equations, and accounts for the influences of downstream plenum and throttle in the system as well. It replaces each blade row of multistage compressors with a disk. For numerical calculations, the time marching procedure, using MacCormack two steps scheme, is used. The main purpose of this paper is to predict the mechanism of two dimensional short wavelength rotating stall inception, the interaction between blade rows in high speed multistage compressors and the influence of rotating inlet distortion on the stability. It has been demonstrated that the model has the ability to predict those phenomena, and the results show that some system parameters have a strong effect on the stall features as well. Results for a five stage high speed compressor are analyzed in detail, and comparison with the experimental data demonstrates that the model and calculating results are reliable.

A Study of Spike and Modal Stall Phenomena in a Low-Speed Axial Compressor

1997 ◽  
Author(s):  
T. R. Camp ◽  
I. J. Day
Keyword(s):  
High Speed ◽  
Three Dimensional ◽  
Axial Compressor ◽  
Operating Conditions ◽  
Two Dimensional ◽  
Stability Criteria ◽  
Stall Inception ◽  
Low Speed ◽  
The Stability ◽  
Dimensional Instability

This paper presents a study of stall inception mechanisms a in low-speed axial compressor. Previous work has identified two common flow breakdown sequences, the first associated with a short lengthscale disturbance known as a ‘spike’, and the second with a longer lengthscale disturbance known as a ‘modal oscillation’. In this paper the physical differences between these two mechanisms are illustrated with detailed measurements. Experimental results are also presented which relate the occurrence of the two stalling mechanisms to the operating conditions of the compressor. It is shown that the stability criteria for the two disturbances are different: long lengthscale disturbances are related to a two-dimensional instability of the whole compression system, while short lengthscale disturbances indicate a three-dimensional breakdown of the flow-field associated with high rotor incidence angles. Based on the experimental measurements, a simple model is proposed which explains the type of stall inception pattern observed in a particular compressor. Measurements from a single stage low-speed compressor and from a multistage high-speed compressor are presented in support of the model.

Theoretical Study of Flow Instabilities and Inlet Distortions in Axial Compressors

1982 ◽  
Vol 104 (3) ◽  
pp. 715-721 ◽  
Author(s):  
P. Ferrand ◽  
J. Chauvin
Keyword(s):  
Theoretical Study ◽  
Rotating Stall ◽  
Time Dependent ◽  
Flow Instabilities ◽  
Axial Compressors ◽  
Independent Variables ◽  
Servo Mechanism ◽  
Dependent Variables ◽  
Multistage Compressors ◽  
Method Of Evaluation

This paper describes a method of evaluation of the single and multistage compressors response to steady and unsteady inlet distortions. It allows also the evaluation of the appearance of unstable regimes and their characterization (rotating stall and surge). It is based on a linearized approach using mean line calculations. The compressor is considered as a series of vaned and vaneless spaces, and the corresponding equations are solved by use of Fourier series for time independent variables and by Laplace’s transform for time-dependent variables. An analogy between the compressor’s response and a servo-mechanism is developed, using Nyquist’s diagram. Results are compared with experimental data which prove the validity of the approach. A parametric study indicates which parameters can be modified to improve the flow stability.

Theoretical Study of Flow Instabilities and Inlet Distortions in Axial Compressors

1981 ◽  
Author(s):  
P. Ferrand ◽  
J. Chauvin
Keyword(s):  
Theoretical Study ◽  
Rotating Stall ◽  
Time Dependent ◽  
Flow Instabilities ◽  
Axial Compressors ◽  
Independent Variables ◽  
Servo Mechanism ◽  
Dependent Variables ◽  
Multistage Compressors ◽  
Method Of Evaluation

This paper describes a method of evaluation of the single and multistage compressors response to steady and unsteady inlet distortions. It allows also the evaluation of the appearance of unstable regimes and their characterization (rotating stall and surge). It is based on a linearized approach using mean line calculations. The compressor is considered as a serie of vaned and vaneless spaces, and the corresponding equations are solved by use of Fourier series for time independent variables and by Laplace’s transform for time dependent variables. An analogy between the compressor’s response and a servo-mechanism is developed, using Nyquist’s diagram. Results are compared with experimental data which prove the validity of the approach. A parametric study indicates which parameters can be modified to improve the flow stability.

Rotating Waves as a Stall inception Indication in Axial Compressors

1991 ◽  
Vol 113 (2) ◽  
pp. 290-301 ◽  
Author(s):  
V. H. Garnier ◽  
A. H. Epstein ◽  
E. M. Greitzer
Keyword(s):  
Growth Rate ◽  
Small Amplitude ◽  
High Speed ◽  
Rotating Stall ◽  
Analytical Models ◽  
Stall Inception ◽  
Axial Compressors ◽  
Spatially Resolved ◽  
Two Stages ◽  
The Waves

Stall inception has been studied in two low-speed compressors (a single-stage and a three-stage) and in a high-speed three-stage compressor, using temporally and spatially resolved measurements. In all three machines, rotating stall was preceded by a period in which small-amplitude waves were observed traveling around the circumference of the machine at a speed slightly less than the fully developed rotating stall cell speed. The waves evolved smoothly into rotating stall without sharp changes in phase or amplitude, implying that, in the machines tested, the prestall waves and the fully developed rotating stall are two stages of the same phenomenon. The growth rate of these disturbances was in accord with that predicted by current analytical models. The prestall waves were observed both with uniform and with distorted inflow, but were most readily discerned with uniform inflow. Engineering uses and limitations of these waves are discussed.

Aeromechanical Control of High-Speed Axial Compressor Stall and Engine Performance— Part I: Control-Theoretic Models

2013 ◽  
Vol 135 (3) ◽  
Author(s):  
O. G. McGee ◽  
K. L. Coleman
Keyword(s):  
High Speed ◽  
Axial Compressor ◽  
Engine Performance ◽  
Maximum Flow ◽  
Rotating Stall ◽  
Design Flow ◽  
Systematic Evaluation ◽  
Stable Operation ◽  
Stall Inception ◽  
Axial Compressors

General methodologies are proposed in this two-part paper that further phenomenological understanding of compressible stall inception and aeromechanical control of high-speed axial compressors and engine performance. Developed in Part I are strategies for passive stabilization of compressible rotating stall, using tailored structural design and aeromechanical feedback control, implemented in certain classes of high-speed axial compressors used in research laboratories and by industry. Fundamentals of the stability of various dynamically-compensated, high-speed compressors was set down from linearized, compressible structural-hydrodynamic equations of modal stall inception extended further in this study from previous work. A dimensionless framework for performance-based design of aeromechanically-controlled compression system stall mitigation and engine performance is established, linking specified design flow and work-transfer (pressure) operability to model stages or local blade components, velocity triangle environment, optimum efficiency, extended stall margin and operability loci, and aeromechanical detailed design. A systematic evaluation was made in Part II (Coleman and McGee, 2013, “Aeromechanical Control of High-Speed Axial Compressor Stall and Engine Performance—Part II: Assessments of Methodology,” ASME J. Fluids Eng. (to be published)) on the performance of ten aeromechanical feedback controller schemes to increase the predicted range of stable operation of two laboratory compressor characteristics assumed, using static pressure sensing and local structural actuation to rudimentary postpone high-speed modal stall inception. The maximum flow operating range for each of the ten dynamically-compensated, high-speed compression systems was determined using optimized or “tailored” structural controllers, and the results described in Part II of the companion paper are compared to maximum operating ranges achieved in corresponding low-speed compression systems.

Comparisons Between Measured and Calculated Stall Development in Four High-Speed Multi-Stage Compressors

1997 ◽  
Author(s):  
A. A. J. Demargne ◽  
J. P. Longley
Keyword(s):  
Numerical Simulation ◽  
High Speed ◽  
Development Process ◽  
Rotating Stall ◽  
Two Dimensional ◽  
Stall Inception ◽  
Mass Injection ◽  
Multi Stage ◽  
Design Speed

In this paper the development of rotating stall in four different high-speed multi-stage compressors is investigated using a numerical simulation. Below 90 per cent of design speed the model calculates well the two-dimensional moderate to long lengthscale development of rotating stall, irrespective of the lengthscale and form of the stall inception mechanism. At higher operating speeds the model is less reliable, providing better comparisons for those compressors which exhibited modal rather than spike stall inception. The model is also used to investigate the feasibility of actively controlling the stall development process in a compressor. The conclusions reached are that mass injection and removal is far more effective than varying the blade stagger angles and that sensors must be upstream of actuators.

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.

Controls and Diagnostics Committee Best 1994 Paper Award: Modeling for Control of Rotating Stall in High-Speed Multistage Axial Compressors

1996 ◽  
Vol 118 (1) ◽  
pp. 1-10 ◽  
Author(s):  
M. R. Feulner ◽  
G. J. Hendricks ◽  
J. D. Paduano
Keyword(s):  
Transfer Function ◽  
Compressible Flow ◽  
Active Control ◽  
High Speed ◽  
Pressure Sensors ◽  
Rotating Stall ◽  
Two Dimensional ◽  
Input Output ◽  
Axial Compressors ◽  
Blade Row

Using a two-dimensional compressible flow representation of axial compressor dynamics, a control-theoretic input–output model is derived, which is of general utility in rotating stall/surge active control studies. The derivation presented here begins with a review of the fluid dynamic model, which is a two-dimensional stage stacking technique that accounts for blade row pressure rise, loss, and deviation as well as blade row and interblade row compressible flow. This model is extended to include the effects of the upstream and downstream geometry and boundary conditions, and then manipulated into a transfer function form that dynamically relates actuator motion to sensor measurements. Key relationships in this input–output form are then approximated using rational polynomials. Further manipulation yields an approximate model in standard form for studying active control of rotating stall and surge. As an example of high current relevance, the transfer function from an array of jet actuators to an array of static pressure sensors is derived. Numerical examples are also presented, including a demonstration of the importance of proper choice of sensor and actuator locations, as well as a comparison between sensor types. Under a variety of conditions, it was found that sensor locations near the front of the compressor or in the downstream gap are consistently the best choices, based on a quadratic optimization criterion and a specific three-stage compressor model. The modeling and evaluation procedures presented here are a first step toward a rigorous approach to the design of active control systems for high-speed axial compressors.

scholarly journals Rotating Waves as a Stall Inception Indication in Axial Compressors

1990 ◽  
Author(s):  
V. H. Garnier ◽  
A. H. Epstein ◽  
E. M. Greitzer
Keyword(s):  
Growth Rate ◽  
Small Amplitude ◽  
High Speed ◽  
Rotating Stall ◽  
Analytical Models ◽  
Stall Inception ◽  
Axial Compressors ◽  
Spatially Resolved ◽  
Two Stages ◽  
The Waves

Stall inception has been studied in two low speed compressors (a single-stage and a three-stage) and in a high speed three-stage compressor, using temporally and spatially resolved measurements. In all three machines, rotating stall was preceded by a period in which small amplitude waves were observed travelling around the circumference of the machine at a speed slightly less than the fully developed rotating stall cell speed. The waves evolved smoothly into rotating stall without sharp changes in phase or amplitude, implying that, in the machines tested, the prestall waves and the fully developed rotating stall are two stages of the same phenomenon. The growth rate of these disturbances was in accord with that predicted by current analytical models. The prestall waves were observed both with uniform and with distorted inflow, but were most readily discerned with uniform inflow. Engineering uses and limitations of these waves are discussed.

scholarly journals Stalled Flow Performance for Axial Compressors: II — Rotating Stall Characteristic

1984 ◽  
Author(s):  
S. G. Koff
Keyword(s):  
Rotating Stall ◽  
Flow Mode ◽  
Thin Shells ◽  
System Behavior ◽  
Stall Inception ◽  
Compression System ◽  
Axial Compressors ◽  
System Parameters ◽  
Multistage Compressors ◽  
The Impact

This paper describes a study of stalled flow performance of multistage compressors. The study is focused on the performance in rotating stall, in particular, the impact on stall inception and stall recovery. It is argued that the recovery point measured in post-stall compressor tests results from a compression system instability, rather than from an unstable rotating stall flow. If so, recoverability from rotating stall may be improved by altering system parameters. Furthermore, the full-span rotating stall characteristic is extrapolated beyond the measured recovery point. On this basis, the compressor stall point is viewed as a bifurcation, where a change in flow mode exists, perhaps analogous to the critical point in the axial compression of thin shells. An application for the extended rotating stall characteristic is in a model of transient compression system behavior.

Sign in / Sign up

Export Citation Format

Share Document