Geometry Scaling Technique and Application to Aerodynamic Redesign of Multi-stage Transonic Axial-flow Compressors

2021 ◽  
pp. 107303
Author(s):  
Xiawen Zhang ◽  
Yaping Ju ◽  
Chuhua Zhang
Keyword(s):  
Axial Flow ◽  
Scaling Technique ◽  
Multi Stage ◽  
Axial Flow Compressors

Paper 17: Stage Matching, Stall, and Surge in Multi-Stage Axial Flow Compressors

1969 ◽  
Vol 184 (7) ◽  
pp. 49-56 ◽  
Author(s):  
S. Gray
Keyword(s):  
Axial Compressor ◽  
Axial Flow ◽  
Rational Method ◽  
Theory And Practice ◽  
Qualitative Description ◽  
Multi Stage ◽  
Compressor Surge ◽  
Stage Matching ◽  
Axial Flow Compressors

Despite major advances in axial compressor theory and practice, the lack of a rational method of predicting surge limits remains as an outstanding deficiency. Accumulating experience suggests the association of surge initiation with local stalling phenomena, within the compressor, which are inadequately represented by conventional assumptions. A simple, revised model of stage matching under local stalling conditions is shown to provide a rational and consistent qualitative description of observed compressor off-design and surge initiation characteristics, and the effects on these of a variety of factors. Improved local stall criteria could provide the key to quantitative predictions of multi-stage compressor surge limits.

Third Paper: Intake Noise from Axial Flow Turbochargers and Compressors

1967 ◽  
Vol 182 (1) ◽  
pp. 73-88
Author(s):  
I. J. Sharland
Keyword(s):  
Gas Turbine ◽  
Axial Flow ◽  
Multi Stage ◽  
Axial Flow Compressors

One of the factors that has to be considered when planning the installation of a turbocharger or gas turbine is the amount of noise that is likely to be radiated from the intake. Frequently such plant employs axial flow compressors, either single-or multi-stage. The object of this paper is to describe how noise is generated in that type of compressor.

Some Effects of Non-Axisymmetric End Wall Profiling on Axial Flow Compressor Aerodynamics: Part II—Multi-Stage HPC CFD Study

2008 ◽  
Author(s):  
N. W. Harvey ◽  
T. P. Offord
Keyword(s):  
Axial Flow ◽  
Design Optimisation ◽  
Multi Stage ◽  
Flow Compressor ◽  
Service Application ◽  
House Design ◽  
Computational Resources ◽  
Gas Turbine Compressor ◽  
End Wall ◽  
Axial Flow Compressors

Non-axisymmetric end wall profiling is now a well established design methodology in axial flow turbines, used principally to improve their aerodynamic efficiency by reducing secondary loss. However, profiled end walls (PEWs) have yet to find an in-service application in a gas turbine compressor. This two-part paper presents the results of a number of studies, both experimental and computational, into the potential aerodynamic benefits of applying PEWs in axial flow compressors. The second paper describes an investigation into PEWs as a means of suppressing stator hub corner stall. An in-house design optimisation system (SOPHY) was applied to a typical embedded stator row in a multi-stage HP compressor. This enabled a new PEW geometry to be defined which is shown to be an effective alternative to 3-D aerofoil shaping in controlling stator hub corner stall. The results of this new study and of the work described in the first paper have been combined in a further investigation. PEWs were applied to an HPC with purely 2-D blading, which exhibited extensive stator hub corner stall at off-design conditions. CFD analysis showed that stator hub corner stall was successfully suppressed by the PEWs. It is concluded that PEWs can significantly affect the end wall flow field and have similar effects on corner stall as 3-D blading. The potential for improving the performance of axial flow compressors using PEWs is discussed. To successfully achieve any such improvements, extensive computational resources that are dedicated to design optimisation will be required.

scholarly journals Wake Mixing in Axial Flow Compressors

1996 ◽  
Author(s):  
John J. Adamczyk
Keyword(s):  
Total Pressure ◽  
Axial Flow ◽  
Recovery Process ◽  
Flow Process ◽  
Direct Function ◽  
Reduced Frequency ◽  
Multi Stage ◽  
Blade Row ◽  
And Performance ◽  
Axial Flow Compressors

Over the years it has been speculated that the performance of multi-stage axial flow compressors is enhanced by the passage of a wake through a blade row prior to being mixed-out by viscous diffusion. The link between wake mixing and performance depends on the ability to recover the total pressure deficit of a wake by a reversible flow process. This paper shows that such a process exists, it is unsteady, and is associated with the kinematics of the wake vorticity field. The analysis shows that the benefits of wake total pressure recovery can be estimated from linear theory and quantified in terms of a volume integral involving the deterministic stress and the mean strain rate. In the limit of large reduced frequency the recovery process is shown to be a direct function of blade circulation. Results are presented which show that the recovery process can reduce the wake mixing loss by as much as seventy percent. Under certain circumstances this can lead to nearly a point improvement in stage efficiency, a nontrivial amount.

Active Control of Surge in Multi-Stage Axial-Flow Compressors

1995 ◽  
Vol 209 (4) ◽  
pp. 249-258 ◽  
Author(s):  
J-F Escuret ◽  
R L Elder
Keyword(s):  
Frequency Response ◽  
Active Control ◽  
Flow Model ◽  
Axial Flow ◽  
Normal Operation ◽  
Linear Controller ◽  
Multi Stage ◽  
Non Linear ◽  
Axial Flow Compressors ◽  
Sensor Locations

Non-linear simulations of a surge model with and without control are investigated using a Runge-Kutta scheme. This shows how some non-linearities in the flow model can affect the normal operation of a linear controller and the problem of actuatop sensor locations. Also, the amplitudes and frequency response required of the actuator to retain stability can sometimes be found to exceed the practical limitations.

New Features in the Design of Axial-Flow Compressors With Tandem Blades

1981 ◽  
Author(s):  
K. Bammert ◽  
R. Staude
Keyword(s):  
Basic Concept ◽  
Axial Flow ◽  
Volume Flow ◽  
Maximum Pressure ◽  
Compressor Blades ◽  
Iron And Steel ◽  
Optimum Performance ◽  
Multi Stage ◽  
Steel Industries ◽  
Axial Flow Compressors

A multitude of examinations and studies of compressor blades with 100 percent reaction have shown that tandem blades can advantageously be used in stationary industrial axial flow compressors, designed for applications in the chemical, iron and steel industries. Because there are no limitations for axial flow compressors with tandem blades, this type of compressor can operate up to maximum pressure ratios of 10 for suction volume flow of about 600,000 m3 /h. In particular, the handling of light gases, such as helium, leads also to large sizes. Based on measurements taken on a four-stage experimental compressor, criteria are developed for the design of axial flow compressors with tandem blades. The basic concept of a multi-stage industrial compressor provides for the combined arrangement of compressor stages of single and tandem-cascade design. This permits an optimum performance to be achieved at a considerable reduction of the constructional expenditure.

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