Potential Flow Analysis of Axial Compressor Cascade Aerodynamics

1961 ◽  
Vol 83 (2) ◽  
pp. 314-315
Author(s):  
J. Pola´sˇek
Keyword(s):  
Potential Flow ◽  
Flow Analysis ◽  
Axial Compressor ◽  
Compressor Cascade

An Analysis of Axial Compressor Cascade Aerodynamics: Part I—Potential Flow Analysis With Complete Solutions for Symmetrically Cambered Airfoil Families

1959 ◽  
Vol 81 (3) ◽  
pp. 362-377 ◽  
Author(s):  
G. L. Mellor
Keyword(s):  
Potential Flow ◽  
Flow Analysis ◽  
Angle Of Attack ◽  
Axial Compressor ◽  
Graphical Form ◽  
Compressor Cascade ◽  
Real Fluid ◽  
Flow Effects ◽  
Complete Solutions

A method is presented whereby complete potential flow solutions for any cascade geometry may be obtained with comparatively great rapidity on desk calculators. This solution is carried out for the case of symmetrically cambered airfoils such as the 65-series compressor and circular are airfoils and the results presented in a compact graphical form completely account for the potential flow effects of camber, profile, thickness, stagger, solidity, and angle of attack. Real fluid effects will be assessed and correlated in Part II using the present results as a supporting theory.

An Analysis of Axial Compressor Cascade Aerodynamics: Part II—Comparison of Potential Flow Results With Experimental Data

1959 ◽  
Vol 81 (3) ◽  
pp. 379-386
Author(s):  
G. L. Mellor
Keyword(s):  
Experimental Data ◽  
Potential Flow ◽  
Lift Coefficient ◽  
Axial Compressor ◽  
Compressor Blade ◽  
Compressor Cascade ◽  
Interesting Point ◽  
Empirical Constant ◽  
Empirical Curve ◽  
Attack Data

The theoretical potential flow results of Part I are compared with the large number of NACA 65-series compressor blade data. It is found that a single empirical constant used to modify the theory permits reasonable predictions of turning or lift coefficient to be made for any cascade geometry in the unstalled regions of flow. Furthermore, it is demonstrated that the theory allows a considerable number of plus and minus stalling angle of attack data to be collapsed to a single empirical curve. Conversely such a curve, once established, allows stalling predictions to be made for any cascade geometry. One interesting point on this curve is the loading limit above which the cascade is always stalled.

VISCOUS POTENTIAL FLOW ANALYSIS OF STRESS-INDUCED CAVITATION IN AN APERTURE FLOW

2006 ◽  
Vol 16 (7) ◽  
pp. 763-776 ◽  
Author(s):  
T. Funada ◽  
J. Wang ◽  
Daniel D. Joseph
Keyword(s):  
Potential Flow ◽  
Flow Analysis ◽  
Viscous Potential Flow

Experimental Investigation Into the Effects of the Steady Wake-Tip Clearance Vortex Interaction in a Compressor Cascade

2015 ◽  
Vol 137 (6) ◽  
Author(s):  
Andreas Krug ◽  
Peter Busse ◽  
Konrad Vogeler
Keyword(s):  
Flow Field ◽  
Experimental Studies ◽  
Axial Compressor ◽  
Field Measurements ◽  
Tip Clearance ◽  
Compressor Cascade ◽  
Unsteady Interaction ◽  
Linear Compressor Cascade ◽  
Tip Clearance Vortex ◽  
The Impact

An important aspect of the aerodynamic flow field in the tip region of axial compressor rotors is the unsteady interaction between the tip clearance vortex (TCV) and the incoming stator wakes. In order to gain an improved understanding of the mechanics involved, systematic studies need to be performed. As a first step toward the characterization of the dynamic effects caused by the relative movement of the blade rows, the impact of a stationary wake-induced inlet disturbance on a linear compressor cascade with tip clearance will be analyzed. The wakes were generated by a fixed grid of cylindrical bars with variable pitch being placed at discrete pitchwise positions. This paper focuses on experimental studies conducted at the newly designed low-speed cascade wind tunnel in Dresden. The general tunnel configuration and details on the specific cascade setup will be presented. Steady state flow field measurements were carried out using five-hole probe traverses up- and downstream of the cascade and accompanied by static wall pressure readings. 2D-particle image velocimetry (PIV) measurements complemented these results by visualizing the blade-to-blade flow field. Hence, the structure of the evolving secondary flow system is evaluated and compared for all tested configurations.

Improving a one-dimensional centrifugal compressor performance prediction method

2005 ◽  
Vol 219 (8) ◽  
pp. 653-659 ◽  
Author(s):  
E Swain
Keyword(s):  
Centrifugal Compressor ◽  
Performance Prediction ◽  
Fluid Dynamic ◽  
Three Dimensional ◽  
Axial Compressor ◽  
Prediction Method ◽  
Compressor Cascade ◽  
One Dimensional ◽  
Compressor Performance ◽  
Cfd Analyses

A one-dimensional centrifugal compressor performance prediction technique that has been available for some time is updated as a result of extracting the component performance from three-dimensional computational fluid dynamic (CFD) analyses. Confidence in the CFD results is provided by comparison of overall performance for one of the compressor examples. The extracted impeller characteristic is compared with the original impeller loss model, and this indicated that some improvement was desirable. The position of least impeller loss was determined using a traditional axial compressor cascade method, and suitable algebraic expressions were derived to match the CFD data. The merit of the approach lies with the relative ease that CFD component performance currently can be achieved and adjusting one-dimensional methods to agree with the CFD-derived models.

scholarly journals Simplified Method for Flow Analysis and Performance Calculation Through an Axial Compressor

1984 ◽  
Author(s):  
Hubert Miton ◽  
Youssef Doumandji ◽  
Jacques Chauvin
Keyword(s):  
Equations Of Motion ◽  
Computing Time ◽  
Flow Analysis ◽  
Axial Compressor ◽  
Computation Method ◽  
Duct Flow ◽  
Axial Compressors ◽  
Flow Through ◽  
And Performance ◽  
Performance Calculation

This paper describes a fast computation method of the flow through multistage axial compressors of the industrial type. The flow is assumed to be axisymmetric between the blade rows which are represented by actuator disks. Blade row losses and turning are calculated by means of correlations. The equations of motion are linearized with respect to the log of static pressure, whose variation along the radius is usually of limited extent for the type of machines for which the method has been developed. In each computing plane (i.e. between the blade rows) two flows are combined: a basic flow with constant pressure satisfying the mass flow requirements and a perturbation flow fulfilling the radial equilibrium condition. The results of a few sample calculations are given. They show a satisfactory agreement with a classical duct flow method although the computing time is reduced by a factor five. The method has also been coupled with a surge line prediction calculation.

scholarly journals Potential Flow Analysis for a Ship with a Flow Control Plate near the Stern

2009 ◽  
Vol 46 (6) ◽  
pp. 587-594 ◽  
Author(s):  
Hee-Jong Choi ◽  
Ho-Hwan Chun ◽  
Hyun-Sik Yoon ◽  
In-Won Lee ◽  
Dong-Woo Park ◽  
...  
Keyword(s):  
Flow Control ◽  
Potential Flow ◽  
Flow Analysis ◽  
Control Plate

scholarly journals Considerations on Axial Compressor Bleed for Sub-Idle Performance Models

2020 ◽  
Author(s):  
Ferran Roig Tió ◽  
Luis E. Ferrer-Vidal ◽  
Hasani Azamar Aguirre ◽  
Vassilios Pachidis
Keyword(s):  
Flow Analysis ◽  
Axial Compressor ◽  
Engine Performance ◽  
Analysis Tool ◽  
Performance Models ◽  
Performance Modelling ◽  
Start Up ◽  
Considerable Impact ◽  
Aero Engines ◽  
Analytical Approaches

Abstract The trend towards increased bypass ratio and reduced core size in civil aero-engines puts a strain on ground-start and relight capability, prompting renewed interest in sub-idle performance modelling. While a number of studies have looked at some of the broad performance modelling issues prevalent in this regime, the effects that bleed can have on sub-idle performance have not been addressed in the literature. During start-up and relight, the unknown variation in bleed flows through open handling bleed valves can have a considerable impact on the compressor’s operating line. This paper combines experimental, numerical and analytical approaches to look at the effect that sub-idle bleed flows have on predicted start-up operating lines, along with their effect on compressor characteristics. Experimental whole-engine data along with a purpose-built core-flow analysis tool are used to assess the effect of bleed model uncertainty on engine performance models. An experimental rig is used to assess the effects of reverse bleed on compressor characteristics and measurements are compared against numerical results. Several strategies for the generation of sub-idle maps including bleed effects are investigated.

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