scholarly journals Quasi Two-Dimensional Flows Through a Cascade

1968 ◽  
Vol 90 (2) ◽  
pp. 119-127 ◽  
Author(s):  
R. Mani ◽  
A. J. Acosta
Keyword(s):  
Axial Velocity ◽  
Axial Flow ◽  
Two Dimensional ◽  
Axial Flow Compressor ◽  
Thin Airfoil ◽  
Converging Channel ◽  
Flow Compressor ◽  
Two Dimensional Flows

A thin airfoil theory is developed for airfoils spanning a slowly diverging or converging channel, the motivation being to predict, theoretically, the effect of varying axial velocity on the cascade performance of axial flow compressor rows.

Compressor Design

1953 ◽  
Vol 57 (511) ◽  
pp. 463-463
Author(s):  
R. G. Taylor
Keyword(s):  
Velocity Profile ◽  
Axial Velocity ◽  
Axial Flow ◽  
Technical Note ◽  
Basic Design ◽  
Wall Effects ◽  
Axial Flow Compressor ◽  
Axial Velocity Profile ◽  
Compressor Design ◽  
Flow Compressor

In Mr. J. M. Stephenson's Technical Note, “ The Elimination of Wall Effects in Axial-Flow Compressor Stages,” in the April 1953 issue of the Journal, the author suggests that the blade rows of an axial flow compressor are so closely spaced as to ensure that the axial velocity profile is unchanged across the rows. Whether this statement is correct or not such an assumption regarding the axial velocity profile is a basic design condition and when made it will not leave any flexibility in the choice of the function f(r).

Investigation on the influence of the structure parameters of blade tip recess on the performance of axial flow compressor

2021 ◽  
pp. 095441002199810
Author(s):  
Song Yan ◽  
WuLi Chu
Keyword(s):  
Axial Flow ◽  
Leading Edge ◽  
Tip Clearance ◽  
Field Analysis ◽  
Structure Parameters ◽  
Two Dimensional ◽  
Axial Flow Compressor ◽  
Aero Engine ◽  
Blade Tip ◽  
Flow Compressor

As one of the important components of an aero engine, the compressor plays an important role in improving the performance of the aero engine. The blade tip recess (BTR) has great potential and advantages in improving the performance of the compressor. It is very important to clarify the influence of the structure parameters of the BTR on the performance of the compressor. In this study, the two-dimensional results of the BTR were analyzed by using the method of variance analysis, and the two-dimensional calculation results of the BTR were used to guide the design of the BTR of axial flow compressor rotor. In the NASA Rotor 35, the influence rules of the structure parameters of BTR on the recess effect that was basically the same as the two-dimensional conditions. The optimization of the rotor BTR structure parameters may be achieved by the two-dimensional calculation. The flow field analysis showed the BTR can retard the growth rate of the blockage area of the leading edge of blade tip by weakening the tip clearance leakage flow intensity that delayed the occurrence of blade tip blockage and improved the aerodynamic stability of the rotor.

Experimental Study of Casing Boundary Layers in a Multistage Axial Compressor

1991 ◽  
Vol 113 (2) ◽  
pp. 240-244
Author(s):  
S. Venkateswaran
Keyword(s):  
Shear Stress ◽  
Skin Friction ◽  
Boundary Layers ◽  
Axial Compressor ◽  
Axial Flow ◽  
Two Dimensional ◽  
Law Of The Wall ◽  
The Law ◽  
Flow Compressor ◽  
Two Dimensional Flows

Measurements of the casing boundary layers were obtained in a four-stage, low speed axial flow compressor, to verify the ‘law of the wall’ applicability to these complex flows. Some of the available shear stress models of the two-dimensional flows have been examined towards the quantitative assessment of skin friction. The shear stress prediction obtained from the Ludwieg-Tillmann relation applied to the streamwise or untwisted profile agreed closely with the measured shear stress by the hot wire. The skin friction was fairly constant for rotor and stator flows and was close to the flat plate values. The boundary layer profiles exhibited a well pronounced semi-logarithmic region with the universal constants of the law of the wall far removed from the standard two dimensional values, especially for rotor flows. Stator flows showed signs of similarity to two dimensional flows.

scholarly journals A DESIGN OF AXIAL-FLOW COMPRESSOR BLADES WITH INCLINED STREAM SURFACE AND VARYING AXIAL VELOCITY

1979 ◽  
Vol 22 (171) ◽  
pp. 1190-1197
Author(s):  
Masahiro INOUE ◽  
Takefumi IKUI ◽  
Yoshihisa KAMADA ◽  
Mitsuo TASHIRO
Keyword(s):  
Axial Velocity ◽  
Axial Flow ◽  
Compressor Blades ◽  
Stream Surface ◽  
Axial Flow Compressor ◽  
Flow Compressor

Inverse Design of Axial-Flow Compressor Blades Using Elastic Surface Algorithm in Subsonic and Transonic Flow Regimes With Separation

2016 ◽  
Author(s):  
M. H. Noorsalehi ◽  
M. Nili-Ahamadabadi ◽  
E. Shirani ◽  
M. Safari
Keyword(s):  
Pressure Distribution ◽  
Transonic Flow ◽  
Design Method ◽  
Axial Flow ◽  
Flow Regimes ◽  
Inverse Design ◽  
Elastic Surface ◽  
Axial Flow Compressor ◽  
Inverse Design Method ◽  
Flow Compressor

In this study, a new inverse design method called Elastic Surface Algorithm (ESA) is developed and enhanced for axial-flow compressor blade design in subsonic and transonic flow regimes with separation. ESA is a physically based iterative inverse design method that uses a 2D flow analysis code to estimate the pressure distribution on the solid structure, i.e. airfoil, and a 2D solid beam finite element code to calculate the deflections due to the difference between the calculated and target pressure distributions. In order to enhance the ESA, the wall shear stress distribution, besides pressure distribution, is applied to deflect the shape of the airfoil. The enhanced method is validated through the inverse design of the rotor blade of the first stage of an axial-flow compressor in transonic viscous flow regime. In addition, some design examples are presented to prove the effectiveness and robustness of the method. The results of this study show that the enhanced Elastic Surface Algorithm is an effective inverse design method in flow regimes with separation and normal shock.

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