A Three Dimensional Theory of Axial Compressor Blade Rows - Application in Subsonic and Supersonic Flows

1958 ◽  
Vol 25 (9) ◽  
pp. 544-560 ◽  
Author(s):  
JAMES E. McCUNE
Keyword(s):  
Three Dimensional ◽  
Axial Compressor ◽  
Supersonic Flows ◽  
Compressor Blade ◽  
Dimensional Theory

Numerical Investigation of End Wall Boundary Layer Removal on Highly Loaded Axial Compressor Blade Rows

2008 ◽  
Vol 130 (1) ◽  
Author(s):  
V. Gümmer ◽  
M. Goller ◽  
M. Swoboda
Keyword(s):  
Boundary Layer ◽  
Three Dimensional ◽  
Axial Compressor ◽  
Flow Path ◽  
Compressor Blade ◽  
Main Flow ◽  
Layer Removal ◽  
Wall Boundary Layer ◽  
End Wall ◽  
Highly Loaded

This paper presents results of numerical investigations carried out to explore the benefit of end wall boundary layer removal from critical regions of highly loaded axial compressor blade rows. At the loading level of modern aero engine compressors, the performance is primarily determined by three-dimensional (3D) flow phenomena occurring in the end wall regions. Three-dimensional Navier–Stokes simulations were conducted on both a rotor and a stator test case in order to evaluate the basic effects and the practical value of bleeding air from specific locations at the casing end wall. The results of the numerical survey demonstrated substantial benefits of relatively small bleed rates to the local flow field and to the performance of the two blade rows. On the rotor, the boundary layer fluid was removed from the main flow path through an axisymmetric slot in the casing over the rotor tip. This proved to give some control over the tip leakage vortex flow and the associated loss generation. On the stator, the boundary layer fluid was taken from the flow path through a single bleed hole within the passage. Two alternative off-take configurations were evaluated, revealing a large impact of the bleed hole shape and the location on the cross-passage flow and the suction side corner separation. On both blade rows investigated, rotor and stator, the boundary layer removal resulted in a reduction of the local reverse flow, blockage, and losses in the respective near-casing region. This paper gives insight into changes occurring in the 3D passage flow field near the casing and summarizes the effects on the radial matching and pitchwise-averaged performance parameters, namely loss and deviation of the rotor and stator when suction is active. Primary focus is put on the aerodynamics in the blade rows in the main flow path; details of the internal flow structure within the bleed off-take cavities/ports are not discussed here.

Structural and Dynamic Optimization of a Single Axial Compressor Blade Using the Gradient-Based Method

2014 ◽  
Author(s):  
Alexander O. Pugachev ◽  
Alexander V. Sheremetyev ◽  
Viktor V. Tykhomirov ◽  
Alexey V. Petrov
Keyword(s):  
Finite Element ◽  
Optimization Problems ◽  
Thickness Distribution ◽  
Three Dimensional ◽  
Axial Compressor ◽  
Compressor Blade ◽  
Element Analysis ◽  
Programming Technique ◽  
Sizing Optimization ◽  
Aerodynamic Properties

This paper describes the development of an in-house code for sizing optimization of blades with constraints imposed on blade’s natural frequencies and static stresses. The optimization environment includes a three-dimensional parametric model of the blade, interface functions for automated execution of the static and modal finite element analyses as well as post-processing of the results, and optimization algorithm. The blade geometry is represented by section profiles at a number of span-wise stations. Each blade section profile is parametrized by nine intuitive geometric parameters which control profile thickness distribution, chord, offset, and stagger angle. Three-dimensional finite element analysis of the blade is performed using ANSYS Mechanical software package. A sequential quadratic programming technique is used to solve the nonlinear optimization problem. Sensitivity analysis is performed using the finite-difference method. Several optimization problems with different objective functions and combinations of constraints are implemented. The aerodynamic constraints are not considered directly. The blade’s aerodynamic properties are sustained by imposing tight limits on the allowable changes of design variables. Sizing optimization is performed for an axial compressor blade of a gas turbine engine. The results show that the code can meet the defined objective and constraints for the most tested cases. A detailed comparison of optimized profiles with the baseline geometry is provided.

Effects of stator splitter blades on aerodynamic performance of a single-stage transonic axial compressor

2020 ◽  
Vol 14 (4) ◽  
pp. 7369-7378
Author(s):  
Ky-Quang Pham ◽  
Xuan-Truong Le ◽  
Cong-Truong Dinh
Keyword(s):  
Stokes Equations ◽  
Three Dimensional ◽  
Axial Compressor ◽  
Aerodynamic Performance ◽  
Numerical Results ◽  
Single Stage ◽  
Navier Stokes ◽  
Navier Stokes Equations ◽  
Operating Stability ◽  
Length Coverage

Splitter blades located between stator blades in a single-stage axial compressor were proposed and investigated in this work to find their effects on aerodynamic performance and operating stability. Aerodynamic performance of the compressor was evaluated using three-dimensional Reynolds-averaged Navier-Stokes equations using the k-e turbulence model with a scalable wall function. The numerical results for the typical performance parameters without stator splitter blades were validated in comparison with experimental data. The numerical results of a parametric study using four geometric parameters (chord length, coverage angle, height and position) of the stator splitter blades showed that the operational stability of the single-stage axial compressor enhances remarkably using the stator splitter blades. The splitters were effective in suppressing flow separation in the stator domain of the compressor at near-stall condition which affects considerably the aerodynamic performance of the compressor.

Membrane theory

2017 ◽  
Author(s):  
David J. Steigmann
Keyword(s):  
Three Dimensional ◽  
Thin Sheets ◽  
Two Dimensional ◽  
Leading Order ◽  
Membrane Theory ◽  
Dimensional Theory ◽  
Small Thickness

This chapter develops two-dimensional membrane theory as a leading order small-thickness approximation to the three-dimensional theory for thin sheets. Applications to axisymmetric equilibria are developed in detail, and applied to describe the phenomenon of bulge propagation in cylinders.

scholarly journals The effect of the outlet angle β2 on the thermomechanical behavior of a centrifugal compressor blade

2020 ◽  
Vol 29 (1) ◽  
pp. 1-8
Author(s):  
Ahmed Allali ◽  
Sadia Belbachir ◽  
Ahmed Alami ◽  
Belhadj Boucham ◽  
Abdelkader Lousdad
Keyword(s):  
Mechanical Behavior ◽  
Centrifugal Compressor ◽  
Three Dimensional ◽  
Complex Form ◽  
Compressor Blade ◽  
Stress Fields ◽  
The Finite Element Method ◽  
Mechanical Fatigue ◽  
Outlet Angle ◽  
The Impact

AbstractThe objective of this work lies in the three-dimensional study of the thermo mechanical behavior of a blade of a centrifugal compressor. Numerical modeling is performed on the computational code "ABAQUS" based on the finite element method. The aim is to study the impact of the change of types of blades, which are defined as a function of wheel output angle β2, on the stress fields and displacements coupled with the variation of the temperature.This coupling defines in a realistic way the thermo mechanical behavior of the blade where one can note the important concentrations of stresses and displacements in the different zones of its complex form as well as the effects at the edges. It will then be possible to prevent damage and cracks in the blades of the centrifugal compressor leading to its failure which can be caused by the thermal or mechanical fatigue of the material with which the wheel is manufactured.

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