Inverse Design of Radial Compressor Components by Modern CFD

2000 ◽  
Author(s):  
R. A. Van den Braembussche ◽  
J. Antolin ◽  
R. Thygesen
Keyword(s):  
Velocity Distribution ◽  
Inverse Method ◽  
Three Dimensional ◽  
Inverse Methods ◽  
Inverse Design ◽  
Centrifugal Impeller ◽  
Design Criteria ◽  
Radial Compressor ◽  
Inlet Guide Vanes ◽  
Return Channel

Abstract The use of a three-dimensional inverse method for the design of inlet guide vanes, a centrifugal impeller and return channel is demonstrated. The geometry of the different components are iteratively defined until a prescribed velocity distribution is obtained. The procedure and design criteria for each component are described and the final result is presented. The advantages, disadvantages and problems related to the use of inverse methods are discussed.

A Three-Dimensional Inverse Method for Turbomachinery: Part I—Theory

1990 ◽  
Vol 112 (3) ◽  
pp. 346-354 ◽  
Author(s):  
J. E. Borges
Keyword(s):  
Velocity Field ◽  
Inverse Method ◽  
Three Dimensional ◽  
Tangential Velocity ◽  
Inverse Methods ◽  
Meridional Section ◽  
Low Speed ◽  
Present Procedure ◽  
Blade Row ◽  
The Mean

There are surprisingly few inverse methods described in the literature that are truly three dimensional. Here, one such method is presented. This technique uses as input a prescribed distribution of the mean swirl, i.e., radius times mean tangential velocity, given throughout the meridional section of the machine. In the present implementation the flow is considered inviscid and incompressible and is assumed irrotational at the inlet to the blade row. In order to evaluate the velocity field inside the turbomachine, the blades (supposed infinitely thin) are replaced by sheets of vorticity, whose strength is related to the specified mean swirl. Some advice on the choice of a suitable mean swirl distribution is given. In order to assess the usefulness of the present procedure, it was decided to apply it to the design of an impeller for a low-speed radial-inflow turbine. The results of the tests are described in the second part of this paper.

Improving a Vaned Diffuser for a Given Centrifugal Impeller by 3D Inverse Design

2002 ◽  
Author(s):  
Mehrdad Zangeneh ◽  
Damian Vogt ◽  
Christian Roduner
Keyword(s):  
Flow Field ◽  
Viscous Flow ◽  
Centrifugal Compressor ◽  
Inverse Method ◽  
Flow Distribution ◽  
Inverse Design ◽  
Centrifugal Impeller ◽  
Design Code ◽  
Vaned Diffuser ◽  
Blade Loading

In this paper the application of 3D inverse design code TURBOdesign−1 to the design of the vane geometry of a centrifugal compressor vaned diffuser is presented. For this study the new diffuser is designed to match the flow leaving the conventional impeller, which is highly non-uniform. The inverse method designs the blade geometry for a given specification of thickness and blade loading distribution. The paper describes the choice of loading distribution used in the design as well as the influence of the diffuser inlet flow distribution on the vane geometry and flow field. The flow field in the new diffuser is analysed by a 3D viscous flow code and the result is compared to that of the conventional diffuser. Finally the results of testing the stage performance of the new diffuser is compared with that of the conventional stage.

Application of a Three-Dimensional Inverse Method to the Design of a Centrifugal Compressor Impeller

1998 ◽  
Author(s):  
Alain Demeulenaere ◽  
Olivier Léonard ◽  
René Van den Braembussche
Keyword(s):  
Centrifugal Compressor ◽  
Inverse Method ◽  
Three Dimensional ◽  
Navier Stokes ◽  
Centrifugal Impeller ◽  
Mean Velocity ◽  
Blade Shape ◽  
Compressor Impeller ◽  
Real Performance ◽  
The Mean

The use of a three-dimensional Euler inverse method for the design of a centrifugal impeller is demonstrated. Both the blade shape and the endwalls are iteratively designed. The meridional contour is modified in order to control the mean velocity level in the blade channel, while the blade shape is designed to achieve a prescribed loading distribution between the inlet and the outlet. The method salves the time dependent Euler equations in a numerical domain of which some boundaries (the blades or the endwalls) move and change shape during the transient part of the computation, until a prescribed pressure distribution is achieved on the blade surfaces. The method is applied to the design of a centrifugal compressor impeller, whose hub endwall and blade surfaces are modified by the inviscid inverse method. The real performance of both initial and modified geometries are compared through three-dimensional Navier-Stokes computations.

A Three Dimensional Inverse Method in Turbomachinery: Part I — Theory

1989 ◽  
Author(s):  
João Eduardo Borges
Keyword(s):  
Velocity Field ◽  
Inverse Method ◽  
Three Dimensional ◽  
Tangential Velocity ◽  
Inverse Methods ◽  
Meridional Section ◽  
Low Speed ◽  
Present Procedure ◽  
Blade Row ◽  
The Mean

There are surprisingly few inverse methods described in the literature that are truly three-dimensional. Here, one such method is presented. This technique uses as input a prescribed distribution of the mean swirl, i.e., radius times mean tangential velocity, given throughout the meridional section of the machine. In the present implementation the flow is considered inviscid and incompressible and is assumed irrotational at inlet to the blade row. In order to evaluate the velocity field inside the turbomachine, the blades (supposed infinitely thin) are replaced by sheets of vorticity whose strength is related to the specified mean swirl. Some advice on the choice of a suitable mean swirl distribution is given. In order to assess the usefulness of the present procedure, it was decided to apply it to the design of an impeller of a low-speed radial-inflow turbine. The results of the tests are described in the second part of this paper.

scholarly journals Three-Dimensional Inverse Design of Low Specific Speed Turbine for Energy Recovery in Cooling Tower System

Energies ◽  
2018 ◽  
Vol 11 (12) ◽  
pp. 3348
Author(s):  
Wei Yang ◽  
Xiaoyu Lei ◽  
Benqing Liu
Keyword(s):  
Response Surface ◽  
Three Dimensional ◽  
Inverse Design ◽  
Design Parameters ◽  
Design Criteria ◽  
Blade Loading ◽  
Turbine Runner ◽  
Lean Angle ◽  
Low Specific Speed ◽  
Specific Speed

A three-dimensional inverse design of a low specific speed turbine is studied, and a set of design criteria for low specific speed turbine runner is proposed, including blade loading distributions and blade lean angles. The characteristics of the loading parameters for low specific speed turbine runner are summarized by analyzing the suction performance of different loading positions, loading slopes and blade lean angles based on the orthogonal experiment design and range analysis. It is found that the blade loading distribution at the band plays a more important role than it does at the crown and it should be fore loaded for both band and crown. The blade lean angle at the blade leading edge should be negative. Then, the blade is optimized through the inverse method by fixing blade lean angle, based on the response surface method. After seeking the optimal value of the response surface function, the optimal result of the design parameters is obtained, which is in conformity with the design criteria and verifies the rationality of the established design criteria for low specific speed turbine.

A Method for Transonic Inverse Cascade Design With a Stream Function Equation

1986 ◽  
Vol 108 (2) ◽  
pp. 200-205 ◽  
Author(s):  
Manchu Ge ◽  
Yiping Lou ◽  
Zhengti Yu
Keyword(s):  
Velocity Distribution ◽  
Stream Function ◽  
Transonic Flow ◽  
Inverse Method ◽  
Design Method ◽  
Thickness Distribution ◽  
Three Dimensional ◽  
Suction Surface ◽  
Stream Surface ◽  
Optimal Velocity

A new profile design method is developed on the basis of [1–3] for transonic flow. The rotational dynamic stream function equation, which is expressed in functional form using calculated coordinates, is deduced. This method can be used for the calculation of cascade and S1 stream surface of a transonic flow with a local shock wave on the blade suction surface. This method consists of two parts: an inverse method with a given velocity distribution along the suction surface and a given thickness distribution; and an inverse method with given velocity distributions on suction and pressure surfaces. Using this method it is easy to obtain a blade profile with prescribed velocity and thickness distributions. The design of optimal profile may then be done with the calculated optimal velocity distribution on the blade surface. The rotational condition is satisfied when the stream function equation is adopted with the entropy term. If the compatibility condition can be fulfilled between the S1 and S2 equations, the iterative calculations of two kinds of stream surfaces in three-dimensional flow will be convergent. In this paper a unique value of density can be determined from the known stream function value. The computational program is written with this method and several transonic examples have been calculated. These results are quite good.

On the role of three-dimensional inverse design methods in turbomachinery shape optimization

1999 ◽  
Vol 213 (1) ◽  
pp. 27-42 ◽  
Author(s):  
M Zangeneh ◽  
A Goto ◽  
H Harada
Keyword(s):  
Flow Field ◽  
Inverse Method ◽  
Design Method ◽  
Three Dimensional ◽  
Design Guidelines ◽  
Secondary Flows ◽  
Inverse Design ◽  
Vaned Diffuser ◽  
Oil Flow ◽  
Inverse Design Method

The application of a three-dimensional (3D) inverse design method in which the blade geometry is computed for a specified distribution of circulation to the design of turbomachinery blades is explored by using two examples. In the first instance the method is applied to the design of radial and mixed flow impellers to suppress secondary flows. Based on our understanding of the fluid dynamics of the flow in the impeller, simple guidelines are developed for input specification of the inverse method in order to systematically design impellers with suppressed secondary flows and a more uniform exit flow field. In the second example the method is applied to the design of a vaned diffuser. Again based on the understanding of the detailed flow field in the diffuser obtained by using 3D viscous calculations and oil flow visualizations, simple design guidelines are developed for input specification to the inverse method in order to suppress corner separation. In both cases the guidelines are verified numerically and in the case of the diffuser further experimental validation is presented.

Application of Flow Control in a Novel Sector Test Rig

2013 ◽  
Vol 136 (4) ◽  
Author(s):  
Alexander Simpson ◽  
Christian Aalburg ◽  
Michael B. Schmitz ◽  
Robbert Pannekeet ◽  
Vittorio Michelassi ◽  
...  
Keyword(s):  
Flow Control ◽  
Numerical Study ◽  
Three Dimensional ◽  
Test Rig ◽  
Blow Down ◽  
Radial Compressor ◽  
Injection Flow ◽  
The Matrix ◽  
Return Channel ◽  
Formed Part

An experimental and numerical study has been performed to evaluate the effectiveness of steady injection flow control for the reduction of losses in the return channel of a radial compressor. This investigation formed part of an overall attempt to develop a strategy for reducing the diffusion ratio of radial compressors. It is envisaged that this flow control would be activated at off-design conditions, where separation levels on the return channel vanes are considerable. A novel radial compressor sector test rig, supported by a blow-down facility and equipped with a range of instrumentation, was used for the experimental portion of the study. This allowed multiple flow control configurations to be studied in a simplified environment. A set of exchangeable, inlet guide vanes provide the test vanes with the correct inlet three-dimensional flow-field, while airfoil static pressure taps allowed the blade loading to be assessed. The numerical portion of the study was conducted using 3D-computational fluid dynamics (CFD) and involved simulations of both the sector test rig and a “substitute system”. In this paper, the rationale for the inclusion of flow control in a radial compressor return channel is discussed. The sector test rig is then described, including the implementation of flow control. The results of the matrix of flow control experiments are then discussed with comparison to the numerical results.

A neural network approach for centrifugal impeller inverse design

2000 ◽  
Vol 214 (2) ◽  
pp. 183-186 ◽  
Author(s):  
H-Y Fan
Keyword(s):  
Neural Network ◽  
Velocity Distribution ◽  
Back Propagation ◽  
Basic Structure ◽  
Inverse Design ◽  
Surface Velocity ◽  
Centrifugal Impeller ◽  
Network Approach ◽  
Back Propagation Algorithm ◽  
Neural Network Approach

In this paper a neural network approach is proposed to solve an inverse design problem of a centrifugal impeller when the basic structure parameter and the hub-shroud contours are known, and the expected blade surface velocity distribution is given. The proposed neural networks have a four-layered feedforward architecture and are trained with finite samples by means of a back-propagation algorithm. The simulations show that the trained networks can yield a blade shape that generates the expected velocity distribution on its surface.

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