Discussion: “Transonic Flow Analysis in Axial-Flow Turbomachinery Cascades by a Time-Dependent Method of Characteristics” (Delaney, R. A., and Kavanagh, P., 1976, ASME J. Eng. Power, 98, pp. 356–363)

Solutions for transonic flow in cascades are determined by a second-order time-dependent method of characteristics using bicharacteristics. The analysis method is based on unsteady, two-dimensional, compressible, inviscid flow with steady-state solutions computed as the asymptotic limit in time of transient solutions. Two turbine cascade cases are presented. The first involves subsonic flow throughout the cascade; the second involves subsonic inlet and discharge flows with transonic flow over a portion of the cascade passage. In both cases, the computed results for blade surface pressure distribution are compared with experimental data. Generally good agreement is shown.

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Aerodynamic modelling of multistage compressor flow fields Part 1: Analysis of rotor-stator-rotor aerodynamic interaction

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering ◽

10.1243/0954410981532153 ◽

1998 ◽

Vol 212 (2) ◽

pp. 77-89 ◽

Cited By ~ 6

Author(s):

E J Hall

Keyword(s):

Flow Analysis ◽

Axial Flow ◽

Sensitivity Study ◽

Time Dependent ◽

Turbine Engine ◽

Mesh Density ◽

Multistage Compressors ◽

Dependent Flow ◽

Aerodynamic Modelling ◽

Flow Compressor

The primary purpose of this study was to investigate improved numerical techniques for predicting flows through multistage compressors. The vehicle chosen for this study was the Pennsylvania State University Research Compressor (PSRC). The PSRC facility consists of a 3 1/2-stage axial flow compressor which shares design features which are consistent with embedded stages of modern gas turbine engine axial flow compressors. In Part 1 of this two-part paper, several computational fluid dynamics techniques were applied to predict both steady and unsteady flows through the PSRC facility. Interblade row coupling via a circumferentially averaged mixing-plane approach was employed for steady flow analysis. A mesh density sensitivity study was performed to define the minimum mesh requirements necessary to achieve reasonable agreement with the experimental data. Time-dependent flow predictions were performed using a time-dependent interblade row coupling technique. These calculations evaluated the aerodynamic interactions occurring between rotor 2, stator 2 and rotor 3 for the PSRC rig.

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Aerodynamic Modeling of Multistage Compressor Flowfields: Part 1 — Analysis of Rotor/Stator/Rotor Aerodynamic Interaction

Volume 1: Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery ◽

10.1115/97-gt-344 ◽

1997 ◽

Cited By ~ 2

Author(s):

Edward J. Hall

Keyword(s):

Flow Analysis ◽

Axial Flow ◽

Sensitivity Study ◽

Time Dependent ◽

State University ◽

Turbine Engine ◽

Mesh Density ◽

Multistage Compressors ◽

Dependent Flow ◽

Flow Compressor

The primary purpose of this study was to investigate improved numerical techniques for predicting flows through multistage compressors. The vehicle chosen for this study was the Pennsylvania State University Research Compressor (PSRC). The PSRC facility consists of a 3-1/2 stage axial flow compressor which shares design features which are consistent with embedded stages of modern gas turbine engine axial flow compressors. In Part 1 of this two part paper, several Computational Fluid Dynamics (CFD) techniques were applied to predict both steady and unsteady flows through the PSRC facility. Inter-blade row coupling via a circumferentially-averaged mixing plane approach was employed for steady flow analysis. A mesh density sensitivity study was performed to define the minimum mesh requirements necessary to achieve reasonable agreement with the experimental data. Time dependent flow predictions were performed using a time dependent interblade row coupling technique. These calculations evaluated the aerodynamic interactions occurring between the second rotor, second stator, and third rotor for the PSRC rig.

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A second-order method of characteristics for two-dimensional unsteady flow with application to turbomachinery cascades

10.31274/rtd-180813-3403 ◽

1974 ◽

Author(s):

Robert Anthony Delaney

Keyword(s):

Unsteady Flow ◽

Method Of Characteristics ◽

Second Order ◽

Two Dimensional ◽

Order Method ◽

Turbomachinery Cascades

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Laminar boundary layers behind detonation waves

Proceedings of the Royal Society of London Series A - Mathematical and Physical Sciences ◽

10.1098/rspa.1983.0063 ◽

1983 ◽

Vol 387 (1793) ◽

pp. 331-349 ◽

Cited By ~ 3

Keyword(s):

Heat Transfer ◽

Boundary Layer ◽

Boundary Layers ◽

Flow Analysis ◽

Time Dependent ◽

Detonation Waves ◽

Planar Geometry ◽

Laminar Boundary Layers ◽

Spherical Detonation ◽

Layer Flow

New solutions are presented for non-stationary boundary layers induced by planar, cylindrical and spherical Chapman-Jouguet (C-J) detonation waves. The numerical results show that the Prandtl number ( Pr ) has a very significant influence on the boundary-layer-flow structure. A comparison with available time-dependent heat-transfer measurements in a planar geometry in a 2H 2 + O 2 mixture shows much better agreement with the present analysis than has been obtained previously by others. This lends confidence to the new results on boundary layers induced by cylindrical and spherical detonation waves. Only the spherical-flow analysis is given here in detail for brevity.

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

Volume 2C: Turbomachinery ◽

10.1115/gt2016-56717 ◽

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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The Development of an Aerodynamic Performance Prediction Tool for Modern Axial Flow Compressor Profiles

Volume 6: Turbomachinery, Parts A and B ◽

10.1115/gt2006-90187 ◽

2006 ◽

Cited By ~ 1

Author(s):

Dario Bruna ◽

Carlo Cravero ◽

Mark G. Turner

Keyword(s):

Performance Prediction ◽

Parametric Design ◽

Flow Analysis ◽

Axial Flow ◽

Navier Stokes ◽

Flow Angle ◽

Flow Solver ◽

Aerodynamic Loss ◽

Axial Flow Compressor ◽

Flow Compressor

The development of a computational tool (MP-LOS) for the aerodynamic loss modeling and prediction for axial-flow compressor blade sections is presented in this paper. A state-of-the-art quasi 3-D flow solver, MISES, has been used for the flow analysis on existing airfoil geometries in many working conditions. Different values of inlet flow angle, inlet Mach number, AVDR, Reynolds number and solidity have been chosen to investigate a possible working range. The target is a loss prediction formulation that will be introduced into throughflow or axisymmetric Navier-Stokes codes for the performance prediction of multistage axial flow compressors. The loss coefficient has been correlated to the flow parameters that have shown an influence on the profile loss for the blades under study. The proposed correlation, using the described computational approach, can be extended to any profile family with the aid of any code for the parametric design of blade profiles.

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