Development and validation of a new universal through flow method for axial compressors

2010 ◽  
Vol 224 (6) ◽  
pp. 869-880 ◽  
Author(s):  
M V Petrovic ◽  
A Wiedermann ◽  
M B Banjac
Keyword(s):  
Axial Compressors ◽  
Flow Method ◽  
Through Flow ◽  
Development And Validation

An Integrated Design System for Fans, Compressors, and Turbines: Part 4 — Through-Flow Solver

2005 ◽  
Author(s):  
Allen Medlock ◽  
Max J. Miller ◽  
S. Murthy Konan ◽  
Ben Chambers ◽  
Bao Q. Nguyen
Keyword(s):  
Integrated Design ◽  
Design System ◽  
Aerodynamic Design ◽  
Flow Paths ◽  
Flow Solver ◽  
Axial Compressors ◽  
Interactive Interface ◽  
Through Flow ◽  
Design Cycle ◽  
Access Information

A new aerodynamic design system has been developed that includes a through-flow solver for fans, axial compressors and turbines, and radial compressors and turbines. Three earlier papers gave an overview of the system and described the interactive interface and geometry generators. This paper focuses on several special features in the through-flow solver that provide increases in aerodynamic designer productivity. Some of the key features are stations decoupled from flow paths, ability to accept a wide variety of input parameters, use of gas property routines, ability to inject flow non-uniformly with a different composition than the main flow gas composition, ability to access information from several airfoil geometry generator solutions, and clear, comprehensive error handling. These special features and others have provided major savings from productivity improvements and reductions in design cycle time.

Development of an aero-thermal coupled through-flow method for cooled turbines

2015 ◽  
Vol 58 (12) ◽  
pp. 2060-2071 ◽  
Author(s):  
ChunWei Gu ◽  
HaiBo Li ◽  
Yin Song
Keyword(s):  
Flow Method ◽  
Through Flow

Multistage Axial Compressor Flow Field Predictions Using CFD and Through-Flow Calculations

2016 ◽  
Author(s):  
Milan Banjac ◽  
Milan V. Petrovic ◽  
Alexander Wiedermann
Keyword(s):  
Axial Compressor ◽  
Operating Conditions ◽  
Test Cases ◽  
Axial Compressors ◽  
Geometric Configurations ◽  
Through Flow ◽  
Blade Row ◽  
Operation Parameters ◽  
Flow Variables ◽  
Multistage Axial Compressor

A comparison between two different methods for aerodynamic calculation of multistage axial compressors is presented. Results obtained using classical 2D through-flow calculations were compared with CFD results for several test cases, including various subsonic and supersonic multistage axial compressors with different geometric configurations and stage operating parameters. Calculated flow fields were compared in terms of overall compressor performances, individual blade row operation parameters and spanwise distributions of different flow variables. Nominal and off-design compressor operating conditions were analyzed and all the results were compared with experimental data. Accuracy, advantages and differences between individual methods are discussed.

A Three-Dimensional Unsteady Through-Flow Model for Rotating Stall in Axial Compressors

2020 ◽  
Author(s):  
Jin Guo ◽  
Jun Hu ◽  
Xuegao Wang ◽  
Rong Xu
Keyword(s):  
Flow Model ◽  
Flow Behavior ◽  
Three Dimensional ◽  
Axial Compressor ◽  
Rotating Stall ◽  
Design Stage ◽  
Preliminary Evaluation ◽  
Source Terms ◽  
Axial Compressors ◽  
Through Flow

Abstract Rotating stall is a natural limit to the stable operating range of compressors due to the inverse pressure gradient of viscous gas. Effective prediction of compressor stall boundary is an important guarantee for the successful development of aeroengine. In this paper, a three-dimensional unsteady through-flow model based on body force theory is developed to reflect the dynamic stall process of multistage axial compressors with acceptable computational costs. The influence of blade geometric parameters is fully considered in blade force source terms. The source terms are related to the attack angle and Mach number of the blade inlet using the deviation angle and loss model in the through-flow theory. Meanwhile, the temporal lag response of the source terms to the upstream flow conditions is taken into account. Therefore, it can be utilized for predicting the off-design performance and rotating stall characteristics of multistage axial compressors. The developed model is validated on a two-stage low-speed axial compressor. The calculated performance line and stall cell speed are in agreement with the experimental results. The unsteady flow behavior of the compressor during stall is presented by the model. The results indicate that the developed model has the potential to be applied to the preliminary evaluation of compressor stability in design stage.

Development and Validation of a New Universal Through Flow Method for Axial Compressors

2009 ◽  
Author(s):  
Milan V. Petrovic ◽  
Alexander Wiedermann ◽  
Milan B. Banjac
Keyword(s):  
Flow Analysis ◽  
Solution Procedure ◽  
Operating Conditions ◽  
Distribution Model ◽  
Test Cases ◽  
Flow Method ◽  
Through Flow ◽  
Wide Range ◽  
Flow Effects ◽  
And Performance

This paper describes the development of a new through flow method for the analysis of axial multistage compressors. The method is based on a stream function approach and a finite element solution procedure. It includes a high-fidelity loss and deviation model with improved correlations and endwall boundary layer calculation. A radial distribution model of losses and a new spanwise mixing model are applied to simulate 3D flow effects. The calibration of the models is made by calculation a number of test cases with different configurations with the aim of achieving high accuracy and optimum robustness for each of the test cases considered. The code was applied to flow analysis and performance prediction of a newly developed gas turbine compressor. Comparison of the predicted results and measured test data for the overall compressor performance and a number of parameters under different operating conditions showed good agreement. The results of the validation confirm that this method based on calibrated correlations can be applied as a reliable tool for flow analysis and parameter variation during the design phase for a wide range of compressor configurations.

scholarly journals Through - flow method of making lemonade.

1962 ◽  
Vol 8 (9) ◽  
pp. 206-209
Author(s):  
P. FILKA ◽  
I. ZELENKA
Keyword(s):  
Flow Method ◽  
Through Flow

Through-Flow Models for Mass and Momentum-Averaged Variables

1987 ◽  
Vol 109 (3) ◽  
pp. 362-370 ◽  
Author(s):  
C. Hirsch ◽  
R. P. Dring
Keyword(s):  
Current Practice ◽  
Incompressible Flows ◽  
Flow Data ◽  
Rigorous Derivation ◽  
Flow Equations ◽  
Flow Models ◽  
Axial Compressors ◽  
Blockage Factor ◽  
Through Flow ◽  
Flow Components

The turbomachinery through-flow equations are reformulated for mass and momentum-averaged quantities. The background of this analysis is the need for an improved assessment of the accuracy of through-flow computations. Traditional through-flow analyses are based on density-weighted averaged quantities reducing to an area average in incompressible flows. On the other hand, experimental data are usually evaluated under the form of mass-averaged quantities, particularly with regard to the overall energy balance and efficiency estimations. The transition between these two sets of quantities is usually taken into account by introducing an averaged aerodynamic blockage factor in addition to the blade blockage factor resulting from the density-averaged quantities. The present analysis provides a rigorous derivation for the momentum-averaged flow quantities and shows that some strong assumptions on the nature of the nonaxisymmetric flow components are necessary in order to justify the current practice of introducing aerodynamic blockage. The recent availability of detailed flow data in single and two-stage axial compressors allows a partial validation of these assumptions, by the comparison of the various nonaxisymmetric components.

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