Aerodynamic Design and Performance of Five-Stage Transonic Axial-Flow Compressor

1961 ◽  
Vol 83 (3) ◽  
pp. 303-320 ◽  
Author(s):  
Karl Kovach ◽  
D. M. Sandercock
Keyword(s):  
Research Work ◽  
Axial Flow ◽  
Performance Characteristics ◽  
Research Center ◽  
Aerodynamic Design ◽  
Axial Flow Compressor ◽  
Turbojet Engine ◽  
And Performance ◽  
Flow Compressor ◽  
Work Done

A five-stage axial-flow compressor with all rotors operating with transonic relative inlet Mach numbers was designed as a research vehicle at the Lewis Research Center in 1952. The compressor was designed and tested as a component of a turbojet engine. This paper summarizes the research work done on this compressor including the aerodynamic design and detailed performance characteristics.

scholarly journals A Turbojet Simulator for Mach Numbers up to 2.0

1972 ◽  
Author(s):  
F. W. Steffen ◽  
E. A. Satmary ◽  
M. R. Vanco ◽  
S. M. Nosek
Keyword(s):  
High Pressure ◽  
Wind Tunnel ◽  
Axial Flow ◽  
Calibration Procedure ◽  
Aerodynamic Design ◽  
Flight Data ◽  
Axial Flow Compressor ◽  
Heated Air ◽  
Turbojet Engine ◽  
Flow Compressor

A turbojet simulator has been designed and fabricated for use in wind tunnel models. The simulator contains a six-stage, axial-flow compressor powered by a three-stage, axial-flow turbine. High pressure heated air was used to drive the turbine. At design conditions, compressor axial flow, turbine exit flow, and a third supplementary flow all entered the exhaust nozzle at equal values of pressure and temperature. Overall aerodynamic design, instrumentation, and calibration procedure is presented. Performance of the device when used to simulate a J-85 turbojet engine at transonic speeds is reported. The installed nozzle performance obtained with the simulator is also discussed and compared with flight data.

Aerodynamic Design and Testing of an Axial Flow Compressor for the GT24/26 Gas Turbines

2013 ◽  
Author(s):  
Damir Novak ◽  
Michael Loetzerich ◽  
Matthias Boese
Keyword(s):  
Gas Turbines ◽  
Pressure Ratio ◽  
Axial Flow ◽  
Leading Edge ◽  
Advanced Technology ◽  
Aerodynamic Design ◽  
3D Design ◽  
Axial Flow Compressor ◽  
Stage Matching ◽  
Flow Compressor

A 22-stage axial flow compressor with a pressure ratio 35:1 has been designed, built and successfully tested for a heavy-duty gas turbine application. Advanced technology and aero engine design tools have been used. The compressor has been designed using an “arbitrary” airfoil blading including 3D design features, like leading edge re-camber, lean, sweep and flowpath contouring. The compressor performance and part load behavior have been improved by accurate stage matching based on whole compressor 3D analyses. The new compressor has been tested in a scaled down rig and validated in the Alstom Test Power Plant (ATPP).The compressor met all design objectives and demonstrated excellent performance. This paper describes the aerodynamic design and test results.

scholarly journals The Use of Experimental Interstate Data for Matching the Performance of Axial Compressor Stages Having Variable-Setting-Angle Blade Rows

1976 ◽  
Author(s):  
L. E. Brown
Keyword(s):  
Rotor Blade ◽  
Axial Compressor ◽  
Axial Flow ◽  
Performance Characteristics ◽  
Test Rig ◽  
Axial Flow Compressor ◽  
Component Test ◽  
Experimental Tool ◽  
Angle Blade ◽  
Flow Compressor

Stage performance characteristics provide a powerful analytic tool for experimentally matching the stages and blade rows of an axial-flow compressor, while the variable stage compressor component test rig provides a most powerful experimental tool for developing compressors. This paper describes: Why and how the stage characteristics “normalized” to correct them for changes of stator setting angles, how these normalized characteristics can be fully defined for every stage; and how these characteristic can point the way to a well-matched configuration of setting angles. In addition, it proposes methods for distinguishing between the stall of rotors and stators and for normalizing the characteristics of stages with variable-setting rotor blade rows.

Flow Analysis of Axial Compressor AV63-15 Variable Stator Simulation

2012 ◽  
Vol 532-533 ◽  
pp. 474-478
Author(s):  
Wei Hua Cheng ◽  
Mian Chang Li ◽  
Chuan Peng Li
Keyword(s):  
Flow Analysis ◽  
Three Dimensional ◽  
Axial Compressor ◽  
Axial Flow ◽  
Operating Conditions ◽  
Axial Flow Compressor ◽  
Air Supply ◽  
The Difference ◽  
And Performance ◽  
Flow Compressor

This paper conducts numerical simulation to a 15-stage civil axial flow compressor and obtains its main parameters distribution and performance curve by a full three-dimensional viscid flow computation software. The computation result indicates that, the developed axial flow compressor meets the anticipated design requirements, and satisfies the customers’ indicators. Under the designed compression ratio, the difference between the maximum air supply quantity in summer and the minimum air supply quantity in winter is 22%. By comparing the operating conditions and data analysis, obtained the change trend of axial velocity, static pressure and temperature, and Ma, and discovered that, under opening of 48° and outlet back pressure of 550KPa, flow separation occurred on the section of machine set close to hud, which indicated that operating condition was close to surging condition.

Performance Predicting Modeling of Axial-Flow Compressor at Design and Off-Design Conditions

2008 ◽  
Author(s):  
Ali Madadi ◽  
Ali Hajilouy Benisi
Keyword(s):  
Performance Prediction ◽  
Work Performance ◽  
Axial Flow ◽  
Accurate Method ◽  
Performance Characteristics ◽  
One Dimensional ◽  
Axial Flow Compressor ◽  
Dimensional Modeling ◽  
Flow Compressor ◽  
Axial Flow Compressors

Axial flow compressor is one of the most important parts of gas turbine units. Therefore, its design and performance prediction are very important. One-dimensional modeling is a simple, fast and accurate method for performance prediction of any type of compressors with different geometries. In this approach, inlet flow conditions and compressor geometry are known and by considering various compressor losses, velocity triangles at rotor, and stator inlets and outlets are determined, and then compressor performance characteristics are predicted. Numerous models have been developed theoretically and experimentally for estimating various types of compressor losses. In present work, performance characteristics of the axial-flow compressor are predicted based on one-dimensional modeling approach. In this work, models of Lieblein, Koch-Smith, Herrig, Johnsen-Bullock, Pollard-Gostelow, Aungier, Hunter-Cumpsty Reneau are implemented to consider compressor losses, incidence angles, deviation angles, stall and surge conditions. The model results are compared with experimental data to validate the model. This model can be used for various types of single stage axial-flow compressors with different geometries, as well as multistage axial-flow compressors.

Axial flow compressor design†

1999 ◽  
Vol 213 (5) ◽  
pp. 437-449 ◽  
Author(s):  
S. J. Gallimore
Keyword(s):  
Design Process ◽  
Axial Flow ◽  
Point Of View ◽  
Aerodynamic Design ◽  
Basic Principles ◽  
Axial Flow Compressor ◽  
Compressor Design ◽  
Aero Engines ◽  
Flow Compressor ◽  
Practical Constraints

The purpose of this paper is to set out some of the basic principles and rules associated with the design of axial flow compressors, principally for aero-engines, as well as the practical constraints that are inevitably present. The thrust is primarily on the aerodynamic design but this cannot be divorced from the mechanical aspects and so some of these are touched upon but are not gone into so deeply. The paper has been written from the point of view of the designer and tries to cover most of the points that need to be considered in order to produce a successful compressor. The emphasis has been on the theory behind the design process and on minimizing the reliance on empirical rules. However, because of the complexity of the flow, some empiricism still remains.

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