Author: K. H. LauPublisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Development of Computer Program to Solve Flow Through a Multi-stage Axial Compressor
Author: K. H. LauComputer Program for Aerodynamic and Blading Design of Multistage Axial-flow Compressors
Author: James E. CrousePublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 112
Book Description
A code for computing the aerodynamic design of a multistage axial-flow compressor and, if desired, the associated blading geometry input for internal flow analysis codes is presented. The aerodynamic solution gives velocity diagrams on selected streamlines of revolution at the blade row edges. Blading is defined from stacked blade elements associated with the selected streamlines. The blade element inlet and outlet angles are established through empirical incidence and deviation angle adjustments to the relative flow angles of the velocity diagrams. The blade element centerline is composed of two segments tangentially joined at a transition point. The local blade angle variation of each segment can be specified with a fourth-degree polynomial function of path distance. Blade element thickness also can be specified with fourth-degree polynomial functions of path distance from the maximum thickness point.
Computer Program for Design of Multistage Axial-flow Compressors
Author: A. C. BryansWISGSK, a Computer Code for the Prediction of a Multistage Axial Compressor Performance with Water Ingestion
Author: T. TsuchiyaPublisher:
ISBN:
Category : Compressors
Languages : en
Pages : 268
Book Description
Users Manual for Updated Computer Code for Axial-Flow Compressor Conceptual Design
Author: National Aeronautics and Space Administration (NASA)Publisher: Createspace Independent Publishing Platform
ISBN: 9781722931087
Category :
Languages : en
Pages : 24
Book Description
An existing computer code that determines the flow path for an axial-flow compressor either for a given number of stages or for a given overall pressure ratio was modified for use in air-breathing engine conceptual design studies. This code uses a rapid approximate design methodology that is based on isentropic simple radial equilibrium. Calculations are performed at constant-span-fraction locations from tip to hub. Energy addition per stage is controlled by specifying the maximum allowable values for several aerodynamic design parameters. New modeling was introduced to the code to overcome perceived limitations. Specific changes included variable rather than constant tip radius, flow path inclination added to the continuity equation, input of mass flow rate directly rather than indirectly as inlet axial velocity, solution for the exact value of overall pressure ratio rather than for any value that met or exceeded it, and internal computation of efficiency rather than the use of input values. The modified code was shown to be capable of computing efficiencies that are compatible with those of five multistage compressors and one fan that were tested experimentally. This report serves as a users manual for the revised code, Compressor Spanline Analysis (CSPAN). The modeling modifications, including two internal loss correlations, are presented. Program input and output are described. A sample case for a multistage compressor is included. Glassman, Arthur J. Unspecified Center NAG3-1165; RTOP 505-69-50...
Optimizing the Efficiency of a Multi-Stage Axial-Flow Compressor
Author: Shawn A. MillerPublisher:
ISBN: 9781423563297
Category : Axial flow compressors
Languages : en
Pages : 94
Book Description
The development of jet engines has become an integral part of maintaining air superiority. In order to achieve the most advanced engine, research has turned to traditional optimization methods to aid in creating new engine designs. To develop simplified mathematical models representative of the engine, the engine can be separated into its components. A jet engine has three major elements, the compressor, combustion chamber and turbine. This research attempts to make an initial analysis of a two stage compressor to determine values of blade angles and spacing to chord ratios for both stages that produce the highest possible efficiency for the overall two stage compressor. A pitch line model is developed for a two stage compressor and is used in conjunction with a optimization method to solve for the on design air angles and spacing to chord ratios. The results of the model were compared to examples available in current literature to ensure the model properly represents a compressor stage. The off design performance of the results was calculated to determine how the designs for on design operated under off design conditions. Since practical compressors are made up of many stages, consideration is given to which optimization method would be most useful in solving for a multistage compressor.
STGSTK
Author: Ronald J. SteinkePublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 74
Book Description
STGSTK: A Computer Code for Predicting Multistage Axial Flow Compressor Performance by a Meanline Stage Stacking Method
Author: Off-Design Computer Code for Calculating the Aerodynamic Performance of Axial-Flow Fans and Compressors
Author: National Aeronautics and Space Adm NasaPublisher:
ISBN: 9781730977305
Category :
Languages : en
Pages : 96
Book Description
An off-design axial-flow compressor code is presented and is available from COSMIC for predicting the aerodynamic performance maps of fans and compressors. Steady axisymmetric flow is assumed and the aerodynamic solution reduces to solving the two-dimensional flow field in the meridional plane. A streamline curvature method is used for calculating this flow-field outside the blade rows. This code allows for bleed flows and the first five stators can be reset for each rotational speed, capabilities which are necessary for large multistage compressors. The accuracy of the off-design performance predictions depend upon the validity of the flow loss and deviation correlation models. These empirical correlations for the flow loss and deviation are used to model the real flow effects and the off-design code will compute through small reverse flow regions. The input to this off-design code is fully described and a user's example case for a two-stage fan is included with complete input and output data sets. Also, a comparison of the off-design code predictions with experimental data is included which generally shows good agreement. Schmidt, James F. Unspecified Center...
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