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  • 1
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    STGSTK- PREDICTING MULTISTAGE AXIAL-FLOW COMPRESSOR PERFORMANCE BY A MEANLINE STAGE-STACKING METHOD (1994)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: The STGSTK computer program was developed for predicting the off-design performance of multistage axial-flow compressors. The axial-flow compressor is widely used in aircraft engines. In addition to its inherent advantage of high mass flow per frontal area, it can exhibit very good aerodynamic performance. However, good aerodynamic performance over an acceptable range of operating conditions is not easily attained. STGSTK provides an analytical tool for the development of new compressor designs. The simplicity of a one-dimensional compressible flow model enables the stage-stacking method used in STGSTK to have excellent convergence properties and short computer run times. Also, the simplicity of the model makes STGSTK a manageable code that eases the incorporation, or modification, of empirical correlations directly linked to test data. Thus, the user can adapt the code to meet varying design needs. STGSTK uses a meanline stage-stacking method to predict off-design performance. Stage and cumulative compressor performance is calculated from representative meanline velocity diagrams located at rotor inlet and outlet meanline radii. STGSTK includes options for the following: 1) non-dimensional stage characteristics may be input directly or calculated from stage design performance input, 2) stage characteristics may be modified for off-design speed and blade reset, and 3) rotor design deviation angle may be modified for off-design flow, speed, and blade setting angle. Many of the code's options use correlations that are normally obtained from experimental data. The STGSTK user may modify these correlations as needed. This program is written in FORTRAN IV for batch execution and has been implemented on an IBM 370 series computer with a central memory requirement of approximately 85K of 8 bit bytes. STGSTK was developed in 1982.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: LEW-14025
    Format: text
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  • 2
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    The design and development of transonic multistage compressors (1988)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The development of the transonic multistage compressor is reviewed. Changing trends in design and performance parameters are noted. These changes are related to advances in compressor aerodynamics, computational fluid mechanics and other enabling technologies. The parameters normally given to the designer and those that need to be established during the design process are identified. Criteria and procedures used in the selection of these parameters are presented. The selection of tip speed, aerodynamic loading, flowpath geometry, incidence and deviation angles, blade/vane geometry, blade/vane solidity, stage reaction, aerodynamic blockage, inlet flow per unit annulus area, stage/overall velocity ratio, and aerodynamic losses are considered. Trends in these parameters both spanwise and axially through the machine are highlighted. The effects of flow mixing and methods for accounting for the mixing in the design process are discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Von Karman Institute for Fluid Dynamics, Transonic Compressors, Volume 2; 97 p
    Format: application/pdf
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  • 3
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    Predicting the Performance of an Axial-Flow Compressor (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Stage-stacking computer code (STGSTK) developed for predicting off-design performance of multi-stage axial-flow compressors. Code uses meanline stagestacking method. Stage and cumulative compressor performance calculated from representative meanline velocity diagrams located at rotor inlet and outlet meanline radii. Numerous options available within code. Code developed so user modify correlations to suit their needs.
    Keywords: MECHANICS
    Type: LEW-14025 , NASA Tech Briefs (ISSN 0145-319X); 9; 4; P. 146
    Format: text
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  • 4
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    Performance of low-pressure-ratio low-tip-speed fan stage with blade tip solidity of 0.65 (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The overall and blade-element performance of a low pressure ratio, low tip speed fan stage is presented over the stable operating range at rotative speeds from 90 to 120 percent of design speed. Stage peak efficiency of 0.927 was obtained at a weight flow of 32.4 kg/sec (190.31 kg/sec/sq m of annulus area) and a pressure ratio of 1.134. The stall margin at design speed and peak efficiency was 15.3 percent.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3341 , E-7604
    Format: application/pdf
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  • 5
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    Performance of inlet stage of transonic compressor (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The overall and blade-element performances are presented over the stable flow operating range of the stage at the design tip speed of 426 m/sec. Stage peak efficiency of 0.83 was obtained at a weight flow of 28.8 kg/sec and a pressure ratio of 1.52. The stall margin for the stage was 8 percent based on weight flow and pressure ratio at peak efficiency and stall. The rotor appears to be stalling prematurely as evidenced by high rotor tip losses.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3345 , E-8056
    Format: application/pdf
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  • 6
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    Preliminary analysis of the effectiveness of variable-geometry guide vanes to control rotor-inlet flow conditions (1967)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Feasibility of variable geometry guide vanes for controlling rotor inlet flow parameters
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TN-D-3823
    Format: application/pdf
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  • 7
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    Analytical studies of aspect ratio and curvature variations for axial flow compressor inlet stages under high loading (1967)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Analyses of aspect ratio and curvature variations for axial flow compressor inlet stages under loading
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-3959
    Format: application/pdf
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  • 8
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    Aerodynamic performance of a 1.35-pressure-ratio axial-flow fan stage (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The overall blade element performances and the aerodynamic design parameters are presented for a 1.35-pressure-ratio fan stage. The fan stage was designed for a weight flow of 32.7 kilograms per second and a tip speed of 302.8 meters per second. At design speed the stage peak efficiency of 0.879 occurred at a pressure ratio of 1.329 and design flow. Stage stall margin was approximately 14 percent. At design flow rotor efficiency was 0.94 and the pressure ratio was 1.360.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1299 , E-9025
    Format: application/pdf
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  • 9
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    STGSTK: A computer code for predicting multistage axial flow compressor performance by a meanline stage stacking method (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A FORTRAN computer code is presented for off-design performance prediction of axial-flow compressors. Stage and compressor performance is obtained by a stage-stacking method that uses representative velocity diagrams at rotor inlet and outlet meanline radii. The code has options for: (1) direct user input or calculation of nondimensional stage characteristics; (2) adjustment of stage characteristics for off-design speed and blade setting angle; (3) adjustment of rotor deviation angle for off-design conditions; and (4) SI or U.S. customary units. Correlations from experimental data are used to model real flow conditions. Calculations are compared with experimental data.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-2020 , E-551 , NAS 1.60:2020
    Format: application/pdf
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  • 10
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    Aerodynamic performance of a 1.25-pressure-ratio axial-flow fan stage (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Aerodynamic design parameters and overall and blade-element performances of a 1.25-pressure-ratio fan stage are reported. Detailed radial surveys were made over the stable operating flow range at rotative speeds from 70 to 120 percent of design speed. At design speed, the measured stage peak efficiency of 0.872 occurred at a weight flow of 34.92 kilograms per second and a pressure ratio of 1.242. Stage stall margin is about 20 percent based on the peak efficiency and stall conditions. The overall peak efficiency for the rotor was 0.911. The overall stage performance showed no significant change when the stators were positioned at 1, 2, or 4 chords downstream of the rotor.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3083 , E-7800
    Format: application/pdf
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