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  • 1
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    Design geometry and design/off-design performance computer codes for compressors and turbines (1995)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report summarizes some NASA Lewis (i.e., government owned) computer codes capable of being used for airbreathing propulsion system studies to determine the design geometry and to predict the design/off-design performance of compressors and turbines. These are not CFD codes; velocity-diagram energy and continuity computations are performed fore and aft of the blade rows using meanline, spanline, or streamline analyses. Losses are provided by empirical methods. Both axial-flow and radial-flow configurations are included.
    Keywords: AERODYNAMICS
    Type: NASA-CR-198433 , NAS 1.26:198433 , E-10041 , NIPS-95-06493
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Users manual and modeling improvements for axial turbine design and performance computer code TD2-2 (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Computer code TD2 computes design point velocity diagrams and performance for multistage, multishaft, cooled or uncooled, axial flow turbines. This streamline analysis code was recently modified to upgrade modeling related to turbine cooling and to the internal loss correlation. These modifications are presented in this report along with descriptions of the code's expanded input and output. This report serves as the users manual for the upgraded code, which is named TD2-2.
    Keywords: AERODYNAMICS
    Type: NASA-CR-189118 , E-6828 , NAS 1.26:189118
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Advanced core technology - Key to subsonic propulsion benefits (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A study was conducted to identify the potential performance benefits and key technology drivers associated with advanced cores for subsonic high bypass turbofan engines. Investigated first were the individual sensitivities of varying compressor efficiency, pressure ratio and bleed (turbine cooling); combustor pressure recovery; and turbine efficiency and inlet temperature on thermal efficiency and core specific power output. Then, engine cycle and mission performance benefits were determined for systems incorporating all potentially achievable technology advancements. The individual thermodynamic sensitivities are shown over a range of turbine temperatures (at cruise) from 2900 to 3500 R and for both constant (current technology) and optimum (maximum thermal efficiency) overall pressure ratios. It is seen that no single parameter alone will provide a large increase in core thermal efficiency, which is the thermodynamic parameter of most concern for transport propulsion. However, when all potentially achievable advancements are considered, there occurs a synergism that produces significant cycle and mission performance benefits. The nature of these benefits are presented along with the technology challenges.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: ASME PAPER 89-GT-241
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Enhanced analysis and users manual for radial-inflow turbine conceptual design code RTD (1995)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Modeling enhancements made to a radial-inflow turbine conceptual design code are documented in this report. A stator-endwall clearance-flow model was added for use with pivoting vanes. The rotor calculations were modified to account for swept blades and splitter blades. Stator and rotor trailing-edge losses and a vaneless-space loss were added to the loss model. Changes were made to the disk-friction and rotor-clearance loss calculations. The loss model was then calibrated based on experimental turbine performance. A complete description of code input and output along with sample cases are included in the report.
    Keywords: AERODYNAMICS
    Type: NASA-CR-195454 , E-9538 , NAS 1.26:195454
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Estimating turbine limit load (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A method for estimating turbine limit-load pressure ratio from turbine map information is presented and demonstrated. It is based on a mean line analysis at the last-rotor exit. The required map information includes choke flow rate at all speeds as well as pressure ratio and efficiency at the onset of choke at design speed. One- and two-stage turbines are analyzed to compare the results with those from a more rigorous off-design flow analysis and to show the sensitivities of the computed limit-load pressure ratios to changes in the key assumptions.
    Keywords: AERODYNAMICS
    Type: NASA-CR-191105 , E-7705 , NAS 1.26:191105
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Modeling Improvements and Users Manual for Axial-flow Turbine Off-design Computer Code AXOD (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An axial-flow turbine off-design performance computer code used for preliminary studies of gas turbine systems was modified and calibrated based on the experimental performance of large aircraft-type turbines. The flow- and loss-model modifications and calibrations are presented in this report. Comparisons are made between computed performances and experimental data for seven turbines over wide ranges of speed and pressure ratio. This report also serves as the users manual for the revised code, which is named AXOD.
    Keywords: AERODYNAMICS
    Type: NASA-CR-195370 , E-9052 , NAS 1.26:195370
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Computer code for preliminary sizing analysis of axial-flow turbines (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This mean diameter flow analysis uses a stage average velocity diagram as the basis for the computational efficiency. Input design requirements include power or pressure ratio, flow rate, temperature, pressure, and rotative speed. Turbine designs are generated for any specified number of stages and for any of three types of velocity diagrams (symmetrical, zero exit swirl, or impulse) or for any specified stage swirl split. Exit turning vanes can be included in the design. The program output includes inlet and exit annulus dimensions, exit temperature and pressure, total and static efficiencies, flow angles, and last stage absolute and relative Mach numbers. An analysis is presented along with a description of the computer program input and output with sample cases. The analysis and code presented herein are modifications of those described in NASA-TN-D-6702. These modifications improve modeling rigor and extend code applicability.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-4430 , E-6150 , NAS 1.26:4430
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Users manual for updated computer code for axial-flow compressor conceptual design (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    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.
    Keywords: COMPUTER PROGRAMMING AND SOFTWARE
    Type: NASA-CR-189171 , E-7003 , NAS 1.26:189171
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Enhanced capabilities and modified users manual for axial-flow compressor conceptual design code CSPAN (1995)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Modifications made to the axial-flow compressor conceptual design code CSPAN are documented in this report. Endwall blockage and stall margin predictions were added. The loss-coefficient model was upgraded. Default correlations for rotor and stator solidity and aspect-ratio inputs and for stator-exit tangential velocity inputs were included in the code along with defaults for aerodynamic design limits. A complete description of input and output along with sample cases are included.
    Keywords: AERODYNAMICS
    Type: NASA-TM-106833 , E-9394 , NAS 1.15:106833
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Enhanced capabilities and updated users manual for axial-flow turbine preliminary sizing code TURBAN (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Several modifications have been made to the axial-flow turbine preliminary sizing code TURBAN. Turbine cooling has been added to the analysis. New alternative input options allow direct specification of stage reaction, stage work factor, and stage work split. The Reynolds number loss dependency was modified and an internal calculation of air viscosity was added. A complete description of input and output along with sample cases are included.
    Keywords: AERODYNAMICS
    Type: NASA-CR-195405 , E-9252 , NAS 1.26:195405
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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