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  • 1
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    Experimental verification of a double-dead-time model describing chugging in liquid- bipropellant rocket engines. (1967)
    In:  Other Sources
    Details
    Publication Date: 2018-12-01
    Description: Stability boundaries of double-dead-time model describing chugging in liquid bipropellant rocket engine
    Keywords: PROPULSION SYSTEMS
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Analysis of chugging in liquid-bipropellant rocket engines using propellants with different vaporization rates (1965)
    In:  CASI
    Details
    Publication Date: 2019-05-24
    Description: Model for prediction of low-frequency stability limits for bipropellant rocket engines
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TN-D-3080
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Investigation of the starting characteristics of the M-1 rocket engine using the analog computer (1965)
    In:  CASI
    Details
    Publication Date: 2019-05-29
    Description: Starting characteristics of M- I liquid propellant rocket engine using analog computer simulation
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TN-D-3136
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Experimental Investigation of Temperature Feedback Control Systems Applicable to Turbojet-engine Control (1957)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Temperature - fuel-flow and temperature-area feedback control systems were investigated as means of controlling tailpipe gas temperature of a turbojet engine during transient operation in the high-speed region. Proportional-plus-integral control was used in both systems, but in the temperature-area control system it was necessary to add nonlinear components to the basic proportional-plus-integral control to provide satisfactory transient response to a desired step increase in temperature. Time integral of temperature-error functions were used as criteria for determining optimum transient response. A description of engine dynamics was obtained from frequency-response data.
    Type: NACA-TN-3936
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Experimental Comparison of Speed : Fuel-flow and Speed-area Controls on a Turbojet Engine for Small Step Disturbances (1957)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Optimum proportional-plus-integral control settings for speed - fuel-flow control, determined by minimization of integral criteria, correlated well with analytically predicted optimum settings. Engine response data are given for a range of control settings around the optimum. An inherent nonlinearity in the speed-area loop necessitated the use of nonlinear controls. Response data for two such nonlinear control schemes are presented.
    Type: NACA-TN-3926
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Real-time hybrid computer simulation of a small turboshaft engine and control system (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The development of an analytical model of a small turboshaft engine designed for helicopter propulsion systems is described. The model equations were implemented on a hybrid computer system to provide a real time nonlinear simulation of the engine performance over a wide operating range. The real time hybrid simulation of the engine was used to evaluate a microprocessor based digital control module. This digital control module was developed as part of an advanced rotorcraft control program. After tests with the hybrid engine simulation the digital control module was used to control a real engine in an experimental program. A hybrid simulation of the engine's electrical hydromechanical control system was developed. This allowed to vary the fuel flow and torque load inputs to the hybrid engine simulation for simulating transient operation. A steady-state data and the experimental tests are compared. Analytical model equations, analog computer diagrams, and a digital computer flow chart are included.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-83579 , E-1968 , NAS 1.15:83579
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Effect of casing treatment on performance of a multistage compressor (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: AJ85-GE-13 engine was equipped with a compressor case which allowed changes to the case wall over the rotor tips of six of its stages. The engine was tested with four inlet configurations: undistorted and with 180 deg circumferential, hub radial, and tip radial distortions. Baseline data defining compressor performance and stall regions were taken for these inlet configurations with solid (untreated) compressor case inserts. Circumferentially grooved inserts were installed in the first three and last three stages, and the compressor was mapped under similar conditions. The compressor was mapped a third time with untreated inserts in the first three stages and inserts having slots conforming to blade angles in the last three stages. In most cases, the stall pressure ratio was the same as or lower than the baseline. Pumping capacity with the slotted inserts was reduced. Overall compressor efficiency with the grooved rings installed did not appreciably differ from the baseline, but it was 1 to 2 percentage points lower than the baseline with the slotted rings in place. Average stage characteristics for the undistorted inlet case showed little or no sensitivity to casing treatment.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-3175 , E-8085
    Format: application/pdf
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  • 8
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    Performance of a J85-13 compressor with clean and distorted inlet flow (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results presented are of a series of experimental tests in which a J85-13 turbojet engine was subjected to both distorted and undistorted inlet total pressure conditions. A distinctive feature of the data base obtained is that it includes compressor interstage information not previously recorded for a J85-13 engine. Each of the eight compressor stages was instrumented to obtain the characteristics of the individual stages for undistorted inlet conditions, and these data are documented in the report along with the undistorted compressor overall performance. Also included in the report is the overall performance of the compressor exposed to 14 different distorted-inlet conditions - 10 circumferential patterns and 4 radial patterns. The distortion patterns were introduced using screens that spoiled from 8 to 50 percent of the compressor face area; the distortion screen density, or the area blocked by the screen wire per unit area of screen, varied from 26 to 69 percent.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-3304 , E-8311
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Power train analysis for the DOE/NASA 100-kW wind turbine generator (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Progress in explaining variations of power experienced in the on-line operation of a 100 kW experimental wind turbine-generator is reported. Data are presented that show the oscillations tend to be characteristic of a wind-driven synchronous generator because of low torsional damping in the power train, resonances of its large structure, and excitation by unsteady and nonuniform wind flow. The report includes dynamic analysis of the drive-train torsion, the generator, passive driveline damping, and active pitch control as well as correlation with experimental recordings. The analysis assumes one machine on an infinite bus with constant generator-field excitation.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-TM-78997 , DOE/NASA/1028-78/19 , E-9413
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Analytical investigation of nonrecoverable stall (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A lumped parameter model of the TF34 engine is formulated to study nonrecoverable stall. Features of the model include forward and reverse flow, radial flow in the fan, and variable corrected speed. The purpose of the study is to point out those parameters to which recoverability is highly sensitive but are not well known. Experimental research may then be directed toward identification of the parameters in that category. Compressor performance in the positive flow region and radial flow in the fan are shown to be important but unknown parameters determining recoverability. Other parameters such as compressor performance during reverse flow and in-stall efficiency have relatively small impact on recoverability.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-82792 , E-1126 , NAS 1.15:82792
    Format: application/pdf
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