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  • Other Sources  (7)
  • AIRCRAFT PROPULSION AND POWER  (7)
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  • Other Sources  (7)
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  • 1
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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
  • 2
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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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    NASA TECHNICAL REPORTS
  • 3
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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
  • 4
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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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    NASA TECHNICAL REPORTS
  • 5
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    Analysis of dynamic inlet distortion applied to a parallel compressor model (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation of surge was conducted by using a parallel compressor model of the J85-13 compressor implement on an analog computer. Surges were initiated by various types of dynamic disturbances in inlet pressure. The compressor model was less sensitive to disturbances of short duration, high frequency, and long duration where the compressor discharge pressure could react. Adding steady distortion to dynamic disturbances reduced the amount of dynamic disturbance required to effect surge. Steady and unsteady distortions combined linearly to reduce surge margin.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-3522 , E-8979
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Experimental program for the evaluation of turbofan/turboshaft c conversion technology (1981)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A TF34 turbofan engine is being modified to produce shaft power from an output coupling on the fan disk when variable inlet guide vanes are closed to reduce fan airflow. The engine, called a convertible engine, could be used on advanced rotorcraft such as X-wing, ABC (Advanced Blade Concept), and Folding Tilt Rotor, and on V/STOL craft in which two engines are cross-coupled. The engine will be tested on an outdoor static test stand at NASA Lewis Research Center. Steady-state tests will be made to measure performance in turbofan, turboshaft, and combined power output modes. Transient tests will be made to determine the response to the engine and a new digital engine control system for several types of rapid changes in thrust and shaft loads. The paper describes the engine modifications, the test facility equipment, proposed testing techniques for several types of tests, and typical test results predicted from engine performance computer programs.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-82988 , E-1420 , NAS 1.15:82988 , AHS-RWP-19 , AD-A233790 , Rotary Wing Propulsion System Specialist Meeting; Nov 16, 1982 - Nov 18, 1982; Williamsburg, VA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    A method to account for variation of average compressor inlet pressure during instantaneous distortion analyses (1976)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A method is presented to calculate the available surge margin as a function of time and incorporate it into an instantaneous distortion analysis. Results show that inlet pressure variations which cause only a small change at the compressor exit can cause a significant variation in the available surge margin.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-73438 , E-8793 , Propulsion Conf.; Jul 26, 1976 - Jul 29, 1976; Palo Alto, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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