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  • 1
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    Propulsion systems technology (1975)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: The selection of components, control design, simulation, and tests are examined for designing supersonic propulsion systems. Inlet-engine combination under electronic control are shown. Design and test results from the integrated control for afterburning turbofan and supersonic cruise inlet are presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeron. Propulsion; p 387-440
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Experimental results of a deflected thrust V/STOL nozzle research program (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Four deflected thrust nozzle concepts, designed to operate at the low pressure ratio typical of high bypass-ratio turbofan engines for medium speed (subsonic) V/STOL aircraft, were studied. Maps of overall performance characteristics and exit velocity distributions are used to highlight similarities and differences between the four concepts. Analytically determined secondary flows at the exit of a 90 deg circular pipe bend are compared with the experimental results from the more complex three dimensional geometries. The relative impact of total-pressure losses and secondary flows on nozzle thrust coefficient is addressed by numerical integration of exit velocity measurements. Previously announced in STAR as N83-25657
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 83-0170
    Format: text
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  • 3
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    Effect of screen-induced total-pressure distortion on axial-flow compressor stability (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental investigation was made to determine the effects of screen-induced total-pressure distortions on two J85-GE-13 turbojet engines. Results were compared to those from a previous program run with a third engine. All compressors were found to be sensitive to a critical angle of circumferential distortion equal to 60 deg., and they all adhered closely to the parallel compressor model. The sensitivity of compressor exit pressure to virtually any type of distortion pattern can be determined by defining stall lines for undistorted, hub radial distorted, and tip radial distorted inflows. The effect of multiple sectors of circumferential distortion is defined.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3017 , E-7792
    Format: application/pdf
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  • 4
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    Instantaneous distortion in a Mach 2.5, 40-percent-internal-contraction inlet and its effect on turbojet stall margin (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental wind tunnel investigation was conducted to determine the effects of time-variant distortions produced in a supersonic inlet on a J85-GE-13 turbojet engine. Results are presented principally in terms of instantaneous distortion amplitudes and total-pressure contours measured through compressor stall. They indicate that, although a time-averaged distortion may be far from a stall-inducing value, corresponding instantaneous distortion amplitudes can approach or exceed this value. Seven engine stall events were studied. In six of these events instantaneous distortion peaks of sufficient magnitude to cause stall were observed in the time period shortly before stall was detected.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-3002 , E-6294
    Format: application/pdf
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  • 5
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    Unstart and stall interactions between a turbojet engine and an axisymmetric inlet with 60-percent internal-area contraction (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Effects of turbojet engine unstart on engine operation and characteristics of stall propagation through compressor and inlet system
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-2192 , E-5923
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    A method to account for variation of average compressor inlet pressure during instantaneous distortion analyses (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Instantaneous distortion analyses compare a time-varying value of an index (or 'surge margin used up') with a critical level (or 'available surge margin' of the compressor) to determine inlet-engine compatibility. Unless freestream conditions or propulsion system controls are changing, it is generally assumed that the available surge margin of the compressor is accurately determined from the steady-state operating point. Results are presented which show that variations of average compressor inlet pressure may occur without changes in freestream conditions or propulsion system controls. The volume dynamics of the compressor will cause these pressure variations to be attenuated and delayed by the time they reach the exit. This will cause the compressor pressure ratio (and available surge margin) to vary with time. 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: AERODYNAMICS
    Type: AIAA PAPER 76-703 , Propulsion Conference; Jul 26, 1976 - Jul 29, 1976; Palo Alto, CA
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  • 7
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    Formulation of a distortion index based on peak compressor pressure ratios (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: In order to effectively use a compressor face total-pressure distortion index as a measure of inlet-engine compatibility, a correlation of distortion amplitude with stall margin must be developed with minimal scatter. A recent analysis of data recorded in extensive distortion screen tests with the J85-GE-13 turbojet engine has resulted in a correlation based on compressor discharge pressure ratioed to the minimum pressure at the compressor face. Simply by determining compressor stall lines with a single hub radial distortion pattern, a single tip radial pattern, and with undistorted inflow, the overall compressor pressure ratio at stall for even the most complex distortion pattern was found to be predictable.
    Keywords: PROPULSION SYSTEMS
    Type: National Conference on Environmental Effects on Aircraft and Propulsion Systems; May 21, 1974 - May 23, 1974; Trenton, NJ
    Format: text
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  • 8
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    Instantaneous and dynamic analysis of supersonic inlet-engine compatibility (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Wind tunnel tests for instantaneous and dynamic analysis of effects of time-variant distortions produced in supersonic inlet on J85-GE-13 turbojet engine
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-67821
    Format: application/pdf
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  • 9
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    Experimental investigation of the effect of screen induced total pressure distortion on turbojet stall margin (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Effect of circumferential, radial, and combined pressure distortions on stall margin of J-85 engine
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2239 , E-5981
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Flow visualization and interpretation of visualization data for deflected thrust V/STOL nozzles (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Flow visualization studies were made for four deflected thrust nozzle models at subsonic speeds. Based on topological rules and the assumption that observed streaks constitute continuous vector fields, available visualization pictures are interpreted and flow patterns on interior surfaces of the nozzles are synthesized. In particular, three dimensional flow structure and separations are discussed. From the synthesized patterns, the overall features of the flow field in a given nozzle can be approximately perceived. Previously announced in STAR as N84-14147
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 84-0102
    Format: text
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