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  • 1
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    Comparison of Predicted and Experimental Heat-Transfer and Pressure-Drop Results for an Air-Cooled Plug Nozzle and Supporting Struts (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A calculational procedure is presented to analyze the heat-transfer and fluid-flow characteristics of a convectively air -cooled plug-nozzle operating on an afterburning turbojet engine. Anderson's method was used to predict hot-gas static pressures in the supersonic stream with fully expanded flow (high nozzle-pressure ratios); the results were excellent. For low nozzle-pressure ratios, the flow was assumed to expand one-dimensionally and isentropically to the plug back pressure. Wall temperatures predicted using this latter pressure distribution agreed well with the wall temperatures predicted using the measured hot-gas pressures (maximum deviation was about 30 K (54 deg R)). Either an in tegral boundary-layer technique or a simple pipe-flow equation may be used to calculate convective heat transfer from the hot gas to the wall. The simple pipeflow equation results in the prediction of slightly higher wall temperatures than does the integral technique. Experimental wall temperatures were generally in good agreement with the two predicted wall temperature distributions. Excellent agreement was noted b etween measured and predicted coolant static-pressure distributions. The plug-coolant temperature rise was generally overpredicted by about 22.2 K (40 deg R); possible explanations are offered. Although an an alysis of the struts, which support the plug, was purposely kept simple, reasonable results were obtained. Potential flow over an ellipse was used to calculate hot-gas static pressure; the results were satisfactory.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-6764 , E-6709
    Format: application/pdf
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  • 2
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    Summary of recent investigations of inlet flow distortion effect on engine stability (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A review is presented of recent experimental results, analytical procedures and test techniques employed to evaluate the effects of inlet flow distortion on the stability characteristics of representative afterburning turbofan and turbojet compression systems. Circumferential distortions of pressure and temperature, separately and in combination are considered. Resulting engine sensitivity measurements are compared with predictions based on simplified parallel compressor models and with several distortion descriptor parameters.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-71505 , E-7878 , Aerospace Sci. Meeting; Jan 30, 1974 - Feb 01, 1974; Washington, DC; United States
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  • 3
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    Summary of recent investigations of inlet flow distortion effects on engine stability (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A review is presented of recent experimental results, analytical procedures and test techniques employed to evaluate the effects of inlet flow distortion on the stability characteristics of representative afterburning turbofan and turbojet compression systems. Circumferential distortions of pressure and temperature, separately and in combination, are considered. Resulting engine sensitivity measurements are compared with predictions based on simplified parallel compressor models and with several distortion descriptor parameters.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 74-236 , Aerospace Sciences Meeting; Jan 30, 1974 - Feb 01, 1974; Washington, DC
    Format: text
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  • 4
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    The effect of inlet temperature and pressure distortion on turbojet performance (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The effects on stability of steady-state, 180 degree extent circumferential distortions of inlet total temperature and pressure were experimentally determined for a turbojet engine. Results for both individual and combined temperature and pressure distortions are presented showing the losses incurred in stall pressure ratio and are compared with results predicted using a simplified parallel compressor model. The loss due to combined distortions was dependent upon the relative orientation between the low pressure and high temperature regions. Reasonable agreement was achieved between the predicted and observed loss in stall pressure ratio when based on a constant corrected speed relationship.
    Keywords: PROPULSION SYSTEMS
    Type: AIAA PAPER 73-1316 , Propulsion Conference; Nov 05, 1973 - Nov 07, 1973; Las Vegas, NV; US
    Format: text
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  • 5
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    The effects of inlet temperature and pressure distortion on turbojet performance (1973)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The effects on stability of steady-state, 180 degree extent circumferential distortions of inlet total temperature and pressure were experimentally determined for a turbojet engine. Results for both individual and combined temperature and pressure distortions are presented showing the losses incurred in stall pressure ratio and are compared with results predicted using a simplified parallel compressor model. The loss due to combined distortions was dependent upon the relative orientation between the low pressure and high temperature regions. Reasonable agreement was achieved between the predicted and observed loss in stall pressure ratio when based on a constant corrected speed relationship.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-71431 , E-7302 , Propulsion Joint Specialists Conf.; Nov 05, 1973 - Nov 07, 1973; Las Vegas, NV; United States
    Format: application/pdf
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