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  • 1
    Electronic Resource
    Electronic Resource
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 13 (1967), S. 52-60 
    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: A unified theory of one-dimensional, adiabatic, separated, two-phase flow is presented. To describe the flow adequately, four mixture specific volumes are defined. They are based on area, momentum, kinetic energy, and velocity averages. Increasing relative velocity between the phases initially lowers all mixture specific volumes except the velocity average. The momentum average specific volume minimizes when the slip ratio equals (Vg/Vf)1/2, while the kinetic energy average specific volume reaches its minimum value at a slip ratio of (Vg/Vf)1/3. Area average specific value does not minimize with slip ratio.Because a higher slip ratio would decrease the entropy of a closed system, (Vg/Vf)1/3 is the maximum slip ratio attainable in two-phase critical flow. Based on the maximum slip ratio and isentropic flow, a new critical flow model was developed and compared with the steam-water critical flow data of four recent investigations. While the predicted flow rates followed well the pressure behavior of the experimental data, they were too low at high qualities and too high at low qualities. The average percentage difference between experimental and predicted critical flow rates was -8.5% (three hundred and seventy-six data points).Differences in the approach to critical flow between a gas and a vapor-liquid stream appear to be caused by the latter's increased frictional and gravitational pressure drops and relative velocity effects.
    Additional Material: 7 Ill.
    Type of Medium: Electronic Resource
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  • 2
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    In:  Other Sources
    Publication Date: 2018-12-01
    Description: Inspector role in prelaunch checkout of space system hardware
    Keywords: GENERAL
    Format: text
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  • 3
    Publication Date: 2019-07-13
    Description: Until recently, the design of jet engines for quiet operation was limited by engineers' ability to predict the jet noise generated by a nozzle exhaust system. More importantly, the 'intermediate steps' between nozzle design and noise had not been understood, limiting the design process to small variations around existing solutions. In recent years NASA's Quiet Aircraft Technology (QAT) Program has advanced the understanding and modeling of jet noise to give engineers the tools they need to design quiet nozzle systems for subsonic exhaust systems. The presentation discusses the approach followed for QAT and argues that a similar effort aimed at supersonic jet exhaust systems will be needed to allow designs of quiet military aircraft in the future.
    Keywords: Acoustics
    Type: E-14878 , Turbine Engine Technology Symposium 2004; Sep 02, 2004; Dayton, OH; United States
    Format: application/pdf
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  • 4
    Publication Date: 2019-07-13
    Description: The NASA Glenn Research Center recently completed an experimental study to reduce the jet noise from modern turbofan engines. The study concentrated on exhaust nozzle designs for high-bypass-ratio engines. These designs modified the core and fan nozzles individually and simultaneously. Several designs provided an ideal jet noise reduction of over 2.5 EPNdB for the effective perceived noise level (EPNL) metric. Noise data, after correcting for takeoff thrust losses, indicated over a 2.0-EPNdB reduction for nine designs. Individually modifying the fan nozzle did not provide attractive EPNL reductions. Designs in which only the core nozzle was modified provided greater EPNL reductions. Designs in which core and fan nozzles were modified simultaneously provided the greatest EPNL reduction. The best nozzle design had a 2.7-EPNdB reduction (corrected for takeoff thrust loss) with a 0.06-point cruise thrust loss. This design simultaneously employed chevrons on the core and fan nozzles. In comparison with chevrons, tabs appeared to be an inefficient method for reducing jet noise. Data trends indicate that the sum of the thrust losses from individually modifying core and fan nozzles did not generally equal the thrust loss from modifying them simultaneously. Flow blockage from tabs did not scale directly with cruise thrust loss and the interaction between fan flow and the core nozzle seemed to strongly affect noise and cruise performance. Finally, the nozzle configuration candidates for full-scale engine demonstrations are identified.
    Keywords: Acoustics
    Type: NASA/TM-2000-209948 , NAS 1.15:209948 , E-11714 , AIAA Paper 2000-1961 , Sixth Aeroacoustics Conference and Exhibit; Jun 12, 2000 - Jun 14, 2000; Lahaina, HI; United States
    Format: application/pdf
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