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  • 1
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    Experimental evaluation of an advanced Space Shuttle main engine hot-gas manifold design concept (1985)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: This study, using an extensively modified, full-scale space shuttle main engine (SSME) hot-gas manifold (HGM), established a detailed aerodynamic data base to support development of an advanced, three-dimensional, fluid-dynamic analysis computer model. In addition, the advanced SSME hot-gas manifold design used in this study demonstrated improved flow environment (uniformity) in the fuel side turbine exit and transfer duct exit regions. Major modifications were incorporated in the full-scale HGM flow test article model using two large transfer ducts on the fuel turbine side of the HGM in place of the three small transfer ducts in the present design. Other model features included an increases in the flow areas downstream of the 180-degree turn and in the fishbowl regions.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Marshall Space Flight Center Advan. High Pressure O2(H2 Technol.; p 512-547
    Format: application/pdf
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  • 2
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    Engine system assessment study using Martian propellants (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A feasibility study was performed that identified and characterized promising chemical propulsion system designs that utilize two or more of the propellant combinations: LOX/H2, LOX/CH4 and LOX/CO. The engine systems examined focused on the usage of common subsystem/component hardware where feasible. From the evaluation baseline employed, tripropellant MTV LOX cooled and bipropellant LEV and MEV engine systems are identified.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 92-3446
    Format: text
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  • 3
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    Feasibility of Mapping Velocity Flow Fields in SSME Powerhead by Laser Anemometry Techniques (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Because of the flow environment associated with the SSME powerhead pressure (3000 psia), temperature (1800 R), and mechanical complexity and the high vibration test stand environment, detailed flow measurements are difficult to make. The feasibility of using laser anemometry techniques to map velocity flow fields in an SSME powerhead is studied. In the study three engine powerhead component flow environments: (1) the high pressure fuel turbopump preburner, (2) the fuel turbopump turbine rotor and stator region, and (3) the 180 deg turnaround duct - are being considered. Flow parameters measured by the anemometry techniques are time averaged values of the velocity magnitude and flow direction, turbulence intensity, velocity component correlation, integral time scale, and turbulence spectrum.
    Keywords: SPACECRAFT INSTRUMENTATION
    Type: NASA. Lewis Research Center Struct. Integrity and Durability of Reusable Space Propulsion Systems; p 199
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Feasibility of mapping velocity flowfields in an SSME powerhead using laser anemometry techniques (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Nonintrusive anemometry measurement techniques are investigated for a NASA study of steady and unsteady aerothermal flow phenomena present in three engine component flow environments in the Space Shuttle Main Engine powerhead, the: (1) high-pressure fuel turbopump preburner; (2) turbine; and (3) turnaround duct. Issues considered include identification of feasible means of optical access to the high-pressure high-temperature measurement flow regions, and measurement system compatibility with the test environment. Descriptions of the two-component LDV and Laser Two Focus measurement systems are given whose capabilities include measurements of the time-averaged values of velocity magnitude and flow direction, turbulence intensity, and velocity component correlations.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: AIAA PAPER 87-1306
    Format: text
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  • 5
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    Turbulent eddy diffusivity and mean eddy lifetimes measured in spray combustion (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: A quantitative description of the eddy structure that occurs in turbulent combustion processes can be obtained by the use of laser velocimetry, as shown in this work. The mean eddy length scales, eddy lifetimes, and turbulent diffusivity have been determined in a spray combustion flame for the first time. Velocity data was obtained at various locations within the flame, and standard correlation techniques were modified and then applied to reduce the data. In order to assess how the spray burns, the measured eddy lifetimes were compared with the relevant reaction times and drop lifetimes. Conditions that are conducive to group combustion of the droplets, rather than individual droplet combustion, were found to exist in the upstream region of the spray. Local measurements of the hydrocarbon concentration also support the conclusion that the majority of droplets undergo group combustion. However, the data indicate that some of the larger drops can survive the initial burning region and form a dilute spray downstream where conditions favor individual droplet combustion.
    Keywords: INORGANIC AND PHYSICAL CHEMISTRY
    Type: Combustion Science and Technology; 21; 5-6,; 1980
    Format: text
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  • 6
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    Computational Simulation Of A Nuclear Engine (1995)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Nuclear Engine System Simulation (NESS) computer program developed to satisfy need for accurate, stand-alone software tool for preliminary design analysis of nuclear thermal propulsion (NTP) engine system. Used for rapid, preliminary detailed design analysis of both reactor and key engine systems. Principal outputs include operating characteristics and weights of reactors, engine-system parameters as performances, weights, dimensions, pressures, temperatures, and mass flows, and operating characteristics of turbopumps under both design and off-design operating conditions. Written in FORTRAN 77.
    Keywords: MACHINERY
    Type: LEW-15586 , NASA Tech Briefs (ISSN 0145-319X); 19; 6; P. 68
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Laser velocimetry measurements in a gas turbine research combustor (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The effects of turbulence on the production of pollutant species in a gas-turbine research combustor are studied using laser diffraction velocimetry (LDV) techniques. Measurements that were made in the primary combustion zone include mean velocity, rms velocity fluctuations, velocity probability distributions, and autocorrelation functions. A unique combustor design provides relatively uniform flow conditions and independent control of drop size, equivalence ratio, inlet temperature, and combustor pressure. Parameters which characterize the nature of the spray combustion (i.e., whether single droplet or group combustion occurs), were determined from the LDV data. Turbulent diffusivity (eddy viscosity) reaches a value of 2930 sq cm/sec, corresponding to a convective integral length scale of 1.8 cm. The group combustion number, based on turbulent diffusivity, is measured to be 6.2
    Keywords: INORGANIC AND PHYSICAL CHEMISTRY
    Type: Laser velocimetry and particle sizing; Third International Workshop; Jul 11, 1978 - Jul 13, 1978; West Lafayette, IN
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Experimental evaluation of an advanced Space Shuttle Main Engine hot-gas manifold design concept (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The Space Shuttle Main Engine's hot gas manifold (HGM) has been the subject of an experimental study aimed at the establishment of an aerodynamic data base to support the development of an advanced, three-dimensional, fluid dynamic analysis computer model. The advanced HGM design used in the study demonstrated improved flow uniformity in the fuel-side turbine exit and transfer duct exit regions. Major modifications were incorporated in the HGM flow test article model, using two large transfer ducts on the fuel turbine side in place of the three small transfer ducts of the present design. The HGM flow field data were found to be essentially independent of Reynolds number over the range examined.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 84-1463
    Format: text
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  • 9
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    The effect of fuel sprays on emissions from a gas turbine combustor (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A research gas turbine combustor which allows for independent control of drop size, fuel/air ratio, air inlet temperature, pressure, reference velocity, and residence time has been used to study the influence of fuel spray characteristics on primary zone emissions. Local concentrations of oxides of nitrogen, carbon monoxide and unburned hydrocarbons at various locations in the flow, local gas temperature, gas velocity, and the turbulence intensity (measured with laser velocimetry) are obtained. A comprehensive data analysis program to compute the local fuel/air ratio and the sum of the mole fractions of the species present confirms the validity of the emissions data. Increasing drop size is correlated with an increase in unburned hydrocarbons, while increasing residence time is associated with sharp decreases in hydrocarbons and carbon monoxide and an increase in oxides of nitrogen.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 79-1321 , AIAA, SAE, and ASME, Joint Propulsion Conference; Jun 18, 1979 - Jun 20, 1979; Las Vegas, NV
    Format: text
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