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  • 1
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    Nonisotropic exchange coefficients in turbulent swirling flames from mean value distributions (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Turbulent swirling flames nonisotropic exchange coefficients determination from time mean velocity, pressure, temperature and concentration distributions
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; - DISCRETE CONTROL S
    Format: text
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  • 2
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    Lateral jet injection into typical combustor flowfields (1984)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The trajectory, penetration and mixing efficiency of lateral air jet injection into typical combustor flowfields in the absence of combustion were investigated so as to characterize the time-mean and turbulence flowfield for a variety of configurations and input parameters, recommend appropriate turbulence model advances, and implement and exhibit results of flowfield predictions. A combined experimental and theoretical approach was followed, in a modified version of the test facility, equipped initially with one and two lateral jets, located one test-section downstream of the inlet.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Turbine Engine Hot Section Technology, 1984; 11 p
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  • 3
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    Lateral jet injection into typical combustor flowfields (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The experimental problem of lateral jet injection into typical flow fields in the absence of combustion was studied. All flow fields being investigated have no expansion of the crossflow (the test section to swirler diameter ratio D/d = 1), after its passage through an optional swirler (with swirl vane angle phi = 0 (swirler removed), 45, and 70 degree). The lateral jet(s) is(are) located one test-section diameter downstream of the test-section inlet (x/D = 1). The lateral jets have round-sectioned nozzles, each of which has an area of 1/100th of the cross sectional area of the crossflow (A sub j/A sub c = 1/100). Jet-to-crossflow velocity ratios of R = v sub j/u sub o = 2, 4, and 6 were investigated. Helium-bubble low visualization, five-hole pitot probe time-mean velocity measurements, and single-wire time-mean velocity and normal and shear stress turbulence data were obtained in the research program.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-3997 , NAS 1.26:3997
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  • 4
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    Hot-wire measurements of a single lateral jet injected into swirling crossflow (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: In the present experiments documenting the time-mean and turbulent flowfield of a deflected turbulent jet in a combined, swirling crossflow, attention is given to a jet-to-crossflow velocity ratio of 4 at swirler vane angles of 45 and 70 deg. The results obtained are presented in the form of r-x plots in order to aid in three-dimensional flowfield visualization. The time-mean velocity measurements were found to closely correspond to pitot-probe data obtained in identical flow conditions. The lateral jet was found to deflect the axis of the precessing vortex core.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 86-0055
    Format: text
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  • 5
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    Experiments on opposed lateral jets injected into swirling crossflow (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Experiments have been conducted to obtain the time-mean and turbulent quantities of opposed lateral jets in a low speed, nonreacting flowfield. A jet-to-crossflow velocity ratio of R = v sub J/u sub 0 = 4 was used throughout the experiments, with swirl vane angles of d = 0 (swirler removed), 45 and 70 deg used with the crossflow. Flow visualization techniques used were neutrally-buoyant helium-filled soap bubbles and multispark photography in order to obtain the gross flowfield characteristics. Measurements of time-mean and turbulent quantities were obtained utilizing a six-orientation single hot-wire technique. For the nonswirling case, the jets were found not to penetrate past the test-section centerline, in contrast to the single lateral jet with the same jet-to-crossflow velocity ratio. In the swirling cases, the crossflow remains in a narrow region near the wall of the test section. The opposed jets are swept from their vertical courses into spiral trajectories close to the confining walls. Extensive results are presented in r-x plane plots.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-175041 , NAS 1.26:175041
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  • 6
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    Measurements of a single lateral jet injected into swirling crossflow (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Experiments have been conducted to document the time-mean and turbulent flowfield of a deflected turbulent jet in a confined swirling crossflow. The jet-to-crossflow velocity ratio of 4 was investigated with swirler vane angles of 45 and 70 degrees. A six-orientation single hot-wire technique was used to measure the velocities and turbulence properties of the flow. In addition, a five-hole pitot probe technique was used to measure the time-mean velocities or verification purposes. The results are presented in the form of r-x plots to aid visualization of the fully three-dimensional flowfield. The swirl in the crossflow intensified the local velocity at the location of the injected jet, which effectively reduced the jet-to-crossflow velocity ratio. This caused the trajectory of the injected jet to follow the path of the local flow direction of the crossflow, and reduce its penetration into the crossflow. The time-mean velocity measurements using the hot-wire corresponded to pitot-probe data obtained in identical flow conditions. Turbulence stress data show the same trends as previous swirl flow data without lateral injection. The lateral jet was found to deflect the axis of the precessing vortex core.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-175040 , NAS 1.26:175040
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  • 7
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    Turbulent Combustor Flowfield Investigation (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The 2-D axisymmetric geometries under low speed, nonreacting, turbulent, swirling flow conditions were investigated. The effect of the parameters on isothermal flowfield patterns, time mean velocities and turbulence quantities is determined and an improved simulation in the form of a computer prediction code equipped with a suitable turbulence model is established. This is a prerequisite to the prediction of more complex turbulent reacting flows.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Combust. Fundamentals Res.; p 101-118
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  • 8
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    Investigations of flowfields found in typical combustor geometries (1984)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Studies are concerned with experimental and theoretical research on 2-D axisymmetric geometries under low speed, nonreacting, turbulent, swirling flow conditions. The flow enters the test section and proceeds into a larger chamber (the linear expansion ratio D/d = 2, 1.5 and 1) via a sudden or gradual expansion (side wall angle alpha = 90 and 45 degrees). A weak or strong nozzle (of area ratio A/a = 2 and 4) may be positioned downstream at x/D = 2 to form a contraction exit to the test section. Inlet swirl vanes are adjustable to a variety of vane angles with values of theta = 0, 38, 45, 60 and 70 degrees being emphasized. The objective is to determine the effect of these parameters on isothermal flow field patterns, time mean velocities and turbulence quantities, and to establish an improved simulation in the form of a computer prediction code equipped with a suitable turbulence model. The goal of the on going research is to perform experiments and complementary computations with the idea of doing the necessary type of research that will yield improved calculation capability. This involves performing experiments where time mean turbulence quantities are measured and taking input conditions and running an existing prediction code for a variety of test cases so as to compare predictions against experiment.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA. Lewis Research Center Combust. Fundamentals Res.; p 139-151
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  • 9
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    Predictions and measurements of isothermal flowfields in axisymmetric combustor geometries (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Numerical predictions, flow visualization experiments and time-mean velocity measurements were obtained for six basic nonreacting flowfields (with inlet swirl vane angles of 0 (swirler removed), 45 and 70 degrees and sidewall expansion angles of 90 and 45 degrees) in an idealized axisymmetric combustor geometry. A flowfield prediction computer program was developed which solves appropriate finite difference equations including a conventional two equation k-epsilon eddy viscosity turbulence model. The wall functions employed were derived from previous swirling flow measurements, and the stairstep approximation was employed to represent the sloping wall at the inlet to the test chamber. Recirculation region boundaries have been sketched from the entire flow visualization photograph collection. Tufts, smoke, and neutrally buoyant helium filled soap bubbles were employed as flow tracers. A five hole pitot probe was utilized to measure the axial, radial, and swirl time mean velocity components.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-174916 , NAS 1.26:174916
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  • 10
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    Deflected jet experiments in a turbulent combustor flowfield (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Experiments were conducted to characterize the time-mean and turbulent flow field of a deflected turbulent jet in a confining cylindrical crossflow. Jet-to-crossflow velocity ratios of 2, 4, and 6 were investigated, under crossflow inlet swirler vane angles of 0 (swirler removed), 45 and 70 degrees. Smoke, neutrally buoyant helium-filled soap bubbles, and multi-spark flow visualization were employed to highlight interesting features of the deflected jet, as well as the tracjectory and spread pattern of the jet. A six-position single hot-wire technique was used to measure the velocities and turbulent stresses in nonswirling crossflow cases. In these cases, measurements confirmed that the deflected jet is symmetrical about the vertical plan passing through the crossflow axis, and the jet penetration was found to be reduced from that of comparable velocity ratio infinite crossflow cases. In the swirling crossflow cases, the flow visualization techniques enabled gross flow field characterization to be obtained for a range of lateral jet-to-crossflow velocity ratios and a range of inlet swirl strengths in the main flow.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-174863 , NAS 1.26:174863
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