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  • 1
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    Jet array impingement flow distributions and heat transfer characteristics: Effects of initial crossflow and nonuniform array geometry (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Flow distributions and heat transfer characteristics for two-dimensional arrays of circular air jets impinging on a surface parallel to the jet orifice plate were determined. The configurations considered were intended to model those of interest in current and contemplated gas turbine airfoil midchord cooling applications. The geometry of the airfoil applications considered dictates that all of the jet flow, after impingement, exit in the chordwise (i.e., streamwise) direction toward the trailing edge. Experimental results for the effect of an initial crossflow on both flow distributions and heat transfer characteristics for a number of the prior uniform array geometries. The effects of nonuniform array geometries on flow distributions and heat transfer characteristics for noninitial crossflow configurations are discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Turbine Eng. Hot Sect. Technol. (HOST); p 161-173
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Local heat transfer measurement with liquid crystals on rotating surfaces including non-axisymmetric cases (1993)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: An overview and summary of test methods and results are given for the problem of measuring local heat transfer on rotating surfaces that model gas turbine engine disks. Disk cavity situations generically similar to those encountered in the high pressure stage disk cooling are considered, with cooling air supplied both at or near the wheel centerline as well as through single or multiple jets impinging outboard on the wheel near the blade attachment region. In some situations provision has been made for ingestion into the disk-cavity from the gas path region radially outboard of the disk. Local heat transfer rates in all cases are determined from the color display from a thin coating of encapsulated liquid crystals sprayed onto the disk, in conjunction with use of a video camera and computer vision system. For cases with axisymmetric disk surfaces, the coated surfaces are illuminated and viewed continuously, and detailed radial distributions of local Nusselt number are obtained. For non-axisymmetric disk surfaces, such as encountered in the vicinity of bolt heads, the disk is illuminated with stroboscopic light, and a method has been developed and used to synchronize the computer frame grabber with the illumination.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD, Heat Transfer and Cooling in Gas Turbines; 11 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Streamwise flow and heat transfer distributions for jet array impingement with crossflow (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Two-dimensional arrays of circular jets of air impinging on a heat transfer surface parallel to the jet orifice plate are considered. The air, after impingement, is constrained to exit in a single direction along the channel formed by the surface and the jet plate. The downstream jets are subjected to a crossflow originating from the upstream jets. Experimental and theoretical results obtained for streamwise distributions of jet and crossflow velocities are presented and compared. Measured Nusselt numbers resolved to one streamwise hole spacing are correlated with individual spanwise row jet Reynolds numbers and crossflow-to-jet velocity ratios. Correlations are presented for both inline and staggered hole patterns including effects of geometric parameters: streamwise hole spacing, spanwise hole spacing, and channel height, normalized by hole diameter. The physical mechanisms influencing heat transfer coefficients as a function of flow distribution and geometric parameters are also discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: ASME PAPER 81-GT-77 , Gas Turbine Conference and Products Show; Mar 09, 1981 - Mar 12, 1981; Houston, TX
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Fundamental heat transfer research for gas turbine engines (1980)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Thirty-seven experts from industry and the universities joined 24 NASA Lewis staff members in an exchange of ideas on trends in aeropropulsion research and technology, basic analyses, computational analyses, basic experiments, near-engine environment experiments, fundamental fluid mechanics and heat transfer, and hot technology as related to gas turbine engines. The workshop proceedings described include pre-workshop input from participants, presentations of current activity by the Lewis staff, reports of the four working groups, and a workshop summary.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CP-2178 , E-666 , Oct 08, 1980 - Oct 09, 1980; Cleveland, OH; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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