摘要 :
Extensive experimental results for heat transfer characteristics have been obtained for configurations designed to model the impingement cooled midchord region of air cooled gas turbine airfoils. The configurations tested were inl...
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Extensive experimental results for heat transfer characteristics have been obtained for configurations designed to model the impingement cooled midchord region of air cooled gas turbine airfoils. The configurations tested were inline and staggered two-dimensional arrays of circular jets with ten spanwise rows of holes. The cooling air was constrained to exit in the chordwise direction along the channel formed by the jet orifice plate and the heat transfer surface. Tests were run for chordwise jet hole spacing of five, ten, and fifteen hole diameters;spanwise spacing of four, six, and eight diameters;and channel heights of one, two, three, and six diameters. Mean jet Reynolds numbers ranged from 5x10 to 5x10. The thermal boundary condition at the heat transfer test surface was isothermal. Tests were run for sets of geometrically similar configurations of different sizes. Mean and chordwise resolved Nusselt numbers were determined utilizing a specially constructed test surface which was segmented in the chordwise direction. Based on these results, both mean and chordwise resolved heat transfer characteristics are presented in graphical form and discussed in detail as a function of mean jet Reynolds number and the geometric parameters, including hole pattern effects. Results for the maximum chordwise resolution of one-third the chordwise hole spacing reflect the periodic variations of the chordwise heat transfer coefficient profiles. Results resolved to one or two chordwise hole spacing’s show more clearly the nature of the profiles smoothed across the periodic variations. A complete tabulation of mean and resolved Nusselt number values for all test conditions covered is included as an appendix.
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摘要 :
This viewgraph presentation gives an overview on the development of a low-cost, subscale test system to evaluate particle impingement erosion in nozzle ablative materials. Details are given on the need for a new test bed, solid fu...
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This viewgraph presentation gives an overview on the development of a low-cost, subscale test system to evaluate particle impingement erosion in nozzle ablative materials. Details are given on the need for a new test bed, solid fuel torch components, solid fuel torch test, additional uses for the solid fuel torch, the development of a supersonic blast tube (SSBT), and particle impingement material discrimination.
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摘要 :
Insect debris is removed from or prevented from adhering to insect impingement areas of an aircraft, particularly on an inlet cowl of an engine, by heating the area to 180.degree.-500.degree. C. An apparatus comprising a means to ...
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Insect debris is removed from or prevented from adhering to insect impingement areas of an aircraft, particularly on an inlet cowl of an engine, by heating the area to 180.degree.-500.degree. C. An apparatus comprising a means to bring hot air from the aircraft engine to a plenum contiguous to the insect impingement area provides for the heating of the insect impingement areas to the required temperatures. The plenum can include at least one tube with a plurality of holes contained in a cavity within the inlet cowl. It can also include an envelope with a plurality of holes on its surface contained in a cavity within the inlet cowl.
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