Simultaneous film and convection cooling of a plate inserted in the exhaust stream of a gas turbine combustor

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035 ⊔ ⊔ ‡asdr-uiuc6405522
035 ⊔ ⊔ ‡a(OCoLC)680502457
040 ⊔ ⊔ ‡aUIU ‡cUIU
049 ⊔ ⊔ ‡aUIUU
100 1 ⊔ ‡aMarek, Cecil J.
245 1 0 ‡aSimultaneous film and convection cooling of a plate inserted in the exhaust stream of a gas turbine combustor ‡cby Cecil J. Marek and Albert J. Juhasz.
260 ⊔ ⊔ ‡aWashington, D.C. : ‡bNational Aeronautics and Space Administration ; ‡a[Springfield, Va. : ‡bFor sale by the National Technical Information Service], ‡c1973.
300 ⊔ ⊔ ‡aiii, 34 p. : ‡bill. ; ‡c27 cm.
490 0 ⊔ ‡aNASA technical note ; ‡vNASA TN D-7156
500 ⊔ ⊔ ‡aPrepared at Lewis Research Center.
500 ⊔ ⊔ ‡aCover title.
504 ⊔ ⊔ ‡aBibliography: p. 34.
520 ⊔ ⊔ ‡aData were obtained on a parallel-flow film- and convection-cooled test section placed in the exhaust stream of a rectangular-sector combustor. The combustor was operated at atmospheric pressure and at exhaust temperatures of 589 and 1033 K (600 and 1400 F). The cooling air was at ambient pressure and temperature. Test results indicate that it is better to use combined film and convection cooling rather than either film or convection cooling alone for a fixed total coolant flow. An optimum ratio of film to convection cooling flow rates was determined for the particular geometry tested. The experimental results compared well with calculated results.
538 ⊔ ⊔ ‡aMode of access: Internet.
650 ⊔ 0 ‡aCombustion chambers ‡xMaterials ‡xCooling.
650 ⊔ 0 ‡aGas-turbines ‡xCombustion.
700 1 ⊔ ‡aJuhasz, Albert J.
710 1 ⊔ ‡aUnited States. ‡bNational Aeronautics and Space Administration.
710 2 ⊔ ‡aLewis Research Center.
CID ⊔ ⊔ ‡a011449250
DAT 0 ⊔ ‡a20101111105322.0 ‡b20141009010000.0
DAT 1 ⊔ ‡a20141112165512.0 ‡b2024-01-26T18:55:04Z
CAT ⊔ ⊔ ‡aSDR-UIUC ‡dUNKNOWN ‡lloader.pl-003-020
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974 ⊔ ⊔ ‡bUIU ‡cUIUC ‡d20240126 ‡sgoogle ‡uuiug.30112106884841 ‡y1973 ‡rpd ‡qbib ‡tUS fed doc--NTIS: pubdate < 2018