GAS TURBINE ENGINE MULTI-HOLE FILM COOLED COMBUSTOR LINER AND METHOD OF MANUFACTURE

A gas turbine engine combustor is provided, having a single wall sheet metal liner which is generally annular in shape which may be corrugated and a multi-hole film cooling means which includes at least one pattern of a great many small closely spaced sharply downstream angled film cooling holes [80...

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Bibliographische Detailangaben
Hauptverfasser:	WAKEMAN, THOMAS G, MACLIN, HARVEY M, WALKER, ALAN
Format:	Patent
Sprache:	eng
Schlagworte:	BLASTING CLADDING OR PLATING BY SOLDERING OR WELDING COMBUSTION APPARATUS COMBUSTION ENGINES COMBUSTION PROCESSES CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MACHINE TOOLS MECHANICAL ENGINEERING METAL-WORKING NOT OTHERWISE PROVIDED FOR PERFORMING OPERATIONS SOLDERING OR UNSOLDERING TRANSPORTING WEAPONS WELDING WORKING BY LASER BEAM
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Beschreibung
Zusammenfassung:	A gas turbine engine combustor is provided, having a single wall sheet metal liner which is generally annular in shape which may be corrugated and a multi-hole film cooling means which includes at least one pattern of a great many small closely spaced sharply downstream angled film cooling holes [80] disposed essentially along portion of the liner to be cooled. Another embodiment provides a corrugated aircraft engine afterburner sheet metal liner having at least one pattern of great many small closely spaced sharply downstream angled film cooling holes disposed essentially along the entire surface of the liner.