GAS TURBINE ENGINE COOLING STRUCTURE AND METHOD FOR MANUFACTURING SAME

In a structure for cooling a constituent member of a gas turbine engine (GT) using a working gas (A) of the gas turbine engine as a cooling medium (CL), on a wall surface (13a) of a passage wall (13) formed from a part of the constituent member and facing a cooling medium passage through which the c...

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Bibliographische Detailangaben
Hauptverfasser:	ISHIDA, Katsuhiko, MURATA, Takayuki, YAMASAKI, Yoshihiro, TANIMURA, Kazuhiko, KINUGAWA, Masayoshi, TSURU, Tomoko, FUKUMOTO, Kenichiro
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING CLADDING OR PLATING BY SOLDERING OR WELDING COMBUSTION APPARATUS COMBUSTION ENGINES COMBUSTION PROCESSES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINE TOOLS MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING METAL-WORKING NOT OTHERWISE PROVIDED FOR NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PERFORMING OPERATIONS SOLDERING OR UNSOLDERING STEAM ENGINES TRANSPORTING WEAPONS WELDING WORKING BY LASER BEAM
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Beschreibung
Zusammenfassung:	In a structure for cooling a constituent member of a gas turbine engine (GT) using a working gas (A) of the gas turbine engine as a cooling medium (CL), on a wall surface (13a) of a passage wall (13) formed from a part of the constituent member and facing a cooling medium passage through which the cooling medium (CL) flows, a recess (21) formed on the wall surface of the passage wall and a projection (23) formed on at least a part of a peripheral edge of the recess are provided.