GAS TURBINE COMBUSTOR AND COOLING METHOD OF GAS TURBINE COMBUSTOR

PROBLEM TO BE SOLVED: To cool a transition pipe with high reliability and effectiveness. SOLUTION: A gas turbine combustor is provided with an opening for introducing air into a clearance between the transition pipe and a transition pipe flow sleeve at a turbine blade side and an air introducing por...

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Bibliographische Detailangaben
Hauptverfasser:	ISHIBASHI YOJI, SAITO TAKEO
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	PROBLEM TO BE SOLVED: To cool a transition pipe with high reliability and effectiveness. SOLUTION: A gas turbine combustor is provided with an opening for introducing air into a clearance between the transition pipe and a transition pipe flow sleeve at a turbine blade side and an air introducing port for convection cooling installed at the turbine blade side of the transition pipe sleeve. In a cooling method of the gas turbine combustion, convection cooling is made by introducing air into the opening and convection cooling is made by introducing air into the port for convection cooling for air, etc. As a result, the transition pipe is effectively cooled with low-pressure loss, and the deformation or the like of a member is controlled so as to improve reliability. COPYRIGHT: (C)2004,JPO