Shroud cooling assembly for a gas trubine

F - Mech Eng,Light,Heat,Weapons – 01 – D

Patent

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Details

F01D 25/12 (2006.01) F01D 9/04 (2006.01) F01D 11/14 (2006.01) F01D 25/14 (2006.01) F01D 25/24 (2006.01)

Patent

CA 2504902

An improved assembly (110) consisting of internal casing (112) and support device (114) for nozzles in a gas turbine stage, these nozzles being grouped together in sectors and each of these sectors being connected externally to an external casing of the gas turbine by means of the support device (114), this support device (114) being kept in position by the internal casing (112), there also being formed first cooling holes (122) on the internal casing (112) and second cooling holes (124) on the support device (114); the first cooling holes (122) of the internal casing (112) have an extension substantially parallel to the axis of the gas turbine.

L'invention concerne un ensemble (110) amélioré constitué d'une carcasse interne (112) et d'un dispositif de support (114) d'injecteurs dans un étage de turbine à gaz, lesdits injecteurs étant groupés ensemble dans des secteurs et chacun desdits secteurs étant relié de manière externe à une carcasse externe de la turbine à gaz à l'aide du dispositif de support (114), ledit dispositif de support (114) étant maintenu en position par la carcasse interne (112), des premiers trous de refroidissement étant également formés (122) sur la carcasse interne (112) et des seconds trous de refroidissement (124) étant formés sur le dispositif de support (114) ; les premiers trous de refroidissement (122) de la carcasse interne (112) présentent un prolongement sensiblement parallèle à l'axe de la turbine à gaz.

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