Turbine shroud segment transpiration cooling with individual...

Details Turbine shroud segment transpiration cooling with individual... Turbine shroud segment transpiration cooling with individual...

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 25/14 (2006.01) F01D 25/12 (2006.01) F01D 25/24 (2006.01)

Patent

CA 2612616

A shroud segment (42) of a turbine shroud (32) of a gas turbine engine comprises a platform (44) with front and rear legs (46, 48). The platform (44) defines a plurality of axially extending transpiration holes / passages (66) with individual inlets (68) on an outer surface of the platform (44) for transpiration cooling of the platform (44) of the turbine shroud segment (42). The individual inlets are in the form of cast cavities with diameters larger that those of the transpiration holes. Providing such an arrangement of individually cast inlets removes the need to provide a single common inlet in the form of a groove which would otherwise impair the strength and durability of the shroud segment.

L'invention concerne un segment (42) d'une enveloppe de turbine (32) d'un moteur de turbine à gaz, ce segment (42) comprenant une plateforme (44) présentant des jambes avant et arrière (46, 48). Cette plateforme (44) définit une pluralité de trous / passages de transpiration (66) s'étendant axialement et présentant des entrées individuelles (68) sur une surface extérieure de la plateforme (44) pour refroidir par transpiration la plateforme (44) dudit segment (42) d'enveloppe de turbine. Les entrées individuelles se présentent sous la forme de cavités moulées dont le diamètre est supérieur à celui des trous de transpiration. Cet ensemble d'entrées moulées individuelles élimine la nécessité de recourir à une entrée commune unique sous forme de rainure qui affecterait la résistance et la durabilité du segment d'enveloppe.

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