Turbine shroud segment
AssigneePratt & Whitney Canada Corp.
InventorsEric Durocher, Guy Lefebvre
Life of this patent
Estimating the term…
Abstract
A turbine shroud segment is metal injection molded (MIM) about a core to provide a composite structure. In one aspect, the core is held in position in an injection mold and then the MIM material is injected in the mold to form the body of the shroud segment about the core. Any suitable combination of materials can be used for the core and the MIM shroud body, each material selected for its own characteristics. The core may be imbedded in the shroud platform to provide a multilayered reinforced platform, which may offer resistance against crack propagation.
Claims16
A turbine shroud segment for a turbine shroud of a gas turbine engine, the segment comprising a metal injection molded (MIM) shroud body, said MIM shroud body including a platform having a hot gas path side surface and a back side surface, the platform being axially defined from a leading edge to a trailing edge in a direction from an upstream position to a downstream position of a hot gas flow passing through the turbine shroud, and being circumferentially defined between opposite lateral sides of the platform, and forward and aft hooks extending from the back side surface of the platform, said forward and aft hooks being axially spaced-apart from each other;
- and a core imbedded in the MIM shroud body, said core having a platform reinforcing section extending longitudinally along a circumferential direction of the platform between said hot gas path and back side surfaces.
A method of manufacturing a turbine shroud segment for a gas turbine engine, the method comprising:
- providing a metallic core;
- holding the metallic core in position in a metal injection mold;
- and metal injection molding (MIM) a shroud segment body about the metallic core to form a composite metallic component, including injecting a metal powder mixture into the injection mold to imbed the metallic core into the shroud segment body and subjecting the composite component to debinding and sintering operations.
A shroud segment for a turbine shroud of a gas turbine engine, comprising a reinforced platform having a hot gas path side and a back side, the reinforced platform being axially defined from a leading edge to a trailing edge in a direction from an upstream position to a downstream position of a hot gas flow passing through a turbine section of the gas turbine engine, and being circumferentially defined between opposite lateral sides of the reinforced platform, the reinforced platform having a multilayer construction including an intermediate reinforcing layer comprising a sheet metal insert imbedded within the platform between said hot gas path side and back side.
Dependencies are inferred from the claim text.