Turbine shroud segment with integrated impingement plate
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 an insert having a cooling air cavity covered by an impingement plate. The insert 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 insert.
Claims17
A method of manufacturing a shroud segment for a gas turbine engine, the method comprising:
- providing an insert defining a cooling air cavity covered by an impingement plate having a plurality of holes defined therethrough;
- holding the insert in position in an injection mold;
- and metal injection molding (MIM) a shroud segment body about the insert to form a composite component, including injecting a metal powder mixture into the injection mold to partially imbed the insert into the shroud segment body and subjecting the composite component to debinding and sintering operations.
A method of creating a cooling air cavity in a shroud segment of a gas turbine engine, the method comprising:
- metal injection molding (MIM) a shroud segment body about a hollow insert having a cavity covered by an impingement plate, the impingement plate being provided at a radially outwardly facing surface of the MIM shroud segment body and having a plurality of holes defined therethrough for admitting air into the cavity of the hollow insert.
A shroud segment of a gas turbine engine comprising a metal injection molded (MIM) shroud body, an insert at least partly imbedded on a radially outer side of the MIM shroud body, the insert comprising first and second members defining therebetween a cooling air cavity, said first member having a plurality of impingement holes defined therethrough for directing cooling air into said cooling air cavity.
Dependencies are inferred from the claim text.