Turbine shroud segment with integrated seal
AssigneePratt & Whitney Canada Corp.
InventorsEric Durocher, Guy Lefebvre
Life of this patent
Estimating the term…
Abstract
A feather seal is positioned in a mold and a shroud body is metal injection molded about a proximal end of the feather seal to provide a shroud segment with an integrated feather seal. A seal groove is provided in an opposite lateral side of the shroud body to receive the feather seal of a circumferentially adjacent shroud segment.
Claims20
A turbine shroud segment for a turbine shroud of a gas turbine engine, the segment comprising a metal injection molded (MIM) shroud body, the MIM shroud body 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 first and second lateral sides, said MIM shroud body including a platform having a hot gas path side surface and a back side surface, and forward and aft arms extending from the back side surface of the platform, said forward and aft arms being axially spaced-apart from each other, a seal groove defined in the first lateral side of the MIM shroud body;
- and a feather seal projecting integrally from the second lateral side of the MIM shroud body for engagement in the seal groove of a similar circumferentially adjacent turbine shroud segment, the feather seal being made from a different material than said MIM shroud body and having a proximal end imbedded in said second lateral side of said MIM shroud body.
A method of manufacturing a turbine shroud segment for a gas turbine engine, the method comprising:
- providing a feather seal insert;
- holding the feather seal insert in position in a metal injection mold;
- and metal injection molding (MIM) a shroud segment body about a proximal end of the feather seal insert to form a green turbine shroud segment body with the feather seal insert projecting integrally from a first circumferential end thereof, and subjecting the green turbine shroud segment body with the integrated feather seal insert to debinding and sintering operations.
A turbine shroud assembly of a gas turbine engine, comprising a plurality of shroud segments disposed circumferentially one adjacent to another, each of the shroud segment having a metal injection molded body (MIM) 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 assembly, and being circumferentially defined between opposite first and second lateral sides, said MIM shroud body including a platform having a hot gas path side surface and a back side surface, and forward and aft arms extending from the back side surface of the platform, said forward and aft arms being axially spaced-apart from each other, each of the shroud segments further comprising an integral feather seal projecting from the second lateral side for engagement in a corresponding seal groove defined in the first lateral side of a circumferentially adjacent shroud segment, the integral feather seal being provided in the form an insert having a proximal end imbedded in the MIM shroud body of the shroud segment.
Dependencies are inferred from the claim text.