Method and system for a ceramic matrix composite shroud hanger assembly
AssigneeGeneral Electric Company
InventorJason David Shapiro
Life of this patent
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Abstract
A shroud and hanger assembly for a gas turbine engine and a method of transferring load from a ceramic matrix composite (CMC) shroud to a CMC shroud hanger assembly are provided. The shroud and hanger assembly includes a shroud hanger assembly formed of a first material having a first coefficient of thermal expansion, the shroud hanger assembly having a forward hanger portion and a separate aftward hanger portion and a shroud formed of a second material having a second coefficient of thermal expansion, the forward and aftward hanger portions configured to couple together to clamp across a forward radially extending wall of the shroud.
Claims18
A shroud and shroud hanger assembly for a gas turbine engine, said assembly comprising:
- a shroud hanger assembly formed of a first material having a first coefficient of thermal expansion, said shroud hanger assembly having a forward hanger portion and a separate aftward hanger portion, said shroud hanger assembly includes a diagonal web member that extends from a radially inner end of a forward radially extending leg to a radially outer end of an aftward radially extending leg of said aftward hanger portion;
- and
- a shroud formed of a second material having a second coefficient of thermal expansion, said forward and aftward hanger portions configured to couple together to clamp across a forward radially extending wall of said shroud.
A method of transferring load from a ceramic matrix composite (CMC) shroud to a CMC shroud hanger assembly, said method comprising:
- clamping a forward hanger portion and a separate aftward hanger portion of a shroud hanger assembly together, a forward radially extending wall of the shroud positioned between the forward hanger portion and the aftward hanger portion, the forward radially extending wall receiving a clamping force on a forward side from the forward hanger portion and on an aftward side from the aftward hanger portion providing a load transfer joint between the shroud and the shroud hanger assembly;
- coupling the shroud hanger assembly to a casing of a turbine;
- and
- transferring load from a nozzle through a diagonal web member of the shroud hanger assembly to the casing.
A gas turbine engine comprising:
- a shroud hanger assembly formed of a first material having a first coefficient of thermal expansion, said shroud hanger assembly having a forward hanger portion and a separate aftward hanger portion, said shroud hanger assembly includes a diagonal web member that extends from a radially inner end of a forward radially extending leg to a radially outer end of an aftward radially extending leg of said aftward hanger portion;
- and
- a shroud formed of a second material having a second coefficient of thermal expansion, said forward and aftward hanger portions configured to couple together to clamp across a forward radially extending wall of said shroud.
Dependencies are inferred from the claim text.