Method of assembly of bi-cast turbine vane
AssigneesROLLS-ROYCE plc, Rolls-Royce North American Technologies Inc.
InventorsTed J. Freeman, Robert F. Proctor, Sean E. Landwehr, Adam L. Chamberlain
Life of this patent
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Abstract
One aspect of the present disclosure includes a turbine vane assembly comprising a vane made from ceramic matrix composite material having an outer wall extending between a leading edge and a trailing edge and between a first end and an opposing second end; an endwall made at least partially from a ceramic matrix composite material configured to engage the first end of the vane; and a retaining region including corresponding bi-cast grooves formed adjacent the first end of the vane and a receiving aperture formed in the endwall; wherein a bond is formed in the retaining region to join the vane and endwall together.
Claims19
-20. (canceled)
A method of assembling a gas turbine engine vane including an airfoil having an outer surface extending between a leading edge and a trailing edge and between a first end and a second end;
- a through slot extending between the first and second ends of the airfoil;
- and a spar slidingly engaged within the slot of the airfoil, the spar including a pair of extensions with at least one bi-cast groove formed on opposing ends thereof, wherein the extensions of the spar are configured to engage with corresponding apertures formed in a pair of opposing endwalls, the method comprising:
- inserting at least one of the extensions into one of the apertures of the end walls,
- injecting a pre-cursor into the at least one bi-cast groove,
- heating the pre-cursor to form a fixed connection.
A method of assembling a gas turbine engine including at least one vane, the at least one vane including an airfoil having an outer surface extending between a leading edge and a trailing edge and between a first end and a second end;
- a through slot extending between the first and second ends of the airfoil;
- and a spar slidingly engaged within the slot of the airfoil, the spar including a pair of extensions with at least one bi-cast groove formed on opposing ends thereof, wherein the extensions of the spar are configured to engage with corresponding apertures formed in a pair of opposing endwalls, the method comprising:
- inserting at least one of the extensions into one of the apertures of the end walls,
- injecting a pre-cursor into the at least one bi-cast groove,
- heating the pre-cursor to form a fixed connection.
Dependencies are inferred from the claim text.