Two-piece baffle
An airfoil vane includes an airfoil section which includes an outer wall that defines an internal cavity. A baffle is situated in the internal cavity. The baffle includes a leading edge portion and a trailing edge portion which is bonded to the leading edge portion at a joint. The leading edge portion and the trailing edge portion define an internal cavity therewithin. Both the leading edge portion and the trailing edge portion include a plurality of cooling holes which are configured to provide cooling air to the airfoil outer wall. The trailing edge portion is formed of sheet metal and the leading edge portion is formed of non-sheet-metal. A method of making a baffle for a vane arc segment and a method of assembling a ceramic matrix composite airfoil vane are also disclosed.
1. A method of making a baffle for a vane arc segment, comprising:
forming a trailing edge portion of the baffle from sheet metal:
forming a leading edge portion of the baffle by additive manufacturing: and
bonding the leading edge portion to the trailing edge portion at a joint such that the trailing edge portion and the leading edge portion together define a common internal cavity therewithin, wherein forming the leading edge portion includes forming first and second sides of the leading edge portion and connecting the first and second sides, and wherein the first and second sides are formed separately from one another prior to the connecting.
2. The method of claim 1 , further comprising measuring an airfoil vane, wherein the airfoil vane is configured to receive the baffle, determining the dimensions of the airfoil vane, and forming the leading edge portion based on the dimensions of the airfoil vane.
3. The method of claim 1 , wherein forming the leading edge portion includes making the leading edge portion as a single piece component.
4. The method of claim 1 , wherein forming the leading edge portion includes making cooling holes in the leading edge portion.
5. The method of claim 4 , wherein the cooling holes are made during the additive manufacturing.
6. The method of claim 1 , wherein forming the leading edge portion includes forming standoffs, the standoffs extending from a wall of the leading edge portion.
7. The method of claim 6 , wherein the standoffs are formed during the additive manufacturing.
8. The method of claim 1 , wherein the bonding includes bonding a forward edge of the trailing edge portion to a step formed in the leading edge portion.
9. The method of claim 8 , wherein the step is formed in the leading edge portion during the additive manufacturing.
10. The method of claim 8 , wherein the step is disposed inside the trailing edge portion to form a smooth surface at the joint when the leading and trailing edge portions are bonded.
11. The method of claim 1 , wherein the connecting is by welding.
12. The method of claim 1 , wherein forming the trailing edge portion includes making cooling holes in the trailing edge portion prior to the bonding step.
13. A method of assembling a ceramic matrix composite airfoil vane, comprising:
inserting a baffle into a central cavity of the ceramic matrix composite airfoil vane, the central cavity defined by an airfoil outer wall, the baffle including a leading edge portion and a separate trailing edge portion connected to the leading edge portion at a joint, wherein the leading edge portion and the trailing edge portion together define a common internal cavity therewithin, wherein both the leading edge portion and the trailing edge portion include a plurality of cooling holes configured to provide cooling air to the airfoil outer wall, wherein the trailing edge portion is formed from sheet metal, wherein making the leading edge portion includes forming first and second sides of the leading edge portion and connecting the first and second sides, and wherein the first and second sides are formed separately from one another prior to the connecting.
14. The method of claim 13 , further comprising making the leading edge portion by additive manufacturing.
15. The method of claim 13 , wherein the leading edge portion includes a neck forward of the joint.
16. The method of claim 13 , wherein the joint includes a step formed on the leading edge portion, the step configured to receive a forward end of the trailing edge portion.
17. The method of claim 13 , wherein the joint includes a neck forward of the joint, and wherein the neck includes step, the step configured to receive a forward end of the trailing edge portion.