Method of testing flow in an airfoil by applying plugs to internal inlet orifices
A method of testing flow in an airfoil includes isolating a first cooling passage network of the airfoil by applying plugs to internal inlet orifices of the other ones of the cooling passage networks in the airfoil. The plugs block flow from an internal core cavity of the airfoil into the other ones of the cooling passage networks. The inlet orifices of the first cooling passage network are left open. A test flow is then applied to the internal core cavity and flows through the inlet orifices of the first cooling passage network.
1. A method of testing flow in an airfoil, the method comprising:
providing an airfoil that has an airfoil wall that defines leading and trailing ends and first and second sides that join the leading and trailing ends, the airfoil wall circumscribes an internal core cavity, and a plurality of cooling passage networks embedded in the airfoil wall between inner and outer portions of the airfoil wall, each said cooling passage network has one or more inlet orifices through the inner portion of the airfoil wall that opens to the internal core cavity, a sub-passage region that includes an array of pedestals, and at least one outlet orifice through the outer portion of the airfoil wall;
isolating a first one of the cooling passage networks for flow testing by applying plugs to the inlet orifices of the other ones of the cooling passage networks, the plugs blocking flow from the internal core cavity into the other ones of the cooling passage networks, wherein the one or more inlet orifices of the first one of the cooling passage networks are left open; and
applying a test flow to the internal core cavity, the test flow flowing through the one or more inlet orifices of the first one of the cooling passage networks.
2. The method as recited in claim 1 , wherein the plugs are adhesive tapes.
3. The method as recited in claim 2 , further comprising removing the adhesive tapes using a solvent to dissolve the adhesive tapes.
4. The method as recited in claim 1 , wherein the plugs are elastomer boots.
5. The method as recited in claim 4 , wherein the elastomer boots are silicone.
6. The method as recited in claim 1 , wherein the plugs are wax.
7. The method as recited in claim 6 , further comprising removing the wax using a solvent to dissolve the wax.
8. The method as recited in claim 6 , further comprising removing the wax by thermal volatilization of the wax.
9. The method as recited in claim 1 , wherein the airfoil includes a platform from which the airfoil wall extends, the platform including an opening that opens into the internal core cavity, and the applying of the plugs includes inserting the plugs through the opening and onto the inlet orifices of the other ones of the cooling passage networks.
10. The method as recited in claim 1 , further comprising, after the applying of the test flow, isolating a second one of the cooling passage networks for flow testing by removing a portion of the plugs, followed by applying plugs to the one or more inlet orifices of the first one of the cooling passage networks, and then re-applying the test flow to the internal core cavity, the test flow flowing through the one or more inlet orifices of the second one of the cooling passage networks.
11. The method as recited in claim 1 , wherein the plugs are selected from the group consisting of elastomer boots, wax, adhesive tape, and combinations thereof.
12. A method of testing flow in an airfoil, the method comprising:
providing an airfoil that has a platform and an airfoil wall that extends from the platform, the airfoil wall defines leading and trailing ends and first and second sides that join the leading and trailing ends, the airfoil wall circumscribes an internal core cavity, and a plurality of cooling passage networks are embedded in the airfoil wall between inner and outer portions of the airfoil wall, each said cooling passage network has one or more inlet orifices through the inner portion of the airfoil wall that opens to the internal core cavity, a sub-passage region that includes an array of pedestals, and at least one outlet orifice through the outer portion of the airfoil wall, and the platform includes an opening that opens into the internal core cavity;
isolating a first one of the cooling passage networks for flow testing by inserting plugs through the opening into the internal core cavity and applying the plugs to the inlet orifices of the other ones of the cooling passage networks, the plugs blocking flow from the internal core cavity into the other ones of the cooling passage networks, wherein the one or more inlet orifices of the first one of the cooling passage networks are left open; and
applying a test flow to the internal core cavity, the test flow flowing through the one or more inlet orifices of the first one of the cooling passage networks.
13. The method as recited in claim 12 , wherein the plugs are adhesive tapes.
14. The method as recited in claim 13 , further comprising removing the adhesive tapes using a solvent to dissolve the adhesive tapes.
15. The method as recited in claim 12 , wherein the plugs are elastomer boots.
16. The method as recited in claim 15 , wherein the elastomer boots are silicone.
17. The method as recited in claim 12 , wherein the plugs are wax.
18. The method as recited in claim 17 , further comprising removing the wax using a solvent to dissolve the wax.
19. The method as recited in claim 17 , further comprising removing the wax by thermal volatilization of the wax.
20. The method as recited in claim 12 , further comprising, after the applying of the test flow, isolating a second one of the cooling passage networks for flow testing by removing a portion of the plugs, followed by applying plugs to the one or more inlet orifices of the first one of the cooling passage networks, and then re-applying the test flow to the internal core cavity, the test flow flowing through the one or more inlet orifices of the second one of the cooling passage networks.