Gas turbine engine including vane structure and seal to control fluid leakage
A gas turbine engine includes a core engine, a fan coupled to be driven by the core engine, a first case structure around the core engine and a second case structure around the fan. The first case structure and the second case structure define a bypass passage there between. A vane structure includes an airfoil extending radially between the first case structure and the second case structure. A seal is configured to control leakage between the bypass passage and a core engine.
1. A gas turbine engine comprising:
a core engine;
a fan coupled to be driven about a central longitudinal engine axis by the core engine;
an inner case structure around the core engine;
an outer case structure around the fan, the inner case structure and the outer case structure defining a bypass passage there between;
a vane structure including an airfoil and a base secured with the airfoil, the base having a radially inward-facing surface, the airfoil extending radially between the inner case structure and the outer case structure, the inner case structure having a forward end that is radially inwards of the base; and
a seal configured to control fluid leakage between the bypass passage and the core engine, the seal abutting the radially inward-facing surface of the base.
2. The gas turbine engine as recited in claim 1 , wherein the seal includes a hollow portion.
3. The gas turbine engine as recited in claim 1 , wherein the seal is flexible.
4. The gas turbine engine as recited in claim 1 , wherein the seal is elastomeric.
5. The gas turbine engine as recited in claim 1 , wherein the seal includes reinforced elastomer.
6. The gas turbine engine as recited in claim 1 , wherein the seal includes a rounded, hollow bulb.
7. The gas turbine engine as recited in claim 1 , wherein the seal includes an attachment section securing the seal to the forward end of the inner case structure.
8. The gas turbine engine as recited in claim 7 , wherein the attachment section includes a pair of spaced apart legs.
9. The gas turbine engine as recited in claim 1 , wherein the seal is within a gas passage between the core engine and the bypass passage, and further comprising a wear member within the gas passage radially inwards of the seal.
10. The gas turbine engine as recited in claim 1 , wherein the seal includes a seal flap bearing against the radially inward-facing surface of the base.
11. The gas turbine engine as recited in claim 1 , wherein the seal includes a fiber reinforcement impregnated with an elastomer.
12. The gas turbine engine as recited in claim 11 , wherein the fiber reinforcement is a fabric.
13. The gas turbine engine as recited in claim 12 , wherein the elastomer is silicone.
14. The gas turbine engine as recited in claim 13 , wherein the seal includes a rounded, hollow bulb.
15. The gas turbine engine as recited in claim 1 , wherein the forward end of the inner case structure slopes toward the central longitudinal engine axis such that the forward end is radially inwards of the radially inward-facing surface of the base.
16. A gas turbine engine comprising:
a vane structure including an airfoil disposed about a central longitudinal engine axis, the vane structure including a radially inward-facing surface;
a panel including a forward section arranged radially inwards of the vane structure, wherein the panel bounds a fan bypass passage; and
a seal arranged radially inwards of the vane structure, between the vane structure and the panel, the seal sealing against the radially inward-facing surface.
17. The gas turbine engine as recited in claim 16 , wherein the seal is flexible.
18. The gas turbine engine as recited in claim 16 , wherein the seal includes a rounded, hollow bulb.
19. The gas turbine engine as recited in claim 16 wherein the seal is within a gas passage between the core engine and the bypass passage, and further comprising a wear member within the gas passage radially inwards of the seal.
20. The gas turbine engine as recited in claim 16 , wherein the seal includes an attachment section securing the seal to the panel, the attachment section including a pair of spaced apart legs.
21. The gas turbine engine as recited in claim 16 , wherein the seal includes a seal flap bearing against the radially inward-facing surface of the vane structure.
22. A gas turbine engine comprising:
a vane structure including an airfoil disposed about a central longitudinal engine axis, the vane structure including a radially inward-facing surface;
a panel including a forward section arranged radially inwards of the vane structure, wherein the panel bonds a fan bypass passage; and
a seal arranged radially inwards of the vane structure, between the vane structure and the panel, the seal sealing against the radially inward-facing surface, wherein the seal includes a hollow portion.