Feather seal assembly
A seal assembly for a gas turbine engine according to an example of the present disclosure includes a seal segment. The seal segment includes a blade-sealing portion that provides an elongated slot, a flange that extends from the blade-sealing portion, and a hook that extends from the blade-sealing portion and is spaced from the flange. The hook has a surface that at least partially provides a cavity. A feather seal has an elongated portion and first and second legs which extend from the elongated portion. The first leg abuts the flange, the second leg is disposed in the cavity, and the elongated portion is disposed in the elongated slot.
1. A seal assembly for a gas turbine engine, comprising:
a seal segment including
a blade-sealing portion providing an elongated slot,
a flange extending from the blade-sealing portion, and
a hook extending from the blade-sealing portion and spaced from the flange, the hook having a surface that at least partially provides a cavity;
a feather seal having an elongated portion and first and second legs extending from the elongated portion, wherein the first leg abuts the flange, the second leg is disposed in the cavity, and the elongated portion is disposed in the elongated slot; and
a middle feather seal, wherein the hook provides a hook slot extending from the elongated slot, and the middle feather seal is received in the hook slot, and an end of the middle feather seal abuts the elongated portion.
2. The seal assembly as recited in claim 1 , wherein the feather seal has a goalpost shaped cross section.
3. The seal assembly as recited in claim 1 , further comprising a gasket received against the first leg.
4. The seal assembly as recited in claim 1 , wherein the seal segment includes a second hook providing a second hook slot.
5. The seal assembly as recited in claim 4 , comprising an L-shaped feather seal received in the second hook slot and the elongated slot.
6. The seal assembly as recited in claim 5 , further comprising a gasket received against the first leg.
7. A seal assembly for a gas turbine engine, comprising:
a seal segment including
a blade-sealing portion providing an elongated slot,
a flange extending from the blade-sealing portion, and
a hook extending from the blade-sealing portion and spaced from the flange, the hook having a surface that at least partially provides a cavity;
a second hook spaced from the first hook and at least partially providing the cavity, wherein the first hook provides a first hook slot extending from the elongated slot, and the second hook provides a second hook slot extending from the elongated slot;
a feather seal having an elongated portion and first and second legs extending from the elongated portion, wherein the first leg abuts the flange, the second leg is disposed in the cavity, and the elongated portion is disposed in the elongated slot;
a middle feather seal received in the first hook slot; and
an L-shaped feather seal received in the second hook slot and the elongated slot.
8. The seal assembly as recited in claim 7 , wherein the distance between the first and second legs is different from the distance between the first hook slot and the second hook slot.
9. The seal assembly as recited in claim 7 , wherein the distance between the first and second legs is less than the distance between the first hook slot and the second hook slot.
10. The seal assembly as recited in claim 7 , wherein an end of the middle feather seal abuts the elongated portion.
11. A gas turbine engine, comprising:
a turbine section positioned about an engine central longitudinal axis; and
a seal assembly of the turbine section including
a seal segment including
a blade-sealing portion providing an axially elongated slot with respect to the engine central longitudinal axis,
a flange extending radially outward from the blade-sealing portion, and
a first hook extending radially outward from the blade-sealing portion and axially aft of the flange, the hook having a surface that at least partially provides a cavity,
a second hook axially aft of the first hook and at least partially providing the cavity, wherein the first hook provides a first hook slot extending radially outward from the elongated slot, and the second hook provides a second hook slot extending radially outward from the elongated slot, and
a feather seal having an elongated portion and first and second legs extending from the elongated portion, wherein the first leg abuts the flange, the second leg is disposed in the cavity, and the elongated portion is disposed in the elongated slot,
a middle feather seal received in the first hook slot, and
an L-shaped feather seal received in the second hook slot and the elongated slot.
12. The gas turbine engine as recited in claim 11 , wherein the axial distance between the first and second legs is different from the axial distance between the first hook slot and the second hook slot.
13. The gas turbine engine as recited in claim 11 , wherein the axial distance between the first and second legs is less than the axial distance between the first hook slot and the second hook slot.
14. The gas turbine engine as recited in claim 11 , further comprising:
a rotor section, wherein the seal assembly is radially outward of and axially aligned with the rotor section; and
a stator section axially spaced from the rotor section.
15. The gas turbine engine as recited in claim 14 , comprising
a gasket received against a forward surface of the flange and a forward surface of the first leg.
16. The gas turbine engine as recited in claim 15 , wherein the stator section includes a stator rail, and the gasket is received between the stator rail and the flange.
17. The gas turbine engine as recited in claim 11 , wherein an end of the middle feather seal abuts the elongated portion.
18. The gas turbine engine as recited in claim 17 , further comprising a gasket received against the first leg.
19. A method of assembling a seal assembly for a gas turbine engine, comprising:
providing a plurality of circumferentially spaced seal segments radially outward of a rotor with respect to an engine centerline axis, each seal segment including
a blade-sealing portion providing an elongated slot,
a flange extending from the blade-sealing portion, and
a first hook extending from the blade-sealing portion and spaced from the flange, the hook having a surface that at least partially provides a cavity, and the hook including a hook slot;
inserting a feather seal assembly into circumferentially adjacent ones of the plurality of seal segments, the feather seal assembly including a feather seal having an elongated portion and first and second legs extending from the elongated portion, such that the first leg abuts the flange of each of the adjacent ones of the plurality of seal segments, the second leg is disposed in the cavity of each of the adjacent ones of the plurality of seal segments, and the elongated portion is disposed in the elongated slot of each of the adjacent ones of the plurality of seal segments; and
inserting a middle feather seal into the hook slot, such that an end of the middle feather seal abuts the elongated portion.
20. The method as recited in claim 19 , wherein each seal segment includes a second hook including a second hook slot, the method comprising inserting an L-shaped feather seal into the second hook slot and the elongated slot.