Feather seal assembly
AssigneeUnited Technologies Corporation
InventorWilliam M. Barker
Life of this patent
Estimating the term…
Abstract
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.
Claims20
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;
- 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 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 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, 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 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
- 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.
Dependencies are inferred from the claim text.