IP Library › Granted Patent US 12692795
Granted Patent B2
US 12692795 · App. 17/977,573 · Granted Jul 28, 2026

Gas turbine engine turbine section with axial seal

Inventors: Paul M. Lutjen (Kennebunkport, ME); Morely S. Sherman (Biddeford, ME)
Assignee: RTX Corporation
F01D11/003F01D11/005F01D11/08F02C7/18F02C7/28F01D25/246F05D2240/11F05D2240/55F05D2300/6033
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Quick Facts
Patent No.
US 12692795
App. No.
17/977,573
Granted
Jul 28, 2026
Kind
B2
Abstract

There is an axial gap between a leading edge of one of a blade outer air seal and a stator vanes and a trailing edge of the other. A feather seal is positioned to span the axial gap. The feather seal has axially spaced curved portions, with one of the curved portions in contact with a surface of the blade outer air seal and another of the curved portions being in contact with a surface of the stator vane. A pressure differential forces the feather seal into contact with the sealing surfaces and the contact being point contact due to the curved portions.

Claims (13)

1 . A gas turbine engine comprising:

a compressor, a combustor and a turbine section, said turbine section including at least one row of turbine blades rotating about a rotational axis and at least one row of stator vanes axially spaced from said at least one row of turbine blades, and a blade outer air seal positioned radially outward of a radially outer tip of said at least one row of rotating turbine blades, each of said blade outer air seals and said stator vanes having a leading edge and trailing edge, and there being an axial gap between a leading edge of one of said blade outer air seals and said stator vanes and a trailing edge of the other;

a feather seal positioned to span said axial gap, said feather seal having axially spaced curved portions, with one of said curved portions in contact with a surface of said blade outer air seal and another of said curved portions being in contact with a surface of said stator vane; and

a connection to supply cooling air to a radially outer chamber radially outward of at least one of said blade outer air seal and said at least one row of stator vanes, such that there would be a pressure differential between said radially outer chamber and a combustion products chamber radially inward of said blade outer air seal and said stator vanes, with the pressure differential forcing the feather seal into contact with the sealing surfaces on the blade outer air seal and stator vane, and the contact being point contact due to the curved portion;

wherein said blade outer air seal is formed of ceramic matrix composite; and

the feather seals are not constrained at their radially outer extent, and are free to move.

2 . A gas turbine engine comprising:

a compressor, a combustor and a turbine section, said turbine section including at least one row of turbine blades rotating about a rotational axis and at least one row of stator vanes axially spaced from said at least one row of turbine blades, and a blade outer air seal positioned radially outward of a radially outer tip of said at least one row of rotating turbine blades, each of said blade outer air seals and said stator vanes having a leading edge and trailing edge, and there being an axial gap between a leading edge of one of said blade outer air seals and said stator vanes and a trailing edge of the other;

a feather seal positioned to span said axial gap, said feather seal having axially spaced curved portions, with one of said curved portions in contact with a surface of said blade outer air seal and another of said curved portions being in contact with a surface of said stator vane;

a connection to supply cooling air to a radially outer chamber radially outward of at least one of said blade outer air seal and said at least one row of stator vanes, such that there would be a pressure differential between said radially outer chamber and a combustion products chamber radially inward of said blade outer air seal and said stator vanes, with the pressure differential forcing the feather seal into contact with the sealing surfaces on the blade outer air seal and stator vane, and the contact being point contact due to the curved portion;

said blade outer air seal is formed of ceramic matrix composite;

said stator vanes are formed of a metal such that said blade outer air seal and said stator vanes have a different thermal coefficients of expansion; and

wherein the feather seals are not constrained at their radially outer extent, and are free to move.