Mateface cooling feather seal assembly
A feather seal assembly includes a seal having a directional passage to direct an airflow generally non-perpendicular to the seal.
1. A feather seal assembly comprising:
an axial seal having a directional passage to direct an airflow generally non-perpendicular to said seal, wherein said directional passage defines a tab along a longitudinal axis of said axial seal; and
a radial seal mounted to said axial seal transverse thereto, said radial seal at least partially retained by said tab, wherein said tab flexes to receive said radial seal thereover.
2. The feather seal assembly as recited in claim 1 , wherein said radial seal is trapped between said tab and a raised feature.
3. The feather seal assembly as recited in claim 1 , wherein said directional passage defines a louver.
4. The feather seal assembly as recited in claim 1 , wherein said seal is an axial seal and said directional passage defines an opening along a longitudinal axis of said axial seal.
5. The feather seal assembly as recited in claim 1 , wherein said directional passage defines an opening transverse to a longitudinal axis of said axial seal.
6. The feather seal assembly as recited in claim 1 , wherein the directional passage provided by the axial seal is configured to be positioned entirely between opposing matefaces of platforms having slots that receive the feather seal.
7. A feather seal assembly comprising:
an axial seal having a directional passage and a raised feature; and
a radial seal mounted to said axial seal between said directional passage and said raised feature, wherein said directional passage defines a tab along a longitudinal axis of said axial seal, said tab flexes to receive said radial seal thereover.
8. The feather seal assembly as recited in claim 7 , wherein said axial seal and said radial seal are mounted between a turbine stator segment.
9. The feather seal assembly as recited in claim 7 , wherein said directional passage is configured to be positioned circumferentially between adjacent stator segments.
10. A method of cooling a mate-face area between stator segments of an annular vane ring structure within a gas turbine engine comprising:
directing an airflow generally non-perpendicular to a seal of a feather seal assembly located between a first stator segment and a second stator segment; and
directing the airflow through a directional passage that defines a tab that traps a radial seal to the seal, the tab flexing to receive said radial seal thereover.
11. The method as recited in claim 10 , further comprising:
directing the airflow along a longitudinal axis of the seal and along the mate-face area.
12. The method as recited in claim 10 , further comprising:
directing the airflow transverse to a longitudinal axis of the seal and toward the first stator segment.