Claims
- 1. A stator vane assembly for a gas turbine engine, comprising:
- a plurality of stator vane segments, each said segment having an outer platform, an inner platform, and an airfoil extending between said platforms, said vane segments collectively forming an annular structure; and
- a seal ring, attached to a non-rotating member within the gas turbine engine, having a body and an abradable bearing pad, said abradable bearing pad extending out from an axial surface of said seal ring, positioned in close proximity to said stator vane segments;
- wherein contact and consequent friction between each said stator vane segment and said abradable bearing pad causes said abradable bearing pad to abrade, thereby creating a sealing surface reflective of each said stator vane segment in contact with said abradable bearing pad.
- 2. A stator vane assembly for a gas turbine engine according to claim 1, wherein said abradable bearing pad is aligned with one of said inner or outer platforms of said stator vane segments.
- 3. A stator vane assembly for a gas turbine engine according to claim 1, wherein abradable bearing pad is bonded to said axial surface of said seal ring.
- 4. A stator vane assembly for a gas turbine engine according to claim 3, wherein said abradable bearing pad is aligned with one of said inner or outer platforms of said stator vane segments.
- 5. A stator vane assembly for a gas turbine engine according to claim 1, wherein seal ring further comprises:
- a stop, attached to said axial surface of said seal ring, wherein said stop extends axially out from said axial surface a distance less than said abradable bearing pad extends axially out from said axial surface.
- 6. A stator vane assembly for a gas turbine engine according to claim 5, wherein said abradable bearing pad is aligned with one of said inner or outer platforms of said stator vane segments.
- 7. A stator vane assembly for a gas turbine engine according to claim 6, wherein said stop is attached to said axial surface adjacent said abradable bearing pad.
- 8. A stator vane assembly for a gas turbine engine according to claim 1, wherein said abradable bearing pad is a detachable and replaceable ring, mounted on said body of said seal ring.
- 9. A stator vane assembly for a gas turbine engine according to claim 8, wherein said abradable bearing pad is aligned with one of said inner or outer platforms of said stator vane segments.
- 10. A method for sealing a stator vane assembly for a gas turbine engine, comprising the steps of:
- providing a stator vane assembly, having a plurality of stator vane segments, each said segment having an outer platform, an inner platform, and an airfoil extending between said platforms, said vane segments collectively forming an annular structure; and
- providing a seal ring, positioned between said stator vane segments and a static member within the gas turbine engine, said seal ring including a body and an abradable bearing pad extending out from an axial surface of said body;
- attaching said seal ring to a non-rotating member within the gas turbine engine, with said abradable bearing pad in close proximity to said stator vane segments; and
- biasing said abradable bearing pad into contact with said stator vane segments;
- abrading said abradable bearing pad with said stator vane segments, thereby creating a sealing surface reflective of each said stator vane segment in contact with said abradable bearing pad.
Government Interests
The invention was made under a U.S. Government contract and the Government has rights herein.
US Referenced Citations (6)