A seal assembly is provided for a turbine engine and includes an annular labyrinth seal holder supported on a radially inner end of vanes A plurality of radially extending labyrinth seal elements are supported on the labyrinth seal holder, and a brush seal assembly is supported to the labyrinth seal
A seal assembly is provided for a turbine engine and includes an annular labyrinth seal holder supported on a radially inner end of vanes A plurality of radially extending labyrinth seal elements are supported on the labyrinth seal holder, and a brush seal assembly is supported to the labyrinth seal holder downstream from the labyrinth seal elements. The brush seal assembly includes a brush seal holder and a brush seal located adjacent to an axially rearward one of the rotor arms. The brush seal holder is attached to an axially facing surface of the labyrinth seal holder. A seal plate defining a detachable labyrinth seal element extends radially inward from the axially facing surface of the labyrinth seal holder to the rearward rotor arm at a location upstream of the brush seal.
대표청구항▼
1. A seal assembly for a turbine engine including adjacent upstream and downstream rotating rotor disks supporting respective rows of blades, a row of stationary vanes located between said rows of blades, and an axially extending rotor arm supported on each said rotor disk and located radially inwar
1. A seal assembly for a turbine engine including adjacent upstream and downstream rotating rotor disks supporting respective rows of blades, a row of stationary vanes located between said rows of blades, and an axially extending rotor arm supported on each said rotor disk and located radially inward from said blades, the seal assembly comprising: an annular labyrinth seal holder supported on a radially inner end of said vanes and having a radially inner surface and a downstream axially facing surface;a plurality of radially extending labyrinth seal elements supported on said radially inner surface of said labyrinth seal holder in axially spaced relation to each other;a brush seal assembly supported to said labyrinth seal holder downstream from said labyrinth seal elements, said brush seal assembly including a brush seal holder and a brush seal comprising seal bristles having fixed ends supported to said brush seal holder and free ends located adjacent to an axially rearward one of said rotor arms, said brush seal holder being attached to said axially facing surface of said labyrinth seal holder; anda seal plate defining a detachable labyrinth seal element extending radially inward from said labyrinth seal holder to said rearward rotor arm at a location upstream of said brush seal, said seal plate being sandwiched between said labyrinth seal holder and said brush seal holder;wherein said brush seal assembly is mounted to said labyrinth seal holder by a plurality of circumferentially spaced bolts extending through said brush seal holder and said labyrinth seal holder, and said bolts extend through holes in said seal plate to circumferentially position said seal plate. 2. The seal assembly of claim 1, wherein said plurality of labyrinth seal elements supported on said inner surface of said labyrinth seal holder have inner ends located axially aligned with a forward one of said rotor arms. 3. The seal assembly of claim 2, wherein a distance from said inner surface of said labyrinth seal holder to an end of said labyrinth seal elements, distal from said labyrinth seal holder, is the same for each labyrinth seal element. 4. The seal assembly of claim 1, wherein said row of vanes includes a radially inner vane endwall defining a radially inner boundary for a hot gas path through said turbine and having upstream and downstream edges, said row of blades on said downstream disk includes a radially inner blade endwall having an upstream edge spaced from said downstream edge of said vane endwall an endwall gap distance, and wherein said downstream disk has a radial face structure that extends radially outward from a location on said rearward rotor arm and faces axially toward a downstream axial face of said brush seal assembly, said radial face structure being spaced said endwall gap distance from said downstream axial face of said brush seal assembly. 5. The seal assembly of claim 4, wherein said radial face structure includes an upstream facing surface that extends radially outward from a downstream end of said rearward rotor arm, said radial face structure including retention elements for retaining cover plates in engagement with a forward facing side of said downstream disk. 6. The seal assembly of claim 5, wherein said retention elements include bolts having bolt heads extending axially forward from said upstream facing surface, and the spacing between said radial face structure and said downstream axial face of said brush seal assembly is a minimum axial distance measured from said downstream axial face of said brush seal assembly to said bolt heads. 7. The seal assembly of claim 4, wherein said rotor arms define a seal surface that is a smooth surface facing radially outward from said rotor arms, said seal surface defining a constant radial distance from a forward seal surface on said forward rotor arm to said inner surface of said labyrinth seal holder and from a rearward seal surface on said rearward rotor arm to a radially inner surface of said brush seal holder. 8. A seal assembly for a turbine engine including adjacent upstream and downstream rotating rotor disks supporting respective rows of blades, a row of stationary vanes located between said rows of blades, and axially extending forward and rearward rotor arms supported on said upstream and downstream rotor disks, respectively, and located radially inward from said blades, the seal assembly comprising: an annular labyrinth seal holder supported on a radially inner end of said vanes and having a radially inner surface and a downstream axially facing surface;a plurality of radially extending labyrinth seal elements supported on said radially inner surface of said labyrinth seal holder in axially spaced relation to each other, and said labyrinth seal elements are all the same length from said inner surface of said labyrinth seal holder to an end of said labyrinth seal elements, distal from said labyrinth seal holder;a brush seal assembly supported to said labyrinth seal holder downstream from said labyrinth seal elements and having a radially inner surface, said brush seal assembly including a brush seal holder and a brush seal extending radially to said rearward rotor arm, said brush seal holder being bolted to said downstream facing surface of said labyrinth seal holder;a seal plate defining a detachable labyrinth seal element extending radially inward from said labyrinth seal holder to said rearward rotor arm at a location upstream of said brush seal, said seal plate being sandwiched between said labyrinth seal holder and said brush seal holder; andsaid rotor arms including seal surfaces that face radially outward toward said inner surfaces of said labyrinth seal holder and said brush seal holder, said seal surfaces being smooth surfaces, extending in the axial direction, defining a constant radial distance from said seal surface on said forward and rearward rotor arms to said inner surface of said labyrinth seal holder and to said inner surface of said brush seal holder;wherein said brush seal assembly is mounted to said labyrinth seal holder by a plurality of circumferentially spaced bolts extending through said brush seal holder and said labyrinth seal holder, and said bolts extend through holes in said seal plate to circumferentially position said seal plate. 9. The seal assembly of claim 8, wherein said plurality of labyrinth seal elements supported on said inner surface of said labyrinth seal holder have inner ends located axially aligned with a forward one of said rotor arms. 10. The seal assembly of claim 8, wherein said row of vanes includes a radially inner vane endwall defining a radially inner boundary for a hot gas path through said turbine and having upstream and downstream edges, said row of blades on said downstream disk includes a radially inner blade endwall having an upstream edge spaced from said downstream edge of said vane endwall an endwall gap distance, and wherein said downstream disk has a radial face structure that extends radially outward from a location on said rearward rotor arm and faces axially toward a downstream face of said brush seal assembly, said radial face structure being spaced said endwall gap distance from said downstream axial face of said brush seal assembly. 11. The seal assembly of claim 10, wherein said radial face structure includes an upstream axially facing surface that extends radially outward from a downstream end of said rearward rotor arm, said radial face structure including retention elements for retaining cover plates in engagement with a forward facing side of said downstream disk. 12. The seal assembly of claim 11, wherein said retention elements include bolts having bolt heads extending axially forward from said upstream facing surface, and the spacing between said radial face structure and said downstream face of said brush seal assembly is a minimum axial distance measured from said downstream face of said brush seal assembly to said bolt heads.
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이 특허에 인용된 특허 (10)
Basu Prithwish (Pawtucket RI), Brush seal device having a recessed back plate.
Burnett, Mark Edward; Turnquist, Norman Arnold; Wolfe, Christopher Edward; Brisson, Bruce William; Baily, Fredrick George; Caruso, David Alan, Method and apparatus for eliminating thermal bowing and axial thrust loads of steam turbine rotors.
Bouchard Joseph P. (Arundel ME) Long Merrell W. (North Waterboro ME), Method and apparatus for improving the airsealing effectiveness in a turbine engine.
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