US 2010/0074734 A1 · Turbine Seal Assembly

Abstract

A seal assembly that limits gas leakage from a hot gas path to one or more disc cavities in a turbine engine. The seal assembly includes a seal apparatus that limits gas leakage from the hot gas path to a respective one of the disc cavities. The seal apparatus comprises a plurality of blade members rotatable with a blade structure. The blade members are associated with the blade structure and extend toward adjacent stationary components. Each blade member includes a leading edge and a trailing edge, the leading edge of each blade member being located circumferentially in front of the blade member's corresponding trailing edge in a direction of rotation of the turbine rotor. The blade members are arranged such that a space having a component in a circumferential direction is defined between adjacent circumferentially spaced blade members.

Claims20

Dependent claims

A seal assembly that limits gas leakage from a hot gas path to one or more disc cavities in a turbine engine comprising a plurality of stages, each stage comprising a plurality of stationary components and a disc structure supporting a plurality of blade structures for rotation on a turbine rotor, the seal assembly comprising:

a first seal apparatus that limits gas leakage from the hot gas path to a first disc cavity associated with a first axially facing side of a blade structure including a row of airfoils, said first seal apparatus comprising:
a plurality of first blade members rotatable with said blade structure, said first blade members associated with said first axially facing side of said blade structure and extending toward adjacent first stationary components, each said first blade member including a leading edge and a trailing edge, said leading edge of each said first blade member located circumferentially in front of said trailing edge of said corresponding first blade member in a direction of rotation of the turbine rotor, said first blade members arranged such that a space having a component in a circumferential direction is defined between adjacent circumferentially spaced first blade members.

a first seal apparatus that limits gas leakage from the hot gas path to a first disc cavity associated with a first axially facing side of a blade structure including a row of airfoils, said first seal apparatus comprising:
a first wing member extending axially from said first axially facing side of said blade structure toward an adjacent first annular inner shroud associated with adjacent first stationary components, said first wing member including a radially inner side and a radially outer side;
and
a plurality of first wing blade members rotatable with said blade structure and arranged on said radially outer side of said first wing member such that a space having a component in a circumferential direction is defined between adjacent circumferentially spaced first wing blade members, each of said first wing blade members extending radially outwardly from said outer side of said first wing member toward a radially facing surface of said first annular inner shroud, said radially facing surface of said first annular inner shroud at least partially axially overlapping said first wing blade members.

1 more element

a first seal apparatus that limits gas leakage from the hot gas path to a first disc cavity associated with a first axially facing side of a blade structure including a row of airfoils, said first seal apparatus comprising:
a plurality of first radial blade members extending axially outwardly from said first axially facing side of said blade structure toward an adjacent first annular inner shroud associated with adjacent first stationary components, said first radial blade members arranged such that a space having a component in a circumferential direction is defined between adjacent circumferentially spaced first radial blade members, wherein a radially inner corner portion of each said first radial blade member is located proximate to a radially outwardly facing surface of an axial end portion of said first annular inner shroud.

Dependencies are inferred from the claim text.

Turbine Seal Assembly

Life of this patent

Turbine Seal Assembly

Life of this patent

Abstract

Claims20