Support rail truss for gas turbine engines
First Claim
Patent Images
1. A turbine engine component, comprising:
- a platform disposed radially outward of at least one of a rotor assembly and a vane assembly anda rail having an outer radial surface and an inner radial surface, the inner radial surface connected to the platform,wherein the rail comprises a plurality of apertures spaced circumferentially between the outer radial surface and the inner radial surface, the plurality of apertures configured within the rail to form an outer beam, an inner beam and connecting webs in the rail andwherein each aperture has a cross sectional shape in the form of a triangle having a base and a height, with each pair of adjacent apertures defining a first aperture having a base facing radially inward and a second aperture having a base facing radially outward with respect to an engine central longitudinal axis.
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Abstract
A component for a gas turbine engine is disclosed. The component includes a platform and a rail having an outer radial surface and an inner radial surface, with the inner radial surface connected to the platform. The rail includes a plurality of apertures spaced circumferentially between the outer radial surface and the inner radial surface, the apertures disposed to form a truss-like structure.
14 Citations
11 Claims
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1. A turbine engine component, comprising:
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a platform disposed radially outward of at least one of a rotor assembly and a vane assembly and a rail having an outer radial surface and an inner radial surface, the inner radial surface connected to the platform, wherein the rail comprises a plurality of apertures spaced circumferentially between the outer radial surface and the inner radial surface, the plurality of apertures configured within the rail to form an outer beam, an inner beam and connecting webs in the rail and wherein each aperture has a cross sectional shape in the form of a triangle having a base and a height, with each pair of adjacent apertures defining a first aperture having a base facing radially inward and a second aperture having a base facing radially outward with respect to an engine central longitudinal axis. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9)
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10. A method of reducing weight of a turbine engine component while minimizing tip gap variation between a blade tip and a blade outer air seal, the method comprising:
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connecting an inner radial surface of a rail of a gas turbine engine component to a platform of the component, the platform configured for disposition radially outward of at least one of a rotor assembly and a vane assembly and the rail comprising an outer radial surface and forming a plurality of apertures within the rail spaced circumferentially between the outer radial surface and the inner radial surface, the plurality of apertures configured within the rail to form an outer beam, an inner beam and connecting webs in the rail, wherein each aperture has a cross sectional shape in the form of a triangle having a base and a height, with each pair of adjacent apertures defining a first aperture having a base facing radially inward and a second aperture having a base facing radially outward with respect to an engine central longitudinal axis. - View Dependent Claims (11)
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Specification