SUPPORT RAIL TRUSS FOR GAS TURBINE ENGINES

• US 20190136716A1
• Filed: 11/08/2017
• Published: 05/09/2019
• Est. Priority Date: 11/08/2017
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: SPANGLER, BRANDON W., PAULINO, JOSE R., McGARRAH, CRAIG R., BAREISS, EDWARD R., OTERO, EDWIN
• Granted Patent: US 10,641,129 B2
• Time in Patent Office: Days
• CPC Class Codes: F01D 11/08 for sealing space between rotor blade tips and stator specially-shaped blade tips therefor F01D5/20
• CPC Class Codes: F01D 25/246 Fastening of diaphragms or stator-rings
• CPC Class Codes: F01D 9/04 forming ring or sector
• CPC Class Codes: F01D 9/042 fixing blades to stators fixing stator-rings in the casing or to each other F01D25/246
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2230/60 Assembly methods
• CPC Class Codes: F05D 2240/11 Shroud seal segments
• CPC Class Codes: F05D 2240/12 Fluid guiding means, e.g. vanes
• CPC Class Codes: F05D 2250/11 triangular
• CPC Class Codes: F05D 2250/12 rectangular
• CPC Class Codes: F05D 2250/13 trapezoidal
• CPC Class Codes: F05D 2250/14 elliptical

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.

Claims

1. A turbine engine component, comprising:

a platform 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.

2. The turbine engine component of claim 1, wherein the component is one or more of a blade outer air seal and a vane.

3. The turbine engine component of claim 1, wherein the component is one or more of a blade outer air seal support and a vane support.

4. The turbine engine component of claim 1, wherein the outer radial surface is configured to engage an engine casing structure.

5. The turbine engine component of claim 1, wherein the rail includes a hook.

6. The turbine engine component of claim 1, further comprising a second rail having a second outer radial surface and a second inner radial surface, the second inner radial surface connected to the platform, wherein the second rail comprises a second plurality of apertures spaced circumferentially between the second outer radial surface and the second inner radial surface.

7. The turbine engine component of claim 1, wherein the plurality of apertures is configured within the rail to form an outer beam, an inner beam and connecting webs in the rail.

8. The turbine engine component of claim 7, wherein the each aperture has a cross sectional shape in the form of one or more of an ellipse, a rectangle and a trapezoid.

9. The turbine engine component of claim 8, wherein each aperture has a width and a height, the width being less than three times the height.

10. The turbine engine component of claim 9, wherein a distance between centers of adjacent apertures is less than two times the width.

11. The turbine engine component of claim 7, wherein each aperture has a cross sectional shape in the form of a triangle.

12. The turbine engine component of claim 11, wherein each aperture has a cross sectional shape in the form of one of an equilateral triangle and an isosceles triangle.

13. The turbine engine component of claim 11, wherein each aperture has a base and a height and wherein the bases of alternating apertures face radially inward toward a central axis.

14. The turbine engine component of claim 11, wherein pairs of adjacent apertures have a first aperture having a base facing radially inward and a second aperture having a base facing radially outward.

15. The turbine engine component of claim 11, wherein each aperture has an apex opposite the base and wherein radial lines extending through the apexes of adjacent apertures are spaced a distance about equal to the length of each base.

16. 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:

connecting an inner radial surface of a rail of a gas turbine engine component to a platform of the component, 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.

17. The method of claim 16, wherein the turbine engine component is one or more of a blade outer air seal and a blade outer air seal support.

18. The method of claim 17, wherein the apertures are configured within the rail to form an outer beam, an inner beam, and connecting webs in the rail.

19. The method of claim 18, wherein the apertures have a cross sectional shape in the form of one or more of ellipses, rectangles, trapezoids and triangles.

20. The method of claim 18, wherein the apertures have a cross sectional shape in the form of one or more of triangles and trapezoids, wherein pairs of adjacent apertures have a first aperture having a base facing radially inward and a second aperture having a base facing radially outward to form a truss-like structure.