Gas turbine frame stiffening rails

Patent metadata

Field	Value
Publication number	US-9316108-B2
Application number	US-201213412014-A
Country	US
Kind code	B2
Filing date	Mar 5, 2012
Priority date	Mar 5, 2012
Publication date	Apr 19, 2016
Grant date	Apr 19, 2016

Abstract

Gas turbine engine frames are disclosed. An example gas turbine engine frame may include a generally annular outer casing disposed coaxially about a hub; a plurality of circumferentially spaced apart struts joined to the hub and the outer casing, individual struts extending radially outwardly from the hub to the outer casing; and a stiffening rail monolithically formed with the outer casing circumferentially between two of the struts. The stiffening rail may extend radially inward beyond the inner surface of the outer casing between the struts.

First claim

What is claimed is:

1. A gas turbine engine frame, comprising:
a generally annular outer casing disposed substantially coaxially about a centerline axis, the outer casing comprising an outer surface facing radially outward away from the centerline axis and an inner surface facing radially inward toward the centerline axis;
a hub disposed within the outer casing and spaced radially inward from the inner surface of the outer casing, the hub being arranged substantially coaxially about the centerline axis;
a plurality of circumferentially spaced apart struts fixedly joined to the hub and the outer casing, individual struts extending generally radially outwardly from the hub to the outer casing; and
a stiffening rail monolithically formed with the outer casing circumferentially between two of the struts, the stiffening rail having
a height radially outward beyond the outer surface of the outer casing generally approximate a first one of the struts and generally approximate a second one of the struts, and
a depth radially inward beyond the inner surface of the outer casing between the first strut and the second strut;

wherein the depth of the stiffening rail increases from a minimum approximate the first strut to a maximum substantially midway between the first strut and the second strut, and
wherein the height of the stiffening rail decreases from a maximum approximate the first strut to a minimum substantially midway between the first strut and the second strut.

2. The gas turbine engine frame of claim 1 , wherein the stiffening rail provides a load path between the outer casing at the first strut and the outer casing at the second strut.

3. The gas turbine engine frame of claim 1 ,
wherein the stiffening rail comprises a first stiffening rail and a second stiffening rail, and
wherein the first stiffening rail and the second stiffening rail are arranged substantially in parallel in a generally circumferential direction.

4. The gas turbine engine frame of claim 1 , wherein the stiffening rail has a mean load line.

5. The gas turbine engine frame of claim 1 ,
wherein the stiffening rail comprises a radially inwardly facing surface, and
wherein the radially inwardly facing surface of the stiffening rail is concavely curved.

6. The gas turbine engine frame of claim 1 ,
further comprising a pad formed in the outer casing generally midway circumferentially between the first strut and the second strut, the pad comprising a central opening extending radially through the outer casing.

7. The gas turbine engine frame of claim 6 , wherein the stiffening rail intersects the pad.

8. The gas turbine engine frame of claim 1 ,
further comprising a first boss formed on the outer casing approximate the first strut and a second boss formed on the outer casing approximate the second strut;
wherein the stiffening rail intersects the first boss and the second boss.

9. The gas turbine engine frame of claim 1 , wherein the stiffening rail comprises a plurality of intersecting ligaments arranged in a web and extending radially inward beyond the inner surface of the outer casing.

10. The gas turbine engine frame of claim 1 , wherein the stiffening rail comprises a fastener interface configured to prevent substantial rotation of a fastener engaged therewith.

11. A gas turbine engine frame, comprising:
a generally annular outer casing disposed substantially coaxially about a centerline axis, the outer casing comprising an outer surface facing radially outward away from the centerline axis and an inner surface facing radially inward toward the centerline axis;
a hub disposed within the outer casing and spaced radially inward from the inner surface of the outer casing, the hub being arranged substantially coaxially about the centerline axis;
a plurality of circumferentially spaced apart struts fixedly joined to the hub and the outer casing, individual struts extending generally radially outwardly from the hub to the outer casing; and
a first stiffening rail and a second stiffening rail monolithically formed with the outer casing circumferentially between two of the struts, the first stiffening rail and the second stiffening rail arranged substantially in parallel in a generally circumferential direction, each of the first stiffening rail and the second stiffening rail having
a height radially outward beyond the outer surface of the outer casing generally approximate a first one of the struts and generally approximate a second one of the struts, and
a depth radially inward beyond the inner surface of the outer casing between the first strut and the second strut;
wherein the depth of the first stiffening rail and the depth of the second stiffening rail increase from minimums approximate the first strut and the second strut to maximums substantially midway between the first strut and the second strut, and
wherein the height of the first stiffening rail and the height of the second stiffening rail decrease from maximums approximate the first strut and the second strut to minimums substantially midway between the first strut and the second strut.

12. The gas turbine engine frame of claim 11 , further comprising a pad formed in the outer casing generally midway circumferentially between the first strut and the second strut, the pad comprising a central opening extending radially through the outer casing.

13. The gas turbine engine frame of claim 12 , wherein the pad extends axially from the first stiffening rail to the second stiffening rail.

14. The gas turbine engine frame of claim 12 , wherein the pad comprises at least one mounting hole.

15. The gas turbine engine frame of claim 11 , wherein a mean load line of the first stiffening rail and a mean load line of the second stiffening rail are between the first strut and the second strut.

16. The gas turbine engine frame of claim 11 ,
wherein each of the first stiffening rail and the second stiffening rail comprises a radially inwardly facing surface, and
wherein the radially inwardly facing surface of the first stiffening rail and the radially inwardly facing surface of the second stiffening rail are concavely curved.

17. A gas turbine engine comprising:
a low-pressure compressor;
a high-pressure compressor;
a combustor;
a high-pressure turbine arranged to drive the high-pressure compressor via a first shaft; and
a low-pressure turbine arranged to drive the low-pressure compressor via a second shaft;
wherein at least one of the first shaft and the second shaft is at least partially supported by a hub of a turbine frame;
wherein the turbine frame comprises
a generally annular outer casing disposed substantially coaxially with the hub, the outer casing comprising an outer surface facing radially outward away from the hub and an inner surface facing radially inward toward the hub, the inner surfacing being spaced radially outward from the hub,
a plurality of circumferentially spaced apart struts fixedly joined to the hub and the outer casing, individual struts extending generally radially outwardly from the hub to the outer casing, and
a stiffening rail monolithically formed with the outer casing circumferentially between two of the struts, the stiffening rail having a depth radially inward beyond the inner surface of the outer casing between the first strut and the second strut
wherein the depth of the stiffening rail increases from a minimum approximate the first strut to a maximum substantially midway between the first strut and the second strut, and
wherein the height of the stiffening rail decreases from a maxim

Assignees

• Pegan Jr Courtland Earl
• Hildebrand Kurt Thomas
• Ryczek Scott Patrick
• Dreischarf Derek Thomas
• Gen Electric

Inventors

• Pegan Jr Courtland Earl
• Hildebrand Kurt Thomas
• Ryczek Scott Patrick
• Dreischarf Derek Thomas

Classifications

• F01D25/162

  Bearing supports · CPC title

• F01D9/065 Primary

  Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26) · CPC title