Split case structure for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-11614002-B2
Application number	US-202017085494-A
Country	US
Kind code	B2
Filing date	Oct 30, 2020
Priority date	Oct 30, 2020
Publication date	Mar 28, 2023
Grant date	Mar 28, 2023

Abstract

An assembly is provided for a gas turbine engine. This gas turbine engine assembly includes a split case structure. The split case structure includes a first wall, a second wall, a first case segment and a second case segment. The first wall extends axially along and circumferentially about an axial centerline. The second wall extends axially along and circumferentially about the axial centerline. The second wall is radially outboard of and axially overlaps the first wall. The first case segment is configured to form a first portion of the first wall and a first portion of the second wall. The second case segment is configured to form a second portion of the first wall and a second portion of the second wall. The second case segment is circumferentially adjacent and attached to the first case segment at a joint.

First claim

What is claimed is:

1. A manufacturing method, comprising:
forming a split case structure preform that includes a first case segment preform and a second case segment preform, wherein the first case segment preform is formed integral with the second case segment preform as a monolithic body;
separating the first case segment preform from the second case segment preform to respectively provide a first case segment and a second case segment that is discrete from the first case segment, wherein the first case segment is configured to be arranged adjacent and mechanically fastened to the second case segment to form a split case structure for a gas turbine engine; and
mechanically attaching the first case segment to the second case segment to form the split case structure, wherein the split case structure comprises at least one of:
an annular combustion chamber of the gas turbine engine;
a compressor wall configured to circumscribe and house a bladed compressor rotor of the gas turbine engine; or
a turbine wall configured to circumscribe and house a bladed turbine rotor of the gas turbine engine.

2. The manufacturing method of claim 1 , wherein the first case segment preform is indirectly connected to the second case segment preform through one or more intermediate bridge structures.

3. The manufacturing method of claim 1 , wherein the first case segment preform is directly connected to the second case segment preform.

4. The manufacturing method of claim 1 , wherein the forming of the split case structure preform includes additively manufacturing the split case structure preform within a build space of an additive manufacturing system.

5. The manufacturing method of claim 1 , wherein
the split case structure includes a first wall, a second wall, the first case segment and the second case segment;
the first wall extends axially along and circumferentially about an axial centerline;
the second wall extends axially along and circumferentially about the axial centerline, and the second wall is radially outboard of and axially overlaps the first wall;
the first case segment is configured to form a first portion of the first wall and a first portion of the second wall; and
the second case segment is configured to form a second portion of the first wall and a second portion of the second wall, and the second case segment is circumferentially adjacent and attached to the first case segment at a joint.

6. The manufacturing method of claim 5 , wherein one of the first wall and the second wall comprises a diffuser wall.

7. The manufacturing method of claim 5 , wherein one of the first wall and the second wall comprises a combustor wall.

8. The manufacturing method of claim 5 , wherein one of the first wall and the second wall comprises the compressor wall.

9. The manufacturing method of claim 5 , wherein one of the first wall and the second wall comprises the turbine wall.

10. The manufacturing method of claim 5 , wherein the first case segment includes a support member that extends between and connects the first wall to the second wall.

11. The manufacturing method of claim 5 , wherein
the first case segment includes a channel; and
the second case segment includes a seal element inserted within the channel to seal an interface between the first case segment and the second case segment at the joint.

12. The manufacturing method of claim 5 , wherein the split case structure further includes a seal element arranged between and engaged with the first case segment and the second case segment to seal an interface between the first case segment and the second case segment at the joint.

13. The manufacturing method of claim 5 , wherein the first case segment includes a crush seal element configured to engage the second case segment to seal an interface between the first case segment and the second case segment at the joint.

14. The manufacturing method of claim 1 , wherein
the first case segment is configured as a monolithic body; and/or
the second case segment is configured as a monolithic body.

15. The manufacturing method of claim 1 , wherein
the split case structure forms a compressor section inlet and a turbine section outlet;
the first case segment extends axially along an axial centerline from the compressor section inlet to the turbine section outlet; and
the second case segment extends axially along the axial centerline from the compressor section inlet to the turbine section outlet.

16. The manufacturing method of claim 1 , wherein
the split case structure includes the compressor wall, a combustor wall, the turbine wall, the first case segment and the second case segment;
the first case segment is configured to form a first portion of the compressor wall, a first portion of the combustor wall and a first portion of the turbine wall; and
the second case segment is configured to form a second portion of the compressor wall, a second portion of the combustor wall and a second portion of the turbine wall.

17. The manufacturing method of claim 16 , wherein at least one of
the first case segment forms a respective portion of an inlet to a compressor section of the gas turbine engine; or
the first case segment forms a respective portion of an outlet from a turbine section of the gas turbine engine.

18. The manufacturing method of claim 16 , wherein
the split case structure further includes a first wall and a second wall radially outboard of and axially overlapping the first wall;
the first case segment is configured to form a first portion of the first wall and a first portion of the second wall; and
the second case segment is configured to form a second portion of the first wall and a second portion of the second wall.

19. The manufacturing method of claim 1 , further comprising arranging the second case segment circumferentially adjacent and attaching the second case segment to the first case segment at an axially extending joint.

Assignees

• Raytheon Tech Corp

Inventors

• Binek Lawrence A
• Lyda Randolph T

Classifications

• F01D25/24 Primary

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title

• B33Y80/00

  Products made by additive manufacturing · CPC title

• B23P2700/13

  Parts of turbine combustion chambers · CPC title

• B22F5/009

  of turbine components other than turbine blades (of turbine blades B22F5/04) · CPC title

• F05D2240/14

  Casings or housings protecting or supporting assemblies within · CPC title