Flange and assembly for gas turbine engine case

Patent metadata

Field	Value
Publication number	US-12084982-B2
Application number	US-202217958946-A
Country	US
Kind code	B2
Filing date	Oct 3, 2022
Priority date	Oct 3, 2022
Publication date	Sep 10, 2024
Grant date	Sep 10, 2024

Abstract

A flange stiffener support for a duct in a gas turbine engine includes a circumferential flange segment that has a plurality of flange fastener openings. An axial body segment extends from a radially inner side of the circumferential segment and has at least one body fastener opening. The axial body segment extends at least partially along a circumferential distance of the circumferential flange segment.

First claim

What is claimed is:

1. A flange stiffener support for a duct in a gas turbine engine and comprising:
a circumferential flange segment having a plurality of flange fastener openings; and
an axial body segment extending from a radially inner side of the circumferential flange segment, the axial body segment having at least one body fastener opening, wherein the axial body segment extends partially along a circumferential distance of the circumferential flange segment;
including a flange fillet segment extending from the radially inner side of the circumferential flange segment with an axial length less than an axial length of the axial body segment, wherein the flange fillet segment is circumferentially spaced from the axial body segment.

2. The flange stiffener support of claim 1 , wherein the axial length of the axial body segment is greater than a radial height of the circumferential flange segment.

3. The flange stiffener support of claim 1 , wherein the circumferential flange segment, the axial body segment, and the flange fillet segment form a single unitary piece.

4. The flange stiffener support of claim 1 , wherein the flange fillet segment extends axially aft of an aft most surface on the circumferential flange segment.

5. The flange stiffener support of claim 1 , wherein the circumferential flange segment includes one of a protrusion or a channel and the axial body segment and flange fillet segment each include the other of the protrusion or the channel.

6. The flange stiffener support of claim 5 , wherein each of the protrusion and the channel include a lengthwise direction that extends circumferentially with the circumferential flange segment.

7. The flange stiffener support of claim 6 , wherein axial body segment extends a first circumferential distance and the flange fillet segment extends a second circumferential distance different from the first circumferential distance.

8. The flange stiffener support of claim 5 , wherein a circumferential end of the axial body segment abuts a circumferential end of the flange fillet segment and a longitudinal axis of the at least one body fastener opening extends substantially perpendicular to a longitudinal axis the plurality of fastener openings in the circumferential flange segment.

9. The flange stiffener support of claim 5 , wherein the protrusion includes one of a dovetail profile or an arcuate profile.

10. The flange stiffener support of claim 5 , wherein the protrusion includes a fir tree profile.

11. A gas turbine engine comprising:
a fan section;
a compressor section;
a turbine section that drives the fan section and the compressor section; and
a duct assembly comprising:
a first duct including a main body and a first flange, wherein the first duct is made of a composite material;
a second duct include including a main body and a second flange; and
a flange stiffener support engaging the first flange, the first flange including a circumferential flange segment, an axial body segment having a plurality of fastener openings, wherein the axial body segment extending from a radially inner side of the circumferential flange segment having at least one body fastener opening, the axial body segment extends along a circumferential distance of the circumferential flange segment, and the axial body segment being secured to the first duct main body by fasteners, with the first duct main body forming an annular structure, and the axial body segment extending only over a portion of a circumference of the first duct main body.

12. The gas turbine engine of claim 11 , including a flange fillet segment extending from the radially inner side of the circumferential flange segment with an axial length less than an axial length of the axial body segment, wherein the flange fillet segment is circumferentially spaced from the axial segment.

13. The gas turbine engine of claim 11 , wherein the axial length of the axial body segment is greater than a radial height of the circumferential flange segment.

14. The gas turbine engine of claim 11 , including an interface ring abutting the first flange and the second flange.

15. The gas turbine engine of claim 11 , wherein the circumferential flange segment includes one of a projection or a channel and the axial body segment and flange fillet segment include the other of the projection or the channel.

16. A method of assembling a duct for a gas turbine engine, the method comprising:
identifying a defect in a composite duct adjacent a first flange; and
selecting a flange stiffener support for engaging the first flange, wherein the flange stiffener support includes a circumferential flange segment having a plurality of fastener openings for securing to the first flange and an axial body segment aligned with the defect and attached to a body portion of the composite duct.

17. The method of claim 16 , wherein selecting the flange stiffener support includes slidably engaging the axially extending portion with the circumferential flange segment of the flange stiffener support.

18. The method of claim 17 , wherein the circumferential flange segment includes one of a protrusion or a channel and the axial body segment include the other of the protrusion or the channel.

Assignees

• Raytheon Tech Corp
• Rtx Corp

Inventors

• Banhos Jonas
• Vieira Thiago B
• Prainito Anthony J
• Roach James T

Classifications

• F05D2240/14

  Casings or housings protecting or supporting assemblies within · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title

• F05D2230/60

  Assembly methods · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F05D2250/70

  Shape · CPC title