Metallic attachment system integrated into a composite structure

• US 10,316,695 B2
• Filed: 12/10/2015
• Issued: 06/11/2019
• Est. Priority Date: 12/10/2015
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Renggli, Bernard James
• Primary Examiner(s): McMahon, Matthew R
• Application Number:
  US14/964,752
• Publication Number:
  US 20170167296A1
• Time in Patent Office: 1,279 Days
• CPC Class Codes: B32B 2260/023 Two or more layers
• CPC Class Codes: B32B 2260/046 Synthetic resin
• CPC Class Codes: B32B 2262/105 Ceramic fibres
• CPC Class Codes: B32B 2605/18 Aircraft blades, propellers B32B2603/00
• CPC Class Codes: B32B 3/06 for securing layers together; for attaching the product to another member, e.g. to a support , or to another product, e.g. groove/tongue, interlocking
• CPC Class Codes: B32B 3/266 characterised by an apertured layer, the apertures going through the whole thickness of the layer, e.g. expanded metal, perforated layer, slit layer regular cells B32B3/12
• CPC Class Codes: B32B 5/26 another layer next to it also being fibrous or filamentary relative arrangement of fibres or filaments of different layers B32B5/12
• CPC Class Codes: C04B 2235/48 Organic compounds becoming part of a ceramic after heat treatment, e.g. carbonising phenol resins
• CPC Class Codes: C04B 2235/522 Oxidic
• CPC Class Codes: C04B 2235/616 Liquid infiltration of green bodies or pre-forms
• CPC Class Codes: C04B 35/14 based on silica
• CPC Class Codes: C04B 35/80 Fibres, filaments, whiskers, platelets, or the like
• CPC Class Codes: F01D 25/005 Selecting particular materials
• CPC Class Codes: F01D 25/243 Flange connections; Bolting arrangements F01D25/265 takes precedence
• CPC Class Codes: F01D 25/26 Double casings; Measures against temperature strain in casings
• CPC Class Codes: F01D 25/28 Supporting or mounting arrangements, e.g. for turbine casing
• CPC Class Codes: F02K 1/04 Mounting of an exhaust cone in the jet pipe
• CPC Class Codes: F02K 1/80 Couplings or connections
• CPC Class Codes: F05D 2230/22 by sintering
• CPC Class Codes: F05D 2230/31 Layer deposition
• CPC Class Codes: F05D 2230/60 : Assembly methods
• CPC Class Codes: F05D 2260/31 : Retaining bolts or nuts
• CPC Class Codes: F05D 2300/175 : Superalloys
• CPC Class Codes: F05D 2300/603 : Composites; e.g. fibre-reinforced
• CPC Class Codes: F05D 2300/6033 : Ceramic matrix composites [CMC]
• CPC Class Codes: F16B 2200/506 : bolted or riveted
• CPC Class Codes: Y02T 50/60 : Efficient propulsion technologies, e.g. for aircraft

Abstract

The present disclosure is directed to a composite component defining a component aperture extending between a first surface and a second surface. The composite component includes an insert having an insert annular wall positioned in the component aperture. The insert annular wall defines an insert aperture therethrough. An insert flange extends radially outwardly from the insert annular wall and contacts the first surface of the composite component. The insert flange includes a diameter about 1.5 times to about 5 times greater than a smallest diameter of the component aperture defined by the composite component.

Claims

1. An attachment assembly for a gas turbine, comprising:

a first component defining a first aperture;

a second component at least partially overlapping the first component, wherein the second component includes a first surface and a second surface and defines a second aperture extending between the first surface and the second surface;

an insert comprising an insert annular wall positioned in the second aperture of the second component and an insert flange extending radially outwardly from the insert annular wall, wherein the insert flange is adjacent to the first surface of the second component, and wherein the insert annular wall defines an insert aperture therethrough;

a bushing comprising a bushing annular wall positioned in the second aperture of the second component and a bushing flange extending radially outwardly from the bushing annular wall, wherein the bushing annular wall defines a bushing aperture therethrough;

a spring washer positioned between the second surface of the second component and the bushing flange; and

a fastener that couples the first component and the second component, wherein the first aperture, the insert aperture, the bushing aperture, and the second aperture receive the fastener, wherein the fastener has a head and a shank extending from the head, and wherein an axial gap is defined between the head and the bushing flange in which no components are positioned.

2. The attachment assembly of claim 1, wherein the first component is a metallic turbine rear frame and the second component is a composite center body.

3. The attachment assembly of claim 1 wherein the first component is a composite forward center body and the second component is a composite aft center body.

4. The attachment assembly of claim 1, wherein a diameter of the insert flange is relatively longer than a length of the insert annular wall.

5. The attachment assembly of claim 1, wherein the bushing directly engages the insert.

6. The attachment assembly of claim 1, further comprising:

a leaf seal positioned between and directly engaging the first component and the insert flange.

7. The attachment assembly of claim 1, further comprising:

a collar positioned in the first aperture of the first component for threadingly engaging the fastener.

8. The attachment assembly of claim 1, further comprising:

a backer washer positioned between and directly engaging the spring washer and the second component.

9. The attachment assembly of claim 1, wherein the bushing, the spring washer, and the fastener are metallic.

10. The attachment assembly of claim 1, wherein the insert annular wall of the insert is threadingly coupled with the bushing annular wall of the bushing.

11. The attachment assembly of claim 1, wherein the insert annular wall has a radial surface and the bushing flange has a first surface and a second surface spaced radially outward of the first surface, and wherein the radial surface of the insert annular wall engages the second surface of the bushing flange.

12. The attachment assembly of claim 11, further comprising:

a backer washer positioned between and directly engaging the spring washer and the second component, and wherein the spring washer directly engages the backer washer and the second surface of the bushing flange.

13. An attachment assembly for a gas turbine, comprising:

a first component defining a first aperture and having a first surface and a second surface radially spaced from the first surface;

a first insert having a first insert annular wall positioned in the first aperture of the first component and a first insert flange extending radially outward from the first insert annular wall, wherein the first insert flange is adjacent to the first surface of the first component, and wherein the first insert annular wall defines a first insert aperture therethrough;

a first bushing having a first bushing annular wall positioned in the first aperture of the first component and a first bushing flange extending radially outward from the first bushing annular wall, wherein the first bushing annular wall defines a first bushing aperture therethrough, and wherein the first bushing flange directly engages the first insert annular wall;

a first spring washer positioned between the second surface of the first component and the first bushing flange;

a second component at least partially overlapping the first component, wherein the second component has a first surface and a second surface and defines a second aperture extending between the first surface of the second component and the second surface of the second component;

a second insert having a second insert annular wall positioned in the second aperture of the second component and a second insert flange extending radially outward from the second insert annular wall, wherein the second insert flange is adjacent to the first surface of the second component, and wherein the second insert annular wall defines a second insert aperture therethrough;

a second bushing having a second bushing annular wall positioned in the second aperture of the second component and a second bushing flange extending radially outward from the second bushing annular wall, wherein the second bushing annular wall defines a second bushing aperture therethrough, and wherein the second bushing flange directly engages the second insert annular wall;

a second spring washer positioned between the second surface of the second component and the second bushing flange; and

a fastener coupling the first component and the second component, wherein the first aperture, the first insert aperture, the first bushing aperture, the second aperture, the second insert aperture, and the second bushing aperture receive the fastener.

14. The attachment assembly of claim 13, wherein the first insert annular wall of the first insert is threadingly coupled with the first bushing annular wall of the first bushing and the second insert annular wall of the second insert is threadingly coupled with the second bushing annular wall of the second bushing.

15. The attachment assembly of claim 13, wherein the second bushing annular wall is threadingly coupled with the fastener.

16. The attachment assembly of claim 13, wherein the first bushing flange of the first bushing has a first surface and a second surface radially spaced from the first surface of the first bushing flange, and wherein the first surface of the first bushing flange directly engages the second insert flange.

17. The attachment assembly of claim 16, wherein the first surface of the first bushing flange directly engages the second bushing annular wall.

18. The attachment assembly of claim 13, wherein the first insert annular wall has a radially inner surface having a threaded portion and a smooth portion positioned axially outward of the threaded portion, wherein the threaded portion of the first insert annular wall threadingly couples the first insert with the first bushing.

19. The attachment assembly of claim 13, wherein the first insert annular flange is positioned radially outward of the first component, the first bushing flange and the second insert annular flange are positioned radially between the first component and the second component, and the second bushing flange is positioned radially inward of the second component.