Component for fastening arrangement, fastening arrangement and gas turbine engine comprising fastening arrangement

Patent metadata

Field	Value
Publication number	US-2020240293-A1
Application number	US-202016744507-A
Country	US
Kind code	A1
Filing date	Jan 16, 2020
Priority date	Jan 28, 2019
Publication date	Jul 30, 2020
Grant date	—

Abstract

A component for a fastening arrangement of a gas turbine engine, the component comprising: a first abutment member; a second abutment member; a spring member between the first and second abutment members; a conduit comprising a throughole through the first and second abutment members and the spring member; the component being configured such that a shaft of a fastener passes through the throughole, a head of the fastener abuts the first abutment member and a part to be fastened by the fastening arrangement abuts the second abutment member, when the component is in the fastening arrangement.

First claim

We claim:

1 . A component for a fastening arrangement of a gas turbine engine, the component comprising:
a first abutment member; a second abutment member; a spring member between the first and second abutment members; and a conduit comprising a throughole through the first and second abutment members and the spring member; the component being configured such that a shaft of a fastener passes through the throughole, a head of the fastener abuts the first abutment member and a part to be fastened by the fastening arrangement abuts the second abutment member, when the component is in the fastening arrangement.

2 . The component of claim 1 , wherein the second abutment member and the conduit comprise respective engagement portions configured to engage with each other to prevent rotational displacement between the second abutment member and the conduit about an axis through the throughole.

3 . The component of claim 2 , wherein the engagement portions comprise respective channels and protrusions.

4 . The component of claim 3 , wherein the channels are provided in an outer wall of the conduit.

5 . The component of claim 2 , wherein the engagement portions are configured to engage with each other to allow translational displacement between the second abutment member and the conduit in a direction parallel to the axis through the throughole.

6 . The component of claim 2 , comprising at least two sets of respective engagement portions.

7 . The component of claim 1 , wherein the first and second abutment members substantially surround the conduit.

8 . The component of claim 1 , wherein the conduit is substantially cylindrical in shape.

9 . The component of claim 1 , wherein the first and/or second abutment members are substantially disc-shaped.

10 . The component of claim 1 , wherein the conduit extends from the first abutment member.

11 . The component of claim 1 , wherein the conduit is integrally formed with the first abutment member.

12 . The component of claim 1 , wherein the second abutment member is connected to the first abutment member by the spring member.

13 . The component of claim 1 , wherein the first and second abutment members and the spring member are integrally formed.

14 . The component of claim 1 , wherein the component is formed as one element by an additive manufacturing process.

15 . The component of claim 1 , wherein the spring member substantially surrounds the walled conduit.

16 . The component of claim 1 , wherein the spring is configured to provide a spring force in a direction parallel to an axis through the throughole.

17 . A fastening arrangement for fastening together first and second parts of gas turbine engine having a throughole therethrough, the fastening arrangement comprising:
the component of claim 1 , wherein the conduit is arranged with the throughole in the first and second parts and the second abutment member abuts the first part; and a fastener comprising a shaft arranged within the throughole of the conduit and a head abutting the first abutment part.

18 . The fastening arrangement of claim 17 , further comprising a nut configured to engage with a thread on the shaft of the fastening member, and arranged to abut the second part of the gas turbine engine and tighten the fastening arrangement such that the spring member is compressed between the head of the fastener and the first part of the gas turbine engine.

19 . The fastening arrangement of claim 17 , further comprising an insert arranged between the first part of the gas turbine engine and at least one of the second abutment member and the conduit.

Assignees

• Rolls Royce Plc

Inventors

• Cousins Daniel
• Gupta Alok

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F16B5/0241

  with the possibility for the connection to absorb deformation, e.g. thermal or vibrational · CPC title

• F05D2260/31

  Retaining bolts or nuts · CPC title

• F02K3/06

  with front fan · CPC title

• F01D25/162

  Bearing supports · CPC title