Guide vane retention assembly for gas turbine engine

Patent metadata

Field	Value
Publication number	US-10808559-B2
Application number	US-201815995907-A
Country	US
Kind code	B2
Filing date	Jun 1, 2018
Priority date	Jun 1, 2018
Publication date	Oct 20, 2020
Grant date	Oct 20, 2020

Abstract

A guide vane retention system for a gas turbine engine. The system includes an outer diameter shroud defining an aperture. Also included is a guide vane having a radially outer end extending through the aperture, the guide vane defining a slot proximate the radially outer end and positioned radially outwardly of the outer diameter shroud in an installed condition of the guide vane. Further included is a clip disposed within the slot of the guide vane. The clip includes a looped end. The clip also includes a first leg extending away from the looped end to a first free end. The clip further includes a second leg extending away from the looped end to a second free end.

First claim

What is claimed is:

1. A guide vane retention system for a gas turbine engine comprising:
an outer diameter shroud defining an aperture;
a guide vane having a radially outer end extending through the aperture, the guide vane defining a slot proximate the radially outer end and positioned radially outwardly of the outer diameter shroud in an installed condition of the guide vane; and
a clip disposed within the slot of the guide vane, the clip comprising:
a looped end;
a first leg extending away from the looped end to a first free end, the first leg defining a hole; and
a second leg extending away from the looped end to a second free end; and

a rubber potting applied between the first leg and the second leg after the clip is inserted into the slot and within the hole of the first leg to provide a rubber rivet.

2. The guide vane retention system of claim 1 , wherein the first leg and the second leg extend away from a loop termination location of the looped end.

3. The guide vane retention system of claim 2 , wherein the loop termination location is in contact with the guide vane in a fully assembled condition.

4. The guide vane retention system of claim 1 , wherein the first leg and the second leg diverge from each other in a direction from the looped end toward the respective free ends.

5. The guide vane retention system of claim 1 , wherein the clip is formed from sheet metal.

6. The guide vane retention system of claim 1 , wherein the guide vane is a fan exit stator.

7. The guide vane retention system of claim 1 , wherein the first leg includes a bent edge region.

8. A clip for a guide vane retention system, the clip comprising:
a looped end;
a first leg extending away from the looped end to a first free end, the first leg defining a hole;
a second leg extending away from the looped end to a second free end, the first leg and the second leg diverging from each other in a direction from the looped end toward the free ends, the first leg and the second leg insertable within a slot defined by a guide vane; and
a rubber potting applied between the first leg and the second leg after the clip is inserted into the slot and within the hole of the first leg to provide a rubber rivet.

9. The clip of claim 8 , wherein the clip is formed from sheet metal.

10. The clip of claim 8 , wherein the first leg includes a bent edge region.

11. A method of retaining a guide vane of a gas turbine engine comprising:
disposing the guide vane between an inner diameter shroud and an outer diameter shroud;
rotating the guide vane to position a radially outer end of the guide vane through an aperture of the outer diameter shroud;
compressing two legs of a clip toward each other;
inserting the two legs of the clip through a slot defined by the guide vane proximate the radially outer end of the guide vane, the slot positioned radially outboard of the outer diameter shroud;
releasing the two legs of the clip; and
applying rubber between the two legs and within a hole of the first leg to define a rivet after the clip is inserted within the slot in order to prevent compression of the two legs.

12. The method of claim 11 , further comprising operatively coupling a radially inner end of the guide vane to the inner diameter shroud.

13. The method of claim 11 , wherein the two legs extend from a loop termination location of a looped end of the clip, wherein inserting the two legs ofthe clip through the slot comprises inserting the two legs until the loop termination location ofthe clip contacts the guide vane.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Barainca Brian

Classifications

• F01D9/042 Primary

  fixing blades to stators (fixing stator-rings in the casing or to each other F01D25/246) · CPC title

• F05D2300/43

  Synthetic polymers, e.g. plastics; Rubber · CPC title

• F05D2240/12

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

• F05D2230/64

  using positioning or alignment devices for aligning or centring, e.g. pins · CPC title

• F05D2260/38

  by a spring, i.e. spring loaded or biased towards a certain position · CPC title