System and method to retain a turbine cover plate with a spanner nut

Patent metadata

Field	Value
Publication number	US-10718220-B2
Application number	US-201514922844-A
Country	US
Kind code	B2
Filing date	Oct 26, 2015
Priority date	Oct 26, 2015
Publication date	Jul 21, 2020
Grant date	Jul 21, 2020

Abstract

In accordance with some embodiments of the present disclosure, a gas turbine engine is presented. The engine has at least one turbine stage and each stage has a turbine disc concentric with the axis of the engine. The turbine disc has a turbine arm positioned axially from the disc and rigidly attached thereto. The drive arm is also concentric with the turbine axis and has an outer surface. The turbine stage also has a cover plate concentric with the turbine axis and covering at least a portion of the turbine disc. An arrangement of turbine blades are positioned around the periphery of the disc and are retained on the turbine disc at least partially by the cover plate. The system includes a spanner nut, and threads on a portion of the turbine drive arm. The spanner nut is threaded onto the turbine arm which applies an axial force on the cover plate, thereby retaining the cover plate.

First claim

I claim:

1. A turbine assembly, comprising:
a turbine disc having a central axis and a radially outer rim, said radially outer rim forming a radially inward facing surface;
a turbine drive arm axially extending from and coaxial with said turbine disc, said turbine drive arm having a threaded portion;
a spanner nut coaxial with the turbine disc and threaded on said turbine drive arm; and
a turbine cover plate having a first end proximate to said turbine drive arm and a second end proximate to said radially outer rim of said turbine disc, wherein said first end and said turbine disc define a free space therebetween having an axial distance;
wherein, at the axial distance, said spanner nut is in contact with said turbine cover plate proximate to said first end such that a force is transmitted from said first end through said turbine cover plate to said second end to thereby hold the second end in contact with said radially inward facing surface of said radially outer rim, wherein the axial distance can be reduced by increasing the force transmitted by the contact of said spanner nut with said turbine cover plate.

2. The turbine assembly of claim 1 wherein the radially outer rim comprises an arrangement of plural turbine blade inserts, the arrangement coaxial with the turbine disc, said second end of the turbine cover plate restricting axial movement of the plural turbine blade inserts.

3. The turbine assembly of claim 1 , wherein the radially outer rim comprises a plurality of turbine disc pilot tabs, wherein one or more of the plurality of turbine disc pilot tabs form the radially inward facing surface of the radially outer rim.

4. The turbine assembly of claim 1 , wherein the turbine cover plate comprises an axial stop extending radially inward from the first end and engaging the spanner nut.

5. The turbine assembly of claim 1 , further comprising a relative rotation locking device preventing relative rotation of the spanner nut with the turbine disc arm, wherein the relative rotation locking device is selected from the group consisting of locking plates, retaining rings, tangs, lugs and keys.

6. The turbine assembly of claim 5 , wherein the spanner nut further comprises a feature complementary of the relative rotation locking device wherein the feature is selected from the group consisting of a dimpled surface, a facet and a slot, and a scalloped surface.

7. In a gas turbine engine having a turbine disc having a central axis and a radially outer rim, said radially outer rim forming a radially inward facing surface, a turbine drive arm axially extending from and coaxial with said turbine disc, a spanner nut coaxial with the turbine disc, and a turbine cover plate having a first end and a second end, a method of retaining the turbine cover plate comprising:
threading the turbine drive arm of the turbine disc to produce a threaded turbine drive arm;
moving the turbine cover plate in an axial direction such that the threaded turbine drive arm is within an opening defined by the second end;
after the step of moving the turbine cover plate, continuing to move the turbine cover plate in the axial direction such that the threaded arm is within a second opening defined by the first end;
positioning the second end of the turbine cover plate proximate the radially outer rim of the turbine disc, wherein said positioning defines a free space between said turbine cover plate and said turbine disc having an axial distance;
applying a rotation to the spanner nut to thread the spanner nut onto the threaded turbine drive arm, wherein the rotation is coaxial with the axis; and
contacting, with the spanner nut and at the axial distance, the turbine cover plate to apply a force that is transmitted from the first end through the turbine cover plate to thereby hold the second end in contact with the radially inward facing surface of the radially outer rim, and wherein increasing the applied force can reduce the axial distance.

8. The method of claim 7 , wherein the radially outer rim further comprises a plurality of pilot tabs and wherein one or more of the plurality of pilot tabs form the radially inward facing surface of the radially outer rim.

9. The method of claim 7 , wherein the step of contacting, with the spanner nut, the turbine cover plate further comprises extending an axial stop radially inward from the first end of the turbine cover plate and contacting with, the spanner nut, the axial stop.

10. The method of claim 7 , wherein the force is predetermined and corresponds to the rotation of the spanner nut.

11. A turbine assembly, comprising:
a turbine disc having a central axis and a radially outer surface;
a turbine drive arm axially extending from and coaxial with said turbine disc said turbine drive arm having a threaded portion;
a spanner nut coaxial with the turbine disc and threaded on said turbine drive arm; and
a turbine cover plate having a first end proximate to said turbine drive arm and a second end proximate to said radially outer surface of said turbine disc, wherein said first end and said turbine disc define a free space therebetween having an axial distance;
wherein, at the axial distance, said spanner nut is in contact with said turbine cover plate proximate to said first end such that force is transmitted from said first end through said turbine cover plate to said second end in contact with the radially outer surface, wherein the axial distance can be reduced by increasing the force transmitted by the contact of said spanner nut with said turbine cover plate.

Assignees

• Rolls Royce Corp

Inventors

• Snyder Brandon R

Classifications

• Y02T50/60

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

• F05D2240/15

  Heat shield · CPC title

• F05D2260/31

  Retaining bolts or nuts · CPC title

• F01D5/3015 Primary

  with side plates · CPC title

• F01D5/082

  on the side of the rotor disc · CPC title