Lock plate for a bladed rotor arrangement

Patent metadata

Field	Value
Publication number	US-10760435-B2
Application number	US-201715457174-A
Country	US
Kind code	B2
Filing date	Mar 13, 2017
Priority date	Mar 16, 2016
Publication date	Sep 1, 2020
Grant date	Sep 1, 2020

Abstract

Described is a turbine arrangement of a gas turbine engine, the turbine comprising: a rotor comprising a disc which incorporates a plurality of circumferentially spaced turbine blades, each blade having an aerofoil extending for a platform and a root portion securing the blade to the disc, a lock plate located at an axial end of the root portion of the blade, the lock plate comprising: a plate body having an inward facing surface which is located adjacent the blade root and an outward facing surface, radially inner and outer edge portions, and first and second circumferential edges; a head located at the radially outer edge portion of the plate body; a foot portion located at the radially inner portion of the plate body; a projection extending from the outwardly facing surface away from the turbine blade root in use, the projection being located adjacent to the foot portion, wherein the foot portion and head portion are located within slots provided at least partially by the disc and turbine blade respectively.

First claim

The invention claimed is:

1. A turbine arrangement of a gas turbine engine, the turbine arrangement comprising:
a rotor comprising a disc which incorporates a plurality of circumferentially spaced turbine blades, each blade having an aerofoil extending from a platform and a root portion securing the blade to the disc,
a lock plate located at an axial end of the root portion of the blade, the lock plate comprising:
a plate body having an inward facing surface which is located adjacent the blade root and an outward facing surface, radially inner and outer edge portions, and first and second circumferential edges, the inward facing surface and the outward facing surface both extending from the radially inner portion to the radially outer edge portion;
a head portion located at the radially outer edge portion of the plate body and located within a head portion slot provided at least partially by the turbine blade;
a foot portion located at the radially inner portion of the plate body and within a foot portion slot provided at least partially by the disc; and,
a projection extending from the outward facing surface away from the turbine blade root in use, the projection being located closer to the foot portion than to the head portion, wherein:

the centre of gravity of the lock plate is axially spaced from the turbine blade root relative to the geometric centre of the lock plate or a pivot point defined by the head portion such that the lock plate moves away from the turbine blade root when centrifugally loaded.

2. A turbine arrangement as claimed in claim 1 , wherein the foot portion slot is provided by a first wall and a second wall, the foot portion slot being therebetween, and wherein the second wall is at least partially provided by a seal plate or a cover plate which is attached to the rotor.

3. A turbine arrangement as claimed in claim 2 , the projection is provided radially proximate to a radially outer periphery of the second wall.

4. A turbine arrangement as claimed in claim 3 , wherein the axial extent of the projection is greater than the second wall.

5. A turbine arrangement as claimed in claim 3 , wherein the radial separation of the projection and the radial periphery of the second wall is in the range of between 2 mm and 4 mm.

6. A turbine arrangement as claimed in any of claim 1 , wherein the head portion slot is provided in the radially inner face of a blade platform.

7. A turbine arrangement as claimed in claim 1 , wherein the head portion slot includes a pivot pad which radially opposes a pivot pad on the radial periphery of the lock plate head portion.

8. A turbine arrangement as claimed in claim 7 , wherein the head portion includes a plurality of pivot pads on a radially outer edge thereof.

9. A turbine arrangement as claimed in claim 8 , wherein radially outer edge of the lock plate includes a chamfer on either or both of the outward facing surface and the inward facing surface, the pivot pad being defined by the chamfer.

10. A turbine arrangement as claimed in claim 1 , wherein the projection is an elongate rib protruding from the outward facing surface.

11. A turbine arrangement as claimed in claim 10 , wherein the rib is circumferentially curved.

12. A turbine arrangement as claimed in claim 1 , wherein the foot portion includes a seal fin located in the foot portion slot and the projection is located radially outwards of the seal fin.

13. A turbine arrangement as claimed in claim 12 , wherein the seal fin includes a chordal inner edge.

14. A turbine arrangement as claimed in claim 12 , wherein the seal fin is axially thinner than the plate body.

15. A lock plate of a turbine blade rotor in a gas turbine engine, the lock plate being provided adjacent to and covering a turbine blade root, the lock place comprising:
a plate body having an inward facing surface which is located adjacent the blade root and an outward facing surface, radially inner and outer edge portions, and first and second circumferential edges, the inward facing surface and the outward facing surface both extending from the radially inner portion to the radially outer edge portion;
a head portion located at the radially outer edge portion of the plate body;
a foot portion located at the radially inner portion of the plate body;
a projection extending from the outward facing surface away from the turbine blade root in use, the projection being located closer to the foot portion than to the head portion, wherein:
the in use centre of gravity of the lock plate is axially spaced from the turbine blade root relative to the geometric centre of the lock plate or a pivot point defined by the head portion such that the lock plate moves away from the turbine blade root when centrifugally loaded.

Assignees

• Rolls Royce Plc

Inventors

• Dawson John
• Bhadresa Ram

Classifications

• F05D2260/36

  by a form fit connection, e.g. by interlocking · CPC title

• F01D5/3015 Primary

  with side plates · CPC title

• F05D2260/20

  Heat transfer, e.g. cooling · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F01D5/18

  Hollow blades, {i.e. blades with cooling or heating channels or cavities (structure of hollow blades in general F01D5/147)}; Heating, heat-insulating or cooling means on blades · CPC title