Seal-plate anti-rotation in a stage of a gas turbine engine

Patent metadata

Field	Value
Publication number	US-2017191370-A1
Application number	US-201615258721-A
Country	US
Kind code	A1
Filing date	Sep 7, 2016
Priority date	Sep 21, 2015
Publication date	Jul 6, 2017
Grant date	—

Abstract

A turbine stage assembly includes a disc carrying a cascade of blades and an annular seal-plate that is secured to the disc by a first connection. One or more of the blades include a root portion configured to be received in a complementarily shaped radially extending slot in the disc such that a face of the root portion faces the plate. A terminal portion of the root portion is cut away adjacent the face to present an open space between a radially inner wall of the slot and a wall of the cutaway root portion. A first part of a second connector extends radially inwardly from the wall of the cutaway root portion. The first part of the second connector is configured to engage with a complementing second part of the second connector provided on the seal-plate.

First claim

1 . A turbine stage assembly, the assembly comprising; a disc carrying a cascade of blades and an annular seal-plate, the seal-plate being secured to the disc by a first connection means, one or more of the blades comprising; a root portion configured to be received in a complementarily shaped radially extending slot in the disc such that a face of the root portion faces the plate; a terminal portion of the root portion being cut away adjacent the face to present an open space between a radially inner wall of the slot and a wall of the cutaway root portion and a first part of a second connector means extending radially inwardly from the wall of the cutaway root portion, the first part of the second connector means configured to engage with a complementing second part of the second connector means provided on the seal-plate.

2 . A turbine stage assembly as claimed in claim 1 wherein the first part of the second connector portion comprises a pair of tangs defining a slot into which a protrusion forming the second part of the second connector can be received.

3 . A turbine stage assembly as claimed in claim 2 wherein the tangs of the first part are configured to follow a line of the recess into which the blade is received in the disc and define a straight sided slot therein.

4 . A turbine stage assembly as claimed in claim 1 wherein the first part of the second connector comprises a single shaped piece defining an open sided recess into which the second part can be received.

5 . A turbine stage assembly as claimed in claim 4 wherein the open sided recess has an arched or C shape.

6 . A turbine stage assembly as claimed in claim 4 wherein the open sided recess is defined by three walls of a rectangle, or three walls of a trapezoid.

7 . A turbine stage assembly as claimed in claim 1 wherein the portion that is cut away from the root portion is cuboid resulting in a face on the wall of the cutaway root portion facing and in parallel alignment with the axis of the radial slot.

8 . A turbine stage assembly as claimed in claim 1 wherein the shape of the portion cut away from the root portion is configured to result in an inclined and/or curved face on the wall of the cutaway root portion.

9 . A turbine stage assembly as claimed in claim 1 wherein the wall of the cutaway portion includes an orifice which opens into a cooling passage inside the body of the blade for delivery of coolant to the cooling passage.

10 . A turbine stage assembly as claimed in claim 1 wherein adjacent the cutaway portion, the root portion defines a wall of a duct, the wall of the duct providing, in use, a heat shield for the base of the radially extending slot into which the root portion is received.

11 . A turbine stage assembly as claimed in claim 10 wherein the duct is arranged to receive cooling air and is in fluid communication with cooling passages extending through the root portion and into the blade main body.

12 . A turbine stage assembly as claimed in claim 11 wherein an inlet to a cooling passage is arranged in the cutaway portion.

13 . A turbine stage assembly as claimed in claim 1 wherein the first part is integrally cast into the blade.

14 . A gas turbine engine comprising one or more turbine stage assemblies, the turbine stage assemblies having a configuration according to claim 1 .

Assignees

• Rolls Royce Plc

Inventors

• Dawson John
• Burford Peter C

Classifications

• F05D2230/239

  Inertia or friction welding · CPC title

• F05D2230/21

  by casting · CPC title

• F01D5/081

  Cooling fluid being directed on the side of the rotor disc or at the roots of the blades (F01D5/087 takes precedence) · CPC title

• F01D5/082

  on the side of the rotor disc · CPC title

• F01D5/3007

  of axial insertion type · CPC title