Rotor blade assembly tool for gas turbine engine

Patent metadata

Field	Value
Publication number	US-9328621-B2
Application number	US-201414159802-A
Country	US
Kind code	B2
Filing date	Jan 21, 2014
Priority date	Oct 28, 2011
Publication date	May 3, 2016
Grant date	May 3, 2016

Abstract

A rotor blade assembly tool for coupling a plurality of circumferentially spaced rotor blades to a rotor disc of a turbine rotor assembly, includes a base ring with an array of circumferentially spaced resilient fingers axially extending from the base ring. The resilient fingers are configured each to radially abut a blade seal, damper or other engine component against radially inner facing surfaces of platforms of the respective blades when the blades are being seated onto the disc during an assembly procedure.

First claim

The invention claimed is:

1. A method of assembling a rotor assembly for a gas turbine engine, the method comprising:
providing a plurality of rotor blades each including a root and a platform, the platform extending from the blade in opposed circumferential directions;
providing a rotor disc including a plurality of slots spaced circumferentially about the disc;
providing a plurality of blade seal members for sealing circumferential gaps between adjacent said platforms when the rotor blades are installed on the rotor disc;
partially inserting the roots of the rotor blades in the respective slots of the rotor disc;
placing the respective seal members radially between the platforms and the rotor disc, each seal member being positioned circumferentially between adjacent said rotor blades using a tool having an array of circumferentially spaced resilient fingers radially abutting the respective seal members against radially inner facing surfaces of the platforms;
seating the rotor blades in the respective slots of the rotor disc substantially simultaneously with attachment of the respective seal members to the platforms, by a relative movement between the rotor disc and the tool having the rotor blades with the attached seal members, thereby forming the rotor assembly; and then
moving the tool away from the rotor assembly to withdraw the respective resilient fingers from a radial clearance between the rotor disc and respective lands of the platforms with the blade seal members remaining in respective platform cavities radially between the platforms and the disc and circumferentially between adjacent blades.

2. The method as defined in claim 1 further comprising circumferentially aligning the fingers of the tool with said respective lands of the platforms when using the tool to attach the seal members to the platforms such that the fingers extend through said radial clearance formed when the rotor blades are fully seated in the respective slots of the rotor disc.

3. A method of assembling a rotor assembly for a gas turbine engine, the method comprising:
providing a plurality of rotor blades each including a root and a platform, the platform extending from the blade in opposed circumferential directions;
providing a rotor disc including a plurality of slots spaced circumferentially about the disc;
positioning and removeably securing the respective rotor blades to a tool in a blade array in which the rotor blades are circumferentially spaced one from another to correspond with a blade distribution pattern of the rotor assembly;
positioning the tool with the rotor blades held thereon to circumferentially align the roots of the rotor blades with the respective slots of the rotor disc;
seating the rotor blades in the respective slots of the rotor disc substantially simultaneously, by a relative movement between the rotor disc and the tool holding the rotor blades, thereby forming the rotor assembly; and then
withdrawing the tool from the rotor assembly.

4. The method as defined in claim 3 further comprising:
providing a plurality of blade seal or damper members; and
between the rotor blade positioning and the seating steps, attaching the respective blade seal or damper members to the platforms, by positioning each blade seal or damper member circumferentially between adjacent said rotor blades using an array of circumferentially spaced resilient fingers of the tool to radially abut the respective blade seal or damper members against radially inner facing surfaces of the platforms such that the blade seal or damper members are held together with the respective platforms when the rotor blades are being seated in the slots of the rotor disc.

5. The method as defined in claim 4 wherein the resilient fingers are withdrawn through a radial clearance between the rotor disc and respective lands of the platforms when the tool is withdrawn from the rotor assembly with the blade seal or damper members remaining in respective platform cavities radially between the platforms and the disc, and circumferentially between adjacent rotor blades.

6. The method as defined in claim 5 wherein the resilient fingers are aligned with respective said lands of the platforms when the rotor blades are positioned and removably secured to the tool in said array.

Assignees

• Pratt & Whitney Canada

Inventors

• Lecuyer Joseph Daniel
• Chatelois Bruno

Classifications

• Y10T29/53913

  Aligner or center · CPC title

• Y10T29/49899

  by multiple cooperating aligning means · CPC title

• Y10T29/53983

  Work-supported apparatus · CPC title

• F05D2230/60

  Assembly methods · CPC title

• B23P19/042

  specially adapted for combustion engines (shape of casings adapted to facilitate fitting or dismantling of engine parts for combustion engines F02F7/0046) · CPC title