Apparatus for circumferential separation of turbine blades

Patent metadata

Field	Value
Publication number	US-11092039-B2
Application number	US-201715723254-A
Country	US
Kind code	B2
Filing date	Oct 3, 2017
Priority date	Oct 27, 2016
Publication date	Aug 17, 2021
Grant date	Aug 17, 2021

Abstract

Embodiments of the present disclosure can provide an apparatus for circumferentially separating turbine blades. An apparatus according to the present disclosure may include: a length-adjustable elongate member having opposing first and second ends; a first clasp coupled to the first end of the length-adjustable elongate member, the first clasp shaped to at least partially engage an airfoil profile of a first turbine blade positioned circumferentially adjacent to a dovetail slot, relative to a centerline axis of the turbomachine; and a second clasp coupled to the second end of the length-adjustable elongate member, the second clasp shaped to at least partially engage an airfoil profile of a second turbine blade circumferentially positioned adjacent to the dovetail slot, the first and second turbine blades being circumferentially adjacent to the dovetail slot at opposing circumferential ends thereof.

First claim

What is claimed is:

1. An apparatus for circumferentially separating turbine blades, the apparatus comprising:
a length-adjustable elongate member having opposing first and second ends;
a first clasp rotatably coupled to the first end of the length-adjustable elongate member so as to rotate about the first end of the length-adjustable elongate member, the first clasp shaped to at least partially engage an airfoil profile of a first turbine blade positioned circumferentially adjacent to a dovetail slot, relative to a centerline axis of a turbomachine including the first turbine blade; and
a second clasp rotatably coupled to the second end of the length-adjustable elongate member so as to rotate about the second end of the length-adjustable elongate member, the second clasp shaped to at least partially engage an airfoil profile of a second turbine blade of the turbomachine circumferentially positioned adjacent to the dovetail slot, the first and second turbine blades being circumferentially adjacent to the dovetail slot at opposing circumferential ends thereof,
wherein one of the first clasp or the second clasp includes an axially extendable member that is a coupling component configured to secure the apparatus to a respective one of the first turbine blade or the second turbine blade, each of the first and second clasps further being shaped to at least partially engage its respective turbine blade while the other of the first and second clasps at least partially engages its respective turbine blade, whereby separating the first and second turbine blades circumferentially is enabled by the first clasp being coupled to the first turbine blade while the second clasp is coupled to the second turbine blade;
wherein the axially extendable member is also configured to modify a shaft of the respective one of the first clasp or the second clasp.

2. The apparatus of claim 1 , wherein the length-adjustable elongate member includes a turnbuckle configured to adjust a displacement of the length-adjustable elongate member between the opposing first and second ends thereof, and wherein one of the first clasp and the second clasp is shaped to include at least one of a concave profile, a convex profile, a leading edge profile, or a trailing edge profile.

3. The apparatus of claim 1 , wherein the axially extendable member is connected to the respective one of the first clasp or the second clasp by a length-adjustable coupler attached to the respective one of the first clasp or the second clasp.

4. The apparatus of claim 1 , wherein the first clasp and the second clasp are shaped to engage portions of the first turbine blade and the second turbine blade, respectively, radially proximal to a shroud portion thereof.

5. The apparatus of claim 1 , wherein one of the first clasp or the second clasp includes a radially-extending member for engaging a sidewall of the first or second turbine blade.

6. The apparatus of claim 5 , wherein the radially-extending member includes a radial endwall shaped to engage a shroud portion of the first or second turbine blade.

7. The apparatus of claim 5 , wherein the radially-extending member includes a polymerous material.

Assignees

• Gen Electric

Inventors

• Kolvick Sandra Beverly
• Bruce Kevin Leon
• Mastroianni Antoine
• Werner Danielle
• Wojtowicz Hubert Karol

Classifications

• F01D5/30 Primary

  Fixing blades to rotors; Blade roots {; Blade spacers} · CPC title

• F01D5/225

  by shrouding · CPC title

• F05D2260/30

  Retaining components in desired mutual position · CPC title

• B25B5/003

  Combinations of clamps · CPC title

• F01D25/285 Primary

  Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures · CPC title