Gas turbine engine components and method of assembly

Patent metadata

Field	Value
Publication number	US-2016303693-A1
Application number	US-201615189573-A
Country	US
Kind code	A1
Filing date	Jun 22, 2016
Priority date	Sep 28, 2012
Publication date	Oct 20, 2016
Grant date	—

Abstract

An exemplary gas turbine engine component assembly includes, among other things, a case having a generally cylindrical outer surface. At least one synchronizing ring is received at least partially about the outer surface of the case. A plurality shims situated between an inner surface on the at least one synchronizing ring and the outer surface of the case at a plurality of shim locations are circumferentially spaced about the case outer surface. Each shim location includes at least one of the shims. A radial thickness of the shims at a first one of the shim locations is different than the radial thickness of the shims at a second one of the shim locations.

First claim

I claim:

1 . A method of assembling gas turbine engine components, comprising the steps of:
situating at least one synchronizing ring about a generally cylindrical case such that an inner surface of the synchronizing ring faces an outer surface of the case; determining an assembled shim thickness for each of a plurality of shim locations, respectively, between the inner surface of the synchronizing ring and the outer surface of the case for establishing a substantially equal spacing between an outer surface of the synchronizing ring and a reference location; and situating a number of shims corresponding to the determined assembled shim thickness at each of the shim locations, respectively.

2 . The method of claim 1 , comprising
positioning shims having an initial shim thickness at each of the plurality of shim locations, respectively; determining a measurement shim thickness to be placed at each of the shim locations based on the initial shim thicknesses, the measurement shim thickness being the same for all of the shim locations; positioning shims having the measurement shim thickness at each of the shim locations; determining a distance between the outer surface of the synchronizing ring and the reference location associated with the case near each of the shim locations with the uniform measurement shim thickness at each of the shim locations; and determine the assembled shim thickness for each of the shim locations from the determined distances, respectively.

3 . The method of claim 2 , comprising
determining two distances between the outer surface of the synchronizing ring and the reference location near each of the shim locations; determine an average of the two measured dimensions for each shim location; and use the determined average for each shim location for determining the corresponding assembled shim thicknesses.

4 . The method of claim 2 , wherein determining the measured dimension near each shim location comprises at least one of
determining a distance between an outer surface on the synchronizing ring and the outer surface of the case near each shim location, or determining a distance between the outer surface on the synchronizing ring and the inner surface on the synchronizing ring near each shim location.

5 . The method of claim 1 , wherein
establishing the assembled shim thickness at each of the shim locations establishes a distance between the outer surface of the synchronizing ring and a center of the case that is approximately equal at each of the shim locations.

6 . The method of claim 5 , wherein establishing the assembled shim thickness at each of the shim locations establishes a distance between the outer surface of the synchronizing ring and a center of the case that is approximately equal around an entire circumference of the synchronizing ring.

7 . The method of claim 1 , wherein the assembled shim thickness at a first one of the shim locations is different than the assembled shim thickness at a second one of the shim locations.

Assignees

• United Technologies Corp

Inventors

• Pickens John T

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F05D2230/60

  Assembly methods · CPC title

• F01D25/24

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• B23P15/04 Primary

  turbine or like blades from several pieces · CPC title