Gas turbine engine module assembly

• US 5,220,784 A
• Filed: 06/27/1991
• Issued: 06/22/1993
• Est. Priority Date: 06/27/1991
• Status: Expired due to Term

• Current Assignee: Alliedsignal Inc.
• Original Assignee: Alliedsignal Inc.
• Inventors: Wilcox, David E.
• Primary Examiner(s): Bertsch, Richard A.
• Assistant Examiner(s): RICHMAN, HOWARD
• Application Number:
  US07/722,065
• Time in Patent Office: 726 Days
• Field of Search: 60/39.75, 60/39.31, 60/39.33, 60/39.161, 29/889.2, 416/198 A
• US Class Current: 60/796
• CPC Class Codes: B63H 21/16 relating to gas turbines
• CPC Class Codes: F01D 25/285 Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
• CPC Class Codes: F01D 5/06 Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections F01D5/022, F01D5/023 take precedence
• CPC Class Codes: F05D 2230/60 Assembly methods
• CPC Class Codes: F05D 2230/70 Disassembly methods

Abstract

A gas turbine engine compressor module subassembly construction and associated assembly method and tooling includes a threaded inner bore on the first stage compressor adapted to receive a tubular tool that slips axially between the compressor bores and the engine central shaft. Securement of the accessible tooling to the module'"'"'s stationary structure permits assembly and handling of the module independently of the engine shaft.

Claims

1. A gas turbine engine comprising:

a stationary housing;

a central rotary shaft rotatably secured to said housing at a forward location along the axial length of said shaft, said shaft having a radially outwardly extending face at said forward location;

an axially spaced set of stationary vanes secured to said housing and extending radially inwardly into a fluid flow path extending axially along said shaft in radially surrounding relation thereto;

a plurality of axially paced rotors disposed in torque transmitting interengagement, said rotors having central bores and blades extending radially outwardly into said flow path in interdigitated relation to said vanes;

the forwardmost of said plurality of rotors having a forward face in axial engagement with said face of the shaft, said central bore of said forwardmost rotor being of a selected diameter greater than the outer diameter of said shaft, said central bores of the remainder of said plurality of rotors having diameters greater than said selected diameter to define a radial space between said shaft and said remainder of said plurality of rotors, said radial space adapted to receive tubularly shaped assembly tooling, said forwardmost rotor having an inner section disposed radially inwardly of said central bores of said remainder of rotors, said inner section being configured to complementally receive and intersecure with the end of the tubularly shaped assembly tooling inserted through said radial space.

2. A gas turbine engine as set forth in claim 1, wherein each of said plurality of motors has radial end face splines in torque transmitting engagement with the end face splines of the adjacent rotor.

3. A gas turbine engine as set forth in claim 2, wherein said plurality of rotors comprises a plurality of compressor rotors, said engine further comprising a turbine rotor disposed axially rearwardly of said compressor rotors and mounted in torque transmitting engagement therewith.

4. A gas turbine engine as set forth in claim 2, wherein said inner section of the forwardmost rotor has internal threads thereon adapted to receive an externally threaded end of the tubularly shaped assembly tooling inserted through said radial space.

5. A gas turbine engine module and transport tooling therefor comprising:

radially outer stationary housing structure;

axially spaced sets of stationary vanes extending radially inwardly from said housing structure into an axially extending fluid flow path;

a plurality of compressor wheels having blades extending radially outwardly into said flow path in interdigitated relation to said vanes, said wheels being in torque transmitting interengagement, the forwardmost one of said said wheel having a threaded bore, the remainder of said wheel having central bores of larger diameter than said threaded central bore;

a tubular member of greater axial length than the total axial length of said plurality of wheels, and an outer diameter smaller than the central bores of the remainder of said wheels, said tubular member having an externally threaded end in engagement with said threaded central bore of the forwardmost one of said wheels; and

means carried with said tubular member for axially securing the rearwardmost one of said plurality of wheels with said tubular member and with said stationary housing structure.

6. A unitary module including a gas turbine engine compressor subassembly and transport tooling, said unitary module adapted to be assembled and disassembled as a unit upon an axially extending central shaft, said unitary module comprising:

radially outer stationary housing structure;

axially spaced set of stationary vanes extending radially inwardly into an axially extending fluid flow path;

a plurality of compressor disks having blades extending radially outwardly into said flow path in interdigitated relation to said vanes, said disks being in torque transmitting interengagement, the forwardmost one of said disks having a threaded central bore, the remainder of said disks having central bores of larger diameter than said threaded central bore;

assembly tooling including a hollow tubular tool received through said central bores of the remainder of said disks, the inner diameter of said tool being greater than the maximum diameter of the engine shaft, a forward end of said tool being releasably intersecured to said threaded central bore;

means for securing a rearward end of said tool to said stationary housing; and

a midsection ring secured to the outer surface of said tool and extending radially outward to a diameter greater than said central bore of the rearwardmost one of said disks, said midsection ring being in axial contact with said rearwardmost compressor disk upon securement of said forward end of the tool to said threaded central bore.