Gas turbine engine module assembly
AssigneeAllied-Signal Inc.
InventorDavid E. Wilcox
Life of this patent
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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.
Claims8
A method for handling a modular subassembly of a gas turbine engine without disturbing a separate shaft extending through the subassembly, wherein the subassembly includes a centrally located set of rotatable disks surrounding the shaft and stationary housing structure arranged in circumferentially surrounding and axially interdigitated relation to the rotatable disks, comprising the steps of:
- inserting a tubular tool axially through the subassembly in a radial space between the shaft and the set of rotatable disks while retaining an axially outer portion of the tubular tool in an accessible location;
- securing an inner end of the tubular tool to the innermost one of said set of rotatable disks;
- engaging the tubular tool with an outer end of said set of rotatable disks to lock said tubular tool to said set of rotatable disks;
- securing the locked tubular member and set of rotatable disks to said stationary structure;
- and
- unitarily moving the modular subassembly relative to the shaft by operably applying axial shifting force to the accessible outer portion of the tubular tool.
Dependencies are inferred from the claim text.