Method of disassembly for a gas turbine engine

Patent · Tue Aug 11 04:00:00 EDT 1987

OSTI ID:5927498

Hetzer, F C; Miller, G W

A method is described of disassembling an axial flow gas turbine engine having a rotor shaft, a rotor blade assembly, an outer case, a bearing supported from the outer case which is adapted to engage an annular second shaft and to support only the rotor shaft and the annular second shaft, and an annular second shaft which is joined to the rotor blade assembly. The annular second shaft engages the bearing to support only the rotor blade assembly and the rotor shaft, and the annular second shaft is capable of movement in the axial direction with respect to the rotor shaft, and is coupled to the rotor shaft in the axial and circumferential directions. An improvement is described comprising the steps of: uncoupling the rotor shaft and the annular second shaft-rotor blade assembly; separating the rotor shaft and the rotor blade assembly by relative movement between the shafts in the axial direction to provide access to the interior of the engine; supporting the rotor blade assembly from the outer case through the annular second shaft after separating the second shaft and the rotor shaft to avoid relative radial movement between the outer case and the rotor blade assembly during disassembly.

• Assignee: United Technologies Corp., Hartford, CT
• Patent Number(s): US 4685286
• OSTI ID: 5927498
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
330103* -- Internal Combustion Engines-- Turbine
BEARINGS
ENGINES
FLUID FLOW
GAS FLOW
GAS TURBINE ENGINES
HEAT ENGINES
INTERNAL COMBUSTION ENGINES
MACHINE PARTS
MECHANICAL STRUCTURES
ROTORS
SEPARATION PROCESSES
SHAFTS
SUPPORTS
TURBINE BLADES