An assembly for a turbine engine extending along an axis, includes a stator, a low-pressure compressor shaft, a low-pressure compressor comprising a rotor comprising a drum rotatably coupled to the shaft of the low-pressure compressor, and a fan comprising a disk rotatably coupled to the shaft of the low-pressure compressor. The drum has a radially internal part rotatably coupled to the shaft of the low-pressure compressor and a radially external part fixed to the radially internal part by means of detachable fixing means. A first axial retention means is configured to axially and detachably retain the disk of the fan relative to the shaft of the low-pressure compressor. A second axial retention means is configured to axially and detachably retain the radially internal part of the drum relative to the shaft of the low-pressure compressor.

A disk assembly may include: a first disk engaged with a compressor section of a gas turbine; a second disk engaged with a turbine section of the gas turbine; and a third disk disposed between the first and second disks, and transferring torque applied to the second disk to the first disk. The third disk has a plurality of legs formed on an inner circumferential surface thereof, the plurality of legs being in contact with an outer circumferential surface of a tie bolt of the gas turbine.

A turbine and a turbine-generator device for use in electricity generation. The turbine has a universal design and so may be relatively easily modified for use in connection with generators having a rated power output in the range of 50 KW to 5 MW. Such modifications are achieved, in part, through use of a modular turbine cartridge built up of discrete rotor and stator plates sized for the desired application with turbine brush seals chosen to accommodate radial rotor movements from the supported generator. The cartridge may be installed and removed from the turbine relatively easily for maintenance or rebuilding. The rotor housing is designed to be relatively easily machined to dimensions that meet desired operating parameters.

A method of disassembling a rotor module of a gas turbine engine. The gas turbine engine having a rotor output shaft. The rotor module having a centre-bolt, a sleeve, at least one rotor stage, at least one stator stage, a casing and an axis. The method having the steps: attaching a fixture to the at least one rotor stage, attaching the fixture to the casing, detaching the centre-bolt from the at least one rotor stage, detaching the sleeve from the output shaft, attaching the fixture to the sleeve, and removing the rotor module and fixture from the rotor output shaft. There is also presented a method of assembling the rotor module to the gas turbine engine and the apparatus used for disassembly and assembly.

According to an aspect, a system includes a memory system configured to store a plurality of instructions and a processing system. The processing system is configured to communicate with the memory system and execute the instructions that result in determining an initial torque applied to a component stack, determining an assembly torque and an angle of turn applied to the component stack after the initial torque is applied, and determining a friction value associated with the component stack. Execution of the instructions further result in determining a stack load of the component stack based on the friction value, the assembly torque, and the angle of turn, and outputting an indicator of the stack load.

A gas turbine engine rotor assembly comprises a torque tube, turbine stage and stiffening mass. The torque tube comprises a shaft extending from a forward location to an aft end, and a shaft fastening flange disposed at the aft end. The turbine stage comprises a disc, a disc adapter extending forward from the disc, and a disc fastening flange extending from the disc adapter and couplable to the shaft fastening flange at an interface. The stiffening mass is positioned proximate the interface to reduce operational stress in the torque tube. A method of reducing operational stress in a rotor assembly comprises de-stacking a rotor stack, separating a first stage rotor disc adapter from a torque tube, attaching a stiffening mass to an inner diameter of one or both of the disc adapter and the torque tube, attaching the disc adapter to the torque tube, and re-stacking the rotor stack.

A safety apparatus for containing a release of energy from a tension stud of a rotor assembly, the safety apparatus including a containment member configured to pivot about a pivot location, the containment member including a retaining arm located on a first side of the pivot location and a catch located on a second side of the pivot location, wherein the containment member is movable about the pivot location to a first position in which the catch is engaged with a lip of a disc of the rotor assembly to position the retaining arm in a containment position.

A rotor assembly includes a plurality of wheels and a tie bolt that extends through the plurality of wheels and applies a compressive force to the plurality of wheels. The tie bolt includes a first segment with a first stiffness and a second segment with a second stiffness to allow for thermal growth of the plurality of wheels.

A rotor assembly comprises a rotor having annular flange including a plurality of protrusions axisymmetrically disposed about the annular flange, each protrusion having a mounting aperture for selectively receiving a balancing feature, and a plurality of slots axisymmetrically disposed about the circumference of the annular flange between adjacent protrusions. Each slot has a pair of converging flat portions extending axially inwardly from an adjacent protrusion end, an inner flat portion at an inner end of each slot, and a pair of curved portions respectively joining each converging flat portion to the inner flat portion in each slot. Each slot has a depth at least as great as an adjacent mounting aperture depth extending normally from the adjacent protrusion end to a far end of the corresponding mounting aperture.

A gas turbine engine, has: a shaft rotatable about a central axis and engaged at an end thereof to a rotatable load via a spline; a reference tube circumferentially extending around the shaft, the reference tube secured at a first end to the shaft for rotation therewith and a second end free relative to the shaft for measuring a deformation of the shaft, the reference tube defining at least one tube aperture therethrough; an oil nozzle fluidly connected to a source of lubricant, the oil nozzle defining an exit flow axis intersecting the at least one tube aperture for injecting oil through the reference tube, the shaft defining at least one shaft aperture extending therethrough, the oil nozzle aligned with the spline via the at least one tube aperture and the at least one shaft aperture.