Abstract: Methods and apparatus are provided for verifying proper operation of a gas turbine engine output torque sensor using a speed sensor, and using the speed sensor as a backup torque sensor. Gas turbine engine output torque is sensed using a reference torque sensor, and gas turbine engine output shaft rotational speed is sensed. Gas turbine engine output torque is calculated from the sensed gas turbine engine output shaft rotational speed. The sensed gas turbine engine output torque is compared to the calculated gas turbine engine output torque to determine if the reference torque sensor is operating properly. The gas turbine engine is controlled at least partially based on the sensed gas turbine engine output torque if the reference torque sensor is determined to be operating properly, and is controlled at least partially based on the calculated output torque if the reference torque sensor is determined to be not operating properly.

Abstract: A rotor assembly or other rotating device having a stack of laminations or laminates that are chemically bonded together. Chemical bond of the laminates may have a strength that approaches the strength of the material of metal laminates. Chemical bonds may be effective in holding the laminates at temperatures when subject to rigorous mechanical operations such as high rotation speed and vibration.

Abstract: A rotor support includes a first ring disposed around a first axis, a second ring disposed around the first axis downstream from the first ring, and a plurality of beams extending between the first and the second rings. Each beam is configured to provide an axial stiffness, when an axial force is exerted on the first ring, and a radial stiffness, when a radial force is exerted on the first ring. Each beam has a height extending parallel to a second axis and a width extending parallel to a third axis. The beams are distributed around the first ring to provide a substantially uniform circumferential axial stiffness around the rotor support, and the height of each beam is greater than the width of each beam. Damping can be provided by the placement of a damper between the rotor support and the support housing.

Abstract: Methods and apparatus are provided for verifying proper operation of a gas turbine engine output torque sensor using a speed sensor, and using the speed sensor as a backup torque sensor. Gas turbine engine output torque is sensed using a reference torque sensor, and gas turbine engine output shaft rotational speed is sensed. Gas turbine engine output torque is calculated from the sensed gas turbine engine output shaft rotational speed. The sensed gas turbine engine output torque is compared to the calculated gas turbine engine output torque to determine if the reference torque sensor is operating properly. The gas turbine engine is controlled at least partially based on the sensed gas turbine engine output torque if the reference torque sensor is determined to be operating properly, and is controlled at least partially based on the calculated output torque if the reference torque sensor is determined to be not operating properly.

Abstract: A rotor mount assembly for an electrical machine, such as a high speed aerospace generator, comprises a spring having a simple annular structure together with an oil squeeze film damper (SFD). The spring is engineered to move the rotor critical speeds outside of the extremes of the operating speed range and the SFD damps out the rotor responses as the speed passes through these points.

Abstract: Centering rings may be used to modify the combined resonance of a rotor and its support assembly to migrate the rotor critical speeds such that they can be engineered out of the rotor operating speed range. The centering rings of the present invention may be useful for any rotating electrical machinery, especially high speed aerospace applications, such as generators and starter-generators.

Abstract: Rings having holes with a centerline offset from the centerline of the outer diameter, or other diameter piloting feature of the ring (i.e., non-concentric rings) may be used to align rotating components within their static components. Two non-concentric rings may be used to support a bearing that contains a shaft there through to allow for maximum offsets between a desired centerline of the rotating component and an actual, assembled centerline of the rotating component. Adjustment of the rotor centerline relative to the static structure centerline may be obtained without disassembly of the rotor assembly or static structure assembly.

Abstract: The present invention provides apparatus and methods for balancing stacked components of rotating machinery, such as in a gas turbine engine. Unlike conventional processes and devices for balancing stacked components, the present invention may use a single non-parallel spacer for obtaining an acceptable and repeatable component group balance. The non-parallel spacer may be used to compensate for rotor bow and the associated imbalance of the rotor group. By indexing a spacer with non-parallel faces, situated terminally at the end of the stack adjacent to the nut, rotor balance can be achieved without disassembly of the rotor group and clocking of its individual components. A spacer may also be disposed at any one or more of the interfaces between various components in the stack.

Abstract: The present invention provides for outer diameter piloting of a nut that secures stacked components to a tie-shaft or other threaded components used to axially secure one or more rotating components. Unlike conventional inner diameter piloting methods, machining a precise inner diameter of the nut is not needed. The nut face of the present invention has superior perpendicularity with the tie-shaft and the radial pilot is not lost when the nut is loaded. Outer diameter nut piloting may be conducted by using a nut alone or a nut in combination with a nut spacer, a pocket in the rotor, a nut spacer seat, or a nut piloting insert.

Abstract: A rotor support includes a first ring disposed around a first axis, a second ring disposed around the first axis downstream from the first ring, and a plurality of beams extending between the first and the second rings. Each beam is configured to provide an axial stiffness, when an axial force is exerted on the first ring, and a radial stiffness, when a radial force is exerted on the first ring. Each beam has a height extending parallel to a second axis and a width extending parallel to a third axis. The beams are distributed around the first ring to provide a substantially uniform circumferential axial stiffness around the rotor support, and the height of each beam is greater than the width of each beam. Damping can be provided by the placement of a damper between the rotor support and the support housing.

Abstract: A rotor mount assembly for an electrical machine, such as a high speed aerospace generator, comprises a spring having a simple annular structure together with an oil squeeze film damper (SFD). The spring is engineered to move the rotor critical speeds outside of the extremes of the operating speed range and the SFD damps out the rotor responses as the speed passes through these points.

Abstract: Centering rings may be used to modify the combined resonance of a rotor and its support assembly to migrate the rotor critical speeds such that they can be engineered out of the rotor operating speed range. The centering rings of the present invention may be useful for any rotating electrical machinery, especially high speed aerospace applications, such as generators and starter-generators.

Abstract: A rotor assembly or other rotating device having a stack of laminations or laminates that are chemically bonded together. Chemical bond of the laminates may have a strength that approaches the strength of the material of metal laminates. Chemical bonds may be effective in holding the laminates at temperatures when subject to rigorous mechanical operations such as high rotation speed and vibration.

Abstract: A face seal assembly with internal weep drain is disclosed for use in a turbo-machine, such as a gas turbine engine, for deterring passage of fluids, such as oil and the like, across an interface dividing the turbo-machine into two distinct regions, the interface being defined between one surface of a seal element and a second surface mounted on a rotating shaft. The face seal assembly includes a housing having a first fixed member including a drain opening, a second member supported for axial motion relative to the first member, and a biasing element positioned between the first and second members for urging the second member toward the interface. The second member supports the seal element and defines with the first member a channel through which the fluids that migrate past the interface are directed into the housing and out through the drain opening.

Abstract: A face seal assembly with internal weep drain is disclosed for use in a turbo-machine, such as a gas turbine engine, for deterring passage of fluids, such as oil and the like, across an interface dividing the turbo-machine into two distinct regions, the interface being defined between one surface of a seal element and a second surface mounted on a rotating shaft. The face seal assembly includes a housing having a first fixed member including a drain opening, a second member supported for axial motion relative to the first member, and a biasing element positioned between the first and second members for urging the second member toward the interface. The second member supports the seal element and defines with the first member a channel through which the fluids that migrate past the interface are directed into the housing and out through the drain opening.

Abstract: A turbine assembly comprising a first rotatable component having a first lip with a first axial facing surface and a second rotatable component having a second lip with a second axial facing surface. The components are held together by an axial load so that the first and second axial surfaces are in frictional contact across a radial plane whereby torque is transmitted between the components. A pilot ring mounted either above or below the radial contact plane maintains the radial position of the two components.

Abstract: A gas turbine engine having a compressor rotor and turbine rotor in back-to-back relation and annular groove therebetween. A nonrotating seal is disposed in the groove. A dual pilot ring is disposed at the radial inner end of the groove. The dual pilot ring includes an inner annular ring and an outer annular ring radially spaced apart to define a clearance gap. The inner ring is mounted to radially facing piloting surfaces on both the compressor and turbine rotors and maintains concentricity between the two rotors as they grow at different thermal rates. The outer annular ring transfers axial loads between the rotors.