Rolls-royce Corporation

Rolls-royce North American Technologies Inc.

Stanford O Clemens

Michel Shawn Smallwood

Andrew D Copeland

Donald W Burns

Matthew Tyler Bouton

Doug Schwerin

Ray F Bowman

Melissa Hughes

Brian R Bennett

Randal L Renback

Kelby Hassenzahl

Alan B Cookerly

A multi-piece radial turbine rotor includes a hub, a plurality of turbine blades, and a flowpath ring that couples the turbine blades to the hub. The flowpath ring is coupled with each of the plurality of turbine blades and the hub to locate the flowpath ring radially between the hub and each of the plurality of turbine blades. The flowpath ring is formed to include a plurality of apertures spaced apart from one another about the flowpath ring and extending radially through the flowpath ring. Each of the plurality of apertures receives a corresponding one of the plurality of turbine blades therein. The hub is fixed to the flowpath ring by a friction weld joint and each of the plurality of turbine blades is fixed to the flowpath ring by a blade joint.

Solid-state welded multi-piece radial turbine with air cooled blades for gas turbine engines

A method of assembling a radial turbine rotor includes manufacturing turbine blades, a flowpath ring, and a hub. The method includes fixing the turbine blades circumferentially around the flowpath ring by a blade joint between the turbine blades and the flowpath ring to form a ring assembly. The method includes spinning the hub and moving the hub into engagement with the flowpath ring to locate the hub radially inwardly of the flowpath ring and to form a hub joint between the flowpath ring and the hub.

Method for assembling a radial turbine rotor by solid-state welding

A starter generator located within a sump region of a turbofan engine and coupled to an adapter shaft. The adapter shaft rotationally coupled to the high pressure shaft, forward of a high pressure shaft bearing, and secured by a spanner nut. The engine makes use of two pluralities of electrical conductors, the first extends through an electrical conduit defined by a forward strut extending from the sump region to the outward casing, the second extends axially away from the electric starter. Each of the first plurality of electrical conductors makes reversible contact with a respective one of the second plurality of electrical conductors via an elbow/pin connector, producing a tight turn in area of limited space.

Starter/generator

A magnetic squeeze film damper system comprises a bearing assembly having an outer race with a first outer surface and a first inner surface and a bearing located along the first inner surface. The system further comprises a squeeze film damper housing having a second outer surface and a second inner surface that is contiguous with the first outer surface. A channel having a forward end and an aft end is defined within the housing along the second inner surface, the channel bordered by the first outer surface. The system further includes a first seal gland located along the forward end of the channel and a second seal gland located along the aft end of the channel. Both seal glands comprise a reservoir for holding a magneto-rheological fluid, the reservoir encased in an elastomer. At least one electromagnet is arranged in close proximity to each of the seal glands.

Magnetic squeeze film damper system for a gas turbine engine

Systems and methods to control an amount of axial clearance within a clutch transmission system are disclosed. A propulsion system includes a clutch transmission system having clutch vibratory response clearance control logic configured to iteratively control the amount of axial clearance within the clutch transmission system so as to achieve a desired, e.g., consistent and/or limited, clutch vibratory response.

System and method for eliminating adverse clutch vibratory responses

The present invention provides in one embodiment of the present invention a surge margin power recuperation system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for recuperating power from surge margin bleed air. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

Gas turbine engine surge margin bleed power recuperation

The invention provides a lock mechanism and method for selectively coupling two concentric shafts rotatable about a common axis. The lock mechanism includes a locking ring assembly movable along an axis of rotation of two rotatable shafts between a locked position to transmit rotation between the two shafts and an unlocked position. The lock mechanism also includes a first locking portion extending radially from the locking ring assembly and circumferentially about the axis of rotation for engaging a first of the two shafts. The lock mechanism also includes a second locking portion extending radially from the locking ring assembly opposite the first locking portion and circumferentially about the axis of rotation for engaging a second of the two shafts. The lock mechanism also includes a third locking portion extending radially from the locking ring assembly opposite the first locking portion and circumferentially about the axis of rotation for engaging a second of the two shafts and spaced the second locking portion along the axis of rotation.

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Carmel, IN, United States of America

Stanford O Clemens