Rolls-royce North American Technologies Inc.

Rolls-royce Corporation

Brett Hartnagel

Brandon R Snyder

Ryan Charles Humes

Jonathan Acker

Eric William Engebretsen

Aaron Weishaar

Michael R Whitten

David C Farnum

Rex M Little

Trevor C Pfeil

A turbine assembly includes a bladed rotor mounted for rotation about an axis of the gas turbine engine, a case assembly, and a tip clearance system. The tip clearance system includes a tip clearance sensor located in an annular plenum defined between an inner case and an outer case included in the case assembly. The tip sensor is configured to monitor a tip clearance formed between the bladed rotor and the case assembly during operation of the gas turbine engine.

Turbine assembly with case-integrated cooled clearance measurement system

A turbine assembly includes a bladed rotor mounted for rotation about an axis of the gas turbine engine, a case assembly, and an actively-cooled tip clearance system. The tip clearance system includes a tip clearance sensor located radially outward of an inner case of the case assembly. The actively-cooled tip clearance system includes a sensor is configured to monitor a tip clearance formed between the bladed rotor and the case assembly during operation of the gas turbine engine.

Turbine assembly with spring biased clearance sensor mount

A gas turbine engine includes: an inlet guide vane; an inlet channel extending from a location downstream of the inlet guide vane to a stem manifold; and an outlet channel extending to an outlet port, the outlet port configured to dump anti-ice air overboard, wherein the inlet guide vane includes an anti-ice cavity in fluid communication with the inlet channel and the outlet channel such that anti-ice air, flowing from a downstream location within a core flow of the gas turbine, flows from the inlet channel, through the inlet guide vane, and to the outlet channel.

Anti-ice system for gas turbine engine and inlet guide vane

A turbine assembly includes a bladed rotor mounted for rotation about an axis of the gas turbine engine, a case assembly, and an internally-cooled tip clearance system. The internally-cooled tip clearance system includes a sensor is configured to monitor a tip clearance formed between the bladed rotor and the case assembly during operation of the gas turbine engine.

Turbine assembly with clearance sensor having integrated internal cooling

A gas turbine engine includes: a manifold arrangement; a plurality of inlet guide vanes located radially inward of the manifold arrangement, wherein each inlet guide vane of the plurality of guide vanes includes an anti-ice cavity for directing a flow of an anti-ice air; and a plurality of crossover ducts located radially inside the manifold arrangement, wherein each crossover duct of the plurality of crossover ducts provides fluid communication between two adjacent inlet guide vanes.

Manifold assembly and anti-ice system for gas turbine engine

An engine that may comprise a first rotatable shaft, a second rotatable shaft, and a turnbuckle shaft. The first shaft rotatable may be disposed about a centerline axis and have threads disposed thereon. The second shaft rotatable may be disposed about the centerline axis and have threads disposed thereon. The turnbuckle shaft may be axially disposed between the first and second shafts, rotatable about the centerline axis, and have threads disposed thereon for engaging the threads of the first and second shafts. The first and second shafts may be drawn together by a force acting on the threads of at least one of the first and second shafts created by a rotation of the turnbuckle shaft relative to the at least one of the first and second shafts. The turnbuckle shaft may rotationally connect the first shaft and second shaft.

Axially clamping rotating engine components

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.

Turbine engine rotor with flexibly coupled tie bolt

An anti-rotation device for a pair of threaded components includes a pair of ratchet interfaces and a spring element. A first ratchet interface and the spring element are movably disposed within a first threaded component, and a second ratchet interface is disposed at a mating end of a second threaded component. During relative rotation of the pair of threaded components, the ratchet interfaces engage, providing a resistance to the threaded components loosening that is greater than a resistance that the ratchet interfaces provide to the threaded components tightening. The anti-rotation device engages automatically upon relative rotation of the threaded components, and not as a separate step occurring after rotation. Additionally, the anti-rotation device may be especially useful in systems where various types of movement can cause the threaded components to loosen, and where visual access to the anti-rotation device is impeded.

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Brownsburg, IN, United States of America

Brett Hartnagel