Rolls-royce North American Technologies Inc.

Rolls-royce Corporation

Ryan Charles Humes

Edward Claude Rice

Andrew J Eifert

Douglas David Dierksmeier

Paulo Bazan

Brett Hartnagel

Adrian Carl Sitler

Brandon R Snyder

Jack K Moody

David C Farnum

Jonathan Sands

Behram Kapadia

A rotor assembly includes a first rotor arranged circumferentially about a central axis. A second rotor is arranged circumferentially about the central axis and couples to the first rotor for rotation therewith. A balance weight is located in a space radially between the first rotor and the second rotor.

Rotor assembly for gas turbine engines with replaceable balance weight bands

A gas turbine engine comprises a turbine, a combustor fluidly coupled to the turbine, and a cooling air system. The turbine includes including a turbine rotor having a shaft mounted for rotation about an axis of the gas turbine engine and a set of turbine blades coupled to the turbine rotor for rotation therewith. The combustor includes an outer combustor case and an inner combustor case that cooperate to define a combustion chamber. The cooling air system is configured to cool the turbine using air form the combustion chamber of the combustor.

Gas turbine engine with combustor section mounted modulated compressor air cooling system

A vane adjustment assembly includes a plurality of vanes, an annular ring coupled to the vanes, and a ring adjustment plate. The adjustment plate includes a main plate portion arranged on the ring and including a first adjustment region defined between two walls and a first elongated opening formed through the first adjustment region, and an adjustment fastener removably arranged in the first adjustment region between the first and second walls and including an adjustment head and a fastening pin eccentrically coupled to the adjustment head and removably coupled to the annular ring. The adjustment fastener can be selectively arranged at rotational positions within the first adjustment region so as to selectively arrange the fastening pin at distinct circumferential positions relative to the first and second walls such that the main plate portion can be positioned at distinct circumferential positions.

Systems and methods for multi-dimensional variable vane stage rigging utilizing adjustable bracket plates

A rotor assembly includes a first rotor arranged circumferentially about a central axis. A second rotor is arranged circumferentially about the central axis and couples to the first rotor for rotation therewith. A balance weight located in a space radially between the first rotor and the second rotor.

Clocking balance weight rotor assembly for gas turbine engines

A rotor assembly includes a first rotor arranged circumferentially about a central axis. A second rotor is arranged circumferentially about the central axis and couples to the first rotor for rotation therewith. A balance weight assembly is configured to balance a weight distribution of the rotor assembly.

Rotor assembly for gas turbine engines with replaceable balance weight pins

A vane adjustment assembly includes a plurality of vanes, an annular ring coupled to the vanes, and a ring adjustment assembly. The ring adjustment assembly includes a base plate coupled to the ring and having a recess, a first collar removably arranged within the recess and having a cavity formed therein, a second collar removably arranged within the cavity, and a roller pin fixedly coupled to the second collar. The cavity is offset relative to the first collar and roller pin is offset relative to the second collar. The first collar can be selectively arranged at rotational positions within the recess and the second collar can be selectively arranged at rotational positions within the cavity such that the roller pin can be positioned at distinct positions each corresponding to a rotational position of the first collar and a rotational position of the second collar.

Systems and methods for multi-dimensional variable vane stage rigging

A vane adjustment assembly includes vanes, an annular ring coupled to the vanes, and a ring adjustment assembly. The adjustment assembly includes a base frame mounted on the ring and including a support body having a first cavity, a first collar removably arranged within the first cavity and having a second cavity formed therein, a second collar removably arranged within the second cavity, and a roller pin coupled to the second collar. The second cavity is offset relative to the first collar and the roller pin is offset relative to the second collar. The first and second collars can be selectively arranged at rotational positions within the first and second cavities such that the roller pin can be positioned at distinct roller pin positions each corresponding to a rotational position of the first collar and a rotational position of the second collar.

Systems and methods for multi-dimensional variable vane stage rigging utilizing coupling mechanisms

A vane adjustment assembly includes a plurality of vanes, an annular ring coupled to the vanes, and a ring adjustment assembly. The ring adjustment assembly includes a first inclined plate and a second inclined plate, the first inclined plate having an inclined surface facing a first inclined surface of the second inclined plate. A roller pin is coupled to a second inclined surface of the second inclined plate opposite the first inclined surface. The second inclined plate is adjustable in the circumferential direction such that the inclined surface of the first inclined plate and the first inclined surface of the second inclined plate slide against each other during adjustment of the second inclined plate so as to adjust an axial position and a circumferential position of the roller pin relative to the annular ring.

Systems and methods for multi-dimensional variable vane stage rigging utilizing adjustable inclined mechanisms

A gas turbine engine system includes a gas turbine engine, an accessory gearbox, and a flywheel powered barring engine system. The gas turbine engine includes a rotor and a turbine. The accessory gearbox is connected with the rotor. The flywheel powered barring engine system is connected with the accessory gearbox and configured to rotate the rotor after shut down of the gas turbine engine.

Flywheel powered barring engine for gas turbine engine

A vane adjustment assembly includes a plurality of vanes, an annular ring coupled to the vanes, and a ring adjustment assembly. The ring adjustment assembly includes a shim plate having a first shim surface removably arranged on an axially facing surface of the annular ring, a carrier plate having a first carrier surface removably arranged on a second shim surface of the shim plate opposite the first shim surface, and a roller pin coupled to a second carrier surface of the carrier plate opposite the first carrier surface. The shim plate is sized so as to locate the roller pin at a predetermined distance from the annular ring so as to adjust a position of the plurality of variable vanes relative to the roller pin.

Systems and methods for multi-dimensional variable vane stage rigging utilizing adjustable alignment mechanisms

A compressor adapted for use in for a gas turbine engine includes a diffuser and a housing. The diffuser is arranged circumferentially around an axis and includes a fore plate, an aft plate spaced apart axially from the fore plate to define a flow path therebetween, and a plurality of vanes that extend between the fore plate and the aft plate. The housing is arranged circumferentially about the axis and located adjacent the diffuser.

Centrifugal compressor assembly for a gas turbine engine with deswirler having sealing features

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 compressor adapted for use in a gas turbine engine includes an impeller, a diffuser, and a deswirler. The impeller is arranged circumferentially about an axis and configured to rotate about the axis. The diffuser is arranged circumferentially around the impeller to receive the air from the impeller. The deswirler is configured to receive the air from the diffuser and to conduct the air into a combustion chamber.

Centrifical compressor assembly for a gas turbine engine

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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Indianapolis, IN, United States of America

Ryan Charles Humes