United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

John C DiTomasso

Gregory E Reinhardt

Matthew P Forcier

Enzo DiBenedetto

Daniel W Major

Nathan F Champion

Joseph Rios

Matthew E Bintz

Thomas J Robertson, Jr

Steven H Zysman

John P Nikkanen

Carl Brian Klinetob

Carney R Anderson

William S Pratt

John P Tirone

Andrew Pope

Karl D Blume

Charles P Gendrich

Andrew J Murphy

Jason Leroux

John P Lucashu

Jody M Grosso

Jason W Mazanec

Steven D Sandahl

Jonathon T Pacuk

Steven L Conner

Jennifer L Grudnoski

Gabriel P Smith

Akwetee E Watkins

David J Yudichak

Michael Glaser Seth

A tandem rotor disk apparatus may include a rotor disk body concentric about an axis. The tandem rotor disk apparatus may also include a first blade extending radially outward of the rotor disk body and a second blade extending radially outward of the rotor disk body. The first blade may be offset from the second blade in a direction parallel to the axis. The tandem rotor disk apparatus may be implemented in a gas turbine engine with no intervening stator vane stages disposed between the first blade and the second blade.

Tandem blade rotor disk

A tandem rotor disk apparatus may include a rotor disk body concentric about an axis. The tandem rotor disk apparatus may also include a first blade extending radially outward of the rotor disk body and a second blade extending radially outward of the rotor disk body. The first blade may be offset from the second blade in a direction parallel to the axis. The tandem rotor disk apparatus may be implemented in a gas turbine engine with no intervening stator vane stages disposed between the first blade and the second blade. The tandem rotor disk apparatus may include two separate rotor disk bodies.

A rotor assembly of a gas-turbine engine may comprise a first rotor blade, a second rotor blade, a third rotor blade, a first platform sealing assembly and a second platform sealing assembly. The first platform sealing assembly may be disposed between a first platform of the first rotor blade and a second platform of the second rotor blade. The second platform sealing assembly may be disposed between the second platform and a third platform of the third rotor blade.

Thermally isolated rotor systems and methods

In one exemplary embodiment, a center body support for a gas turbine engine includes a fan exit guide vane mounting ring and an outer annular wall. An aft flange extends radially outward from the outer annular wall. An inner annular wall is radially spaced from and structurally interconnected to the outer annular wall by a circumferential array of struts. A brace interconnects the aft flange to a forward portion of the outer annular wall. The aft flange includes inner and outer mounting features spaced radially apart from one another. The inner and outer mounting feature respectively receive first and second sets of fasteners. The forward portion extends in a radially outward direction from the outer annular wall. The forward portion includes a forward mounting feature that receives a third set of fasteners. The outer and forward mounting features are secured to the fan exit guide vane mounting ring respectively by the first and third sets of fasteners. Forward, outer and inner mounting features define a triangular cross-sectional shape. The forward portion has a radial inner end opposite a radial outer end. The brace is joined at the radial outer end. The brace transfers an axial load from the aft flange to the radial outer end of the forward portion.

Gas turbine engine front center body architecture

A compressor rotor assembly including a plurality of rotor disks axially spaced from each other, each rotor disk extending radially from an inner end to an outer end. Also included is a spacer extending axially from each rotor disk to engage an adjacent spacer extending from an adjacent rotor disk, the spacer and adjacent spacer disposed proximate the outer end of the respective rotor disks, the spacers forming an outer backbone of the compressor rotor assembly. Further included is an inner backbone of the compressor rotor assembly, the inner backbone comprising a plurality of backbone segments, each of the backbone segments extending axially from each rotor disk to engage an adjacent backbone segment extending from an adjacent rotor disk, the backbone segment and the adjacent backbone segment disposed proximate the inner end of the respective rotor disks.

Compressor rotor stack assembly for gas turbine engine

A modular variable vane assembly includes an airfoil, an inner case, and an outer case. The airfoil extends between a first end and a second end along an axis. The airfoil has a connector that extends from the first end and a pivot member that extends from the second end. The inner case defines a pivot opening that is arranged to receive the pivot member. The outer case defines a first opening that extends from a first outer case surface towards a second outer case surface along the axis. The first opening is arranged to receive the connector.

Modular variable vane assembly

A bellcrank assembly for variable vane assembly of a gas turbine engine includes a first bellcrank segment. Also included is a second bellcrank segment. Further included is a bolt extending through respective interior barrels defined by the first and second bellcrank segments to couple the first and second bellcrank segments to each other. Yet further included is a torque frame wall defining an aperture, the bolt extending through the aperture.

Bellcrank assembly for gas turbine engine and method

A clutched compressor section of a gas turbine engine coupled to a rotor shaft. The clutched compressor section includes at least one decoupleable rotor stage, the decoupleable rotor stage switchable between a coupled condition and a decoupled condition with a clutch mechanism, the coupled condition coupling the decoupleable rotor stage with the rotor shaft, the decoupled condition decoupling the decoupleable rotor stage from the rotor shaft.

Clutched compressor section for gas turbine engine

In one exemplary embodiment, a gas turbine engine system for cooling engine components includes an engine core, a core housing containing the engine core, an engine core driven fan forward of the core housing, a nacelle surrounding the fan and the core housing, and a bypass duct defined between an outer diameter of the core housing and an inner diameter of the nacelle. Also included is a thermal management system having a coolant circuit including at least one of a first heat exchanger disposed on the inner diameter of the nacelle and a second heat exchanger disposed on a leading edge of a BiFi spanning the bypass duct. The first heat exchanger is in thermal communication with the second heat exchanger.

Thermal management system for a gas turbine engine with an integral oil tank and heat exchanger in the nacelle

A center body support for a gas turbine engine includes an outer annular wall. An aft flange extends radially outward from the outer annular wall. A brace interconnects the aft flange to a forward portion of the outer annular wall. The aft flange, brace and forward portion of the outer annual wall provide a unitary, one-piece structure.

An upper bifi frame for preventing air leakage in a gas turbine engine including an engine casing and a fan case is provided. The upper bifi frame includes a forward fairing having a forward fairing midsection extending between the engine casing and the fan case. The forward fairing has a forward fairing first end including a flange configured to couple to the engine casing. The forward fairing has a forward fairing second end extending from the forward fairing midsection and configured to couple to the fan case. At least one aft seal is secured to the forward fairing and forms a seal therewith.

Upper bifi frame for a gas turbine engine and methods therefor

An upper bifi frame for preventing air leakage in a gas turbine engine including an engine casing and a fan case is provided. The upper bifi frame includes a forward fairing having a forward fairing midsection extending between the engine casing and the fan case. The forward fairing has a forward fairing first end including a flange configured to couple to the engine casing. The forward fairing has a forward fairing second end extending from the forward fairing midsection and configured to couple to the fan case. At least one aft seal is secured to the forward fairing and forms a seal therewith. A wedge seal is coupled to the forward fairing and the at least one aft seal and is operative to prevent air leakage to a pylon that is secured to the engine casing.

A grounding sleeve for grounding an electrically insulated element disposed between two metal components includes an annular body extending between a first end and a second end. At least one window is formed in the annular body between the first end and the second end.

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Glastonbury, CT, United States of America

John C DiTomasso