United Technologies Corporation

Raytheon Technologies Corporation

Utc Power Corporation

Dale William Petty

Shawn M McMahon

Timothy A Swanson

Cynthia M Phillips

Michael Joseph Murphy

Jonathan Lemoine

Sean P Zamora

Joseph T Caprario

Steven J Bauer

Karl D Blume

John D Wiedemer

Jason Arnold

Jeffrey G Lake

James P Allore

Gonzalo F Martinez

Kenneth E Harmon

Alex J O Simpson

Enzo Ingriselli

Shawn M Mcmahon

A fastener assembly may be configured to mount structures in a gas turbine engine. The fastener assembly may comprise a fastener and a leak resistant insert. The leak resistant insert may be configured to at least partially reduce fluid leakage between the coupling of the fastener and the leak resistant insert. The leak resistant insert may comprise an outer surface opposite an inner threaded surface. The inner threaded surface may define an insert opening through leak resistant fastener insert, configured to receive the fastener. The outer surface may define an insert end enclosing the inner threaded surface opposite the insert opening.

Fastener assembly having a leak resistant threaded insert

A turbine housing section includes a radially inner case centered on a first axis, and a radially outer case spaced radially outwardly of the inner case, and centered on a second axis. The first and second axes are offset relative to each other. A plurality of tie rods include a threaded nut received on a tie rod, with the plurality of tie rods connecting the inner and outer cases. The plurality of tie rods are spaced circumferentially about both of the first and second axes, and extend for distinct lengths between the inner and outer cases such that the inner and outer cases are held at a position wherein the first and second axes are offset.

Turbine case adjustment using Adjustable tie rods

An example diffuser assembly includes a diffuser case, an annular ring, and a retaining tab that is mounted to the annular ring and has an end that engages an inner wall of the diffuser case. The engagement between the second end and the inner wall locks the retaining tab and limits movement of the annular ring along a central longitudinal axis of the diffuser case. Another example diffuser assembly includes a diffuser case, an annular ring, and a snap ring. The snap ring is situated in an annular groove of an inner wall of the diffuser case, and restricts movement of the annular ring along a central longitudinal axis of the diffuser case. A retaining tab is affixed to either the annular ring or the diffuser case, and has an end retaining the annular ring in the annular groove.

Retaining tab for diffuser seal ring

A retractable exhaust liner segment according to an example of the present disclosure includes, among other things, at least one liner segment extending between a forward end and an aft end. The forward end of the at least one liner segment is configured to overlap an aft end of an engine structure and the aft end of the at least one liner segment is configured to overlap a forward end of an exhaust liner when in an assembled position. The at least one liner is configured such that a gap exists between the at least one liner segment and one of the engine structure and the exhaust liner when the at least one liner segment is moved along an axis in a first direction to a disassembled position. The gap closes as the at least one liner segment is moved along the axis in a second, different direction to the assembled position.

Retractable exhaust liner segment for gas turbine engines

A tie rod includes a gusset which extends between a rod and a base.

Tie rod for a gas turbine engine

The present disclosure relates to plug assemblies within a gas turbine engine. In one embodiment, a plug assembly includes a boss which includes a shaft and a collar, a retaining element including at least two prongs, and a plug including a shank and at least one retaining feature. The at least two prongs of the retaining element are configured to retain the plug to the boss.

Plug assembly with retaining element

A flexible panel assembly for a gas turbine engine selectively exhibits a range of positions to regulate exhaust of the engine.

Gas turbine engine systems involving variable nozzles with flexible panels

A retractable exhaust liner segment according to an exemplary aspect of the present disclosure includes, among other things, a first retractable exhaust liner segment which defines a first flange and a second retractable exhaust liner segment which defines a second flange. A fastener assembly received by the first flange and the second flange is configured to mount the first retractable exhaust liner segment and the second retractable exhaust liner segment. A forward end of the retractable exhaust liner segment overlaps an aft end of an engine structure and an aft end of the retractable exhaust liner segment overlaps a forward end of an exhaust liner in an assembled position. A gap exists between the retractable exhaust liner segment and one of the engine structure and the exhaust liner as the retractable exhaust liner segment is moved along an axis in one direction to a disassembled position and the gap closes as the retractable exhaust liner segment is moved along the axis in other direction to the assembled position. A method of maintaining a gas turbine engine is also disclosed.

An engine has a blade, a casing surrounding the blade, an seal ring, and a passive system for connecting the seal ring to the casing and for accommodating thermal expansion of the seal ring relative to the casing so as to maintain blade tip clearance control. The passive system may include at least one, metallic Z-band extending between the casing and the seal ring.

Fan blade tip clearance control via Z-bands

A regulator system includes a slidable ramp intermediate a secondary flow path and a primary flow path of a gas turbine engine nozzle section.

Sliding ramp nozzle system for a gas turbine engine

An exemplary turbine engine link assembly includes a link extending longitudinally from a rod end and terminating at a hemispherical end. The rod end is secured to an engine liner or an engine casing. The hemispherical end is biased toward a corresponding hemispherical recess in the engine liner or in the other of the engine liner or the engine casing.

Pivoting liner hanger

A nozzle assembly for a gas turbine engine includes a door axially slidable relative to a passage in communication with a secondary flow path to regulate the secondary flow though the passage.

Gas turbine engine systems involving variable nozzles with sliding doors

A pair of reactant cover plates, e.g., fluid manifolds or protective covers (), on opposite sides of a fuel cell stack () are drawn to the fuel cells () and pressure plates () by tensioning lines, e.g., cables () or straps (), which may extend around structures, e.g., pins or extensions () extending outwardly from the ends of the cover plates or guides () on the stack, e.g., on the pressure plates in a closed loop, and are tensioned by a tensioning device, such as a turnbuckle ().

Fuel cell cover plate tie-down

A power plant () having a pair of substantially identical fuel cell stacks (), each having an oxidant or fuel inlet/outlet manifold () identical to the inlet/outlet manifold of the other stack, each inlet/outlet manifold mounted on the same side of the corresponding stack as the other inlet/outlet manifold on the other stack (the right side herein). Inlet/outlet plumbing is disposed at the end of one of the stacks () between the inlet/outlet manifolds (), the plumbing including a T-like transition () between a supply pipe () and an inlet tube () that feeds the inlets of both of the inlet/outlet manifolds (). At each inlet/outlet manifold, the side which is not connected to plumbing is blocked off with a seal plate (). Inlet and outlet tubes () include flexible tubing portions, whereby to allow for dimensional and/or positional variations between fuel cell power plants.

Compact reactant gas plumbing serving dual identical fuel cell stacks

A pair of reactant gas manifolds (and) on opposite sides of a fuel cell stack () are sealed to the fuel cells () and pressure plates () by means of pressure applied by load cables (). The centers of the manifolds are prevented from having leakage between them and the end plates by means of a tensioning system comprising a plurality of pins () extending outwardly from the ends of the manifolds, and tensioning cables () extending around the pins in a closed loop and tensioned by a turnbuckle ().

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Wallingford, CT, United States of America

Dale William Petty