Abstract: A tube assembly, in particular for a fluid supply system of a turbomachine, the assembly including a first tube, a second tube, a connection connecting the first and second tube, wherein the connection includes a first sealed spherical joint and a first sealed linear joint.

Abstract: A mid-turbine frame (MTF”) for a jet engine is disclosed and comprises a duct that extends between a high pressure jet engine turbine (“HPT”) and a low pressure jet engine turbine (“LPT”), the duct comprising a plurality of segments that together form an outer annular structure and an inner annular structure, the inner annular structure situated radially inward of the outer annular structure, and/or a plurality of vanes that extend radially outward from the inner annular structure toward the outer annular structure, each vane comprising a channel. Each segment may be coupled to an adjacent segment by a seal.

Abstract: An installation tool for an airfoil trim balance weight includes a tool body having a support for supporting the tool body with respect to the trim balance weight. A linear actuator is provided for contacting a tab of the trim balance weight, the linear actuator for moving linearly with respect to the tool body in a linear motion toward the support to permit the tab to bend. A method for installation, a gas turbine engine and a method for manufacturing also are provided.

Abstract: A mid-turbine frame (MTF”) for a jet engine is disclosed and comprises a duct that extends between a high pressure jet engine turbine (“HPT”) and a low pressure jet engine turbine (“LPT”), the duct comprising a plurality of segments that together form an outer annular structure and an inner annular structure, the inner annular structure situated radially inward of the outer annular structure, and/or a plurality of vanes that extend radially outward from the inner annular structure toward the outer annular structure, each vane comprising a channel. Each segment may be coupled to an adjacent segment by a seal.

Abstract: A mid-turbine frame (MTF”) for a jet engine is disclosed and comprises a duct that extends between a high pressure jet engine turbine (“HPT”) and a low pressure jet engine turbine (“LPT”), the duct comprising a plurality of segments that together form an outer annular structure and an inner annular structure, the inner annular structure situated radially inward of the outer annular structure, and/or a plurality of vanes that extend radially outward from the inner annular structure toward the outer annular structure, each vane comprising a channel. Each segment may be coupled to an adjacent segment by a seal.

Abstract: A mid-turbine frame (MTF”) for a jet engine is disclosed and comprises a duct that extends between a high pressure jet engine turbine (“HPT”) and a low pressure jet engine turbine (“LPT”), the duct comprising a plurality of segments that together form an outer annular structure and an inner annular structure, the inner annular structure situated radially inward of the outer annular structure, and/or a plurality of vanes that extend radially outward from the inner annular structure toward the outer annular structure, each vane comprising a channel. Each segment may be coupled to an adjacent segment by a seal.

Abstract: A portable display stand including a sheet of substantially rigid but not inflexible material having a plurality of cuts to provide four sections which are moveable relative to one another such that the sheet may be converted from a first, flat configuration to a second, erected configuration in which it is able to support an information display article in an inclined position.

Abstract: A portable display stand including a sheet of substantially rigid but not inflexible material having a plurality of cuts to provide four sections which are moveable relative to one another such that the sheet may be converted from a first, flat configuration to a second, erected configuration in which it is able to support an information display article in an inclined position.

Abstract: A fuel nozzle assembly for a combustor of a gas turbine including: a nozzle body having a front and an inner tube defining a fuel passage extending through the nozzle body, wherein the front proximate to a combustion section of the combustor; an outer casing around the inner tube, wherein an air passage is defined between the outer casing and the inner tube; a gas conduit arranged in the air passage and having an outlet proximate to the front of the nozzle body, wherein fuel starts flowing through the expandable conduit only after a flashback condition occurs in the combustor, and a premix fuel passage and port discharging fuel to a premix section of the combustor, wherein the gas conduit has an inlet open to the premix fuel passage.

Abstract: A nozzle is provided and includes an outer annulus defined by an exterior wall and an interior wall and including air inlets through which air flows to a fuel mixing zone and a combustion zone, an inner annulus disposed within the interior wall and including a fuel volume into which fuel is fed to a distal end thereof, which is adjacent to and isolated from the combustion zone and an airflow line, disposed between the fuel volume and the interior wall, through which air flows to the combustion zone with the airflow line and the combustion zone isolated from the fuel volume, and a fuse configured to melt during a flameholding incident and to form a breach through which fuel flows from the fuel volume, bypassing the fuel mixing zone, to a fuel burning zone downstream from the fuel mixing zone.

Abstract: A fuel nozzle assembly for a combustor of a gas turbine including: a nozzle body having a front and an inner tube defining a fuel passage extending through the nozzle body, wherein the front proximate to a combustion section of the combustor; an outer casing around the inner tube, wherein an air passage is defined between the outer casing and the inner tube; a gas conduit arranged in the air passage and having an outlet proximate to the front of the nozzle body, wherein fuel starts flowing through the expandable conduit only after a flashback condition occurs in the combustor, and a premix fuel passage and port discharging fuel to a premix section of the combustor, wherein the gas conduit has an inlet open to the premix fuel passage.

Abstract: A nozzle is provided and includes an outer annulus defined by an exterior wall and an interior wall and including air inlets through which air flows to a fuel mixing zone and a combustion zone, an inner annulus disposed within the interior wall and including a fuel volume into which fuel is fed to a distal end thereof, which is adjacent to and isolated from the combustion zone and an airflow line, disposed between the fuel volume and the interior wall, through which air flows to the combustion zone with the airflow line and the combustion zone isolated from the fuel volume, and a fuse configured to melt during a flameholding incident and to form a breach through which fuel flows from the fuel volume, bypassing the fuel mixing zone, to a fuel burning zone downstream from the fuel mixing zone.