Abstract: A plenum assembly for a compressor has a plenum housing defining a radially inward entry to a compressor and an outer circumference, and at least two open areas in the outer circumferences which are defined by at least two plenum flanges; an inlet duct connected to a first plenum flange of the at least two plenum flanges; and a panel having a flow control feature, wherein the panel is connected to a second plenum flange of the at least two plenum flanges.

Abstract: A three-dimensional capacitor component that includes a substrate having a textured (contoured) surface and a stack of layers formed conformally over the textured surface to constitute a capacitive stack structure. Respective contacts to the bottom and top electrodes of the capacitive stack structure are both provided at a first side of the component. The bottom electrode and substrate are doped with dopants of the same polarity, and the substrate is heavily doped so that current between a terminal portion of the bottom electrode and remote parts of the bottom electrode flows via the substrate, lowering ESR. A backside metallization layer produces a further, and greater, reduction in ESR. The capacitor component may be implemented as a discrete capacitor component, but may also be integrated with other components/devices. Corresponding fabrication methods are described.

Abstract: An electronic device is provided that includes a board equipped with a pair of differential transmission lines that each have an opening extending between two line terminals. Moreover, the device includes a capacitor module that includes a support and two capacitors that each have two capacitor terminals, respectively, connected to the two line terminals of one line of the pair of transmission lines. In addition, the support includes a separating region between the two capacitors that has at least one cavity disposed between the two capacitors.

Abstract: A plenum assembly for a compressor has a plenum housing defining a radially inward entry to a compressor and an outer circumference, and at least two open areas in the outer circumferences which are defined by at least two plenum flanges; an inlet duct connected to a first plenum flange of the at least two plenum flanges; and a panel having a flow control feature, wherein the panel is connected to a second plenum flange of the at least two plenum flanges.

Abstract: An electronic device and a method for manufacturing an electronic device. The electronic device includes: a board equipped with a pair of differential transmission lines, each line of the pair having an opening extending between two line terminals; and a capacitor module that includes: a base; and two 3D capacitors supported by the base, each 3D capacitor comprising two capacitor terminals respectively connected to the two line terminals of one line of the pair of transmission lines.

Abstract: An electronic device and a method for manufacturing an electronic device. The electronic device includes: a board equipped with a pair of differential transmission lines, each line of the pair having an opening extending between two line terminals; and a capacitor module that includes: a base; and two 3D capacitors supported by the base, each 3D capacitor comprising two capacitor terminals respectively connected to the two line terminals of one line of the pair of transmission lines.

Abstract: An electronic device is provided that includes a board equipped with a pair of differential transmission lines that each have an opening extending between two line terminals. Moreover, the device includes a capacitor module that includes a support and two capacitors that each have two capacitor terminals, respectively, connected to the two line terminals of one line of the pair of transmission lines. In addition, the support includes a separating region between the two capacitors that has at least one cavity disposed between the two capacitors.

Abstract: An electronic device and a method for manufacturing an electronic device. The electronic device includes: a board equipped with a pair of differential transmission lines, each line of the pair having an opening extending between two line terminals; and a capacitor module that includes: a base; and two 3D capacitors supported by the base, each 3D capacitor comprising two capacitor terminals respectively connected to the two line terminals of one line of the pair of transmission lines.

Abstract: A three-dimensional capacitor component that includes a substrate having a textured (contoured) surface and a stack of layers formed conformally over the textured surface to constitute a capacitive stack structure. Respective contacts to the bottom and top electrodes of the capacitive stack structure are both provided at a first side of the component. The bottom electrode and substrate are doped with dopants of the same polarity, and the substrate is heavily doped so that current between a terminal portion of the bottom electrode and remote parts of the bottom electrode flows via the substrate, lowering ESR. A backside metallization layer produces a further, and greater, reduction in ESR. The capacitor component may be implemented as a discrete capacitor component, but may also be integrated with other components/devices. Corresponding fabrication methods are described.

Abstract: A bearing arrangement rotatably supports a shaft of an aircraft engine. The bearing arrangement comprises a bearing having rolling elements disposed between inner and outer races. The inner race is affixed to the shaft. A decoupler normally structurally couples the outer race of the bearing to a stator structure of the engine. The decoupler is configured to release the bearing from the stator structure when subject to a predetermined critical load. A bumper is mounted to the stator structure and encircles the bearing. The bumper has a radially inwardly facing surface disposed in close proximity to a radially outer surface of the outer race of the bearing and defines therewith a radial gap to accommodate and constrain an orbiting motion of the rotor about the central axis of the engine after decoupling at the bearing.

Abstract: A bearing arrangement rotatably supports a shaft of an aircraft engine. The bearing arrangement comprises a bearing having rolling elements disposed between inner and outer races. The inner race is affixed to the shaft. A decoupler normally structurally couples the outer race of the bearing to a stator structure of the engine. The decoupler is configured to release the bearing from the stator structure when subject to a predetermined critical load. A bumper is mounted to the stator structure and encircles the bearing. The bumper has a radially inwardly facing surface disposed in close proximity to a radially outer surface of the outer race of the bearing and defines therewith a radial gap to accommodate and constrain an orbiting motion of the rotor about the central axis of the engine after decoupling at the bearing.

Abstract: A frangible mounting arrangement between a bearing and a bearing support in a gas turbine engine comprises a plurality of frangible bolts connecting mounting flanges of the bearing and the bearing support. The bolts are disposed on a circle. A distance on the circle between a first pair of adjacent bolts is greater than a distance on the circle between a second pair of adjacent bolts. The bolts are configured to break when subjected to a breaking load above a predetermined value. The breaking load results from at least one of a bending moment and a shear load on the mounting flanges. When subjected to the breaking load, the first pair of adjacent bolts breaks before the second pair of adjacent bolts. A method of providing a frangible mounting arrangement between a bearing and a bearing support is also provided.

Abstract: The structural case has an annular body having a central axis and including a plurality of boss sections circumferentially interspaced from one another around the axis by a plurality of arcuate panel sections, each panel section having: two parallel arcuate structural flange members being axially interspaced from one another; a sheet metal wall extending between and interconnecting the two flange members; and at least one rib having an edge welded to the sheet-metal wall.

Abstract: A bearing arrangement rotatably supports a shaft of an aircraft engine. The bearing arrangement comprises a bearing having rolling elements disposed between inner and outer races. The inner race is affixed to the shaft. A decoupler normally structurally couples the outer race of the bearing to a stator structure of the engine. The decoupler is configured to release the bearing from the stator structure when subject to a predetermined critical load. A bumper is mounted to the stator structure and encircles the bearing. The bumper has a radially inwardly facing surface disposed in close proximity to a radially outer surface of the outer race of the bearing and defines therewith a radial gap to accommodate and constrain an orbiting motion of the rotor about the central axis of the engine after decoupling at the bearing.

Abstract: Vane assemblies for gas turbine engines and methods for assembling vane assemblies are disclosed. The vane assemblies may include at least one shroud having at least one vane-receiving portion, at least one vane having at least one end portion received in the vane-receiving portion, and at least one sealing member having an uncompressed cross-section that is substantially circular. The sealing member(s) are disposed between and in contact with the end portion of the vane and the vane-receiving portion of the shroud.

Abstract: A bearing arrangement rotatably supports a shaft of an aircraft engine. The bearing arrangement comprises a bearing having rolling elements disposed between inner and outer races. The inner race is affixed to the shaft. A decoupler normally structurally couples the outer race of the bearing to a stator structure of the engine. The decoupler is configured to release the bearing from the stator structure when subject to a predetermined critical load. A bumper is mounted to the stator structure and encircles the bearing. The bumper has a radially inwardly facing surface disposed in close proximity to a radially outer surface of the outer race of the bearing and defines therewith a radial gap to accommodate and constrain an orbiting motion of the rotor about the central axis of the engine after decoupling at the bearing.

Abstract: A bearing arrangement rotatably supports a shaft of an aircraft engine. The bearing arrangement comprises a bearing having rolling elements disposed between inner and outer races. The inner race is affixed to the shaft. A decoupler normally structurally couples the outer race of the bearing to a stator structure of the engine. The decoupler is configured to release the bearing from the stator structure when subject to a predetermined critical load. A bumper is mounted to the stator structure and encircles the bearing. The bumper has a radially inwardly facing surface disposed in close proximity to a radially outer surface of the outer race of the bearing and defines therewith a radial gap to accommodate and constrain an orbiting motion of the rotor about the central axis of the engine after decoupling at the bearing.

Abstract: A bleed valve having a piston with a sealing member, the piston being displaceable between a first position to seal an aperture of a fluid conduit and an opposed second position spaced apart from the aperture to allow the working fluid therethrough. The bleed valve also has a guiding assembly with at least one guide wheel mounted to the piston and being displaceable therewith along a guide rail. The guide wheel has a guide groove extending inwardly from an outer rolling surface. The guide rail has a rail surface with a guide protrusion. The guide groove and the guide protrusion are complementary and in rolling contact with one another. The bleed valve also has a displacement mechanism for displacing the piston between the first and second positions. A compressor with a bleed valve and method for controlling bleeding of a working fluid are also discussed.

Abstract: The structural case has an annular body having a central axis and including a plurality of boss sections circumferentially interspaced from one another around the axis by a plurality of arcuate panel sections, each panel section having: two parallel arcuate structural flange members being axially interspaced from one another; a sheet metal wall extending between and interconnecting the two flange members; and at least one rib having an edge welded to the sheet-metal wall.

Abstract: The structural case has an annular body having a central axis and including a plurality of boss sections circumferentially interspaced from one another around the axis by a plurality of arcuate panel sections, each panel section having: two parallel arcuate structural flange members being axially interspaced from one another; a sheet metal wall extending between and interconnecting the two flange members; and at least one rib having an edge welded to the sheet-metal wall.