A passive flow modulation device for a machine defining an axial direction and a radial direction, the passive flow modulation device including: a first ring with a first coefficient of thermal expansion; a second ring disposed coaxially with the first ring and positioned at least partially inward of the first ring along the radial direction, spaced from the first ring along the axial direction, or both, the first ring, the second ring, or both defining at least in part one or more passages, the second ring with a second coefficient of thermal expansion that is less than the first coefficient of thermal expansion to passively modulate a size of the one or more passages during operation.

A mixing tube with multiple shapes is provided, allowing additional injection of gas in order to keep the flow detached from the second shape in an ascent phase and to bring about, in a descent phase, a controlled detachment as a result of the change of slope between the two shapes. A propulsion nozzle for an engine of a spacecraft or aircraft is provided including such a mixing tube and a method for controlling the speed transition of the propulsion gases in such a nozzle in accordance with the altitude. Also, a method is provided for vectorising the thrust in such a nozzle by radial and asymmetrical injection of gas and a control method which prevents re-attachment of the jet to the second shape of such a propulsion nozzle for an engine of a spacecraft when it is in the take-off or landing phase.

A turbomachine compressor module comprising an annular array of struts provided with pivotable flaps. The struts can define inter-strut spaces between two circumferentially adjacent struts, and variably oriented stator vanes are disposed at least partially in the inter-strut spaces. Also, a turbomachine having such a module and a row of rotor blades directly downstream of the module.

An assembly is provided for a gas turbine engine. This gas turbine engine assembly includes a stationary engine structure. The stationary engine structure includes a diffuser, a combustor, an engine case and a plenum. The combustor is disposed within the plenum. The engine case forms a peripheral boundary of the plenum. A gas path extends sequentially through the diffuser, the plenum and the combustor. A first section of the stationary engine structure is formed as a first monolithic body. The first section includes the diffuser and the combustor. A second section of the stationary structure is formed as a second monolithic body. The second section is configured as or otherwise includes the engine case.

A variable capacity turbocharger includes a housing, a turbine impeller at least partially located in the housing, a scroll flow path located in the housing and encircling the turbine impeller, a first nozzle ring and a second nozzle ring facing each other in the housing, a nozzle flow path located between the first nozzle ring and the second nozzle ring and fluidly coupling the scroll flow path to the turbine impeller, a gap formed between the first nozzle ring and the housing, and a bearing hole located in the first nozzle ring and including an opening adjacent to the gap. The gap is located on an opposite side of the first nozzle ring to the nozzle flow path. Additionally, the gap is connected to the scroll flow path.

A turbine nozzle for an aircraft turbine engine, the nozzle including at least one vane and a base having a platform. The nozzle is fitted with a passive system for reintroducing blow-by gas into the primary jet, the passive system including gas extraction ports on the base as well as gas reinjection ports on the radially outer surface of the platform and/or on a suction-side surface of the vanes, the gas reinjection ports being designed to redirect the gas flow in a reinjection direction having a circumferential orientation.

A turbopump includes: a main shaft rotatably supported; a pump section including an impeller attached to one end of the main shaft; and a turbine section including: a disk attached to the other end of the main shaft, rotor blades provided on an outer periphery of the disk, and nozzles provided inclined to an entrance plane of a blade cascade constituted of the rotor blades, the nozzles having axisymmetric cross sections and arranged in at least two rows along a circumferential direction of the main shaft in a plane orthogonal to the main shaft.

A turbine nozzle assembly system includes a plurality of nozzle sets, where each nozzle set forms an annulus. The nozzles in each set include an inner endwall and an outer endwall that include joint openings to receive the respective endwall mount ends of an airfoil. The airfoils across the plurality of nozzle sets have an inner endwall mount end and an outer endwall mount end that are identical amongst the plurality of nozzle sets. A wing portion of the airfoil has a selected wing shape that is identical within the respective nozzle set but different amongst the plurality of nozzle sets. In this manner, the endwalls can be removed from an airfoil and replaced with an airfoil having a different wing shape that provides a different pairwise throat area. The system allows changing of a pairwise throat area for a nozzle set without replacing the entirety of each nozzle.

A variable nozzle device includes: a nozzle mount; a plurality of nozzle vanes; a drive ring being having a plurality of receiving portions disposed at different positions along a circumferential direction; and a plurality of lever plates each having a fixed portion to be fixed to corresponding one of the plurality of nozzle vanes and an engaging portion to be engaged with corresponding one of the plurality of receiving portions of the drive ring. The receiving portions include a first-side guide surface and a second-side guide surface. The engaging portions each include a first-side roll surface which is to be in contact with the first-side guide surface and a second-side roll surface which is to be in contact with the second-side guide surface. The first-side roll surface includes a lever-plate-side linear portion extending linearly in at least a part of a range which is to be in contact with the first-side guide surface. The first-side guide surface includes a drive-ring-side protruding curved surface portion extending in a protruding curve shape in at least a part of a range which is to be in contact with the first-side roll surface.

A turbocharger includes a bearing housing, a variable displacement mechanism, and a restricting member. The variable displacement mechanism includes a nozzle ring and a drive ring. The restricting member includes a flange part, a drive ring guide pin part, and a phase determining pin part. The flange part straddles a first surface of the nozzle ring facing the bearing housing and a second surface of the drive ring facing the bearing housing so that a position thereof with respect to the nozzle ring is fixed. The drive ring guide pin part is formed integrally with the flange part and disposed in a first hole formed on the first surface. The phase determining pin part is formed integrally with the flange part and disposed in a second hole formed on a third surface of the bearing housing facing the variable displacement mechanism.