A system for energy conversion that includes a propulsion system, a fuel circuit, a combustion device, a turbine, and a load device. The fuel circuit is in fluid communication with a fuel tank and a fuel flow control device that separates a flow of fuel into a first portion and a second portion. The combustion device receives a flow of oxidizer and the second portion of fuel to generate combustion gases. The turbine receives the combustion gases from the combustion device via a fluid circuit. The load device is operably coupled to the turbine via a driveshaft and is configured to receive torque from the driveshaft.

A turbine stator includes a partition plate including an inner ring that extends along a circumferential direction, an outer ring that is disposed on an outer side of the inner ring in a radial direction, and extends in the circumferential direction, a plurality of nozzles that are disposed in the circumferential direction between the inner ring and the outer ring, and are configured to guide a fluid from an upstream side toward a downstream side in an axial direction, and an annular protruding portion, protrudes from the outer ring to the downstream side in the axial direction, and extends along the outer ring in the circumferential direction, and a casing surrounding the partition plate from the outer side in the radial direction, and having a contact support surface that is in contact with the annular protruding portion from the downstream side in the axial direction.

A sealing arrangement for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a groove that extends between an upstream rail and a downstream rail, a complementary static structure spaced from the groove, and a seal positioned within the groove and configured to seal a clearance between at least one of the upstream rail and the downstream rail and the complementary static structure.

A variable-capacity turbocharger includes a nozzle flow passage in which a gas is capable of flowing therethrough from a scroll flow passage toward a turbine impeller, a connecting pin connecting flow passage wall surfaces forming the nozzle flow passage, and nozzle vanes arranged in a rotation direction of the turbine impeller. At least one of the flow passage wall surfaces includes an inner peripheral side wall surface extending radially inward of a first reference line extending in the rotation direction, an outer peripheral side wall surface which is a plane extending radially outward from a second reference line extending in the rotation direction and parallel to a plane orthogonal to rotation axes of the nozzle vanes, and an intermediate wall surface which is a plane extending from the first reference line to the second reference line and parallel to the plane extending orthogonal to the rotation axes of the nozzle vanes.

A component assembly for a gas turbine engine defining a core air flowpath is provided. The component assembly includes an outer shell comprising a first array of integral outer shell airfoils that extend inward from an outer shell periphery; and an inner shell comprising a second array of integral inner shell airfoils that extend outward from an inner shell periphery, wherein the outer shell and the inner shell are one or both of translatable and rotatable relative to one another between a first position and a second position.

A turbine component assembly for a gas turbine engine includes: a first component having a first coefficient of thermal expansion and including an end face; a second component including a mating surface abutting the end face; and a fastener having a second coefficient of thermal expansion different from the first coefficient of thermal expansion, the fastener including a shank engaging the second component and an enlarged head engaging a mounting slot in the first component; wherein the mating surface and the end face shaped to permit relative pivoting movement between the first and second components.

A variable geometry assembly for modulating a fluid flow in a turbomachine is disclosed. The assembly comprises: a first ring having a plurality of first wedge-shaped elements and having an axis; a second ring having a plurality of second wedge-shaped elements and having an axis. The second ring is substantially coaxial to the first ring. The second wedge-shaped elements co-act with the first wedge-shaped elements Flow passages are defined between pairs of sequentially arranged first wedge-shaped elements and second wedge-shaped elements. The first ring and the second ring are angularly displaceable one with respect to the other. Moreover, the first ring and the second ring are configured to move axially with respect to one another when the first ring and the second ring are angularly displaced one with respect to the other.

A variable area nozzle assembly for a gas turbine engine includes a fixed structure including a first fixed ring and a second fixed ring. The second fixed ring is spaced axially aft from the first fixed ring to define a first portion of an ejector passage therebetween. A nozzle defines an inner radial exhaust flow path surface. The nozzle includes a forward ejector door and an aft ejector door. The forward ejector door and the aft ejector door define a first surface portion of the inner radial exhaust flow path surface. Each of the forward ejector door and the aft ejector door are pivotable between respective closed positions and respective open positions. A translating ejector sleeve is mounted within the fixed structure and configured to axially translate within the fixed structure between a first axial position and a second axial position.

A gas turbine engine for an aircraft includes a turbine section and an exhaust section configured to receive an exhaust gas stream from the turbine section. The exhaust section includes a monolithic catalyst structure configured to remove nitrogen oxides (NO.sub.x) from the exhaust gas stream.

An airfoil for a gas turbine engine including an airfoil body extending between a leading edge and a trailing edge and between a pressure side and a suction side. The airfoil body includes a strut portion extending from the leading edge and a flap portion extending from the trailing edge. The flap portion is pivotable relative to the strut portion. A flexible skin surrounds both the strut portion and the flap portion on both the pressure side and the suction side.