An internal combustion engine, ICE, system, includes a turbocharger having a turbine and a compressor for compressing intake air and feeding the intake air to the ICE. A turbo turbine unit is disposed in an exhaust gas path downstream the turbocharger to receive exhaust gas from the turbocharger. The turbo turbine unit having a turbine wheel, a bearing housing defining an inside volume for containing lubrication oil, and a sealing arrangement positioned in the vicinity of the turbine wheel for preventing lubrication oil from escaping from the inside volume of the bearing housing to an exhaust duct of the turbo turbine unit. A buffer air conduit extends between a selected position at the compressor and a buffer air inlet of the turbo turbine unit. The buffer air inlet is in fluid communication with a buffer air channel inside the turbo turbine unit to direct buffer air to a position in-between axially opposite arranged annular sealing members to provide a counter-pressure against at least one of the annular sealing members.

A fireproof assembly for an aircraft engine, comprises a fireproof housing having an internal volume and an opening. A fireproof internal shield is located within the fireproof housing. The internal shield divides the volume into a first sub-volume and a second sub-volume, the first sub-volume configured for receiving a component of the aircraft engine. A non-fireproof component seals the opening of the fireproof housing. Fireproof fasteners are used to support internal shield inside the housing.

Sealing arrangements and turbomachines are provided. A sealing arrangement includes a transition duct having an upstream end and a downstream end. The transition duct includes an aft frame that circumferentially surrounds the downstream end of the transition duct. A first stage nozzle is spaced apart from the aft frame and defines a gap therebetween. A sealing assembly is coupled to the aft frame. The sealing assembly includes a flexible sealing element that extends from the aft frame, across the gap, to the first stage nozzle. The flexible sealing element is forced into sealing engagement with the first stage nozzle by pressure from a compressed working fluid. The sealing assembly further includes a heat shield disposed between the flexible sealing element and the aft frame. The heat shield terminates within the gap.

A turbine rotor wheel for an aircraft turbomachine includes a rotor disk, an annular shroud extending around the disk, and blades arranged between the disk and the shroud. The the root of each of the blades has two tabs configured for attachment to the disk. The tabs are arranged upstream and downstream, respectively, of a wall of the disk, relative to the axis. The tab arranged upstream is engaged in a first recess of the disk and configured to cooperate by abutment with a peripheral edge of the first recess. The tab arranged downstream is engaged in a second recess of the disk and is configured to cooperate by abutment with a peripheral edge of the second recess.

A heat shield for a fuel nozzle of a gas turbine engine combustor. The heat shield includes a radial flange extending in radial and circumferential directions and has an opening therethrough at a radially inward end of the radial flange, and an annular conical wall extending in longitudinal and circumferential directions, the annular conical wall being connected to the radial flange at the radially inward end of the radial flange. The radial flange includes a flange forward side, and a flange aft side, and has a flange outer end portion. The flange outer end portion includes a flange rounded end portion on one of the flange forward side or the flange aft side, and a flange rounded protruding lip on the other of the flange forward side or the flange aft side, the rounded protruding lip extending in the longitudinal direction.

Provided is a turbine housing (10) having: a housing part (11) that forms a spiral space (S5) extending around a rotating shaft (40); a heat-shielding core (12) which is disposed in the spiral space (S5) and forms a spiral exhaust gas flow passage (S6) in which exhaust gas introduced from an exhaust gas introduction port flows; and a variable nozzle mechanism (13) that guides the exhaust gas to a turbine wheel, wherein heat-shielding spaces (S1, S2, S3) are formed between the inner circumferential surface of the housing part (11) and the outer circumferential surface of the heat-shielding core (12), and wherein the heat-shielding core (12) has a first flange part (12d) and a second flange part (12e) and is fixed between the variable nozzle mechanism (13) and the housing part (11) while a first sealing (14) is interposed between the first flange part (12d) and the variable nozzle mechanism (13).

A method of fabricating an airfoil fairing for a vane arc segment includes providing a mandrel that necks down through a mandrel neck portion, providing fiber plies around the mandrel to form a tube that defines at least a portion of an airfoil profile of an airfoil section of an airfoil fairing, the fiber plies following the mandrel neck portion such that the tube has a corresponding tube neck portion that necks down to a collar, and removing the mandrel from the tube.

A turbomachinery stator apparatus includes: a compressor casing including a casing wall defining an arcuate flowpath surface and an opposed backside surface, the flowpath surface defining at least two spaced-apart rotor lands, a stator vane row of stator vanes disposed inside the compressor casing, wherein the casing wall includes a heat shield positioned outboard of the rotor lands immediately upstream or downstream of the stator vane row, and wherein a) the casing wall includes the heat shield and b) the stator vanes form a single monolithic whole.

A heat insulating material assembly is provided with: a heat insulating material covering an outer surface of a casing of a gas turbine; and a guard part disposed so as to protrude from the outer surface of the casing and face an end surface of the heat insulating material. The heat insulating material is disposed outside an arrangement area of a plurality of openings for air intake from an external space into the casing and on an opposite side to the arrangement area across the guard part.

A cylinder head assembly for an internal combustion engine includes a cast cylinder head, a turbocharger housing including a compressor housing and turbine housing integrally cast with the cylinder head, and a turbocharger cartridge assembly configured to be inserted into the turbocharger housing and including a shaft coupled between a compressor wheel and a turbine wheel. A compressor cover is configured to couple to the compressor housing and define a compressor inlet and at least partially define a compressor diffuser passage. The cartridge assembly includes a housing having a diffuser flange extending outwardly therefrom, the diffuser flange including a front surface and an opposite contoured volute surface. The compressor diffuser passage is at least partially defined by the compressor cover and the diffuser flange front surface. A compressor volute is at least partially defined by the diffuser flange contoured volute surface and a contoured inner surface of the compressor housing.