For a rotary electric machine housing, a cooling jacket and compressed air flow passages are formed on an outer circumferential side of the cooling jacket. On an outer side wall of the rotary electric machine housing, a terminal casing is formed and electric terminal portions are accommodated in the terminal casing. Air bleed ports are formed in a shroud case of a gas turbine engine. Compressed air that is compressed by a compressor wheel flows into the air bleed ports. The compressed air that has passed through the air bleed ports flows through air bleed passages formed in an engine housing and the compressed air flow passages. Then, the compressed air reaches the terminal casing.

A gas turbine engine component includes an inner support structure surrounding an engine center axis and fixed to an engine static structure, an outer support structure spaced radially outward of the inner support structure, and a curved beam comprised of a plurality of curved beam spring segments that are positioned adjacent to each other to form a ring. The inner and outer support structures are coupled together around the curved beam to enclose the curved beam therebetween and form an assembly. A bearing is spaced radially inward of the assembly.

An assembly is provided for rotational equipment. This assembly includes a seal land and a seal element. The seal land extends circumferentially around and is rotatable about an axial centerline. The seal land includes a seal land surface. The seal element extends circumferentially around the axial centerline. The seal element includes a seal element surface and a seal element passage. The seal element surface is abutted against and is sealingly engaged with the seal land surface. The seal element passage extends through the seal element to an interface between the seal element surface and the seal land surface.

The invention relates to a threaded bearing housing and a side channel blower incorporating the same wherein the threaded bearing housing is installed on the outer casing element of the side channel blower. The bearing housing supports the outer ring of the blower's bearing. The bearing housing location is adjustable radially and along the axial axis of the side channel blower. These adjustments provide a variable positioning of the rotating components of the side channel blower. This adjustment reduces the necessary assembly tolerancing and allows the impeller's blade and the channel between the casing elements in which it rotates to be properly spaced apart for easy and facile installation and efficient operation.

An assembly for supporting and guiding a drive shaft for an aircraft turbine engine includes a bearing support having a cylindrical housing for receiving an outer ring of a bearing, and a device for rotationally retaining a first portion of the outer ring which is detached from its attachment to the bearing support. When the detachment occurs, the free outer peripheries of the first teeth of the first portion cooperate by wedge effect in the tangential direction with complementary inner surfaces of the housing of the bearing support and/or the free inner peripheries of the second teeth inside the housing cooperate by wedge effect in the tangential direction with complementary outer surfaces of the outer ring.

A turbo fluid machine includes a rotary shaft configured to rotate in one rotational direction, and a thrust foil bearing that includes: a plurality of bump foils each having a corrugated shape and a plurality of top foils each having a bearing surface that faces a thrust collar. Each bump foil is divided into an outer peripheral foil and an inner peripheral foil in a radial direction of the rotary shaft. Ridges on the outer peripheral foil are inclined in the other rotational direction of the rotary shaft while extending from an edge of the outer peripheral foil adjacent to an inner peripheral side toward an outer peripheral side, and the ridges on the inner peripheral foil are inclined in the other rotational direction while extending from an edge of the inner peripheral foil adjacent to the outer peripheral side toward the inner peripheral side.

A gas turbine engine includes: a fan that is arranged in front of a compressor and rotates in association with a rotating shaft; a casing including an inner shell accommodating the compressor, a combustor, and a turbine, and an outer shell arranged such that a bypass passage through which part of air supplied by the fan flows exists between the inner shell and the outer shell; bearings arranged inside the inner shell; an oil mist generator that is arranged outside the outer shell and generates oil mist by mixing oil with compressed air extracted through an extraction port of the compressor; an air pipe through which the compressed air extracted from the compressor is guided to the oil mist generator; and an oil mist pipe through which the oil mist generated by the oil mist generator is guided to the bearings. At least one of the air pipe and the oil mist pipe includes a heat exchanger that is arranged in the bypass passage and is cooled by the air flowing through the bypass passage.

A mixed-flow turbine wheel includes: a plurality of rotor blades disposed on a circumferential surface of the hub at intervals in a circumferential direction and configured such that each of the plurality of rotor blades has a leading edge which includes, in a meridional view, an oblique edge portion where a distance between the leading edge and an axis of the rotational shaft decreases from a tip side toward a hub side, and a sensor detection surface having a flat shape and being applied with a marking which is detectable by an optical sensor device. The sensor detection surface is formed on at least one of the circumferential surface of the hub or an edge portion of a reference rotor blade being one of the plurality of rotor blades, such that, in the meridional view, a trailing-edge side angle of two angles formed between the axis of the rotational shaft and a normal of the sensor detection surface is smaller than a trailing-edge side angle of two angles formed between the axis of the rotational shaft and a normal of the oblique edge portion.

A gas turbine including a turbine driven by a combustion gas, a gas turbine casing that includes an exhaust casing having an inner tube and an outer tube, a bearing that rotatably supports a shaft of the turbine, a bearing casing that holds the bearing, a support leg that supports the gas turbine casing, struts that connect the inner tube and the outer tube, and a first support and a second support that support the bearing casing on the inner tube. The first support is located on a side same as the support leg relative to the struts in a flow direction of the combustion gas. The struts are located between the first support and the second support. The first support is fixed to the inner tube and the bearing casing. The second support is fixed to the inner tube and is in slidable contact with the bearing casing.

Aircraft turbomachine comprising a casing, a fan, a compressor and a turbine and an epicyclic gear train comprising an input driven in rotation by the turbine, a first output stage configured to drive in rotation the compressor and a second output stage coupled to the first output stage and configured to drive in rotation the fan, the compressor being driven in rotation by the ring gear of the first output stage.