An apparatus and method for assembling an inducer assembly for inducing a rotation on an airflow passing within a turbine engine. The inducer assembly can provide a volume of fluid from a compressor section to a turbine section of the engine. The inducer assembly can include the combination of separate segments to form an annular inducer.

A method of assembling a gas turbine engine is disclosed herein. The method comprises providing a set of standard axial compressor stages. Each axial compressor stage included in the set of standard axial compressor stages includes a rotor having a plurality of blades configured to rotate about an axis and a stator having a plurality of stator vanes.

A nozzle blade for a turbine engine includes a blade body in which at least one through-cavity is provided extending between an inner end of the blade and an outer end of the blade and housing, respectively, a first and a second liner, the first liner extending along a trailing edge of the blade, the second liner extending along a leading edge of the blade, wherein each of the first and second liners includes an intertwining system suitable for linking the first liner to the second liner, independently of the blade body.

A manufacturing method of a casing, the manufacturing method includes a step of manufacturing a plurality of metal members which are components constituting the casing including a casing body having a tubular shape that extends with an axis as a center; a step of arranging the plurality of metal members according to the casing to be formed; and a step of forming the casing by welding the plurality of metal members to each other, in which in the step of manufacturing the metal members, the plurality of metal members are manufactured by at least two kinds of manufacturing methods among forging, steel plate processing, casting, and a fused metal deposition method.

A turbo shield with a slit, wherein the slit is configured to allow an inner diameter across the turbo shield to increase and decrease without altering the properties of fibers associated with the turbo shield.

The invention relates to a planetary gear reducer (21) for an aircraft turbine engine (1), the reducer (21) comprising a sun gear (30) and a ring gear (33) which are centred on a longitudinal axis X and a planet carrier (32) which carries at least one planet gear (31) rotatably mounted about a planet axis A parallel to the longitudinal axis X, the sun gear (30) being rotatable about the longitudinal axis, the planet gear (31) meshing both with the sun gear (30) and the ring gear (33), the planet carrier (32) being movable about the longitudinal axis and the ring gear (33) being rotationally fixed. According to the invention, the reducer (21) comprises an electric machine (50) integrated therewith and which comprises a rotor (51) mounted on the planet carrier (32) in such a way as to be rotated about the longitudinal axis X and a stator (52) mounted on the ring gear (33).

A turbine blade tip, turbine blade and method where improved cooling is made possible by an improved cooling structure with cooling air holes inside a depression in a blade tip and a special arrangement of multiple cooling air holes which are supplied by a single cooling air channel inside a wall.

An energy storage includes a first container including an inner space, a plurality of pressure vessels for compressed air that are stacked in rows inside the inner space of the first container, a tank containing a heat transfer fluid arranged inside the inner space of the first container, a compressor adapted to compress air, and a plurality of pneumatic ducts for compressed air connected to the compressor. The plurality of pneumatic ducts includes a plurality of heat exchangers adapted to enable a heat exchange between compressed air contained in the plurality of pneumatic ducts and heat transfer fluid contained inside the tank. The plurality of pneumatic ducts is connected to the plurality of pressure vessels supplying pressure vessels with compressed air, an electric turbine connected by the plurality of pneumatic ducts with the plurality of pressure vessels supplying compressed air for rotating the electric turbine to generate electric current.

A system (10) includes a modular exhaust collector (30) configured to be arranged in a first orientation (50) or a second orientation (114, 116). The modular exhaust collector (30) is configured to receive an exhaust flow along an inlet axis (54), to direct the exhaust flow along a first direction (36) through an outlet (58) when in the first orientation (50), and to direct the exhaust flow along a second direction (114, 116) through the outlet (58) when in the second orientation (114, 116). The modular exhaust collector (30) includes an exhaust passage (64) to receive the exhaust flow, a plurality of compressor discharge (CD) ports (72), a plurality of flow ports (76), a bottom face (84) opposite the outlet (58) with a first drain (88), and a first side wall (82) with a second drain (88) between the bottom face (84) and the outlet (58). Each CD port (72) is disposed a first radial distance (118) from the inlet axis (54), and each flow port (76) is disposed a second radial distance (130) from the inlet axis (54).

A fan including a hub having a central axis; a plurality of interlock blade elements connected to the hub by means of an interlock such that each interlock blade element is prevented from moving in a radial direction with respect to the hub; and an end blade element positioned on the hub between two interlock blade elements, the end blade element being fixed to the hub to prevent movement of each interlock blade element in a circumferential direction of the hub; wherein each interlock blade element is connected to the hub by a first blade movement in a radially inward direction with respect to the hub followed by a second blade movement in a circumferential direction of the hub to establish the interlock.