A thermally responsive flow meter may comprise a coil and a plate coupled to the coil. The plate may define a first airflow aperture. The plate may translate in a circumferential direction in response to a thermal expansion of the coil. The thermally responsive flow meter may regulate the flow of air through a second airflow aperture.

A liquid fuel cartridge assembly for a gas turbine combustor comprising an elongated stem provided with a fuel injector tip at an aft end of said stem, said injector tip provided with a pilot fuel passage extending to a pilot fuel orifice; a plurality of air channels surrounding said pilot fuel passage and in communication with plural air holes; an annular main fuel passage surrounding said plurality of air channels and in communication with plural fuel exit holes; and a plurality of substantially radially oriented air supply holes in said stem upstream but proximate to a forward end of said tip in communication with said plurality of air channels.

A screw system including a plurality of segmented blades. Each blade segment of the plurality of blade segments including a mounting portion and a vane portion. The mounting portion, having a helical length, for removably attaching the blade segment. The vane portion extending from the mounting portion along the helical length thereof. The vane portion having a front surface that is not parallel to a back surface from the mounting portion to a tip of the blade segment, along the helical length.

A screw rocket nozzle may include a disc shaped nozzle body and a spiral flow path having an inlet and an outlet. In some examples the flow path is radial with the inlet positioned at a higher pressure region than the outlet.

A guide vane within an annular inlet duct of a gas-turbine engine provides for generating swirl within an annular inlet duct so as to provide for reducing the rate of deceleration of the inlet air flow within the annular inlet duct while providing for diffusion of the meridional component of velocity thereof.

A tip rail cooling insert for attaching into a tip rail pocket in a tip rail of a turbine blade is disclosed. The insert includes a first inner layer defining at least one first insert cooling channel therein, the first inner layer including a pair of spaced legs defining a first coolant collection plenum with at least the tip rail pocket for directing coolant from at least one internal cooling cavity in the turbine blade to the at least one first insert cooling channel. Each of the pair of spaced legs has an angled outer end configured to accommodate rounded inner corners of the tip rail pocket. A first outer layer is on a first side of the first inner layer, and a second outer layer is on a second side of the first inner layer.

A turbocharger contains a turbine housing having an accommodating region for a turbine rotor disk of the turbocharger, which accommodating region is arranged centrally with respect to a turbine housing axis, and a turbine spiral channel, which tapers helically toward the accommodating region. A wastegate valve, having a spindle arm and a valve plate arranged on the spindle arm, or a variable exhaust-gas guiding device, having bearing disks and guide vanes, is arranged in the turbine housing. At least one of the: turbine housing, spindle arm and valve plate, or bearing disks and guide vanes, has a steel material for high-temperature applications. The material composition of which contains, in addition to iron, Fe, at least the following alloying constituents in amounts within the specified limits in weight percent: carbon: 0.4-0.5%; silicon: 1.25-1.75%; manganese: 3.0-12.0%; chromium: 19.5-20.5%; nickel: 5.0-6.0%; niobium: 1.00-1.5%. The material composition ensures sufficient temperature resistance of the components.

The invention relates to a de-icing device for an air intake of an aircraft turbojet engine nacelle extending along an X-axis in which an air stream flows from upstream to downstream, the air intake having an inner cavity, extending annularly about the X-axis, which comprises an inner wall facing the X-axis and an outer wall which is opposite the inner wall, the walls being connected by a leading edge, the de-icing device comprising at least one injector for injecting a stream of hot air into the inner cavity, the injector comprising a nozzle extending along a nozzle axis, the nozzle being configured to inject a stream of hot air having a dissymmetry along the nozzle axis.

The present invention belongs to the technical field of turbine cooling of aero-engine and gas turbine, and relates to the honeycomb-like helically cavity cooling structure of turbine blade. The honeycomb-like helically cavity cooling structure of turbine blade includes hollow turbine blade, honeycomb-like helically cavity and pin fins. Some cooling channels are arranged inside the hollow the hollow turbine blade, the cooling gas flows through the tunnels and cools the blade. Multi-arrays of honeycomb-like helically cavity are arranged in the blade wall, for cooling gas to enter and convective cooling. A cylindrical pin fin is arranged in the center of the honeycomb-like helically cavity. In each unit, the inlet hole and film hole are located on both sides of the blade wall, and the center lines of them are parallel in the same vertical plane.

The present invention relates to a disc turbine for converting the energy associated with a fluid into mechanical energy. The turbine (1) comprises a housing and a rotor (4) inside said housing (3) which can rotate with respect to it about a rotation axis (100). The rotor (4) comprises a plurality of disc elements (11A, 11B) coaxial with said axis. The turbine is characterized in that it comprises a distributor (5) with a distribution wall (5A) which at least partially surrounds the discs. Such a wall (5A) is arranged inside said housing (3) so as to define a diffusion chamber (7) with the housing itself, which chamber at least partially surrounds the distribution wall (5A). The latter comprises a plurality of nozzles (6A, 6B, 6C, 66A, 66B, 66C), each of which is provided with an inlet section (61) communicating with said chamber (7), an outlet section (62) adjacent to the discs (11A, 11B), and a converging portion (615) which accelerates said fluid towards said outlet section (62).