Wind-funneling systems for gas turbines are disclosed. Air travels through a wind funnel where it is compressed, and then flows into a gas turbine that is fueled by a hydrocarbon fuel source such as natural gas. The wind funnels have a controlled volume with an opening facing the wind that concentrates air power and energy and directs the force into a constricted outlet that feeds into the gas turbine. Compressed air from the wind funnel may enter the front compressor section of the gas turbine at relatively high density and force. As a result, the gas turbine does not have to use as much energy to pull the air in, which creates fuel savings. The compressed air from the wind funnel then flows to the combustion section of the gas turbine where oxygen from the wind-compressed air is used to combust the hydrocarbon fuel supplied to the gas turbine. The wind funnel is thus used to generate compressed air that may increase efficiency in the front compressor section of the gas turbine, and serves as an oxygen source in the combustion section of the gas turbine.

A control ring for a stage of variable-pitch vanes for a turbine engine includes at least one member for bearing on a casing and means for fixing the member. The member includes a bushing with an axial bore for the passage of the member or an element for supporting the member. A through-slot opens into the bore and allows for substantial radial deformation of the bushing. The member further includes an outer thread for screwing the bushing into a complementary thread of a hole in the body, thereby deforming the bushing. The member or support can be mounted and moved inside the bore, to a second position, in which the bushing is radially constrained and is tightly mounted on the member or support, which is thus immobilized in relation to the bushing.

A connecting element (1) interacting with a fan blade (50) to transfer torque of a drive to the fan blade (50). An attachment portion (2) connects the connecting element (1) with the fan blade. The attachment portion (2) forms an outer edge portion (4) adjoining the outer contour of the connecting element (1). The attachment portion (2) cross-sectional shape is designed to taper toward the outer edge in at least some portions.

Turbine components are disclosed including a component wall defining a constrained portion, a manifold having an impingement wall, and a post-impingement cavity disposed between the manifold and the component wall. The impingement wall includes a wall thickness and defines a plenum and a tapered portion. The tapered portion tapers toward the constrained portion and includes a plurality of impingement apertures and a wall inflection. The wall inflection is disposed proximal to the constrained portion, and the tapered portion is integrally formed as a single, continuous object. The wall inflection may include an inflection radius of less than about 3 times the wall thickness of the impingement wall, or the tapered portion may include a consolidated portion with the impingement wall extending across the plenum. A method for forming the turbine component is also disclosed, including forming the tapered portion as a single, continuous tapered portion by an additive manufacturing technique.

A system includes an exhaust collector tunnel (32) configured to mount inside an exhaust collector (30) of a gas turbine (12). The exhaust collector tunnel (32) has a tunnel wall (33) configured to extend around a turbine shaft (17, 19) of the gas turbine (12). The tunnel wall (33) has a variable diameter (98) along at least a portion of a length of the exhaust collector tunnel (32).

A compressor includes a shaft extending in axial directions thereof, an impeller secured to one end of the shaft, a first bearing action member provided at the one end of the shaft, a second bearing action member provided at an opposite end of the shaft that is opposite to the one end of the shaft, a first bearing that acts on the first bearing action member and supports the first bearing action member in one axial direction of the axial directions and in a radially inward direction of the shaft, and a second bearing that acts on the second bearing action member and supports the second bearing action member in another axial direction, which is opposite to the one axial direction, and in the radially inward direction of the shaft.

Aspects of the disclosure are directed to an apparatus comprising a first section, and a second section coupled to the first section, wherein the second section is configured to substantially coincide with an edge of a seal and includes a pre-tapered edge.

A face seal assembly for a gas turbine engine includes a seal body having a seal face defining a contact area disposed between tapered sides. The seal body defines an axial width between a back surface of the seal body and the seal face. A decrease in the axial width from wear increases the contact area. A bearing assembly and method are also disclosed.

The present invention enables machining to be easily performed and reduces stress concentration on a machined hole that is formed in a cylindrical member. Recesses (2) recessed in the depth direction of a machined hole (1) are formed on circumferential side-portions of the machined hole 1 formed in a cylindrical member (10). In each of the recesses (2), a part of the opening edge is formed to be a circular arc portion (2a) that has a circular arc shape, the bottom is formed to be gradually shallowed by an inclined surface (2c) toward an opened portion (2b) in which the circular arc shape is opened, from a part along the circular arc portion (2a), and the circular arc portion (2a) is disposed toward the machined hole (1).

A variable nozzle unit is used in a turbine having a gas inflow passage which is sandwiched between a first flow passage wall surface and a second flow passage wall surface facing each other and through which a gas flowing from a scroll flow passage into a turbine impeller flows. The variable nozzle unit includes nozzle vanes, each of which is rotatably supported on both sides thereof by the first flow passage wall surface side and the second flow passage wall surface side and pivots about a pivotal axis parallel to the rotational axis of the turbine impeller in the gas inflow passage. An end face of the nozzle vane is formed with a cut face that is located closer to a leading edge than the pivotal axis, is cut out such that a gap between the cut face and the second flow passage wall surface is greater than other regions, and intersects the leading edge.