A runner for a Pelton turbine has a multiplicity of buckets which are arranged on a disk-shaped wheel and which each have a bucket root directly adjoining the wheel and a bucket body. The disk-shaped wheel, with the bucket roots, is formed in one piece from a forged material. Separately produced bucket bodies, formed of three separate parts per bucket, are connected by welding to the respectively associated bucket root. A first part encompasses the entire part of the bucket body that extends radially beyond the bucket root, and two other parts, axially adjacent to the bucket root, encompass the rest of the bucket body.

Through dividing all blades into four or more blade groups including a certain number, which is three or more, of the blades, the blade located in the rearmost portion of each blade group in a direction of rotation is selected as a main blade, and remaining blades are selected as auxiliary blades, the length of each of the auxiliary blades is set to be shorter than the length of the main blade, and corresponding inner edge portions are positioned to the front, in the direction of rotation, of a normal line that passes through an outer edge portion of the blade, and an extension line of a chord line that connects the outer edge portion and the inner edge portion of the blade to one another are made to intersect with the main blade that is adjacent to the front in the direction of rotation.

Through dividing all blades into four or more blade groups including a certain number, which is three or more, of the blades, the blade located in the rearmost portion of each blade group in a direction of rotation is selected as a main blade, and remaining blades are selected as auxiliary blades, the length of each of the auxiliary blades is set to be shorter than the length of the main blade, and corresponding inner edge portions are positioned to the front, in the direction of rotation, of a normal line that passes through an outer edge portion of the blade, and an extension line of a chord line that connects the outer edge portion and the inner edge portion of the blade to one another are made to intersect with the main blade that is adjacent to the front in the direction of rotation.

A guide vane for use in a gas turbine engine fan section has an airfoil extending between a radially inner platform and a radially outer platform. The radially inner platform has a radially outwardly facing surface from which the airfoil extends and a radially inwardly facing underside. The airfoil has a trailing edge extending to a leading edge. The underside is attached to a mount bracket and a main rib extending from the underside of the platform adjacent the trailing edge and in a direction generally towards the leading edge, and merging into a top surface on the mount bracket. A pair of shoulders is formed on each of two circumferential sides of the rib. Each of the shoulders is spaced from each other at a point on the shoulders connected into the top surface of the mount bracket. The shoulders extend circumferentially toward each other and the under surface.

Systems and methods of coupling a nose cone to a turbine machine. Nose cone assembly weight and coupling difficulty are each reduced by eliminating the number of bolts used to mount the nose cone to the turbine machine, as well as the support or retaining ring. The disclosed nose cone comprises a plurality of hub mounting elements including one or more flexible spring flanges, one or more bayonet flanges, and one or more pilot flanges, each configured to engage a respective portion of the turbine machine.

Systems and methods of coupling a nose cone to a turbine machine. Nose cone assembly weight and coupling difficulty are each reduced by reducing or eliminating the number of bolts used to mount the nose cone to the turbine machine, as well as the support or retaining ring. The disclosed nose cone comprises a plurality of hub mounting elements including one or more bayonet flanges, two or more apertures defined by a flange forming an annular hub mating surface of the nose cone and configured to receive an fastener therethrough, and one or more pilot flanges.

Systems and methods of coupling a nose cone to a turbine machine. Nose cone assembly weight and coupling difficulty are each reduced by reducing or eliminating the number of bolts used to mount the nose cone to the turbine machine, as well as the support or retaining ring. The disclosed nose cone comprises a plurality of hub mounting elements including one or more bayonet flanges, two or more apertures defined by a flange forming an annular hub mating surface of the nose cone and configured to receive an fastener therethrough, and one or more pilot flanges.

Systems and methods related to floating powerhouse for hydropower turbine systems are presented. A turbine system may be coupled to floating powerhouse that can include a floating platform. A pressurized water delivery system can be coupled to the floating powerhouse and can accommodate vertical and/or horizontal movement of the floating power house. The pressurized water delivery system can include a segmented penstock coupling the turbine to an intake, and individual segments of the penstock can be free to rotate about a substantially horizontal axis, such that in response to variations in a tailwater height, the floating platform rising and falling does not disrupt fluid flow from a fluid source.

Systems and methods related to floating powerhouse for hydropower turbine systems are presented. A turbine system may be coupled to floating powerhouse that can include a floating platform. A pressurized water delivery system can be coupled to the floating powerhouse and can accommodate vertical and/or horizontal movement of the floating power house. The pressurized water delivery system can include a segmented penstock coupling the turbine to an intake, and individual segments of the penstock can be free to rotate about a substantially horizontal axis, such that in response to variations in a tailwater height, the floating platform rising and falling does not disrupt fluid flow from a fluid source.

Systems and methods related to linear turbine systems are presented. Each embodiment described herein may be designed as a single-stage, linear, impulse turbine system. In an embodiment, a linear turbine includes a first shaft extending along a first axis; a second shaft extending along a second axis, the second axis being separated from and substantially parallel to the first axis; a first plurality of buckets to travel a first continuous path around the first shaft and the second shaft along a first plane, the first path including a first substantially linear path segment between the first axis and the second axis; and a nozzle configured to direct a first fluid jet to contact the first plurality of buckets in the first linear path segment.