A rotating machine system can include a rotating machine. The rotating machine system can include a housing. The housing can include an inner surface. The housing can surround at least a portion of the rotating machine. The inner surface of the housing can be spaced from the rotating machine such that a space is defined therebetween. The rotating machine system can include one or more super elastic wires. The one or more super elastic wires can be positioned in the space and can be operatively connected to the rotating machine and the inner surface of the housing. The one or more super elastic wires can reduce vibration within the rotating machine system.

A turbomachine is provided. The turbomachine includes a casing, a first airfoil disposed inside the casing such that a fluid passes through the first airfoil while flowing through the casing, a first inner frame coupled to a radially inner end of the first airfoil, a first inner wing protruding from the first inner frame in an axial direction of the casing, a second airfoil disposed inside the casing and between adjacent first airfoils in a flow direction of a fluid, a second inner frame coupled to a radially inner end of the second airfoil and disposed adjacent to the first inner frame, a second inner wing protruding from the second inner frame along the axial direction of the casing and disposed adjacent to the first inner wing, and a plurality of rim seals disposed between the first inner wing and the second inner wing, arranged at intervals along a circumferential direction of the casing, and configured such that cooling air present inside the first and second inner wings in a radial direction flows into each rim seal through an ingress port, passes through each rim seal, and flows out through an egress port, wherein a region on a downstream side of the first airfoil in the flow direction of the fluid flowing through the casing is divided into a first region having a relatively high pressure and a second region having a relatively low pressure, a first flow passage and a second flow passage are provided in a gap between each rim seal, the first flow passage is configured such that a size in the circumferential direction increases from the ingress port to the egress port and the egress port communicates with the first region, and the second flow passage is configured such that a size in the circumferential direction decreases from the ingress port to the egress port and the egress port communicates with the second region.

A turbine exhaust unit supporting device that supports a turbine exhaust unit is provided. The turbine exhaust unit supporting device installed at a rear side of a turbine casing to support a turbine exhaust unit through which exhaust gas passing through a turbine is discharged, the supporting device includes a casing supporting block unit installed on an outer circumferential surface of the turbine casing, an exhaust unit supporting block unit spaced apart from the casing supporting block unit and installed on an outer circumferential surface of the turbine exhaust unit, and a rotary coupler including a first end rotatably coupled to the casing supporting block unit and a second end rotatably coupled to the exhaust unit supporting block unit.

A blade for a turbo machine is provided. The blade for a turbo machine includes an airfoil body extending in a radial direction and including a suction side surface and a pressure side surface opposite to the suction side surface with respect to a circumferential direction extending across the radial direction, and a snubber structure including a first snubber element protruding in the circumferential direction from the suction side surface of the airfoil body and a second snubber element protruding in the circumferential direction from the pressure side surface of the airfoil body, wherein the first snubber element is connected to the suction side surface of the airfoil body by a concave curved first transition portion having a first radius, and the second snubber element is connected to the pressure side surface of the airfoil body by a concave curved second transition portion having a second radius, the first radius being smaller than the second radius.

A turbine nozzle assembly system includes a plurality of nozzle sets, where each nozzle set forms an annulus. The nozzles in each set include an inner endwall and an outer endwall that include joint openings to receive the respective endwall mount ends of an airfoil. The airfoils across the plurality of nozzle sets have an inner endwall mount end and an outer endwall mount end that are identical amongst the plurality of nozzle sets. A wing portion of the airfoil has a selected wing shape that is identical within the respective nozzle set but different amongst the plurality of nozzle sets. In this manner, the endwalls can be removed from an airfoil and replaced with an airfoil having a different wing shape that provides a different pairwise throat area. The system allows changing of a pairwise throat area for a nozzle set without replacing the entirety of each nozzle.

A rotary machine seal assembly (200) includes seal segments (102) configured to circumferentially extend around a rotor (108) between a stator (106) and the rotor (108) of a rotary machine. One or more seal segments include a shoe plate (110, 410, 710, 910), a seal base (112, 412, 712, 912), and at least one intermediate member (114, 414, 714). The shoe plate is disposed along the rotor. The seal base is disposed radially outward of the shoe plate. At least one intermediate member is coupled to and disposed between the seal base and the shoe plate. The at least one intermediate member includes an actuator portion (302, 402, 702, 902) having first coefficient of thermal expansion and a constrictor portion (304, 404, 704, 904) having a different, second coefficient of thermal expansion. The at least one intermediate member is configured to move the shoe plate from a radially outward position to a radially inward position with respect to the rotor responsive to the at least one intermediate member undergoing a temperature change.

An accelerated and/or redirected flow arrangement, optimally serving as a wildlife and/or debris excluder (WDE), is used in combination with a turbine-like device having an inlet end and an outlet end for fluid flowing therethrough, e.g., a hydro-turbine. The arrangement includes at least a forward part designed to be placed in front of a fluid inlet of a turbine-like device and configured to produce at least one of the following effects on the fluid: (a) imparting a re-direction of the fluid; and/or (b) accelerating the flow velocity of the fluid, as it flows through the forward part. Turbine-like devices having both a forward part and a rearward part of flow arrangement are disclosed, as well as a method of enhancing turbine performance.

A gas turbine engine with a rotor comprising a turbine and compressor, mounted in a housing surrounding the rotor. The rotor rotates on one or more hydro bearings, the profiles of the outer surface of the rotor and the inner surface of the housing generating the hydro bearing(s). A combustion chamber is formed within the housing, and the combustion products of the fuel/air mixture are directed from the combustion chamber to the turbine. The housing and rotor are formed by an additive manufacturing process in a single procedure, with the rotor enclosed within the housing, and unsupported by any mechanical connections. A gas turbine respiratory ventilator system is described using a compressed oxygen flow to power the turbine which rotates the centrifugal blower for generating the air flow for respiration of the patient. The oxygen exhausted from the turbine can then be used to supplement the air flow.

A turbomachine part or assembly of parts includes a first blade and a second blade, and platform from which the first blade and the second blade extend, The platform has, between a pressure side of the first blade and a suction side of the second blade a non-axisymmetric surface defining at least one fin, and a transverse section of the fin is asymmetric. The transverse section includes a first and a second oblique faces joining at a dorsal edge, the first oblique face is oriented toward the pressure side of the first blade, the second oblique face is oriented toward the suction side of the second blade, and the first oblique face has a steeper slope than the second oblique face.

A gas expander includes a scroll casing, an impeller accommodated in the scroll casing and rotationally driven to a first side in a circumferential direction around a central axis by the gas flowing while expanding from an outside to an inside in a radial direction, a diffuser disposed on a first side in an axial direction with respect to the scroll casing and forming a flow path of the gas discharged from the impeller to the first side in the axial direction and swirling to the first side in the circumferential direction, and a vortex preventer provided in the diffuser, in which the vortex preventer includes a profile rectifying blade portion, which is curved or inclined to a second side in the circumferential direction from the first side toward a second side in the axial direction, at least in a portion of the second side in the axial direction.