Abstract: A gas turbine includes a compressor, a turbine downstream of the compressor having stators, and a rotor connecting the compressor to the turbine. The rotor includes rotor cavities. A supply plenum containing a process by-product gas and a control valve is connected to at least one of the rotor cavities to supply the process by-product gas to at least one of the rotor cavities. A process for operating a gas turbine having a compressor and a turbine includes connecting the compressor to the turbine by a rotor, creating cavities in the rotor, and injecting a process by-product gas into at least one of the cavities. The process further includes regulating the flow of the process by-product gas into at least one of the cavities according to a pre-programmed parameter.

Abstract: An adaptor assembly for coupling a blade root of a turbine blade to a root slot of a rotor disk is described. The adaptor assembly includes a turbine blade having a blade root and an adaptor body having an adaptor root. The adaptor body defines a slot having an open end configured to receive the blade root of the turbine blade such that the adaptor root of the adaptor body and the blade root of the turbine blade are adjacent to one another when the blade root of the turbine blade is positioned within the slot. Both the adaptor root of the adaptor body and the blade root of the turbine blade are configured to be received within the root slot of the rotor disk.

Abstract: An airfoil for a turbine system is disclosed. The airfoil includes a first body having exterior surfaces defining a first portion of an aerodynamic contour of the airfoil and formed from a first material. The airfoil further includes a second body having exterior surfaces defining a second portion of an aerodynamic contour of the airfoil, the second body coupled to the first body and formed from a second material having a different temperature capability than the first material.

Abstract: A turbomachine includes a turbine section including a turbine inlet. A transition piece includes a transition piece inlet and a transition piece outlet. A ceramic matrix composite (CMC) bridge member links the transition piece outlet and the turbine inlet.

Abstract: A gas turbine inner flow path cover piece for a gas turbine a first turbine wheel and a second turbine wheel is provided is provided. The gas turbine inner flow path cover piece can include a main body having an first surface and a second surface, side pieces disposed on the first surface of the main body and mating pairs disposed on the second surface of the main body.

Abstract: Embodiments of the invention can provide systems, methods, and an apparatus for providing a magnetic seal. According to one embodiment, a system having a magnetic seal can be provided. The system can include a rotary machine having a first component and a second component. A magnetic seal can be mounted to the first component and positioned relative to the second component to provide a gap between the magnetic seal and the second component. The magnetic seal can include a first magnetic element and a compliant material adapted to adjust in response to a force exerted on the magnetic seal by a second magnetic element. The second magnetic element can be mounted to the second component so that the gap between the magnetic seal and the second component can be modified in response to the force exerted by second magnetic element on the magnetic seal.

Abstract: A turbine shroud assembly is disclosed, the shroud assembly including an outer shroud, at least one inner shroud attached to the outer shroud, and at least one discourager enclosed within the inner shroud. The discourager prevents the hot gas or steam in the turbine from having a direct line of access to the outer shroud. In one embodiment, one inner shroud is provided for the shroud assembly, with one discourager enclosed within the inner shroud, the discourager positioned offset from the inner shroud so as to extend past the inner shroud and into an inner shroud of a neighboring shroud assembly. In another embodiment, a plurality of inner shrouds are provided, each inner shroud enclosing a discourager, the discouragers being adjacent to each other within the inner shrouds and positioned offset from the inner shrouds so as to cover a gap between the inner shrouds.

Abstract: An adaptor assembly for coupling a blade root of a turbine blade to a root slot of a rotor disk is disclosed. The adaptor assembly may generally include an adaptor body having a root configured to be received within the root slot. The adaptor body may also define a slot having an open end configured to receive the blade root. The adaptor body may further define a channel. The adaptor assembly may also include a plate having an outwardly extending foot. The foot may be configured to be received within the channel. Additionally, the plate may be configured to cover at least a portion of the open end of the slot when the foot is received within the channel.

Abstract: Disclosed is an apparatus configured to seal with a turbine blade stage of a gas turbine. The apparatus includes an outer shroud coupled to an inner shroud and configured to circumferentially surround the turbine blade stage. The inner shroud is configured to circumferentially surround the turbine blade stage to seal with the turbine blade stage and includes an attachment element configured to be inserted into the outer shroud to couple the inner shroud to the outer shroud.

Abstract: A system for reinforcing a substrate includes a rotary device, a first guide connected to the rotary device, and a form positioned against the first guide. A reinforcement is supplied to wind around the form and against the first guide. A method for reinforcing a substrate includes connecting a first guide to a rotary device and positioning a form on a first side of the first guide. The method further includes winding a reinforcement around the form and against the first side of the first guide.

Abstract: A nozzle is disclosed for use in a turbine or compressor. In an embodiment, each of a plurality of vanes is supported by an outer shroud including a plurality of outer shroud segments disposed adjacent to adjoining segments in end-to-end relationship. Each segment includes a hole therethrough, dimensioned to receive a vane extension sleeve. This system may be used in conjunction with a modulated cooling system and may allow for improved removal for overhaul.

Abstract: A turbomachine includes a turbine section including a turbine inlet. A transition piece includes a transition piece inlet and a transition piece outlet. A ceramic matrix composite (CMC) bridge member links the transition piece outlet and the turbine inlet.

Abstract: A blade assembly for a rotor includes an attachment section operably connectable to a rotor, and an airfoil section. At least one retainer extends in a substantially tangential direction at least partially through the airfoil section and the attachment section to secure the airfoil section to the attachment section. A method of assembling a rotor assembly includes inserting at least one retainer in a substantially tangential direction at least partially through an attachment section of a blade assembly and an airfoil section of the blade assembly, thereby securing the airfoil section to the attachment section. The blade assembly is then secured to a rotor.

Abstract: A sealing device for sealing a gap between a dovetail of a bucket assembly and a rotor wheel is disclosed. The sealing device includes a cover plate configured to cover the gap and a retention member protruding from the cover plate and configured to engage the dovetail. The sealing device provides a seal against the gap when the bucket assembly is subjected to a centrifugal force.

Abstract: In one embodiment, a compressor discharge casing of a gas turbine engine is designed to receive discharge air from a compressor and to direct a first portion of the discharge air into a combustor of the gas turbine engine and a second portion of the discharge air into a nozzle assembly of a gas turbine to cool components of the gas turbine. A heat transfer device is configured to receive a cooling fluid and to cool the second portion of the discharge air with the cooling fluid.

Abstract: In exemplary embodiments, a nozzle can include a first flow wall, a second flow wall and a vane disposed between the first and second flow walls, wherein the vane is mechanically coupled to the first flow wall and in contact with the second flow wall.

Abstract: The present application describes a locking spacer assembly for use with a groove in a rotating disk. The locking spacer assembly may include a locking spacer with a leg and a wedge tool in contact with the leg so as to pull the leg inward and into the groove.

Abstract: A turbine shroud assembly is disclosed, the shroud assembly including an outer shroud, at least one inner shroud attached to the outer shroud, and at least one discourager enclosed within the inner shroud. The discourager prevents the hot gas or steam in the turbine from having a direct line of access to the outer shroud. In one embodiment, one inner shroud is provided for the shroud assembly, with one discourager enclosed within the inner shroud, the discourager positioned offset from the inner shroud so as to extend past the inner shroud and into an inner shroud of a neighboring shroud assembly. In another embodiment, a plurality of inner shrouds are provided, each inner shroud enclosing a discourager, the discouragers being adjacent to each other within the inner shrouds and positioned offset from the inner shrouds so as to cover a gap between the inner shrouds.

Abstract: Embodiments of the invention can provide systems, methods, and an apparatus for providing a magnetic seal. According to one embodiment, a system having a magnetic seal can be provided. The system can include a rotary machine having a first component and a second component. A magnetic seal can be mounted to the first component and positioned relative to the second component to provide a gap between the magnetic seal and the second component. The magnetic seal can include a first magnetic element and a compliant material adapted to adjust in response to a force exerted on the magnetic seal by a second magnetic element. The second magnetic element can be mounted to the second component so that the gap between the magnetic seal and the second component can be modified in response to the force exerted by second magnetic element on the magnetic seal.

Abstract: Turbine blade assemblies of a turbine include airfoils that are mounted on bases. The leading and/or trailing edges of the bases are provided with curved portions. Likewise, curved portions may be provided on leading and/or trailing edges of the angle wings of a turbine blade assembly. Also, curved portions may be provided on the leading and/or trailing edges of nozzle assemblies of a turbine.