| Patent application number | Description | Published |
|---|
| 20100254805 | GAS TURBINE INNER FLOWPATH COVERPIECE - 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. | 10-07-2010 |
| 20110027064 | SYSTEM AND METHOD FOR MODIFYING ROTOR THRUST - 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. | 02-03-2011 |
| 20110052387 | NON-AXISYMMETRIC AIRFOIL PLATFORM SHAPING - 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. | 03-03-2011 |
| 20110062671 | SYSTEMS, METHODS, AND APPARATUS FOR PROVIDING A MAGNETIC SEAL - 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. | 03-17-2011 |
| 20110085899 | SHROUD ASSEMBLY WITH DISCOURAGER - 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. | 04-14-2011 |
| 20110164983 | Locking Spacer Assembly - 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. | 07-07-2011 |
| 20110171018 | TURBINE NOZZLE ASSEMBLY - 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. | 07-14-2011 |
| 20110271689 | GAS TURBINE COOLING - 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. | 11-10-2011 |
