|| List of recent Gas Turbine-related patents
|Localized repair of superalloy component|
A method for repairing a damaged portion (144) of a brazed-on gas turbine engine seal (142) without the need to remove and to replace the entire seal. The damaged portion is removed to reveal a repair surface (146) of the underlying superalloy material, and a new seal structure (148) is formed by an additive manufacturing processes using a laser beam (124) to melt a powder (116) including superalloy material (116′) and flux material (116″).
|Cooling structures in the tips of turbine rotor blades|
A turbine rotor blade for a gas turbine engine is described. The turbine rotor blade includes an airfoil that includes a tip at an outer radial end.
|Cooling structures in the tips of turbine rotor blades|
A turbine rotor blade used in a gas turbine engine, which includes an airfoil having a tip at an outer radial edge, is described. The airfoil includes a pressure sidewall and a suction sidewall that join together at a leading edge and a trailing edge of the airfoil, the pressure sidewall and the suction sidewall extending from a root to the tip.
In a turbine vane and a gas turbine, an outer shroud is fixed to one end of a vane body formed in a hollow shape, an inner shroud is fixed to the other end thereof, and a partition plate is fixed to the inner portions of the vane body, the outer shroud, and the inner shroud, so that a cavity is formed so as to be continuous between the partition plate and the group of the vane body, the outer shroud, and the inner shroud. Then, the vane body, the outer shroud, and the inner shroud are provided with a plurality of cooling holes, and the partition plate is provided with a plurality of penetration holes.
|Exhaust plenum for gas turbine|
An exhaust plenum for connection to an exhaust outlet portion of a gas turbine for receiving turbine exhaust gas. The exhaust plenum includes a first wall.
|Turbine shroud cooling assembly for a gas turbine system|
A turbine shroud cooling assembly for a gas turbine system includes an inner shroud component disposed within a turbine section of the gas turbine system and proximate a hot gas path therein, wherein the inner shroud component includes a base portion in direct contact with the hot gas path. Also includes is a rib protruding radially away from the base portion and disposed proximate at least one cavity configured to receive a cooling flow from a cooling source, wherein the cooling flow passes through the main passage of the rib for cooling the inner shroud component..
|Method for pulling a bearing body off the rotor of a gas turbine and tubular shaft extension|
A method is provided for pulling a bearing body off the rotor of a gas turbine having a casing, while the casing is closed. The method includes fixing a shaft extension on the relevant end of the rotor.
|Gas turbine engine components with cooling hole trenches|
An engine component includes a body having an interior surface and an exterior surface; a cooling hole formed in the body and extending from the interior surface; and a nonconcave trench extending from the cooling hole to the exterior surface of the body in a downstream direction such that cooling air flow from within the body flow through the cooling hole, through the trench, and onto the exterior surface.. .
|Nozzle with extended tab|
A nozzle feature for sealing leakage in a gas turbine engine having a plurality of nozzle segments within the turbine engine which includes a radially inner band, a radially outer band, at least one vane disposed between the radially inner and outer bands, the radially inner band having a first tab formed in said inner band extending radially downwardly from at least one of first and second circumferential ends.. .
A roller bearing, in particular of a gas turbine, comprising a number of rolling elements (4) located between an inner ring (2) and an outer ring (3),a housing component (8) to which the outer ring (3) is non-rigidly attached, wherein the outer ring (3) is designed in a single piece and comprises a track section (7) that abuts against the housing component (8), a spring section (9) comprising radial inner and radial outer spring rods (12,14) and a flange (10) that is bolted to the housing component (8), wherein the radial inner spring rods (12) are connected together with the radial outer spring rods (14) by way of a single connecting ring (13).. .
|System of support thrust from wasted exhaust|
Systems and methods for influencing thrust of a gas turbine engine are disclosed. A system includes a plurality of pipes positioned at an exhaust nozzle of the gas turbine engine.
|Self-sealing tube for a gas turbine secondary air system|
A self-sealing and self-centering tube made of metal, having a tube axis, and configured to form part of a secondary system in a gas turbine engine is disclosed herein. The self-sealing and self-centering tube includes a tube having a tube wall, an inward end, an outward end, a first seal section located towards the inward end, a second seal section towards the outward end, and an extension section located between the second seal section and the outward end..
|Method of detecting shaft break|
A method of detecting shaft break in a gas turbine engine having a shaft system. The shaft system including a shaft that couples a compressor and a turbine.
|Fuel control system for a gas turbine engine|
A fuel valve for a gas turbine engine includes a passageway configured to direct a fuel to the engine and a flow restriction positioned in the passageway. The fuel valve may also include a first pressure sensor coupled to the passageway upstream of the restriction through an upstream port, and a second pressure sensor coupled to the passageway downstream of the restriction through a downstream port.
|Chamber-bottom baffle, combustion chamber comprising same and gas turbine engine fitted therewith|
A baffle for the bottom of a combustion chamber of a gas turbine engine is disclosed. The baffle includes a flat portion of wall with an opening for an injector of the combustion chamber to pass through, two longitudinal edges for the assembly to two adjacent baffles and two transverse edges.
|Gas turbine engine shaft bearing configuration|
A gas turbine engine includes a core housing that has an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. The shaft supports a compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path.
|Gas turbine system having a plasma actuator flow control arrangement|
A gas turbine system having a plasma actuator flow control arrangement including a compressor section for compressing an airstream, wherein the compressor section includes at least one inlet guide vane for controlling the airstream proximate an inlet portion of the compressor section. Also included is a turbine inlet assembly for ingesting the airstream to be routed to the compressor section.
|Flex-fuel hydrogen generator for ic engines and gas turbines|
To improve thermal efficiency of a mobile vehicle or a distributed power generator, portion of the reformate from the storage vessels is used to mix with the primary fuels and air as part of a lean burn fuel mixture for the engine/gas turbine. Also, this on-board flex-fuel h2 generator can provide h2 to regenerate the nox and diesel particulate traps for diesel engines, and/or it can provide h2 for a mobile or a portable fuel cell power generator..
|Method and device for modifying a secondary air system in a gas turbine engine|
A method and device for modifying a gas turbine engine is disclosed herein. The method for modifying a gas turbine engine includes accessing a first outward end of a first tube installed in the gas turbine engine, the first tube having a tube axis.
|System and method for controlling and diagnosing a combined cycle power plant|
A system and method in a combined cycle power plant includes a processor modeling plant level performance by considering the interrelation between outputs of the gas turbine and the steam turbine. The model can be computational, predictive, or both.
|Electrospark deposition process and system for repair of gas turbine|
A system and method for repairing a metal substrate includes an electrospark device and an electrode removably supported in the electrode holder. The electrospark device applies a coating of a material when placed into contact with the metal substrate.
Vibration damping is important with regard to such components as hollow turbine blades in gas turbine engines. Traditionally damping has occurred through damping elements secured at the root or tip of such blades.
|Compressor case overhaul|
A longitudinally-split compressor case of a gas turbine engine is overhauled to inhibit leakage between case segments that have been distorted. Grooves are machined in mating surfaces of the case segments.
|Shield system for gas turbine engine|
A shield system for a gas turbine engine extends between an inner case structure and a vane pack.. .
|Detachable fan blade platform and method of repairing same|
A fan section for a gas turbine engine includes a hub. A fan blade is secured to the hub.
|Inner bypass duct wall attachment|
A bypass duct of a gas turbine engine has an inner bypass duct wall has a front end portion which is rigidly mounted to an engine core case and a rear end portion which is flexibly mounted to the core case. The flexible mounting between the rear portion of the inner bypass duct wall and the core case allows hot engine areas of the core case to thermally grow and contract relative to the inner bypass duct wall without imposing additional loads on the inner bypass duct wall..