|| List of recent Gas Turbine-related patents
|Online enhancement for improved gas turbine performance|
A system is provided that includes a memory storing a turbomachinery degradation model configured to model degradation of a turbomachinery over time. The system also includes a controller communicatively coupled to the memory and configured to control the turbomachinery based on a feedback signal and the turbomachinery degradation model.
|System and method for positioning error compensation during manufacturing of complex-shaped gas turbine engine parts|
A system and method for error compensation in positioning a complex-shaped gas turbine engine part during manufacturing thereof with a machine. Theoretical measurements for a plurality of control points on the part are first retrieved.
|Mounting system for a planatary gear train in a gas turbine engine|
A mounting system for a planetary gear train in a gas turbine engine comprises a support strut, a deflection flange and a deflection limiter. The support strut extends between a stationary engine case and a rotating engine shaft that provides input to the planetary gear train in the gas turbine engine.
|Lubrication oil system for a reduction gearbox|
A reduction gear box is part of a gas turbine engine and includes a casing and reduction epicyclic gear stages within the casing. The reduction gear stages comprising at least an epicyclic array of gears meshing together with at least one planetary gear mounted for rotation on a gear carrier and a bearing associated therewith.
|Coating, coating layer system, coated superalloy component|
Coatings as may be used in a gas turbine are provided. A cobalt based coating may include 15 to 40 wt % nickel, 15 to 28 wt % chromium, 5 to 15 wt % aluminum, 0.05 to 1 wt % yttrium and/or at least one of elements from lanthanum series, 0.05 to 5 wt % ruthenium and/or molybdenum, 0 to 2 wt % iridium, 0 to 3 wt % silicon, 0 to 5 wt % tantalum, hafnium, unavoidable impurities, and a balance of cobalt.
|Gas turbine blade|
The gas turbine blade includes a cooling channel formed therein, and a partition disposed on its tip side for isolating the cooling channel from the outside. The partition is integrally formed with a blade portion in a position on its inner side in the radial direction with respect to the tip of the gas turbine blade.
|Aerodynamic fairings secondarily attached to nosecone|
An aerodynamic fan nosecone for a gas turbine engine is provided and includes a fan nosecone that may be made of composite material. To improve airflow transition to the blade members, aerodynamic fairings are provided and are secured to an exterior surface of the nosecone which enhances fuel economy.
|Rotor blades for gas turbine engines|
A rotor dual-blade for a gas turbine engine that has a first blade component extending radially between a root and a tip and a second blade component, separate from the first component, extending radially between a root and a tip, wherein the second blade component is downstream, in series, of the first blade component and at least the first blade component is made of metal while the second blade component is a light weight composite material.. .
|Double split blade lock ring|
A rotor assembly for a gas turbine engine includes a plurality of blades including a root portion and an airfoil portion. The rotor includes a plurality of slots that receive the root portion of a corresponding blade.
|Gas turbine engine airflow member having spherical end|
A gas turbine engine airflow member is disclosed having spherical interface shapes at a tip end and a hub end. In one embodiment, the airflow member is a fan blade.
|Attachment feature of a gas turbine engine blade having a curved profile|
An airfoil member is disclosed having an attachment feature such as a fir tree or dovetail design that includes a curved profile formed from a combination of curves. In one embodiment, the curved profile can be a compound curve formed by a forward curve and a rearward curve that are joined at a point of common tangency.
|Push-lock pin connector|
A push-lock pin for connecting a tile to a gas turbine engine wall according to an exemplary aspect of the present disclosure includes, among other things, a housing extending longitudinally along an axis; a shaft assembly within the housing, the shaft assembly including a push-down pop-up mechanism and a locking mechanism, the locking mechanism moveable to a locked position such that the locking mechanism limits movement of a tile away from a gas turbine engine wall; and a stop feature to limit movement of the tile toward the gas turbine engine wall.. .
|Gas turbine engine diffuser system for a high pressure (hp) compressor|
A gas turbine engine includes a compressor assembly that is rotationally coupled to a shaft. The engine includes a radial diffuser assembly coupled to a shroud of the compressor assembly and positioned to receive compressed air from a centrifugal impeller.
|Low profile vane retention|
A gas turbine having an annular casing with a series of circumferentially spaced openings defined therethrough; a plurality of vanes extending radially inwardly though respective casing openings, an outer end of the vanes projecting radially outwardly from the casing through the respective openings and located within the respective openings by grommets, and an inner end of the vanes being mounted to an inner portion of the casing; a flexible, segmented strap extending around the annular casing, surrounding the projecting outer ends of the vanes; and a spring radially loading the flexible strap configured to apply a tension force to the flexible strap.. .
|Outboard insertion system of variable guide vanes or stationary vanes|
A method of assembling a gas turbine engine comprising the steps of providing a casing having an insertion aperture in its outer surface. A guide vane is inserted through the insertion aperture.
|Manufacture of full ring strut vane pack|
A vane assembly for a gas turbine engine is disclosed and includes a plurality of individual vane segments forming an annular ring. Each of the plurality of vane segments is formed of a ceramic matrix composite including at least one airfoil extending between an inner platform and an outer platform.
|Low profile push-lock device|
A push-lock device for connecting a tile to a gas turbine engine wall includes, among other things, a housing extending longitudinally along an axis; a shaft assembly within the housing, the shaft assembly including portions of both a push-down pop-up mechanism and a locking-bracket mechanism, the locking-bracket mechanism moveable to a locked position such that the locking-bracket mechanism limits movement of a tile away from a gas turbine engine wall; and a biasing member to be positioned closer to the tile than the locking-bracket mechanism.. .
|Cmc turbine engine component|
A component of a gas turbine engine is formed from a continuous fibre reinforced ceramic matrix composite (cmc). The component has a sealing portion which, in use, makes sealing contact with an adjacent component of the engine.
|Gas turbine including bellyband seal anti-rotation device|
A turbine including a plurality of stages, each stage including a rotatable disk and blades carried thereby. An annular gap defined between a pair of adjacent rotatable disks.
|Inter-module flow discourager|
An assembly for a gas turbine engine includes a first module, a second module, and a flow discourager. The second module is connected to the first module along a joint.
|Consumable assembly tool for a gas turbine engine|
A method of assembling a gas turbine engine includes locating a consumable assembly tool within the engine. .
|Adjustable floating oil channel for gas turbine engine gear drive|
A turbine is operably connected to drive a compressor, and to drive a fan through a gear drive. A number of intermediate gears connecting an output shaft of the turbine to a fan drive shaft for the fan.
|Coating process for gas turbine engine component with cooling holes|
A method of coating a component having a multiple of cooling holes includes removing at least a portion of a prior coating; directing a gas through at least one of the multiple of cooling holes; and applying a coat layer while directing the gas through at least one of the. .
|Non-contacting seals for geared gas turbine engine bearing compartments|
A gas turbine engine includes a fan, a compressor section, a combustor, and a turbine section. The engine also includes a rotating element and at least one bearing compartment including a bearing for supporting the rotating element, a seal for resisting leakage of lubricant outwardly of the bearing compartment and for allowing pressurized air to flow from a chamber adjacent the seal into the bearing compartment.
|Fan track liner designed to yield next to fan case hook|
A containment system for a gas turbine engine includes a fan track assembly for use with a containment case. The fan track assembly includes a body of collapsible material that is positioned within a cavity of the fan case, and voids are provided for providing space in the event of a catastrophic blade failure.
|Gas turbine engine clearance control|
One embodiment of the present disclosure is a unique gas turbine engine having a bearing system and method of operating the engine. Another embodiment is a unique rotor machine.
|Systems and methods for providing a flow of purge air and an adjustable flow of cooling air in a gas turbine application|
Embodiments of the disclosure include systems and methods for providing a flow of purge air and an adjustable flow of cooling air to a wheel space cavity or a stator cavity. According to one embodiment, there is disclosed a turbine assembly.
|Actively cooled gas turbine sensor probe housing|
An actively cooled turbine sensor assembly is designed to withstand post-combustion gas-path conditions of gas turbine engines. The housing forms part of a cooling system and includes an elongated tubular structure that may be inserted into the hot flow path.
|Spiral turbine operating on pressure principle|
An apparatus of a gas turbine for the purpose of converting the pressure and temperature energy of a gas into rotational kinetic energy of a turbine; through an axial injection of such gas into the center of flat disks to perform work as the gas moves outward in one or more spirals cut out of these flat disks; such that the gas experiences a gradual release of pressure along the length of the spirals as the gas presses down on the width and length of the spiral; with the spiral being of many turns such that the radius of the spiral is a prescribed increasing function of turns of the radius; and the spiral has a long length in the order of a meter, a moderate width in the order of a centimeter, and a shallow depth being a small fraction of a millimeter.. .
|Gas turbine engine with internal electromechanical device|
A gas turbine engine including high and low pressure shafts, an electromechanical device having a rotor and a stator coupled such that the rotor is rotatable with respect to the stator, the rotor having a device gear secured thereto, the device being secured to a support structure in a bearing housing forming part of a bearing assembly supporting a portion of the low pressure shaft extending in proximity of the high pressure shaft and of the shaft gear, and a coupling idle gear secured for rotation about a stationary gear support mounted in the bearing housing, the idle gear being in toothed engagement with the shaft gear and with the device gear. An electromechanical device assembly for a gas turbine engine and a method of operating an electromechanical device are also provided..
|Support structure with dissimilar metal welds|
A support structure for a gas turbine exhaust system having an exterior shell, an interior liner, and insulation therebetween, the support structure including a support bar welded to the exterior shell, wherein the support bar weld includes a first filler material including a carbon steel filler material. The support structure further including a stud welded to the support bar and coupled to the interior liner, wherein the stud weld includes a second filler material including a low percentage of chromium..
|Reverse core engine thrust reverser for under wing|
A gas turbine engine for mounting under a wing of an aircraft has a propulsor that rotates on a first axis, and an engine core including a compressor section, a combustor section, and a turbine section, with the turbine section being closer to the propulsor than the compressor section. The engine core is aerodynamically connected to the propulsor and has a second axis.
|Reverse flow gas turbine engine removable core|
An engine mounting arrangement includes a propulsor mounted to an aircraft wing, and an engine core aerodynamically connected to the propulsor and positioned rearward of the propulsor.. .
A fuselage mounted gas turbine engine installation the installation includes at least one propeller stage and a gas turbine core arranged in use to drive the propeller stage. The core is external to the fuselage and the rotational axes of the core and propeller stage are offset with respect to each other..
|Filtration system for a gas turbine air intake and methods|
A gas turbine air filter system includes a housing having an interior, an inlet arrangement, and an outlet hood having an outlet arrangement. The inlet arrangement defines an inlet flow face for taking in unfiltered air.
|Seal test fixture for a gas turbine fuel nozzle|
A seal test fixture for a gas turbine fuel nozzle including an enclosed container for receiving a body of the gas turbine fuel nozzle including a seal; a test chamber coupled to the enclosed container for sealingly enclosing a flange of the gas turbine fuel nozzle and fluidly communicating with a leak path of the gas turbine fuel nozzle; an air injector opening through which pressurized air is injected into a main fuel chamber of the gas turbine fuel nozzle; and a pressure gauge for measuring an air pressure within the test chamber.. .
|Combustion chamber heat shield and seal assembly and a method of manufacturing a combustion chamber heat shield and seal assembly|
A gas turbine engine combustion chamber heat shield and seal assembly comprises a heat shield and a seal. The heat shield has an aperture and the seal is located in the aperture in the heat shield.
|System and method for aligning a gas turbine engine|
A system and method for aligning a gas turbine engine. The system and method includes installing an alignment mount, determining whether the gas turbine engine is aligned and/or in a sufficiently aligned condition, and modifying a vertical position of the gas turbine engine at the alignment mount in response.
|Starter motor shared lubrication system|
A starter motor has a housing. The housing receives the starter motor and a plurality of locations to receive lubricant.
|Method for operating a combined-cycle power plant|
Method for operating a combined-cycle power plant is provided. The plant includes at least a gas turbine and at least a steam power generation system.
|Processing exhaust for use in enhanced oil recovery|
A method for generating steam for hydrocarbon production is provided. The method includes producing steam using heat from an exhaust stream from a gas turbine system.
|Gas turbine fuel injector with metering cavity|
A fuel injector for a gas turbine engine may include a flow path for a fuel-air mixture extending longitudinally through the fuel injector, and a fuel gallery extending circumferentially around the flow path. The fuel gallery may be adapted to inject a liquid fuel into the flow path.
|Capacity control of turbine by the use of a reheat combustor in multi shaft engine|
One example of a gas turbine engine can include a first compressor and a first turbine connected to the first compressor by a first shaft. The engine can include a reheat combustor, which is disposed downstream of the first turbine, and a second turbine, which is disposed downstream of the reheat combustor.
|Cogen heat load matching through reheat and capacity match|
One example of a gas turbine engine may include a gas generator, a reheat combustor that is disposed downstream of the gas generator, and a power turbine that is disposed downstream of the reheat combustor and includes a plurality of nozzle guide vanes. The reheat combustor is configured to increase a fuel flow so as to increase a temperature of the reheat combustor and match a required exhaust temperature.
|Compressed air injection system method and apparatus for gas turbine engines|
This invention relates to electrical power systems, including generating capacity of a gas turbine, and more specifically to augmentation of power output of gas turbine systems, that is useful for providing additional electrical power during periods of peak electrical power demand.. .
|Method for starting-up and operating a combined-cycle power plant|
A method for starting-up a steam turbine of a combined-cycle power plant is provided. The combined-cycle power plant includes a gas turbine and a steam power generation system having a steam turbine.
|Gas turbine power plant with carbon dioxide separation|
The invention relates to a gas turbine power plant, having a gas turbine, a waste heat steam generator following the gas turbine, an exhaust gas recooler, an exhaust gas blower, a carbon dioxide separation plant which separates the carbon dioxide contained in the exhaust gases from these and discharges it to a carbon dioxide outlet. A bypass chimney is arranged in the gas turbine power plant between the outlet of the waste heat steam generator and the exhaust gas blower and is connected to a fail-safe open connection both in the throughflow direction from the exhaust gas line to the bypass chimney and in the throughflow direction from the bypass chimney to the exhaust gas line.
|Gas turbine engine thermally controlled flow device|
An apparatus includes a gas turbine engine flow device having an inner member and a surrounding member. The inner member has a first coefficient of thermal expansion; and the surrounding member at least partially surrounds the inner member and has a second coefficient of thermal expansion that is different from the first coefficient of thermal expansion.
|Tip-controlled integrally bladed rotor for gas turbine engine|
An integrally bladed rotor for a gas turbine engine includes a hub, a plurality of blades radially extending from the hub and being integrally formed therewith. The hub having a rim from which the blades project and a pair of axially opposed split hub members extending at least radially inward from the rim.
|Modulated ejector cooling|
A cooling air flow ejector has a primary nozzle position to entrain air from a secondary nozzle. Mixed air is provided into a downstream flow conduit to be directed to an exhaust liner for a gas turbine engine.
|Dual-wall impingement, convection, effusion (dice) combustor tile|
A gas turbine engine includes a combustor having a dual-wall impingement convention effusion combustor tile assembly. The dual-wall tile assembly provides a cooling air flow channel and attachments for securing the tile to the cold skin liner of the combustor.
|Lean fuel intake gas turbine|
A lean fuel intake gas turbine which uses, as a working gas, a mixed gas having a concentration equal to or lower than a flammability limiting concentration and obtained by mixing two types of fuel gases having different fuel concentrations, includes a first mixer configured to mix a second fuel gas having a higher fuel concentration with a first fuel gas having a lower fuel concentration, of the two types of the fuel gases having different fuel concentrations, to generate a first stage mixed gas and a second mixer configured to further mix the second fuel gas with the first stage mixed gas to generate a second stage mixed gas which is the working gas.. .
|Engine generating energy through physical and chemical energy conversions of a compressed gaseous fuel|
An engine for propelling vehicles on land, in the air and on the water. The engine is able to extract energy from a same fuel twice, including extracting a first amount of energy with a gas turbine and a second amount of energy by burning the fuel in a combustion engine..
|Bottoming cycle for aeroderivative turbine-based combined power systems and methods for using same|
Systems and methods for implementing the systems includes aeroderivative gas turbine subsystem and an energy extraction subsystem extracting energy from an exhaust of the aeroderivative gas turbine subsystem, where the energy extraction subsystem includes a heat exchange subsystem, a dual pressure turbine subsystem, and a condensation-thermal compression subsystem and where an intercooler portion of the heat recovery and vapor generator subsystem permits a working fluid flow rate to be increased to relative to a flow of the exhaust stream resulting in a bottoming cycle gross output increase of at least 23% relative a dual pressure rankine cycle bottoming cycle, a bottoming cycle net output increase of at least 25% relative a dual pressure rankine cycle bottoming cycle, a combined cycle net output increase of at least 5.5% relative a dual pressure rankine cycle bottoming cycle, and a combined cycle efficiency increase to at least 54% relative to 51.1% for a dual pressure rankine cycle bottoming cycle.. .
|Rear mounted reverse core engine thrust reverser|
In one embodiment, a gas turbine engine for mounting to a rear of an aircraft fuselage has a propulsor that rotates on a first axis, and an engine core including a compressor section, a combustor section, and a turbine section, with the turbine section being closer to the propulsor than the compressor section. The engine core is aerodynamically connected to the propulsor and has a second axis.
|Reverse flow gas turbine engine airflow bypass|
A gas turbine engine has a propulsor including a fan and a power turbine, an engine core aerodynamically connected to the propulsor by a transition duct, and a bypass valve in the transition duct that allows for air from the engine core to bypass the power turbine.. .
|Multi-shaft gas turbine engine|
A gas turbine engine is disclosed with a first spool having a first turbine connected to a first compressor through a first rotatable shaft; a second spool having a second turbine connected to a second compressor through a second rotatable shaft; and a gearbox having a power input port coupled to each of the first and second shafts and a power output port connected to a third shaft, wherein the rotational speed of the third shaft is lower than the rotational speed of each of the first and second shafts.. .
|Low-concentration methane gas oxidation system using exhaust heat from gas turbine engine|
A low-concentration methane gas oxidation system is provided which effectively uses exhaust heat from a gas turbine engine and is able to avoid burnout of a catalyst etc. To enable stable operation even when a methane concentration in a low-concentration methane gas which is a treatment target is rapidly increased.
A filter assembly is provided which is particularly suitable for use in filtering intake air for gas turbines. The filter assembly (6) includes a final filter (9) and a pre-filter (8) which are directly engageable one with the other to provide a complete filter assembly.