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Gas Turbine patents



      

This page is updated frequently with new Gas Turbine-related patent applications.




Date/App# patent app List of recent Gas Turbine-related patents
05/19/16
20160138808 
 Device for determining a fuel split, as gas turbine or an aircraft engine comprising such a device and application of the same patent thumbnailDevice for determining a fuel split, as gas turbine or an aircraft engine comprising such a device and application of the same
A device for determining a fuel split, and particularly a final fuel split in at least one staged combustion chamber of a gas turbine or an aircraft engine is provided. The device comprises a first control device for determining a preselected fuel split demand for the staged combustion chamber, wherein this determination can be performed based on the detection of a steady state or the detection of a transient state.
Rolls-royce Deutschland Ltd & Co Kg


05/19/16
20160138807 
 Gas turbine engine flow regulating patent thumbnailGas turbine engine flow regulating
A gas turbine combustor assembly includes a fuel injector, a dome stator around the fuel injector, and a dome sleeve coupled to the dome stator. The dome sleeve defines an air inlet opening with the dome stator, and is carried to move with respect to the dome stator to change a flow area of the air inlet opening.
United States Government


05/19/16
20160138603 
 Split axial-centrifugal compressor patent thumbnailSplit axial-centrifugal compressor
A gas turbine engine including a compressor, a turbine, and a variable-ratio unit is disclosed. The turbine is coupled to the compressor to drive rotation of multiple stages of the compressor.
Rolls-royce Corporation


05/19/16
20160138523 
 Optimal thrust control of an aircraft engine patent thumbnailOptimal thrust control of an aircraft engine
A control system for a gas turbine engine, a method for controlling a gas turbine engine, and a gas turbine engine are disclosed. The control system may include a nozzle scheduler for determining an exhaust nozzle position goal based on a nozzle schedule of exhaust nozzle positions related to flight conditions.
United Technologies Corporation


05/19/16
20160138483 
 Application of fuel flow-based probabilistic control in gas turbine tuning under part load, related control systems, computer program products and methods patent thumbnailApplication of fuel flow-based probabilistic control in gas turbine tuning under part load, related control systems, computer program products and methods
Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (gts) by performing actions including: commanding each gt in the set of gts to a base load level, based upon a measured ambient condition for each gt; commanding each gt in the set of gts to adjust a respective output to match a nominal mega-watt power output value, and subsequently measuring an actual fuel flow value for each gt; adjusting an operating condition of each gt in the set of gts based upon a difference between the respective measured actual fuel flow value and a nominal fuel flow value at the ambient condition; commanding each gt in the set of gts to a part load level, the part load level representing a fraction of the base load level, and subsequently measuring an actual fuel flow value for each gt at the part load level; and calibrating the set of gts based upon a difference between the measured actual fuel flow value at the part load level and the measured actual fuel flow value after adjusting the output to match the nominal mega-watt power output value.. .
General Electric Company


05/19/16
20160138482 
 Application of probabilistic control in gas turbine tuning with measurement error, related control systems, computer program products and methods patent thumbnailApplication of probabilistic control in gas turbine tuning with measurement error, related control systems, computer program products and methods
Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (gts) by performing actions including: commanding each gt in the set of gts to a base load level, based upon a measured ambient condition for each gt; commanding each gt in the set of gts to adjust a respective output to match a nominal mega-watt power output value, and subsequently measuring an actual emissions value for each gt; adjusting an operating condition of each gt in the set of gts based upon a difference between the respective measured actual emissions value and a nominal emissions value at the ambient condition; and further adjusting an operating condition of each gt in the set of gts based upon a determined emissions measurement error.. .
General Electric Company


05/19/16
20160138481 
 Degraded gas turbine tuning and control systems, computer program products and related methods patent thumbnailDegraded gas turbine tuning and control systems, computer program products and related methods
Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (gts) by performing actions including: commanding each gt in the set of gts to a base load level, based upon a measured ambient condition for each gt; commanding each gt in the set of gts to adjust a respective output to match a nominal mega-watt power output value, and subsequently measuring an actual emissions value for each gt; adjusting an operating condition of each gt in the set of gts based upon a difference between the respective measured actual emissions value and a nominal emissions value at the ambient condition; and calculating a degradation for each gt in the set of gts over a period.. .
General Electric Company


05/19/16
20160138480 
 Application of probabilistic control in gas turbine tuning, related control systems, computer program products and methods patent thumbnailApplication of probabilistic control in gas turbine tuning, related control systems, computer program products and methods
Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (gts) by performing actions including: commanding each gt in the set of gts to a base load level, based upon a measured ambient condition for each gt; commanding each gt in the set of gts to adjust a respective output to match a nominal mega-watt power output value, and subsequently measuring an actual emissions value for each gt; and adjusting an operating condition of each gt in the set of gts based upon a difference between the respective measured actual emissions value and a nominal emissions value at the ambient condition.. .
General Electric Company


05/19/16
20160138479 
 Application of fuel flow-based probabilistic control in gas turbine tuning, related control systems, computer program products and methods patent thumbnailApplication of fuel flow-based probabilistic control in gas turbine tuning, related control systems, computer program products and methods
Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (gts) by performing actions including: commanding each gt in the set of gts to a base load level, based upon a measured ambient condition for each gt; commanding each gt in the set of gts to adjust a respective output to match a nominal mega-watt power output value, and subsequently measuring an actual fuel flow value for each gt; and adjusting an operating condition of each gt in the set of gts based upon a difference between the respective measured actual fuel flow value and a nominal fuel flow value at the ambient condition.. .
General Electric Company


05/19/16
20160138478 
 Gas turbine engine patent thumbnailGas turbine engine
A gas turbine engine is disclosed comprising a shaft driven by a turbine, the turbine directly driving a lower speed compressor via a shaft and driving a higher speed compressor via the shaft and a multiplier power gearbox. The gearbox comprises a ring gear, a plurality of planet gears and planet carrier and a sun gear.
Rolls-royce Deutschland Ltd & Co Kg


05/19/16
20160138475 

Method of starting a gas turbine engine


(iii) modifying at least one operating parameter of the gas turbine engine as the rotational speed increases such that for a rotational speed, an operational working line is closer to the reference stability boundary than the reference working line is to the reference stability boundary.. .

05/19/16
20160138474 

Low noise compressor rotor for geared turbofan engine


A gas turbine engine according to an example of the present disclosure includes, among other things, a fan and a turbine section having a fan drive turbine rotor, and a compressor rotor. A gear reduction effects a reduction in a speed of the fan relative to an input speed from the fan drive turbine rotor.
United Technologies Corporation


05/19/16
20160138470 

Application of probabilistic control in liquid-fueled gas turbine tuning, related control systems, computer program products and methods


Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (gts) by performing actions including: commanding each gt in the set of gts to a base load level, based upon a measured ambient condition for each gt; commanding each gt in the set of gts to adjust a respective output to match a nominal mega-watt power output value, and subsequently measuring an actual fuel flow value and an actual emissions value for each gt; adjusting at least one of a fuel flow or a water flow for each gt to an adjusted water/fuel ratio in response to the actual emissions value deviating from an emissions level associated with the base load level, while maintaining the respective adjusted output; and adjusting an operating condition of each gt in the set of gts based upon a difference between the respective measured actual fuel flow value and a nominal fuel flow value at the ambient condition, while maintaining the adjusted water/fuel ratio.. .
General Electric Company


05/19/16
20160138425 

Turbofan engine front section


A front section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan section including a fan hub. The fan hub includes a hub diameter supporting a plurality of fan blades including a tip diameter.
United Technologies Corporation


05/19/16
20160138423 

Titanium-aluminide components


The present disclosure relates to a hot section gas turbine engine component assembly and a method for forming such.. .
Rolls-royce North American Technologies, Inc.


05/19/16
20160138417 

Turbine and detecting rubbing


A turbine, in particular a gas turbine, includes a rotor, a housing spaced from the rotor by a gap, and a system for monitoring structure-borne noise, permit rubbing of the rotor and the housing to be localised with the least possible technical complexity. In both a first and second axial region, one or more inwardly directed rubbing teeth of the housing and one or more outwardly directed rubbing edges of the rotor are arranged, wherein the one or more rubbing teeth and the one or more rubbing edges are distributed along the circumference such that contact of the particular rubbing teeth and rubbing edges at a specified rotational frequency of the rotor occurs at a different frequency in the first axial region than in the second axial region..
Siemens Aktiengesellschaft


05/19/16
20160138416 

Variable fan nozzle using shape memory material


A gas turbine engine includes a fan, a nacelle arranged about the fan, and an engine core at least partially within the nacelle. A fan bypass passage downstream of the fan between the nacelle and the gas turbine engine conveys a bypass airflow from the fan.
United Technologies Corporation


05/19/16
20160138411 

Fully integrated air guide element


An air guide element of an aircraft gas turbine, including an external housing that is provided with an inflow opening, as well as with a flow channel that is arranged inside the housing, characterized in that a tubular intermediate element that is made of an elastic material is arranged inside the inflow opening, connecting the inflow opening to the flow channel in a sealing and position-adjusting manner.. .
Rolls-royce Deutschland Ltd & Co Kg


05/19/16
20160138406 

Composite components for gas turbine engines


A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. Each blade is formed as a composite structure including a number of plies of ceramic-containing material.
Rolls-royce North American Technologies, Inc.


05/19/16
20160138399 

Reinforced gas turbine engine rotor disk


A structurally-reinforced rotor disk for a gas turbine engine is disclosed. The rotor disk may comprise a body including a rim configured to support airfoils (which may be separate or integral with the airfoils), an axially-extending bore disposed radially inward of the rim, and a radially-extending web connecting the rim and the bore.
United Technologies Corporation


05/12/16
20160131159 

Gas turbine comprising a compressor casing with an inlet opening for tempering the compressor casing and use of the gas turbine


A gas turbine includes at least one rotor assembly and at least one compressor casing. The compressor casing has at least one inner compressor casing chamber for arranging the rotor assembly and at least one outer compressor casing chamber for tempering the compressor casing.
Siemens Aktiengesellschaft


05/12/16
20160131158 

Compressor and gas turbine


This compressor is provided with: a rotor casing that encircles a rotor, which rotates around a rotational axis; an air bleed chamber casing that is provided to the outer peripheral side of the rotor casing and demarcates an air bleed chamber interconnecting to a primary duct via a slot; and an air bleed tube that is connected to the air bleed chamber casing from the outer peripheral side and is provided with an air bleed pathway. In the slot, at which an opening to the primary duct is formed, a large opening, at which the opening area of the opening is locally larger than that of the other positions in the peripheral direction of the opening, is formed at a position in the peripheral direction corresponding to the position at which the air bleed tube is provided..
Mitsubishi Heavy Industries, Ltd.


05/12/16
20160131151 

Gas turbine engine airfoil


An airfoil arrangement of a turbine engine according to an example of the present disclosure includes adjacent airfoils including pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position. The airfoils have a relationship between a gap/chord ratio and span position that defines a curve with a gap/chord ratio having a portion with a negative slope..
United Technologies Corporation


05/12/16
20160131084 

Geared turbofan arrangement with core split power ratio


A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section, and a compressor section including at least a first compressor section and a second compressor section. A power ratio is provided by the combination of the first compressor section and the second compressor section.
United Technologies Corporation


05/12/16
20160131079 

Engine cowling of a gas turbine with thrust-reversing device and adjustable outlet nozzle


An engine cowling of an aircraft gas turbine having a front cowling and a single rear cowling movable in the axial direction. By a drive device, the rear cowling is movable into different positions including a closed cruise position, a partially opened maximum thrust position and a completely opened thrust-reversing position.
Rolls-royce Deutschland Ltd & Co Kg


05/12/16
20160131045 

Emissions control system for a gas turbine engine


An emissions control system (10) for a gas turbine engine (12) for reducing co emissions at partial load of the gas turbine engine (12) is disclosed. In at least one embodiment, the emissions control system (10) may be formed from one or more compressed air exhausts (14) for exhausting compressed air into a hot gas pathway contained within a channel (18) formed by a transition (20) extending from a combustor (22) to a turbine assembly (24).
Siemens Energy, Inc.


05/12/16
20160131044 

Gas turbine engine driving multiple fans


A gas turbine engine includes a core engine with a compressor section, a combustor and a turbine. The turbine drives an output shaft, and the output shaft drives at least four gears.
United Technologies Corporation


05/12/16
20160131043 

Turbine engine gearbox


A gas turbine engine comprises a fan, a compressor, a combustor, and a fan drive turbine rotor. The fan drive turbine drives the fan through a gear reduction.
United Technologies Corporation


05/12/16
20160131039 

Gas turbine engine heat exchanger manifold


A heat exchanger manifold for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a manifold body extending between a first face and a second face, a first seal land defining a first fluid port extending through the manifold body between the first face and the second face, and a first seal received within the first fluid port.. .
United Technologies Corporation


05/12/16
20160131037 

Supply duct for cooling air


In a featured embodiment, a gas turbine engine has a compressor section having a downstream rotor and a diffuser downstream of the compressor section. A combustor receives air downstream of the diffuser.
United Technologies Corporation


05/12/16
20160131036 

Thermal management system for a gas turbine engine


In one exemplary embodiment, a gas turbine engine system for cooling engine components includes an engine core, a core housing containing the engine core, an engine core driven fan forward of the core housing, a nacelle surrounding the fan and the core housing, and a bypass duct defined between an outer diameter of the core housing and an inner diameter of the nacelle. Also included is a thermal management system having a coolant circuit including at least one of a first heat exchanger disposed on the inner diameter of the nacelle and a second heat exchanger disposed on a leading edge of a bifi spanning the bypass duct.
United Technologies Corporation


05/12/16
20160131033 

Filtration cleaning the intake air of a gas turbine


In a filtration system, in particular for cleaning the intake air of a gas turbine, including a flow channel surrounded by walls with an inflow opening and an outflow opening, a partition wall with at least two openings between a dirty side and a clean side which is positioned between the inflow opening and the outflow opening and limited by the walls of the flow channel, and at least two filters for purifying a flowing fluid. At least one filter is installed at a first opening on the dirty side of the partition wall and at least one filter at a second opening on the clean side of the partition wall..

05/12/16
20160131031 

Gas turbine fast regulation and power augmentation using stored air


The present invention discloses a novel apparatus and methods for augmenting the power of a gas turbine engine, improving gas turbine engine operation, and reducing the response time necessary to meet changing demands of an electrical grid. Improvements in power augmentation and engine operation include systems and methods for providing rapid response given a change in electrical grid..
Powerphase Llc


05/12/16
20160131030 

Gas turbine efficiency and power augmentation improvements utilizing heated compressed air and steam injection


The present invention discloses a novel apparatus and methods for augmenting the power of a gas turbine engine, improving gas turbine engine operation, and reducing the response time necessary to meet changing demands of a power plant. Improvements in power augmentation and engine operation include systems and methods for preheating piping of a power augmentation system and directing flows of hot compressed air, steam or a combination thereof into the gas turbine engine..
Powerphase Llc


05/12/16
20160131028 

Gas turbine


A gas turbine, in particular an aircraft engine, including a core flow channel (k), in which a first compressor (20), a second compressor (40) adjacent downstream from the first compressor, a combustion chamber (60) adjacent downstream from the second compressor, a second turbine (50) adjacent downstream from the combustion chamber, which is coupled to the second compressor, and a first turbine (30) adjacent downstream from the second turbine, which is coupled to the first compressor via a first transmission (71), are situated; a quotient (r/r) of an inside diameter (r) of the core flow channel divided by an outside diameter (r) of the core flow channel at an upstream inflow of the first compressor being at most 0.65, in particular at most 0.5 is provided.. .
Mtu Aero Engines Ag


05/12/16
20160130983 

Method for coupling a steam turbine and a gas turbine at a desired differential angle


A method and an associated arrangement for coupling a rotational device, particularly a steam turbine, and a shaft device, particularly a gas turbine, includes the following steps: 1) accelerating the rotational device up to an output rotational speed that is below the rotational speed of the shaft device; 2) detecting a differential angle between the shaft device and the rotational device; and 3) accelerating the rotational device with an acceleration value that is derived from the target rotational speed difference, which is formed as a function of the detected differential angle, the acceleration and a desired target coupling angle.. .
Siemens Aktiengesellschaft


05/12/16
20160130982 

Gas turbine efficiency and power augmentation improvements utilizing heated compressed air


The present invention discloses a novel apparatus and methods for augmenting the power of a gas turbine engine, improving gas turbine engine operation, and reducing the response time necessary to meet changing demands of a power plant. Improvements in power augmentation and engine operation include systems and methods for preheating a steam injection system..
Powerphase Llc


05/12/16
20160130980 

Gas turbine engine and frame


One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique frame for a gas turbine engine.
Rolls-royce North American Technologies, Inc.


05/12/16
20160130977 

Turbine rotor segmented sideplates with anti-rotation


A segmented sideplate for use in a gas turbine engine is described. The segmented sideplate includes a first plate having a first circumferential edge configured to interface with a complementary circumferential edge.
United Technologies Corporation


05/12/16
20160130975 

Collapsible support structure for a gas turbine engine


Described is a shaft support system for a gas turbine engine comprising: a rotatable fan shaft; first and second support structures extending in parallel from the shaft to a load bearing structure to provide radial location of the shaft within an engine casing, wherein the first support and second support structures include first and second respective mechanical fusible joints; wherein the first fusible joint is a two-stage fuse which partially fails within a first predetermined load range, the second fusible joint fails within a second predetermined load range which is different to the first load range, and the first fusible joint fully fails only when the second fusible joint has failed.. .
Rolls-royce Plc


05/12/16
20160130973 

Guide vane


A gas turbine engine variable guide vane has a fixed portion on an upstream side, a movable flap on a downstream side and a transfer slot between a fixed portion trailing surface and a movable flap leading surface. The movable flap has opposite pressure and suction sides along a chord line between leading and trailing edges, and is rotatable about an axis along a movable flap span over a range of angular positions between open and closed.
Rolls-royce Plc


05/12/16
20160130972 

Bleed valve


A bleed valve for a gas turbine engine, the bleed valve comprising: an inlet coupled to an air source; and an outlet coupled to an air sink. The bleed valve also comprises a first stage of flow area modulation between the inlet and the outlet.
Rolls-royce Plc


05/12/16
20160130971 

Gas turbine electrical machine arrangement


A gas turbine engine comprising an electrical machine 30, 130, 200, 210, the electrical machine 30, 130, 200, 210 having an axis of rotation that is canted with respect to the main rotational axis of the gas turbine engine.. .
Rolls-royce Plc


05/12/16
20160130969 

Additive process for an abradable blade track used in a gas turbine engine


A gas turbine engine assembly comprising a rotor, a gas path component, and a carrier. The rotor includes a shaft adapted to rotate about an axis and a gas-path component that extends from the shaft for rotation therewith about the axis.
Rolls-royce Corporation


05/12/16
20160130966 

Sealing arrangement for a gas turbine engine


There is described a seal assembly for a gas turbine engine comprising: a first seal having a sealing passage which defines a flow path trajectory for leakage air, the first seal for partitioning a first pressure area to a lower pressure area; a second seal located along the line of the flow path trajectory of the first seal, the second seal for partitioning a second pressure area and the lower pressure area; a deflection member located between the first seal and second seal, and in the trajectory of the flow path from the first seal.. .
Rolls-royce Plc


05/12/16
20160130964 

Gas turbine engine flow control device


A flow control device for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner surface and a radially outer surface and at least one stand-up protruding from the radially outer surface and configured to seal an interrupted surface.. .
United Technologies Corporation


05/12/16
20160130963 

Gas turbine engine and seal assembly therefore


The present disclosure relates generally to a hydrostatic advanced low leakage seal having a shoe supported by at least two beams. An anti-vibration beam spacer is disposed in contact with two adjacent beams and operative to mitigate an externally induced vibratory response of the beams..
United Technologies Corporation


05/12/16
20160130961 

Gas turbine engine


A gas turbine engine includes in axial flow series a fan rotor, a series of outlet guide vanes for guiding flow from the fan rotor; and a bifurcation. The gas turbine engine further includes a substantially annular fluid passageway extending from fan to the bifurcation, the outlet guide vanes being positioned within the passageway.
Rolls-royce Plc


05/12/16
20160130959 

Gas turbine engine


A gas turbine engine comprising in axial flow series: a fan having a fan rotor; a series passages defined between adjacent outlet guide vanes for guiding flow from the fan; and a bifurcation. The gas turbine engine further comprises a substantially annular fluid passageway extending from the fan to the bifurcation, the outlet guide vanes being positioned within the passageway.
Rolls-royce Plc


05/12/16
20160130958 

Gas turbine engine structural guide vanes


A structural guide vane is disclosed. The structural guide vane may include a first root, a second root positioned radially outward from the first root and a truss extending between the first root and second root.
United Technologies Corporation


05/12/16
20160130951 

Cooling for turbine blade platform-aerofoil joints


The invention concerns a turbine blade for a gas turbine having a platform part and an aerofoil part. The platform part includes a platform surface arranged to be attached to a corresponding aerofoil surface of the aerofoil part.
Alstom Technology Ltd.


05/12/16
20160130950 

Gas turbine engine component with rib support


A component according to an exemplary aspect of the present disclosure includes, among other things, an airfoil that includes a first sidewall and a second sidewall joined together at a leading edge and a trailing edge and extending from a base to a tip. A plenum is defined inside the airfoil.
United Technologies Corporation




Gas Turbine topics: Gas Turbine, Gas Turbine Engine, Internal Combustion Engine, Distributed, Combustion, Uv Radiation, Exhaust Gas, Circulation, Downstream

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