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Gas Turbine

Gas Turbine-related patent applications - as published by the U.S. Patent and Trademark Office (USPTO).


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Application of combined probabilistic control in gas turbine tuning for power output-emissions parameters with scaling ...
General Electric Company
June 22, 2017 - N°20170179790

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 power output ...
Machine-specific combined probabilistic control in gas turbine tuning for power output-emissions parameters with scaling factor, ...
General Electric Company
June 22, 2017 - N°20170176960

Commanding gts to base load level based upon measured ambient condition for each gt; commanding each gt to adjust a power output to match scaled power output value equal to a fraction of a difference between the respective power output and a nominal power output value, and measuring actual emissions value for each gt during the adjusting of the respective ...
Boroscope sheath
Ansaldo Energia Switzerland Ag
June 22, 2017 - N°20170176737

A boroscope sheath is disclosed for providing a boroscope with temperature protection during a boroscope inspection of a machine such as a gas turbine or a steam turbine. The boroscope sheath includes an elongate tube having a wall extending from a front end to a back end and around a central bore configured and arranged to allow removable insertion of ...
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Slotted injector for axial fuel staging
General Electric Company
June 22, 2017 - N°20170176015

An axial fuel staging injector for a gas turbine includes a body. The body includes an upstream end and a downstream end. The body defines a primary compressed air flow path through which compressed air flows from a compressed air source to a transition duct of a gas turbine combustor. The body includes a plurality of outlets disposed on an ...
Staged fuel and air injection in combustion systems of gas turbines
General Electric Company
June 22, 2017 - N°20170176014

A gas turbine that includes: a combustor coupled to a turbine that define a working fluid flowpath; a compressor discharge cavity; a staged injection system that includes the forward injector and a staged injector; a stator blade positioned extending across the working fluid flowpath between an inboard sidewall and an outboard sidewall. A one-way continuous coolant flowpath that includes: an ...
Staged fuel and air injection in combustion systems of gas turbines
General Electric Company
June 22, 2017 - N°20170176013

A gas turbine that includes: a combustor coupled to a turbine that define a working fluid flowpath; a compressor discharge cavity; a staged injection system that includes the forward injector and a staged injector; a stator blade positioned extending across the working fluid flowpath between an inboard sidewall and an outboard sidewall. A one-way continuous coolant flowpath that includes: an ...
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Gas Turbine Patent Applications
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  • 2202+ full patent PDF documents of Gas Turbine-related inventions.
  • Exact USPTO filing data with full-text, images, drawings & claims.
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Compensating for thermal expansion via controlled tube buckling
Delavan Inc.
June 22, 2017 - N°20170176011

One embodiment includes a fuel injector for a gas turbine engine. The fuel injector has an inlet fitting for receiving fuel. The fuel injector also has an outlet fitting for delivering fuel through a nozzle to a combustor of the gas turbine engine. An injector support extends between the inlet fitting and the outlet fitting and has an internal bore ...
Helmholtz damper for a gas turbine and gas turbine with such helmholtz damper
Ansaldo Energia Ip Uk Limited
June 22, 2017 - N°20170176009

A helmholtz damper for a gas turbine is disclosed which includes a static resonator volume, which can be connected via a neck to an inner space of the gas turbine to damp pressure pulsations developing in the inner space. The static resonator volume can be changed in order to match resonances of the helmholtz damper with the pressure pulsations. A ...
Wall of a structural component, in particular of a gas turbine combustion chamber wall, to ...
Rolls-royce Deutschland Ltd & Co Kg
June 22, 2017 - N°20170176006

A wall of a structural component to be cooled by means of cooling air with at least one cooling air channel, which at least in its outflow area is arranged so as to be inclined at an angle with respect to the wall inclined, penetrating the wall from the side at which the cooling air is supplied to the thermally ...
Combustion chamber
Rolls-royce Plc
June 22, 2017 - N°20170176005

A gas turbine engine combustion chamber arrangement includes an annular outer wall and annular inner wall including an upstream and a downstream row of tiles. The downstream end of each tile in the upstream row of tiles has a rail extending towards and sealing with the outer wall and a lip extending in a downstream direction towards the tiles in ...
Liquid fuel cartridge for a fuel nozzle
General Electric Company
June 22, 2017 - N°20170176000

A liquid fuel cartridge for a gas turbine fuel nozzle includes a tube having an inlet end and an outlet end with one or more fuel exit orifices; and a homogenizer located within the tube, adjacent and up-stream of the outlet end. The homogenizer is formed by a substantially-cylindrical body open at opposite ends, and a first row of circumferentially-spaced ...
Electric windmill pump for gearbox durability
United Technologies Corporation
June 22, 2017 - N°20170175874

A gas turbine engine installed on an aircraft includes a fan rotor, a turbine rotor, a gearbox, an auxiliary pump, and an electric motor. The gearbox couples the fan rotor to the turbine rotor, the turbine rotor being adapted to drive the fan rotor via the gearbox. The auxiliary pump is configured to circulate lubricating fluid in an auxiliary lubrication ...
Mistuned fan
Pratt & Whitney Canada Corp.
June 22, 2017 - N°20170175776

A compressor rotor for a gas turbine engine is described which includes sets of blades having different airfoil thickness distributions, each including a frequency modifier forming a thickness differential relative to a baseline blade thickness. The frequency modifiers provide different natural vibration frequencies for each of the blades, and facilitate modifying natural vibration frequency separation between adjacent blades of the ...
Gas Turbine Patent Pack
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Gas Turbine Patent Applications
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inventor
  • 2202+ full patent PDF documents of Gas Turbine-related inventions.
  • Exact USPTO filing data with full-text, images, drawings & claims.
  • Index pages: Table View and Image-Grid View layouts. All images in each PDF.
Gas turbine engine with short inlet and blade removal feature
United Technologies Corporation
June 22, 2017 - N°20170175767

A gas turbine engine comprises a fan rotor having fan blades received within an outer nacelle, and the outer nacelle having an inner surface. At least a portion of the nacelle inner surface extends radially inwardly to be radially inward of an outer diameter of the fan blades. The inner surface of the nacelle is formed with a trench, which ...
Gas turbine engine with rotating inlet
United Technologies Corporation
June 22, 2017 - N°20170175766

A gas turbine engine comprises a nacelle that encloses a fan rotor carrying a plurality of fan blades. The nacelle is formed with droop such that one portion extends axially further from the fan blades than does another portion. The nacelle is rotatable such that a circumferential location of the one portion and the other portion may be varied dependent ...
Gas turbine engine with short inlet and mistuned fan blades
United Technologies Corporation
June 22, 2017 - N°20170175761

A gas turbine engine comprises a fan rotor having fan blades received within an outer nacelle. The fan blades are provided with at least a first type having a first natural frequency, and a second type having a second natural frequency. The fan rotor has a first mount structure intended for the first type and a distinct second mount structure ...
Gas turbine engine airfoil
United Technologies Corporation
June 22, 2017 - N°20170175760

A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides extending in radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a leading edge dihedral angle and span position defined by a curve with the leading edge dihedral angle including 10° or less change from 0% span to 60% ...
Gas turbine engine airfoil
United Technologies Corporation
June 22, 2017 - N°20170175759

A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a tangential trailing edge position and span position that defines a curve with a non-positive slope from 90% span to 100% span. The non-positive slope corresponds to ...
Gas turbine engine airfoil
United Technologies Corporation
June 22, 2017 - N°20170175758

An airfoil of a turbine engine includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a leading edge angle and span position that defines a curve with a leading edge angle of less than 40° at 100% span.
Modelling probabilistic control in gas turbine tuning for power output-emissions parameters, related control systems, computer ...
General Electric Company
June 22, 2017 - N°20170175651

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 power output ...
Application of combined probabilistic control in gas turbine tuning for power output-emissions parameters with scaling ...
General Electric Company
June 22, 2017 - N°20170175650

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 power output ...
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