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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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Gas turbine engine fleet performance deterioration
General Electric Company
June 14, 2018 - N°20180164796

A method for determining gas turbine engine fleet performance deterioration includes receiving data indicative of deterioration parameter values for a plurality of gas turbine engines. The method also includes determining an average deterioration parameter value for each gas turbine engine at a plurality of intervals, and further determining an individual engine slope between the average deterioration parameter value at each ...
Injector head with a resonator for a gas turbine engine
Solar Turbines Incorporated
June 14, 2018 - N°20180163967

A fuel injector for a combustor of a gas turbine engine is disclosed herein. In embodiments, the fuel injector includes an injector head adjoining a stem.
Fuel supply system
Rolls-royce Plc
June 14, 2018 - N°20180163966

A fuel supply system for fuel injectors of a multi-stage combustor of a gas turbine engine. The fuel supply system includes a metering and splitting arrangement which receives a total fuel flow and controllably meters and splits the received total fuel flow into metered pilot and mains flows.
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Stator with support structure feature for tuned airfoil
United Technologies Corporation
June 14, 2018 - N°20180163751

A vane stage assembly includes an airfoil including a leading edge and a trailing edge. An inner shroud extends from the leading edge to the trailing edge for supporting the airfoil.
Propulsion system arrangement for turbofan gas turbine engine
United Technologies Corporation
June 14, 2018 - N°20180163665

A method of designing an engine according to an exemplary aspect of the present disclosure includes, among other things, designing an engine and a nacelle assembly together in an interactive process, the engine including a turbine section that drives a fan section and a compressor section. The step of designing the compressor section includes the step of designing a first ...
Concentric shafts driving adjacent fans for aircraft propulsion
United Technologies Corporation
June 14, 2018 - N°20180163664

A propulsion system for an aircraft has at least two fans, each fan having a fan drive shaft. A turboshaft gas turbine engine drives each of the at least two fans, and drive an output shaft which drives a gear to, in turn, engage for driving a gear on a first intermediate shaft extending from the turboshaft gas turbine engine ...
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System and method for monitoring hot gas path hardware life
General Electric Company
June 14, 2018 - N°20180163639

A system and a method for predicting and optimizing remaining hardware life of gas turbine components. Operating parameters of the gas turbine which may impact remaining hardware life are sensed and tracked using a plurality of sensors in communication with a control system including a computing device.
System and method for controlling a fuel flow to a gas turbine engine
General Electric Company
June 14, 2018 - N°20180163638

A computer-implemented method for controlling a fuel flow to a gas turbine engine of an aircraft includes determining a control initiated fuel flow demand that is based, at least in part, on an operator command. In addition, the method includes determining a first rate of change of fuel flow demand based, at least in part, on a tracking error of ...
Fluid valves
Delavan Inc
June 14, 2018 - N°20180163635

A fluid valve for a gas turbine engine includes a valve body with a fluid inlet and a fluid outlet, a fluid circuit extending between the fluid inlet and the fluid outlet, and a linkage. The linkage is arranged within the fluid circuit between the fluid inlet and the fluid outlet to apply effort from a solenoid actuator to a ...
Start biased liquid fuel manifold for a gas turbine engine
Solar Turbines Incorporated
June 14, 2018 - N°20180163634

A fuel distribution manifold for a gas turbine engine is disclosed herein. The fuel distribution manifold includes a manifold body, a stage divider, and a plurality of manifold outlet ports.
Twin shafts driving adjacent fans for aircraft propulsion
United Technologies Corporation
June 14, 2018 - N°20180163633

A propulsion system for an aircraft has at least two fans with each fan having a fan drive shaft. A turboshaft gas turbine engine drives each of the at least two fans.
Pilot/main fuel shifting in an axial staged combustor for a gas turbine engine
United Technologies Corporation
June 14, 2018 - N°20180163629

A combustor a gas turbine engine includes an axial fuel injection system in communication with a combustion chamber, the axial fuel injection system operable to supply a first percentage of fuel and a radial fuel injection system that communicates with the combustion chamber downstream of the axial fuel injection system, the radial fuel injection system operable to supply a second ...
Methods for startup and operation of gas turbine combined cycle power plants using nmhc fuels
General Electric Company
June 14, 2018 - N°20180163628

A method for starting and operating a nmhc fueled gas turbine combined cycle power plant includes injecting gaseous nmhc fuel into a gaseous nmhc fuel treatment system, injecting at least one of auxiliary steam, hrsg steam, or hrsg water into the gaseous nmhc fuel treatment system, and mixing the at least one of auxiliary steam, hrsg steam, or hrsg water ...
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Gas Turbine Patent Applications
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  • Exact USPTO filing data with full-text, images, drawings & claims.
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Air logic control for auxiliary air injection system
Powerphase Llc
June 14, 2018 - N°20180163626

The invention relates generally to gas turbine engines used for electrical power generation. More specifically, embodiments of the present invention provide systems and ways for improving the life and reducing start-up time necessary for bringing gas turbine engines online and up to full power..
Systems and methods for gas turbine compressor cleaning
General Electric Company
June 14, 2018 - N°20180163624

In one embodiment, a gas turbine fluid wash system includes a fluid wash system controller comprising a processor. The processor is configured to receive a cleaning fluid flow demand from a turbine system controller, wherein the turbine system controller is configured to control the turbine system to produce power.
System and method for improving output and heat rate for a liquid natural gas combined ...
General Electric Company
June 14, 2018 - N°20180163570

A combined cycle power plant and heating and cooling system and method for the power plant is disclosed as having a liquid natural gas supply and a vaporizer configured to vaporize the liquid natural gas into natural gas that is supplied to a gas performance heater before entering a combustion section of a gas turbine. A closed cooling water circuit ...
Low pressure ratio fan engine having a dimensional relationship between inlet and fan size
United Technologies Corporation
June 14, 2018 - N°20180163568

According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan section including a fan, the fan including a plurality of fan blades, a diameter of the fan having a dimension d that is based on a dimension of the fan blades, each fan blade having a leading edge, and a forward most portion on ...
Lubrication system for a turbine engine
General Electric Company
June 14, 2018 - N°20180163566

A lubrication system for a gas turbine engine includes a tank, a circulation pump, and a heat exchanger. The circulation pump generates a flow of lubricant from the tank to, e.g., a power gear box of the gas turbine engine and the heat exchanger removes an amount of heat from such flow of lubricant provided to the power gear ...
Conduit box assembly systems and methods
General Electric Company
June 14, 2018 - N°20180163559

A system includes a conduit box assembly configured to be rated as an explosion-proof (ex d) rated enclosure. The conduit box assembly includes a housing configured to support an electrical device.
Transition ducts of a gas turbine combustor
Siemens Aktiengesellschaft
June 14, 2018 - N°20180163550

A combustor has a trailing edge duct (110) that has a trailing edge (120) that is adapted to be connected to an adjacent trailing edge (120) of a trailing edge duct (110). The connections between the adjacent trailing edges may be formed along the lengthwise direction of the trailing edges and/or using interfacing components..
Internal airfoil component electrolplating
Howmet Corporation
June 14, 2018 - N°20180163547

Method and apparatus are provided for electroplating a surface area of an internal wall defining a cooling cavity present in a gas turbine engine airfoil component.. .
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