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Class 60/785 - Air bleed


Subclass of Class 60 - Power plants
Definition: Apparatus wherein the feature is compressed atmospheric
No. of applications: 201
Last issue date: 05/09/2013


1            
Application No.Application TitleIssue Date
20130111916SYSTEM FOR OPERATING A POWER PLANT
A system for operating a power plant is provided and includes a grid configured to generate a normal load and an abnormal load, a turbomachine configured to provide power to the grid in accordance with the normal load by firing at normal temperatures and in accordance w...
05/09/2013
20130111921METHOD FOR CONTROLLING GAS TURBINE ROTOR TEMPERATURE DURING PERIODS OF EXTENDED DOWNTIME
A method for warming the rotor of a gas turbine during extended periods of downtime comprising feeding ambient air to an air blower; extracting compressed air from the air blower; feeding a portion of the compressed air to one side of a heat exchanger and steam (typical...
05/09/2013
20130104564ACTIVE CLEARANCE CONTROL SYSTEM AND METHOD FOR GAS TURBINE
A method to provide clearance control for a gas turbine having a multi-stage compressor and a turbine having turbine buckets rotating within a turbine shell, the method includes: selecting a first compressor stage from which to extract compressed air; ducting the compre...
05/02/2013
20130098051AUXILIARY POWER UNIT BLEED CLEANING FUNCTION
An auxiliary power unit is operable to provide bleed air to a vehicle system. A method includes diverting substantially all of the bleed air to an exhaust for a selected time period commencing with startup of the auxiliary power unit. After the selected time period, at ...
04/25/2013
20130098061GAS TURBINE ENGINE COOLING SYSTEMS HAVING HUB-BLEED IMPELLERS AND METHODS FOR THE PRODUCTION THEREOF
Embodiments of a gas turbine engine cooling system for deployment within a gas turbine engine are provided, as are embodiment of a method for producing a gas turbine engine cooling system. In one embodiment, the gas turbine engine cooling system includes an impeller hav...
04/25/2013
20130098062COMPRESSOR BLEED COOLING FLUID FEED SYSTEM
A compressor bleed cooling fluid feed system for a turbine engine for directing cooling fluids from a compressor to a turbine airfoil cooling system to supply cooling fluids to one or more airfoils of a rotor assembly is disclosed. The compressor bleed cooling fluid fee...
04/25/2013
20130098063COOLNG STRUCTURE FOR RECOVERY-TYPE AIR-COOLED GAS TURBINE COMBUSTOR
In a cooling structure for a recovery-type air-cooled gas turbine combustor having a recovery-type air-cooling structure that bleeds, upstream of the combustor, and pressurizes compressed air supplied from a compressor, that uses the bled and pressurized air to cool a w...
04/25/2013
20130091858EFFUSION COOLED NOZZLE AND RELATED METHOD
A fuel nozzle for a turbine combustor includes a nozzle head configured to supply a fuel/air mixture to a burner tube attached to said nozzle head and extending downstream of the nozzle head. The burner tube is provided with plural holes for introducing a fluid into the...
04/18/2013
20130091862PRESSURIZED AUXILIARY POWER UNIT LUBRICATION SYSTEM
An exemplary lubrication system includes a flow path that carries fluid from a fluid supply through at least a portion of an auxiliary power unit to an outlet separate from the fluid supply. The fluid supply is pressurized to move the fluid along the flow path....
04/18/2013
20130086920COMBUSTOR AND METHOD FOR SUPPLYING FLOW TO A COMBUSTOR
A device for supplying flow to a combustor includes a flow sleeve configured to circumferentially surround the combustor, wherein the flow sleeve defines a first annular passage around the combustor. A first section of the first annular passage converges at a first conv...
04/11/2013
20130086921COMBUSTOR AND METHOD FOR SUPPLYING FLOW TO A COMBUSTOR
A device for supplying flow across a combustor includes an axial fluid injector configured to circumferentially surround at least a portion of the combustor. An inner annular passage extends through the axial fluid injector and provides fluid communication through the a...
04/11/2013
20130067928METHOD FOR OPERATING A GAS TURBINE PLANT AND GAS TURBINE PLANT FOR IMPLEMENTING THE METHOD
A method is provided for operating a gas turbine plant including a compressor, which on an inlet side inducts intake air and compresses it, providing compressor exit air on a discharge side. The plant also includes a combustion chamber where fuel is combusted, using com...
03/21/2013
20130067882BLEED AIR DUCT JOINT INSULATION MEANS
A bleed air duct joint insulation means is disclosed in which a leak vent comprises valve means....
03/21/2013
20130061600METHOD OF CONTROLLING TEMPERATURE OF GAS TURBINE COMPONENTS USING A COMPRESSED MOISURIZED COOLANT
A method and apparatus for controlling a temperature a component of a gas turbine is disclosed. A compressed gas for use as a coolant is provided. The coolant is moisturized at a moisturizeing unit. A circulating unit circulates the moisturized coolant to the component ...
03/14/2013
20130055724GAS TURBINE ENGINE AIR CYCLE SYSTEM
An air cycle system for a gas turbine engine includes a compressor, a turbine and a heat exchanger fluidly connected between the compressor and the turbine. A fluid source communicates a fluid through the heat exchanger. The heat exchanger exchanges heat between the flu...
03/07/2013
20130000321GAS TURBINE INLET HEATING SYSTEM
A gas turbine inlet heating system is disclosed. In one embodiment, the system includes: a compressor having: an inlet bellmouth adjacent to a set of inlet guide vanes (IGVs); and an outlet fluidly connected to the inlet bellmouth; and a conduit coupled to an outlet of ...
01/03/2013
20120312027FLOW DISCHARGE DEVICE
A bleed flow discharge device (136) adapted to discharge a bleed fluid flow into a main fluid flow, wherein the bleed flow discharge device comprises an outer wall (135) defining a passage (137) for the bleed fluid flow, the outer wall comprising a ...
12/13/2012
20120304663METHOD AND SYSTEMS FOR BLEED AIR SUPPLY
A method and system for an integrated ejector valve assembly is provided. The integrated ejector valve assembly includes a first valve assembly configured to control a flow of relatively lower pressure fluid from a first inlet port, a second valve assembly configured to...
12/06/2012
20120297780ACTIVE FUEL TEMPERATURE CONTROL
A system for managing fuel temperature in an engine includes a source of hot pressurized air and a turbine for converting hot pressurized air into cool expanded air. The system further includes a fuel tank for storing fuel, a fuel conduit fluidly connected to the fuel t...
11/29/2012
20120297789FLADE DUCT TURBINE COOLING AND POWER AND THERMAL MANAGEMENT
An aircraft compound cooling system includes a power thermal management system for cooling one or more aircraft components, an air cycle system, a vapor cycle system, and a turbine cooling circuit for cooling bleed air and cooling turbine components in a high pressure t...
11/29/2012
20120260667Power Plant
A power plant is provided and includes a gas turbine engine to generate power, a heat recovery steam generator (HRSG) to produce steam from high energy fluids produced from the generation of power in the gas turbine engine, a steam turbine engine to generate additional ...
10/18/2012
20120247121AIRCRAFT GAS TURBINE
An aircraft gas turbine is constituted by accommodating a compressor (14), a combustor (15), and a turbine (16) in a cylindrical main unit casing (12). A thick wall part (52) is provided on an outer periphery side of rotor blades (3...
10/04/2012
20120247117VEHICLE SYSTEM
A system is disclosed one form of which is an aircraft that includes a pod capable of housing a work providing device. The pod can also include a thermal conditioning system and a power generation device that can be powered from the work providing device. The pod can pr...
10/04/2012
20120247113SYSTEM AND METHOD FOR AIR EXTRACTION FROM GAS TURBINE ENGINES
The disclosed embodiments relate to a system and method that allows air to be extracted from a plurality of gas turbine engines and fed to a downstream process, even in situations in which one or more of the gas turbine engines are operating in a part load condition. Fo...
10/04/2012
20120227414GAS TURBINE ENGINE SWIRLED COOLING AIR
A gas turbine engine has in flow series a compressor section, a combustor, and a turbine section. The engine includes a turbine section rotor disc, and a stationary wall forward of a front face or rearward of a rear face of the rotor disc. The wall defines a cavity betw...
09/13/2012
20120216545ENVIRONMENTAL CONTROL SYSTEM SUPPLY PRECOOLER BYPASS
A precooler for cooling compressor bleed air for an environmental control system includes a heat exchanger in fluid communication with a source of cooling air and operable for cooling the bleed air. A variable bypass valve between a bleed air source and environmental co...
08/30/2012
20120210721DISTRIBUTED BLEED SYSTEM TEMPERATURE MANAGEMENT
A distributed bleed system temperature management scheme utilizes a distributed, closed loop temperature protection function. By allowing consumer systems to limit the consumer flow to meet a specified bleed system outlet temperature (which may be different for each con...
08/23/2012
20120192569PITOT TUBE WITH INCREASED PARTICLE SEPARATION EFFICIENCY
A pneumatically actuated valve includes a valve body, a pneumatic actuator, and a pitot tube. The valve body includes a valve disc positioned in a valve housing that defines a flow passage with a flow passage diameter. The pneumatic actuator rotates the valve disc in th...
08/02/2012
20120186267TURBINE INTEGRATED BLEED SYSTEM AND METHOD FOR A GAS TURBINE ENGINE
A bleed system for a gas turbine engine includes: (a) a bleed air turbine having a turbine inlet adapted to be coupled to a source of compressor bleed air at a first pressure; (b) a bleed air compressor mechanically coupled to the bleed air turbine, and having a compres...
07/26/2012
20120167587GAS TURBINE ENGINE WITH BLEED AIR SYSTEM
One embodiment of the present invention is a unique gas turbine engine. Another embodiment of the present invention is also a unique gas turbine engine. A further embodiment is a unique method for operating a gas turbine engine. Other embodiments include apparatuses, sy...
07/05/2012
20120167584CONTROLLING BLADE TIP CLEARANCES IN A TURBINE ENGINE
A turbine engine including a controller controlling clearance between tips of moving blades of a high-pressure turbine and an outer casing surrounding the blades, by cooling the outer casing by the impact of air taken from a high-pressure compressor stage of the engine,...
07/05/2012
20120167586Fuel Nozzle Passive Purge Cap Flow
A cooling circuit for a fuel nozzle in a gas turbine includes an end cap cavity receiving passive purge flow from a compressor of the turbine, and fuel nozzle swozzles disposed in a swozzle shroud that impart swirl to incoming fuel and air. Purge slots are formed in the...
07/05/2012
20120167588COMPRESSOR TIP CLEARANCE CONTROL AND GAS TURBINE ENGINE
One embodiment of the present invention is a unique compressor. Another embodiment of the present invention is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for blade tip clearance control for c...
07/05/2012
20120167589GAS TURBINE ENGINE AND SYSTEM FOR MODULATING SECONDARY AIR FLOW
One embodiment of the present invention is a unique gas turbine system having a system for modulating secondary air flow. Another embodiment is a compressor vane stage with a plenum employed in providing secondary air flow. Other embodiments include apparatuses, systems...
07/05/2012
20120151936TURBOJET INCLUDING AN AUTOMATICALLY VARIABLE FLOW RATE BLEED CIRCUIT FOR COOLING AIR
Bleeding cooling air to cool a subassembly, e.g. such as a turbine, with automatic adjustment of the air flow section as a function of the speed of the engine. According to the invention, a shutter element is fastened to co-operate with a bleed hole, with the material t...
06/21/2012
20120153076AIRCRAFT, PROPULSION SYSTEM, AND SYSTEM FOR TAXIING AN AIRCRAFT
One embodiment of the present invention is a unique aircraft. Another embodiment is a unique aircraft propulsion system. Still another embodiment is a unique system for taxiing an aircraft without starting one or more main aircraft propulsion engines. Other embodiments ...
06/21/2012
20120144842GAS TURBINE ENGINE AND HEAT EXCHANGE SYSTEM
One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique gas turbine engine heat exchange system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and heat ...
06/14/2012
20120137651GAS TURBINE SYSTEM
A gas turbine system (1A) includes a gas turbine unit (2) and a cooling fluid generator (5). The gas turbine unit (2) includes a first compressor (21) and a first expansion turbine (23) coupled to each other by a first shaft (
06/07/2012
20120137704METHODS AND APPARATUS FOR ASSEMBLING A LOW NOISE EJECTOR MOTIVE NOZZLE
A method of assembling an ejector is provided, wherein the method includes providing a motive nozzle tip having a centerline axis and including a nozzle tip edge having at least one protrusion extending through a plane substantially normal to the centerline axis. The me...
06/07/2012
20120125010Spring loaded pressure relief door
A pressure relief apparatus for an engine compartment having a wall and an opening in the wall is provided. The pressure relief apparatus includes a door panel arranged in blocking relationship to the opening in the wall of the engine compartment, a plurality of hinges ...
05/24/2012
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