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Air Bleed

Air Bleed patent applications listed include Date, Patent Application Number, Patent Title, Patent Abstract summary and are linked to the corresponding patent application page.

Related Categories:

Power Plants


Combustion Products Used As Motive Fluid > For Nominal Other Than Power Plant Output Feature > Air Bleed



Gas turbine engine with bleed duct for minimum reduction of bleed flow and minimum rejection of hail during hail ingestion events
11/27/14 - 20140345294 - A gas turbine engine includes a bleed structure which includes a forward wall and a rear structural wall to define a deposit space downstream of the bleed structure for a hail event of a predetermined duration....

Aircraft having an engine, a fuel tank, and a fuel cell
11/06/14 - 20140325991 - An aircraft includes a propulsion unit with a compressor and a bleed air device for providing bleed air from the propulsion unit, a fuel tank for a fuel, at least one fuel cell, a reactor for reforming fuel from the fuel tank to a hydrogen-containing fuel gas, and at least...

Contamination free reverse flow fitting
10/09/14 - 20140298823 - A precooler for an aircraft engine system includes a precooler core and a precooler inlet to direct a compressor bleed flow into the precooler core to cool the compressor bleed flow. The precooler further includes a precooler outlet to direct the compressor bleed flow from the precooler to a selected...

Nacelle anti-ice valve utilized as compressor stability bleed valve during starting
09/04/14 - 20140245749 - A gas turbine engine has a compressor section received within an inner housing. An is an outer housing is spaced radially outwardly of the inner core housing. A nacelle has an anti-icing system which taps compressed air from the compressor section through an anti-ice valve and to the nacelle. The...

Gas turbine engine buffer system
08/28/14 - 20140238042 - A gas turbine engine includes a fan, a compressor section, and a turbine section configured to drive the compressor section and the fan. A buffer system is configured to communicate a buffer supply air to a portion of the gas turbine engine. The buffer system includes a first bleed air...

Low pressure compressor bleed exit for an aircraft pressurization system
07/17/14 - 20140196469 - An aircraft pressurization system, includes an auxiliary compressor for further compressing compressed air received from a low pressure compressor section of a gas turbine engine while the compressed air is below a predetermined pressure level; a bleed passage for fluidically connecting the auxiliary compressor to the low pressure compressor section;...

Gas turbine engine buffer system
07/17/14 - 20140196470 - A gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, a fan section configured to be driven by the turbine section via a geared architecture, and a buffer system that communicates buffer air to...

System and method for expanding a compressor bleed flow
07/03/14 - 20140182307 - A system includes a bleed system configured to direct a bleed flow from a high pressure region to a low pressure region. The bleed system includes a valve configured to control the bleed flow through the bleed system and a staged bleed conduit configured to incrementally depressurize the bleed flow....

System for controlling a cooling flow from a compressor section of a gas turbine
06/12/14 - 20140157791 - A system for controlling a flow rate of a compressed cooling medium between a compressor section and a turbine section of a gas turbine includes a flow path that is defined between the compressor section and the turbine section of the gas turbine and a thermally actuated variable flow valve...

Air cooling shaft at bearing interface
06/05/14 - 20140150449 - A gas turbine engine including a compressor rotor and a turbine rotor connected by a compressor shaft portion connected to the compressor rotor and a turbine shaft portion connected to the turbine rotor. The compressor shaft portion and the turbine shaft portion are connected axially together by a shaft coupling,...

Bleed air slot
04/10/14 - 20140096536 - A disclosed gas turbine engine includes a case for a case for a compressor section including a bleed air slot. The bleed air slot includes an inlet having a first area radially inward of an outlet having a second area with the second area being greater than the first area....

Bleed tube attachment
04/03/14 - 20140090397 - An anti-vortex assembly for a gas turbine engine includes a support ring including a seat surrounding an opening and a bleed tube including a base with a bearing face sealing against the seat. A retaining ring is mounted within the support ring and engages the base of the bleed air...

Turbomachine with bleed valves located at the intermediate case
03/20/14 - 20140075956 - An assembly including an intermediate case of a bypass turbojet engine and of an inter-jet case extending upstream of the intermediate case to separate a primary air jet of the turbojet engine from its bypass air jet, the inter-jet case including, passing through it, a closable duct for diverting part...

Gas turbine engine buffer system
03/06/14 - 20140060075 - A gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, and a buffer system. The buffer system can include a first circuit that supplies a first buffer supply air and a second circuit that...

Gas turbine
02/27/14 - 20140053572 - A gas turbine provided with an air bleeder tube (1) that, during startup, bleeds a portion of the compressed air of a compressor from the compressor and discharged the bled air into a cylindrical exhaust duct (20), wherein the air bleeder tube (1) is disposed at a portion that does...

Flow discharge device
02/06/14 - 20140033733 - 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 wave-shaped edge (139) where the bleed fluid...

Baffle assembly for bleed air system of gas turbine engine
01/16/14 - 20140013767 - A baffle assembly for a housing of a combustor system of a gas turbine engine is provided. The baffle assembly includes a baffle retainer and a baffle. The baffle retainer includes a retainer tube and a collar. The retainer tube is received within a bleed port of the housing. The...

Machined aerodynamic intercompressor bleed ports
12/26/13 - 20130340440 - An air bleed system for a jet engine is provided. The air bleed system is located in the low pressure compressor chamber and comprises a movable bleed valve and a stationary, annular bleed case having a forward section and an aft section and ligaments connecting the two sections and providing...

Aerodynamic intercompressor bleed ports
12/26/13 - 20130340441 - An air bleed system for a gas turbine engine includes an annular bleed case with a manifold therein. The annular bleed case has a forward section and an aft section and ligaments connecting the two sections. The forward section, the aft section and the ligaments define bleed ports. The manifold...

Fuel nozzle cap
11/21/13 - 20130305739 - Certain embodiments include a first individual sector configured to fit together with a plurality of individual sectors to form a combustor cap assembly of a turbine combustor, wherein the first individual sector is configured to fixedly attach to a first fuel nozzle of a plurality of fuel nozzles, the first...

Air cooler system for gas turbine engines
11/07/13 - 20130291554 - A buffer air cooler system for gas turbine engines disposed in a bypass duct of the engine, includes a housing for containing the buffer air cooler therein and an inlet portion attached to the housing. In one embodiment, the inlet portion has a double-skin configuration in at least one region...

Aircraft gas turbine having a booster bleed duct in a stator vane root element of a bypass duct
10/24/13 - 20130276453 - The present invention relates to an aircraft gas turbine having a core engine and a bypass duct surrounding the latter, where the core engine includes in its inflow zone a booster, in the area of which at least on booster bleed duct is provided for supplying an airflow from the...

Constant speed pump system for engine ecs loss elimination
09/19/13 - 20130239582 - A gas turbine engine has an impeller pump for delivering air to an environmental control system and a speed control pump connected to the impeller pump for driving the impeller pump at a constant speed....

Pump system for hpc eps parasitic loss elimination
09/19/13 - 20130239583 - An engine includes a duct containing a flow of cool air and a pump system for providing air to an environmental control system. The pump system has an impeller having an inlet for receiving cool air from the duct and an outlet for discharging air to the environmental control system....

Mid-section of a can-annular gas turbine engine with a cooling system for the transition
08/29/13 - 20130219921 - A cooling system is provided for a transition (420) of a gas turbine engine (410). The cooling system includes a cowling (460) configured to receive an air flow (111) from an outlet of a compressor section of the gas turbine engine (410). The cowling (460) is positioned adjacent to a...

Outer fuel nozzle inlet flow conditioner interface to end cap
08/15/13 - 20130205799 - An interface between an inlet flow conditioner and a compressor discharge air passage in a gas turbine includes a cap back plate including a curved exterior surface, and an inlet flow conditioner (IFC) cooperable with the cap back plate. An end of the IFC includes a curved exterior surface that...

Customer bleed air pressure loss reduction
08/08/13 - 20130199205 - A bleed air supply system for a gas turbine engine comprising a duct having an inlet end and extending to an outlet end. The inlet end of the duct is provided with a central insert. In another feature, there may be a plurality of ducts, and inlet ends of the...

Heat exchanger
08/01/13 - 20130192254 - A gas turbine engine has a fan, a compressor section, a combustor, and a turbine section. The fan delivers a portion of air into the compressor, and into a duct, as bypass air. A bleed air system bleeds a quantity of air from the compressor into a chamber at least...

Method of using external fluid for cooling high temperature components of gas turbine for a process power plant
07/25/13 - 20130186101 - An external fluid in a closed loop is used to cool hot gas path components of gas turbine. After cooling the turbine components, the heated external fluid is dumped either in the compressor discharge casing or in the one of the turbine's stages. Where the external fluid is nitrogen to...

Gas turbine engine in-board cooled cooling air system
07/25/13 - 20130186102 - A system for supplying turbine cooling air flow includes a turbofan engine, a heat exchanger, and a door. The turbofan engine includes an engine case that has an inner volume within which at least a gas turbine engine is mounted, and a bypass flow passage that is defined by an...

Environmental control system for aircraft utilizing turbo-compressor
07/11/13 - 20130174573 - An environmental control system includes a higher pressure tap to be associated with a higher compression location in a main compressor section associated with a gas turbine engine. A lower pressure tap is associated with a lower pressure location, which is at a lower pressure than the higher pressure location....

Gas turbine engine bearing chamber seals
07/11/13 - 20130174574 - A gas turbine engine sealing air supply system comprising a bearing chamber seal to prevent lubricant fluid loss from a fluid chamber, the sealing effected by ingress of sealing air. An air supply duct is coupled to the bearing chamber seal to provide the sealing air. A first duct is...

Method for optimizing the operability of an aircraft propulsive unit, and self-contained power unit for implementing same
06/06/13 - 20130139522 - A method for optimizing operability of an aircraft propulsive unit, and a self-contained power unit implementing the method. The method removes mechanical bleed constraints in engines during transient flight phases of an aircraft to optimize operability of the engine assembly during the phases. To this end, a supply of power...

Gas turbine engine cooling systems having hub-bleed impellers and methods for the production thereof
04/25/13 - 20130098061 - 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 having a hub, a plurality of hub...

Compressor bleed cooling fluid feed system
04/25/13 - 20130098062 - 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 feed system may enable cooling fluids...

Coolng structure for recovery-type air-cooled gas turbine combustor
04/25/13 - 20130098063 - 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 wall, and that recovers and reuses the bled and pressurized...

Pressurized auxiliary power unit lubrication system
04/18/13 - 20130091862 - 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....

Gas turbine inlet heating system
01/03/13 - 20130000321 - 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 the compressor, the conduit...

Flow discharge device
12/13/12 - 20120312027 - 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 wave-shaped edge (139) where the bleed fluid...

Method and systems for bleed air supply
12/06/12 - 20120304663 - 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 control a flow of relatively higher pressure...

Flade duct turbine cooling and power and thermal management
11/29/12 - 20120297789 - An air to air FLADE duct heat exchanger is disposed in a FLADE duct of the engine and a valving apparatus is operable for selectively switching the FLADE duct heat exchanger between the turbine cooling circuit and the air cycle system. A vapor cycle system includes a vapor cycle system...

Aircraft gas turbine
10/04/12 - 20120247121 - 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 (34) in the main unit casing (12), a cooling passage...

Pitot tube with increased particle separation efficiency
08/02/12 - 20120192569 - 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 the valve housing. The pitot...

Compressor tip clearance control and gas turbine engine
07/05/12 - 20120167588 - 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 compressors and gas turbine engine compressors. Further embodiments, forms, features, aspects, benefits,...

Gas turbine engine and system for modulating secondary air flow
07/05/12 - 20120167589 - 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, devices, hardware, methods, and combinations for secondary air flow...

Turbojet including an automatically variable flow rate bleed circuit for cooling air
06/21/12 - 20120151936 - 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 that constitutes either...

Gas turbine engine and heat exchange system
06/14/12 - 20120144842 - 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 exchange systems for gas turbine engines. Further embodiments, forms, features, aspects,...

Methods and apparatus for assembling a low noise ejector motive nozzle
06/07/12 - 20120137704 - 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 method also includes coupling the motive nozzle...

Centrifugal compressor with bleed flow splitter for a gas turbine engine
05/03/12 - 20120102969 - An impeller includes a plurality of vanes formed around a hub, each of the plurality of vanes defines an offset between a leading edge and a trailing edge....

Bleed valve
03/22/12 - 20120067061 - A bleed valve having an inlet port and an outlet port. The bleed valve comprises mutually perpendicular radial, longitudinal and tangential axes arranged such that the outlet port is substantially in a plane defined by the longitudinal and tangential axes. The bleed valve also comprises at least one vane spanning...

Inner bleed structure of 2-shaft gas turbine and a method to determine the stagger angle of last stage stator of compressor for 2-shaft gas turbine
03/15/12 - 20120060509 - An inner bleed structure of the 2-shaft gas turbine includes a slit for leading part of compressed air to a cavity is formed between a wall surface of a rotor wheel of the compressor equipped with a last stage rotor of the compressor which is connected to a first rotating...

Air bleed having an inertial filter in the tandem rotor of a compressor
02/16/12 - 20120036865 - The invention relates to a secondary air system for a compressor of centrifugal or mixed type including a rotor presenting an axis of rotation, said compressor being adapted to compress an oxidizer gas. The secondary air system includes an oxidizer gas bleed system arranged in the rotor....

Gas turbine engine system with bleed air powered auxiliary engine
11/10/11 - 20110271687 - One embodiment of the present invention is a unique gas turbine engine with a bleed air powered auxiliary engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for bleed air powered auxiliary engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent...

Flow mixing vent system
11/03/11 - 20110265490 - A vent system is disclosed having a first flow stream flowing over a first surface in a flow path, a conduit that channels a second flow stream and an aero-chimney that is in flow communication with the conduit and located near the first surface wherein the aero-chimney has a body...

Bearing compartment pressurization and shaft ventilation system
08/25/11 - 20110203293 - An assembly and method for providing buffer air and/or ventilation air within a gas turbine engine, the assembly includes an accessory gearbox and a centrifugal compressor. The accessory gearbox is connected to a driven shaft of the gas turbine engine. The centrifugal compressor is driven by the accessory gearbox during...

Air contamination detection in an aircraft air system
08/11/11 - 20110192170 - An aircraft air system includes a gas turbine engine, a bleed air duct directing compressed air bled from a compressor to an inner compartment within the aircraft, and an air contamination detector located downstream of the gas turbine engine compressor. The air contamination detector includes a visual indicator which detects...

Bled diffuser fed secondary combustion system for gas turbines
07/28/11 - 20110179803 - The present subject matter provides a system for modifying static pressure recoveries and emissions formation within a gas turbine. The system includes a bled diffuser positioned downstream from a compressor section of the gas turbine and a bleed duct extending from the bled diffuser. The bleed duct may be configured...

Ejector-obb scheme for a gas turbine
07/07/11 - 20110162386 - A cooling circuit in a gas turbine includes an over board bleed (OBB) circuit bleeding air from a last stage of the compressor, an extracted air circuit extracting air from an upstream stage of the compressor, and an ejector receiving input from the OBB circuit and the extracted air circuit....

Gas turbine engine surge margin bleed power recuperation
06/30/11 - 20110154830 - The present invention provides in one embodiment of the present invention a surge margin power recuperation system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for recuperating power from surge margin bleed air. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent...

Method and apparatus for controlling fluid flow
06/23/11 - 20110146296 - A method and apparatus for controlling fluid flow is provided. The valve assembly includes a valve body including a longitudinal axis and a radially inner internal flow passage extending axially between an inlet opening and an outlet opening, a disk selectively positionable to modulate a flow of working fluid through...

Bleed assembly for a gas turbine engine
06/23/11 - 20110146297 - A bleed assembly for a gas turbine engine is provided. The assembly includes: a duct having an inlet and an outlet; a bleed valve that controls the flow of bleed fluid into the inlet; and a dome-shaped diffuser screen which covers the outlet. The diffuser screen has a plurality of...

Bleed air transfer tube
04/07/11 - 20110079018 - A fluid-conveying device including an inner tubular member with a circumferential end portion, a non-elastomeric ring received in a depression of the end portion, and an outer tubular member. The ring has a peripheral surface with a rounded contour defined along a longitudinal direction configured to remain out of the...

Air manifold in a turbomachine
03/31/11 - 20110072829 - A turbomachine including an intermediate casing including, fastened to the end thereof, an outer casing of a high pressure compressor, and an air bleed mechanism bleeding air downstream from the stream through the compressor and including an outlet connected to an air reinjection mechanism reinjecting air upstream from the compressor...

Continuous slot in shroud
01/27/11 - 20110016877 - A compressor shroud has a continuous slot defined in a gaspath side surface thereof for communicating through the body of the shroud. Spaced-apart structural bridges span a rear portion of the slot in the shroud to maintain structural rigidity of the shroud. The method of forming the continuous slot is...

Systems and methods for gas turbine combustors
01/27/11 - 20110016878 - A gas turbine system comprising, a diffuser operative to diffuse an airstream output from a compressor, a fuel nozzle operative to receive fuel and emit the fuel in a combustor, and at least one bleed duct operative to direct bleed air from down stream of the combustor to the fuel...

Air filtration system for gas turbine engine pneumatic system
12/30/10 - 20100326090 - A gas turbine engine pneumatic system for controlling an air bleed valve includes a variable orifice device for controllably discharging air from the pneumatic system in order to reduce a maximum air pressure applied to the air bleed valve, to a predetermined level. A filter device is provided to filter...

Apu bleed valve with integral anti-surge port
12/16/10 - 20100313573 - A compressor bleed air valve in an auxiliary power unit (“APU”) modulates bleed air flow both for accessory pneumatic systems powered by the bleed air and for reducing or removing surge in the compressor....

Aircraft propulsion assembly comprising hot air bleed systems
11/11/10 - 20100281880 - An aircraft propulsion unit includes a nacelle (50) in which a power plant (52) is arranged. The nacelle includes an inside wall that delimits a pipe (54) with an air intake (56) at the front. The propulsion unit includes a frost treatment system having at least one first pipe (62)...

Direct transfer axial tangential onboard injector system (tobi) with self-supporting seal plate
11/04/10 - 20100275612 - An apparatus for cooling turbine blades in a turbine engine including a direct transfer axial tangential onboard injector (TOBI) for a turbine rotor and a self-supporting seal plate disposed on a rotating disk for the turbine engine. The TOBI includes a plurality of openings emanating a flow of cooling air....

Compressor for a gas turbine
11/04/10 - 20100275613 - An axial compressor providing a thermal adjustment of a housing of a compressor of a stationary gas turbine to the rotor is provided. A partial flow is decoupled from the compressor air flow for cooling gas turbine components. The contact of the partial flow decoupled from the compressor with the...

Flow discharge device
09/23/10 - 20100236256 - A flow discharge device, such as a compressor bleed outlet discharging into a bypass duct of a gas turbine engine, comprises an outlet panel 46 which is perforated by openings 48, 50 disposed in an array which tapers in the downstream direction with respect to the flow B in the...