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Match Document Document Title
US20150052908 BLEED DUCT ASSEMBLY FOR A GAS TURBINE ENGINE  
A bypass duct has a support unit comprising a pair of aerofoils arranged as an “A” frame. A bleed duct assembly is provided on the radially inner wall of the bypass duct annulus and the aerofoils...
US20140345294 GAS TURBINE ENGINE WITH BLEED DUCT FOR MINIMUM REDUCTION OF BLEED FLOW AND MINIMUM REJECTION OF HAIL DURING HAIL INGESTION EVENTS  
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...
US20120117974 AIR FLOW DELIVERY AND FUEL CONSUMPTION CONTROL FOR AIRCRAFT AIR MANAGEMENT AND AUXILIARY POWER SYSTEMS  
A turbine controller controls the operation of a gas turbine generator used to drive an electric generator of an aircraft. The turbine controller controls the gas turbine generator according to...
US20110162386 Ejector-OBB Scheme for a Gas Turbine  
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...
US20150082804 TURBINE ENGINE INCORPORATING THERMOELECTRIC GENERATORS  
A front-fan turbojet engine including at least one fluid circuit and an air/fluid heat exchanger by which the fluid is cooled by air external to the turbojet engine and a splitter for splitting a...
US20110192170 AIR CONTAMINATION DETECTION IN AN AIRCRAFT AIR SYSTEM  
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...
US20140245747 GAS TURBINE ENGINE TWO DEGREE OF FREEDOM VARIABLE BLEED VALVE FOR ICE EXTRACTION  
A gas turbine engine variable bleed apparatus includes a variable bleed valve door disposed in a bleed inlet in a transition duct, rotatable about two or more separate pivot points, operable to...
US20120111021 Integrated Turbomachine Oxygen Plant  
An integrated turbomachine oxygen plant includes a turbomachine and an air separation unit. One or more compressor pathways flow compressed air from a compressor through one or more of a combustor...
US20150047315 GAS TURBINE ENGINE FLOW DUCT HAVING INTEGRATED HEAT EXCHANGER  
A gas turbine engine flow duct comprising a flow duct disposed along an engine centerline of the gas turbine engine and defining a stream flow passage, and first and second rows of heat exchangers...
US20140123674 Inlet Bleed Heat System with Integrated Air Knife/Silencer Panels  
The present application provides an inlet bleed heat system for supplying a flow of bleed air to a flow of incoming air into a compressor of a gas turbine engine. The inlet bleed heat system may...
US20130269366 MODULAR LOUVER SYSTEM  
Louver systems for gas turbine bleed air systems are disclosed. An example louver system may include a bleed system discharge opening arranged to vent bleed air from a bleed flow conduit and a...
US20140158242 PRESSURE SUPPLY FOR A WATER SYSTEM  
A pressure supply system for a fresh water system is provided. The pressure supply system includes a water reservoir having a bleed air inlet and a water outlet. The pressure supply system also...
US20130111916 SYSTEM 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...
US20080115503 MULTI-PORT BLEED SYSTEM WITH VARIABLE GEOMETRY EJECTOR PUMP  
A bleed air system selectively supplies engine bleed air from one or more of at least three bleed air sources to a variable geometry ejector pump. The bleed air system provides improved...
US20140060073 MULTIPLE POINT OVERBOARD EXTRACTOR FOR GAS TURBINE  
The disclosed overboard extractor provides overboard extraction of compressor fluid at multiple extraction points. The overboard extractor includes multiple extraction manifolds and a delivery...
US20130067882 BLEED AIR DUCT JOINT INSULATION MEANS  
A bleed air duct joint insulation means is disclosed in which a leak vent comprises valve means.
US20140053572 GAS TURBINE  
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...
US20120247121 AIRCRAFT 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...
US20110131999 THERMOELECTRIC GENERATOR ON AN AIRCRAFT BLEED SYSTEM  
A device for producing electrical power. A thermoelectric device is coupled to an aircraft bleed system for generating electrical power using temperature differentials between ram air and bleed air.
US20150143793 SELECTIVE PRESSURE KETTLE BOILER FOR ROTOR AIR COOLING APPLICATIONS  
A system for use in a combined cycle power plant including gas and steam turbines includes a single kettle boiler and a valve system. The valve system is operated such that feedwater from a first...
US20120260667 Power 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...
US20130111921 METHOD 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...
US20130186100 SMALL ENGINE COOLED COOLING AIR SYSTEM  
A system for managing thermal transfer in an aircraft includes a fuel stabilization unit, a fuel-air heat exchanger, and a turbine. The fuel-air heat exchanger is located downstream from the fuel...
US20120297780 ACTIVE 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...
US20110016877 CONTINUOUS SLOT IN SHROUD  
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...
US20100139288 HEAT EXCHANGER TO COOL TURBINE AIR COOLING FLOW  
A cooling system of a gas turbine engine, includes a heat exchanger having a common wall shared by a first air passage for directing a portion of a compressor air flow to be used as cooling air,...
US20150176590 FLOW OUTLET  
A noise attenuation panel for a bleed flow is presented that causes a total pressure loss of the bleed flow before it is exhausted. The total pressure loss results from at least two regions in...
US20150059355 Method and System for Controlling Gas Turbine Performance With a Variable Backflow Margin  
A system and method for controlling the performance of a gas turbine system is provided. A backflow margin pressure ratio for a component is determined. A modified backflow margin pressure ratio...
US20130247584 ACTIVE CONTROL OF COMPRESSOR EXTRACTION FLOWS USED TO COOL A TURBINE EXHAUST FRAME  
A gas turbine includes at least one combustor and an exhaust frame; a compressor adapted to supply air to the combustor and to supply bleed air to the exhaust frame. A cooling air supply duct is...
US20130192251 BUFFER SYSTEM THAT COMMUNICATES BUFFER SUPPLY AIR TO ONE OR MORE PORTIONS OF A GAS TURBINE ENGINE  
A gas turbine engine includes a buffer system that can communicate a buffer supply air to a portion of the gas turbine engine. The buffer system includes a first bleed air supply having a first...
US20140165583 BLEED VALVE OVERRIDE SCHEDULE ON OFF-LOAD TRANSIENTS  
In one aspect, the present disclosure is directed to a method for controlling a position of a bleed valve of a gas turbine engine. The onset of an off-load transient may be determined. Values...
US20130192253 GAS TURBINE ENGINE BUFFER SYSTEM PROVIDING ZONED VENTILATION  
A gas turbine engine includes a first zone and a second zone downstream from the first zone. A buffer system can communicate a buffer cooling air to at least the first zone. A bleed source can...
US20130213054 Gas Turbine Inlet System with Solid-State Heat Pump  
A gas turbine inlet system includes a first passage that delivers inlet air to a compressor, a second passage that delivers fuel to a combustor, and a heat pump that transfers heat from the inlet...
US20130192238 BUFFER SYSTEM THAT COMMUNICATES BUFFER SUPPLY AIR TO ONE OR MORE PORTIONS OF A GAS TURBINE ENGINE  
A gas turbine engine includes a buffer system that communicates a buffer supply air to a portion of the gas turbine engine. The buffer system includes a first bleed air supply having a first...
US20120210721 DISTRIBUTED 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...
US20090188234 SHARED FLOW THERMAL MANAGEMENT SYSTEM  
A thermal management system includes at least two of a multiple of heat exchangers arranged in an at least partial-series relationship.
US20130199205 CUSTOMER BLEED AIR PRESSURE LOSS REDUCTION  
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...
US20120137651 GAS 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...
US20130091858 EFFUSION 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...
US20130192250 GAS TURBINE ENGINE BUFFER SYSTEM  
A gas turbine engine includes a buffer system that can communicate buffer supply air to a portion of the gas turbine engine. The buffer system can include a first circuit and a second circuit. The...
US20100314877 GAS TURBINE BLEED ENERGY RECOVERY VIA COUNTER ROTATING GENERATOR  
A gas turbine engine includes a main compressor section for compressing air, a main combustor section positioned downstream of the main compressor section, a main turbine section positioned...
US20090149122 AIRCRAFT AIR CONDITIONING SYSTEM  
According to the invention, in addition to a main air conditioning device (4, 5) which taps air off the turbine engine (2), the invention provides an auxiliary unit (16 to 22) with compressor,...
US20140000278 TURBOMACHINE THERMAL ENERGY EXCHANGE  
An example method of thermal energy exchange within a turbomachine includes heating a liquid using thermal energy from compressed air, injecting the liquid into a first portion of a turbomachine,...
US20120153076 AIRCRAFT, 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...
US20130239582 CONSTANT SPEED PUMP SYSTEM FOR ENGINE ECS LOSS ELIMINATION  
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...
US20090188232 THERMAL MANAGEMENT SYSTEM INTEGRATED PYLON  
A thermal management system includes at least one heat exchanger in communication with a bypass flow of a gas turbine engine. The placement of the heat exchanger(s) minimizes weight and...
US20150068217 INLET BLEED HEAT SYSTEM AND RELATED METHOD FOR A COMPACT GAS TURBINE INLET  
An inlet system for a gas turbine includes an inlet air duct; a silencer disposed in the inlet air duct, the silencer including a plurality of panels with spaces between the panels; and a conduit...
US20090235670 Bleed Air Supply System and Method to Supply Bleed Air to an Aircraft  
The invention relates to a bleed air supply system and a safety device for closing a valve in at least one of the several bleed air supply lines depending on an alarm signal that indicates an...
US20050109016 Turbine tip clearance control system  
An apparatus and method for selectively cooling a gas turbine engine component for the purpose of controlling blade tip clearance during transient conditions, wherein cooling air is admitted...
US20120102969 CENTRIFUGAL COMPRESSOR WITH BLEED FLOW SPLITTER FOR A GAS TURBINE ENGINE  
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.

Matches 1 - 50 out of 343 1 2 3 4 5 6 7 >