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| Application No. | Application Title | Issue Date |
| 20130111916 | 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 with the normal load by firing at normal temperatures and in accordance w... | 05/09/2013 |
| 20130111921 | 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 portion of the compressed air to one side of a heat exchanger and steam (typical... | 05/09/2013 |
| 20130104564 | ACTIVE 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 |
| 20130098051 | AUXILIARY 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 |
| 20130098061 | GAS 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 |
| 20130098062 | COMPRESSOR 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 |
| 20130098063 | COOLNG 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 |
| 20130091858 | 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 burner tube is provided with plural holes for introducing a fluid into the... | 04/18/2013 |
| 20130091862 | PRESSURIZED 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 |
| 20130086920 | COMBUSTOR 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 |
| 20130086921 | COMBUSTOR 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 |
| 20130067928 | METHOD 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 |
| 20130067882 | BLEED 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 |
| 20130061600 | METHOD 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 |
| 20130055724 | GAS 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 |
| 20130000321 | GAS 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 |
| 20120312027 | FLOW 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 |
| 20120304663 | METHOD 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 |
| 20120297780 | 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 fuel tank for storing fuel, a fuel conduit fluidly connected to the fuel t... | 11/29/2012 |
| 20120297789 | FLADE 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 |
| 20120260667 | 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 in the gas turbine engine, a steam turbine engine to generate additional ... | 10/18/2012 |
| 20120247121 | 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 outer periphery side of rotor blades (3... | 10/04/2012 |
| 20120247117 | VEHICLE 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 |
| 20120247113 | SYSTEM 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 |
| 20120227414 | GAS 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 |
| 20120216545 | ENVIRONMENTAL 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 |
| 20120210721 | 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 specified bleed system outlet temperature (which may be different for each con... | 08/23/2012 |
| 20120192569 | PITOT 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 |
| 20120186267 | TURBINE 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 |
| 20120167587 | GAS 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 |
| 20120167584 | CONTROLLING 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 |
| 20120167586 | Fuel 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 |
| 20120167588 | COMPRESSOR 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 |
| 20120167589 | GAS 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 |
| 20120151936 | TURBOJET 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 |
| 20120153076 | 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 starting one or more main aircraft propulsion engines. Other embodiments ... | 06/21/2012 |
| 20120144842 | GAS 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 |
| 20120137651 | 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 each other by a first shaft ( 06/07/2012 | |
| 20120137704 | METHODS 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 |
| 20120125010 | Spring 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 |
