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| Application No. | Application Title | Issue Date |
| 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 |
| 20120102969 | 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.... | 05/03/2012 |
| 20120067061 | BLEED VALVE 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 val... | 03/22/2012 |
| 20120047908 | METHOD FOR OPERATING A BURNER ARRANGEMENT AND BURNER ARRANGEMENT FOR IMPLEMENTING THE METHOD An exemplary burner arrangement and method for operating a burner arrangement are disclosed. During operation of the burner arrangement a hot combustion gas, including combustion air, flows essentially parallel to a burner wall through a mixing chamber, which is delimit... | 03/01/2012 |
| 20120036864 | GAS TURBINE ENGINE AND METHOD FOR COOLING THE COMPRESSOR OF A GAS TURBINE ENGINE A gas turbine engine includes a compressor with rotor blades having roots connected into seats of a compressor drum. The rotor blade roots and/or the compressor drum have longitudinal passages for a cooling fluid, connecting higher pressure areas to lower pressure areas... | 02/16/2012 |
| 20120036865 | AIR BLEED HAVING AN INERTIAL FILTER IN THE TANDEM ROTOR OF A COMPRESSOR 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 arra... | 02/16/2012 |
| 20110271687 | GAS TURBINE ENGINE SYSTEM WITH BLEED AIR POWERED AUXILIARY ENGINE 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, f... | 11/10/2011 |
| 20110265490 | FLOW MIXING VENT SYSTEM 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... | 11/03/2011 |
| 20110247344 | REAR HUB COOLING FOR HIGH PRESSURE COMPRESSOR In one exemplary embodiment, a gas turbine engine includes a turbine and a high pressure compressor. The high pressure compressor includes a last stage having a last stage compressor blade and a last stage vane. The gas turbine engine includes a first flow path through ... | 10/13/2011 |
| 20110203293 | BEARING COMPARTMENT PRESSURIZATION AND SHAFT VENTILATION SYSTEM 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 c... | 08/25/2011 |
| 20110192170 | 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 detector located downstream of the gas turbine engine compressor. The air contami... | 08/11/2011 |
| 20110179803 | BLED DIFFUSER FED SECONDARY COMBUSTION SYSTEM FOR GAS TURBINES 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... | 07/28/2011 |
| 20110162386 | 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 the compressor, and an ejector receiving input from the OBB circuit and the ... | 07/07/2011 |
| 20110154830 | GAS TURBINE ENGINE SURGE MARGIN BLEED POWER RECUPERATION 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 e... | 06/30/2011 |
| 20110146296 | METHOD AND APPARATUS FOR CONTROLLING FLUID FLOW 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 position... | 06/23/2011 |
| 20110146297 | BLEED ASSEMBLY FOR A GAS TURBINE ENGINE 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 p... | 06/23/2011 |
| 20110131999 | 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.... | 06/09/2011 |
| 20110088405 | GAS TURBINE ENGINE TEMPERATURE MODULATED COOLING FLOW A gas turbine engine cooling system includes a heat exchanger in fluid communication with a source of cooling air, a first cooling circuit including a first heat exchanger circuit in the heat exchanger and a first bypass circuit with a first bypass valve for selectively... | 04/21/2011 |
| 20110079018 | BLEED AIR TRANSFER TUBE 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 longi... | 04/07/2011 |
| 20110072829 | AIR MANIFOLD IN A TURBOMACHINE 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 r... | 03/31/2011 |
| 20110072828 | GAS TURBINE ENGINE SYSTEM PROVIDING SIMULATED BOUNDARY LAYER THICKNESS INCREASE A gas turbine engine system for an aircraft includes a nacelle having a fan cowl with an inlet lip section and a core cowl, at least one compressor and at least one turbine, at least one combustor between the compressor and the turbine, a bleed passage, and a controller... | 03/31/2011 |
| 20110016878 | Systems and Methods for Gas Turbine Combustors 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 ... | 01/27/2011 |
| 20110016877 | 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 slot in the shroud to maintain structural rigidity of the shroud. The method ... | 01/27/2011 |
| 20100326089 | 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... | 12/30/2010 |
| 20100326090 | AIR FILTRATION SYSTEM FOR GAS TURBINE ENGINE PNEUMATIC SYSTEM 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 f... | 12/30/2010 |
| 20100326088 | GAS TURBINE, LOAD COUPLING OF GAS TURBINE, AND COOLING METHOD OF GAS TURBINE COMPRESSOR To include a cooling passage leading from a latter stage of a compressor, via an external cooler, to a hollow part provided in a load coupling that couples a rotor of the compressor and a rotor of a turbine to each other, and also leading from the hollow part to the lat... | 12/30/2010 |
| 20100314877 | 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 downstream of the main combustor section, and a spool extending from the main co... | 12/16/2010 |
| 20100313573 | APU BLEED VALVE WITH INTEGRAL ANTI-SURGE PORT 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.... | 12/16/2010 |
| 20100300113 | ANTI-VORTEX DEVICE FOR A GAS TURBINE ENGINE COMPRESSOR An anti-vortex device for use in a compressor rotor assembly of a gas turbine engine is described. Spaced-apart radial passageways extend from an axially extending passage provided in a central area of the device to an outer peripheral rim surface thereof. The radial pa... | 12/02/2010 |
| 20100288890 | WING-ENGINE COMBINATION, AN AIRCRAFT, AND A WING SECTION OF AN AIRCRAFT COMPRISING AN ENGINE BLEED-AIR DUCT ARRANGEMENT A wing-engine combination includes: a wing with a main wing and an engine with a premixing chamber, a combustion chamber and a hot-air space, which includes: an engine bleed-air duct, which extends along the wingspan direction and along the leading edge of the main wing... | 11/18/2010 |
| 20100281879 | MULTI-SOURCE GAS TURBINE COOLING A cooling arrangement for a gas turbine engine includes: (a) a turbine nozzle having: (i) spaced-apart arcuate inner and outer bands; and (ii) a hollow, airfoil-shaped turbine vane extending between the inner and outer bands, the vane disposed in a primary flowpath of t... | 11/11/2010 |
| 20100281875 | Dynamic control of a gas turbine engine compressor during rapid transients A gas turbine engine is disclosed that has with two or more compressors. A first one of the compressors include a compressor variable geometry mechanism that may be in the form of adjustable vanes, bleed valves, or the like. A first one of the compressors is turned at a... | 11/11/2010 |
| 20100281880 | AIRCRAFT PROPULSION ASSEMBLY COMPRISING HOT AIR BLEED SYSTEMS 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 sy... | 11/11/2010 |
| 20100275612 | DIRECT TRANSFER AXIAL TANGENTIAL ONBOARD INJECTOR SYSTEM (TOBI) WITH SELF-SUPPORTING SEAL PLATE 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 ope... | 11/04/2010 |
| 20100275613 | Compressor for a gas turbine 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 f... | 11/04/2010 |
| 20100242491 | Systems and Methods for Controlling Compressor Extraction Cooling Embodiments of methods and apparatus for providing compressor extraction cooling are provided. According to one example embodiment, a method is disclosed for controlling compressor extraction cooling. The method can include providing a cooling medium. The method can inc... | 09/30/2010 |
| 20100236256 | FLOW DISCHARGE DEVICE 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 respec... | 09/23/2010 |
| 20100219638 | Turbomachinery Electric Generator Arrangement A turbomachinery electric generator arrangement includes a rotary compressor, a generator having a rotary armature and a stator, a combustion chamber to which compressed gas is directed from the compressor, a rotary turbine to which combustion product is directed from t... | 09/02/2010 |
| 20100199683 | OPTIMIZATION OF LOW-BTU FUEL-FIRED COMBINED-CYCLE POWER PLANT BY PERFORMANCE HEATING Disclosed is an optimized approach of using bleed-off of compressed air flow from a gas turbine compressor in a combined-cycle power plant and performance heating to augment plant performance. In one embodiment, a diverted portion of a by-product off gas and the bleed-o... | 08/12/2010 |
| 20100180574 | GAS TURBINE ENGINE A gas turbine engine is disclosed which comprises a bypass duct, a core engine, and a fluid mixing arrangement. The fluid mixing arrangement is configured to mix a bypass flow of fluid and a secondary flow of fluid, the secondary flow of fluid being drawn from the core ... | 07/22/2010 |
