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Match Document Document Title
US20140165593 GAS TURBINE ENGINE TURBINE BLADE LEADING EDGE TIP TRENCH COOLING  
An airfoil for a gas turbine engine includes pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil having an exterior surface that...
US20140083116 GAS TURBINE ENGINE COMPONENTS WITH BLADE TIP COOLING  
A turbine rotor blade for a turbine section of an engine is provided. The rotor blade includes a platform and an airfoil extending from the platform into a mainstream gas path of the turbine...
US20140216056 HEAT EXCHANGE MODULE FOR A TURBINE ENGINE  
A heat exchange module is provided for a turbine engine. The heat exchange module includes a duct and a plurality of heat exchangers. The duct includes a flowpath defined radially between a...
US20140096502 BURNER FOR A GAS TURBINE  
A burner for a gas turbine is provided. The burner has a pilot combustor, a supply module providing pilot fuel and air into a pilot combustion room enclosed by a pilot burner housing having a...
US20110079019 COOLING AIR SYSTEM FOR MID TURBINE FRAME  
A mid turbine frame is disposed between high and low pressure turbine assemblies. A cooling air system defined in the mid turbine frame of a gas turbine engine includes internal cavities for...
US20150082808 GAS TURBINE ENGINES WITH TURBINE AIRFOIL COOLING  
An airfoil for a gas turbine engine is provided. The airfoil includes a body with a leading edge, a trailing edge, a first side wall extending between the leading edge and the trailing edge, and a...
US20130104560 GAS TURBINE ENGINE WITH INTERCOOLING TURBINE SECTION  
A gas turbine engine includes a fan section and an intercooling turbine section along an engine axis aft of a fan section and forward of a combustor section.
US20130098050 GAS TURBINE ENGINE WITH INTERCOOLING TURBINE SECTION  
A gas turbine engine includes a fan section and an intercooling turbine section along an engine axis aft of a fan section and forward of a combustor section.
US20110079021 APPARATUS AND METHOD FOR REMOVING HEAT FROM A GAS TURBINE  
An apparatus for removing heat from a turbine includes a stator having a cavity and a first plenum and a second plenum inside the cavity. The second plenum is connected to the first plenum and...
US20140318141 HOT STREAK ALIGNMENT FOR GAS TURBINE DURABILITY  
Embodiments of hot streak alignment for gas turbine durability include structures and methods to align hot streaks with the leading edges of aligned first stage nozzle vanes in order to improve...
US20150167493 TURBINE BUCKET AND METHOD FOR COOLING A TURBINE BUCKET OF A GAS TURBINE ENGINE  
The present application and the resultant patent provide a turbine bucket for a gas turbine engine. The turbine bucket may include a platform, an airfoil extending radially outward from the...
US20140165570 OSCILLATING HEAT PIPE FOR THERMAL MANAGEMENT OF GAS TURBINE ENGINES  
An oscillating heat pipe of a gas turbine engine includes a plurality of channels that define a continuous loop through which a fluid flows, and an evaporator of a gas turbine engine. The fluid...
US20130247587 BI-METALLIC ACTUATOR FOR SELECTIVELY CONTROLLING AIR FLOW BETWEEN PLENA IN A GAS TURBINE ENGINE  
A system for selectively supplying air between separate plena of a gas turbine engine includes a gas turbine engine, a door, and a bi-metallic door actuator. The gas turbine engine comprises at...
US20120079827 AIR-COOLED SWIRLERHEAD  
A combustor for a gas turbine engine is disclosed which is able to operate with high combustion efficiency, and low nitrous oxide emissions during gas turbine operations. The combustor consists of...
US20130255278 EFFUSION COOLED SHROUD SEGMENT WITH AN ABRADABLE SYSTEM  
A turbine casing assembly, comprising an annular seal segment assembly for surrounding the turbine adjacent to the turbine blades. An abradable coating is provided on the inboard surface of the...
US20130067933 GAS TURBINE  
A gas turbine is provided and includes a compressor, which via an air intake inducts and compresses air; a combustion chamber, in which a fuel is combusted using the compressed air, producing a...
US20110001324 System and Method for Gas Turbine Chilled Water Storage Discharge Control and/or Gas Turbine Output Control  
Variable speed drive controlled discharge pumps are used for pumping chilled water from a chilled water storage tank to coils operatively associated with the air inlet of a gas turbine, wherein...
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,...
US20140338364 TURBINE ROTOR BLADE FOR A TURBINE SECTION OF A GAS TURBINE  
A turbine rotor blade includes a mounting portion that partially defines a cooling circuit within the turbine rotor blade and an airfoil portion that extends radially outward from the mounting...
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...
US20110067409 Air Cooled Turbine Component Having an Internal Filtration System  
A centrifugal particle separator is provided for removing particles such as microscopic dirt or dust particles from the compressed cooling air prior to reaching and cooling the turbine blades or...
US20120304662 FUEL AIR HEAT EXCHANGER  
A gas turbine engine with a fuel air heat exchanger located in the high pressure plenum. The heat exchanger includes at least one air conduit and at least one fuel conduit in heat exchange...
US20140205447 PURGE AND COOLING AIR FOR AN EXHAUST SECTION OF A GAS TURBINE ASSEMBLY  
A turbine exhaust casing having an outer casing, an inner casing, an annular exhaust gas path defined between outer and inner flow path walls, and a turbine exhaust casing cavity located radially...
US20120000205 ADAPTIVE POWER AND THERMAL MANAGEMENT SYSTEM  
An aircraft adaptive power thermal management system for cooling one or more aircraft components includes an air cycle system, a vapor cycle system, and a fuel recirculation loop operably disposed...
US20110247347 PARTICLE SEPARATOR IN A GAS TURBINE ENGINE  
A gas turbine engine includes a supply of cooling fluid, a rotatable shaft, blade disc structure coupled to the shaft and having at least one bore for receiving cooling fluid, and a particle...
US20140116058 ASSEMBLIES AND APPARATUS RELATED TO COMBUSTOR COOLING IN TURBINE ENGINES  
A combustor of a combustion turbine engine is described. The combustor may include an inner radial wall, which defines a combustion chamber downstream of a primary fuel nozzle, and an outer radial...
US20130239588 PUMP SYSTEM FOR TMS AOC REDUCTION  
An engine includes a duct containing a flow of cool air and a pump system having an impeller with an inlet for receiving air from the duct and an outlet for discharging air into a discharge...
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...
US20150040582 CROSSOVER COOLED AIRFOIL TRAILING EDGE  
A cooling circuit for a turbine bucket having an airfoil portion includes a trailing edge cooling circuit portion provided with a first radially outwardly directed inlet passage intermediate...
US20150135715 Cooling System for Gas Turbine  
The invention provides a gas turbine cooling system that efficiently cools a first-stage turbine wheel and the attachment portions of first-stage turbine blades. A gas turbine comprises: a...
US20110047958 TURBINE GENERATOR SYSTEM  
Provided is a turbine generator system capable of sufficiently lubricating a bearing without impeding heat transmissibility of an evaporator and a condenser. The turbine generator system comprises...
US20140000287 GAS TURBINE ENGINE TURBINE VANE AIRFOIL PROFILE  
A turbine vane for a gas turbine engine includes inner and outer platforms joined by a radially extending airfoil. The airfoil includes leading and trailing edges joined by spaced apart pressure...
US20140000286 GAS TURBINE ENGINE TURBINE VANE AIRFOIL PROFILE  
A turbine vane for a gas turbine engine includes inner and outer platforms joined by a radially extending airfoil. The airfoil includes leading and trailing edges joined by spaced apart pressure...
US20140053571 SEAL FOR A PERFORATED PLATE  
A cooling circuit of a gas turbine passes an airflow through a combustor section that includes a plurality of mixing tubes for transporting a fuel/air mixture and a perforated plate including a...
US20150075180 SYSTEMS AND METHODS FOR PROVIDING ONE OR MORE COOLING HOLES IN A SLASH FACE OF A TURBINE BUCKET  
A turbine bucket is disclosed herein. The turbine bucket may include a platform and a shank portion extending radially inward from the platform. The shank portion may include a slash face, a...
US20140352324 DUAL PRESSURE REGULATOR SHUT OFF VALVE APPARATUS  
A pre-cooler system is provided and includes first and second pre-coolers, each of which is sized to handle demands of one downstream flow system, a piping system by which the first and second...
US20130283814 TURBINE COOLING SYSTEM  
A system includes a turbine. The turbine includes a rotor, a stator, and a cooling insert. The rotor includes multiple turbine blades. The stator surrounds the rotor and includes an inner wall...
US20110232299 IMPINGEMENT STRUCTURES FOR COOLING SYSTEMS  
An impingement structure 204 in an impingement cooling system, wherein the impingement structure 204 comprises a plurality of impingement apertures 214 that are configured to impinge a flow of...
US20150107267 REVERSE BULK FLOW EFFUSION COOLING  
Effusion cooling holes formed through a transition component provided in a combustion section of a gas turbine engine. The transition component directs a hot working gas from a combustion basket...
US20150000291 GAS TURBINE ENGINE COMBUSTOR HEAT EXCHANGER  
A gas turbine engine having a combustor is disclosed in which a heat exchanger is disposed within the combustor. The heat exchanger can take the form of a fuel/air heat exchanger. In one form the...
US20110283713 System For Cooling A Heat Exchanger On Board An Aircraft  
A system (10) for cooling a heat exchanger (12) on board an aircraft comprises a process air line (28), a first end of which is connected to an engine (16) of the aircraft in order to supply...
US20150096306 GAS TURBINE AIRFOIL WITH COOLING ENHANCEMENT  
A turbine nozzle vane segment includes one or more nozzle vanes extending between radially inner and outer side walls, each nozzle vane having a peripheral edge wall extending between a leading...
US20120247114 Water Cooling System For Intercooled Turbines  
An intercooled gas turbine is provided having an air cooled heat exchanger and a chiller disposed to remove heat from the cooling medium of the intercooler heat exchanger. During peak hours when...
US20120285172 PREMIXED BURNER FOR A GAS TURBINE COMBUSTOR  
The disclosure relates to a burner for a single combustion chamber or first combustion chamber of a gas turbine, with an injection device for the introduction of at least one gaseous and/or liquid...
US20150033761 HEAT TRANSFER ASSEMBLY AND METHODS OF ASSEMBLING THE SAME  
A heat transfer assembly for controlling heat transfer of a turbine engine is provided. The turbine engine includes a housing and includes a compressor, a combustor and a turbine located within...
US20140060084 GAS TURBINE ENGINE AIRFOIL COOLING CIRCUIT ARRANGEMENT  
A component for a gas turbine engine according to an exemplary aspect of the present disclosure including, among other things, an airfoil that extends between a leading edge and a trailing edge...
US20150121898 TURBINE AND POWER GENERATION SYSTEM  
A turbine and so on capable of enabling high reliability are provided. In the turbine of an embodiment, a turbine rotor is accommodated in a turbine casing, and is rotated by a working medium...
US20120251309 CMC TURBINE NOZZLE ADAPTED TO SUPPORT A METALLIC TURBINE INTERNAL CASING BY AN AXIAL CONTACT  
Composite material turbine nozzle blade including an airfoil (10) adapted to have a cooling fluid flow through it and extending between a shroud (11) and a root (12), said shroud being shaped to...
US20120017605 HEAT TRANSFER AUGMENTED FLUID FLOW SURFACES  
A heat transfer augmented channel wall includes a bulk portion, a wall surface and a plurality of multi-portion indented features extending from the wall surface into the bulk portion. The...
US20140116064 VENTILATION OF AN ACCESSORY GEAR BOX, AND TURBOJET ENGINE COMPRISING SUCH A GEAR BOX  
An accessory gear box configured to be mounted on a fan casing of a turbojet engine, including: an input shaft; a plurality of accessory drive shafts; and a compartment forming an interface with...

Matches 1 - 50 out of 432 1 2 3 4 5 6 7 8 9 >