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US20140090400 |
VARIABLE FLOW DIVIDER MECHANISM FOR A MULTI-STAGE COMBUSTOR
The present invention discloses a novel apparatus and way for altering the airflow to a gas turbine combustion system. The apparatus comprises a flow divider mechanism which splits the airflow... |
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US20130160464 |
ANTI-VIBRATION MOUNT
An anti-vibration mount is provided for mounting a first component to a second component. The mount has an elastomeric body which provides a recess into which the first component is received. The... |
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US20100263386 |
TURBINE ENGINE HAVING A LINER
In one embodiment, a combustor of a turbine system may include a liner disposed inside the combustor. The lining element may include a heat shield having a mounting stud extending along an axis... |
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US20160313005 |
ADDITIVE MANUFACTURED COMBUSTOR HEAT SHIELD WITH COOLED ATTACHMENT STUD
A heat shield for use in a combustor of a gas turbine engine including an attachment stud that extends from a cold side, the attachment stud at least partially hollow. A method of manufacturing a... |
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US20130192256 |
GEARED TURBOFAN ENGINE WITH COUNTER-ROTATING SHAFTS
A mid-turbine frame is incorporated into a turbine section of a gas turbine engine intermediate a high pressure turbine and a low pressure turbine. The high pressure and low pressure turbines... |
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US20150096304 |
AIR ACCELERATOR ON TIE ROD WITHIN TURBINE DISK BORE
A gas turbine engine high pressure rotor with first and second high pressure turbine stages include first and second stage disks having first and second stage disk bores and a single tie rod... |
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US20120186269 |
SUPPORT BETWEEN TRANSITION PIECE AND IMPINGEMENT SLEEVE IN COMBUSTOR
A support between a transition piece and an impingement sleeve in a combustor is disclosed. The support includes a resilient portion, the resilient portion configured to provide dampening between... |
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US20150101344 |
Systems and Methods for Bypassing a Coalescer in a Gas Turbine Inlet
A system including an air intake subsystem having a housing is provided. A coalescer having a frame is disposed inside the housing. The system includes a mounting bracket, and a release mechanism... |
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US20120180500 |
SYSTEM FOR DAMPING VIBRATION IN A GAS TURBINE ENGINE
A system, including, a turbine combustor, including, a first wall disposed about a flow path of hot combustion gases, a second wall disposed about the first wall, and a damping system disposed... |
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US20130305739 |
FUEL NOZZLE CAP
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... |
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US20140318149 |
SEAL FOR A TURBOJET ENGINE PYLON AND NACELLE, AND TURBOJET ENGINE PYLON-NACELLE ASSEMBLY INCORPORATING SUCH A SEAL
A fire-resistant seal for a propulsion assembly which includes a pylon, an O-duct type nacelle of a turbojet engine. The nacelle includes an inner fixed nacelle structure and a combustion gas... |
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US20130042630 |
GAS TURBINE ENGINE ACCESSORY MOUNT
A gas turbine engine accessory mount comprises a bracket fixedly attached to the engine's case, a link adapted for connection to the accessory and bracket and a fastener such as a pin disposed... |
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US20110016882 |
Electrical Cable Shroud
An electrical cable shroud forming an annular structure having an outer surface and an inner surface, the cable shroud comprising a substantially J-shaped cross-section having a longest side, a... |
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US20120047909 |
COMBUSTOR LINER CONCENTRIC SUPPORT AND METHOD
Systems and methods provide for reducing motion which causes wear in a combustor. The method includes attaching a first end of a combustor liner to a retainer which encircles the first end of the... |
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US20100180573 |
A GAS TURBINE ENGINE
A gas turbine engine is proposed 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... |
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US20070199331 |
Power transmission arrangement
A power transmission arrangement comprises a first power transmission member connectable to a first main shaft of an engine. The arrangement also includes a second power transmission member... |
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US20140096537 |
Thin Metal Duct Damper
A damper for damping vibration of a structural member of a gas turbine engine is disclosed. The damper may include a first metal mesh pad which abuts an outer circumferential surface of the... |
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US20160333786 |
SYSTEM FOR SUPPORTING ROTOR SHAFTS OF AN INDIRECT DRIVE TURBOFAN ENGINE
In one aspect the present subject matter is directed to a system for supporting shafts of an indirect-drive turbofan engine. The system includes a fan frame assembly that is coaxially aligned with... |
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US20150345793 |
FUEL NOZZLE ASSEMBLY WITH REMOVABLE COMPONENTS
A fuel nozzle assembly (10) for a gas turbine engine (12) is provided. The fuel nozzle assembly (10) includes a rocket unit (14) and a flow-guiding element, such as may include swirler elements,... |
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US20090120093 |
Turbulated aft-end liner assembly and cooling method
In a combustor for a turbine a cover sleeve is disposed between the aft end portion of the combustor liner and a resilient seal structure to define an air flow passage therebetween. The cover... |
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US20130081404 |
DEVICE FOR THE MUTUAL FIXATION OF TWO COMPONENTS
A device is provided for the mutual fixing of two components, which are interconnected via a flanged joint, for preventing a relative movement of the components in relation to each other in the... |
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US20160153306 |
RADIAL POSITION CONTROL OF CASE SUPPORT STRUCTURE WITH SPLINED CONNECTION
A radial position control assembly for a gas turbine engine includes a case structure. A support structure is operatively supported by the case structure respectively with first and second splines... |
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US20110192171 |
TRANSITION SUPPORT SYSTEM FOR COMBUSTION TRANSITION DUCTS FOR TURBINE ENGINES
A transition duct support system for a transition duct that channels hot gases from a combustor exit to a gas turbine inlet of a turbine engine. The transition duct support system includes a... |
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US20100132371 |
MID TURBINE FRAME SYSTEM FOR GAS TURBINE ENGINE
A gas turbine engine has a mid turbine frame system which includes an outer case surrounding a spoke casing. Spokes of the spoke casing are detachably connected to the outer case and radially... |
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US20090120101 |
Organic Matrix Composite Components, Systems Using Such Components, and Methods for Manufacturing Such Components
Organic matrix composite components, systems using such components, and methods for manufacturing such components are provided. In this regard, a representative organic matrix composite component... |
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US20130192257 |
TURBINE SHROUD HANGER WITH DEBRIS FILTER
A turbine shroud hanger apparatus for a gas turbine engine includes: an arcuate shroud hanger having at least one cooling hole passing therethrough, the cooling hole having an inlet and an outlet;... |
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US20090049842 |
ENCLOSURE FOR A GAS TURBINE AND METHOD FOR ENCLOSING THE SAME
Disclosed is an enclosure for a gas turbine, the enclosure including an enclosure section configured to partially enclose the gas turbine, and at least one other enclosure section, the at least... |
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US20160305270 |
GAS TURBINE OFFSHORE INSTALLATIONS
The off-shore gas turbine system comprises a floating structure with at least one deck and a baseplate mounted on the deck. The baseplate supports a gas turbine having: a low pressure compressor,... |
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US20150226125 |
COMBINED HIGH PRESSURE TURBINE CASE AND TURBINE INTERMEDIATE CASE
A disclosed gas turbine engine includes a compressor section, a combustor section, a first turbine section and a second turbine section. An outer case structure for the gas turbine engine includes... |
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US20110219781 |
GAS TURBINE ENGINE WITH TIE SHAFT FOR AXIAL HIGH PRESSURE COMPRESSOR ROTOR
A compressor section to be mounted in a gas turbine engine has a plurality of axial compressor rotors arranged from an upstream location toward a downstream location. A tie shaft applies an axial... |
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US20110000223 |
GAS TURBINE COMPONENT AND A METHOD FOR PRODUCING A GAS TURBINE COMPONENT
A gas turbine component includes an inner ring, an outer ring, and a plurality of circumferentially spaced struts which are rigidly connected to the inner ring and the outer ring forming a... |
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US20100000227 |
AIR INTAKE FOR AN AIRCRAFT TURBINE ENGINE
According to the invention, the air intake (2) is made of a piece (23) of fibre/resin composite material, reinforced on the side of the flange (24) by a reinforcing ring (26). |
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US20140260318 |
SIDE SEAL SLOT FOR A COMBUSTION LINER
A side seal slot extends along a one side of an aft frame for a combustion liner of a gas turbine. The side seal slot is at least partially defined between a downstream wall and an upstream wall... |
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US20160069570 |
METHOD AND APPARATUS FOR CONDITIONING DIFFUSER OUTLET FLOW
A diffuser for a gas-turbine engine is provided. The diffuser has an outer housing, an inner housing, and a diffusion plate. The outer housing has a first wall. The inner housing has a second wall... |
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US20140216055 |
GAS TURBINE
In this gas turbine, at a downstream portion of a transition piece of a combustor, inner surfaces of a pair of lateral walls facing each other in a circumferential direction of a turbine rotor... |
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US20140137567 |
MICRO GAS TURBINE HAVING IGNITOR-COUPLING STRUCTURER AND METHOD OF ASSEMBLING THE SAME
Disclosed are a micro gas turbine and a method of assembling the same. The micro gas turbine includes an ignitor assembly having an ignitor, along with an ignitor-coupling structure. The... |
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US20130167552 |
EXHAUST STRUT AND TURBOMACHINE INCORPRATING SAME
An exhaust strut is provided and includes a body having an airfoil-shaped cross-section defining a lead edge portion and a trailing edge portion opposite the lead edge portion, the lead edge... |
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US20140311161 |
METHOD FOR CREATING A CONNECTING ELEMENT POSITIONED BETWEEN TWO COMPONENTS OF A STRUCTURE, CONNECTING ELEMENT AND BYPASS TURBOJET ENGINE COMPRISING SUCH A CONNECTING ELEMENT
A method for creating a connecting element, arranged between two components of a structure, or a turbojet engine structure, which is subjected to compressive and/or tensile loadings and which... |
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US20120272660 |
METHOD AND ASSEMBLY FOR RETROFITTING A GAS TURBINE COMBUSTOR END COVER
A method for retrofitting an end cover of a turbine engine combustor. The method includes inserting a first insert into a opening formed in the end cover so a circular land on the insert centers... |
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US20130327011 |
Method And Apparatus For A Fuel Nozzle Assembly For Use With A Combustor
A fuel nozzle assembly for use with a combustor is provided. The fuel nozzle assembly includes a fuel nozzle including a discharge end. A cap is coupled adjacent to the nozzle discharge end,... |
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US20140325992 |
ELECTRICAL UNIT WITH ELECTRICAL CONNECTOR
An electrical unit comprises an electrical connector having a set of elongate electrical terminals which are each a one-piece component. The terminals extend into the unit such that first ends of... |
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US20110016881 |
GAS TURBINE WITH EXHAUST GAS CASING AND METHOD FOR PRODUCING A GAS TURBINE
A gas turbine (10) has an annular exhaust gas casing (16) which is arranged at the outlet of the turbine at a distance from the supporting foundation (22) and includes an outer shell (20a).... |
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US20150114004 |
GAS TURBINE ENCLOSURE
A gas turbine enclosure apparatus is provided and includes a frame defining an interior, gas turbine equipment disposed in the interior, the gas turbine equipment being pre-assembled at a first... |
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US20130255276 |
Transition Duct Mounting System
The present invention is directed to a mounting system for a gas turbine transition duct. The mounting system includes a generally C-shaped mounting bracket having a generally radially extending... |
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US20090064684 |
Systems Involving Inlet-Mounted Engine Controls
Systems involving inlet-mounted engine control components are provided. A representative system includes: a forward keep out zone defined by converging inner and outer walls of a nacelle; an aft... |
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US20110126510 |
PULSE DETONATION COMBUSTOR
In one embodiment, a pulse detonation combustor includes a gas discharge annulus including multiple nozzles engaged with one another via mating surfaces to support the gas discharge annulus in a... |
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US20100242494 |
CASING ARRANGEMENT
Asymmetric distortion between an inner casing and outer casing such as with regard to a gas turbine engine between an inner high pressure compressor casing and an outer combustion casing can... |
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US20160053636 |
Injection Molded Composite Fan Platform
A fan platform for a gas turbine engine may include an outer flow path surface extending between a first side and a second side. An inner surface extends between the first side and the second... |
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US20140260321 |
GAS TURBINE ENGINE STATIC STRUCTURE JOINT WITH UNDERCUTS
A gas turbine engine static structure has a joint that includes at least two flanges. The first flange includes a face extending axially proud between radially spaced apart undercuts. The second... |
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US20120297792 |
THERMOCOUPLE WELL FOR A TURBOMACHINE
A turbomachine includes a nozzle. The nozzle includes an end portion and an airfoil portion. A diaphragm is mounted to the end portion of the nozzle in a wheel space portion of the turbomachine.... |