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US20130111924 |
FLEXIBLE PRINTED CIRCUIT BOARD HARNESS
A gas turbine engine installation is provided that has a plurality of flexible printed circuit board (FPCB) harnesses to transfer electrical signals, including electrical power, around a gas... |
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US20140013769 |
MID-TURBINE FRAME WITH OIL SYSTEM MOUNTS
A gas turbine engine includes a combustor, a first turbine section in fluid communication with the combustor, a second turbine section in fluid communication with the first turbine section, and a... |
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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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US20110185746 |
GAS TURBINE COMBUSTION DEVICE
The combustion device (1) of a gas turbine includes burners (2) connected to a front plate (5) of a combustion chamber (3). The front plate (5) has, spaced apart from one another, a front sheet... |
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US20130031913 |
MOVABLE STRUT COVER FOR EXHAUST DIFFUSER
A strut cover for use in a gas turbine engine having structure defining an annular flow path for receiving exhaust gas from a turbine section of the engine. The strut cover is located downstream... |
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US20140047848 |
ADJUSTABLE CABLE FOR EXHAUST DUCT LINER HANGER
A hanger for suspending a liner within an exhaust duct of a gas turbine engine exhaust system comprises a connector assembly, a cable and a bracket. The connector assembly is for connecting to an... |
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US20120023968 |
EXHAUST MANIFOLD FLANGE CONNECTION
A flange connection for an exhaust section of a gas turbine engine. The flange connection includes a stub flange attached to an exhaust manifold. The stub flange has a first axial face for... |
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US20140305134 |
RIGID RAFT FOR A GAS TURBINE ENGINE
A rigid raft is provided for a gas turbine engine. The raft has an electrical system and/or a fluid system embedded in the material of the raft. The raft further has one or more first mounts for... |
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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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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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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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US20140245750 |
CIRCUMFERENTIALLY RETAINED FAIRING
An assembly for a gas turbine engine includes a frame, a mount, and a fairing. The mount is attached to the frame and the fairing is connected to the mount. The fairing and mount have mating... |
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US20150252691 |
Gas Turbine Duct Casing
A gas turbine duct casing, in particular for an aircraft engine, is disclosed. The duct casing has a first wall segment and a second wall segment which is connected to the first wall segment by a... |
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US20140260308 |
REAR MOUNTED WASH MANIFOLD RETENTION SYSTEM
A retention system includes a structure clamp to connect the retention system to another structure; and a manifold clamp connected to the structure clamp, the manifold clamp including a trough to... |
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US20150176430 |
COOLED FLANGE CONNECTION OF A GAS-TURBINE ENGINE
A cooled flange connection of a gas-turbine engine is annular and includes a first flange of a first component, at least a second and central flange of a second component, and a third flange of a... |
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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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US20130160463 |
RAFT ASSEMBLY
A raft assembly for a gas turbine engine is provided. The raft assembly includes a rigid raft formed of a rigid material that has an electrical system and/or a fluid system embedded therein. The... |
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US20140123677 |
GAS TURBINE ENGINE AIRFOIL PROFILE
An airfoil for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil body including a leading edge and a trailing edge joined by... |
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US20150219015 |
SEAL ASSEMBLY FOR A STATIC STRUCTURE OF A GAS TURBINE ENGINE
A static structure of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an outer platform, an inner platform, an airfoil that extends... |
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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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US20110308257 |
ATTACHMENT STRUCTURE FOR A TURBOJET ENGINE
The present invention relates to an attachment structure (1) for attaching a turbojet engine (2) to a fixed structure of an airplane via an attachment pylon, characterized in that it comprises a... |
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US20130042628 |
GAS TURBINE ENGINE INTERNAL COMPARTMENT STRUCTURE HAVING EGRESS FEATURE
A gas turbine engine includes a gas turbine engine internal compartment structure having an integral passageway. Wiring is routed through the integral passageway of the gas turbine engine internal... |
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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... |
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US20150114003 |
TRANSITION DUCT ASSEMBLY WITH MODIFIED TRAILING EDGE IN TURBINE SYSTEM
Transition duct assemblies for turbine systems and turbomachines are provided. In one embodiment, a transition duct assembly includes a plurality of transition ducts disposed in a generally... |
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US20130008177 |
SUPPORT ASSEMBLY FOR TRANSITION DUCT IN TURBINE SYSTEM
A support assembly for a turbine system is disclosed. The support assembly includes a transition duct extending between a fuel nozzle and a turbine section. The transition duct has an inlet, an... |
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US20140137568 |
DEVICE FOR MOUNTING A SPARK PLUG IN A COMBUSTION ENGINE OF A GAS TURBINE ENGINE
A device for mounting a spark plug in a combustion chamber of a gas turbine engine includes a chimney including a collar extending radially inwards, a washer fastened on an axial end of the... |
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US20110088409 |
FUEL INJECTOR MOUNTING SYSTEM
A combustor is provided for mounting a fuel injector to a gas turbine engine. The combustor comprises an engine casing having an aperture formed therein. The system further comprises a fuel... |
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US20110030386 |
MID-TURBINE FRAME
A mid-turbine frame connected to at least one mount of a gas turbine engine transfers a first load from a first bearing and a second load from a second bearing to the mount. The mid-turbine frame... |
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US20130160460 |
RIGID RAFT
The present invention provides a rigid raft formed of rigid composite material. The raft has an electrical system and/or a fluid system embedded therein. The raft further has a tank for containing... |
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US20140060077 |
COMBUSTOR
A combustor includes a breech end, a fuel nozzle connected to the breech end and extending downstream from the breech end, and a shroud that circumferentially surrounds the fuel nozzle inside the... |
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US20150241067 |
FASTENED JOINT FOR A TANGENTIAL ON BOARD INJECTOR
A combustor assembly for a gas turbine engine includes a combustor shell, a TOBI, a case, and a joint for securing the combustor shell, TOBI and case together. The joint has a combustor flange... |
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US20120042660 |
MANIFOLD MOUNTING ARRANGEMENT
A manifold mounting arrangement comprising: a discrete manifold module; a clevis arrangement having a clevis straddling a flange and pivotally secured to the flange by a clevis pin; and a locking... |
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US20150068214 |
LOW THERMAL MASS JOINT
A gas turbine engine includes a tangential on-board injector (TOBI) fluidly connected to a compressor section. A diffuser case structurally supports a combustor section and the tangential on-board... |
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US20150252728 |
GAS TURBINE ENGINE HAVING SUPPORT STRUCTURE WITH SWEPT LEADING EDGE
A gas turbine engine nacelle assembly according to an exemplary aspect of the present disclosure includes, among other things, a core casing defined about an axis; a fan nacelle mounted at least... |
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US20140223920 |
CONSUMABLE ASSEMBLY MISTAKE PROOFING TOOL FOR A GAS TURBINE ENGINE
A method of assembling a gas turbine engine includes locating a consumable assembly tool clip within the engine |
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US20130042629 |
TURBOMACHINE LOAD MANAGEMENT ASSEMBLY
An example turbomachine load management assembly includes a support rod extending from a first rod end to a second rod end that is moveable radially relative to a fan duct, a bearing housing, or... |
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US20110056213 |
SPOOL SUPPORT STRUCTURE FOR A MULTI-SPOOL GAS TURBINE ENGINE
A gas turbine engine is provided that includes a low pressure spool, a high pressure spool, a stationary support frame, and at least one support arch. The low pressure spool extends between a low... |
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US20150128609 |
TRANSITION SUPPORT SYSTEM FOR COMBUSTION TRANSITION DUCTS FOR TURBINE ENGINES
An adjustable 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 adjustable transition duct support... |
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US20130008178 |
SUPPORT ASSEMBLY FOR TRANSITION DUCT IN TURBINE SYSTEM
A support assembly for a turbine system is disclosed. The support assembly includes a transition duct extending between a fuel nozzle and a turbine section. The transition duct has an inlet, an... |
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US20110088407 |
FUEL INJECTOR MOUNTING SYSTEM
A system is provided for mounting fuel injectors to a gas turbine engine. The system comprises an engine casing having a plurality of apertures formed therein. The system further comprises a... |
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US20150013344 |
TUBE
The present disclosure relates generally to the field of tubes for carrying fluids. More specifically, the present disclosure relates to a tube having an oval shaped cross-section. In some... |
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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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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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US20120291450 |
AUXILIARY POWER UNIT MOUNTING FEATURE
An auxiliary power unit assembly includes an auxiliary power unit with an auxiliary power unit exhaust duct, a bell mouth, and one or more bell mouth struts. The auxiliary power unit exhaust duct... |
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US20120304665 |
MOUNT DEVICE FOR TRANSITION DUCT IN TURBINE SYSTEM
A mount device and mounting assembly for a turbine system are disclosed. The mounting assembly includes a transition duct extending between a fuel nozzle and a turbine section. The transition duct... |
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US20140060078 |
COMBUSTOR
A combustor includes a breech end, a plurality of fuel nozzles connected to the breech end and extending downstream from the breech end, and a shroud that circumferentially surrounds the plurality... |
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US20120180501 |
BLEED VALVE MODULE
A bleed valve module for mounting to a support structure within an aircraft includes a pipe, a plurality of bleed valves connected to the pipe, a plurality of pneumatic actuators connected to the... |
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US20140053564 |
LINER BRACKET FOR GAS TURBINE ENGINE
A hanger for a gas turbine exhaust system includes an exhaust duct attachment structure associated with an exhaust duct and a liner attachment structure associated with a liner spaced radially... |
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US20150198094 |
CERAMIC PEDESTAL AND SHIELD FOR GAS PATH TEMPERATURE MEASUREMENT
A mounting stand for a temperature sensor is disclosed. The mounting stand includes a base, a pedestal, and a shield. The pedestal extends from the base to a pedestal end distal to the base. The... |
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US20120047910 |
STEPPED INLET RING FOR A TRANSITION DOWNSTREAM FROM A COMBUSTOR BASKET IN A COMBUSTION TURBINE ENGINE
A hot gas path system for a gas turbine including a stepped inlet ring at an intersection between a downstream end of a combustor basket and an upstream end of a transition is disclosed. The heat... |