Matches 1 - 50 out of 361 1 2 3 4 5 6 7 8 >


Match Document Document Title
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...

Matches 1 - 50 out of 361 1 2 3 4 5 6 7 8 >