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Power Plants > Combustion Products Used As Motive Fluid > Having Mounting Or Supporting Structure

Having Mounting Or Supporting Structure

Having Mounting Or Supporting Structure patent applications listed include Date, Patent Application Number, Patent Title, Patent Abstract summary and are linked to the corresponding patent application page.

10/30/14 - 20140318148 - Burner seal for gas-turbine combustion chamber head and heat shield
The present invention relates to a combustion chamber for a gas turbine with a combustion chamber head and a heat shield which are designed in one piece, with the heat shield being provided with at least one recess, in which is arranged a burner or an annular sleeve enclosing the...

10/30/14 - 20140318149 - 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 ejection primary nozzle, and the fire-resistant seal is placed in an annular sector defined by the inner fixed nacelle...

10/23/14 - 20140311160 - Hybrid turbomachine enclosure
A hybrid turbomachine enclosure includes a plurality of walls interconnected to form an interior configured and disposed to receive a turbomachine, the plurality of walls including a first wall having a panel on frame construction and a hybrid wall including a first portion having a panel on frame structure and...

10/23/14 - 20140311161 - 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 includes a hollow shaft immersed, at least partially, in a stream of air flowing between the two components, the method including:...

10/16/14 - 20140305134 - 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 mounting the raft to the gas turbine engine, and one or more second...

10/02/14 - 20140290268 - Gas turbine engine geared architecture axial retention arrangement
A gas turbine engine includes a fan, an engine static structure, a geared architecture to drive the fan and supported relative to the static structure, a fan drive turbine to drive the geared architecture, a first member secured to the geared architecture, and a second member secured to the engine...

09/25/14 - 20140283528 - Aftertreatment module and method of assembly
To assemble an aftertreatment module for use in the treatment of exhaust gasses and the like, an aftertreatment brick is inserted into a sleeve opening in a sleeve and advanced toward an opposite end of the sleeve. To retain the aftertreatment brick in the sleeve, the end of the sleeve...

09/18/14 - 20140260315 - System having multi-tube fuel nozzle with floating arrangement of mixing tubes
A system includes a multi-tube fuel nozzle. The multi-tube fuel nozzle includes an end cover, a first plate, and multiple tubes. The multiple tubes are disposed and supported in a floating arrangement between the end cover and the first plate. Each tube includes a forward end adjacent the end cover...

09/18/14 - 20140260316 - Gas turbine transition inlet ring adapter
A combustion system for a gas turbine engine including a combustor assembly comprising a combustor basket having a downstream terminal end, and a transition duct extending downstream from the combustor basket and having an upstream end located adjacent to the downstream terminal end of the combustor basket. A coupling is...

09/18/14 - 20140260317 - Gas turbine combustor exit piece with hinged connections
An exit piece (66) with an inlet throat (67) that conducts a combustion gas flow (36A) in a path (82) from a combustor (63) to an annular chamber (68) that feeds the first blade section (37) of a gas turbine (26). The exit piece further includes an outlet portion (69)...

09/18/14 - 20140260318 - 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 that extend outward from the first side of the aft frame. A...

09/18/14 - 20140260319 - Combustor support assembly for mounting a combustion module of a gas turbine
A gas turbine comprises a compressor discharge casing that is coupled to an outer turbine shell. The compressor discharge casing includes a combustor opening that extends through the compressor discharge casing and an outer mating surface that circumferentially surrounds the combustor opening. The outer turbine shell defines an inner mating...

09/18/14 - 20140260320 - Bi-metal fastener for thermal growth compensation
An improved fastening system and method overcomes traditional thermal mismatch that occurs with standard fastener systems that are employed in extreme temperature environments. The fastening system could employ a metallic fastener that is combined with metallic spacer, each of which having a differing thermal growth coefficient. This arrangement may reduce...

09/18/14 - 20140260321 - 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 flange abuts the face. Fasteners secure the flanges to one another through the face....

09/11/14 - 20140250915 - Centerline support bar for steam turbine component
A centerline support bar for steam turbine component assembly, installation, and/or alignment is disclosed. In one embodiment, the support bar includes a body portion configured to be disposed across a centerline of a steam turbine, the body portion configured to transversely connect to a steam turbine component; and a first...

09/04/14 - 20140245750 - 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 anti-deflection features that engage to prevent circumferential movement of the fairing relative to the...

09/04/14 - 20140245751 - Passages to facilitate a secondary flow between components
An annular mount for a gas turbine engine includes a first flange and a second flange. The first flange has an arcuate shape, and the second flange extends from the first flange. The second flange has an interface surface along at least one side and has a plurality of mounting...

08/14/14 - 20140223919 - Flexible liner hanger
A gas turbine engine exhaust system includes a liner extending along an axial direction and a radial direction and circumscribing a combustion plenum, a high pressure plenum circumscribing the liner along the radial direction, a structural component circumscribing the high pressure plenum along the radial direction, and a leaf spring...

08/14/14 - 20140223920 - 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...

08/07/14 - 20140216054 - Variable volume combustor with aerodynamic support struts
The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles and a fuel injection system for providing a flow of fuel to the micro-mixer fuel nozzles. The fuel injection system may include a number of support struts...

08/07/14 - 20140216055 - 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 form inclination surfaces that incline down to a downstream end of the transition piece in a...

07/24/14 - 20140202168 - Continuous ring composite turbine shroud
A composite annular shroud supported by a support assembly including at least one ring and at least partially disposed within the ring. The shroud is biased against and in sealing engagement with an inner flange of the ring. A three ring assembly includes the inner ring disposed radially inwardly of...

07/17/14 - 20140196471 - Fan drive gear system flexible support features
A disclosed gear assembly support for a gas turbine engine includes a first portion configured for attachment to a case of the gas turbine engine and a second portion configured for supporting a gear assembly. The support further includes a snap portion defining a fit within the case. The snap...

07/03/14 - 20140182308 - Gas turbine engine with v-band clamp connection for collector box
A gas turbine engine includes a turbine section, a compressor section, a bleed air collector box, and a v-band clamp. The compressor section is positioned upstream of the turbine section and includes a compressor case circumferentially surrounding the compressor section. The v-band clamp attaches the bleed air collector box to...

06/05/14 - 20140150450 - Exhaust component mounting structure
An exhaust after-treatment system including a first exhaust treatment device having a first mounting surface and a second mounting surface, and a second exhaust treatment device and a third mounting surface and a fourth mounting surface. A first mounting structure is attached to the first mounting surface of the first...

06/05/14 - 20140150451 - Band structure and micro gas turbine having the same
Disclosed are a band structure and a micro gas turbine having the same. An insert wall and a nozzle ring casing are respectively surrounded in part by a first band structure of a heat resistant material and a second band structure of a material that is identical or similar to...

06/05/14 - 20140150452 - Transition piece for a gas turbine system
A system includes a gas turbine transition piece. The gas turbine transition piece includes a duct body having a forward end portion and an aft end portion. The duct body defines an enclosure for routing a flow of combustion products from a combustor to a turbine first stage nozzle, and...

06/05/14 - 20140150453 - Gas turbine combustion chamber
A gas turbine combustion chamber is provided, including a flow sleeve structure with an improved anti-vibration performance. A gas turbine combustion chamber of the present invention includes a liner, a transition piece, and a flow sleeve including a plurality of segments and integrated by welding a tie piece along joint...

05/22/14 - 20140137567 - 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 ignitor-coupling structure includes a mounting bracket having first and second ends, the first end being coupled to the ignitor and...

05/22/14 - 20140137568 - 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 chimney so as to project towards the inside of the chimney, and a bushing forming a...

05/15/14 - 20140130511 - Combustor connection structure, combustor transition piece, desigining method of combustor transition piece and gas turbine
A cross-sectional area (Dout) of a transition piece outlet is set within a range of 0.79£DoutDin£0.9, relative to a cross-sectional area (Din) of a transition piece inlet of a combustor, and in a first stage turbine nozzle of a turbine connected to the transition piece outlet, a size (Hin) in...

05/08/14 - 20140123677 - 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 a pressure side and a suction side spaced apart from the pressure side to provide an external...

04/24/14 - 20140109592 - Leaf spring hanger for exhaust duct liner
A hanger assembly for use between a first duct and a second duct has a flexible leaf spring having a body and a leg, a locking member for attaching the leg to the first duct, and a mounting member for attaching the body to the second duct....

04/24/14 - 20140109593 - Coil spring hanger for exhaust duct liner
A hanger assembly for use between a first duct and a second duct having an opening therein includes a spring having a first end and a second end, a first mount for attaching the first end to the first duct, a second mount for attaching the second end to the...

04/24/14 - 20140109594 - Deformable mounting assembly
A deformable fastener assembly for use with a gas turbine engine. The deformable fastener may be used to fasten a component of the gas turbine that is subjected to high temperatures and thermal deformation, such as an impingement sleeve assembly, to a rigid portion, such as the inner turbine shell...

04/24/14 - 20140109595 - Annular combustion chamber of a turbomachine
An annular combustion chamber for a turbomachine presenting an axial direction, a radial direction, and an azimuth direction, the combustion chamber including a first annular wall and a second annular wall, each annular wall defining at least a portion of an enclosure of the combustion chamber. The first annular wall...

04/24/14 - 20140109596 - Arrangement for connecting a duct to an air-distribution casing
An arrangement for connecting at least one duct with an air-distribution casing, the at least one duct including two sidewalls opposite one another and including a peripheral wall connecting edges of the two sidewalls. The arrangement includes a connecting tube that extends through the casing, passes through an orifice associated...

04/10/14 - 20140096537 - 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 structural member, and a garter spring which abuts the first metal mesh pad. Both the metal mesh...

04/03/14 - 20140090398 - Flexible connection between a wall and a case of a turbine engine
A wall assembly includes a wall that extends axially along a centerline, and circumferentially at least partially around the centerline. The wall assembly also includes a plurality of mounting brackets arranged circumferentially around the centerline, and a plurality of wall brackets. Each of the mounting brackets includes a groove that...

04/03/14 - 20140090399 - Panel support hanger for a turbine engine
A support hanger is provided for a turbine engine. The support hanger includes a pin with a pin head, a retainer and a flexible seal. The retainer is pivotally connected to the pin head. The retainer includes a seal bearing surface facing towards the pin head. The seal includes a...

04/03/14 - 20140090400 - 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 surrounding a combustion liner into two distinct portions, one directed towards a pilot and one directed towards a main stage...

03/13/14 - 20140069106 - Sliding u-joint hanger for gas turbine engine nozzle
A disclosed hanger assembly for supporting a liner within a gas turbine engine exhaust nozzle includes a first mount for attachment to a case and a second mount for attachment to the liner. A u-joint assembly is attached between the first and second mounts and includes a first yoke and...

03/06/14 - 20140060077 - 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 combustor. A support extends radially inside at least a portion of the shroud, and a flexible coupling is...

03/06/14 - 20140060078 - 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 of fuel nozzles inside the combustor. A support extends radially inside at least a portion of the shroud. A...

02/27/14 - 20140053573 - Hot gas expander inlet casing assembly and method
A gas turbine device includes an inlet casing and a stator diaphragm provided inside the inlet casing. The stator diaphragm has an integral inner stator shroud and an outer stator shroud and a plurality of stator vanes provided in a circumferential arrangement between the inner stator shroud and the outer...

02/20/14 - 20140047848 - 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 exhaust duct of the gas turbine exhaust system. The cable extends from the connector assembly and...

02/20/14 - 20140047849 - Spherical button washer for exhaust duct liner hanger
A hanger for suspending a liner within an exhaust duct of a gas turbine engine comprises a bracket, a washer, a rod and a cap. The bracket is for connection to an exhaust duct liner of a gas turbine exhaust system. The washer is connected to the bracket at a...

02/06/14 - 20140033734 - Stator anti-rotation lug
A compressor assembly of a gas turbine engine includes a case including at least one opening and a stator assembly supported within the case. A lug assembly is secured to the case and sets a position of the stator assembly relative to the case. The lug assembly includes a lug...

01/30/14 - 20140026590 - Flexible combustor bracket
A bracket for an augmentor assembly of a gas turbine engine includes a first mount attachable to a support structure. A second mount is attachable to an augmentor pilot assembly and extends radially inward of the support structure. First and second spring members attach on a first end to the...

01/30/14 - 20140026591 - Axial retention for fasteners in fan joint
In a gas turbine engine, a fan rotor and a compressor rotor are connected to a joint which is attached to a shaft. The fan rotor is connected to the joint by a plurality of fasteners extending through mounting openings in the joint and through apertures in the fan rotor....

01/30/14 - 20140026592 - Assembly for a jet engine of an aircraft
The present invention proposes a structural unit for an aircraft engine having at least one fuel pump of a fuel circuit and at least one hydraulic fluid pump of a hydraulic fluid circuit, where the structural unit can be coupled to an accessory gearbox shaft of an accessory gearbox of...