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7614236 |
Positioning bridge guide and its utilisation for the nozzle support pipe of a turboprop
A bridge positioned between two parts, such as a nozzle support pipe envelope and a heat shield liner, includes a central part with inversed curvature thus having two contact zones with the nozzle...
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7610763 |
Tailorable design configuration topologies for aircraft engine mid-turbine frames
A mid-turbine frame has a pre-stress design and is connected to an engine casing of a jet turbine engine to distribute a first load from a first bearing and a second load from a second bearing. The...
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7594405 |
Catenary mid-turbine frame design
An engine casing assembly having dual load transfer points includes a U-shaped mid-turbine frame, an engine casing, a plurality of dimples, a strut and a mounting apparatus. The engine casing has...
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7594404 |
Embedded mount for mid-turbine frame
An engine casing for a mid-turbine frame having a plurality of radially extending struts includes a ring structure and at least one mount. The ring structure has an interior surface, an exterior...
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7584620 |
Support system for transition ducts
Aspects of the invention relate to a system for supporting the exit end of a transition duct. The system includes a plurality of support ring segments that collectively form an annular support ring...
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7581402 |
Turbine engine combustor with bolted swirlers
Aspects of the invention relate to a system for attaching a fuel swirler assembly in a turbine engine combustor. According to embodiments of the invention, at least an axial upstream end of the...
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7581399 |
Damped coil pin for attachment hanger hinge
The present invention is directed toward a suspension system for mounting an exhaust duct liner within an exhaust duct of a gas turbine engine. An exhaust liner suspension system comprises a...
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7578134 |
Methods and apparatus for assembling gas turbine engines
A method for assembling a gas turbine engine is provided. The method includes providing a combustor liner support including a first portion formed with a plurality of circumferentially-spaced...
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7571614 |
Turboshaft engine comprising two subassemblies assembled under axial stress
Turboshaft engine including two subassemblies defining between them an annular chamber housing a seal. The two subassemblies are assembled under axial stress thereby defining an annular chamber...
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7568350 |
Combustion chamber for a turbomachine
Combustion chamber for a turbomachine, comprising a chamber endwall equipped with fuel injection means and axisymmetric walls connecting the chamber endwall to internal and external flanges for...
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7566029 |
Suspension for suspending a jet engine on an aircraft strut
A suspension for suspending a jet engine on an aircraft strut includes a beam having a platform provided with fasteners for fastening the beam to the aircraft strut and arranged transversely with...
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7565807 |
Heat shield for a fuel manifold and method
The manifold includes supports which slidably engage a heat shield to floatingly suspend it around the manifold. The manifold is part of a heat shield assembly inside a gas turbine engine. The...
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7559203 |
Cooled support boss for a combustor in a gas turbine engine
The support boss is used in a combustor of a gas turbine engine. It comprises a side wall defining an internal space. The side wall has at least one air inlet orifice. It also comprises a bottom...
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7559202 |
Reduced thermal stress fuel nozzle assembly
An assembly that includes two components joined by a pre-compressed braze where the compression in the braze is progressively relieved upon relative thermal expansion of the two components. Also...
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7546743 |
Bolting configuration for joining ceramic combustor liner to metal mounting attachments
A gas turbine combustor includes a substantially cylindrical combustor liner located substantially concentrically within a flow sleeve, the combustor liner composed through a ceramic matrix...
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7546742 |
Gas turbine engine assembly and method of assembling same
A method of reducing gas turbine engine distortion includes coupling a core gas turbine engine to a power turbine, coupling the power turbine to a thrust bearing support assembly through a...
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7543442 |
Turbojet engine comprising a connector arm for ancillary systems, and the connector arm for ancillary systems
A turbofan jet engine includes an outer fan duct, an inner fan duct, fluid-conveying ancillaries located outside the outer fan duct, fluid-conveying ancillaries located inside the inner fan duct....
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7526921 |
Auxiliary power unit with integral firebox
An auxiliary power unit (APU) with integral firebox provides an integral unit for aircraft to utilize an APU without the use of a separate firebox. The present invention comprises a turbomachine...
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7523616 |
Methods and apparatuses for assembling a gas turbine engine
A method for assembling a gas turbine engine includes coupling an axisymmetric structure within the gas turbine engine, wherein the axisymmetric structure includes a plurality of mounting bushings...
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7516621 |
Modular LRU accessory mounting substrate for auxiliary power unit
A multiple accessory support bracket that mounts a plurality of external accessories for an auxiliary power unit (APU) so that all the external accessories may be mounted to the APU in a single...
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7506514 |
Augmentor fuel conduit bushing
A gas turbine engine augmentor has a centerbody within a gas flowpath from upstream to downstream. A plurality of vanes are positioned in the gas flowpath outboard of the centerbody. An augmenter...
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7506499 |
Turbofan jet engine with ancillaries distribution support
A turbofan jet engine includes an outer casing supported by arms, an inner casing facing the outer casing, ancillaries, and an ancillaries distribution support. The ancillaries distribution support...
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7493771 |
Methods and apparatuses for assembling a gas turbine engine
A method for assembling a gas turbine engine includes coupling an axisymmetric structure within the gas turbine engine, wherein the axisymmetric structure includes at least one mounting bushing...
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7478534 |
Arrangement with a twist-lock coupling for a turbomachine combustion chamber
The invention relates to an arrangement for a turbomachine combustion chamber, the arrangement comprising a chamber end wall pierced by at least one opening, an injector system, and a deflector...
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7438262 |
Redundant gas turbine engine mounting arrangement
A gas turbine engine mounting arrangement for attaching a gas turbine engine to a support structure, such as a pylon of an aircraft, comprises a main mounting member adapted to interconnect the...
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7434383 |
Bypass duct boss repair technology
The present invention provides a bypass duct and boss assembly comprising: a bypass duct having an exterior surface, an interior surface, an edge surface, an inner bonding surface, and a side wall...
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7424360 |
Overspeed control system for gas turbine electric powerplant
A turbine overspeed control system for use with a gas turbine engine of a gas turbine electrical powerplant. The overspeed control system preferably comprises a first and second overspeed control...
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7409819 |
Gas turbine engine and method of assembling same
A method of assembling a gas turbine engine that includes rotatably coupling a first low-pressure turbine rotor to a high-pressure turbine, rotatably coupling a second low pressure turbine rotor to...
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7377117 |
Transition piece for gas turbine
As used to connect a combustor of a gas turbine to a stage of the gas turbine, a transition piece has a generally tubular body, an inlet to receive hot gases from the combustor, and an outlet to...
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7377116 |
Gas turbine combustor barrier structures for spring clips
A barrier structure ( 302 ) blocks exit of spring clip fragments ( 317 ) that may break off from a spring clip assembly disposed between a gas turbine engine combustor ( 300 ) and a transition...
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7360988 |
Methods and apparatus for assembling turbine engines
A method facilitates the assembly of a gas turbine engine. The method comprises providing a turbine nozzle including an inner band, an outer band, and at least one vane extending between the inner...
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7350619 |
Auxiliary power unit exhaust duct with muffler incorporating an externally replaceable acoustic liner
Methods and apparatus are provided for an exhaust duct having an externally replaceable acoustic liner. The exhaust duct includes a forward section that is configured to be axially coupled with a...
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7316117 |
Can-annular turbine combustors comprising swirler assembly and base plate arrangements, and combinations
A gas turbine combustor ( 10 ) comprises a main swirler assembly ( 400 ) comprising an annulus casting ( 410 ) itself comprising a modified downstream end ( 418 ) fitted into an reversed-edge base...
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7310952 |
Methods and apparatus for attaching swirlers to gas turbine engine combustors
A method facilitates assembling a combustor for a gas turbine engine, wherein the combustor includes a swirler assembly. The method comprises machining material to form a domeplate, positioning a...
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7275362 |
Thrust reversers including latching mechanisms and methods for manufacturing such thrust reversers
Thrust reversers having latching mechanisms and methods for manufacturing such thrust reversers are disclosed herein. An aircraft system in accordance with one embodiment includes a thrust reverser...
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7249462 |
Mounting a turbine nozzle on a combustion chamber having CMC walls in a gas turbine
The gas turbine comprises an annular combustion chamber having inner and outer walls made of ceramic matrix composite material, and a high pressure turbine nozzle secured to a downstream end of the...
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7249461 |
Turbine fuel ring assembly
A turbine fuel ring assembly includes a fuel distribution ring, at least one fuel supply tube attached to the fuel distribution ring and at least one attachment leg connected to the fuel...
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7237388 |
Assembly comprising a gas turbine combustion chamber integrated with a high pressure turbine nozzle
The high pressure turbine nozzle is mechanically connected to a downstream end portion of the combustion chamber and inner and outer connection ferrules connect the combustion chamber and turbine...
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7237387 |
Mounting a high pressure turbine nozzle in leaktight manner to one end of a combustion chamber in a gas turbine
The downstream end portions of the inner and outer walls of the combustion chamber of the gas turbine are pressed against the inner and outer platforms respectively of the vanes of the high...
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7234306 |
Gas turbine combustion chamber made of CMC and supported in a metal casing by CMC linking members
The annular combustion chamber having ceramic matrix composite material walls is mounted inside a metal casing by linking members fastened to the chamber by brazing. The linking members comprise a...
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7210900 |
Gas turbine engine component having bypass circuit
A gas turbine engine component has an annular flange arm, a backing plate mounted to the flange arm and a bypass circuit formed between the flange arm and the backing plate. The bypass circuit...
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7197882 |
Turbojet diffuser
A turbojet diffuser disposed between a compressor and a combustion chamber, and secured to an outer upstream annular flange of an outer casing of the combustion chamber by suspension means which...
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7194866 |
Static structure for an expendable gas turbine engine
A static structure for a miniature gas turbine engine includes a forward housing, a forward cover, a diffuser housing, a diffuser, a turbine nozzle, a combustor liner, a combustor housing and an...
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7185499 |
Device for passive control of the thermal expansion of the extension casing of a turbo-jet engine
The invention relates to a device for passive control of the thermal expansion of the extension casing of a turbo-jet engine, said extension casing surrounding the casing of the high pressure...
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7185498 |
Modular gas turbine
Method and arrangement for providing a gas turbine ( 1 ) having a duct ( 11 ) for carrying gas from a gas turbine inlet ( 9 ) to a gas turbine outlet ( 10 ) and an outer housing ( 19, 20, 21 )...
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7168253 |
Monobloc flameholder arm for an afterburner device of a bypass turbojet
A support arm ( 13 ) is intended to be installed in a radial position in an afterburner device of a bypass turbojet. The device comprises first and second inner annular casings defining a passage...
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7152411 |
Rabbet mounted combuster
A combustor includes an outer wall and an inner liner joined to an inner shell in turn mounted to an inner casing. The casing includes a first rabbet at an end flange in which is mounted a...
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7140189 |
Gas turbine floating collar
A simplified floating collar is provided comprising an collar with opposed flanges. The arrangement offers reduced cost, and simplicity, and therefore facilitates manufacturing.
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7134287 |
Turbine combustor endcover assembly
The endcover assembly for a combustor includes an endcover having an aperture, an insert disposed in the stepped bore opening through an internal face of the endcover, a fuel cartridge extending...
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7134286 |
Gas turbine floating collar arrangement
A simplified floating collar mounting arrangement for receiving a fuel nozzle swirler body of a gas turbine engine combustor is provided. The assembly comprises a floating collar mounted between a...
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