Matches 1 - 50 out of 84 1 2 >


Match Document Document Title
US20140075957 FORMED GUSSETS FOR BRACKETS ON GAS TURBINE ENGINES  
Disclosed is a bracket mount assembly for use in a gas turbine engine. The bracket mount assembly includes a communicating member, a mount, and a bracket. The bracket is supported by a static...
US20130192235 INTERNAL MANIFOLD FOR TURNING MID-TURBINE FRAME FLOW DISTRIBUTION  
A mid-turbine frame (MTF) for a gas turbine engine includes an inner manifold directing air to a turbine rotor of the gas turbine engine.
US20130319002 NACELLE BIFURCATION FOR GAS TURBINE ENGINE  
A nacelle structure for a gas turbine engine includes a core engine nacelle disposed about an engine axis and an outer nacelle disposed about the core engine nacelle. A bifurcation extends between...
US20110197595 ENGINE ASSEMBLY FOR AN AIRCRAFT COMPRISING ATTACHMENTS FOR ENGINES OFFSET BELOW ON THE FAN FRAME  
An aircraft engine assembly including an attachment mechanism of a turbojet onto a rigid structure of a mounting strut, including a first, second, and third forward engine attachment for taking up...
US20140290270 ATTACHMENT PYLON FOR A TURBINE ENGINE  
A pylon for attaching a turbine engine, the pylon configured to connect the engine to a structural element of an aircraft. The pylon includes a streamlined profile defined by two opposite lateral...
US20130161446 HINGING CRADLE FOR FAN COWLS SUPPORTED BY SAID COWLS IN CLOSED POSITION  
The invention relates to an engine assembly for aircraft in which the coupling device comprises a fore aerodynamic structure having a cradle equipped with an aerodynamic cowling, the cradle being...
US20130227963 ASSEMBLY FOR ATTACHING THE HANGERS FROM WHICH AN AIRCRAFT PROPULSION UNIT IS SUSPENDED  
An assembly is designed to attach hangers from which an aircraft propulsion unit is suspended. The propulsion unit is intended to be suspended from a structural element of the aircraft. The...
US20140252159 ENGINE INSTALLATION  
A fuselage mounted gas turbine engine installation the installation includes at least one propeller stage and a gas turbine core arranged in use to drive the propeller stage. The core is external...
US20140252160 REVERSE FLOW GAS TURBINE ENGINE REMOVABLE CORE  
An engine mounting arrangement includes a propulsor mounted to an aircraft wing, and an engine core aerodynamically connected to the propulsor and positioned rearward of the propulsor.
US20140202169 ASSEMBLY FORMED BY A TURBINE ENGINE AND A SYSTEM FOR ATTACHING IT TO AN AIRCRAFT STRUCTURE  
In an assembly including a bypass turbine engine and an attachment system attaching the turbine engine to an aircraft structure, the attachment system includes a mast, at least two rear...
US20140047850 ASSEMBLY FOR MOUNTING A TURBINE ENGINE TO AN AIRFRAME  
An assembly is provided for mounting a turbine engine to an airframe. The turbine engine extends along an axial centerline and includes an engine core mount and an engine exhaust mount. The...
US20110146299 ANNULUS FILLER ASSEMBLY FOR A ROTOR OF A TURBOMACHINE  
An annulus filler assembly for a rotor of a turbomachine, the assembly comprising: an annulus lid (56) having a radially outwardly facing surface (58) for forming an inner wall of a flow annulus...
US20150052909 FUEL CONTROL MODULE GAS VENT MANIFOLD  
A fuel control module including a gas vent manifold is disclosed. The gas vent manifold includes a first gas vent portion including a first gas vent connection and a second gas vent portion...
US20130145770 SUBSTITUTION DEVICE FOR AIRCRAFT ENGINE  
A substitution device for replacing a turbojet type of aircraft engine, with a nacelle comprising protective covers, and a support mast having two engine mounts, each of said protective covers...
US20140360206 AIRCRAFT POWERPLANT  
An aircraft propulsion power plant for use in an aircraft includes one or more core engines housed in an airframe of the aircraft, one or more secondary propulsion units, each of the one or more...
US20130125560 LATERAL TURBOJET IMPROVED IN ORDER TO LIMIT THE DEFORMATION THEREOF  
A turbojet includes an intermediate casing outer shroud connected to a front suspension and a primary structure connected to a rear suspension; the shroud and the primary structure are held in a...
US20150007580 METHOD OF PRODUCING SUSPENSION FOR A STRUCTURE IN A TURBOJET ENGINE USING A HYPERSTATIC TRELLIS WITH PRE-STRESSED LINK ELEMENTS  
The invention relates to a method of manufacturing an assembly comprising a first structure (23), arranged to be rigidly connected to a housing of a turbojet engine, a second annular structure...
US20130074517 GAS TURBINE ENGINE MOUNT ASSEMBLY  
A forward mount assembly for connecting a pylon to an intermediate case of a gas turbine engine, the forward mount assembly includes a forward mount platform, a wiffle tree assembly, and first and...
US20110154831 AIRCRAFT ENGINE ASSEMBLY COMPRISING A TURBOJET ENGINE WITH REINFORCING STRUCTURES CONNECTING THE FAN CASING TO THE CENTRAL CASING  
An aircraft engine assembly including an annular structure surrounding a central casing and mechanically connected to the central casing by the intermediary of a mounting mechanism. To each of the...
US20120167592 MOUNTING SYSTEM FOR A GAS TURBINE ENGINE  
A mounting system for a gas turbine engine includes a mounting linkage assembly and a tangential link positioned generally transverse to the mounting linkage assembly. The mounting linkage...
US20140130512 TURBINE ENGINE ATTACHMENT STRUCTURE  
An attachment structure for attaching a power plant including unducted propellers to a fuselage of an aircraft, the attachment structure being connected by first and second fasteners to respective...
US20110048029 TURBOMACHINE CORE COUPLING ASSEMBLY  
A coupling assembly for an engine core of a turbomachine is provided. The coupling assembly comprises a duct having a substantially circular shape and surrounding the engine core, and a plurality...
US20130067931 GAS TURBINE ENGINE ASSEMBLIES INCLUDING STRUT-BASED VIBRATION ISOLATION MOUNTS AND METHODS FOR PRODUCING THE SAME  
Embodiments of a gas turbine engine assembly including a strut-based vibration isolation mount are provided, as are embodiments of a method for producing such a gas turbine engine assembly. In one...
US20070144180 Dual bayonet engagement and method of assembling a combustor liner in a gas turbine engine  
A combustor assembly is provided that includes a forward annular liner, an aft annular liner, and a stator. The forward annular liner has an inner annular edge and an outer annular edge. The aft...
US20130174572 METHOD FOR COOLING A THERMAL PROTECTION FLOOR OF AN AFT AERODYNAMIC FAIRING OF A STRUCTURE FOR MOUNTING AN AIRCRAFT PROPULSION SYSTEM  
A propulsion system for an aircraft, including a dual-flow turbojet and a mounting structure for mounting this turbojet on the wing surface or on the fuselage of an aircraft. The mounting...
US20140033729 METHOD FOR MOUNTING AN AIRCRAFT ENGINE ON A PYLON, AND ENGINE FASTENER FOR IMPLEMENTING SAID METHOD  
A method for mounting an aircraft engine on a pylon includes positioning at least a first shear pin either in a first opening provided in a front engine fastener which is previously attached to...
US20060080971 Power trailer structural elements for air flow, sound attenuation and fire suppression  
An enclosure comprising elements for air management, sound attenuation and fire suppression in a trailer-mounted mobile electrical power generation system. Air management is provided by ducts,...
US20130327058 DEVICE FOR SUSPENDING A TURBOJET ENGINE  
A turbojet is suspended by attachments including hinged links. An attachment includes a support including three branches with passages through which a pin passes, the pin being oriented generally...
US20140102110 MID-TURBINE FRAME WITH TENSIONED SPOKES  
A mid-turbine frame located in a gas turbine engine axially aft of a high-pressure turbine and fore of a low-pressure turbine includes an outer frame case, an inner frame case, and at least a...
US20100024435 NACELLE FOR TURBOFAN  
The nacelle of the invention includes an air-inlet front section, a middle section for encasing the fan of the turbofan (7) and a rear section including means for connection to a pylon to be...
US20090255271 STRUCTURAL NACELLE  
The present invention relates, on the one hand, to a nacelle (1) for a double flow turboreactor (2) comprising a front air intake section (5), a median section (6) intended for surrounding a fan...
US20090121083 Nacelle Flow Assembly  
A nacelle assembly for a turbine engine has a cowl for a turbine engine. The cowl has a first surface spaced from a second surface. The second surface defines defining a bypass flow passage. A...
US20140013771 MID-TURBINE FRAME WITH THREADED SPOKES  
A mid-turbine frame located in a gas turbine engine axially aft of a high-pressure turbine and fore of a low-pressure turbine includes an outer frame case, an inner frame case, and at least a...
US20150198093 BRACKET FOR MOUNTING/REMOVAL OF ACTUATORS FOR ACTIVE VIBRATION CONTROL  
An active vibration control actuator mount including at least one actuator bracket having an actuator interface member configured to hold one or more active vibration element thereon in one or...
US20130074518 GAS TURBINE ENGINE TIE ROD RETAINER  
An assembly for use with a gas turbine engine includes a tie rod and a connector. The tie rod, which is for extending radially outwardly from a latitudinal axis of the gas turbine engine, has a...
US20080307795 EXHAUST CASING HUB COMPRISING STRESS-DISTRIBUTING RIBS  
An exhaust casing hub comprises a hub center (6), and an upstream flange (8) and a downstream flange (10) arranged on either side of the hub center. Each flange is terminated by a rim (12). A...
US20140290269 DUCT BLOCKER SEAL ASSEMBLY FOR A GAS TURBINE ENGINE  
A seal system for a gas turbine engine includes a cover plate with a radial flange; a seal carrier adjacent the cover plate; an outer compliant seal supported by the seal carrier; an inner...
US20140190180 FAIRING OF A GAS TURBINE STRUCTURE  
A gas turbine structure includes a first housing and a second housing, one of the first and second housings being located around the other of the first and second housings such that a core flow...
US20140069107 TURBOPROP ENGINE WITH COMPRESSOR TURBINE SHROUD  
A turboprop engine including an annular outer case including a mount ring for attachment to an aircraft along a plane to transfer loads from a propeller and having an annular flange extending...
US20130019609 GAS TURBINE ENGINE SYSTEMS INVOLVING I-BEAM STRUTS  
Gas turbine engine systems involving I-beam struts are provided. In this regard, a representative strut assembly for a gas turbine engine includes a first I-beam strut having first and second...
US20100162726 Mobile platform system for a gas turbine engine  
A system for moving an auxiliary component of a gas turbine engine is disclosed. The system may have a mobile support platform configured to support the auxiliary component during operation of the...
US20150260103 INTEGRATED STRUT AND IGV CONFIGURATION  
A strut and IGV configuration in a gas turbine engine positioned at an upstream of a rotor includes a plurality of radial struts, for example for bearing engine loads, and a plurality of inlet...
US20100043450 SYSTEM FOR ATTACHING AN ENGINE TO THE STRUCTURE OF AN AIRCRAFT, SUCH AS A SAIL WING AIRCRAFT  
System for attaching an engine to the structure of an aircraft, such as a sail wing aircraft. The system includes an upper beam which is firmly fixed at its front end to a first frame mounted on...
US20100163671 A MOUNTING ELEMENT FOR A GAS TURBINE ENGINE, AND A STRUCTURE AND AN AIRCRAFT WITH SUCH A MOUNTING ELEMENT  
A mounting element for transferring loads between a gas turbine engine and an airframe is provided, the mounting element presenting a cylindrical hole for receiving a fastening element, such as a...
US20140260322 SUPPORT MECHANISM FOR HEAVY STRUCTURE  
To provide a support mechanism for a heavy structure, capable of accommodating thermal deformation of component parts of a device operated under high temperature condition, a support mechanism for...
US20120324907 MOUNTING ASSEMBLY  
A mounting assembly for attaching a ducted fan gas turbine engine that includes an intake, a propulsive fan, a fan case surrounding the fan, and a core engine. The air intake is attached to the...
US20130327059 DRAINING DEVICE  
A draining device for draining a fluid from an aircraft engine support strut includes a suction arrangement having an inlet and extending along a longitudinal main axis to form a plenum chamber...
US20130160465 GAS TURBINE ENGINE SYSTEMS  
A gas turbine engine 10 comprises at least one rigid raft assembly that has a fluid passageway 210 at least partially embedded therein. The fluid passageway 210 is at least a part of a fluid...
US20130186105 ANISOTROPIC VIBRATION ISOLATION MOUNTING ASSEMBLY  
An anisotropic vibration isolation mounting assembly includes at least two three-parameter vibration isolators each having a first end configured for attachment to a rotating member assembly or a...
US20150114006 AIRCRAFT ENGINE STRUT ASSEMBLY AND METHODS OF ASSEMBLING THE SAME  
An engine strut for providing fan hub frame structural support and monitoring an air flow within an aircraft engine includes an airfoil coupled to the aircraft engine and has a first portion and a...

Matches 1 - 50 out of 84 1 2 >