Match Document Document Title
9038362 Turbofan engine with variable area fan nozzle and low spool generator for emergency power generation and method for providing emergency power  
A turbofan engine (10) employs a flow control device (41) that changes an effective exit nozzle area (40) associated with a bypass flow path (B) of the turbofan engine. A spool (14) couples a fan...
9021784 Thermodynamic louvered jet engine  
The thermodynamic louvered jet engine is a jet engine having a central air inlet surrounded by an annular air inlet. Both inlets are adapted to receive relatively cool, low-pressure air and to...
9010085 Turbine section of high bypass turbofan  
A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating...
8984894 Method for operating a combined-cycle power plant with cogeneration, and a combined-cycle power plant for carrying out the method  
The invention relates to a method for operation of a combined-cycle power plant with cogeneration, in which method combustion air is inducted in at least one gas turbine, is compressed and is...
8943797 Cylinder head with symmetric intake and exhaust passages  
A cylinder head for an internal combustion engine defines first and second intake passages for supplying air through first and second intake valve openings to first and second cylinders. The...
8943796 Variable cycle turbine engine  
A gas turbine engine comprises a high spool, a low spool and an intermediate spool. The high spool comprises a high pressure turbine coupled to a high pressure compressor. The intermediate spool...
8881502 Mixer that performs reciprocating rotary motion for a confluent-flow nozzle of a turbine engine, and a method of controlling it  
A mixer for a confluent-flow nozzle of a turbine engine is provided. The mixer includes: an annular cap designed to be centered on a longitudinal axis of the nozzle and having a stationary...
8850793 Turbine section of high bypass turbofan  
A turbofan engine is disclosed and includes a fan and a compressor in communication with the fan section, a combustor, a turbine and a speed reduction mechanism coupled to the fan and rotatable by...
8850824 Aircraft gas turbine with variable bypass nozzle by deforming element  
The present invention relates to an aircraft gas turbine with a core engine which is surrounded by a bypass duct enclosed radially outwards by a bypass wall, with a radially inner wall of the...
8844262 Exhaust for a gas turbine engine  
A gas turbine engine is provided having an offtake passage that in one form is capable of extracting a bypass flow from the engine. The airflow traversing the offtake passage is introduced to an...
8844265 Turbine section of high bypass turbofan  
A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating...
8844264 Gas turbine engine with ejector  
Disclosed is a boundary layer ejector fluidically connecting boundary layer bleed slots from an external surface of an aircraft to reduce aircraft/nacelle/pylon drag, reduce jet noise and decrease...
8813472 System and method for controlling a semi-closed power cycle system  
A system includes a controller configured to control a semi-closed power cycle system. The controller is configured to receive at least one of a first signal indicative of an oxygen concentration...
8800260 Fan variable area nozzle with cable actuator system  
A fan variable area nozzle (FVAN) includes a flap driven through a cable which circumscribes the fan nacelle. The cable is strung through a multiple of flaps to define a flap set of each...
8713910 Integrated thrust reverser/pylon assembly  
Assembly for supporting a gas turbine engine comprises a support member including mounting sites for attachment to an associated aircraft. The support member includes integral slider tracks...
8701385 Method and apparatus for the operation of a turboprop aircraft engine provided with pusher propellers  
A method and an apparatus is disclosed for the operation of a turboprop aircraft engine provided with pusher propellers. In order to reduce thermal loading of the pusher propellers impaired by the...
8695324 Multistage tip fan  
A fan assembly having an outer fan system is disclosed, the fan assembly comprising an outer fan first stage and an outer fan second stage both extending radially outward from an arcuate platform.
8683812 Arrangement for controlling fluid jets injected into a fluid stream of a bleed air discharge nozzle  
In an air mixing arrangement wherein a primary fluid is introduced through an opening in a wall to be mixed with a secondary fluid flowing along the wall surface, the opening is airfoil shaped...
8671693 Thermally conductive structure  
A multi-layered honeycomb structure adapted to reduce and/or eliminate thermal deformation is disclosed herein. In some embodiments, walls of the honeycomb structure comprise a first layer,...
8667775 Reverse flow engine core having a ducted fan with integrated secondary flow blades  
Secondary air flow is provided for a ducted fan having a reverse flow turbine engine core driving a fan blisk. The fan blisk incorporates a set of thrust fan blades extending from an outer hub and...
8667774 Coannular ducted fan  
Secondary air flow is provided for a ducted fan having an engine core driving a fan blisk. The fan blisk incorporates a set of thrust fan blades extending from an outer hub and a set of integral...
8635875 Gas turbine engine exhaust mixer including circumferentially spaced-apart radial rows of tabs extending downstream on the radial walls, crests and troughs  
A gas turbine engine exhaust mixer has a plurality of circumferentially distributed alternating inner and outer lobes. The outer lobes protrude into the annular bypass passage of the engine,...
8601788 Dual flow turboshaft engine and improved hot flow nozzle  
An improved bypass turbojet engine includes a particularly shaped hot flow nozzle arranged about a particularly shaped type of boss. The boss is bulbous in shape and is connected by a first...
8584356 Method of manufacturing a CMC flow mixer lobed structure for a gas turbine aeroengine  
A method of fabricating a lobed structure for a gas turbine flow mixer having an annular upstream portion extended downstream by a portion forming a multilobed skirt, the method comprising: making...
8579225 Device for acoustic treatment of the noise emitted by a turbojet  
The invention provides a device for acoustical treatment of the noise emitted by a bypass turbojet comprising a primary cowl having in an outer surface an inner annular acoustic treatment panel...
8572947 Gas turbine engine with ejector  
The present inventions include a boundary layer ejector fluidically connecting boundary layer bleed slots from an external surface of an aircraft to reduce aircraft/nacelle/pylon drag, reduce jet...
8534043 Air-oil heat exchanger  
A heat exchange system for use in fluid operated equipment to provide air and working fluid heat exchanges to cool the working fluid in airstreams on a stream side of a wall. An actuator is...
8522528 System for diffusing bleed air flow  
In one aspect, the present disclosure is directed an apparatus configured to diffuse a flow of bleed air. The apparatus having an inlet collar configured to receive the flow of bleed air in a...
8522572 Adaptive power and thermal management system  
An aircraft adaptive power thermal management system for cooling one or more aircraft components includes an air cycle system, a vapor cycle system, and a fuel recirculation loop operably disposed...
8516824 Gas ejection cone for an aircraft turbojet equipped with a device for generating turbulence in a primary flow limiting jet noise  
A gas ejection cone for an aircraft turbojet, the cone including a hollow main body defining, on the outside, a radially inner skin of an annular primary flow channel, and a device generating...
8516791 Methods and apparatus for mixing fluid in turbine engines  
A method of assembling a gas turbine engine is provided. The method includes providing at least one heat exchanger assembly including a heat exchanger and a mixer extending downstream from the...
8511098 Slideable liner link assembly  
An example engine assembly includes a first attachment structure secured to an engine casing or an engine liner, and a second attachment structure secured to the other of the engine casing or the...
8499544 Turbogenerator with cooling system  
A turbogenerator having a gas turbine engine powering generator and a cooling system and an annular heat exchanger powered by a fan disposed across an outer fan duct of the engine. Fan variable...
8490382 Modulating flow through gas turbine engine cooling system  
A gas turbine engine system includes a fan bypass passage in a cooling passage having an inlet that receives a bleed flow from the fan bypass passage and an outlet that discharges the bleed flow...
8484943 Impingement cooling for turbofan exhaust assembly  
A system comprises a bypass duct, a turbine case, a turbine exhaust ring and a splash plate. The turbine case is formed along a radially inner margin of the bypass duct, and the turbine exhaust...
8464512 Actuator for an aircraft nacelle mobile structure, and nacelle comprising at least one such actuator  
This actuator for an aircraft engine nacelle mobile structure (9) comprises a motor (1) intended to be mounted on a fixed part of the said nacelle, an endless screw (21) able to be turned by this...
8459017 Low pressure drop mixer for radial mixing of internal combustion engine exhaust flows, combustor incorporating same, and methods of mixing  
An exhaust aftertreatment system is provided. The exhaust aftertreatment system includes a mixing arrangement for mixing flows of exhaust along a flow path. The mixing arrangement radially and...
8438835 Methods and apparatus for mixing fluid in turbine engines  
A method of assembling a gas turbine engine includes providing at least one heat exchanger assembly including a heat exchanger and a lobed mixer extending downstream from the heat exchanger,...
8438829 Turboprop propulsion unit with pusher propeller  
A turboprop propulsion unit includes at least one pusher propeller 5, 6 driven by an aircraft gas-turbine engine, with the aircraft gas-turbine engine being arranged in front of the pusher...
8408009 Cooling air bleed device in a turbine engine  
Air bleed device for cooling components in a turbine engine, including an annular conduit (18) having a radially internal portion swept by an airflow (22) and which comprises at least one air...
8408491 Nacelle assembly having inlet airfoil for a gas turbine engine  
A nacelle assembly includes an inlet lip section and an airfoil adjacent to the inlet lip section. The airfoil is selectively moveable between a first position and a second position to adjust the...
8402740 Aircraft propulsion unit in multi-fan design  
An aircraft propulsion unit includes a gas-turbine core engine 10 having at least one compressor, one combustion chamber and one turbine driving a main shaft 11. The main shaft 11 of the...
8402739 Variable shape inlet section for a nacelle assembly of a gas turbine engine  
A nacelle assembly includes an inlet section having a plurality of discrete sections. Each of the plurality of discrete sections includes an adaptive structure. A thickness of each of the...
8393139 Device with secondary jets reducing the noise generated by an aircraft jet engine  
An aircraft jet engine including a wall centered about a longitudinal axis and surrounding a stream of gas ejected at a downstream end of the wall in the direction of the axis, primary ducts...
8387389 Gas turbine engine  
A gas turbine engine includes a first flow passage and a main combustion arrangement in the first flow passage. The engine further includes a second flow passage and a first catalytic combustion...
8365514 Hybrid turbofan engine  
A gas turbine engine has, in at least a first mode of operation, a core engine, a fan, and an auxiliary turbine engine coupled as follows. The core engine has, along a core flowpath, at least one...
8360358 Ram air duct flap arrangement and ram air duct  
A ram air duct flap arrangement (22) comprises at least one ram air duct flap (24, 26) which is designed to close, in a closed position, a ram air inlet (14) or a ram air outlet (18) of a ram air...
8356468 Gas turbine engine nozzle configurations  
In one embodiment, a gas turbine engine exhaust nozzle comprises a housing having a length which extends along a central longitudinal axis and comprising an interior surface and an exterior...
8341934 Infrared suppression system with spiral septum  
An InfraRed Suppression System (IRSS) includes a double-walled exhaust duct and double walled septum. The double walled structure provides a flow path for secondary (non-exhaust gas) cooling air...
8336288 Gas-turbine engine in particular aircraft engine  
On a gas-turbine engine, in particular an aircraft engine, with a fan, a fan casing and a fan duct as well as with high-pressure and low-pressure turbines arranged behind each other in flow...