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| Number | Title | Issue Date |
| 8438832 | High turning fan exit stator A turbine engine includes a fan section that rotates about a longitudinal axis and a compressor section. The turbine engine also includes a fan exit stator located between the fan section and the compressor section, the fan exit stator including an airfoil. The airf... | 05/14/2013 |
| 8402742 | Gas turbine engine systems involving tip fans Gas turbine engine systems involving tip fans are provided. In this regard, a representative gas turbine engine system includes: a multi-stage fan having a first rotatable set of blades and a second counter-rotatable set of blades, the second rotatable set of blades... | 03/26/2013 |
| 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 plurality of discrete sections is selectively adjustable between a first posit... | 03/26/2013 |
| 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 gas-turbine core engine 10 is operationally connect... | 03/26/2013 |
| 8402741 | Gas turbine engine shaft bearing configuration A gas turbine engine includes a core housing providing a core flowpath. A shaft supports a compressor section arranged within the core flowpath. First and second bearings support the shaft relative to the core housing and are arranged radially inward of and axially ... | 03/26/2013 |
| 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 compressor section, a combustor, and at least one turbine section. The... | 02/05/2013 |
| 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 direction in the casing of the engine, the auxiliaries connected are to be o... | 12/25/2012 |
| 8276362 | Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method A turbine engine includes a plurality of variable fan inlet guide vanes. Where the turbine engine is a tip turbine engine, the variable fan inlet guide vanes permit the ability to control engine stability even though the fan-turbine rotor assembly is directly couple... | 10/02/2012 |
| 8272203 | External fan duct casing in a turbomachine Twin-flow turbo-jet engine, comprising a cylindrical casing externally defining an annular flow space for a secondary flow, wherein the cylindrical casing is formed from a lattice framework and from removable cowling panels fixed to the framework, said framework com... | 09/25/2012 |
| 8261530 | Cambered aero-engine inlet An inlet of a nacelle for channeling inlet airflow to a fan of a gas turbine engine includes a forward lip and an inner surface. The forward lip extends around a centerline axis of the engine and is adapted to accommodate a flow angle of incoming airflow. The inner ... | 09/11/2012 |
| 8250852 | Dual flow turbine engine equipped with a precooler A pre-cooler having an annular cross-sectional shape about the axis of a pod and arranged inside the rear part of an inner shroud in external contact with a cold flow exiting a fan duct channel and in close contact with a cooling air stream drawn from the cold flow.... | 08/28/2012 |
| 8209953 | Gas turbine engine system providing simulated boundary layer thickness increase A gas turbine engine system for an aircraft includes a nacelle having a fan cowl with an inlet lip section and a core cowl, at least one compressor and at least one turbine, at least one combustor between the compressor and the turbine, a bleed passage, and a contro... | 07/03/2012 |
| 8209952 | Gas turbine engine with intermediate speed booster A gas turbine engine having speed an intermediate stage booster configured to provide speed change to a boost compressor. The boost compressor and fan stage are driven by a low pressure turbine; the fan stage rotates with the low pressure turbine shaft and the boost... | 07/03/2012 |
| 8205430 | Variable geometry nacelle assembly for a gas turbine engine A nacelle assembly includes an inlet lip section and a cowl section positioned downstream of the inlet lip section. At least a portion of the cowl section is moveable to influence an effective boundary layer thickness of the nacelle assembly. ... | 06/26/2012 |
| 8205431 | Bearing-like structure to control deflections of a rotating component A bearing like surface on a stationary component reduces deflection of an adjacent rotating component. The stationary component is generally parallel to and offset from a rotational component. The rotational component rotates about a central axis. Protrusions locate... | 06/26/2012 |
| 8186144 | Component ventilation and pressurization in a turbomachine A dual-flow turbomachine (10), essentially comprising a fan (14), a compressor (20), a combustion chamber (21), a turbine (22) and an exhaust casing (24), which comprises an auxiliary air compressor (48) driven by a S... | 05/29/2012 |
| 8181442 | Gas turbine aircraft engine with power variability A gas turbine aircraft engine with power variability is provided. The gas turbine aircraft engine comprises a compressor and a turbine mounted on a common shaft, and, a continuously variable transmission coupled to the shaft for transmitting power to a propulsion lo... | 05/22/2012 |
| 8181443 | Heat exchanger to cool turbine air cooling flow A cooling system of a gas turbine engine, includes a heat exchanger having a common wall shared by a first air passage for directing a portion of a compressor air flow to be used as cooling air, and a second air passage for directing a portion of a bypass air flow, ... | 05/22/2012 |
| 8176725 | Reversed-flow core for a turbofan with a fan drive gear system A gas turbine engine comprises a fan drive gear system, a low spool connected to the fan drive gear system, and a high spool disposed aft of the low spool. The low spool comprises a rearward-flow low pressure compressor disposed aft of the fan drive gear system, and... | 05/15/2012 |
| 8141337 | Dual flow turbine engine equipped with a precooler A bypass turbine engine includes a precooler having an annular cross-sectional shape about the axis of a pod and arranged inside the rear part of an inner shroud in contact with a cold fluid exiting a fan duct. ... | 03/27/2012 |
| 8127528 | Auxiliary propulsor for a variable cycle gas turbine engine A core engine of a variable cycle gas turbine engine includes a low pressure spool for generating streams of bypass air and pressurized air, and a high pressure spool for further pressurizing the stream of pressurized air to generate streams of combustion air and su... | 03/06/2012 |
| 8099944 | Hybrid propulsive engine including at least one independently rotatable propeller/fan A hybrid propulsive technique includes providing at least some first thrust associated with a flow of a working fluid through at least a portion of an at least one axial flow jet engine. The hybrid propulsive technique comprises extracting energy from the working fl... | 01/24/2012 |
| 8082727 | Rear propulsor for a variable cycle gas turbine engine A gas turbine propulsion system comprises a turbofan engine, a peripheral duct, an annular frame, an auxiliary turbine and an auxiliary fan. The turbofan engine is configured to produce bypass air and combustion air. The bypass air flows through a bypass duct and th... | 12/27/2011 |
| 8082726 | Tangential anti-swirl air supply A turbofan flow delivery system includes a fan case housing a fan. Flow exit guide vanes are arranged downstream from the fan and extend radially inwardly from the fan case toward a bypass flow path. A supply passage includes an opening provided in the fan case betw... | 12/27/2011 |
| 8065867 | Radial ball bearing A bearing assembly includes an outer race and an inner race with a ball bearing element located between the inner and the outer races. The inner race has a first portion and a second portion separated from the first portion by a split. The first portion includes a f... | 11/29/2011 |
| 8033094 | Cantilevered tip turbine engine A tip turbine engine (10) according to the present invention includes an engine support structure (12) for cantilevering a load bearing shaft from an engine support plane (P). An engine support structure (12) defines the engine support plane (P)... | 10/11/2011 |
| 8028513 | Variable bypass turbine fan An engine for powering a vehicle, such as a military aircraft or a commercial aircraft, is provided. The engine broadly comprises a main core with a plurality of spools with each spool having a plurality of compressor blades and a plurality of turbine blades attache... | 10/04/2011 |
| 8015796 | Gas turbine engine with dual fans driven about a central core axis A gas turbine engine includes a compressor section, a combustor section and a turbine section, all arranged about a central axis. A turbine rotor drives a driveshaft for rotation on the central axis. The driveshaft in turn drives at least two fan rotors on axes para... | 09/13/2011 |
| 7966806 | Turbofan engine assembly and method of assembling same A turbofan engine assembly includes a core gas turbine engine including a high-pressure compressor, a combustor, and a high-pressure turbine, a low-pressure turbine coupled to said core gas turbine engine, a counter-rotating booster compressor comprising a first rot... | 06/28/2011 |
| 7966807 | Vapor cooled static turbine hardware A cooling system for a gas turbine engine includes a non-rotating component extending into an engine flowpath, a vapor cooling assembly configured to transport thermal energy from a vaporization section to a condenser section through cyclical evaporation and condens... | 06/28/2011 |
| 7963098 | Composite duct assembly A carbon composite duct assembly has a duct body having an opening. The duct body extends along an axis. The opening extends transversely to the axis. The duct body has a carbon composite fabric layer. The duct body has an axial flange extending along the axis and a... | 06/21/2011 |
| 7946104 | Bleed air relief system for engines A bleed air relief system for engines in which a flow of bleed air from the engine compressor is passed along a bleed air duct and exhausted into a bypass air stream passing through the engine. A cover is mounted over the outlet of the bleed air duct and can include... | 05/24/2011 |
| 7926260 | Flexible shaft for gas turbine engine A shaft for a gas turbine engine is provided that includes a first shaft section, a second shaft section, a first flexible linkage, and a second flexible linkage. The first shaft section extends between a forward axial end and an aft axial end along a first axial ce... | 04/19/2011 |
| 7921637 | High bypass-ratio turbofan jet engine To provide a turbofan jet engine which is capable of increasing the bypass ratio without increasing the fan diameter, and of reducing air resistance acting on the engine, a front fan duct that discharges air compressed by a front fan to the atmosphere and an aft fan... | 04/12/2011 |
| 7921635 | Peripheral combustor for tip turbine engine A tip turbine engine (40) provides a peripheral combustor (30) with a more efficient combustion path through the combustor and through the tip turbine blades (34). In the combustor, the core airflow is received generally axially from compressor ... | 04/12/2011 |
| 7921636 | Tip turbine engine and corresponding operating method A tip turbine engine has a more efficient core airflow path from the hollow fan blades, through the combustor and to the combustion chamber of a combustor. The turbine engine includes a rotatable fan having a plurality of radially-extending fan blades each defining ... | 04/12/2011 |
| 7900433 | Fan exhaust nozzle for turbofan engine The cross sectional flow area of a fan discharge nozzle on one side of a central plane of an associated gas turbine engine power plant is greater than the corresponding flow area of the fan discharge nozzle on an opposite side of the central plane to compensate for ... | 03/08/2011 |
| 7886518 | Turbofan engine cowl assembly and method of operating the same An inner core cowl baffle assembly for a turbofan engine assembly is provided. The engine assembly includes a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, and a fan no... | 02/15/2011 |
| 7882695 | Turbine blow down starter for turbine engine In order to start a turbine engine (10), high-pressure fluid is directed onto a turbine (34a) to cause rotation of the turbine and thereby start the turbine engine. In a disclosed embodiment, the high-pressure fluid is provided through a fluid o... | 02/08/2011 |
| 7882694 | Variable fan inlet guide vane assembly for gas turbine engine A turbine engine includes a plurality of variable fan inlet guide vanes. Where the turbine engine is a tip turbine engine, the variable fan inlet guide vanes permit the ability to control engine stability even though the fan-turbine rotor assembly is directly couple... | 02/08/2011 |
