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WO/2010/128241A3 |
The invention relates to an electric power generating device for a propfan-type aircraft propeller rotor, whereby the propulsion unit (1) comprises a turbine engine (8) rotating at least one rotor (3a) having a plurality of blades (4a) d...
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WO/2011/046620A2 |
An aircraft system and method with a first counterweight rotating balancing rotor including holding stepping inboard magnets and outboard mass concentration, and a second counterweight rotating balancing rotor including holding stepping ...
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WO/2010/128239A3 |
The invention relates to a deicing device for propfan-type aircraft propeller blades, whereby the propulsion unit comprises a turbine engine rotating at least one rotor having a plurality of blades (4a) disposed around a ring (5a) that m...
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WO/2011/037852A1 |
An electric power management system of a vehicle may interconnect a power plant, a propeller drive unit, and a battery via a bus. A controller may direct the operation of the power plant and the propeller drive unit. In a slow control mo...
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WO/2011/033204A1 |
The invention relates to a turbine engine with contra-rotating upstream and downstream non-ducted propellers (12, 14) including a power turbine which is mounted axially between the two propellers (12, 14) and which includes an outer roto...
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WO/2011/017071A2 |
A method and apparatus for a novel adaptive aerostructure is presented that relies on certified aerospace materials and can therefore be applied in conventional passenger aircraft. This structure consists of a honeycomb material which ce...
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WO/2011/015475A1 |
The invention relates to a hub for a propeller having variable pitch blades for a turbine engine, in particular for a propfan turbine engine. The propeller hub comprises a polygonal ring (134) having substantially radial cylindrical hous...
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WO/2010/128240A3 |
The invention relates to a deicing device for propfan-type aircraft propeller blades, whereby the propulsion unit comprises a turbine engine rotating at least one rotor having a plurality of blades (4a) disposed around a ring (5a) that m...
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WO/2011/009702A1 |
A mechanical joint for joining two components, the joint having a male part on one component and a corresponding female part on the other component. The male and female parts have respective castellations which intercalate on insertion o...
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WO/2011/010059A2 |
The invention relates to an aircraft turbine engine propeller, comprising a plurality of blades (1) mounted on a hub (2) that is rotatable about a rotational axis (I-I) of the propeller, the aim of the invention being to reduce the risks...
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WO/2011/008337A2 |
A fluid dynamic section (11) provides one or more fixed size escapelets (17, 19) through a foil body to reduce the induced and interference drag caused by trailing vortices and similar wake turbulence. The escapelets, which can be provid...
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WO/2010/136686A3 |
The invention relates to a device for controlling the orientation of the blades of a turboprop fan, comprising at least one set (24a) of fan blades (26) of adjustable orientation coupled in rotation to a rotary ring (28a) connected mecha...
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WO/2008/105704A3 |
A propeller (1) having n blades (2) where n is an integer larger than 0. The propeller (1) having a surface (3) which is described as composed of n identical units (6). Each identical unit (6) is a mathematical minimal surface.
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WO/2010/136685A3 |
The invention relates to a device for controlling the orientation of the blades of a turboprop fan, comprising at least one set (24a) of fan blades (26) of adjustable orientation coupled in rotation to a rotary ring (28a) coaxial with a ...
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WO/2011/003196A1 |
Efficient impeller or propeller wherein at least one blade in a set of blades on a hub of said impeller is oriented with respect to the tilted plane rotated clockwise or counter clockwise in an axis perpendicular to the longitudinal axis...
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WO/2011/000943A1 |
The invention relates to a hub of a propeller with variable-pitch blades for a turbine engine, in particular for a propfan engine. The hub of the propeller comprises a polygonal ring (234) with substantially radial cylindrical recesses (...
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WO/2010/144003A1 |
The present invention relates to a main rotor arrangement (1) for an UAV-helicopter, comprising a rotor mast (3) defining a vertical axis of rotation (R), and a hub (5) for attachment of rotor blades, wherein the hub (5) is mounted to th...
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WO/2010/140933A1 |
The invention relates to a rotor damper for a tail rotor (1) of a helicopter (4), comprising a main body (30) of a resilient material to be arranged between a drive shaft (6) for the tail rotor (1) and a hub (12) on which rotor blades (1...
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WO/2010/136686A2 |
The invention relates to a device for controlling the orientation of the blades of a turboprop fan, comprising at least one set (24a) of fan blades (26) of adjustable orientation coupled in rotation to a rotary ring (28a) connected mecha...
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WO/2010/136684A1 |
The invention relates to a device for controlling the orientation of the blades of a turboprop fan, comprising at least one set of fan blades (26) of adjustable orientation coupled in rotation to a rotary ring (28b) coaxial with a longit...
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WO/2010/136685A2 |
The invention relates to a device for controlling the orientation of the blades of a turboprop fan, comprising at least one set (24a) of fan blades (26) of adjustable orientation coupled in rotation to a rotary ring (28a) coaxial with a ...
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WO/2010/137052A1 |
A safety system for wind turbines and a wind turbine fitted with this safety system. The safety system comprises a propeller shaft adapted to be solidly connected to a wind turbine rotor, an adjustment shaft movable with respect to this ...
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WO/2010/086338A3 |
The invention relates to an engine for a vehicle having at least one rotor (3, 4), driven in rotation around a rotor axis (5) aligned in the direction of flight and having a plurality of rotor blades (6, 7). At least one geometric parame...
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WO/2010/135593A1 |
The torsional rigidity of a wind turbine blade affects the twist response of the blade induced by bending moments within the blade. By including regions having a lower modulus of rigidity than the remainder of the blade shell, the torsio...
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WO/2010/135597A1 |
The use of premium material in the construction of wind turbine blades may provide increases in blade efficiency and enable the use of thinner blades. By providing a spar cap having a section of premium material having a constant thickne...
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WO/2010/130893A1 |
The invention relates to a turbine engine, including at least one unducted propeller (22, 24) with variable pitch blades, said blades (34) being supported by substantially cylindrical plate (36) rotatably mounted about the axes (B) there...
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WO/2010/108576A3 |
The present invention provides a mechanical arrangement for an engine (10) having two propeller stages (23, 24), comprising: a first epicyclic gear (72) stage comprising a sun gear (60), a planet gear (62), a planet carrier (64) and an a...
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WO/2010/128239A2 |
The invention relates to a deicing device for propfan-type aircraft propeller blades, whereby the propulsion unit (1) comprises a turbine engine (8) rotating at least one rotor (3a) having a plurality of blades (4a) disposed around a rin...
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WO/2010/128240A2 |
The invention relates to a deicing device for propfan-type aircraft propeller blades, whereby the propulsion unit (1) comprises a turbine engine (8) rotating at least one rotor (3a) having a plurality of blades (4a) disposed around a rin...
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WO/2010/128241A2 |
The invention relates to an electric power generating device for a propfan-type aircraft propeller rotor, whereby the propulsion unit (1) comprises a turbine engine (8) rotating at least one rotor (3a) having a plurality of blades (4a) d...
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WO/2010/119298A1 |
A method of manufacturing a rotor blade (10) comprising the steps of; applying at least one optical fibre strain sensor (14) to the leading edge of the rotor blade body; and fitting an erosion shield (16) to the leading edge of the rotor...
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WO/2010/116080A1 |
The invention relates to a propeller (1) for an aircraft turbine engine including a plurality of blades (2) as well as a hub (4) having a plurality of recess openings (5) receiving the blade roots, each root (8) being pivotably mounted i...
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WO/2010/112453A1 |
The present invention relates to a rotating inlet cowl (30) for a turbine engine, having a rotational axis (34) and the front end of which is eccentric to said rotational axis (34). Further, a front cone (32) of the cowl is truncated by ...
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WO/2010/109085A1 |
The invention relates to a non-streamlined propeller having blades with a variable setting for a turbine engine, the blades of the propeller being rotatably mounted about the axes thereof in radial recesses (136) of a rotor element (124)...
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WO/2010/099730A1 |
An amphibious large aircraft without airstairs is provided. The fuselage (7) of the amphibious large aircraft is flat，and the shape of its bottom is rectangular. The longitudinal cross-section of the fuselage has a shape of the cross-s...
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WO/2010/097440A1 |
The device according to the invention includes a pair of counter-rotating propellers suitable for being modified by an actuator (31) located in a central recess of the shafts. The system for transporting energy to the actuator (31) inclu...
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WO/2010/093531A1 |
An air vehicle propulsion system incorporates an engine core (10) with a power shaft (24) to drive an outer blade row (12). The power shaft is extends through and is supported by a counter rotation transmission unit (28) which drives an ...
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WO/2010/086338A2 |
The invention relates to an engine for a vehicle having at least one rotor (3, 4), driven in rotation around a rotor axis (5) aligned in the direction of flight and having a plurality of rotor blades (6, 7). At least one geometric parame...
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WO/2010/085642A1 |
A system and method for erecting a vertical axis wind turbine are disclosed that uses an internal hinge.
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WO/2010/052042A3 |
An arrangement for the hydraulic adjustment of the propeller blades of an aircraft propeller (1) with the help of a hydraulic pump (5) having a hydraulic cylinder (3) which is acted upon by compressed oil comprises a pressure control val...
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WO/2010/028943A3 |
The invention relates to a control system for an aircraft propeller drive for controlling the power of a diesel engine (2) by means of a accelerator (7) and a control module (8), and for controlling the speed of the aircraft propeller (4...
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WO/2010/066791A1 |
The invention relates to a fan (1) for an aircraft turbine engine, including an inlet cone provided with a balancing system having a plurality of holes for housing bodies (42), and also including at least one balancing body (44) mounted ...
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WO/2010/057368A1 |
A cylindrical propeller includes paddles (3), a rotary steel cylinder (2), a fixed disk (6) and a rotary main shaft (4). The paddles (3) and the fixed disk (6) are mounted in the rotary steel cylinder (2). Stoppers (9) and teeth (10) are...
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WO/2010/057627A1 |
A method for defining the shape of an edge of an aerofoil comprises the following steps: obtaining a starting value for the thickness of the edge; defining a distance from the edge of the aerofoil in terms of the thickness; over the defi...
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WO/2010/059071A1 |
The invention relates to aircraft engineering, in particular to controllable pitch propeller hubs with automatic blade feathering mechanisms. A propeller hub barrel is seated on a blade root, is fastened to said root by means of a bolt a...
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WO/2010/052042A2 |
An arrangement for the hydraulic adjustment of the propeller blades of an aircraft propeller (1) with the help of a hydraulic pump (5) having a hydraulic cylinder (3) which is acted upon by compressed oil comprises a pressure control val...
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WO/2009/135468A3 |
The invention relates to a propeller device comprising a flow profile body that is associated with a propeller and a multiple eccentric cam arrangement that is functionally coupled to the flow profile body, said arrangement having two ec...
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WO/2010/037087A1 |
Provided is a turbine having a first impingement-type turbine portion and a second impingement-type turbine portion integrated into a rotatable disk, wherein the first impulse-type turbine portion has a plurality chutes and a high contac...
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WO/2010/033060A1 |
The present invention relates to an adjustable propeller arrangement comprising a drive shaft extending in a longitudinal direction and an adjustable propeller connected to the drive shaft. The adjustable propeller comp rises at least on...
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WO/2010/028943A2 |
The invention relates to a control system for an aircraft propeller drive for controlling the power of a diesel engine (2) by means of a accelerator (7) and a control module (8), and for controlling the speed of the aircraft propeller (4...
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