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WO/2011/113821A1 |
Variable pitch mechanism for the blades of a fan (16) of a system of contrarotary fans for a turbomachine, each blade (16a) being able to move about a radial axis (Y), said mechanism comprising a linear actuator, means (56) for convertin...
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WO/2011/107691A1 |
The invention relates to a device for controlling the orientation of fan blades of a turboprop engine comprising at least one set (24a, 24b) of adjustable-orientation fan blades rotatably secured to a rotary ring (28a, 28b) mechanically ...
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WO/2011/098712A1 |
The invention relates to an assembly, in a turbine machine, for controlling a plurality of toothed pivoting blades (30), said assembly comprising an actuation gear (40) for controlling the position of the vanes. Racks (50), mounted on th...
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WO/2011/098736A2 |
The invention relates to a turboprop provided with a blade-positioning device. The invention relates in particular to a turboprop (1) comprising: a stationary nacelle (2), a rotary nacelle (3a) comprising a plurality of blade (5) roots (...
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WO/2011/087411A1 |
The invention regards an article comprising an outer surface (11), which serves as an aerodynamic surface when the article (3, 3', 16, 27, 53) is subjected for an air stream (a), the article (3, 3', 16, 27, 53) comprises a resin matrix m...
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WO/2011/087479A2 |
A fluid turbine comprising a rotor, having an axis of rotation, comprising at least two rotor blades disposed at a radius from the axis of rotation, each rotor blade having a pitch axis and a variable pitch angle. The fluid turbine compr...
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WO/2011/083137A1 |
The invention relates to a contra-rotating propeller system for an aircraft turbine engine, including a free power turbine including a first rotor and a second rotor contra-rotating relative to said first rotor, a first contra-rotating p...
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WO/2011/083250A1 |
The invention relates to an aircraft propeller blade (10) which includes a structure having an aerodynamic profile (20), characterised in that the structure having an aerodynamic profile includes at least one fibrous reinforcement obtain...
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WO/2011/084246A1 |
A method and apparatus for controlling a propeller of a contra-rotation open fan (CROF) engine of an aircraft. A diameter of the propeller is set to be at a first diameter during at least a portion of a first flight condition of the airc...
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WO/2011/082239A1 |
One embodiment of the present invention is a unique composite gas turbine engine component. In one form, the composite component is an airfoil. Another embodiment is a unique method for manufacturing a composite gas turbine engine compon...
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WO/2011/081577A1 |
The invention concerns an air propeller arrangement (10, 30, 50) for propulsion of a fixed-wing aircraft (8), said arrangement comprising a first air propeller (11, 31, 51) that comprises a first hub member (15, 35, 55) and at least a fi...
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WO/2011/082237A1 |
A turbomachinery blade for a gas turbine engine is provided and includes an airfoil extending between a leading edge and a trailing edge. In one embodiment the turbomachinery blade is a compressor blade. The blade can include a platform ...
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WO/2011/077454A1 |
A rotor blade for a fluid turbine is disclosed. The rotor blade includes a flange section configured to connect the rotor blade to a rotor hub; and an airfoil section extending outward from the flange section. The flange section is compr...
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WO/2011/069981A1 |
The invention relates to a polygonal ring (17) for supporting the blades of the propeller, which consists of two annular end sides (20, 21) spaced apart parallel to one another and between which rings (23) having radial cylindrical reces...
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WO/2011/066708A1 |
An aerobat toy, which includes propellers (30), a fuselage (50) and an undercarriage (70), is provided. The propellers (30) have a first propeller (310) set on the top of the fuselage (50) and a second propeller (320) set between the fus...
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WO/2011/064419A1 |
Concave blade for wind turbine, formed by a body (1) determined by a surface that defines a concavity (3), with a flattened part (2) at one extremity, to be attached, using said flattened part (2), in a radial position to a supporting disk.
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WO/2011/053805A1 |
A Real-time Allocation Flight Management System and method, which defines specific roles functions for crew during the implementation of the flight plan. The flight control system requires crew input during pre-programmed way points duri...
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WO/2011/048081A1 |
The present invention relates to a system for varying the angle of attack of the blades of an aircraft turbine engine propeller, including a brushless axial flow engine (10) comprising a stator (10a) provided with windings (12), as well ...
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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/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/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/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/2010/135593A1 |
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/2010/128239A2 |
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/2010/066791A1 |
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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