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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/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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WO/2010/007146A1 |
The invention relates to a device for attaching a blade that includes a ferrule (28) mounted about an outer collar (23) of the pivot (15) of the blade (27), and capable of rotating by a sufficient angle so that cleats (30, 31) can close ...
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WO/2009/154736A1 |
A banded turbine configuration has an integral outer band support structure capable of providing two point simple support for a multiplicity of blades. A large scale vertical array has a set of twelve 23m-diameter banded turbines with up...
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WO/2009/142792A2 |
A propeller blade retention system and method of manufacture are disclosed. Because of the design, a truly integral hub is able to house a set of variable pitch blades. Each hub socket establishes a substantially cylindrical interface wi...
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WO/2009/135468A2 |
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/2009/131479A1 |
The inventive gyroplane comprises a fuselage (1) with a cockpit and a folding strut mounted on the fuselage, a rotor head (3) which is provided with an adjustable torsional hub (16) and an adjustable pith pusher propeller (5). In order t...
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WO/2009/126469A1 |
A flying vehicle in accordance to an embodiment of the present invention includes a propeller control mechanism for flying the vehicle. The propeller control mechanism includes a propeller having a center shaft for connecting to the driv...
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WO/2009/126905A1 |
An aircraft is equipped with hingeless rotors on tilting nacelles, and the tilt angles of the nacelles are controlled using either or both of an actuator and a mast moment generated by a hingeless rotor. An aircraft with two or more roto...
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WO/2009/115593A1 |
The invention relates to a contra-rotating propeller system (1) for the turbine engine of an aircraft that comprises first and second propellers (6, 8) each including a control system (26, 56) for setting the blades, the latter including...
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WO/2009/111956A1 |
An axial flow fan comprises a hub (2) and a plurality of blades(1) extending radially outwardly from the hub(2),a single-side arc brim(5) is provided at the tip each blade. The axial flow fan characterizes in that the angle or the averag...
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WO/2009/108885A2 |
A method for making a propeller product is disclosed. The propeller is formed using polyurethane cores adhered to a laminate hub to form a core assembly. An encapsulating structural laminate skin is then formed on the core assembly using...
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WO/2009/102227A2 |
The invention refers to raise theoretical some complex movements which generated well determined direction and sense accelerations, resulting an acceleration direction principle, and on the base of the principle it describes an accelerat...
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WO/2009/097846A2 |
Thrust or carrying force generates a tubular fluid jet, which is created in that a fluid after radial acceleration in a disk-shaped driven rotor (11) mixes with another fluid (28, 32) in the peripherally disposed annular chamber (20) bef...
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WO/2009/093937A1 |
A device for changing a pitch of a blade of an impeller/propeller is disclosed. It comprises at least one linear actuator. A first bearing is mounted to a non rotary mechanical element with the first portion, and a second bearing is moun...
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WO/2009/094602A1 |
A wind energy to electrical power conversion device provides a protected multiple turbine mechanism axially aligned to convert kinetic energy of air movement, i.e. wind (or other moving fluid such as water), into rotational mechanical po...
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WO/2009/091782A1 |
A check valve turbine assembly includes an assembly base, a vertical member rotatable relative to the base, and a sail assembly attached to the vertical member, wherein the sail assembly has a frame with parallel horizontal airfoil membe...
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WO/2009/083987A1 |
The present invention relates to enhancing performance of fans and propellers using outsized Gurney flaps. Specifically, the current invention proposes the application of 'outsized Gurney flaps' (OGFs) to the trailing-edges of fan blades...
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WO/2009/082396A1 |
A locknut which defines a multiple of inner apertures about an inner diameter and a multiple of outer apertures about an outer diameter.
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WO/2009/082581A2 |
A main rotor blade assembly includes a tip spar which defines a tip spar non-straight form, an upper blade skin which defines an upper blade skin non-straight form adjacent to the tip spar non-straight form and a lower blade skin which d...
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WO/2009/079161A2 |
A main rotor blade assembly having a blade skin bonded to a main spar and a tip spar.
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WO/2009/079162A2 |
A main rotor blade assembly includes a tip spar which defines a tip spar non-straight form, an upper blade skin which defines an upper blade skin non-straight form adjacent to the tip spar non-straight form and a lower blade skin which d...
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WO/2009/078871A1 |
A helicopter rotor blade includes a structural composite skin defining a cavity therein; a composite spar disposed within the cavity and adhesively bonded to the skin, a portion of the spar exhibiting a C-shape in cross section; and a fo...
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WO/2009/074669A1 |
The invention relates to a covering (22) of a fuselage (1) for aircraft comprising propeller engines (3) comprising an opening (12) which is surrounded by a structural frame formed by the ribs (5) and the stringers (6) of the aircraft ar...
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WO/2009/073191A1 |
A rotor assembly for a wind turbine including at least one blade adapted to automatically adjust its shape as a function of rotational speed to create an efficient fluid dynamic profile over a wide range of wind conditions and rotational...
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WO/2009/058357A1 |
A control system for a turbine blade, including: an operational control element for generating and outputting an operational control signal, the operational control signal for non¬ emergency operation of a motor for controlling pitch of...
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WO/2009/038923A1 |
A fan blade comprises an airfoil having an upper surface with region that has a generally elliptical curvature. In some examples, the lower surface has a convex region and a concave region. The curvature of the concave region corresponds...
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WO/2009/032195A1 |
Composite structures with internal cavities are constructed with relatively stiff walls that can support additional composite laminate layers, creating a self-tooling structure. The structure is subsequently simulcured, preferably in com...
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WO/2009/013323A2 |
The invention relates to an aerodynamic profile (400) which is provided on a side to be directed away from an incident flow (S) with a rear edge region (410) forming a rear edge (412). To make it possible for the rear edge (412) to combi...
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WO/2009/011609A1 |
The inventive idling rotor comprises two axial blades disposed on the external side of a split cup-shaped rotor hub provided with a centrifugal blower which is arranged therein and the blades of which rotate oppositely to rotation of the...
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WO/2009/010618A1 |
Method for the manufacture of wind vanes, consisting in: formation of a single foam core (2), with numerical control machines, application of reinforcing layers (3) pre-impregnateted in resin (4), curing of the layers (3) as part of the ...
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WO/2008/147451A2 |
A translational thrust system for a high speed rotary-wing aircraft includes a propeller system driven by a propeller gearbox (42), a hydraulic system (44), and a mechanical-hydraulic control system (48). The mechanical-hydraulic control...
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WO/2008/147402A2 |
Methods and apparatus are provided for making a rotor blade spar from composite material wherein a multi-component mandrel is used to form the composite spar. The mandrel (10) is made using a number of components (38, 44, 50, 56, 62, 64)...
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WO/2008/147376A1 |
Rotor blades are pre-bent in at least one of a flap direction and a lag direction, wherein the pre-bent portion comprises at least 20-60% of the length of the blade. Preferred methods include analyzing the rotor dynamic behavior using co...
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WO/2008/142498A1 |
A variable-diameter rotor comprises a hub with a shaft and rotor blades mounted on the hub, wherein each one of the rotor blades comprises a radially internal blade part (6), which is radially stationary, and a radially external blade pa...
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WO/2008/144228A2 |
A flight control system and method which determines an expected power required data in response to a flight control command of the at least one model following control law and utilizes the expected power required data to perform at least...
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WO2008079553B1 |
Pairs of oscillating wind paddles are mounted in the lee of a wind turbine of the lift type An oscillating wind paddle assembly has upper and lower pairs of paddles, each pair moving between a first position at substantially right angles...
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WO/2008/127362A2 |
A system (10) for balancing an aircraft propeller (12) system receives a vibration signal from the aircraft propeller system and determines whether the vibration signal indicates a transient vibration condition. If it is determined that ...
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WO/2008/118637A2 |
A governor configured, to regulate the rotational velocity of one or more rotors (14) of an aircraft (12) by adjusting a collective blade pitch of the one or more rotors. In one embodiment, the governor (30) comprises a control monitor (...
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WO/2008/105704A2 |
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/2008/096124A2 |
A method of operating a counter-rotating propeller engine having front and rear propellers. The engine is operated during at least a take-off, a climb, a cruise and an approach phase; during the cruise phase the engine operates with a ge...
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WO/2008/087443A1 |
A composite blade assembly is disclosed including a composite blade or aerofoil (2) and a root member (1). One end of the blade (2) extends along the root member (1) and is secured therewith. The blade (2) includes a plurality of layers ...
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WO/2008/081098A1 |
The invention relates to a rear tail assembly (1) for an aircraft, including a fuselage (3), a wing (2) and at least one propulsion engine (5, 5a, 5b) attached in the rear portion of the fuselage located behind the wing (2) along the X l...
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WO/2008/065647A1 |
There is provided a self torque-balancing differential mechanism (2), including two coaxial counter- rotating wheels (4, 6), rotatable about a central shaft (24), mutually reacting and balancing a torque of a motor drive (20) interacting...
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WO/2008/053230A1 |
According to one embodiment of the present invention, there is provided a propeller blade assembly comprising a hub (1) with a plurality of recesses (15) and a plurality of propeller blades (3) of composite construction having one end se...
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