US 9,038,940 B1Granted

Rotor configuration for reaction drive rotor system

AssigneeGroen Brothers Aviation, Inc.

InventorJacob Johannes van der Westhuizen

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Abstract

A rotor system is disclosed for a reactive drive rotary wing aircraft. Apparatus and methods are disclosed for maintaining the rigidity of the rotor and eliminating play between flight controls and the rotor by mounting swashplate actuators to a flange rigidly secured to the mast. Methods are disclosed for modulating the temperature of oil pumped over one or more of the mast bearing, swashplate bearing, and spindle bearing. The temperature of air passively or actively drawn through rotor may also be modulated to maintain bearing temperature within a predetermined range. Structures for reducing pressure losses and drag on components due to air flow through the rotor are also disclosed. A rotor facilitating thermal management by oil and air flow is also disclosed. Surfaces interfacing between the swashplate and the mast and between control rods and the swashplate or pitch horn may bear a solid lubricant layer.

Claims12

Dependent claims

A rotor system comprising:

a mast mounted to an airframe and defining a rotor axis;
a hub rotatably mounted to the mast and rotatable with respect to the mast only about the rotor axis, the hub defining a hub cavity;
and
a plurality of blades mounted to the hub, blade of the plurality of blades defining a duct in fluid communication with the hub cavity, the blade duct being defined by a blade spar of the each blade, the blade spar extending through the hub and into the hub cavity and having a pitch horn secured thereto and positioned within the hub cavity;
a swashplate encircling the mast;
a plurality actuators coupled to the swashplate and adjusting the position of the swashplate;
and
a plurality of pitch control rods coupling the swashplate to the pitch horns of the plurality of blades;
a shroud encircling the mast and rotatably engaging the hub, the shroud defining an air channel in fluid communication with the cavity, the swashplate being located within the air channel and the plurality of pitch control rods extend into the hub cavity;
and
a compressed air source in fluid communication with the air channel.

8 more elements

Dependencies are inferred from the claim text.

Facts

Application: 13/373,433Filed 14 Nov 2011 · us provisional application
Priority: 16 May 2011
Granted: 26 May 2015
Term ends: Not estimatedThe source records don’t support an estimate.

Classification4 codes

B64C 27/605
Mechanical: including swash plate, spider or cam mechanisms
B64C 27/025
Rotor or rotor head construction: rotor drives, in particular for taking off; Combination of autorotation rotors and driven rotors
B64C 27/18
Drive of rotors by means, e.g. propellers, mounted on rotor blades: the means being jet-reaction apparatus
B64C
Aeroplanes

Family

Application61/519,055Us provisional application · filed 16 May 2011
US 9,038,940 B1This patent

From the US filing history. Foreign family members aren’t listed.

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