SIMPLIFIED SYSTEM OF PROPELLER SCREW BLADE PITCH CONTROL IN AIRCRAFT TURBOSHAFT ENGINE Russian patent published in 2013 - IPC F01D7/00 F04D29/36 

FIELD: engines and pumps.

SUBSTANCE: system of propeller screw blade pitch control in a turboshaft engine comprises the first and second circular guides, an activating element, and also the first and second blocking elements. The first circular guide provides for installation of an angle of attack of the specified blade and has the first and second seats that are distant from each other along the circumference. Each seat is formed with the first and second thrust surfaces. The second circular guide is made concentrically with the first guide and is located outside relative to it. The second thrust surface of the first seat and the first thrust surface of the second seat are aligned towards the second guide. The activating element is placed between the first and second guides and has the first and second thrust surfaces. The first blocking element is placed in the first seat opposite to the specified second thrust surface of the activating element. The second blocking element is placed in the second seat opposite to the first thrust surface of the activating element. The first and second blocking elements are made as capable of taking normal centralised position, and also unblocking position in the first and second circular directions. During control of the above system of propeller screw blade pitch control, the activating torque is applied to the activating element. Other inventions of the group relate to a propeller screw of a turboshaft engine comprising the above system of blade pitch control, and also to an aircraft engine comprising such propeller screw.

EFFECT: inventions make it possible to increase reliability of a system of blade pitch control, to reduce its weight.

10 cl, 7 dwg