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Static variable pitch propeller

A variable-pitch propeller and static technology, which is applied to propellers, aircraft parts, and aircraft power devices, can solve problems such as poor consistency of blade angles, long time-consuming, and complex operation of pitch-variable structures, so as to improve operating efficiency. Improve the effect of regulating speed

Active Publication Date: 2018-04-13
AECC HUNAN AVIATION POWERPLANT RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The operation of the existing pitch control structure is complicated, time-consuming (the time of multiple blades is multiplied), and the angle consistency of the blades is poor (each blade needs to be adjusted separately, and the influence of human operation is large)

Method used

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  • Static variable pitch propeller
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Examples

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Embodiment Construction

[0035] Example embodiments will now be described more fully with reference to the accompanying drawings. Example embodiments may, however, be embodied in many forms and should not be construed as limited to the embodiments set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the concept of example embodiments to those skilled in the art. The same reference numerals in the drawings denote the same or similar structures, and thus their detailed descriptions will be omitted.

[0036] refer to Figure 1 to Figure 3 , according to a specific embodiment of the present invention, a static variable pitch propeller is provided, and the static variable pitch propeller may include a blade 101 , a propeller shaft and a propeller hub 102 . Wherein the paddle shaft may have a first end and a second end, and the first end of the paddle shaft may be fixed on the engine so as to be driven to rotate by the engine...

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Abstract

The invention discloses a static variable pitch propeller which comprises blades, a propeller shaft and a propeller hub. The blades are provided with blade roots which are provided with blade bevel gears. One end of the propeller shaft is fixedly connected with an engine to transmit power of the engine to the blades, and the propeller hub is fixed to the other end, away from the engine, of the propeller shaft. The propeller hub is internally provided with a linkage bevel gear engaged with the blade bevel gears, and the linkage bevel gear is rotatably connected to the propeller hub. The blade bevel gears are engaged with the linkage bevel gear, and thus when the angles of the blades are adjusted, the blade bevel gears can roll on the linkage bevel gear, that is, the linkage bevel gear rotates relative to the propeller hub to drive all the other blade bevel gears engaged with the linkage bevel gear to rotate by the same angle so that consistency adjustment of the angles of the blades canbe achieved; and furthermore, the adjusting speed of the propeller pitch is increased, that is, the operating efficiency is improved.

Description

technical field [0001] The present invention relates to a propeller, in particular to a static variable pitch propeller. Background technique [0002] In the design of the scaled propeller test piece, in order to fully understand the aerodynamic performance of the propeller blade, the installation angle of the propeller needs to be changed, so it is necessary to design a variable pitch structure to meet the requirements of different installation angles of the propeller. [0003] At present, in the design of the scaled propeller test piece, the half-type propeller hub (the front half propeller hub and the rear half propeller hub) is tightened by screws to reduce the gap with the blade handle and directly "seize" the propeller blade. When changing the installation angle of the propeller, you first need to loosen the screw, then adjust each propeller to the target angle with the angle gauge, and then tighten the screw to "seize" the propeller. [0004] The operation of the exi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C11/32B64C11/00B64D35/00
CPCB64C11/00B64C11/32B64D35/00
Inventor 周威王涛李家俊
Owner AECC HUNAN AVIATION POWERPLANT RES INST
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