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Blade with adaptive twist and rotor with such a blade

一种自适应、桨叶的技术，应用在旋翼机、与风向一致的的风力发动机、应用等方向，能够解决桨叶重量增大等问题

Active Publication Date: 2011-08-31
EUROCOPTER
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This increases the weight of the blade

Method used

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  • Blade with adaptive twist and rotor with such a blade
  • Blade with adaptive twist and rotor with such a blade
  • Blade with adaptive twist and rotor with such a blade

Examples

Experimental program
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Embodiment Construction

[0085] Elements appearing in more than one figure are provided with the same reference numerals in each figure.

[0086] The three mutually orthogonal directions are labeled X, Y, and Z, which can be found in figure 1 and 2 see in.

[0087] The direction X is called the transverse direction. The term "width" refers to the transverse dimension of the blade along said transverse direction X.

[0088] The other direction Y is called the reference direction, ie the case where the blade extends along said direction Y. Both the so-called "longitudinal" direction and the direction of the axis about which the pitch of the blade changes are parallel to this reference direction.

[0089] Finally, the third direction Z is vertical and corresponds to the height dimension of the described structure. The term "thickness" then refers to the vertical dimension along this vertical direction.

[0090] figure 1 is a schematic diagram of the blade 1 of the present invention. The blade 1...

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PUM

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Abstract

A rotor blade (1) with adaptive twisting, the blade being provided with an outer covering (2) extending along a pitch variation axis (AY) from a first end zone (3) to a second end zone (4), the outer covering (2) defining an internal cavity (8). The blade includes a strip (10) extending inside said cavity (8) along said pitch variation axis (AY), said strip (10) comprising a composite material that is anisotropic so as to be suitable for twisting under the effect of centrifugal forces (F) directed parallel to said pitch variation axis (AY) when the blade (1) is in rotation, said strip (10) being fastened to said outer covering (2) via first and second fastener means (11, 12) in order to be capable of twisting said outer covering (2).

Description

[0001] priority claim [0002] This application claims priority from French Patent Application No. 1000809, filed February 26, 2010, the entire content of which is hereby incorporated by reference. technical field [0003] The present invention relates to adaptively twisting blades, to rotors provided with such blades, and more particularly, but not exclusively, to blades of rotorcraft lifting rotors. Background technique [0004] Typically, the blades extend longitudinally from a first end fixed to the rotor hub towards a second end called the free end. It is understood that the blades extend radially from the first end to the second end with respect to the rotor. [0005] Furthermore, the blade extends transversely from the leading edge to the trailing edge. The blade comprises in particular an outer covering provided on its suction side with a first skin and on its pressure side with a second skin, the first skin being simply referred to as "suction side skin ”, while...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C11/16B64C11/20
CPCB64C27/33Y02E10/721F05B2240/301B64C27/54B29L2031/085F03D1/0675Y02E10/72Y02P70/50B64C27/473B64C27/35B64C11/30B29C70/10
Inventor L·比安基R·昆卡M·格兰D·瑞维伦
Owner EUROCOPTER
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