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Propeller blade arrangement

A technology of propellers and blades, which is applied in the field of propeller design and optimization of the centrifugal recovery torque of the blades, and can solve the problems of harmful blades

Pending Publication Date: 2021-10-12
拉季埃-菲雅克有限责任公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0013] While this works well under operating conditions where the blades are stacked to minimize the total bending moment, this design can be detrimental to said blades under other flight conditions

Method used

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  • Propeller blade arrangement
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Examples

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Embodiment Construction

[0024] The described embodiments are examples only. The scope of the present disclosure is limited only by the claims.

[0025] first reference Figure 1A and Figure 1B , the existing arrangement for generating the centrifugal restoring moment of the blade will be briefly explained.

[0026] The blade 1 is shown with a centerline C about which the blade rotates. In the example shown, it has been calculated that, in forward thrust operation in 'cruise mode', the engine torque load E and the external thrust load A will combine to produce a resulting orientation on blade hold in the fourth quadrant The aerodynamic bending moment R. In order to generate a restoring centrifugal bending moment that will counteract the load on the blade, the blade will be constructed or stacked such that its center of gravity CG is offset relative to its centerline C. will determine the azimuth position of the center of gravity such that if Figure 1B As shown, the centrifugal bending moment wi...

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PUM

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Abstract

A propeller blade arrangement comprising a propeller blade attached to and rotatable with a hub, via a retention bearing, the blade being rotatable about a center line of the blade, the retention bearing configured to tilt the blade such that its center line is tilted with respect to the hub.

Description

technical field [0001] The present disclosure relates to propeller design for aircraft and optimization of blade centrifugal restoring torque. Background technique [0002] A propeller has many blades mounted around the hub. The hub and blade set rotate around the axis of the hub. Furthermore, each blade is mounted to the hub by a retaining bearing which allows the blade itself to rotate about an axis of rotation perpendicular to the axis of the hub. This allows the pitch of the blades to be varied to accommodate different flight conditions and output power requirements. [0003] Depending on flight conditions, the propellers rotate at different speeds and in either forward or reverse operating modes. During climbs, greater power and forward thrust are required. During the cruise phase, forward thrust moves the aircraft forward. During landing, the propellers operate in reverse thrust mode to slow the aircraft down. [0004] Engine torque applied to the blades via the ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C11/16
CPCB64C11/16B64C11/04B64C11/20B64C11/06F01D5/02F01D25/16F05D2240/50B64C11/343
Inventor B·塞米内尔
Owner 拉季埃-菲雅克有限责任公司