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Improvements in directionally adjustable blade pivot radial locking for turbine fan hub

A pivoting part, turbine technology, applied in the direction of rotors, mechanical equipment, aircraft parts, etc., can solve problems such as contact wear of inner bushings, and achieve the effect of eliminating wear

Pending Publication Date: 2022-07-22
SAFRAN AIRCRAFT ENGINES SAS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0008] This radial retention of the pivot has the disadvantage
Due to the mounting tolerances of the retaining ring, when stopped, the entire pivot "drops" and consumes this residual mounting clearance, which creates contact wear on the inner bushing of the rolling bearing

Method used

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  • Improvements in directionally adjustable blade pivot radial locking for turbine fan hub
  • Improvements in directionally adjustable blade pivot radial locking for turbine fan hub
  • Improvements in directionally adjustable blade pivot radial locking for turbine fan hub

Examples

Experimental program
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Effect test

Embodiment Construction

[0041] The present invention is applicable to equipment equipped with at least one ducted fan or non-ducted fan, and whose fan blades (in the case of ducted fans) or propeller blades (in the case of non-ducted fans) are equipped with a pitch setting system any turbine.

[0042] The invention is particularly applicable to turbojets of the type comprising fans with very high bypass ratios (large fan diameters) and very low pressure ratios.

[0043] The architecture of these types of turbojets is well known to those skilled in the art and therefore will not be described in detail here. Briefly, these turbojets include a large diameter ducted fan provided with a system for changing the pitch setting of the fan blades.

[0044] Such a pitch setting changing system may, for example, include a lever arm (or eccentric) coupled to each vane pivot and pivotally actuated by a cylinder.

[0045] More specifically, the function of the pivot of each blade is to ensure that the fan blade r...

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Abstract

The invention relates to a directionally adjustable blade pivot (2) for a turbine fan hub, comprising: a stud (4) having means for holding (10) the root of a fan blade and coupling means for transmitting torque; a rolling bearing (14) for absorbing centrifugal forces, having an inner ring (16) mounted to abut against a radially outer portion of the stud in a laterally abutting manner; a radial retaining ring (24) for retaining the stud relative to the rolling bearing, the ring being housed in an annular groove (22) formed in the stud; a plurality of clamping members (26) each mounted in a laterally abutting manner against the retaining ring and in a radially abutting manner against the inner ring of the rolling bearing; and a clamping nut (28) which is screwed onto the external thread (30) of the stud so as to be in conical abutment with the clamping member such that the clamping member clamps the inner ring of the rolling bearing on the stud and the retaining ring in the groove.

Description

technical field [0001] The present invention relates to the general field of turbines equipped with one or two ducted or non-ducted fans, and more particularly to the control of the orientation of the fan blades of these turbines. [0002] A preferred field of application of the invention is turbojet engines, which include fans with very high bypass ratios (large fan diameters) and very low pressure ratios. Background technique [0003] The operability of turbojets with very high bypass ratios is ensured by introducing variability on the low pressure module of the turbojet, which is activated according to the flight phase to restore sufficient surge margin. [0004] It is known to ensure the variability by a system for changing the setting of the fan blades, which is integrated into the fan hub. This blade setting change system also allows to ensure the thrust reversal function, which for such turbojets is no longer performed by the nacelle of the engine. [0005] In addit...

Claims

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Application Information

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IPC IPC(8): B64C11/06F01D7/00F16B21/16F16C33/60F16C35/063F16B21/18F16C19/06F01D25/16
CPCB64C11/06F01D7/00F16C19/06F16C35/063F16C33/60F16B21/186F01D25/16F05D2260/30F05D2260/70
Inventor V·F·G·米利尔O·贝尔莫特
Owner SAFRAN AIRCRAFT ENGINES SAS
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