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Ring for controlling a stage of variable-setting vanes for a turbine engine

a technology of variable pitch and control ring, which is applied in the direction of machines/engines, mechanical apparatus, liquid fuel engines, etc., can solve the problems of reducing the service life of the pad, destroying the threaded connection, and affecting the accuracy of the pitch, so as to limit the risk of damaging the ring and limit the direct transmission of torque

Inactive Publication Date: 2018-09-20
SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The invention is a device that fixes a bearing member or its support to a casing. It uses a bushing that can be tightly screwed or loosely positioned. This technology limits the risk of damaging the bushing by reducing the direct transmission of torque to it. Its main advantages are the immobilization and precise positioning of the bearing member or its support in relation to the casing.

Problems solved by technology

However, it has been noted, particularly in the case of single-cylinder actuation means, that, depending on the opening and closing ranges of the variable-pitch vanes, the cold clearances cause off-centring of the control ring in relation to the casing, which negatively affects the precision of the pitch.
During operation, the presence of this clearance causes, under the action of the surrounding vibrations, a relative displacement between the parts, leading to the destruction of the threaded connection.
Consequently, the pad function is no longer provided.
Furthermore, this wear directly affects the pitch angle of the vanes during operation, which can affect the correct operation of the engine (surging in the event of a significant number of worn pads on the same stage).

Method used

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Examples

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Embodiment Construction

[0033]FIG. 1 is a schematic axial sectional view of part of a high-pressure compressor 10 of a turbine engine, in particular an aircraft turbine engine, having a plurality of stages, each stage comprising an annular row of movable vanes 12 supported by the rotor (not shown) of the turbine engine and an annular row of fixed vanes 14 forming rectifiers supported by a casing 16 of the stator of the turbine engine, the angular orientation of the vanes 14 being adjustable in order to optimise the gas flow in the compressor 10.

[0034]Each vane 14 comprises a blade 18 and a radially outer cylindrical pivot 20 connected, by a disc or “plate”22 extending perpendicularly to the axis 24 of the vane, in a corresponding housing 26 of the casing 16. The radially inner surface 28 of the disc is aligned with the inner wall 30 of the casing so as not to oppose the gas flow.

[0035]The cylindrical pivot 20 of each vane 14 extends inside a radial cylindrical chamber 32 of the casing 16 and its radially o...

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PUM

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Abstract

A control ring for a stage of variable-pitch vanes for a turbine engine includes at least one member for bearing on a casing and means for fixing the member. The member includes a bushing with an axial bore for the passage of the member or an element for supporting the member. A through-slot opens into the bore and allows for substantial radial deformation of the bushing. The member further include an outer thread for screwing the bushing into a complementary thread of a hole in the body, thereby deforming the bushing. The member or support can be mounted and moved inside the bore, to a second position, in which the bushing is radially constrained and is tightly mounted on the member or support, which is thus immobilized in relation to the bushing.

Description

TECHNICAL FIELD[0001]The present invention relates to a control ring for a stage of variable-pitch vanes for a turbine engine.PRIOR ART[0002]The prior art includes in particular EP-A2-1 696 134, EP-A1-1 820 942, FR-A1-2 882 577 and EP-A1-0 375 593.[0003]A stage of this type comprises an annular row of variable-pitch stator vanes (also referred to as VSV, an acronym for Variable Stator Vanes) that are supported by an outer annular casing, generally of a compressor of the turbine engine. Each vane comprises a blade, which is connected at its radially outer end, by a plate having a substantially circular contour, to a radial cylindrical pivot that defines the axis of rotation of the vane and is rotationally guided in a corresponding hole in the outer casing. The radially inner end of the blade of each vane generally comprises a second cylindrical pivot extending along the axis of rotation of the vane and rotationally guided in a hole in an inner casing of the compressor.[0004]The radia...

Claims

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Application Information

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Patent Type & Authority Applications(United States)
IPC IPC(8): F01D17/16F04D29/56
CPCF01D17/162F04D29/563F05D2230/644F05D2250/37F05D2260/30F05D2260/31F05D2250/292F05D2240/128F16B5/0233Y02T50/60F01D17/16F01D25/28F01D17/14F16B5/0258
Inventor EDYNAK, JÉRÉMYBAZOT, OLIVIER
Owner SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A
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