Variable pitch vane control ring bush retention foil and turbojet containing same
AssigneeSafran Aircraft Engines
InventorsOlivier BAZOT, Jérémy Philippe Pierre EDYNAK
Life of this patent
Estimating the term…
Abstract
A flexible metal foil can be fixed on the inside part of a variable pitch vane control ring of a turbojet compressor, so as to close all through holes in which lever pins and their surrounding bushes are housed. As a result, the foil can retain the shank of the bush if the bush breaks. The use of such foil does not impose the development of a new model of control ring and its impact on the mass is small enough so that it does not affect engine performances. Therefore it avoids problems related to the breakage of bushes without having to make major changes to the existing system.
Claims9
A foil made from a flexible metal material and to be fixed to an inside surface of a vane control ring with variable pitch for a turbojet, said control ring comprising a plurality of through holes each with an internal radial opening on a side of the inside surface of the control ring and an external radial opening on a side of an outside surface of the control ring, in each of which a bush can be housed to hold a pin of a control lever of one of the vanes, through the external radial opening of the hole, the foil having a length along a longitudinal direction and a width along a direction orthogonal to said longitudinal direction that are adapted to close the internal radial opening of at least one through hole in the control ring, said foil length being longer than the developed length of a determined angular sector of the control ring in which at least one pad of the control ring is located, at the angular sector at which the foil is to be fixed, and in which the foil contains an adapted hole to allow a pad support to pass through connecting the pad to the control ring, and wherein the foil adopts a determined shape in a section plane orthogonal to said longitudinal direction by which the foil can be fixed by click fitting onto the control ring at its inner surface.
A control assembly for variable pitch vanes of a turbojet comprising a variable pitch vane control ring, said control ring having an inside surface and an outside surface and having:
- at least one pad located in a determined angular sector of the control ring, at least at its internal surface;
- and,
- a plurality of through holes each with an internal radial opening on a side of the inside surface of the control ring and an external radial opening on a side of an outside surface of the control ring, in each of which a bush can be housed to hold a pin of a control lever of one of the vanes, through the external radial opening of the hole,
- said control assembly comprises comprising a foil made of a flexible material fixed to the inside surface of the control ring, said foil having:
- a length along a longitudinal direction and a width along a direction orthogonal to said longitudinal direction that are adapted to close the internal radial opening of at least one through hole in the control ring, said foil length being longer than the developed length of a determined angular sector of the control ring in which at least one pad of the control ring is located, at the angular sector at which the foil will be fixed;
- a determined shape in a section plane orthogonal to the longitudinal direction by which it can be fixed by click fitting onto the control ring at its inner surface, and,
- a suitable hole through which a support of said pad can pass;
- to connect said pad to the control ring.
Dependencies are inferred from the claim text.