Hub for radial housing of a helical ring of a turbomachine with variable-pitch blades and assembly comprising such a hub
a turbomachine and variable-pitch technology, which is applied in the direction of rotors, marine propulsion, vessel construction, etc., can solve the problems of large stress on external bearing rings b>15/b>, complex machining operations, and high cost production of polygonal rings
Active Publication Date: 2014-01-02
SAFRAN AIRCRAFT ENGINES
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AI Technical Summary
Benefits of technology
The present invention is related to a helical ring structure for a turbomachine with variable-pitch blades. The technical effects of the invention include simplifying the manufacturing process and reducing the risk of machining discards, as well as minimizing deformation of bearing pieces and limiting wear on these pieces. The invention proposes a hub for a radial housing of a helical ring, which is separate from the annular body and can be easily connected to the edges of the housing. This hub has a machined area adapted to receive the bearing rings of a cylindrical blade support crown. The invention also relates to an assembly for helical ring of a turbomachine with variable-pitch blades, which includes a plurality of hubs.
Problems solved by technology
These machining operations are complex.
They have to be repeated for each of the housings of the ring, and this increases the risk of discards and therefore the cost production of the polygonal ring.
Also, in operation, the external bearing rings 15 are considerably stressed and wear quickly.
As these deformations are different, they cause ovalisation of these rings, which is at the origin of friction and rapid wear for the rings.
Method used
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Embodiment Construction
[0029]The assembly forming a helical ring illustrated in FIGS. 4a and 4b comprises a polygonal ring body 20 and a plurality of radial cylindrical housings 21, just one of these housings in this case having been shown in the figures.
[0030]It also comprises a plurality of hubs 22 which are pieces separate from the polygonal ring body 20, and which are received in the cylindrical radial housings 21.
[0031]On their inner surface these hubs 22 comprise machined areas 23 for mounting the bearing rings of rotating crown bearings identical to the crowns 12 of FIG. 3.
[0032]The machined areas 23 are for example annular grooving dimensioned to receive coaxial rings of bearing rings. They can more generally be of any type conventionally used to enable cylindrical housings to receive rotating crowns intended to receive helical blade plates, as well as the means for centring and guiding these crowns in rotation in their housing. An example of assembly in this sense could for example be found in ap...
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The present invention relates to a helical ring (100) comprising a polygonal body (110) and a plurality of cylindrical radial housings (150) arranged in said body, each housing (150) having a surface adapted to receive support means of a blade of a helix, characterised in that the surface of each housing (150) is arranged on a radially internal surface (201) of a corresponding hub (200), each hub (200) being a separate piece attached to the body (110) of the ring, intended to be received in a radial housing (21) of the latter, and in that it also comprises two projecting pins (32) relative to its external surface to be fastened to the edges of a housing of the annular body, the two projecting pins forming a centring axis.The invention also relates to a manufacturing process of such a ring, a helix and a turbomachine fitted with such a ring.
Description
FIELD OF THE INVENTION[0001]The present invention relates to the field of helical rings of a turbomachine with variable-pitch blades.[0002]It can be applied especially advantageously in the case of open-rotor helix (or “unducted fan”).PRIOR ART[0003]FIG. 1 illustrates a turbomachine 1 of the open-rotor helix type. From upstream to downstream, in the direction of flow of air flow as shown by arrows F, it comprises a compressor 2, an annular combustion chamber 3, a high-pressure turbine (not shown), and two low-pressure turbines 8 which are counter-rotating.[0004]Each low-pressure turbine 8 is connected to an external helix 9, both helices being arranged coaxially behind each other, around the longitudinal axis A of the turbomachine 1 and each comprising a plurality of blades P distributed uniformly around said axis.[0005]For this purpose, each conventionally comprises (FIG. 2) an annular rotor body 10, generally polygonal, which is centred on the longitudinal axis of the turbomachine...
Claims
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IPC IPC(8): F01D7/00
CPCF01D7/00F01D5/3023F02C3/067F02C6/206F05D2220/324F05D2220/325F05D2260/33F05D2260/79
Inventor PERDRIGEON, CHRISTOPHEJABLONSKI, LAURENTJOLY, PHILIPPE GERARD EDMOND
Owner SAFRAN AIRCRAFT ENGINES
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