EP1553262A1 - Distribution support for service conduit in a turbofan engine. - Google Patents

Abstract

The present invention relates to a turbofan engine comprising an outer casing (11) supported by arms (12), an inner casing (34) to the casing (11) and servitudes (38). In the axis of an arm (12) is provided, on the inner casing (34), a service distribution support (35) having, on the outer side of the inner casing (34), a first sole for receiving easements (36). Thanks to the invention, the longitudinal size associated with the passage of easements is reduced. <IMAGE>

Description

The invention relates to a turbofan engine.

A turbojet engine comprises, functionally, a inlet handle, a blower, a compressor, a chamber of combustion, a turbine and an exhaust nozzle. These various elements are contained in crankcases.

The turbojet engine further comprises, around these housings, a crankcase internal secondary flow, in the form of a hull to contain, on its outer surface, the secondary air flow. The secondary air flow corresponds to the air driven by the fan does not not penetrating into the compressor. This hull includes means opening in two half-shells, in order to access the heart of the turbojet. By heart of the turbojet, we mean the elements of the turbojet engine located in the enclosure defined by the inner casing of the flow secondary.

Some fluids necessary for the operation of the turbojet, such as fuel and oil, must be brought from outside the turbojet to his heart. These fluids serve in particular to feed the fuel combustion chamber, the various elements of the engine in lubricating oil, various actuating cylinders of discharge valves, Variable compressor timing, piloting the clearance of the turbine housings high pressure and low pressure, etc.

The routing of the fluids is carried out by pipelines commonly called easements. The invention is particularly the passage of easements along the support arms of a crankcase turbojet, says intermediate.

FIG. 1 represents a partial view of a turbojet engine 1 of the art prior. The latter comprises, downstream of the retention casing of the blades of blower, the outer shell 2 of a housing, said intermediate, which is traditionally fixed the front suspension of the turbojet engine to an airplane. The intermediate casing also comprises radial arms 3. At the right of its outer shell 2, is arranged an inner shell 4, this inner shell 4 comprising a bearing shoulder 5 of the internal casing of the secondary flow, not shown.

Some easements 6 must be brought from the outside of the intermediate casing, towards the heart of the turbojet engine 1. This routing is generally done along an arm 3 of the intermediate casing, the easements 6 opening into the heart of the turbojet 1 at the level of the inner ferrule 4.

The turbojet 1 presented is intended to be mounted on an airplane whose ground clearance is quite low. His nacelle is flattened in his lower portion and swollen on the sides. For security reasons, servitudes must not pass through the lower part of turbojet 1, case of friction on the ground of the latter. They are therefore transported on along an arm 3 of the intermediate casing spaced apart from the plane of symmetry - overall vertical of the turbojet engine 1.

The easements 6 pass through the outer shell 2 of the housing intermediate and are contained between the outer shell 2 and the inner ferrule 4, in an arm 7, ensuring their protection and guiding the air flow secondary. The easements 6 are fixed at the inner ferrule 4, on a sheet 8, by nuts on each side of the sheet 8.

These easements 6 are quite numerous, for example in the number of eleven, and must be guided in a fairly congested area. They do not can in addition, in a plane transverse to the axis of the turbojet, lie outside the section defined by the projection on the transverse plane of the support arm 3 of the intermediate casing, for aerodynamic reasons related to the secondary air flow. So it is necessary to spread them longitudinally on the sheet 8. Due in particular to the surface needed to screw nuts, sheet 8 extends longitudinally beyond the inner shell 4, and exceeds in the opening area of the covers of the inner casing of the secondary flow, since it can not be located, as we have seen, in the vertical plane of symmetry, containing the hinge opening hoods.

It is therefore necessary to make a recess on a hood of the internal casing of the secondary flow to ensure the passage of the sheet 8 during the opening or closing of the hoods. Exhibit 8 must be adapted and complete this recess, to ensure the continuity of the flow guidance of air between the inner shell 4 and the surface of the inner casing of the flow secondary, at the level of the recess. Production costs of said housing and turbojet engine maintenance are all increased.

The present invention aims at reducing the production costs of the internal casing of the secondary flow, to simplify the maintenance of the turbojet engine and to facilitate access to the heart of the turbojet engine at the passage of easements along an arm of the intermediate casing.

According to the invention a turbofan engine, comprising an outer casing supported by arms, an internal casing right of the outer casing and easements is characterized by the fact that in the axis of an arm, is formed, on the inner casing, a receiving support of servitudes comprising, on the external side of the inner casing, a first sole for receiving easements.

By axis, here means the axis or direction of the gas flow around the arms.

Thus, thanks to the service distribution support of the invention, it is no longer necessary to make a cut in the inner casing of the flow secondary jet of the turbojet, since the longitudinal clutter is reduced.

Preferably, the first sole has channels of reception of easements.

Advantageously, the service distribution support comprises, on the inner side of the inner casing, a second sole for the distribution of easements.

Advantageously in this case, the reception channels of easements open onto the second flange, which has fittings easements.

In the preferred embodiment of the invention, the housing external includes a set of easements.

Preferably, the easement crossing assembly comprises a fixing flange, supporting a seal, and an attached bearing area.

More preferably, the seal is of elastomeric material and includes channels of passage of easements.

Advantageously, the turbojet engine comprises a protective arm of easements mounted between the easement passage assembly and the support distribution of easements.

The invention is particularly applicable to an external casing which is the outer shell of the intermediate casing of a turbojet engine, and a crankcase internal which is the inner shell of the intermediate casing, but the plaintiff does not intend to limit the scope of his rights to this application.

The invention also concerns, as an intermediate product, a servitude distribution support for the turbojet engine presented above, having a first sole for receiving easements and a second sole for the distribution of easements.

Preferably, the platform for receiving servitudes comprises service receiving channels.

More preferably, on the platform for receiving easements, are arranged metal locking plates in translation of easements.

Advantageously, the channels open on the sole of distribution system, which includes at its point of easements.

• la figure 1 représente une vue schématique partielle en perspective d'un turboréacteur de l'art antérieur ;
• la figure 2 représente une vue schématique partielle en perspective du carter intermédiaire de la forme de réalisation préférée du turboréacteur de l'invention ;
• la figure 3 représente une vue schématique partielle en perspective de la virole externe du carter intermédiaire, avec sa bride, son joint élastomère et son secteur d'appui joint, de la forme de réalisation préférée du turboréacteur de l'invention ;
• la figure 4 représente une vue schématique en perspective de la bride et du joint élastomère de la forme de réalisation préférée du turboréacteur de l'invention ;
• la figure 5 représente une vue schématique en perspective du secteur d'appui joint de la forme de réalisation préférée du turboréacteur de l'invention ;
• la figure 6 représente une vue schématique en perspective de la semelle de support de servitudes de la forme de réalisation préférée du support de distribution de servitudes de l'invention ;
• la figure 7 représente une vue schématique partielle en perspective de la forme de réalisation préférée du turboréacteur de l'invention, sans son bras de protection de servitudes ;
• la figure 8 représente une vue schématique partielle en perspective de la forme de réalisation préférée du support de distribution de servitudes de l'invention ;
• la figure 9 représente une vue schématique partielle en perspective de la forme de réalisation préférée du turboréacteur de l'invention, avec son bras de protection de servitudes ;
• la figure 10 représente une vue schématique en coupe de la forme de réalisation préférée du support de distribution de servitudes de l'invention, et
• la figure 11 représente une vue schématique de dessous de la forme de réalisation préférée du support de distribution de servitudes de l'invention.

The invention will be better understood with the aid of the following description of the preferred embodiment of the turbojet engine and the service distribution support of the invention, with reference to the appended drawing, in which:

• FIG. 1 represents a partial schematic perspective view of a turbojet engine of the prior art;
• FIG. 2 represents a partial schematic perspective view of the intermediate casing of the preferred embodiment of the turbojet engine of the invention;
• FIG. 3 is a partial schematic perspective view of the outer shell of the intermediate casing, with its flange, its elastomer seal and its attached bearing sector, of the preferred embodiment of the turbojet engine of the invention;
• Figure 4 shows a schematic perspective view of the flange and the elastomeric seal of the preferred embodiment of the turbojet engine of the invention;
• Figure 5 shows a schematic perspective view of the joint bearing sector of the preferred embodiment of the turbojet of the invention;
• Figure 6 is a schematic perspective view of the service support footing of the preferred embodiment of the service delivery support of the invention;
• FIG. 7 represents a partial schematic perspective view of the preferred embodiment of the turbojet engine of the invention, without its service protection arm;
• Figure 8 shows a partial schematic perspective view of the preferred embodiment of the service delivery support of the invention;
• FIG. 9 represents a partial schematic perspective view of the preferred embodiment of the turbojet engine of the invention, with its service protection arm;
• FIG. 10 represents a schematic sectional view of the preferred embodiment of the service distribution support of the invention, and
• Figure 11 is a schematic bottom view of the preferred embodiment of the service delivery support of the invention.

With reference to FIG. 2, the turbojet engine 10 of the invention comprises, downstream of the fan blade retention casing, a casing intermediate housing, which is traditionally attached to the suspension before the turbojet engine 10 to an airplane; the intermediate casing has a outer shell 11, supported radial arms 12, at the foot of which extends, on the downstream side, an inner shell 34, to the right of the outer shell 11.

The invention particularly relates to the routing of easements along a radial arm 12 of the intermediate casing.

For the sake of differentiation of the elements, we will designate by the the outer casing 11 of the intermediate casing by the unique expression of "intermediate casing 11" and the inner ring 34 of the intermediate casing by the only term of "ferrule 34".

On the intermediate casing 11, to the right of the ferrule 34, is pierced, from the downstream edge 14 of the intermediate casing 11, a recess 13 globally rectangular. The intermediate casing 11 comprises, along the circumference of its downstream edge 14, a gutter 28.

With reference to FIG. 3, the recess 13 is arranged to receive a set of easement passage 53, comprising a fastening flange 14, supporting a seal 15 for guiding and clamping servitudes, and a piece 16 which will be named attached support sector 16.

The various parts of the turbojet engine of the invention will be described, in the rest of the description, in the reference of the turbojet engine. So, when the pieces will be represented, in a figure, not mounted on the turbojet engine, we will designate their various portions according to their placement once mounted. It is in the reference of the turbojet, particular in terms of its axis, that it will be necessary to understand the various qualifiers such as internal, external, radial, axial, longitudinal, upstream, downstream, ...

With reference to FIG. 4, the flange 14 is generally under the shape of a metal stirrup, comprising a base 17 and two branches 20, 20 ', slightly curved to fit the crankcase shape intermediate 11. The base 17 of the flange 14 is arranged to come in support on the upstream bottom 19 of the recess 13 of the intermediate casing 11. It comprises a longitudinal shoulder 18 whose projecting portion is on the side internal of the base 17. The shoulder 18 is shaped to come into support on the inner face of the intermediate casing 11, upstream of the recess 13.

Between the branches 20, 20 'of the flange 14, on its external side, is mounted a seal 15, here elastomeric material, whose outer surface is at same level as the outer surface of the flange 14. The elastomeric seal 15 is pierced with a plurality of radial channels 25 easement passage. AT its downstream end, the flange 14 comprises, at the level of each of its branches 20, 20 ', a longitudinal shoulder 21, 21', located at a distance of the outer surface of the flange is smaller than that of the opposite shoulder 18.

On the shoulders 21, 21 'are pierced, through the branches 20, 20 ', two radial bores 22, 22' for receiving a screw. Upstream shoulders 21, 21 ', two lugs 23, 23' project from the lateral faces branches 20, 20 '. Each ear is pierced with a radial bore 24, 24 '.

With reference to FIG. 5, the joint support sector 16 presents itself in the form of a metal plate. It comprises, on its downstream edge, two radial projections 26, 26 'forming a gutter 27, arranged to ensure the continuity of the gutter 28 of the intermediate casing 11.

On its upstream edge, the attached support sector 16 has a protrusion radial central 29 having at its outer end two fingers longitudinal 30, 30 ', extending upstream. The upstream face 31 of the projection 29 and its fingers 30, 30 'are shaped to bear on the downstream face and the outer face, respectively, of the elastomeric seal 15.

The attached support sector 16 further comprises, on its upstream edge, on either side of the central projection 29, two radial bores 32, 32 'of receiving screws 33, 33 'spaced from each other by the same distance as the bores 22, 22 'of the flange 14.

The mounting of the flange 14, on which is arranged the seal elastomer 15, and the attached bearing sector 16 in the recess 13 is the next. The flange 14 is mounted in the recess 13, with its base 17 bearing on the upstream bottom 19 of the recess 13 and its shoulder 18 in bearing on the inner face of the intermediate casing 11, upstream of the recess 13. The ears 23, 23 'are in contact with the inner face of the intermediate casing 11, fixed to the latter by screws in their bores 24, 24 '. The joint support sector 16 is fixed to the flange 14 by the screws 33, 33 ' in the bores 22, 22 'of the flange 14 through the bores 32, 32' of the joint bearing sector 16. The upstream face 31 of the projection 29 and its fingers 30, 30 'are then supported on the downstream face and the outer face of the elastomer seal 15 and there is continuity between the two. In addition, in this configuration, the gutter 27 of the attached support sector 16 ensures the continuity of the gutter 28 of the intermediate casing 11.

Thus mounted, the flange 14, the elastomer seal 15 and the sector support 16 ensure the continuity of the intermediate casing 11, while providing channels for the passage of easements. They constitute a set of passage of easements 53, which ensures the passage of servitudes through the intermediate casing 11, while tightening the relative to each other, according to the distribution of the channels 25 on the joint elastomer 15. It also ensures the tightness of the assembly, easements being inserted by force into their channels 25.

With reference to FIGS. 6 and 7, on the shell 34 of the turbojet engine 10 is arranged a service distribution support 35, placed at the right of the crossing set of easements 53.

The support 35 comprises, on the outer side of the shell 34, a first outsole for the receipt of easements 36 protruding out of the latter. The sole 36 has a rounded triangular shape, the base of which is on the upstream side of ferrule 34, at arm 12, and the top on the downstream side of ferrule 34. The width of the base corresponding to approximately the transverse width of the arm 12. The first sole 36 comprises service receiving channels 37, opening on its outer surface.

Easements 38, coming from outside the intermediate casing 11, are inserted into the channels 25 of the elastomer seal 15, extend the along a radial support 39 parallel to the arm 12 mounted between the housing intermediate 11 and the ferrule 34, and their end is fitted into the channels 37 of the sole 36.

With reference to FIG. 8, the end of the servitudes 38 comprises a specific tip, composed of an annular seal 40, comprising a annular groove 41. The seal 40 is adapted to its receiving channel 37, and is fitted so that its groove 41 is flush with the surface of the first sole 36. Metal plates 42, comprising adapted recesses 43, are fixed, using screws 44, on the sole 36, their recesses 43 engaging on the grooves 41 of the joints 40 of the easements 38 to block the latter in radial translation.

With reference to FIG. 9, an arm 45 for the protection of servitudes is attached to the sole 36, to the radial support 39, to the flange 14 and to the bearing sector 16. This arm 45 is in the form of a sheet adapting to all the elements to which it is attached, in order to protect the whole. Its section is globally constant and corresponds to the contour of the sole 36. It is arranged to complete the shape of the arm for the purpose of guiding the secondary air flow flowing between the intermediate casing 11 and the ferrule 34. This form is adapted to the dynamic stresses that are imposed on the flow, and proceeds from parameters mainly related to fluid mechanics.

With reference to FIGS. 10 and 11, the distribution support of servitudes 35 comprises, on the inner side of the ferrule, a second sole 46 distribution of easements, located at the right of the first sole 36. The reception channels 37 of the easements 38 pass through the first sole 36, external, and extend into the second sole of distribution 46. In the latter, they can be oriented, by an elbow 47, so as to open on a lateral face of the second sole 46, or do not change direction and lead to the inner face of the second sole 46. They can further change diameter if this is longed for.

At the open end of the channels 37, on the second flange 46, Arrangements 48 are provided. These connectors 48 comprise a connecting joint 49, a nozzle 50 and a nut 51 for screwing an easement. Thus, it is possible to connect servitudes 52, provided with end caps arranged for this purpose, at the service connections 48 of the second sole 46.

Thanks to the invention, the passage of easements 38 between the housing intermediate 11 and the ferrule 34 is insured. Easements 38 are inserted in the channels 25 of the elastomer seal 15 extend into the formed enclosure by the arm 45 and the radial support 39, between the intermediate casing 11 and the ferrule 34, and are inserted into the channels 37 of the distribution support of easements 35, by their tips 40 adapted for this purpose, at which they are blocked in radial translation by the metal plates 42. Channels 37 provide the link with easements 52 from within the ferrule 34, that is to say the heart of the turbojet engine 10, connected to them by the connectors 48 of the distribution soleplate 46.

The channels 25 of the elastomer seal 15, the channels 37 of the support of distribution of easements 35, metal plates 42 and connectors 48 of the second sole 46 are dimensioned and shaped according to the easements 38, 52 that they must connect. The assembly of these is therefore, thanks to the invention, perfectly simplified and standardized.

In addition, and in particular because easements 38, 52 are not more fixed by nuts on both sides of the shell 34 but fitted into channels 37 or end-pieces 48, saving space for their connection is large, and allows to obtain a distribution support of easements 35 whose longitudinal surface does not extend beyond that of ferrule 34. It is therefore no longer necessary to practice a recess in the covers of the internal casing of the secondary flow, since the arm 45, located at right of the service distribution support 35 and in particular of its first sole 36, does not encroach on their opening zone and closing.

The service distribution support 35 can indifferently be formed in one piece with the ferrule 34 or reported on the latter.

Claims (14)

Turbofan engine comprising an outer casing (11) supported by arms (12), an inner casing (34) to the right of the outer casing (11), easements (38, 52), characterized in that , in the axis of an arm (12) is provided on the inner casing (34), a service distribution support (35) having, on the outer side of the inner casing (34), a first sole for the reception of easements (36). A turbojet engine according to claim 1, wherein the first sole (36) has service receiving channels (37). Turbojet engine according to one of claims 1 to 2, wherein the service distribution support (35) has, on the inner side of the internal casing (34), a second sole for the distribution of easements (46). Turbojet engine according to claims 2 and 3, in which the service receiving channels (37) open on the second sole (46), which has service connections (48). Turbojet engine according to one of claims 1 to 4, wherein the outer casing (11) comprises an easement passage assembly (53). A turbojet engine according to claim 5, wherein the assembly passage of servitudes (53) comprises a fastening flange (14), supporting a seal (15), and an attached bearing area (16). Turbojet engine according to claim 6, wherein the seal (15) comprises service passage channels (25). Turbojet engine according to claim 7, wherein the seal (15) is elastomeric material. Turbojet engine according to one of claims 5 to 8, comprising a service protection arm (45) mounted between the passage assembly of servitudes (53) and the service distribution support (35). Turbojet engine according to one of claims 1 to 9, wherein the outer casing is the outer shell of the intermediate casing (11) and the casing internal is the inner shell of the intermediate casing (34). Servitude distribution support for the turbojet engine of the claim 1, comprising a first sole for the reception of easements (36) and a second footing for the distribution of easements (46). Service distribution support according to claim 11, wherein the first sole (36) has channels for receiving easements (37). Service distribution support according to claim 12, in which, on the first flange (36), plates are arranged metal (42) blocking translation of easements. Easement distribution support according to one of the 12 or 13, wherein the channels (37) open on the second sole (46), which has service connections (48).

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