EP1553263A1 - Connecting strut for service conduits in a turbofan engine - Google Patents

Abstract

The engine has a removable modular arm (25) forming servicing connector and arranged between an outer fan duct (24) and an inner fan duct (23). The arm has an oval indention formed in a plate and provided with orifices for passage of tubing components. Each tubing component is the servicing connector, between service connection outside the duct (24) and connection`s extension inside the duct (23).

Description

The invention relates to a turbofan engine comprising a outer casing of secondary flow.

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 housings.

Generally, it is suspended from the structure of an aircraft by two casings: an intermediate housing, placed just downstream of the retention housing of the blades of blower, and an exhaust casing at the rear of the engine.

In the case, for example, where a turbojet engine is placed on the fuselage of an airplane, generally in the rear position, the secondary air flow must be contained and guided along the turbojet engine to the exhaust casing. In this guiding goal, a structural outer secondary flow casing, called "outer fan duct ", is placed between the intermediate housing and a connected suspension ring to the exhaust casing by a series of rods. This external flow casing secondary structure provides dual function, restraint and guiding the secondary air flow, on the one hand, resumption of thrust forces, on the other.

The annular secondary airflow is guided on its inner surface by an inner casing called "inner fan duct", placed globally concentric to outer structural casing, between the inner base of the arms of the intermediate casing and the exhaust casing.

The various fluids necessary for the operation of the turbojet, such as the fuel, oil and accessory organ control fluids of the motor, must be routed from outside the turbojet engine, in particular outside the structural outer casing, towards its core, that is to say the enclosure, defined by the internal casing, containing the compressor, the chamber of combustion, the turbine and the nozzle. This routing is carried out by pipelines commonly referred to as easements. The invention relates to particularly the passage of the servitudes between the outer casing of the flow secondary and internal housing.

In Figure 1, which partially represents the elements of the envelope, a turbojet 1 of the prior art, we see an intermediate casing 2 and a 3. The ring is attached to the exhaust housing, no represented by connecting rods. An external structural casing 4 mounted between the casing 2 and the ring 3 comprises access hatches 5 distributed over its circumference, allowing access to the interior of the enclosure that it defines, and in particular to the housing internal. It is through these hatches 5 that the easements 7 are mounted.

With reference to FIG. 2, the internal casing comprises a plurality of panel support plates 6, extending longitudinally between the base of the intermediate casing arm and exhaust housing. They are intended for support panels that will define the surface of the inner housing. Easements 7 are brought and fixed on these panel support plates 6, to which the operator has access through the access hatches 5 of the external structural casing 4, on a sole 8 protruding radially on the plates 6. On this sole 8 is then mounted, between the outer structural casing 4 and non-structural internal casing, a profiled envelopment sleeve of easements 7, to ensure their protection and a good flow of the gas vein. The fitting of the profiled shirt is also by hatches 5. These can then be closed.

The assembly of easements as just described presents many disadvantages. It is very tedious, easements to be mounted one by one on the sole, according to a precise assembly order. Access to the housing internal by the hatches of the structural outer casing is also impractical. The maintenance or disassembly finally have the same disadvantages as the mounting.

The present invention aims to simplify the assembly, disassembly and maintenance of the servitudes passing between the structural outer casing and the casing internal non-structural of a turbojet.

According to the invention, a turbofan engine comprising an external secondary flow casing, an internal secondary flow casing, fluid transport servitudes located outside the external flow casing secondary, fluid transport servitudes located inside the housing internal secondary flow, is characterized by the fact that at least one arm removable modular forming servitude connector is arranged between said housing external and said inner housing.

Thanks to the invention, the connection of external servitudes to the housing secondary flow, at internal servitudes to the internal casing, is made simply using a removable modular arm, it is easy to mount and dismount. Indeed, because it is modular, the arm forms a any compound of a prefefined set of standard elements; his character Removable means the possibility of removing it, as a whole modular.

This arm can also be calibrated for various applications or different turbojets.

Preferably, the non-structural inner housing having panels and longitudinal panels for supporting the panels, at least one plate longitudinal panel support comprises a receiving plate of a removable modular arm.

According to another characteristic, the outer casing comprises less a passage opening of a removable modular arm.

According to another characteristic, the modular arm comprises pipe elements, comprising external connecting means to easements, and intended to be inserted in channels opening on the face external board.

Advantageously in this case, the channels also open at least one different face of the plate and comprise connecting means to easements.

Advantageously, the outer face of the plate comprises a recess receiving the modular arm, in which the channels are drilled.

The invention concerns, as an intermediate product, a modular arm removable for the turbojet engine shown above, comprising a sheet metal, pierced orifices for the passage of calibrated pipe elements, elements of calibrated pipelines and a profiled jacket adapted to the sheet.

Preferably, the pipe elements comprise, at one of their ends, connecting means to servitudes.

Preferably, the pipe elements comprise, at one of their ends, an O-ring seal.

Preferably, the sheet comprises a recess, on which are drilled the orifices, intended to be fitted into the profiled jacket.

• la figure 1 représente une vue schématique en perspective d'une enveloppe de turboréacteur de l'art antérieur ;
• la figure 2 représente une vue schématique en perspective des servitudes montées sur une plaque de support de carter interne de l'art antérieur ;
• la figure 3 représente une vue de profil en coupe du turboréacteur de l'invention ;
• la figure 4 représente une vue schématique en perspective d'une partie du bras modulaire de l'invention ;
• la figure 5 représente une vue de dessous schématique en perspective partiellement en coupe du bras modulaire de l'invention ;
• la figure 6 représente une vue schématique en perspective d'une autre partie du bras modulaire de l'invention ;
• la figure 7 représente une vue de profil du bras modulaire de l'invention ;
• la figure 8 représente une vue schématique en perspective des supports de panneaux du carter interne non structural du turboréacteur de l'invention ;
• la figure 9 représente une vue en coupe transversale d'un support de panneaux du carter interne non structural du turboréacteur, dans lequel sont insérés des éléments de canalisations du bras modulaire de l'invention, et
• la figure 10 représente une vue schématique de face en perspective du turboréacteur 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 its modular service coupling arm of the invention, with reference to the appended drawings, in which:

• FIG. 1 represents a schematic perspective view of a turbojet envelope of the prior art;
• FIG. 2 represents a schematic perspective view of the servitudes mounted on an inner casing support plate of the prior art;
• FIG. 3 represents a cross sectional profile view of the turbojet engine of the invention;
• Figure 4 shows a schematic perspective view of a portion of the modular arm of the invention;
• Figure 5 shows a schematic bottom view in perspective partially in section of the modular arm of the invention;
• Figure 6 shows a schematic perspective view of another part of the modular arm of the invention;
• Figure 7 shows a side view of the modular arm of the invention;
• FIG. 8 represents a schematic perspective view of the panel supports of the non-structural internal casing of the turbojet engine of the invention;
• FIG. 9 represents a cross-sectional view of a panel support of the non-structural internal casing of the turbojet, in which pipe elements of the modular arm of the invention are inserted, and
• FIG. 10 represents a diagrammatic perspective view of the turbojet engine of the invention.

With reference to FIG. 3, the turbojet engine 10 of the invention comprises from upstream to downstream in the direction of gas flow, an air intake sleeve, a fan 11, a compressor 12, a combustion chamber 13, a turbine 14 and an exhaust duct 15. The blower is contained in a fan retention housing 16, downstream of which is mounted a housing intermediate 17, supported by arms 18 resting on an annular internal base 19 extending around the compressor housing 20. The conduit 15 is contained in an exhaust housing 21. A suspension ring 22, intended to be attached to a turbojet engine suspension to an airplane, is attached to the crankcase exhaust 21 by not shown rods.

Between the annular internal base 19, on the one hand, and the exhaust casing 21, on the other hand, is mounted an internal casing 23 non-structural, commonly called "inner fan duct", which envelops the heart of the turbojet engine 10, for the purpose to contain and guide the secondary flow flowing outside of the latter.

Between the intermediate casing 17, on the one hand, and the suspension ring 22, on the other hand, is mounted an outer casing secondary flow 24, structural, commonly called "outer fan duct", whose role is to contain and guide, on its external surface, the secondary flow flowing outside the heart of the turbojet engine 10, but also to take up the thrust forces between the ring of suspension 22 and the intermediate casing 17, to which is connected the other suspension from the turbojet engine 10 to the airplane.

According to the invention, a modular radial arm 25 servitudes is arranged, for the purpose of connecting servitudes, between the crankcase 24 and the inner casing 23. Its role is to ensure continuity between servitudes located outside the external flow casing 24 and other located inside the inner housing 23.

With reference to FIG. 4, the modular arm 25 comprises a plate 26 overall rectangular, slightly curved, in which is practiced a recess 27, here of oval shape. In the recess 27 are drilled orifices 28 for passage of pipe elements 29, here ten in number. More precisely, in each orifice 28, a pipe element 29 can be inserted and fixed, for example by bolting, at this orifice 28, as it will be seen more precisely further. The pipe elements 29 are here metallic.

Each pipe element 29 is a service coupling, between a servitude outside the outer casing 24 and its extension inside the internal casing 23. Each duct element 29 is calibrated according to the servitude for which it provides the function of connection. The diameter of the orifice 28 is calibrated according to the pipe element 29 that it receives.

By internal or external, for a room or part of a room, one will later hear a portion that, once mounted, is placed respectively radially inwardly or outwardly of the turbojet engine 10.

With reference to FIG. 5, each line element 29 comprises a skirt 31 for positioning and sealing, which is integral with it and is intended to abut on the inner face of the recess 27. Thus, during assembly of the modular arm 25, each pipe element 29 is inserted, by its end closest to the skirt 31, in the orifice 28 which is intended for it, until the skirt 31 abuts the inner face of the recess 27. A nut 30 is then screwed onto a thread of the pipe element 29 provided for this purpose, the outer side of the recess 27, ensuring the maintenance of the pipe element 29 in its orifice 28, between the nut 30 and the skirt 31. Other intermediate sealing or positioning parts, in particular outer side of the recess 27, may be provided. At the most extreme close to the skirt 31, the pipe elements 29 comprise, beyond the nut 30, connecting means 50 to an easement, for example here a thread 50 on the pipe element 29 considered. These connection means 50 connect the service on the outside of the outer casing 24, and for which it is desired to provide a connection with an easement within the enclosure defined by the inner casing 23, to the pipe element 29, which has been previously sized to ensure this connection.

All the pipe elements 29 are fixed in their orifice 28 respective. The same number of orifices 28 are provided as elements of 29. If this were not the case, the unused ports 28 would be blocked. In the illustrated embodiment of the invention, the elements of pipes 29 have an elbow 32 near their skirt 31 and extend in a generally rectilinear manner on either side of this elbow 32. pipe elements 29 all have the same shape, except for their diameter, and therefore extend all parallel to each other once mounted.

With reference to FIG. 6, the removable modular arm 25 of the invention further comprises a profiled shirt 33. The shirt 33 has a body of shirt 34 of generally oval section, corresponding to the oval shape of the recess 27, and elongated so as to adapt to the distance separating the housing internal 23 of the outer casing 24. The jacket 33 is hollow and open from both sides, and has an outer rim 35, generally perpendicular to the body 34, and whose shape corresponding to the shape of the sheet 26.

The oval shape is linked initially to the oval shape that we wish give the liner 33 of the modular arm 35. Indeed, once the turbojet mounted, the jacket 33 extends between the inner casing 23 and the outer casing 24, by consequently, in the secondary stream, its shape must be adapted according to the flow of the secondary flow around it. The oval shape can of course be replaced by any appropriate form.

Referring to Figure 7, but also to Figure 5, the modular arm 25 of the invention, once assembled, comprises the plate 26, on which are fixed the pipe elements 29, around which is threaded the profiled jacket 33, whose shape adapts to the whole. The rim 35 of the jacket 33 is arranged, as we saw earlier, to fit the shape of the inner face of the sheet 26, the recess 27 of the sheet being embedded, on the inner side where it protrudes, in the body 34 of the sleeve 33, dimensioned for this purpose. The liner 33 is made integral, by welding or brazing, for example, sheet metal 26, forming, with it and the pipe elements 29, the modular arm 25 of the invention. Once the arm 25 is assembled, the pipe elements 29 protrude, opposite the sheet 26, from the enclosure defined by the jacket 33.

With reference to FIG. 8, the inner casing 23 comprises a plurality of longitudinal plates panel supports 36, here four in number, which form, with other holding elements such as a ring 37, the armature of the internal casing 23. Referring to Figure 10, the inner casing 23 is formed when panels 38 are placed between the successive panel supports 36, wedged in recesses 47 provided for this purpose, thereby creating the surface required for the enveloping of the heart of the turbojet engine 10 and the flow guidance secondary.

On the panel supports 36, in the central part which is not in contact with the panels 38, is arranged a plate 39 for receiving an arm modular connection 25 servitudes. Such a plate 39 includes a longitudinal recess 40, forming a shoulder 41 which follows a shape globally oval corresponding to the section of the inner end of the sleeve 33 of the modular arm 25.

With reference to FIG. 9, the recess 40 is pierced with a plurality of channels 42, here at the number of ten, receiving and connecting elements of conduits 29 of the modular arm 25 of the invention. Each channel 42 includes a portion 43 opening on the surface of the recess 40, here in front view perpendicular to this surface, an elbow 51 and a portion 44 parallel to the surface of the recess 40, therefore perpendicular to the first portion 43, opening onto a lateral longitudinal wall of the support 36 in which the channel 42 is pierced. In the preferred embodiment of the turbojet engine 10 the invention, two parallel rows of five channels 42 are drilled on the recess 40, the channels 42 opening, depending on the row to which they belong to one or other of the lateral longitudinal walls of the support 36. It goes without saying that instead of opening onto the lateral faces of the support 36, the Channels 42 could lead to its inner face.

It is possible to connect at the level of the portion 44 of a channel 42 opening on the side portion of the support 36, duly dimensioned, a servitude 45 located inside the enclosure defined by the internal casing 23. Fittings 46, well known to those skilled in the art, may be provided for this purpose on the support 36. The connectors 46 and the channels 42 are well sure sized according to the servitude to which they must serve as connection.

Each channel 42 is dimensioned, in its portion 43 opening on the surface of the recess 40, for receiving the end of a pipe element 29. The latter may be provided with an O-ring 48 sealing. In the exemplary embodiment of the invention described herein, the ten channels 42 are dimensioned to receive each end of the pipe element 29 of the modular arm 25 corresponding to their position.

The distribution and the diameter of the channels 42 on the surface of the recess 40 of the support 36 is comparable to the distribution and the diameter of the orifices 28. on the surface of the recess 27 of the modular arm 25. The plate 39 is exactly arranged and designed for the reception of a modular arm 25 particular: its channels 42 are arranged to receive the elements of 29, while the shoulder 41 of the recess 40 is arranged to support the inner end of the body 34 of the shirt 33.

The assembly of the easements and their connection between the outer casing 24 and the internal casing 23 of the turbojet engine 10 of the invention will now be described in more detail, taking the example of a connection by a single modular arm 25.

The panel supports 36 of the internal casing 23 of the turbojet engine 10 are mounted around the heart of the turbojet engine 10, between the internal base 19 of the arm 18 of the intermediate casing 17 and the exhaust casing 21. The easements, extending inside the enclosure which will be defined by the inner housing 23 and intended to be connected with servitudes located outside the housing external 24, are then connected to the portions 43 of the channels 42 which are intended, on the connections 46, provided for this purpose, the support 36 on which is arranged the plate 39 for receiving the modular arm 25.

This internal connection being made, it is possible to place the panels 38 on their supports 36 and thus to form the internal casing 23. The outer structural casing 24 is then mounted between the casing intermediate 17 and the suspension ring 22.

The modular arm 25 is then slid through a hole 49 oval provided for this purpose on the outer casing 24, between the latter and the inner casing 23. The orifice 49 is at the base of the plate 39, so that it is possible, just by inserting the arm 25 into the orifice 49, to insert the ends of the elements of pipes 29 in the portions 43 of pipes 42 of the platinum 39 intended to receive them, without the need to access the space defined by the inner casing 23 and the outer casing 24. The plate 26 of the arm 25 is then fixed removably to the outer structural casing 24, for example by means of inserts, or any other suitable means. It could also be brazed, this which would, however, make it more difficult to disassemble the arm 25.

The easements extending outside the outer casing 24, and to be connected to the aforementioned internal servitudes, may then be connected to the connecting means 50 of the pipe elements 29, the choice obviously taking into account the easement already connected to each pipe element 29 through the plate 39.

Thus, thanks to the modular arm 25 of the invention, the connection of the servitudes between the outer structural casing 24 and the non-structural internal casing 23 is assured, the arm 25, in cooperation with the plate 39 and the orifice 49 of the outer structural casing 24, allowing the connection of servitudes here. This connection can be easily removed and dismounted without having to disassemble internal connection made at the side walls of the supports 36.

It goes without saying that several sets of arms 25, plate 39 and orifice 49 can be provided, either on different panel supports 36 of the inner casing non-structural 23, even on the same support 36, for example along this latest.

In the described embodiment of the turbojet engine 10 of the invention, the modular arm 25, its orifices 28 for passage of pipe elements 29, the pipe elements 29 and their connections 50, the channels 42 and their connectors 46 are calibrated according to the servitudes they allow to connected. It goes without saying that all of these elements could be calibrated standard way, fittings 46, 50 or other fittings allowing adaptation according to the type and size of easements to be connected.

Claims (10)

A turbofan engine comprising an external secondary flow casing (24), an internal secondary flow casing (23), fluid transport servitudes located outside the external secondary flow casing (24), servitudes of fluid transport located inside the internal secondary flow casing (23), characterized in that at least one removable modular arm (25) forming a service connection is arranged between said outer casing (24) and said inner casing (23). A turbojet engine according to claim 1, wherein, the inner housing (23) comprising panels (38) and longitudinal support plates panels (36), at least one longitudinal panel support plate (36) comprises a plate (39) for receiving a removable modular arm (25). Turbojet engine according to one of claims 1 or 2, wherein the outer casing (24) comprises at least one orifice (49) for passage of said arm modular (25). Turbojet engine according to one of claims 2 or 3, wherein said modular arm (25) comprises pipe elements (29) provided with external means (50) for connection to servitudes, and intended to be inserted into channels (42) opening on the outer face of the plate (39). Turbojet engine according to claim 4, wherein the channels (42) also open on at least one different face of the plate (39) and comprise means (46) for connecting to servitudes. Turbojet engine according to one of claims 4 or 5, wherein the outer face of the plate (39) comprises a recess (40) for receiving the arm modular (25), in which the channels are drilled. Modular arm for the turbojet engine of one of claims 1 to 6, comprising a plate (26) pierced with orifices (28) for the passage of elements of pipes (29), pipe elements (29) and a profiled jacket (33) adapting to the sheet (26). Modular arm according to claim 7, wherein the elements of pipes (29) comprise, at one of their ends, means for fitting (50) to servitudes. Modular arm according to one of Claims 7 or 8, in which the pipe elements (29) have, at one of their ends, a seal sealing ring (48). Modular arm according to one of Claims 7 to 9, of which said plate (26) comprises a recess (27) on which said holes (28) are drilled, intended to be fitted into the profiled jacket (33).

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