Connecting strut for service conduits in a turbofan engine

A turbofan engine with a outer casing secondary flow.

A turbofan engine includes functionally a handle air inlet, a blower, a compressor, a chamber combustion, a turbine and an exhaust nozzle. These elements are contained in casings.

Generally, it is suspended to the structure of an aircraft by two housings: said intermediate casing, positioned just downstream of blade retention housing fan, and an exhaust casing to the rear of the engine.

In the case, for example, where a turbojet is placed on the fuselage an aircraft, usually in the rear position, the secondary air flow must be content and guided along the jet engine to the exhaust casing. In This guiding purpose, a casing of structural external secondary flow, called "outer fan duct ", is placed between the intermediate casing and connected to a suspension ring to the exhaust casing by a series of rods. This external flow housing Secondary structural has a dual function, restraint and guidance secondary air flow on the one hand, recovery of the thrust forces on the other.

The annular flow of secondary air is guided on its inner surface by an inner casing called "inner fan duct", placed in generally concentric structural outer casing, among the inner base of the arm of the intermediate casing and the exhaust casing.

The various fluids required for the operation of the jet engine, such as fuel, oil, and control fluids Accessories organs engine must be routed from outside the turbojet engine, including outside the structural outer casing toward its core, that is to say, the enclosure, defined by the inner housing, containing the compressor, the chamber combustion, turbine and the nozzle. This routing is carried out by pipes commonly called easements. Disclosed particularly the passage easements between the external casing of the flow secondary and the inner casing.

In Figure 1, that partially shows the elements of the casing, a turbojet engine 1 of the prior art, there is shown a middle housing 2 and a suspension ring 3. The ring is fixed to the exhaust casing, not represented by links. A structural outer casing 4 mounted between the housing 2 and ring 3 comprises access hatches 5 distributed over its circumference, allowing access to the interior of the enclosure defined therein, and in particular to the housing internal. It is through these doors that are mounted 5 easements 7.

Referring to Figure 2, the inner casing includes a plurality of plates 6 of panel support extending longitudinally between the base of arm of the intermediate casing and the exhaust casing. They are intended to supporting panels that will define the surface of the inner casing. easements 7 are supplied and attached to these carrier plates of panels 6, which the operator has access via access doors 5 of the structural outer casing 4, on a flange 8 projecting radially from the plates 6. In this flange 8 is then mounted between the structural outer casing 4 and non-structural inner case, a wrap profiled shirt easements 7, to ensure their protection and a good flow of the gas stream. The mounting of the profiled liner was also from the doors 5. These can then be closed.

The mounting of such easement has just been described has many disadvantages. It is very tedious, easements must be mounted one by one on the base, according to a specific assembly order. Access to housing Internal from the doors of the structural external housing is also impractical. The maintenance or disassembly finally present the same drawbacks as the mounting.

The invention aims to simplify the assembly, dismantling and maintenance easement passing between the structural outer housing and the housing non-structural internal of a turbojet.

According to the invention a dual-flow turbojet, comprising an outer casing of the secondary flow, an inner casing secondary flows, fluid transport easement located outside of the outer casing flows secondary, fluid transport easement located within the housing Internal secondary flow, is characterized in that at least one arm A removable modular forming easement connection is arranged between said housing external and said internal casing.

Thanks to the invention, the connection of external easements housing external secondary flow, domestic servitude to the inner casing, is simply performed using a removable modular arm, it is easy to mount and dismount. Indeed, since it is modular, the arm forms a all composed of a set of standard elements préféfini; his character removable means the ability to remove, in its modular set.

This arm can also be calibrated for various applications or various jet engines.

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

According to another feature, the outer casing comprises at least one passage opening with a removable modular arm.

According to another feature, the modular arm comprises piping elements comprising external connection means for easement, and intended to be inserted in channels opening on the face external of the plate.

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

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

The invention, as an intermediate product, a modular arm removable for turbojet presented above, comprising a sheet pierced of through-holes with calibrated pipe elements, elements of calibrated pipe and a profiled sleeve conforming to the sheet.

Preferably, the piping elements comprise at one of their ends, connecting means to easements.

Preferably, the piping elements comprise at one of their ends, a sealing O-ring.

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

The invention will be better understood using the following description of the preferred embodiment of the turbojet engine and its modular arm fitting easement of the invention, with reference to the accompanying drawings, in which :<ul><li>1 shows a schematic perspective view of a turbojet casing of the prior art; </li><li>2 shows a schematic perspective view of the easement mounted on an inner casing supporting plate of the prior art;</li><li>3 shows a view in section of the profile turbojet the invention;</li><li>4 shows a schematic perspective view of a portion the modular arm of the invention;</li><li>5 shows a schematic bottom view partially in section of the modular arm of the invention;</li><li>6 shows a schematic perspective view of another part of the modular arm of the invention;</li><li>7 shows a side view of the modular arm the invention;</li><li>8 shows a schematic perspective view of the supports panels of the non-structural inner case of the turbojet of the invention;</li><li>9 shows a cross-sectional view of a support panels of the non-structural internal casing of the turbojet, wherein are inserted pipe elements of the modular arm of the invention, and</li><li>10 shows a schematic front view in perspective of turbojet of the invention.</li></ul>

Referring to Figure 3, the turbine engine 10 of the invention comprises, upstream to downstream in the direction of the gas flow, an air inlet duct, a fan 11, a compressor 12, a combustor 13, a turbine 14 and an exhaust duct 15. The blower is contained in a fan retention casing 16, downstream of which is mounted a housing Intermediate 17, supported by arm 18 resting on an inner annular base 19 extending around the compressor casing 20. The conduit 15 is contained in an exhaust casing 21. A suspension ring 22, intended to be fixed to a suspension of the turbojet engine to an aircraft is attached to the housing exhaust 21 by unrepresented rods.

Between the annular inner base 19 on the one hand, and the exhaust casing 21, on the other hand, is mounted an inner casing 23, non-structural, commonly called "inner fan duct", which wraps the core of the turbojet engine 10, in order to contain and guide the secondary flow flowing to the outside thereof.

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

According to the invention, a modular radial arms 25 of connector easements is arranged in order to connect easements between the housing 24 external and internal casing 23. Its role is to ensure continuity between easement located outside the outer casing of the secondary stream 24 and other located inside of the inner casing 23.

Referring to Figure 4, the modular arm 25 comprises a sheet 26 generally rectangular, slightly curved, wherein is formed a recess 27, here oval. In the recess 27 are pierced orifices 28 passing piping elements 29, here ten in number. More Specifically, in each aperture 28, a conduit member 29 may be inserted and fixed, for example by bolting, at this orifice 28, as will be seen more precisely later. 29 piping elements here are metal.

Each pipe element 29 is a bonded connection between a bonded to the outside of the external casing 24 and its extension inside the inner casing 23. Each pipeline element 29 is calibrated to the bondage which it ensures the fitting function. The diameter of the orifice 28 is calibrated to the section of pipe 29 it receives.

By internal or external, to a room or part of a workpiece, it hear, thereafter, a portion which, when mounted, is placed respectively radially inwards or outside the turbojet engine 10.

Referring to Figure 5, each duct member 29 comprises a skirt 31 for positioning and sealing, which is fixed and is intended for it to abut on the inner face of the recess 27. Thus, during assembly Modular arms 25, each pipe member 29 is inserted, by its the nearest end of the skirt 31 in the aperture 28 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 on the outer side of the recess 27, ensuring the maintenance of the pipe member 29 in its hole 28, between the nut 30 and the skirt 31. Other intermediate sealing parts or positioning, in particular outer side of the recess 27, may be provided. At the end more close to the skirt 31, 29 of piping elements comprise, beyond the nut 30, connecting means 50 to an easement, for example by a thread 50 on the pipe member 29 considered. These connection means 50 used to connect the easement located outside the outer casing 24, and for which we want to make a connection with an easement within the enclosure defined by the inner casing 23, the pipe element 29, which has been previously dimensioned to provide this connection.

All 29 lines of elements are secured in their opening 28 respective. There is provided the same number of orifices 28 as elements of pipes 29. If this were not the case, the unused 28 holes would blocked. In the illustrated embodiment of the invention, the elements of pipes 29 comprise a bend 32 near their skirt 31 and extend generally linearly on either side of the bend 32. pipe elements 29 all have the same form, except for their diameter, and thus all extend parallel to each other when mounted.

Referring to Figure 6, the removable modular arm 25 of the invention further comprises a shaped jacket 33. The jacket 33 has a body jacket 34 of generally oval cross section, corresponding to the oval shape of recess 27, and elongated so as to adapt to the distance between the housing internal 23 of the outer casing 24. The liner 33 is hollow and open at both sides, and comprises an outer rim 35, generally perpendicular to the body jacket 34, and the shape corresponding to the shape of the sheet 26.

The oval shape is due to the departure to the oval shape that is desired give to the jacket 33 of the modular arm 35. In effect, once the turbojet mounted, the sleeve 33 extends between the inner casing 23 and the outer casing 24 by Therefore in the secondary flow, its shape to be adapted according to the flow of the secondary flow around it. The oval shape can of course be replaced by any suitable form.

Referring to Figure 7, but also to Figure 5, the modular arm 25 of the invention, when assembled, includes the sheet 26, on which are fixed pipe elements 29, which is threaded around the profiled sleeve 33, the shape of which suits the assembly. The flange 35 of the sleeve 33 is arranged, as we have seen, to match 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 into the body 34 of the jacket 33, dimensioned to this end. The jacket 33 is secured by welding or soldering, for example, sheet metal 26, forming with it and piping elements 29, the modular arm 25 of the invention. After 25 assembled arm, piping elements 29 protrude away from the plate 26, outside the enclosure defined by the liner 33.

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

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

Referring to Figure 9, the recess 40 is pierced with a plurality of channels 42, here ten in number, receiving and fitting elements pipes 29 of the modular arm 25 of the invention. Each channel 42 comprises an opening portion 43 on the surface of the recess 40, here in front view perpendicular to this surface, a bend 51 and a portion 44 parallel to the surface of the recess 40, thus perpendicular to the first portion 43, opening on a longitudinal side wall of the carrier 36 wherein the channel 42 is pierced. In the preferred embodiment of the turbojet 10 the invention two parallel rows of five channels 42 are drilled on the recess 40, the channels 42 opening, according to the row to which they belong to one or other of the longitudinal side walls of the support 36. It goes without saying that, instead of lead on the side faces of the carrier 36, the channels 42 lead to its inner face.

It is possible to connect, at the portion 44 of a channel 42 opening on the side of the support 36, properly dimensioned, a bondage 45 located within the enclosure defined by the inner casing not structural connectors 23. 46, well known in the art, can be provided for this purpose on the support 36. The fittings 46 and the channels 42 are safe sized according to the servitude to which they must serve connection.

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

The distribution and diameter of the channels 42 on the surface of the recess 40 of the holder 36 is comparable to the distribution and 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 receiving a modular arm 25 particular: its channels 42 are arranged to receive the elements of pipes 29, while the shoulder 41 of the recess 40 is arranged to support the inner end of the body 34 of the jacket 33.

Mounting easement and connection between the external casing 24 and the inner housing 23 of the jet 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 inner casing 23 of the turbojet 10 are mounted around the core of the turbojet engine 10, between the inner base 19 of arm 18 of the intermediate casing 17 and the exhaust casing 21. Easements, extending within the enclosure to be defined by the inner casing 23 and for connection with easement located outside of the housing external 24, are then connected to the portions 43 of the 42 channels to them for, 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 is performed, it is possible to place the panels 38 to their supports 36 and thereby form the inner casing not 23. The structural structural outer casing 24 is then mounted between the housing Intermediate 17 and the suspension ring 22.

The modular arm 25 is then slipped through an opening 49 oval provided for this purpose on the external casing 24, between the latter and the inner casing 23. The orifice 49 is located vertically above the platen 39, so that it is possible, just by inserting the arm 25 in the orifice 49, to come to insert the ends of the piping elements 29 in the portions 43 of the pipes 42 plate 39 intended to receive them, without need for access to the space defined by the inner casing 23 and the outer casing 24. The plate 26 of the arm 25 is then fixed releasably to the structural outer casing 24, for example through inserts, or any other suitable means. It may also be brazed, this However, that would make more difficult a dismounting operation of the arm 25.

Easement extending outside the outer casing 24, and to be connected to the aforementioned internal easement, may then be connected to the connection means 50 conduits 29 elements, the choice obviously place as a function of the easement already connected to each channeling member 29 through the plate 39.

Thus, thanks to the modular arm 25 of the invention, the coupling of easements between the structural outer casing 24 and the non-structural internal casing 23 is provided, the arm 25, in cooperation with the plate 39 and the orifice 49 of structural outer casing 24, here for the fitting of easements. this connector is assembled and disassembled easily without having to disassemble the particular internal connections made at the level of the side walls of the supports 36.

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

In the embodiment described of the jet engine 10 of the invention, the modular arm 25, its 28 holes of passage of piping elements 29, the elements of pipes and fittings 29 50, channels 42 and their connections 46 are calibrated for easements that allow connected. It goes without saying that all of these elements could be calibrated standard way, couplings 46, 50 or other fittings to enable a adaptation according to the type and caliber of easements to be connected.