TURBOMACHINE OIL TANK

Abstract

The invention relates to a turbojet engine oil tank (30). The tank (30) comprises a main chamber and an envelope (34) delimiting the main chamber, and a fixing portion (44) for example with fixing flanges (46) and a branch (48). The envelope (34) features in particular an envelope part (34) relative to which the fixing portion (44) projects. The envelope part (34) and the fixing portion (44) are produced by layered additive fabrication so as to be in one piece. The invention also relates to a method of fabricating an oil tank (30).

Claims

1. An oil tank for a turbojet engine, the oil tank comprising a main chamber, an envelope delimiting the main chamber, and a fixing portion; the envelope comprising an envelope part from which the fixing portion projects towards the exterior of the main chamber; the envelope part and the fixing portion being integrally formed.

2. The oil tank in accordance with claim 1, wherein the fixing portion comprises a first fixing flange projecting relative to the partition and a second fixing flange projecting relative to the envelope, the envelope comprising a base forming an increased thickness on the envelope part of the envelope at the level of at least one or each flange.

3. The oil tank in accordance with claim 2, wherein the envelope features a thinner first zone between the two fixing flanges and/or opposite the two fixing flanges.

4. The oil tank in accordance with claim 2, wherein at least one or each of the two fixing flanges comprises a curved free edge.

5. The oil tank in accordance with claim 2, wherein at least one or each des of the two fixing flanges has a triangular and asymmetrical shape.

6. The oil tank in accordance with claim 1, wherein it comprises an internal stiffener extending the fixing portion toward the main chamber; said internal stiffener, the envelope part of the envelope and the fixing portion being integrally formed.

7. The oil tank in accordance with claim 1, wherein the envelope has an end with a second thinner zone, said end being a lower end of the oil tank.

8. The oil tank in accordance with claim 1, wherein the envelope comprises a reinforcing belt or a reinforcing belt portion, the reinforcing belt or the reinforcing belt portion, the envelope part and the fixing portion are integrally produced.

9. The oil tank in accordance with claim 1, wherein it comprises at least one equipment including at least one of the group consisting in a vent, a de-aerator, a probe support, and a strainer; each equipment, the envelope part and the fixing portion being integrally produced.

10. The oil tank in accordance with claim 1, wherein the envelope part is a first envelope part, the envelope further comprising a second envelope part produced by layered additive fabrication and welded to the first envelope part by a weld.

11. The oil tank in accordance with claim 10, wherein the main chamber features a principal elongation, the weld being generally perpendicular to said principal elongation.

12. The oil tank in accordance with claim 10, wherein the first envelope part forms a bottom of the oil tank and/or the second envelope part forms a lid of the oil tank.

13. A turbojet engine comprising a supporting casing and an oil tank, the oil tank comprising a fixing portion, a main chamber, an envelope delimiting the main chamber and comprising an envelope part from which the fixing portion projects outside the main chamber, the fixing portion being fixed to the supporting casing, the material of the envelope part and of the fixing portion exhibit an integral stack of layers with a layer stacking direction that is transverse or perpendicular to the thickness of the envelope.

14. The turbojet engine in accordance with claim 13, wherein it comprises an oil circuit with a bearing and/or a heat exchanger, said oil circuit communicating with the oil tank.

15. The turbojet engine in accordance with claim 13, wherein in that the supporting casing comprising fixing means fixed to the fixing portion isostatically.

16. A method of fabricating an oil tank of a turbojet engine, the method comprising the steps: design of an oil tank with a main chamber, an envelope delimiting the main chamber, and a fixing portion; the envelope comprising a part from which the fixing portion projects outwards; layered additive fabrication of the envelope part and of the fixing portion so as to be one-piece.

17. The method according to claim 16, wherein during the layered additive fabrication step the envelope part is produced sector by sector including a first sector with a concave surface and a second sector with a convex surface; during the layered additive fabrication step the convex surface is fabricated in the concave surface.

18. The method according to claim 16, wherein the envelope comprises a third part formed by a metal plate of constant thickness welded to another envelope part.

19. The method according to claim 18, wherein it further comprises a welding step of the envelope part and of the third part to one another.

20. The method according to claim 16, wherein the layered additive fabrication is based on powder, said powder comprising at least one of the group consisting titanium powder and Inconel powder.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0044] FIG. 1 shows a turbojet engine according to the invention.

[0045] FIG. 2 is a sketch of a turbojet engine casing supporting a tank according to the invention.

[0046] FIG. 3 shows an oil tank envelope junction conforming to the invention.

[0047] FIG. 4 is a diagram of the method of fabricating the oil tank according to the invention.

[0048] FIG. 5 shows a batch of envelope sectors produced by additive fabrication in accordance with the invention.

DESCRIPTION OF EMBODIMENTS

[0049] The directions referred to in the following description correspond to the normal assembly direction. The interior of the tank refers to its chamber and the exterior to its environment.

[0050] FIG. 1 is a simplified representation of an axial turbomachine. In this specific instance this is a turbofan. The turbojet engine 2 comprises a first compression stage, termed the low-pressure compressor 4, a second compression stage, termed the high-pressure compressor 6, a combustion chamber 8 and one or more turbine stages 10. In operation, the mechanical power of the turbines 10 transmitted via shafts 24 to the rotor 12 drives the two compressors 4 and 6. The latter include a plurality of rows of rotor blades associated with rows of stator blades. The rotation of the rotor about its rotation axis 14 therefore makes it possible to generate a flow of air and to compress the latter progressively up to the point of entry into the combustion chamber 8.

[0051] An inlet fan 16 commonly referred to as a blower is coupled to the rotor 12. It generates an air flow that is divided into a primary flow 18 and a secondary flow 20 through an annular duct. An epicyclic gear 22 can reduce the rotation speed(s) of the blower 16 and/or of the low-pressure compressor 4 relative to the associated turbine 10.

[0052] The rotor 12 includes a plurality of concentric shafts 24 that are articulated in a rotary manner via bearings 26. Cooling and/or lubrication are provided by an oil circuit. That circuit can be specific to the turbojet engine 2. The oil circuit can also comprise a heat exchanger 28 for cooling the oil, the temperature of which can exceed 200 C. and even 230 C. in some cases. These temperatures make the corrosive oil more aggressive to the seals and to polymer parts in general. Here the position and the orientation of the tank 30 are purely illustrative. In practice, this tank 30 can be fixed to the casing of the turbojet engine 2. For example, it can be connected to the casing of the blower 16, to the casing of the low-pressure compressor 4 or to the casing of the high-pressure compressor 6. Such installation tends to add thermal stresses and direct exposure to the vibrations of the turbojet engine, notably in the event of loss of a blower blade.

[0053] FIG. 2 shows the fixing of the oil tank 30 to a supporting casing 32 of the turbojet engine. In this instance this can be the casing 32 of the low-pressure compressor that also supports an annular row of concentric blades 33. The turbojet engine can be that from FIG. 1.

[0054] In order to increase its usable volume, the tank 30 is essentially elongate whilst espousing the exterior curvature of the supporting casing 32. This compactness enables installation between two closely spaced tubular walls. In operation, the tank 30 is partially filled with oil, or to be more precise with a mixture of oil, air and impurities, such as abrasive metal particles released through wear.

[0055] The tank 30 features an envelope 34 with for example a lower part 36 or first part 36 and an upper part 38 or second part 38. These parts (36; 38) can be connected by a weld 40 or via a central part 42 of the envelope 34, also called the third part 42, which connects the lower part 36 to the upper part 38 via the welds 40. Each weld 40 can form a closed loop around the general lengthwise axis of the tank. Thanks to its parts (36; 38; 42), the envelope 34, a true skin, defines a main chamber (not visible) forming an oil storage volume. The chamber is an internal chamber intended to be filled. The description of the main chamber as principal is to be understood in the sense that it is the largest receptacle of the tank 30.

[0056] Regarding mounting on the supporting casing 32, the tank 30 features a fixing portion 44 projecting relative to the envelope 34, for example toward the casing 32. This fixing portion 44 can comprise one or at least two fixing flanges 46 (a flange that is visible conceals the other one). These flanges 46 can be secured to the lower part 36. The flanges 46 can be connected to thicker portions of the partition 34 forming reinforced and separated bases. For its part, the upper part 38 can feature a fixing branch 48, for example connected to the casing 32 via an arm and ball joint 50. The branch 48 and the fixing flanges 46 can be connected to the casing 32 so as to enable isostatic fixing. In other words they respectively and uniquely eliminate one, two and three degrees of freedom when they are fixed to the complementary fixing means of the casing 32. The six degrees of freedom of the tank are therefore fixed. This tends to reduce the effects of expansion and limits internal stresses.

[0057] The tank 30 can comprise other equipments. For example, it can comprise inlet and outlet orifices (not shown). A stopper 52 can be placed in the upper part 38, for example at its top. A level viewing window 54 can be formed in the upper part 38. A deserter, a vent and/or a de-oiler (not shown) can be associated with the tank 30.

[0058] The tank 30 is advantageously produced by additive fabrication, at least in part. For example at least one part, such as the first part 36 and possibly the second part 38, are produced separately by additive fabrication. They could be produced together in order to be in one piece. The third part 42 is optionally produced by additive fabrication. Alternatively, it is formed of rolled sheet metal, for example of constant thickness. Its thickness can be less than the thickness of the envelope 34 in the first and second parts. The thickness of the envelope 34 can vary between 2 mm and 0.5 mm or from 1.5 mm to 1 mm.

[0059] Moreover, the fixing flanges 46 can be in one piece with the lower part 36 of the envelope 34 and in particular produced by additive fabrication with the envelope 34 in order to improve the connection between each flange and the envelope 34. The addition of connecting spokes there further increases the transmission of forces and reduces the risk of fatigue cracks appearing. The tank 30 optionally features a belt 56 on the outside. The latter connects the flanges 46 and forms a localized increased thickness on the envelope 34.

[0060] Each fixing flange 46 can be generally triangular. The sides facing the casing 32, i.e. toward the concavity of the curved shape of the tank 30, can be curved. This makes them more slender and enables them to be lengthened at the same time as preserving their lightness. Moreover, the fixing ends of the fixing portion 44 are spaced from one another in order to increase the stability of the tank 30.

[0061] FIG. 3 shows in section a zone in which the envelope 34 forms a junction 58 that connects a fixing flange 46 to an internal stiffener 60 extending inside the main chamber 62. Although only one flange 46 is shown, the present teaching can be applied to each flange 46 of the tank.

[0062] The envelope 34 becomes an intermediary between the stiffener 60 and the flange 46 that extend away from one another. The concave sides 64 of the triangle that the flange 46 forms are shown; they can become tangents to the envelope 34. A fixing hole 65 can be seen in the flange 46.

[0063] FIG. 4 is a diagram of the method of fabrication of an oil tank such as that shown in the previous figures.

[0064] The method may comprise the following steps, possibly carried out in the following order:

[0065] (a) design 100 of a turbojet engine oil tank allowing for a service life of at least 25 years and operating stresses;

[0066] (b) layered additive fabrication 102 based on powder of at least one, or at least two or each envelope part and the fixing portion;

[0067] (c) welding 104 the parts to one another;

[0068] (d) finishing 106 the tank, including sandblasting and treatment of the envelope; this finishing step (d) 106 remaining entirely optional.

[0069] During the design step (a) 100 the various sectors are defined. These can be angular sectors. Combining them can enable production of the first envelope part and/or the second envelope part.

[0070] The additive fabrication step (b) 102 can be one of fabrication by scanning a powder bed with an electron beam or a laser beam. The additive fabrication step (b) 102 is effected in a pocket on a mobile plate of a machine on which the powder bed is renewed and then precompacted before solidification of the various superposed layers. During this step the powder can be preheated, for example to 700 C. The raw powder can have a particle size of 20 m.

[0071] FIG. 5 is a sketch of an intermediate result of the additive fabrication step (c) of the method from FIG. 4. It shows a batch of envelope sectors 66 produced simultaneously in an additive fabrication machine. The sectors 66 are shown in section.

[0072] This batch forms a block the size of which optimizes the occupancy of the fabrication pocket of the additive fabrication machine in order to increase the production rate. In this block the sectors 66 are interleaved with one another. These sectors 66 have concave surfaces and convex surfaces. In order to improve compactness, the convex surfaces are in the concave surfaces and espouse one another. The flanges 46 and the stiffener 60 can be fabricated toward the exterior of the block.

[0073] The sectors 66 can be eighths of a sphere 68; where applicable with a vertical extension 70.