ASSEMBLY FOR TURBOMACHINE WITH A RADIALLY MOUNTED STRUCTURAL AIR-OIL INTERCOOLER IN A HOUSING

Abstract

Assembly (1) for a turbomachine comprising a housing (2) having an annular surface (2a) framed by an upstream flange (2b) and a downstream flange (2c) and a housing (2d), and an air-oil heat exchanger (3) mounted in the housing (2d) of the housing (2), the heat exchanger (3) comprising an inner plate (3a), an outer plate (3b) and two side plates (3c, 3d). The housing (2) includes an opening machined in the annular surface (2a) allowing radial mounting and dismounting of the heat exchanger (3), the assembly (1) also including means for reinforcing the heat exchanger (3) and means for securing the heat exchanger (3) to the housing (2). Figure for the abbreviation: Fig 1

Description

Title of the invention: ASSEMBLY FOR TURBOMACHINE WITH A STRUCTURING AIR-OIL EXCHANGER MOUNTS RADIALLY IN A HOUSING technical field

[0001] The invention relates to the technical field of assembling air-oil heat exchangers with a turbomachine casing. The invention relates in particular to the air-oil heat exchanger and the intermediate compressor casing located in the turbomachine's flow path.

[0002] Today, the air-oil heat exchangers are mounted in the turbomachine's flow via an axial mounting inside the compressor intermediate housing. The entire air-oil heat exchanger assembly and the compressor intermediate housing are surrounded within the turbomachine by components that must be removed before the air-oil heat exchangers can be accessed. Indeed, the entire air-oil heat exchanger assembly and the compressor intermediate housing are surrounded by a set of engine parts such as fairings.

[0003] This configuration leads to accessibility and maintainability problems for the air-oil heat exchangers in the turbomachine. The current dismantling time for all the air-oil heat exchangers is generally around four days, which is not optimal.

[0004] Climate change is a major concern for many legislative and regulatory bodies worldwide. Indeed, various restrictions on carbon emissions have been, are being, or will be adopted by various states. In particular, an ambitious standard applies to both new types of aircraft and those already in service, requiring the implementation of technological solutions to bring them into compliance with current regulations. Civil aviation has been actively working for several years now to contribute to the fight against climate change.

[0005] Technological research efforts have already led to very significant improvements in the environmental performance of aircraft. The Applicant takes into account the factors impacting all phases of design and development in order to obtain aeronautical components and products that are less energy-intensive, more environmentally friendly, and whose integration and use in civil aviation have moderate environmental consequences, with the aim of improving the energy efficiency of aircraft.

[0006] Consequently, the Applicant is constantly working to reduce its negative climate impact through the use of methods and the operation of processes virtuous development and manufacturing that minimizes greenhouse gas emissions to the minimum possible in order to reduce the environmental footprint of its activity.

[0007] This sustained research and development work focuses on new generations of aircraft engines, the lightening of aircraft, in particular through the materials used and lighter on-board equipment, the development of the use of electrical technologies to provide propulsion, and, as essential complements to technological progress, aviation biofuels.

[0008] To this end, the invention is the result of technological research aimed at significantly improving aircraft performance and, in this sense, contributes to reducing the environmental impact of aircraft. Description of the invention

[0009] The present invention aims to overcome the aforementioned problems by optimizing the assembly and disassembly time of air-oil heat exchangers in a crankcase.

[0010] The invention therefore relates to a turbomachine assembly comprising a housing with an annular surface framed by an upstream flange and a downstream flange and a recess, and an air-oil heat exchanger mounted in the recess of the housing, the heat exchanger comprising an inner plate, an outer plate, and two side plates. The housing includes an opening machined in the annular surface allowing for the radial mounting and dismounting of the heat exchanger. The assembly also includes means for reinforcing the heat exchanger and means for securing the heat exchanger to the housing.

[0011] Advantageously, the housing includes guide grooves for the heat exchanger, the grooves being radially machined on at least one internal surface of the housing.

[0012] According to one embodiment, the means for fixing the exchanger to the housing include axial screws fixing the exchanger to the upstream flange and the downstream flange of the housing and radial screws fixing the exchanger to the annular surface of the housing.

[0013] Advantageously, the means for reinforcing the exchanger include a structural plate.

[0014] According to a first embodiment, the structural plate is directly integrated into the external plate of the exchanger.

[0015] According to a second embodiment, the structural plate is a plate independent of the exchanger and is fixed to the casing by means of fixing the structural plate to the casing.

[0016] Advantageously, the means for fixing the structural plate to the housing include axial screws fixing the structural plate to at least one of the upstream and downstream flanges of the housing.

[0017] Preferably, the housing is an intermediate compressor housing.

[0018] The invention also relates to an aircraft turbomachine comprising an assembly as defined above.

[0019] The invention further relates to a method for assembling an assembly for an aircraft turbomachine as defined above. The assembly method comprises a step of radially inserting the heat exchanger into the casing through the opening in the casing and a step of securing the heat exchanger to the casing by means of the heat exchanger-to-casing fastening means.

[0020] The invention also relates to a method for dismantling a turbomachine assembly as defined above. The dismantling method comprises a step of separating the heat exchanger from the housing by removing the means for attaching the heat exchanger to the housing and a step of radially withdrawing the heat exchanger from the housing through an opening in the housing. Brief description of the drawings

[0021] Other objects, features and advantages of the invention will become apparent from the following description, given solely by way of non-limiting example and made with reference to the accompanying drawings in which:

[0022] - Figure [Fig. 1] is a perspective view of the assembly comprising a housing compressor intermediate and an air-oil heat exchanger;

[0023] - Figure [Fig.2] is a perspective view of an intermediate housing of compressor;

[0024] - Figure [Fig.3] is a top view of the assembly comprising a housing compressor intermediate and an air-oil heat exchanger;

[0025] - Figure [Fig.4] is a perspective view of an air-oil heat exchanger comprising a structural plate;

[0026] - Figure [Fig. 5] is a perspective view of the assembly comprising a housing Intermediate compressor, an air-oil heat exchanger, and a structural plate; and

[0027] - Figure [Fig. 6] is an exploded view of the assembly comprising a housing compressor intermediate, an air-oil heat exchanger and a structural plate. Detailed description

[0028] Figure 1 shows a turbomachine assembly designated by reference numeral 1, comprising an intermediate compressor casing 2 and an air-oil heat exchanger 3 mounted in the intermediate compressor casing 2. The casing 2 comprises an annular surface 2a, axially framed by an upstream flange 2b and a downstream flange 2c, and a housing 2d. The air-oil heat exchanger 3 comprises an inner plate 3a, an outer plate 3b, and two side plates 3c and 3d, and is mounted in the housing 2d of the casing 2.

[0029] Fig. 2 illustrates the intermediate compressor housing 2. It further includes an opening 4 machined in the annular surface 2a allowing radial mounting and dismounting of the air-oil exchanger 3 along an axis R.

[0030] The housing 2d of the casing 2 includes a sealing surface 5 positioned inside the casing 2, two radial lateral surfaces 6, 7 and then an external surface including the opening 4. The casing 2 includes guide grooves 8 allowing precise positioning of the heat exchanger 3, radially machined on the lateral surfaces 6, 7 of the housing 2d.

[0031] Indeed, the air-oil heat exchanger 3 is inserted radially into the housing 2 via the opening 4, the inner plate 3a of the heat exchanger 3 being positioned in contact with the sealing surface 5 of the housing 2d and the outer plate 3b of the heat exchanger 3 being positioned so as to close the opening 4 of the outer surface of the housing 2d. The outer plate 3b of the heat exchanger 3 is substantially at the same level as the annular surface 2a of the housing 2. The side plates 3c, 3d of the heat exchanger 2 are positioned against the side surfaces 6, 7 of the housing 2d.

[0032] The sealing surface 5 of the housing 2 is thus arranged axially between the internal plate 3a of the exchanger 3 and the surrounding components and prevents oil and air leaks from the exchanger 3.

[0033] Assembly 1 also includes means for fixing the heat exchanger 3 to the housing 2, as illustrated in [Fig. 3]. Indeed, the means for fixing the heat exchanger 3 to the housing 2 include axial screws 9 for fixing the heat exchanger 3 to the upstream flange 2b and the downstream flange 2c of the housing 2 and radial screws 10 for fixing the heat exchanger 3 to the annular surface 2a of the housing 2.

[0034] The outer plate 3b of the heat exchanger 3 includes rims 11, 12 at its axial ends, allowing the heat exchanger 3 to be fixed to the housing 2. The rims 11, 12 are surfaces that extend outwards from the housing 2 along the radial axis R. Specifically, a first rim 11 is fixed via axial screws 9, allowing the heat exchanger 3 to be fixed to the upstream flange 2b of the housing 2, and a second rim 12 is fixed via axial screws 9, allowing the heat exchanger 3 to be fixed to the downstream flange 2c of the housing 2. The heat exchanger 3 also includes a third rim 13 extending along the axis R from an axial end of the inner plate 3a. This third border 13 has openings 14 allowing the oil supply connection of the exchanger 3. The third border 13 and the oil supply openings 14 are visible in [Fig.1].

[0035] Assembly 1 further includes means for reinforcing the exchanger 3. Indeed, the air-oil exchanger 3 is designed with reinforcing means in order not to degrade the mechanical characteristics of the intermediate compressor casing 2. Thus, according to one embodiment, the external plate of the exchanger 3 is reinforced.

[0036] According to the embodiment illustrated in the figures, the means for reinforcing the exchanger 3 comprise a structural plate 15 independent of the exchanger 3 and fixed to the casing 2 by means of fixing the structural plate 15 to the casing 2.

[0037] As illustrated in [Fig.4], the structural plate 15 is a plate placed on the external plate 3b of the exchanger 3 which strengthens it and thus allows the continuity of the annular surface 2a of the casing 2. This design provides rigidity to the assembly 1.

[0038] The structural plate 15 includes a rim 16 at one of its axial ends allowing the structural plate 15 to be fixed to the housing 2. The rim 16 extends outwards from the housing 2 along the axis R.

[0039] Figure 5 illustrates assembly 1 comprising the housing 2, the heat exchanger 3 and the plate structural 15. The means for fixing the structural plate 15 to the housing 2 include axial screws 17 fixing the edge 16 of the structural plate 15 to the upstream flange 2b of the housing 2.

[0040] Of course, we do not depart from the scope of the invention when assembly 1 has a different composition. The edge 16 of the structural plate 15 can be designed to be fixed to the downstream flange 2c of the housing 2. According to another embodiment, the structural plate 15 comprises two edges at its axial ends, allowing said structural plate 15 to be fixed to the upstream flanges 2b and downstream flanges 2c of the housing 2.

[0041] According to another embodiment, the structural plate 15 is directly integrated into the outer plate 3b of the heat exchanger 3. Indeed, the outer plate 3b of the heat exchanger 3 can be directly reinforced. In this case, the outer plate 3b of the heat exchanger 3 provides the necessary rigidity to the assembly 1 so that the housing 2 retains its mechanical properties.

[0042] Figure 6 illustrates the assembly of set 1 comprising the housing 2, the heat exchanger 3 and the structural plate 15.

[0043] The assembly method for unit 1 comprises a first step of radially inserting the heat exchanger 3 into the compressor intermediate housing 2 along axis R. The heat exchanger 3 is inserted into the housing 2 through the opening 4 in the outer surface of the housing 2d of the housing 2. The guide grooves 8 in the housing 2d allow the heat exchanger 3 to be guided into a precise position. When the heat exchanger 3 is positioned in the housing 2d of the housing 2, the openings 14 in the heat exchanger 3 are accessible to allow the oil supply connection.

[0044] Once the heat exchanger 3 is positioned in the housing 2d of the casing 2, the method includes a second step of securing the heat exchanger 3 to the casing 2 by means of the heat exchanger 3 to the casing 2 fastening means. Indeed, the The edges 11,12 at the ends of the outer plate 3b of the exchanger 3 are fixed to the upstream flanges 2b and downstream flanges 2c of the casing 2 by means of the axial screws 9 and the outer plate 3b of the exchanger 3 is fixed to the annular surface 2a of the casing 2 by means of the radial screws 10.

[0045] Finally, the method includes a third step of fixing the structural plate 15 onto the housing 2. The rim 16 located at an axial end of the structural plate 15 is fixed to the upstream flange 2b of the housing 2 by means of the axial screws 17.

[0046] The disassembly method of assembly 1 includes a first step of separating the structural plate 15 and the housing 2 by removing the means of fixing the structural plate 15 to the housing 2. The axial screws 17 of the structural plate 15 are removed and the structural plate 15 is also removed.

[0047] The disassembly process for assembly 1 then includes a step of separating the heat exchanger 3 from the housing 2, in which the means for attaching the heat exchanger 3 to the housing 2 are removed. The axial screws 9 and radial screws 10 of the heat exchanger 3 are removed.

[0048] The dismantling process of assembly 1 finally includes a third step of removing the heat exchanger 3 from the housing 2. The heat exchanger 3 is thus radially released from the housing 2d of the housing 2 along the axis R.

[0049] The invention also covers, in general, any housing of assembly 1.

Claims

Demands

1. Assembly (1) for a turbomachine comprising a housing (2) including an annular surface (2a) framed by an upstream flange (2b) and a downstream flange (2c) and a housing (2d), and an air-oil heat exchanger (3) mounted in the housing (2d) of the housing (2), the heat exchanger (3) including an inner plate (3a), an outer plate (3b) and two side plates (3c, 3d), characterized in that the housing (2) includes an opening (4) machined in the annular surface (2a) allowing the radial mounting and dismounting of the heat exchanger (3), the assembly (1) also including means for reinforcing the heat exchanger (3) and means for fixing the heat exchanger (3) to the housing (2).

2. Assembly (1) according to claim 1, wherein the housing (2) includes guide grooves (8) for the heat exchanger (3), the grooves (8) being radially machined on at least one internal surface (6, 7) of the housing (2d).

3. Assembly (1) according to any one of claims 1 and 2, wherein the means for fixing the heat exchanger (3) to the housing (2) comprise axial screws (9) fixing the heat exchanger (3) to the upstream flange (2b) and the downstream flange (2c) of the housing (2) and radial screws (10) fixing the heat exchanger (3) to the annular surface (2a) of the housing (2).

4. Assembly (1) according to any one of claims 1 to 3, wherein the means for reinforcing the exchanger (3) include a structural plate (15).

5. Assembly (1) according to claim 4, wherein the structural plate (15) is directly integrated into the external plate (3b) of the exchanger (3).

6. Assembly (1) according to claim 4, wherein the structural plate (15) is a plate independent of the exchanger (3) and is fixed to the casing (2) by means of fixing the structural plate (15) to the casing (2).

7. Assembly (1) according to claim 6, wherein the means for fixing the structural plate (15) to the housing (2) comprise axial screws (17) fixing the structural plate (15) to at least one of the upstream and downstream flanges (2b, 2c) of the housing (2).

8. Assembly (1) according to any one of claims 1 to 7, wherein the housing (2) is an intermediate compressor housing.

9. Aircraft turbomachine, comprising an assembly (1) according to any one of claims 1 to 8.

10. Method of mounting an assembly (1) for an aircraft turbomachine according to any one of claims 1 to 9, characterized in that it comprises a step of radially inserting the exchanger (3) into the casing (2) via the opening (4) of the casing (2) and a step of fixing the exchanger (3) to the casing (2) via the means of fixing the exchanger (3) to the casing (2).

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