Housing for return turbomachine

Abstract

Turbomachine casing (1), comprising a first channel in which a low-pressure compressor (3) and a high-pressure compressor (4) are arranged; a combustion chamber (5), a second channel in which a high-pressure turbine and a low-pressure turbine (7) are arranged; an annular casing (10) delimiting the first and second channels, in which the casing has: a fixing position, a first sliding position in which the casing is able to slide relative to the low-pressure compressor and the high-pressure turbine along the axial direction, and a second sliding position in which the casing is able to slide relative to the high-pressure compressor and the low-pressure turbine along the axial direction. Figure for the abbreviation: Fig. 1.

Description

Title of the invention: Housing for a return turbomachine Technical field

[0001] The present disclosure relates to a turbomachine casing. The casing of the present invention is particularly suitable for a so-called "return" turbomachine. Prior art

[0002] Optimizing thermodynamic flows within a turbomachine is an area that allows the fuel consumption of these turbomachines to be reduced. Taking these parameters into account has led to the design of so-called "return" turbomachines, as described in FR3080652. In this configuration, the high-pressure turbine is linked to the low-pressure compressor and the low-pressure turbine is linked to the high-pressure compressor.

[0003] Although this configuration is advantageous in terms of thermodynamic flows, the maintenance of such turbomachines is more complex due to the return structure. Indeed, the compressors and turbines of this type of turbomachine are more difficult to access. In order to carry out a maintenance operation on a turbine or a compressor, it may be necessary to dismantle a large number of other parts, which is costly in terms of resources and time.

[0004] There is therefore a need to improve return turbomachines and their maintenance methods to overcome, at least partially, the aforementioned disadvantages. Statement of the invention

[0005] The present disclosure relates to a turbomachine comprising a first vein in which a low pressure compressor and a high pressure compressor are arranged, supplied with compressed air by the low pressure compressor, a combustion chamber supplied with compressed air by the high pressure compressor, a second vein, radially external and concentric to the first vein, in which a high pressure turbine is arranged supplied with gas by the combustion chamber and a low pressure turbine supplied with gas by the high pressure turbine;an annular casing delimiting the first and second veins and being connected to the low pressure compressor, to the high pressure compressor, to the high pressure turbine and to the low pressure turbine, the low pressure compressor and the high pressure turbine being located in front of the casing in the axial direction and the high pressure compressor and the low pressure turbine being located behind the casing in the axial direction, in which the casing has a fixing position, a first sliding position in which the casing is able to slide relative to the low pressure compressor; pressure and the high pressure turbine along the axial direction, and a second sliding position in which the casing is capable of sliding relative to the high pressure compressor and the low pressure turbine along the axial direction.

[0006] In the present disclosure, the terms “axial”, “radial”, “tangential”, “internal”, “external” and their derivatives are defined in relation to the main axis of the turbomachine.

[0007] In particular, the term "axially" is understood relative to the main axis of the turbomachine. Furthermore, the terms "front" and "rear" relate to the axial direction. It is understood that the front of the turbomachine corresponds to the air inlet into the turbomachine, and the rear of the turbomachine corresponds to the air outlet.

[0008] This advantageous configuration makes it possible to greatly facilitate the maintenance of the turbomachine. Indeed, thanks to the casing of the invention, it is possible to selectively isolate the part in front of the casing or the part behind the casing. This therefore makes it possible to dismantle, for example, the high-pressure turbine without dismantling the low-pressure turbine and the high-pressure compressor. The maintenance operations of a turbomachine according to the invention are therefore less expensive and less time-consuming than these same operations for known turbomachines.

[0009] Consequently, the use of a casing according to the invention represents a saving of means and time.

[0010] In some embodiments, the casing is connected to the low pressure turbine and the high pressure turbine by bolted connections, and is connected to the low pressure compressor and the high pressure compressor by sliding connections capable of being released by sliding the casing in the axial direction.

[0011] This configuration is simple to manufacture and to incorporate into the turbomachine. In addition, this compromise offering simplicity nevertheless provides a casing sufficiently robust for the constraints applied to the turbomachine.

[0012] In some embodiments, the housing is configured to move from the attachment position to one of the first or second sliding positions by disassembling one of the bolted connections.

[0013] In this configuration, it is possible to move from the fixing position to one of the sliding positions by dismantling a single bolted connection. This therefore represents a saving in time and resources.

[0014] In some embodiments, the sliding links comprise a roller link.

[0015] This type of sliding connection represents a good compromise between compliance with specifications and cost.

[0016] In some embodiments, the housing comprises at least two distinct structural elements.

[0017] In this configuration, the mechanical properties of the casing are improved, so that the structural strength of the turbomachine is improved.

[0018] The present disclosure further relates to a method for maintaining a turbomachine according to one of the preceding aspects comprising the passage of the casing from the fixing position to one of the first or second sliding positions, the sliding of the casing in the axial direction, optionally until its removal from the turbomachine.

[0019] The above-mentioned characteristics and advantages, as well as others, will appear on reading the detailed description which follows, of exemplary embodiments of the proposed device and method. This detailed description refers to the attached drawings. Brief description of the drawings

[0020] The attached drawings are schematic and are intended primarily to illustrate the principles of the disclosure.

[0021] [Fig-1] [Fig.l] represents a sectional view of a turbomachine according to a first embodiment.

[0022] [Fig.2] [Fig.2] represents a detailed view of [Fig.l], illustrating a first sliding position.

[0023] [Fig.3] [Fig.3] represents the view of [Fig.2], illustrating a second sliding position. Description of the embodiments

[0024] In order to make the disclosure more concrete, an example of a device is described in detail below, with reference to the attached drawings. It is recalled that the invention is not limited to this example.

[0025] The turbomachine 1 comprises a low pressure compressor 3, a high pressure compressor 4, a combustion chamber 5, a high pressure turbine 6, and a low pressure turbine 7. These different elements of the turbomachine 1 can be installed inside a nacelle 20.

[0026] In the present disclosure, the terms “axial”, “radial”, “tangential”, “internal”, “external” and their derivatives are defined in relation to the main axis AA of the turbomachine 1.

[0027] In particular, the term “axially” is understood relative to the main axis XX of the turbomachine 1. Furthermore, the terms “front” and “rear” relate to the axial direction. It is understood that the front of the turbomachine 1 corresponds to the air inlet into the turbomachine, and the rear of the turbomachine corresponds to the air outlet.

[0028] As shown in [Fig.l], the turbomachine comprises a first vein in which the low pressure compressor 3 and the high pressure compressor 4 are arranged. In addition, the turbomachine comprises a second vein, radially external and concentric to the first vein, in which a high pressure turbine 6 and a low pressure turbine 7 are arranged.

[0029] A blower 2 is provided upstream of the low-pressure compressor 3, and for example inside the nacelle 20. In this case, downstream of the blower 2, the air flow is divided into a first part of the air flow (also called the primary flow) F1 passing through the low-pressure compressor 3 and entering the first vein, and a second part of the air flow (also called the secondary flow) F2 flowing in a bypass around the low-pressure compressor 3. The primary flow F1 is separated from the secondary flow F2 by two shells, an inner shell 11 and an outer shell 12. In addition, the secondary flow F2 is guided by the outer shell 12 and a casing shell 14 arranged around the outer shell 12.

[0030] The low pressure compressor 3 and the high pressure turbine 6 can be connected by a first rotary shaft A, while the high pressure compressor 4 and the low pressure turbine 7 can be connected by a second rotary shaft B. The blower 2 can also be connected to the first rotary shaft A, for example through a first reducer RL. The high pressure compressor 4 can comprise at least one axial stage 4a and a rotary stage 4b ​​arranged downstream of the rotary stage 4a and possibly connected to the latter through a second reducer R2.

[0031] In a known manner, when the turbomachine 1 is operating, the low-pressure compressor 3 compresses the air of the primary flow FL. The high-pressure compressor 4 is supplied with compressed air by the low-pressure compressor 3, and the combustion chamber 5 is supplied with compressed air by the high-pressure compressor 4. A fuel injector (not shown) injects fuel into the combustion chamber 5, this fuel being burned with the compressed air arriving in the combustion chamber 5. The hot gases resulting from this combustion leave the combustion chamber 5 and feed the high-pressure turbine 6. In the high-pressure turbine 6, the gases undergo a first expansion and drive the high-pressure turbine 6. The gases thus expanded then feed the low-pressure turbine 7. In the low-pressure turbine 7, the gases undergo a second expansion and drive the low-pressure turbine 7.

[0032] When the turbomachine 1 is operating, the high-pressure turbine 6 and the low-pressure turbine 7 drive the low-pressure compressor 3 and the high-pressure compressor 4. In particular, the fan 2 and the low-pressure compressor 3 can be driven by the high-pressure turbine 6 through the first rotating shaft A, while the axial 4a and radial 4b stages of the high-pressure compressor 4 are driven by the low-pressure turbine 7.

[0033] [Fig.2] represents a detailed view of [Fig.l], centered on an annular casing 100. The casing 100 delimits the first and second veins and is connected to the com low pressure compressor 3, to the high pressure compressor 4, to the high pressure turbine 6 and to the pressure pass turbine 7. The casing 100 can be formed from a single monobloc part or from an assembly of parts.

[0034] In other words, the casing 100 axially separates the low pressure compressor 3 and the high pressure compressor 4 at the level of the first vein and axially separates the high pressure turbine 6 and low pressure turbine 7 at the level of the second vein.

[0035] The casing 100 is connected to the high-pressure turbine 6 and to the low-pressure turbine 7 by bolted connections 101, 101'. For example, the bolted connections 101, 101' may comprise a plurality of bolts tightened on an annular contact portion provided, for the bolted connection 101, between the high-pressure turbine 6 and the casing 100. The bolted connections 101, 101' axially hold the casing 100. The present exemplary embodiment is based on bolted connections 101, 101'. However, any other reversible axial fixing method may be envisaged.

[0036] On the other hand, the casing 100 is connected to the low-pressure compressor 3 and to the low-pressure compressor 4 by sliding connections 102. In the present disclosure, a sliding connection 102 is a connection capable of being released by sliding in one direction. Here, the sliding connections 102 connecting the casing 100 to the compressors 3, 4 are released by sliding in the axial direction.

[0037] In the present example, the sliding connections 102 are roller connections.

[0038] The casing 100 has a fixing position in which the casing 100 is secured to the compressors 3, 4 and the turbines 6, 7. This position corresponds to the position of the casing 100 when the turbomachine 1 is in operation.

[0039] With reference to [Fig. 2], the casing 100 has a first sliding position. When the casing 100 is in the first sliding position, the casing 100 is able to slide relative to the low-pressure compressor 3 and the high-pressure turbine 6 in the axial direction. Under these circumstances, the high-pressure compressor 4 and the low-pressure turbine 7 also slide relative to the high-pressure turbine 6 and the low-pressure compressor 3.

[0040] The casing 100 moves from the fixing position to the first sliding position when the bolted connection 101 between the casing 100 and the high-pressure turbine 6 is removed. On the other hand, the bolted connection 101' between the casing 100 and the low-pressure turbine 7 is maintained. In the first sliding position, the axial retention of the casing 100 is therefore only at the rear, at the level of the low-pressure turbine 7. It is then possible to slide the casing 100 in the axial direction, towards the rear, thus undoing the sliding connections 102. It is then understood that no element of the turbomachine 1 comes into axial abutment when the casing 100 slides in the axial direction.

[0041] Furthermore, the low pressure turbine 7 and the high pressure compressor 4, which remain connected to the casing 100, also slide in the axial direction. The parts thus separated are delimited by dotted lines in [Fig.2].

[0042] Thus, during a maintenance operation of the turbomachine 1 targeting the low-pressure compressor 3 or the high-pressure turbine 6, the casing 100 is moved from the fixing position to the first sliding position, then the casing 100 is slid axially backwards until it is completely removed from the turbomachine 1. In these circumstances, the low-pressure turbine 7 and the high-pressure compressor 4, with the second rotary shaft B, or even the second reduction gear R2, which remain connected to the casing 100, are also removed from the turbomachine 1. The high-pressure turbine 6, the low-pressure compressor 3 and the first rotary shaft A therefore become accessible for a maintenance operation.

[0043] With reference to [Fig. 3], the casing 100 has a second sliding position. When the casing 100 is in the second sliding position, the casing 100 is able to slide relative to the high-pressure compressor 4 and the low-pressure turbine 7 in the axial direction. Under these circumstances, the low-pressure compressor 3 and the high-pressure turbine 6 also slide relative to the low-pressure turbine 7 and the high-pressure compressor 4.

[0044] The casing 100 moves from the fixing position to the second sliding position when the bolted connection 101' between the casing 100 and the low-pressure turbine 6 is removed. On the other hand, the bolted connection 101 between the casing 100 and the high-pressure turbine 6 is maintained. In the second sliding position, the axial retention of the casing 100 is only at the front, at the high-pressure turbine 6. It is then possible to slide the low-pressure turbine 7 and the high-pressure compressor 4 towards the rear, thus undoing the sliding connections 102.

[0045] It is noted that this movement is equivalent to a sliding of the casing 100 forward. Furthermore, it is then understood that no element of the turbomachine 1 comes into axial abutment during this sliding. The parts thus separated are delimited by dotted lines in [Fig.2].

[0046] Optionally, the low pressure turbine 7 and the high pressure compressor 4 are integral and can be slid into a single unit.

[0047] Thus, during a maintenance operation of the turbomachine 1 targeting the high-pressure compressor 4 or the low-pressure turbine 7, the casing 100 is moved from the fixing position to the second sliding position, then the high-pressure compressor 4 or the low-pressure turbine 7 are slid axially backwards until they are completely removed from the turbomachine 1. Under these circumstances, the low-pressure turbine 7 and the high-pressure compressor 4 therefore become accessible for a maintenance operation.

[0048] Although the present invention has been described with reference to examples of rea specific embodiments, it is obvious that modifications and changes may be made to these examples without departing from the general scope of the invention as defined by the claims. In particular, individual features of the various illustrated / mentioned embodiments may be combined in additional embodiments. Therefore, the description and drawings should be considered in an illustrative rather than restrictive sense.

[0049] It is also obvious that all the characteristics described with reference to a method are transposable, alone or in combination, to a device, and conversely, all the characteristics described with reference to a device are transposable, alone or in combination, to a method.

Claims

Claims

1. Turbomachine (1), comprising: a first vein in which a low pressure compressor (3) and a high pressure compressor (4) are arranged, supplied with compressed air by the low pressure compressor (3); a combustion chamber (5) supplied with compressed air by the high pressure compressor (4), a second vein, radially external and concentric to the first vein, in which a high pressure turbine (6) is arranged, supplied with gas by the combustion chamber (5) and a low pressure turbine (7) supplied with gas by the high pressure turbine (6);an annular casing (10) delimiting the first and second veins and being connected to the low pressure compressor (3), to the high pressure compressor (4), to the high pressure turbine (6) and to the low pressure turbine (7), the low pressure compressor (3) and the high pressure turbine (6) being located in front of the casing (100) in the axial direction and the high pressure compressor (4) and the low pressure turbine (7) being located behind the casing (100) in the axial direction, in which the casing has: a fixing position, a first sliding position in which the casing (100) is able to slide relative to the low pressure compressor (3) and the high pressure turbine (6) along the axial direction, and a second sliding position in which the casing (100) is able to slide relative to the high pressure compressor (4) and the low pressure turbine (7) along the axial direction.;

2. Turbomachine according to claim 1, in which the casing (100) is connected to the low pressure turbine (7) and to the high pressure turbine (6) by bolted connections (101, 101'), and is connected to the low pressure compressor (3) and to the high pressure compressor (4) by sliding connections (102) capable of being released by sliding the casing in the axial direction.

3. A turbomachine according to claim 2, wherein the casing (100) is configured to move from the fixing position to one of the first or second sliding positions by dismantling one of the bolted connections (101, 101').

4. Turbomachine according to one of claims 2 or 3, in which the sliding connections (102) comprise a roller connection.

5. Turbomachine according to one of claims 1 to 4, in which the casing (100) comprises at least two distinct structural elements.

6. Method for maintaining a turbomachine (1) according to one of the preceding claims comprising the passage of the casing (100) from the fixing position to one of the first or second sliding positions, the sliding of the casing (100) in the axial direction, optionally until its removal from the turbomachine (1).

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