Turbine seal ring

Abstract

The application relates to an assembly for a turbine engine (1), comprising: a first rotor (2) rotatable about a longitudinal axis (X-X) of the turbine engine (1), the first rotor (2) comprising a first arm (26); a second rotor (3) rotatable about the longitudinal axis (X-X) and comprising a second arm (36); a first seal ring (4) centred on the longitudinal axis (X-X), the first seal ring being arranged radially outside the first arm (26) and comprising a first radial flange (40) fixedly mounted between the first arm (26) and the second arm (36); and a second seal ring (5) separate from the first seal ring (4), the second seal ring being centred on the longitudinal axis (X-X) and arranged radially outside the second arm (36), the second seal ring (5) comprising a first portion (51) designed to come into contact with the second rotor (3) and a second portion (52) separate from the first portion (51) and designed to come into contact with the first seal ring (4).

Description

Technical Field

[0001] This invention relates to a turbine for a turbine.

[0002] More specifically, the present invention relates to a sealing ring for a stator component arrangement facing a nozzle of a turbine turbine. Background Technology

[0003] Documents FR 3 019 584 and FR 3 077 327 describe a ring arranged between the two rotors of a turbine, facing the stator component of the turbine nozzle, to ensure a seal between different chambers of the turbine's flow path through the engagement of the scraping portion of the sealing ring with the wear-resistant portion of the nozzle.

[0004] The ring includes at least one arm that supports abutting a rotor to prevent axial movement of blades added to the rotor (“L”-shaped ring). In some cases, the ring includes two arms, each of which supports abutting one rotor (“Y”-shaped ring). In any case, the ring is mounted with significant axial clamping at one or more arm supports abutting one or more rotors.

[0005] In addition, the ring allows air to circulate and ventilate the blades of one or more rotors.

[0006] Finally, one or more arms of the ring can ensure thermal protection for one or more rotors, thereby protecting one or more rotors from the effects of hot air flowing within the flow path.

[0007] This type of ring is not entirely satisfactory.

[0008] In practice, the axial clamping of the ring is performed with a force that would destroy the ring's mechanical strength. Furthermore, the installation becomes more complex.

[0009] Furthermore, despite this high-strength axial clamping, gaps still occur between one or more arms and one or more rotors, and at the locations where one or more arm supports abut against one or more rotors, which disrupts the ventilation circuit of the rotor blades.

[0010] Finally, the thermal expansion of one or more arms degrades the connection between the ring and one or more rotors.

[0011] Therefore, in this respect, it is necessary to overcome at least one drawback of the existing technology. Summary of the Invention

[0012] One object of the present invention is to improve the mechanical strength of the sealing ring of the turbine.

[0013] Another objective of this invention is to limit leakage within the ventilation circuit of the turbine blades.

[0014] Another object of the present invention is to facilitate the installation of the sealing ring of the turbine.

[0015] Therefore, according to a first aspect of the present invention, a component for a turbine is provided, the component comprising:

[0016] - The first rotor, which is rotatable about the longitudinal axis of the turbine, includes a first arm.

[0017] - A second rotor, which is rotatable about a longitudinal axis and includes a second arm.

[0018] - A first sealing ring, centered on the longitudinal axis, is arranged radially outside the first arm and includes a first radial flange fixedly mounted between the first arm and the second arm.

[0019] - A second sealing ring, which is different from the first sealing ring, is centered on the longitudinal axis and arranged radially outside the second arm. The second sealing ring includes a first part and a second part that is different from the first part. The first part is configured to contact the second rotor, and the second part is configured to contact the first sealing ring.

[0020] In this assembly, the thermal expansion of the second sealing ring exerts less pressure on the first radial flange of the first sealing ring, which improves the mechanical strength of the first sealing ring and thus increases its lifespan. Furthermore, the axial clamping of the first sealing ring to the first rotor and the axial clamping of the second sealing ring to the second rotor are reduced. In fact, the dimensions of the first and second sealing rings are reduced compared to single sealing rings known in the prior art. This allows for limiting clearance between the first and second sealing rings, and also limits clearance between the second sealing ring and the second rotor. Therefore, leakage within the turbine blade ventilation circuit is reduced. Moreover, the reduced axial clamping lowers the mechanical stress within the first and second sealing rings, which improves their mechanical strength and thus extends their lifespan. Finally, the installation of the first and second sealing rings is performed in a manner similar to that of sealing rings known in the prior art, making it easy to integrate the assembly described above into existing turbines.

[0021] Advantageously, but optionally, the components according to the invention include at least one of the following features, either individually or in combination:

[0022] The second rotor has a first inner axial surface, and the second sealing ring has a first outer axial surface. The first outer axial surface is positioned facing the first inner axial surface and at a distance from it, such that the first outer axial surface is configured to contact the first inner axial surface when the second sealing ring thermally expands.

[0023] - The first sealing ring has a second inner axial surface, and the second sealing ring has a second outer axial surface. The second outer axial surface is positioned facing the second inner axial surface and spaced apart from it by a distance, such that the second outer axial surface is configured to contact the second inner axial surface when the second sealing ring undergoes thermal expansion.

[0024] The first part has a groove, and the assembly also includes a seal disposed within the groove.

[0025] One of the second arm and the second sealing ring includes a lug, and the other of the second arm and the second sealing ring includes a notch. The lug is configured to engage with the notch to prevent circumferential rotation of the second sealing ring relative to the second rotor.

[0026] - An orifice is provided in the second sealing ring to allow fluid to flow between a first chamber arranged radially inside the second sealing ring and a second chamber arranged radially outside the second sealing ring, and

[0027] -The second rotor includes:

[0028] *plate,

[0029] * Blades, blades are added to the disc, and

[0030] - A retaining ring, which is arranged within the second rotor and configured to prevent axial movement of the blades relative to the disk.

[0031] The second sealing ring is configured to contact the retaining ring.

[0032] According to a second aspect of the invention, a sealing ring is provided, comprising a first portion and a second portion different from the first portion, the first portion being configured to contact a second rotor of the assembly as described above, and the second portion being configured to contact a first sealing ring of the assembly as described above.

[0033] According to a third aspect of the invention, a turbine section is provided, which includes the components described above.

[0034] According to a fourth aspect of the invention, a turbine is provided, which includes the components described above, the sealing ring described above, or the turbine section described above.

[0035] According to a fifth aspect of the invention, an aircraft is provided that includes a turbine as described above. Attached Figure Description

[0036] Other features, objects, and advantages of the invention will become apparent from the following description, which is purely illustrative and not restrictive, and should be read in conjunction with the accompanying drawings, in which:

[0037] Figure 1 This is a schematic cross-sectional view of a turbine.

[0038] Figure 2 This is a schematic cross-sectional view of an exemplary embodiment of a component according to the present invention.

[0039] In all the accompanying drawings, similar elements are represented by the same reference numerals. Detailed Implementation

[0040] turbine

[0041] Reference Figure 1 In one embodiment, the turbine 1 has a longitudinal axis XX, and the turbine includes a fan 10, a compressor section 12, a combustion chamber 14, and a turbine section 16, which can be driven to rotate about the longitudinal axis XX relative to the casing 18 of the turbine 1.

[0042] During operation, fan 10 draws in airflow, a portion of which is continuously compressed in compressor section 12, ignited in combustion chamber 14, and expanded in turbine section 16 before being ejected from turbine 1. In this way, turbine 1 generates thrust. Furthermore, this thrust can benefit an aircraft (not shown) to which turbine 1 is added and fixed.

[0043] In this document, upstream and downstream are defined relative to the conventional direction of airflow through turbine 1 during operation. Similarly, the axial direction corresponds to the direction of the longitudinal axis XX, the radial direction is the direction perpendicular to and through the longitudinal axis XX, and the circumferential or tangential direction corresponds to the direction of a closed curve of a surface, wherein all points of the closed curve are equidistant from the longitudinal axis XX. Furthermore, unless otherwise stated, the terms "inner" and "outer" are used to denote the radial direction, such that the interior (i.e., radially interior) or inner surface (i.e., radially inner surface) of an element is closer to the longitudinal axis XX than the exterior (i.e., radially exterior) or outer surface (i.e., radially outer surface) of the same element.

[0044] turbine

[0045] Reference Figure 2The turbine section 16 includes a first rotor 2, which is rotatable relative to the housing 18 about a longitudinal axis XX. The first rotor 2 includes a first disc 20, first blades 22, and a first shroud. The first blades are typically added to the first disc 20 by being fitted into first slots 24 of the first disc 20. The axial cross-section of the first shroud is in the form of a first arm 26. Figure 2 As can be seen, the first arm extends upstream of the first plate 20.

[0046] The turbine section 16 also includes a second rotor 3, which is rotatable relative to the housing 18 about a longitudinal axis XX. The second rotor 3 includes a second disk 30, second blades 32, and a second shroud. The second blades are typically added to the second disk 30 by being fitted into second slots 34 of the second disk 30. The axial cross-section of the second shroud is in the form of a second arm 36. Figure 2 As can be seen, the second arm 36 extends upstream of the second disk 30. Furthermore, a retaining ring 38 is advantageously arranged within the second rotor 3, and the retaining ring is configured to prevent axial movement of the second blade 32 relative to the second disk 30.

[0047] The first arm 26 is preferably, for example, by means of, Figure 2 The bolted connection shown is fixed to the second arm 36. This bolted connection is typically formed by sector flanges 260, 360 of each of the first arm 26 and the second arm 36, which are arranged to face each other during installation, and then the bolts are inserted into the holes of the sector flanges 260, 360.

[0048] Furthermore, in one embodiment, the turbine section 16 includes a nozzle 9 disposed radially outside the first arm 26 and the second arm 36. The nozzle 9 includes a stator 90, which includes a wear-resistant portion 900 at its inner radial end.

[0049] Therefore, the first blade 22, the second blade 32, and the stator 90 extend into the flow path 160, in which air expanded by the turbine section 16 flows during operation.

[0050] sealing ring

[0051] Reference Figure 2A first sealing ring 4, centered on the longitudinal axis XX, is arranged radially outward of the first arm 26. The first sealing ring 4 includes a first radial flange 40, which is typically fixed between the first arm 26 and the second arm 36 by fanning out the flanges 260 of the first arm 26 and 360 of the second arm 36, thereby engaging in a bolted connection. In one embodiment, the first sealing ring 4 further includes a sealing scraper 400, which extends radially outward to engage with the wear-resistant portion 900 of the stator 90. Therefore, air cannot flow from the first chamber 1601 located upstream of the wear-resistant portion 900 to the second chamber 1602 located downstream of the wear-resistant portion 900.

[0052] A second sealing ring 5, distinct from the first sealing ring 4 and centered on the longitudinal axis XX, is arranged radially outside the second arm 36. The term "distinct" means that the first sealing ring 4 and the second sealing ring 5 are not integral. Therefore, unlike the integral Y-rings known in the prior art, in... Figure 2 In the assembly shown, the first sealing ring 4 is separated from the second sealing ring 5, resulting in a smaller degree of radial outward offset of the first radial flange 40. This significantly increases the lifespan of the bolted connection orifice and sector. In any case, the second sealing ring 5 also serves as a heat shield for the second arm 36 to protect it from the heat of the air circulating within the first chamber 1601.

[0053] As in Figure 2 As shown by the dashed arrow, the assembly formed by the first rotor 2, the first sealing ring 4, the second rotor 3, and the second sealing ring 5 defines a ventilation circuit, in which air configured to cool the first blade 22 and the second blade 32 circulates.

[0054] like Figure 2 As shown, the second sealing ring 5 includes a first portion 51 configured to contact the second rotor 3, preferably the retaining ring 38. Therefore, the upstream axial clamping of the second sealing ring 5 is distributed on the second rotor 3. Furthermore, the second sealing ring 5 includes a second portion 52, distinct from the first portion 51, configured to contact the first sealing ring 4. The term "distinct" means that the first portion 51 is configured not to contact the first sealing ring 4, or that the second portion 52 is configured not to contact the second rotor 3. Therefore, the first sealing ring 4 and the second rotor 3 serve as the axially adjacent portion of the second sealing ring 5.

[0055] exist Figure 2In one embodiment, the second rotor 3 has a first inner axial surface 301, and the second sealing ring 5 has a first outer axial surface 501. The first outer axial surface is positioned facing the first inner axial surface 301 and spaced apart from it by a distance, such that the first outer axial surface 501 is configured to contact the first inner axial surface 301 during thermal expansion (preferably radial thermal expansion) of the second sealing ring 5. Typically, as Figure 2 As shown, the radially inner bottom of the second slot 34 extends downstream to form the first inner axial surface 301.

[0056] In one embodiment, the first sealing ring 4 has a second inner axial surface 401, and the second sealing ring 5 has a second outer axial surface 502. The second outer axial surface is positioned facing the second inner axial surface 201 and spaced apart from it by a distance, such that the second outer axial surface 502 is configured to contact the second inner axial surface 201 during thermal expansion (preferably radial thermal expansion) of the second sealing ring 5. Typically, as Figure 2 As shown, the first sealing ring 4 includes an axial flange 41 that extends upstream to form a second inner axial surface 201.

[0057] Therefore, advantageously, radial clearances can be provided upstream and downstream of the second sealing ring 5, corresponding respectively to the spaces separating the first outer axial surface 501 from the first inner axial surface 301 and the spaces separating the second outer axial surface 502 from the second inner axial surface 201. Thus, the radial contact between the second sealing ring 5 and the second rotor 3 and the first sealing ring 4 is precise. More specifically, radial contact between the second sealing ring and the second rotor and the first sealing ring occurs only when the second sealing ring 5 reaches the point of radial outward expansion. Since the first radial flange 40 is only radially pushed outward when the second sealing ring 5 makes radial contact with the first sealing ring 4 at the axial flange 41, the degree of radial outward offset of the first radial flange 40 is small. This significantly increases the lifespan of the bolted connection orifice and sector. Furthermore, the bottom of the second groove 34 and the axial flange 41 serve as the radial abutment of the second sealing ring 5.

[0058] In one embodiment, one of the second arm 36 and the second sealing ring 5 includes a lug 7, and the other of the second arm 36 and the second sealing ring 5 includes a recess 8. The lug 7 is configured to mate with the recess 8 to prevent circumferential rotation of the second sealing ring 5 relative to the second rotor 3. The mating of the lug 7 and the recess 8 serves as a tangential abutment of the second sealing ring 5. Multiple lugs 7 and multiple recesses 8, distributed around the longitudinal axis XX, can be provided to distribute mechanical stress.

[0059] In one embodiment, a groove 510 is provided in the first portion 51 of the sealing ring. Furthermore, a seal 6 is disposed within the groove 510. The engagement of the seal 6 and the second rotor 3 allows for limiting leakage within the ventilation circuit even when an axial clearance exists between the second rotor 3 and the second sealing ring 5 (despite clamping during installation).

[0060] In one embodiment, the second sealing ring 5 is provided with orifices 50 to allow fluid to flow between a third chamber 1603 arranged radially inward of the second sealing ring 5 and a first chamber 1601 arranged radially outward of the second sealing ring 5. This allows for increased pressurization in the first chamber 1601 to resist the flow of air from the flow path 160, thereby relieving pressure on the sealing scraper and wear-resistant portion 900. Preferably, a plurality of orifices 50 are provided in the second sealing ring 5, for example, by being circumferentially distributed all around the longitudinal axis XX.

Claims

1. An assembly for a turbomachine (1), the assembly comprising: - a first rotor (2) movable in rotation about a longitudinal axis (X-X) of the turbomachine (1), the first rotor (2) comprising a first arm (26), - a second rotor (3) movable in rotation about the longitudinal axis (X-X) and comprising a second arm (36), - a first seal ring (4) centered on the longitudinal axis (X-X), the first seal ring being arranged radially outward of the first arm (26), comprising a first radial flange (40) fixedly mounted between the first arm (26) and the second arm (36), and further comprising a sealing scraping portion (400) extending radially outward so as to be able to cooperate with a wear portion (900) of a stator (90) of the turbomachine (1), - a second seal ring (5) distinct from the first seal ring (4), the second seal ring being centered on the longitudinal axis (X-X) and being arranged radially outward of the second arm (36), the second seal ring (5) comprising a first portion (51) configured to come into contact with the second rotor (3) and a second portion (52) distinct from the first portion (51) and configured to come into contact with the first seal ring (4), wherein the first seal ring (4) has a second inner axial surface (401), the second seal ring (5) has a second outer axial surface (502) positioned facing the second inner axial surface (401) and at a distance from the second inner axial surface in a radial direction, such that the second outer axial surface (502) is configured to come into contact with the second inner axial surface (401) when the second seal ring (5) thermally expands.

2. The assembly of claim 1, wherein, the second rotor (3) has a first inner axial surface (301), the second seal ring (5) has a first outer axial surface (501) positioned facing the first inner axial surface (301) and at a distance from the first inner axial surface, such that the first outer axial surface (501) is configured to come into contact with the first inner axial surface (301) when the second seal ring (5) thermally expands.

3. The assembly of claim 1 or 2, wherein, a recess (510) is provided in the first portion (51), the assembly further comprising a seal (6) arranged within the recess (510).

4. The assembly of claim 1 or 2, wherein, one of the second arm (36) and the second seal ring (5) comprises a lug (7) and the other of the second arm (36) and the second seal ring (5) comprises a notch (8), the lug (7) being configured to cooperate with the notch (8) to prevent circumferential rotation of the second seal ring (5) relative to the second rotor (3).

5. The assembly of claim 1 or 2, wherein, The second seal ring (5) is provided with an aperture (50) to enable fluid communication between a first chamber (1603) arranged radially inside the second seal ring (5) and a second chamber (1601) arranged radially outside the second seal ring (5).

6. The assembly of claim 1 or 2, wherein, The second rotor (3) comprises: - a disc (30), - a blade (32) connected to the disc (30), and - a retaining ring (38) arranged inside the second rotor (3) and configured to prevent axial movement of the blade (32) relative to the disc (30), The second seal ring (5) is configured to come into contact with the retaining ring (38).

7. A turbine section (16) comprising the assembly according to any one of claims 1 to 6.

8. A turbomachine (1) comprising the assembly according to any one of claims 1 to 6 or the turbine section (16) according to claim 7.

9. An aircraft comprising the turbomachine (1) according to claim 8.

Images