CA2873197A1

CA2873197A1 - Final-stage internal collar gasket of an axial turbine engine compressor

Info

Publication number: CA2873197A1
Application number: CA2873197A
Authority: CA
Inventors: Damien Verhelst
Original assignee: Techspace Aero SA
Current assignee: Safran Aero Boosters SA
Priority date: 2013-12-20
Filing date: 2014-12-03
Publication date: 2015-06-20
Also published as: RU2014151115A; RU2709752C2; RU2014151115A3; EP2886802B1; CN104727861A; US20150176421A1; CN104727861B; EP2886802A1

Abstract

The invention relates to an axial turbine engine guide vane assembly. The guide vane assembly comprising an annular row of blades which extend radially, an internal collar disposed at the internal ends of the blades. The internal collar comprises a circular gasket in elastomer or in silicon which is disposed on one of the upstream or downstream sides of said collar, so as to ensure airtightness with a sealing surface of the intermediate casing of the turbine engine. The internal collar comprises a cavity in which the gasket is housed, the cavity being integrally formed in the material of the internal collar and/or with the help of one or a plurality of added members. The invention allows the airtightness in the event of vibrations to be improved, while at the same time increasing the rigidity of the internal collar without increasing the production cost. The invention likewise relates to an axial turbine engine.

Description

FINAL-STAGE INTERNAL COLLAR GASKET OF AN AXIAL TURBINE ENGINE
COMPRESSOR
Technical field The invention relates to a turbine engine guide vane assembly. More specifically, the invention relates to a turbine engine compressor guide vane assembly fitted with an internal collar having a gasket ensuring airtightness with a casing of the turbine engine. The invention likewise relates to a turbine engine having a gasket disposed between a collar and a casing of the turbine engine.
Prior art A turbojet engine comprises a plurality of levels such as a fan, compressors, a combustion chamber and turbines. These compartments are fixed to the intermediate casing, such that they are all connected. The intermediate casing is crossed by annular flows that circulate in the turbine engine. In order to limit leaks, sealing devices are provided at the interfaces between the intermediate casing and the compartments. In particular, the low-pressure compressor which is fixed directly to the intermediate casing exhibits gaskets at its external casing and at the internal collar of its downstream guide vane assembly.
The internal collar of the upstream guide vane assembly is fixed to the internal ends of the blades and cooperates in an airtight manner with a planar surface of the intermediate casing. To this end, the guide vane assembly comprises a circular silicon gasket pressed against the sealing surface of the casing.
Document EP 1 426 559 Al discloses an inner collar for the guide vane assembly of a low-pressure axial turbojet engine compressor. The compressor is fixed to the intermediate casing of the turbine engine, the internal collar of the last stage of the compressor being in contact with the intermediate casing by means of a circular gasket. During operation of the turbojet engine, the circular gasket is subject to vibrations due, for example, to the operation of the turbine engine itself, to ingestion, to a pumping phenomenon, to the existence of an unbalancing mass or to a "fan

2 blade off" state. These vibrations deform the gasket radially and axially, thereby reducing the airtightness. The gasket may likewise become detached from the intermediate housing, thereby creating a leak. The gasket no longer achieves either its contact pressure or its nominal position.
Brief description of the invention The aim of the invention is to solve at least one of the problems presented by the former art. More precisely, the invention aims to preserve the airtightness of a guide vane assembly at the junction between its internal collar and a sealing surface of a casing when the guide vane assembly is subject to turbine engine vibrations.
The invention relates to a guide vane assembly of an axial turbine engine compressor, the guide vane assembly comprising an annular row of blades which extend radially, an internal collar disposed at the internal ends of the blades which comprises a circular gasket on one of the upstream or downstream sides of said collar, so as to ensure airtightness with a sealing surface of an intermediate casing of the turbine engine, this being exceptional in that the internal collar comprises a cavity in which the gasket is housed.
According to an embodiment of the invention, the cavity is formed, possibly integrally, in the material of the internal collar, said collar preferably being realized in a polymer material, more preferably in a composite material with an organic matrix.
According to an embodiment of the invention, the cavity is formed by a portion of the collar and one or a plurality of members added to said collar and preferably creating a generally circular form, the internal collar and each added member preferably being realized in composite materials with an organic matrix.
According to an embodiment of the invention, the guide vane assembly comprises a hook which forms the cavity, so as to hold the gasket against the sealing surface of the casing and against the internal collar, the cavity preferably forming an annular throat essentially opened axially.

3 According to an embodiment of the invention, the guide vane assembly comprises an annular shoulder delimiting the cavity axially, the shoulder preferably being formed by an annular flange extending radially, the annular shoulder preferably being formed by the annular collar and/or by each added member.
According to an embodiment of the invention, the guide vane assembly comprises a generally tubular face delimiting the inside of the cavity radially, the tubular face possibly being formed on the annular collar and/or on each added member, preferably at least one added member tubular face compressing the gasket radially against the internal surface of the internal collar.
According to an embodiment of the invention, the gasket is for the most part disposed axially and/or radially inside the cavity,.the gasket preferably comprising an elastomer material such as a silicon material.
According to an embodiment of the invention, the gasket exhibits a generally toroidal form, the revolution profile of the gasket preferably generally being a circle, a triangle or a quadrilateral such as a parallelogram.
According to an embodiment of the invention, the gasket guarantees airtightness between the internal collar and each added member, preferably right around the internal collar.
According to an embodiment of the invention, each added member is fixed to the internal collar, each added member possibly being interlocked or bonded adhesively to the internal collar or fixed to the blades with the help of fixing means by material engagement.
According to an embodiment of the invention, each added member extends over most of, possibly over all, the axial length of the internal collar, each added member preferably being placed against the internal surface of the internal collar.

4 According to an embodiment of the invention, the length of the internal collar is more than twice the chord of each blade measured according to said chord, the length of each added member possibly being greater than the chord of each blade measured according to said chord.
According to an embodiment of the invention, the guide vane assembly comprises an annular layer of abradable material disposed on the upstream or downstream side of the internal collar which is axially opposed to that which the circular gasket comprises, the abradable layer possibly extending axially up to the material io delimiting the cavity.
According to an embodiment of the invention, the internal collar and at least one added member are realized in different materials, the density of each added member preferably being lower than the density of the internal collar.
According to an embodiment of the invention, each added member is fixed to the internal collar with the help of fixing means by material engagement and/or each added member fits closely against the internal surface of the internal collar.
According to an embodiment of the invention, the tubular face is disposed axially and/or radially to the inside of the external surface of the internal collar.
According to an of the invention, the gasket extends axially beyond the internal collar and/or each added member.
According to an embodiment of the invention, the abradable layer is delimited axially with the help of the internal collar and/or by each added member.
According to an embodiment of the invention, the gasket fits closely against most of the internal surface of the cavity, preferably against all of it, and/or the gasket fills most of the internal volume of the cavity.

The invention likewise relates to an axial turbine engine comprising a casing provided with a sealing surface, at least one compressor with a guide vane assembly which cooperates in an airtight manner with the sealing surface, this being exceptional in that the guide vane assembly conforms to the invention, the gasket

5 preferably being compressed axially between the guide vane assembly and the sealing surface of the casing.
According to an embodiment of the invention, axial play J is conserved between the casing and the internal collar, the gasket extending axially over the entire axial play J, the turbine engine preferably comprises at least one turbine, at least one fan, the casing being the intermediate casing of the turbine engine, and withstands most, possibly all, of the forces of each compressor, each turbine and each fan.
The invention allows the gasket to be effectively held against the sealing surface of the casing. The cavity allows the gasket to be housed and held against the casing surface. The solution in which the cavity is integrally formed in the material of the internal collar allows a simple collar to be realized integrally. The collar can be realized by grinding, its cavity can be ground directly and/or fabricated, which enables production costs to be kept down.
Thanks to the added member, a radial compressive stress can be applied to the gasket, which further improves the seal. The added member allows the gasket to be supported, it forms a support improving positioning, the gasket holding position. It further allows the contact between the gasket and the casing to be made rigid.
In passing, the added member improves the rigidity of the internal collar and limits its axial and/or radial deformation, such as its out-of-roundness, significantly.
The addition of the added member enables a cavity with a complex form to be realized without increasing the production cost of the internal collar.
The added member allows the lightness of the guide vane assembly to be preserved. In fact, it can be realized in a lighter material than the internal collar. For

6 example, the internal collar can be realized in metal and the added member perhaps in a polymer, such as a composite material.
During production of the turbine engine, the compressor is assembled so as to form an assembly which is then placed against the intermediate casing. At this point the circular gasket is compressed axially against the sealing surface of the turbine engine casing. The compression of the gasket relies on a series of sides including a plurality of members including the blades of the guide vane assembly. Said blades may exhibit variations in position of more than 2.00 mm, which increases the margin that the circular gasket must be able to tolerate. Moreover, the circular gasket must likewise be adapted to a differential dilatation phenomenon.
Brief description of the drawings Figure 1 depicts an axial turbine engine according to the invention.
Figure 2 is a schematic representation of a turbine engine compressor according to the invention.
Figure 3 illustrates the downstream guide vane assembly of the compressor in contact with the casing of the turbine engine according to the invention.
Description of embodiments In the following description, the terms "interior" or "internal" and "exterior" or "external" relate to a position in respect of the axis of rotation of an axial engine turbine. The axial direction relates to the axis of rotation.
Figure 1 depicts a simplified representation of an axial engine turbine. In this particular case, it is a double-flow turbojet engine. The turbojet engine 2 comprises a plurality of communication levels, such as a first compression level referred to as a

7 low-pressure compressor 4, a second compression level referred to as a high-pressure compressor 6, a combustion chamber 8 and one or a plurality of turbine levels 10.
During operation, the mechanical power of the turbine 10 transmitted via the central shaft up to the rotor 12 sets the two compressors 4 and 6 in operation. Gear reduction means or concentric shafts may connect the turbines 8 to the compressors 4 and 6. Said compressors comprise a plurality of rows of rotor blades associated with rows of stator blades. The rotation of the rotor about its axis of rotation 14 thereby allows an air flow rate to be generated and progressively compressed up to the inlet of the combustion chamber 10, in order to increase the output of the turbine engine.
An input blower usually referred to as a fan 16 is coupled with the rotor 12 and generates an air flow that divides up into a primary flow 18 crossing the different levels of the turbine engine mentioned above and a secondary flow 20 crossing an annular conduit (partially represented) along the engine, after which it joins up with the primary flow again at the turbine outlet. The turbine engine may comprise a plurality of fans. The primary 18 and secondary 20 flows are annular flows and are channelled through the casing of the turbine engine.
The turbine engine may comprise a casing, possibly an intermediate casing. The intermediate casing guarantees a fixing structure function to which the compressors 4 and 6, the turbines 8, the combustion chamber 10, the fan 16 and the shafts are all fixed or connected, so that at least most of the forces, preferably all of the forces, coming from it are withstood.
Figure 2 is a sectional view of a compressor of an axial turbine engine 2 such as that shown in Figure 1. The compressor may be a low-pressure compressor 4. This shows part of the fan 16 and the separation spout 22 of the primary flow 18 and of the secondary flow 20. The rotor 12 comprises a plurality of rows of rotor blades 24, in this case three.

8 The low-pressure compressor 4 comprises a plurality of guide vane assemblies, in this case four, which each contain a row of stator blades 26. The stator blades 26 extend essentially radially from an exterior casing 28 and can be fixed there with the help of an axle. They are regularly spaced relative to one another and exhibit the same angular orientation in the flow. The guide vane assemblies are linked to the fan 16 or to a row of rotor blades to guide the flow of air, so as to convert the flow speed into pressure.
The blades in the same row are advantageously identical. The space between the blades, just as their angular orientation, may possibly vary locally. Certain blades may differ from the rest of the blades in their row.
Each guide vane assembly comprises an internal collar 30 which is disposed at the internal ends of the stator blades 26 of the corresponding row. The internal collars 30 allow the primary flow 18 to be guided during its compression. They likewise allow the ends of the blades 26 to be held in relation to one another. The guide vane assemblies may likewise comprise annular layers of abradable material 32, possibly applied to each internal surface of the internal collar 30. These abradable layers 32 cooperate by abrasion with radial annular ribs of the rotor 12, in order to guarantee its airtightness.
Downstream, the compressor may be mounted, possibly directly, on the casing of the turbine engine, possibly on the intermediate casing 34. The compressor may be mounted on any casing or any portion of the turbine engine casing. The compressor may be in contact with the intermediate casing 34 at its exterior casing 28 and at the downstream side of the internal collar 30 of its downstream guide vane assembly.
Annular seals are provided for at the interfaces.
In this perspective, the internal collar 30 comprises an annular gasket 36 or a circular gasket 36 which ensures airtightness with a sealing surface of the casing, possibly the intermediate casing 34 of the turbine engine 2. The gasket 36 may form a sealing

9 bead and may comprise, possibly for the most part or in its entirety, an elastomer material such as a silicon material. The silicon material may be organic or made of resin. The gasket 36 may be disposed at an opposite axial end to that receiving the abradable layer 32.
Figure 3 depicts the guide vane assembly downstream of the compressor and the intermediate casing 34 of the turbine engine, as well as an enlargement at the sealing interface between the internal collar 30 and the casing 34.
The intermediate casing 34 may be crossed by the primary flow 18, it guides it with the help of an external wall 38 and an internal wall 40 which are linked by casing arms 41 which cross the flow radially. The internal wall 40 may be formed by an internal hub 42 to which shafts of the turbine engine can be articulated.
Axially in respect of the gasket 36 of the internal collar 30, the casing comprises a sealing surface 44, generally planar for example, in order to reduce rubbing in the case of axial vibration and to avoid hyperstatic assembly. The sealing surface 44 may be substantially conical. -The internal collar 30 comprises a cavity 45 in which is housed the gasket 36, for the most part or completely, for example. The cavity 45 may be circular. The cavity 45 may be formed, possibly integrally, in the material of the internal collar 30.
The cavity 45 may run right around the collar 30 or be formed in a discontinuous manner.
The cavity 45 may form a hook, it may be open essentially axially towards the sealing surface 44 of the casing 34. It may exhibit a general U-shaped profile pivoted towards the casing 34. The cavity 45 and the sealing surface 44 envelop the gasket for the most part or essentially completely. They may enclose it on at least four faces.
The internal collar 30 may comprise one or a plurality of added members 46.
The added member or members 46 extend along the circular gasket 36 following its circumference. Each added member 46 may exhibit a generally circular or annular form, the combination of added members 46 being generally circular. Each added member 46 may be disposed inside the internal collar 30 and may hold the circular gasket 36, possibly against the internal surface of the collar and/or against the intermediate casing 34. Each added member 46 may apply an axial and/or radial pressure against the circular gasket 36, possibly in such a manner as to increase the 5 axial length of the gasket 36 following compression.
The cavity 45 may be formed by combining a portion of the internal collar 30 and of the added member or members 46, the cavity 45 exhibiting a circular continuity.
Alternatively, the added members 46 may be inserted in the discontinuous portions

10 of the internal collar, so as to form a generally continuously circular cavity 45.
The guide vane assembly may comprise a shoulder 48. The shoulder 48 may be formed on the internal collar 30 and/or on each added member 46. Each shoulder extends radially, is in contact with the circular gasket 36 and can form an axial stop for the circular gasket 36. The shoulder 48 or the combination of shoulders may possibly extend over most or all of the radial thickness of the circular gasket 36. At least one or every shoulder 48 may be an annular flange extending radially.
Each added member 46 may be fixed to the internal radial end of the shoulder of the internal collar 30, by adhesive bonding for example. When the internal collar 30 and each added member 46 each exhibit a shoulder, these are radial to one another in the extension. The added member 46 may allow the circular gasket to be held axially.
The guide vane assembly may comprise a generally tubular 50 or substantially conical face which is possibly disposed axially and/or radially to the inside of the internal collar 30. The tubular face 50 may extend over the majority, preferably over substantially the entirety, of the axial thickness of the circular gasket 36, this applying right around the gasket. The tubular face 50 may be formed on the internal collar 30 and/or on each added member 46. It may exhibit material discontinuities and be both formed by the collar and also by the added member or members 46.

11 The circular gasket 36 may be added and adhesively bonded to the internal collar 30 or realized in the cavity and adhered there. The gasket 36 may exhibit a ring or toroidal form, it may exhibit a generally round or polygonal revolution profile. It may exhibit a revolution profile in triangular, quadrilateral ¨ such as a parallelogram ¨ or square form. The gasket 36 may guarantee airtightness between the internal collar 30 and each added member 46.
The internal collar 30 may comprise an annular partition 52 with a generally constant thickness, for example. Its revolution profile may be inclined relative to the axis of rotation of the turbine engine, possibly by at least 5 , preferably by at least 100, more preferably by at least 15 . The internal collar 30 may comprise an annular row of openings (not shown) into which are introduced the internal ends of the blades 26 in order to fix them. The internal collar 30 forms an axial annular junction between a portion of rotor and the intermediate casing 34. Its length is greater than 130%, preferably greater than 250%, of the chord of the blade 26, both measured according to said chord at the junction between the blade 26 and the internal collar 30.
Axial play J is conserved between the sealing surface 44 of the casing 34 and the internal collar 30. The same equal axial play is preferably conserved between the sealing surface 44 of the casing and each added member. The circular gasket 36 extends axially right along the play J, so as to form an airtight barrier. The material of the gasket 36 likewise enables a cushioning of vibrations at the axial play J
to be guaranteed.
At least one or each added member 46 can be fixed to the internal collar 30, for example by adhesive bonding and/or by interlocking. It may comprise an annular platform 54 fitting closely against the inside of the partition 52 of the internal collar 30. The internal collar 30 and/or each added member 46 and/or the blades 26 may comprise fixing means by material engagement, resulting in the fixing of each added member 46 on the internal collar 30 and/or on the blades 26, the internal collar 30 likewise being able to be fixed to the blades 26 by these means.

12 The internal collar 30 and/or each added member 46 may be realized in metal such as titanium or aluminium. The internal collar 30 and/or each added member 46 may be realized by injection of a polymer or a filled resin. At least one, preferably both, of these may be realized in composite materials with an organic matrix. They may comprise a polyetherimide (PEI) or polyether ether ketone (PEEK) matrix. They may comprise carbon fibres, glass fibres, graphite fibres. The fibres may exhibit a length of less than 3.00 mm, preferably less than 1.00 mm, more preferably less than 0.30 mm. At least one of these members preferably comprises a fibrous preform with an epoxy matrix.
The invention may likewise be applied to a high-pressure compressor, for example an internal collar of a guide vane assembly upstream of the high-pressure compressor. In this configuration, the upstream guide vane assembly comprises an elastomer gasket disposed upstream of its internal collar, the gasket cooperating with a sealing surface of the downstream face of the intermediate casing of the turbine engine. The gasket is likewise held against the collar and the sealing surface with the help of at least one added member.

Claims

1 . Axial turbine engine compressor guide vane assembly, the guide vane assembly comprising:
- an annular row of blades which extend radially, - an internal collar disposed at the internal ends of the blades which comprises a circular gasket on one of the upstream or downstream sides of said collar, so as to ensure airtightness with a sealing surface of an intermediate casing of the turbine engine, characterized in that the internal collar comprises a cavity in which the gasket is housed.

2. Guide vane assembly according to Claim 1, characterized in that the cavity is formed integrally in the material of the internal collar.

3. Guide vane assembly according to Claim 2, characterized in that said collar is realized in a polymer material.

4. Guide vane assembly according to Claim 2, characterized in that said collar is realized in a composite material with an organic matrix.

5. Guide vane assembly according to any one of Claims 1 to 4, characterized in that the cavity is formed by a portion of the collar and one or a plurality of members added to said collar.

6. Guide vane assembly according to any one of Claims 1 to 4, characterized in that the cavity is formed by a portion of the collar and one or a plurality of members added to said collar and creating a generally circular form.

7. Guide vane assembly according to Claim 5 or 6, characterized in that the internal collar and each added member are realized in composite materials with an organic matrix.

8. Guide vane assembly according to any one of Claims 1 to 7, characterized in that it comprises a hook which forms the cavity, so as to hold the gasket against the sealing surface of the casing and against the internal collar.

9. Guide vane assembly according to any one of Claims 1 to 7, characterized in that it comprises a hook which forms the cavity, so as to hold the gasket against the sealing surface of the casing and against the internal collar, the cavity forming an annular throat essentially opened axially.

10. Guide vane assembly according to any one of Claims 1 to 9, characterized in that it comprises an annular shoulder delimiting the cavity axially.

11. Guide vane assembly according to any one of Claims 1 to 9, characterized in that it comprises an annular shoulder delimiting the cavity axially, the shoulder being formed by an annular flange extending radially.

12. Guide vane assembly according to Claim 10 or 11, characterized in that the annular shoulder is formed by the annular collar.

13. Guide vane assembly according to Claim 10 or 11, characterized in that the annular shoulder is formed by each added member.

14. Guide vane assembly according to Claim 10 or 11, characterized in that the annular shoulder is formed by the annular collar and by each added member.

15. Guide vane assembly according to any one of Claims 1 to 14, characterized in that it comprises a generally tubular face delimiting the inside of the cavity radially.

16. Guide vane assembly according to any one of Claims 1 to 14, characterized in that it comprises a generally tubular face delimiting the inside of the cavity radially, the tubular face being formed on the annular collar.

17. Guide vane assembly according to any one of Claims 1 to 14, characterized in that it comprises a generally tubular face delimiting the inside of the cavity radially, the tubular face being formed on each added member.

18. Guide vane assembly according to any one of Claims 1 to 14, characterized in that it comprises a generally tubular face delimiting the inside of the cavity radially, the tubular face being formed on the annular collar and on each added member.

19. Guide vane assembly according to any one of Claims 15 to 18, characterized in that at least one added member tubular face compresses the gasket radially against the internal surface of the internal collar.

20. Guide vane assembly according to any one of Claims 1 to 19, characterized in that the gasket is for the most part disposed axially inside the cavity.

21. Guide vane assembly according to any one of Claims 1 to 19, characterized in that the gasket is for the most part disposed radially inside the cavity.

22. Guide vane assembly according to any one of Claims 1 to 19, characterized in that the gasket is for the most part disposed axially and radially inside the cavity.

23. Guide vane assembly according to any one of Claims 20 to 22, characterized in that the gasket comprises an elastomer material such as a silicon material.

24. Guide vane assembly according to Claim 23, characterized in that the elastomer is a silicon material.

25. Guide vane assembly according to any one of Claims 1 to 24, characterized in that the gasket exhibits a generally toroidal form.

26. Guide vane assembly according to any one of Claims 1 to 24, characterized in that the gasket exhibits a generally toroidal form, the revolution profile of the gasket generally being a circle, a triangle or a quadrilateral.

27. Guide vane assembly according to Claim 26, characterized in that the quadrilateral is a parallelogram.

28. Guide vane assembly according to any one of Claims 5 to 27, characterized in that the gasket guarantees airtightness between the internal collar and each added member.

29. Guide vane assembly according to any one of Claims 5 to 27, characterized in that the gasket guarantees airtightness between the internal collar and each added member, and right around the internal collar.

30. Guide vane assembly according to any one of Claims 5 to 29, characterized in that each added member is fixed to the internal collar.

31. Guide vane assembly according to any one of Claims 5 to 29, characterized in that each added member is fixed to the internal collar, each added member being interlocked or bonded adhesively to the internal collar or fixed to the blades with the help of fixing means by material engagement.

32. Guide vane assembly according to any one of Claims 5 to 31, characterized in that each added member extends over most of, possibly over all, the axial length of the internal collar.

33. Guide vane assembly according to Claim 32, characterized in that each added member is placed against the internal surface of the internal collar.

34. Guide vane assembly according to any one of Claims 1 to 33, characterized in that the length of the internal collar is more than twice the chord of each blade measured according to said chord.

35. Guide vane assembly according to any one of Claims 1 to 33, characterized in that the length of the internal collar is more than twice the chord of each blade measured according to said chord, and the length of each added member is greater than the chord of each blade measured according to said chord.

36. Guide vane assembly according to any one of Claims 1 to 35, characterized in that it comprises an annular layer of abradable material disposed on the upstream or downstream side of the internal collar which is axially opposed to that which the circular gasket comprises.

37. Guide vane assembly according to any one of Claims 1 to 35, characterized in that it comprises an annular layer of abradable material disposed on the upstream or downstream side of the internal collar which is axially opposed to that which the circular gasket comprises, the abradable layer extending axially up to the material delimiting the cavity.

38. Axial turbine engine comprising a casing provided with a sealing surface, at least one compressor with a guide vane assembly which cooperates in an airtight manner with the sealing surface, characterized in that the guide vane assembly conforms to any one of Claims 1 to 37.

39. Axial turbine engine comprising a casing provided with a sealing surface, at least one compressor with a guide vane assembly which cooperates in an airtight manner with the sealing surface, characterized in that the guide vane assembly conforms to any one of Claims 1 to 37, the gasket being compressed axially between the guide vane assembly and the sealing surface of the casing.

40. Turbine engine according to Claim 38 or 39, characterized in that axial play J is conserved between the casing and the internal collar, the gasket extending axially over the entire axial play J.

41. Turbine engine according to Claim 38 or 39, characterized in that axial play J is conserved between the casing and the internal collar, the gasket extending axially over the entire axial play J, and the turbine engine comprises at least one turbine, at least one fan, the casing being the intermediate casing of the turbine engine, and withstands most, possibly all, of the forces of each compressor, each turbine and each fan.