Stator assembly for aviation turbine engine

Abstract

The invention relates to a seal (600) for an aeronautical turbine engine, comprising a plurality of seal segments distributed circumferentially about a longitudinal axis (X), each seal segment comprising a radially outer annular wall segment and a radially inner annular wall segment (610), which are interconnected by an elastically deformable member (203), characterized in that the radially outer annular wall segments form an integral outer cover, and the radially inner annular wall segments form an outer cover. The radially inner annular wall segments (610) are arranged circumferentially end-to-end, and wherein each radially inner annular wall segment (610) comprises a first circumferential edge (612) and an opposing second circumferential edge, each having a slit (614), and wherein a tongue (616) is partially mounted at the junction of the two opposing circumferential edges.

Description

Technical Field

[0001] This invention relates to an annular seal, such as a hydrostatic annular seal. This document also relates to an assembly including such a seal, and a turbine or turbine engine including such a seal. Background Technology

[0002] Figure 1 A turbine engine 1 with a longitudinal axis X is schematically shown. This turbine engine 1 typically includes, in the direction from upstream AM to downstream AV of the gas flow within the turbine engine 1, a fan 2, a low-pressure compressor 3, a high-pressure compressor 4, a combustion chamber 5, a high-pressure turbine 6, a low-pressure turbine 7, and an exhaust system downstream of the turbine engine 1. The gas flow entering upstream of the turbine engine 1, particularly air, first passes through the fan 2 and then splits into two parts: one part is an annular flow channel called the core flow 8, and the other part is an annular flow channel surrounding the core flow 8 called the bypass flow 9. The low-pressure compressor 3, the high-pressure compressor 4, the combustion chamber 5, the high-pressure turbine 6, and the low-pressure turbine 7 are all arranged within the core flow 8.

[0003] In this document, the terms "longitudinal," "radial," and "circumferential" are defined relative to the longitudinal axis X of the turbine engine 1, which coincides with the rotational axes of the low-pressure and high-pressure rotors of the turbine engine 1. The terms "inner" and "outer," as well as "inner side" and "outer side," are defined in the radial direction relative to the longitudinal axis X. The terms "upstream" and "downstream" are defined relative to the overall flow direction of gas within the turbine engine along the longitudinal axis X, around which the turbine engine extends.

[0004] Now for reference Figure 2 A schematic view of a portion of a low-pressure turbine 7 having a longitudinal axis, the turbine comprising alternating annular rows of moving blades 9, which are longitudinally alternating with annular rows of stator blades 10. Figure 2 Only two annular rows of rotor blades 9 and one annular row of stator blades 10 are shown. The annular rows of rotor blades 9 or moving blades 9 are interconnected by a cylindrical cover 11.

[0005] Each stator blade 10 annular row includes a radially inner annular platform 12 and a radially outer annular platform (not shown), with multiple blades 13 extending between them. The radially outer annular platform is connected to the turbine casing.

[0006] Managing the seal between the stator blade 10 end and the rotor shroud 11 is crucial for limiting gas leakage between the rotor and stator 10, as well as controlling pressure and temperature conditions on both sides of the seal and in the region radially below the seal. For this purpose, it is known to provide a radially annular diaphragm 14 extending inward from a radially inner annular platform, with a seal 15 mounted at one end, designed to maintain a small clearance with the corresponding shroud of the rotor during operation.

[0007] Therefore, such as Figure 2 As shown in A and 2B, the stator blades 10 annular row is equipped with a clearance-controlled annular seal 15, which is radially arranged on the inner side of the stator blades 10 annular row and the outer side of the cylindrical cover 11. The clearance-controlled annular seal 22 cooperates with the cylindrical cover 11 in a non-contact sealing manner to limit the flow rate from upstream to downstream of the stator blades 10 annular row in the annular space between the seal 15 and the cylindrical cover 11.

[0008] In particular, this clearance-controlled seal 15 operates with a low and controlled annular clearance between the turbine and the casing 11 during turbine operation. Furthermore, this type of seal is designed to adapt to the clearance during operation. The use of the hydrostatic seal 15 thus has the advantage of limiting leakage flow at the seal, thereby improving turbine engine performance and reducing the requirements for thermal and mechanical stresses when assembling the various components of the turbine 7.

[0009] like Figure 2 As shown in Figure B, the hydrostatic annular seal 15 can be formed by two concentric annular walls 16, 17 and a plurality of circumferentially adjacent elastic deformable members extending between the two walls 16, 17, particularly including circumferentially extending elastic deformable blades 18. For example, WO 2009 / 148787 describes such a seal. This configuration improves control over the radial deformation of the seal 15, thus improving clearance control between the seal 15 and the shroud 11 that mates with the seal 15, thereby restricting air passage.

[0010] It has been observed that segmenting the hydrostatic annular seal leads to parasitic gas flow between the sealing segments, thereby reducing sealing efficiency.

[0011] This document provides a simple, reliable, and economical solution to meet this requirement. Summary of the Invention

[0012] Therefore, a seal for an aero-turbine engine is proposed, comprising a plurality of sealing segments circumferentially distributed around a longitudinal axis, each sealing segment comprising a radially outer annular wall segment and a radially inner annular wall segment interconnected by an elastically deformable member, characterized in that the radially outer annular wall segment forms an integral outer cover, and the radially inner annular wall segments are circumferentially end-to-end disposed, wherein each radially inner annular wall segment includes a first circumferential edge and an opposite second circumferential edge, each having a slit, and wherein a tongue is partially installed in the slit of the first circumferential edge of the radially inner annular wall segment, and partially installed in the circumferentially opposite slit of the second circumferential edge of the circumferentially adjacent radially inner annular wall segment.

[0013] Inserting a tongue between two circumferentially continuous shoe sections can reduce the passage of parasitic air in the space between the two opposing circumferential edges of two circumferentially adjacent shoe sections.

[0014] Each slit may have a radial dimension between 0.5 and 1.2 mm, preferably about 0.8 mm.

[0015] Each tongue can have a longitudinal dimension smaller than its circumferential dimension, and a radial dimension smaller than its longitudinal dimension.

[0016] The tongue can be positioned between the upstream end of the radially inner annular wall section and the longitudinal midline.

[0017] The tongue can have a roughly rectangular shape.

[0018] This document also relates to an assembly comprising a cylindrical rotor shroud intended to rotate about a longitudinal axis and a distributor having a stator blade ring, the distributor having a mounting foot at its radially inner end, a seal being mounted on the mounting foot of the distributor, and the seal engaging with the cylindrical rotor shroud of the turbine engine in a non-contact sealing manner, the cylindrical rotor shroud being arranged radially below the distributor.

[0019] The present invention also relates to a turbine for an aircraft turbine engine, the turbine including a casing, components, and a rotor, the rotor including a cylindrical shroud that rotates about a longitudinal axis, the guide being mounted in the casing, and the cylindrical shroud being arranged radially below the guide.

[0020] Finally, this document relates to a turbine engine, such as an aircraft turbojet engine or a turboprop engine, which includes components or a turbine. Attached Figure Description

[0021] Further features, details, and advantages will become apparent by reading the following detailed description and examining the accompanying drawings:

[0022] [ Figure 1 A cross-sectional view of an exemplary turbine engine is schematically shown;

[0023] [ Figure 2 This schematically illustrates a partial view of a portion of a turbine, such as a low-pressure turbine. Figure 2 B is Figure 2 An enlarged view of the seal shown in Figure A;

[0024] [ Figure 3 The annular seal is shown schematically.

[0025] [ Figure 4 A portion of the stator blade annular row and seals are schematically shown according to this document;

[0026] [ Figure 5 ]yes Figure 4 A larger scale view of the seal shown;

[0027] [ Figure 6 ]and[ Figure 7 This schematically illustrates the sealing principle of the seal according to this document;

[0028] [ Figure 8 The first seal according to this document is shown schematically;

[0029] [ Figure 9 The second seal according to this document is shown schematically;

[0030] [ Figure 10 ]to[ Figure 16 This schematically illustrates a third type of seal and its variations according to this document;

[0031] [ Figure 17 ]to[ Figure 20 An alternative embodiment of the connecting leg between the radially outer annular wall and the radially inner annular wall of the seal is schematically shown;

[0032] [ Figure 21 This is a three-dimensional schematic diagram of a segment of the stator blade annular row or guide vane row according to this document;

[0033] [ Figure 22 [A schematic perspective view of a portion of a hydrostatic annular seal;]

[0034] [ Figure 23 [This is a schematic perspective view of the leg of the hydrostatic annular seal;]

[0035] [ Figure 24 ]and[ Figure 25[This is a schematic perspective view of the radial sliding device between the hydrostatic annular seal and the annular row of stator blades;]

[0036] [ Figure 26 [This is a cross-sectional view of the component based on this document;]

[0037] [ Figure 27 ]to[ Figure 33 [This is a schematic perspective view of an assembly including a hydrostatic annular seal according to this document;]

[0038] [ Figure 34 ]and[ Figure 35 [Illustrated perspective view of an assembly according to this document, which includes a hydrostatic annular seal that conforms to the shape of a radially sliding connection on the annular row of stator blades;]

[0039] [ Figure 36 [This is a schematic perspective view of the circumferential edge of the annular seal as described in this document;]

[0040] [ Figure 37 [This is a schematic diagram of an annular seal according to this document, which has a housing on its radial inner surface;]

[0041] [ Figure 38 A partial view of an exemplary component according to this document is schematically shown, the component including an annular seal;

[0042] [ Figure 39 [Illustratively shown according to] Figure 38 A magnified partial view of an exemplary component;

[0043] [ Figure 40 [Illustratively shown according to] Figure 38 Another exemplary component's magnified partial view;

[0044] [ Figure 41 This schematically illustrates a partial view of an exemplary component according to this document, and two magnified partial views of the exemplary component in two different configurations;

[0045] [ Figure 42 A partial view of an exemplary hydrostatic annular seal is schematically shown.

[0046] [ Figure 43 A partial cross-sectional view of an exemplary component according to this document is schematically shown;

[0047] [ Figure 44 A partial cross-sectional view of another exemplary component according to this document is schematically shown;

[0048] [ Figure 45A partial cross-sectional view of another exemplary component according to this document is schematically shown;

[0049] [ Figure 46 A partial cross-sectional view of another exemplary component according to this document is shown schematically. Detailed Implementation

[0050] This document relates to an annular seal, such as a hydrostatic annular seal for use in a turbine engine. Specifically, it includes different embodiments and integration methods of such a hydrostatic annular seal.

[0051] refer to Figure 3 The diagram schematically illustrates a partial view of a hydrostatic annular seal 51 according to this document. Preferably, this hydrostatic annular seal 51 is integrated into an assembly 52 of a turbine engine having a longitudinal axis X. Such an assembly is used in the turbine of a turbine engine, particularly a low-pressure turbine. This document also relates to any type of turbine engine including such a turbine, such as a turboprop or turbojet engine for aircraft.

[0052] Assembly 52 includes a cylindrical cover 53 for rotation about a longitudinal axis X and an annular row of stator blades. The assembly may also include two annular rows of moving blades arranged longitudinally on either side of the annular row of stator blades 54 and interconnected via the cylindrical cover 53. The annular row of stator blades 54 is equipped with a hydrostatic annular seal 51. This hydrostatic annular seal 51 is radially arranged inside the annular row of stator blades 54 and outside the cylindrical cover 53, and engages with the cylindrical cover 53 in a non-contact sealing manner.

[0053] The hydrostatic annular seal 51 preferably includes a radially outer annular wall 55, a radially inner annular wall 56, and a plurality of elastically deformable members or elements 57, particularly distributed circumferentially around the longitudinal axis X. The hydrostatic annular seal 51 is capable of radial deformation by the flexibility provided by the elastically deformable members 57 connecting the radially inner annular wall 56 and the radially outer annular wall 55. The radially inner and outer annular walls and the elastically deformable elements are specifically sized to control the radial deformation of the hydrostatic annular seal 51, thereby controlling the gap J2 between the hydrostatic annular seal 51 and the cylindrical cover 53.

[0054] The seal may include multiple sealing segments circumferentially distributed around a longitudinal axis. Each sealing segment includes a radially inner annular wall segment 56 and a radially outer annular wall segment 55, which are interconnected by an elastically deformable member 57. The radially outer annular wall segment may form an integral outer cover, i.e., be integrally molded, while the radially inner annular wall segments are separate and arranged circumferentially end-to-end.

[0055] The turbine is a system that expands air from high pressure upstream to low pressure downstream. As much air as possible must pass through the turbine, rather than escape from the flow path. An air layer from the annular cavity upstream of seal 51 passes between the cylindrical cover 53 and seal 51; the radial dimensional difference between them forms a gap J2. By maintaining a small radial gap, the hydrostatic annular seal 51 provides a seal. It is the pressure difference between the annular cavity upstream of hydrostatic annular seal 51 and the annular cavity immediately downstream of it that controls the total radial pressure acting on the radially inner annular wall 56 of hydrostatic seal 51.

[0056] The hydrostatic annular seal 51 includes an inner surface 59 radially facing the cylindrical cover 53. This inner surface 59 includes a first generally cylindrical surface portion 60, a second concave curved surface portion 61 with its concave side facing outward to form an annular cavity facing the cylindrical cover 53, a third generally cylindrical surface portion 62, and a fourth truncated conical surface portion 63 with its cross-section increasing downstream. A gap j1 exists between the first surface portion 60 and the cylindrical cover 53, and a gap j2 exists between the third surface portion 62 and the cylindrical cover 53. Gap j1 and j2 satisfy the condition that j1 is greater than j2. The difference between gaps j1 and j2 creates a constraint. This constraint accelerates airflow and results in hydrostatic pressure loss at high gaps j1 (e.g., >0.6 mm). The hydrostatic annular seal 51 deforms under the combined mechanical force applied to the inner surface 59 and outer surface 63 of the shoe segment 58. This specific configuration allows for maintaining small gaps, thereby achieving a high-performance seal without the risk of contact between the shoe segment 58 and the cover 53.

[0057] The stator blades 54 annular row includes a radial annular partition 64 that carries a hydrostatic annular seal 51. The hydrostatic annular seal 51 may include a device 65 for radial sliding along the direction of the stator blades 54 annular row. A radially outer annular wall 55 is connected to an annular portion 71, which includes an upstream annular leg 66 and a downstream annular leg 67, each leg including longitudinally opposing holes 68 for mounting a pin 69. The outer annular wall 55 and the annular portion 71 may be integrally formed. The pin 69 is interference-fitted only with the hole 68 of one of the upstream 66 and downstream 67 annular legs to allow insertion into the other of the upstream 66 and downstream 67 annular legs. Preferably, the interference fit is made on the upstream annular leg 66. The radial annular partition 64 of the stator blades 54 annular row includes a plurality of preferably oblong openings 70 for mounting the middle portion of the pin 69. Alternatively, the openings may be rectangular. This mounting allows the hydrostatic annular seal 51 a certain degree of freedom in the radial direction relative to the stator blades 54 annular row. Other radial displacement devices can be imagined. The radial sliding of the hydrostatic annular seal 51 can be as follows: Figures 21 to 26 It can be done as shown, or as... Figures 27 to 33 As shown.

[0058] Therefore, during turbine engine operation, the hydrostatic annular seal 51 has a degree of freedom in the radial direction. In fact, under thermal effects, the annular row of stator blades 54 facing the annular portion 71 expands. The U-shape created by the connection between the upstream annular leg 66 and the downstream annular leg 67 facilitates the assembly and radial sliding guidance of the seal on the annular diaphragm 64. Thus, this U-shape expands radially under the expansion effect, and this U-shape ensures no radially outward thrust. Therefore, the hydrostatic annular seal 51 is guided, and the deformation due to temperature differences with adjacent / nearby components in the radial, circumferential, and even longitudinal directions is minimal.

[0059] To maintain the aforementioned pressure difference between the upstream and downstream chambers of the turbine, a secondary seal 72 is necessary. This secondary seal 72 prevents leakage between the radially inner annular wall 56 and the radially outer annular wall 55, ensuring that air flows only between the cylindrical cover 53 and the radially inner annular wall section 56.

[0060] Therefore, now refer to Figures 4 to 7 .

[0061] Figure 4 and 5 A hydrostatic annular seal 51, with a secondary seal 72 mounted and connected to the annular row of stator blades 54, is shown. This hydrostatic annular seal 51 is designed to be arranged longitudinally between two annular rows 73 of rotor blades, located on either side of the annular row of stator blades 54. As described above, the hydrostatic annular seal 51 includes a radially inner annular wall 56 and a radially outer annular wall 55, which are interconnected by an elastically deformable member 57. An annular flange is arranged facing the upstream face 74 of the elastically deformable member 57. This flange is supported by the radially outer annular wall 55. An annular gap exists between the radially inner end 76 of the ring 75 and the radially inner annular wall 56. This annular gap is sealed by the secondary seal 72, which will be described in detail below.

[0062] like Figures 4 to 6As shown, the first annular plate segment 77 is arranged circumferentially end-to-end and applied to the upstream surface 78 of the ring 75. The second annular plate segment 79 is applied to the upstream surface 80 of the first annular plate segment 77. The thickness of the plate segments 77 and 79 is between 0.1 and 0.6 mm. The second plate segment 79 can be offset circumferentially relative to the first plate segment 77, such that one second plate segment 79 is longitudinally arranged facing two axially adjacent first plate segments. The inner edge 81 of the second plate segment 79 is longitudinally aligned with the inner edge 82 of the first plate segment 77. The outer edge 83 of the second plate segment 79 is longitudinally aligned with the outer edge 84 of the first plate segment 77. The circumferential edges 85 and 86 of the first plate segment 77 are misaligned with the circumferential edges 87 and 88 of the second plate segment 79. The misalignment of the circumferential edges 85, 86, 87, and 88 of the first plate segment 77 and the second plate segment 79 prevents leakage due to annular gaps.

[0063] More precisely, such as Figure 7 As shown, the radially inner end 89 of the first plate segment 77 abuts against the radial surface 90 of the radially inner annular wall 56. The flange 75 includes an upstream extending inner annular edge 91a. The upstream surface 92 of the ring 75 is formed at the upstream end of the inner annular edge 91a of the flange 75. The first annular row of first plate segments 77 is arranged circumferentially end-to-end and applied to the upstream surface 92 of the ring 75. The materials of the first plate segments and the flange are determined to facilitate sliding between these two parts.

[0064] Flange 75 also includes an annular edge 91b extending downstream and forming at its radially outer end. (As...) Figure 5 As shown, the annular edge 91b radially covers the upstream end of the radially outer annular wall segment.

[0065] like Figures 4 to 7 As shown, plate segments 77 and 79 are connected to ring 75 by fastening elements 93 passing through openings 94 in plate segments 77 and 79. These fastening elements 93 secure the first plate segment 77 and the second plate segment 79 together to ring 75, which is itself supported by radially outer annular wall 66. The fastening elements may be pins. Openings 94 allow for a gap, enabling slight movement of plate segments 77 and 79.

[0066] Now for reference Figure 8 It shows a hydrostatic annular seal 150, designed to provide a seal between its connected stator annular row and cylindrical cover, as shown in the reference. Figure 2 As described. Figure 8As shown, this known type of annular seal 150 includes an inner annular wall 151 formed by circumferentially end-to-end segments 152. It also includes an outer annular wall 153 from which at least one annular leg or wall 154 may extend, including at least one hole 155 for inserting a shaft, preferably implemented by a pin, or by a smooth shank or spacer of a screw, intended to mate with a rectangular opening of a radial annular diaphragm supported by an inner annular platform of a stator blade annular row.

[0067] Each radially inner annular wall segment 152 is connected to the outer annular wall 153 via an elastically deformable member 156. Therefore, each radially inner annular wall segment is associated with an elastically deformable member 156.

[0068] Each elastic deformation member 156 includes two circumferentially extending and mutually parallel elastic strips 159. A first end of each strip 159 is connected to a first radial leg 158 supported by a radially inner annular wall segment, and a second end of each strip 159 is connected to a second radial leg 157 supported by a radially outer annular wall 153. While this implementation has proven effective, it does not provide an optimal trade-off between radial flexibility and torsional resistance for strips of a given thickness, as mentioned at the beginning of this description with reference to the background art.

[0069] Therefore, a hydrostatic annular seal 100 formed by multiple circumferentially distributed sealing sections is proposed. Figure 9 Only one is shown in the diagram. Each sealing segment 102a, 102b includes radially outer annular wall segments 106a, 106b and radially inner annular wall segments 110a, 110b, which are interconnected by elastic deformation members 105a, 105b. The sealing segments 102a, 102b are circumferentially adjacent in pairs, and their respective elastic deformation members 105a, 105b are integrally implemented as a common elastic deformation member 105. This common elastic deformation member 105 connects the radially inner annular wall segments 110a, 110b of the two circumferentially adjacent sealing segments, and the radially outer annular wall segments 106a, 106b of the sealing segments form an integral outer cover 106.

[0070] Therefore, each common elastic member 105 is elastically connected to at least two radially inner annular wall segments 110a, 110b, in this case exactly two, which are circumferentially adjacent and connected to two radially outer annular wall segments 106a, 106b. The radially inner annular wall segments 110a, 110b sequentially form the radially inner annular walls of the hydrostatic annular seal 100. Figure 9 In the embodiment shown, each elastic deformation member 105 is connected to two circumferentially adjacent internal segments 110a and 110b, one of which 110a is referred to as the main segment and the other 110b as the secondary segment.

[0071] Each common elastic member 105 is observed to include at least one first elastically deformable circumferential strip 112a, 112b and at least one second elastically deformable circumferential strip 114a, 114b, which are connected to the outer annular wall via first circumferential ends (opposite to each other), and their second ends 122 (opposite to each other in the circumferential direction relative to the first ends) are respectively connected to the main segment 110a and the secondary segment 110b. The first ends 116 of the at least one first strip 112a, 112b and the first ends 116 of the at least one second strip 114a, 114b are arranged in circumferentially opposite positions.

[0072] exist Figure 9 In the study, it was observed that the at least one first stripe 112a, 112b and the at least one second stripe 114a, 114b comprise two stripes radially spaced apart from each other. The first stripe 112a, 112b and / or the second stripe 114a, 114b can be as follows: Figure 9 The strips shown are generally parallel to each other. The first strips 112a, 112b and / or the second strips 114a, 114b may also form an angle between them. Of the first strips 112a, 112b, one first strip 112b is the first inner strip 112b, and the other first strip 112a is the first outer strip. Of the second strips 112a, 112b, one second strip 112b is the second inner strip, and the other second strip 112a is the second outer strip.

[0073] The first ends 116 of the first and second elastic strips can be as follows Figure 9 As shown, they are connected to the same first leg 118, which can extend generally radially. A first inner strip 111b and / or a second inner strip 114b can be connected to the radially inner end of the first leg 118. A first outer strip 112a and / or a second outer strip 114a can be connected near the radially outer end of the first leg 118, which is connected to the radially outer annular wall.

[0074] The radial inner end of the first leg 118 is not directly connected to one of the two circumferentially adjacent main segments 110a and secondary segments 110b. The connection between the first leg 118 and segments 110a and 110b is indirectly made through the first strips 112a and 112b and the second strips 114a and 114b, as well as the second legs 120a and 120b, which will be described in the following paragraphs.

[0075] exist Figure 9 In the embodiment shown, the legs are sized so that they are not deformable, and deformation occurs at the strips.

[0076] The second ends 122 of the first and second elastic strips can be as follows Figure 9The first strip 118 is shown connected to the second legs 120a and 120b, which can extend approximately radially. Two second legs 120a and 120b are observed, circumferentially arranged on either side of the first leg 118 and positioned approximately symmetrically circumferentially relative to the position of the first leg 118. One second leg, referred to as the second main leg 120a, is connected to the second end of the first strip 112a and 112b; the other second leg, referred to as the secondary leg 120b, is connected to the second end of the second strip 114a and 114b.

[0077] according to Figure 9 In the illustrated embodiment, the common elastic deformable member thus has a first circumferential end radial leg 120a connected to the circumferential end of the inner annular wall segment 110a of the first sealing segment 102a, and a second circumferential end radial leg 120b connected to the circumferential end of the inner annular wall segment 110b of the second sealing segment 102b. Each circumferential end radial leg 120a, 120b is connected to a common radial leg 118 via first strips 112a, 112b and second strips 114a, 114b, which extend circumferentially to connect each circumferential end radial leg 120a, 120b to the common radial leg 118.

[0078] The terms “primary” and “secondary” are used only to distinguish the two secondary legs 120a and 120b and their connection with the primary segment 110a and the secondary segment 110b.

[0079] The first outer strip 112a and / or the second outer strip 114a may be connected to the radially outer ends of the second main leg 120a and the secondary leg 120b. The first inner strip 112b and / or the second inner strip 114b may be connected near the radially inner ends of the second legs 120a and 120b, which are connected to the shoe parts 110a and 110b. More precisely, the radially inner end of the second main leg 120a is connected to the main segment 110a, for example, near its circumferential end. The radially inner end of the second leg 120b is connected to the secondary shoe part 110b, for example, near its circumferential end. The two ends of the main segment 110a and the secondary segment 110b are opposite to their circumferentially opposite ends.

[0080] refer to Figure 8 The above-described embodiment allows for the removal of one connecting leg from each pair of main segments 110a and secondary segments 110b, which reduces the structural complexity of the hydrostatic annular seal 100. Significant spatial gains are also achieved in the circumferential direction. Compared to the prior art, a thicker strip can therefore be used at constant stiffness, thus limiting torsion. Therefore, only three legs are needed for each pair of main segments 110a and secondary segments 110b, instead of... Figure 8 The four of them.

[0081] The annular seal 100 may include means for enabling the hydrostatic annular seal to slide radially relative to the radial annular diaphragm of the stator blade annular row. These means may be, for example, referenced to… Figures 21 to 25 Or refer to Figures 27 to 33 The type described.

[0082] Now for reference Figures 10 to 20 .

[0083] Figures 10 to 16 The third hydrostatic annular seal 201 and its variants are schematically shown.

[0084] Figure 10 A hydrostatic annular seal 201 is shown, comprising a radially inner annular wall 202, an elastically deformable member 203, and a radially outer annular wall 204. The radially inner annular wall 202 is formed by a plurality of shoe segments 205. The shoe segments 205 shown are connected to the radially outer annular wall 204 via the elastically deformable member 203. The elastically deformable member 203 includes an inner leg 206 and an outer leg 207. Each leg 206, 207 is generally flat. The inner leg 206 includes a radially inner end 208 to which the shoe segment 205 is connected. The outer leg 207 includes a radially outer end 209 to which the radially outer annular wall 204 is connected. The inner leg 206 includes a radially outer end 210 connected to the radially inner end 211 of the outer leg 207 via a connecting wall 215. Figure 10 In the embodiment shown, the inner leg 206 and the outer leg 207 extend radially such that the radially inner end 211 of the outer leg 207 is arranged radially inside the radially outer end 210 of the inner leg 206.

[0085] Figure 11 The illustrated hydrostatic annular seal 201 includes an elastically deformable member 203 formed by a plurality of elastically deformable members. Therefore, it includes a first elastically deformable member 212 and a second elastically deformable member 213. The first elastically deformable member 212 and the second elastically deformable member 213 are arranged such that the inner leg 206 (and outer leg 207, respectively) of the first member 212 is axially adjacent to the outer leg 207 (and inner leg 206, respectively) of the second member 212.

[0086] Figure 12 The illustrated hydrostatic annular seal 201 includes an elastically deformable member 203 formed by three elastically deformable members (a first member 212, a second member 213, and a third member 214). The first member 212 and the second member 213 are arranged such that the inner leg 206 of the first member 212 (and its outer leg 207, respectively) is axially adjacent to the outer leg 207 (and its inner leg 206, respectively) of the second member 213. The third member 214 is arranged such that its outer leg 207 (and its inner leg 206, respectively) is axially adjacent to the inner leg 206 (and its outer leg 207, respectively) of the second member 213.

[0087] The outer leg 207 can be inclined relative to the tangent of the radially outer annular wall 204 at the connection point between the outer leg 207 and the radially outer annular wall 204. Similarly, the inner leg 206 can be inclined relative to the tangent of the radially inner annular wall 202 at the connection point between the inner leg 206 and the radially inner annular wall 202. This angle can be between 10° and 150°. Therefore, it can be understood that the inner leg 206 and the outer leg 207 can have different inclinations, such as... Figure 13 As shown. Other embodiments are of course possible as well. The inclination of legs 207 and 206 relative to the radial direction allows for the restriction of displacement of the elastically deformable member in the longitudinal direction.

[0088] Each connecting wall 215 may include a thickness defined by the radial dimension of the connecting wall 215, between 0.5 and 10 mm, and / or a width defined by the longitudinal dimension of the connecting wall 215, between 2 and 30 mm.

[0089] Each leg 206, 207 may include at least one of the following parameters:

[0090] - The width in the longitudinal direction is between 2 and 30 millimeters.

[0091] - In its extending direction, the dimension between its radial inner and outer ends is between 3 and 60 mm.

[0092] - The dimension perpendicular to the direction of leg extension is between 0.5 and 10 mm.

[0093] like Figure 14 As shown, the hydrostatic annular seal 201 includes a first component 212 and a second component 213. The connecting wall 215 restricts upstream / downstream tilting movement due to its torsional resistance. The deformable inner and outer legs 206, 207 achieve radial movement primarily through the bending of the elastically deformable members. The tilting of legs 206 and 207 relative to the inner and outer annular walls 202, 204 restricts displacement of the shoe portion 205 along the longitudinal axis.

[0094] like Figure 15 As shown, the hydrostatic annular seal 201 may include a first elastic deformation member 212 and a second elastic deformation member 213. The connecting wall 215 of the first member 212 includes a radially inner surface, continuously formed by a concave surface 216 followed by a convex surface 217. The connecting wall 215 of the second member 213 includes a radially inner surface, continuously formed by a convex surface 217 followed by a concave surface 216.

[0095] Figure 16The hydrostatic annular seal 201 shown includes an elastically deformable member 203, which comprises a first member 212 and a second member 213. The connection between the radially outer end of the inner leg 206 and the connecting wall 215 of each member is at a right angle. Similarly, the connection between the radially inner end of the outer leg 207 and the connecting wall 215 of each member is also at a right angle. Figure 16 The inclination of components 212 and 213 is shown.

[0096] Figures 17 to 20 An alternative embodiment of the connecting wall 215 of the hydrostatic annular seal 201, connected to the legs of the radially inner annular wall 202 and the radially outer annular wall 204, is schematically shown. Only the outer leg 207 is shown, but the description also applies to the inner leg 206.

[0097] Figure 17 Leg 207 is shown, whose cross-section is approximately constant between its inner and outer ends.

[0098] Figure 18 Leg 207 is shown, its cross-section varies radially, and... Figure 18 This is added in special cases. The approximate shape here is a triangle.

[0099] Figure 19 Leg 207 is shown, including a concave circumferential surface facing the other leg and a generally flat circumferential surface facing the opposite leg.

[0100] Figure 20 Leg 207 is also shown, including, for example Figure 19 The concave and flat circumferential surface is shown. However, in this embodiment, the radially inner end of the leg has a smaller dimension than the radially outer end.

[0101] The hydrostatic annular seal 201 comprises at least one material or combination of materials from the following list: steel, titanium, aluminum alloy, cobalt-based alloy, nickel-based alloy, and / or any composite material.

[0102] Now for reference Figures 21 to 26 These figures relate to the radial sliding of the hydrostatic annular seal 300 on the annular diaphragm 305 of the stator blade annular row.

[0103] Figure 21 A segment 310 of a stator blade annular row or ring is shown, in this case, as a guide. This segment is arranged circumferentially end-to-end to form a stator blade ring. This ring is equipped with a hydrostatic annular seal 300, such as... Figure 26 As shown. It can be any type described in this specification, such as the reference. Figure 9 or Figures 10 to 20 Those described.

[0104] All loop segments 310 of the guide are identical, therefore the following description refers to... Figure 21 The segment shown applies to the other segments 310 of the guide.

[0105] refer to Figure 21 This section includes the inner platform 312, the outer platform 314, and the blade 316.

[0106] Each blade 316 is connected to the inner platform 312 on one side and the outer platform 314 on the other side, so as to extend radially through the main airflow channel, which is radially defined by these platforms 312, 314.

[0107] The blades of segment 310 are spaced apart from each other in the circumferential direction. The outer platform 314 is configured to connect to the casing of the turbine engine 1.

[0108] Section 310 includes a radial partition 305, forming mounting feet for the guide 310, and connecting to the inner platform 312 to extend radially inward from the inner platform 312 toward the cylindrical cover 11 of the rotor, the cylindrical cover being as... Figure 2 or Figure 38 or Figure 41 As shown.

[0109] Radial partition 305 is configured to work with hydrostatic annular seal 300 ( Figure 26 The hydrostatic annular seal 300 includes a segmented radial annular wall 320, formed by a plurality of radially inner annular wall segments arranged circumferentially end-to-end. The latter is connected to a radially outer annular wall 325 via an elastically deformable member 322, which is connected to a sealing support 324. The sealing support includes a radially outer annular wall 323 and at least one radially outwardly oriented radial annular leg 326, preferably as follows: Figure 22 The two radial annular legs are shown.

[0110] In this regard, Figure 22 Only the circumferential section of the sealing support 324 is shown.

[0111] refer to Figure 22 The radial annular legs 326 or flanges are generally parallel and spaced apart from each other in the longitudinal direction to form a U-shaped cross section, defining the space in which radial partitions 305 can be inserted into each segment 310.

[0112] The longitudinal distance between the legs 326 is chosen to allow for longitudinal positioning and proper longitudinal retention of the segment 310, while still allowing for radial sliding movement of the partition 305 between the legs 326 (see below). Specifically, axial or longitudinal clearances J1 and J2 are provided between the legs 326 and the partition 305 during assembly to allow for this radial movement. Clearance J1 extends between the upstream leg 326 and the partition 305, and clearance J2 extends between the partition 305 and the downstream leg 326.

[0113] In addition, the partition 305 is fitted with a radial clearance J3 relative to the bottom of the space defined by the leg 326.

[0114] exist Figure 26 In the embodiment shown, the radially outer annular wall 324 is integrally formed with the elastically deformable member 322, the radially inner annular wall 320, and at least one annular leg 326.

[0115] Figure 23 Two holes 328 are shown, respectively, formed in the upstream leg 326 and the downstream leg 326.

[0116] Hole 328 has a common axis A2 and is provided to receive a pin 330 as shown in the figure. Pin 330 is a cylindrical component with axis A2, having two shoulders that define an upstream portion 332, a middle portion 334, and a downstream portion 336.

[0117] The diameter of the middle portion 334 is smaller than the diameters of the upstream portion 332 and the downstream portion 336. The diameter of the upstream portion is also smaller than the diameter of the downstream portion.

[0118] The bore 328 of the upstream leg 326 of the hydrostatic annular seal 300 is sized to be the upstream portion 332 of the receiving pin 330 to form a tight fit. Similarly, the bore 328 of the downstream leg 326 of the hydrostatic annular seal 300 is sized to be the downstream portion 336 of the receiving pin to form a tight or sliding fit.

[0119] After assembly, pin 330 is thus supported by upstream leg 332 and downstream leg 436, forming a complete connection.

[0120] Pin 330 is configured to mate with the guide, particularly with the radial diaphragm 305 of section 310.

[0121] refer to Figure 21 Each segment of the partition 310 includes an opening 338 for this purpose, which has a radially extending rectangular groove shape.

[0122] In this example, opening 338 opens radially toward the interior of ring segment 310. It could not open radially. This would require different pin geometry and different assembly steps than those presented here.

[0123] The opening 338 has a width, or circumferential dimension, that allows the middle portion 334 of the pin 330 to pass through, i.e., the width is greater than the diameter of the middle portion 334 of the pin 330.

[0124] The width of the opening 338 is also smaller than the diameter of the upstream portion 332 and the downstream portion 336 of the pin 330. Therefore, if the connection between the pin 330 and the upstream leg and the downstream leg 326 breaks, the partition 305 of the segment 310 forms an axial stop for retaining the pin 330.

[0125] The assembly of the stator element involves pre-inserting the pin 330 into the upstream leg and the downstream leg 326 by passing the upstream portion 332 of the pin 330 through the hole 328 of the downstream leg 326.

[0126] The pin is then secured to the leg by forcibly inserting the upstream portion 332 of the pin 330 into the hole 328 of the upstream leg 326, while simultaneously inserting its downstream portion 336 into the hole 328 of the downstream leg 326.

[0127] Then segment 310 moves radially inward so as to axially introduce partition 305 between legs 326 and insert the middle portion 334 of pin 330 into opening 338 of partition 305.

[0128] These assembly steps led to Figure 25 The configuration shown.

[0129] In this configuration, pin 330 forms a circumferential stop for annular segment 310, preventing the hydrostatic annular seal 300 and annular segment 310 from rotating relative to each other around the axis of segment 310, and allowing the hydrostatic annular seal 300 to be centered relative to this axis A1.

[0130] On the other hand, given the corresponding dimensions of the middle portion 334 of the pin 330 and the rectangular opening 338, the assembly allows for radial displacement of the hydrostatic annular seal 300 relative to the segment 310.

[0131] The stator assembly may include other pins similar to pin 330, each of which engages with a partition 305 according to the principles described above.

[0132] Of course, these principles can be generalized. For example, each segment 310 of the guide can mate with multiple pins similar to pin 330.

[0133] Generally, the present invention enables the hydrostatic annular seal 300 and guide 310 to be connected to each other according to a defined radial degree of freedom or radial sliding connection, which can compensate for differential thermal expansion within the turbine 9.

[0134] Finally, the forced engagement of pin 330 in the orifice 328 with the upstream leg and downstream leg 326 helps reduce gas leakage outside the internal airflow.

[0135] Now for reference Figures 27 to 33 .

[0136] Figures 27 to 32The embodiment shown presents a hydrostatic annular seal 419, wherein the radially outer annular wall 401 is bolted to the sealing support 402.

[0137] The hydrostatic annular seal 419 therefore includes a segmented radially inner annular wall 420 and a segmented radially outer annular wall 401.

[0138] Sealing support 402 is installed for use in the above reference Figure 21 The radial annular partition 403 slides radially. The annular sealing support 402 includes an upstream annular leg 404 and a downstream annular leg 405. The upstream annular leg 404 and the downstream annular leg 405 are connected to each other through their bases, forming a U-shape. The radial annular partition 403 includes a rectangular opening 406 that opens radially inward.

[0139] exist Figures 27 to 31 In one particular embodiment shown, the sealing support 402 includes longitudinal and circumferential protrusions 415 defining a radial groove therebetween, wherein a radially outwardly projecting radial tongue 416 of the radially outer annular wall segment 401 of the hydrostatic annular seal is engaged. This form fit prevents the annular seal from rotating on the sealing support 402.

[0140] like Figure 33 As shown, plate 414 can be longitudinally inserted between radial annular partition 403 and sealing support 402. Plate 414 includes two radial annular arms that are interconnected by a generally cylindrical base. The arms include free end portions that are radially inwardly curved to form a curved portion that mates with the lateral protrusions of the annular legs 404, 402 of the annular sealing support.

[0141] Each elastically deformable member 407 can be elastically connected to at least two circumferentially adjacent radially inner annular wall segments 408a, 408b. Figure 28 , 29 In the embodiments shown in 32, each elastic deformation member 407 is connected to two circumferentially adjacent radially inner annular wall segments, one referred to as the primary segment and the other as the secondary segment.

[0142] It was observed that each elastic deformation member 407 includes at least one first elastic deformation circumferential strip 408 and at least one second elastic deformation circumferential strip 409, which are connected to the radially outer annular wall 401 at a first common end, and their second ends (opposite to each other in the circumferential direction relative to the first common end) are respectively connected to the radially inner annular wall segments 408a and 408b of the shoe part.

[0143] exist Figure 28 , 29In 32, it is observed that the at least one first strip 408 and the at least one second strip 409 comprise two strips spaced apart from each other in the radial direction. The first strip and / or the second strip can be as follows: Figure 28 , 29 The first and / or second stripes are approximately parallel to each other, as shown in Figure 32. They may also form an angle with each other. In the first strip, one first strip 408 is the first inner strip 408, and the other is the first outer strip 408. In the second strip, one second strip 409 is the second inner strip 409, and the other is the second outer strip 409.

[0144] The first ends of the first and second elastic strips can be as follows: Figure 28 , 29 As shown in Figure 32, it is connected to the same first leg 410, which can extend generally radially. A first inner strip 408 and / or a second inner strip 409 can be connected to the radially inner end of the first leg 410. A first outer strip 408 and / or a second outer strip 409 can be connected near the radially outer end of the first leg 410, which is connected to the radially outer annular wall 401.

[0145] The radial inner end of the first leg 410 is not directly connected to one of the two circumferentially adjacent shoe parts. The connection between the first leg 410 and the radial inner annular wall is made indirectly through the first and second strips and the second leg, which will be described in the following paragraphs.

[0146] The second ends of the first and second elastic strips can be as follows: Figure 28 , 29 As shown in Figure 32, it is connected to the second leg 411, which can extend generally radially. Two second legs 411 are observed, circumferentially arranged on either side of the first leg 410, and can be positioned approximately circumferentially symmetrically to each other relative to the position of the first leg 410. One second leg 411, referred to as the second main leg 411, is connected to the second end of the first strip; the other second leg 411, referred to as the secondary leg 411, is connected to the second end of the second strip.

[0147] The terms "primary" and "secondary" are used only to distinguish between two secondary legs and their connection to the corresponding primary or secondary foot part.

[0148] The first outer strip 408 and / or the second outer strip 409 may be connected to the radially outer ends of the second main leg and the secondary leg. The first inner strip 408 and / or the second inner strip 409 may be connected near the radially inner end of the second leg 411, which is connected to the shoe part. More precisely, the radially inner end of the second main leg 411 is connected to the main shoe part, for example, near its circumferential end. The radially inner end of the second leg 411 is connected to the secondary shoe part, for example, near its circumferential end. The two ends of the main shoe part and the secondary shoe part are opposite to their circumferentially opposite ends.

[0149] like Figure 30 As shown, the ring or spacer 413 acts as a shaft to allow the seal support 402 to expand freely.

[0150] exist Figure 32 In the specific embodiment shown, the radial outer annular wall 401 is formed by a radial ring 417.

[0151] Now for reference Figure 34 and 35 The diagram shows a hydrostatic annular seal 501. The hydrostatic annular seal 501 includes a segmented radially outer annular wall 502, a segmented radially inner annular wall 503, and an elastically deformable member 504 disposed between the two inner and outer walls.

[0152] like Figure 34 As shown in Figure A, a radially outer annular wall 502 is fixed in a sealing support 505. Each radially outer annular wall segment 502 is equipped with a coupling member 506, which engages circumferentially and is held radially in a circumferential groove of the sealing support 505. The coupling member 506 has a circumferentially extending dovetail shape. The sealing support 505 includes an upstream wall 507 that extends radially inward and is formed facing the upstream surface of the hydrostatic annular seal 501 to facilitate sealing of the elastically deformable member 504. The annular portion 505 includes an upstream annular leg 508 and a downstream annular leg 509. The upstream annular leg 508 and the downstream annular leg 509 have a U-shape, capable of... Figure 21 The stator blade annular array shown slides radially on a radial annular partition. The radial annular partition may include a radially inwardly opening rectangular or oblong opening, through which fastening devices passing through the upstream and downstream legs of the sealing support 505 are engaged. Figure 24 and 25 The aforementioned pin.

[0153] Figure 34 B illustrates the presence of a locking member on the radially outer annular wall segment of the sealing support 505. Locking is achieved here by an interference fit of a pin 513 through a coupling member 506 that passes between the support and the seal 501.

[0154] like Figure 35 As shown in Figure A, the sealing support can be a 360° component including a side opening 509 that enters into a circumferential groove within the sealing support. Therefore, the circumferential groove is made accessible to allow each seal to be installed in the side opening by longitudinal translation followed by rotation.

[0155] The annular seal can be of any type. For example, it can be a reference. Figure 9The described type includes two radially inner annular wall segments 510a and 510b, each integrally formed with a radial leg 515. Each radial leg 515 connects to the same leg 514 circumferentially arranged between the two legs 515. Further details of the seal can be found in... Figure 9 As seen in [the document], the coupling between seal support 505 and seal 401 can be achieved using other seals described in this document, such as those mentioned in [reference]. Figures 10 to 15 The seal described.

[0156] After all sealing sections are assembled, an annular flange 519 is installed on the downstream face of the seal to block the side opening. The flange therefore includes a protrusion 517 that is bolted to the seal support 505.

[0157] Figure 36 A specific embodiment of the hydrostatic annular seal 600 is shown.

[0158] As described above, the hydrostatic annular seal 600 includes a radially inner annular wall and a radially outer annular wall, with an elastically deformable member formed between them. Figure 36 This description applies to any annular seal described with reference to the accompanying drawings. The elastically deformable seal may be as described in the reference drawings. Figure 9 The type described, or Figures 10 to 15 One of the types. In Figure 36 The radial leg 618 and the elastically deformable strip 620 are shown in the figure.

[0159] The radially inner annular wall is segmented and comprises multiple circumferentially end-to-end segments 610. Each segment 610 includes a first circumferential edge 612 and a second circumferential edge (not shown) circumferentially opposite the first edge 612. The first circumferential edge 612 of segment 610 is circumferentially end-to-end with the second circumferential edge of the circumferentially adjacent segment 610.

[0160] like Figure 36 As shown, regarding the first circumferential edge 612 of segment 610, a slit 614 is formed in the thickness of segment 610 and the first circumferential edge 612. This slit 614 is circumferentially open and may have a generally rectangular cross-sectional shape. The same slit 614 is formed in the second circumferential edge of each shoe segment.

[0161] According to this document, the tongue 616 is partially installed in the slit 614 of the first circumferential edge 612 and in the opposing slit 614 of the second circumferential edge of the circumferentially adjacent shoe portion 610.

[0162] For reference Figure 36Each internal segment 610 may include a radially inner surface comprising a first generally cylindrical surface portion 610a, a second surface portion 610b formed by a recess, a third generally cylindrical surface portion 610c, and preferably a fourth truncated conical surface portion 610d, the cross-section of which increases downstream. The recess extends from one circumferential end of the segment 610 to the other end and has a concave curved shape, which may be formed by a longitudinally continuous flat surface. Figure 37 The aforementioned outer shell can also be formed in the recess.

[0163] It was observed that slit 614 was formed approximately radially outside the recess, such that a plane perpendicular to the longitudinal axis simultaneously transcribed slit 614 and the recess.

[0164] In one particular embodiment, the slit extends to the third portion 610c. The slit opens upstream in both the circumferential and axial directions. The upstream opening is sealed by a seal (not shown) that prevents airflow at the upstream opening. [The following text appears to be a separate, unrelated section:] ...can be used as... Figures 5 to 7 The aforementioned seal.

[0165] Now for reference Figure 37 The diagram illustrates a hydrostatic annular seal 700, comprising a radially outer annular wall 710 and a radially inner annular wall 712, the radially inner annular wall being segmented and formed by a plurality of circumferentially end-to-end arranged segments 714. An elastically deformable member 716 is radially arranged between the inner wall 712 and the outer wall 710. The seal 700 can be installed at the radially inner end of the stator blade annular row of a turbine. It can be installed in any other location where it can have the same function, such as at the radially outer end of the stator blade annular row, or at the interface between any rotating and stationary parts in a turbine engine.

[0166] As shown in the figure Figure 37 The segment shown is Figure 8 The segments shown are the same shape. However, the following references Figure 37 The description also applies to other seals in this document, especially those such as Figures 9 to 12 The seal shown.

[0167] Each elastically deformable member 716 may include two generally radial legs 718, 720, wherein the first 720 is connected to the segment 714 and the second 718 is connected to the outer annular wall 710. The two legs 718, 720 are interconnected by an elastic strip 722.

[0168] It is proposed to form a housing 724 on the radially inner surface of each segment 714, the housing 724 being radially inwardly open, the housing 724 having upstream and downstream surfaces 724a, and a circumferential surface 724b formed in the thickness of the segment 714. The housing also includes a bottom wall 724c that connects the radially outer ends of the circumferential wall 724b, the upstream and downstream walls 724a. Figure 37 Parts A, B, C, and D in the diagram represent different directions of the seal and the cross-sections of parts B, C, and D.

[0169] It can be observed that the outer casing 724 may have a generally parallelepiped shape, i.e., its side or circumferential walls 724b, upstream and downstream walls 714a, and bottom wall 724c are generally flat, regardless of the connection radius between the walls. The outer casing 724 may be approximately circumferentially centered over the circumferential range of segment 714.

[0170] The housing 724 thus manufactured does not have openings in the circumferential or longitudinal direction because the opposing circumferential surfaces 724b and the opposing upstream and downstream surfaces 724a are formed in the thickness of the segment 714.

[0171] The housing 724 may extend over 80% of the circumferential range of the segment. Furthermore, the housing 724 may extend over 50% of the longitudinal range of the segment 714.

[0172] In one particular embodiment of the seal 700, the depth of each housing 724 is at least 50% of the maximum radial dimension of the segment 714.

[0173] Figure 37 D shows that the radial inner surface of segment 714 includes a first generally cylindrical surface portion 726a, a second surface portion 716b forming a recess, a third generally cylindrical surface portion 726c, and a fourth truncated conical surface portion 726d, the cross-section of which increases downstream.

[0174] According to this document, the housing 724 is formed in the annular recess 726b. The recess 726b may have a concave curved shape. Here, it consists of a series of conical surfaces.

[0175] The elastic member 716 can have the following characteristics: Figures 9 to 12 The shapes described. In this case, the main segment and the secondary segment each have a housing 724, the housing being formed within their thickness. Further characteristics of the elastic member will be referenced as follows: Figures 9 to 12 The description made.

[0176] like Figure 37 The integration of the housing 724 can be implemented on any annular seal and assembly described in this document.

[0177] The annular seal 700 may also include slits formed in the circumferential edges of each segment for receiving, such as Figure 36 The aforementioned sealing tongue.

[0178] Now for reference Figure 38 A partial view schematically illustrates an assembly 800 of a turbine engine having a longitudinal axis according to this document. Preferably, this assembly is used as referenced above. Figure 1 The turbines of the aforementioned turbine engines, particularly low-pressure turbines, are also relevant. This document also relates to any type of turbine engine that includes such a turbine, such as a turboprop or turbojet engine for aircraft.

[0179] Assembly 800 includes a cylindrical shroud 811 designed to rotate about a longitudinal axis and an annular row of stator blades 820. Assembly 800 may also include two annular rows of moving blades 810 arranged longitudinally on either side of the annular row of stator blades 820 and interconnected by the cylindrical shroud 811. The annular row of stator blades 820 is equipped with a hydrostatic annular seal 822, which is radially arranged inside the annular row of stator blades 820 and outside the cylindrical shroud 811, and the hydrostatic annular seal 822 engages with the cylindrical shroud 811 in a non-contact sealing manner.

[0180] In addition, the cylindrical cover 811 includes an annular layer 812 facing the hydrostatic annular seal 822, which is made of a first material with a hardness greater than that of the material of the radial inner end 823 of the hydrostatic annular seal 822 facing the annular layer 812.

[0181] Using a harder material for the annular layer increases the mechanical strength of the cylindrical cover relative to the hydrostatic annular seal. Therefore, in the event of rotor eccentricity due to sudden manipulation or malfunction, this assembly mechanically protects the cylindrical cover during prolonged contact between the hydrostatic annular seal and the cylindrical cover. The mechanical integrity of the cylindrical cover is thus maintained.

[0182] Specifically, the cylindrical cover 811 has a circular cross-section with a constant radius along the longitudinal axis in at least one longitudinal portion of the cylindrical cover. This shape provides better control over the gap between the hydrostatic annular seal and the cylindrical cover. In particular, the cylindrical cover 811 has no lip.

[0183] The hydrostatic annular seal preferably comprises a radially outer annular wall, a radially inner annular wall, and a plurality of elastically deformable members, particularly distributed circumferentially around a longitudinal axis. Each of the plurality of elastically deformable members includes a first generally radial leg connected to the radially outer annular wall, a second generally radial leg connected to the radially inner annular wall, and at least one circumferentially extending elastically deformable strip. The at least one strip is connected to the first leg at one circumferential end and to the second leg at the opposite circumferential end. In other words, the first leg performs the connection between one circumferential end of the at least one strip and the radially outer annular wall, and the second leg performs the connection between the other circumferential end of the at least one strip and the radially inner annular wall. The hydrostatic annular seal is thus capable of radial deformation by the flexibility provided by the at least one strip connecting the radially inner and radially outer annular walls. The radially inner and outer annular walls, legs, and strips are specifically sized to control the radial deformation of the hydrostatic annular seal, thereby controlling the gap between the hydrostatic annular seal and the cylindrical cover. Such deformable members, as Figure 8 As shown.

[0184] Elastic deformation members can also be like... Figures 9 to 12 The type of description.

[0185] The first material must be harder than the material used for the shoe body.

[0186] The shoe part, made of a material with higher abrasion resistance than the cover coating, ensures that wear during contact between the cover and the hydrostatic seal shoe part occurs only on the shoe part, not on the cover.

[0187] The shoe section can have a particularly aerodynamic shape. Through the negative and positive pressure on both sides of the shoe section, this increases the gap between the cylindrical cover and the hydrostatic annular seal when they are close to each other, and conversely, reduces the gap between the cylindrical cover and the hydrostatic annular seal when they are far apart.

[0188] The hydrostatic annular seal is preferably made of metal.

[0189] The first material can also have greater wear resistance than the material of the radial inner end 823 of the hydrostatic annular seal 822 facing the annular layer 812.

[0190] A portion 814 of the cylindrical cover 811, extending longitudinally between the two annular rows of moving blades 810, is made of a first material, which has a harderness than that of the second material. In other words, portion 814 of the cylindrical cover 811, made of the second material, connects the two annular rows of moving blades. The second material is particularly well-suited to ensure the mechanical transmission of torque between the two annular rows of moving blades 810.

[0191] The wear resistance of the second material can be lower than that of the first material.

[0192] The second material can be, in particular, steel, nickel-based alloys, or cobalt-based alloys.

[0193] The first and second materials possess mechanical strength and temperature resistance properties that are consistent with the thermomechanical operating conditions of a turbine engine.

[0194] The annular layer 812 may have a longitudinal dimension L1, which is larger than the longitudinal dimension L2 of the hydrostatic annular seal 822 along the longitudinal axis X. This feature ensures that even if relative longitudinal movement occurs between the cylindrical cover 811 and the annular row of stator blades 820, the hydrostatic annular seal 822 can still face the annular layer 812 radially. This relative longitudinal movement is commonly referred to as longitudinal slip. Longitudinal slip can occur at different stages of turbine engine operation.

[0195] refer to Figure 39 The cylindrical cover 811 may have an annular recess 813 designed to receive the annular layer 812. In particular, the annular recess 813 and the annular layer 812 may have the same thickness. In other words, the annular layer 812 may not add any additional thickness to the cylindrical cover 811.

[0196] refer to Figure 40 The annular layer 812 may form a protrusion relative to the first radially outer surface 815 of the cylindrical cover 811. The first radially outer surface 815 of the cylindrical cover 811 may specifically correspond to the innermost surface of the radial periphery of the cylindrical cover 811. For example, the annular layer 812 may form a ring, i.e., extend in 360°. This layer may be partially installed inside the cover and partially form a protrusion relative to the outer surface of the cover.

[0197] The annular layer 812 may have a radial thickness h to provide sufficient mechanical strength for the annular layer in contact with the cylindrical cover and the hydrostatic annular seal.

[0198] According to another aspect, a method for manufacturing the component 100 as described above is described. The method includes the following steps:

[0199] - Place the annular layer 812 on the cylindrical cover 811.

[0200] - Machining the radial outer surface 816 of the annular layer 812.

[0201] Then, the method ensures that the annular layer 812 conforms to the dimensional constraints, geometric tolerances and surface conditions of the cylindrical cover 811.

[0202] Now for reference Figure 41 A partial cross-sectional view of an assembly 900 of a turbine engine having a longitudinal axis, according to this document, and two enlarged views of the assembly are schematically shown. Preferably, this assembly is used in the turbine of a turbine engine, particularly a low-pressure turbine, as referenced above. Figure 1 This document also relates to any type of turbine engine that includes such a turbine, such as an aircraft turboprop or turbojet engine.

[0203] Assembly 900 includes a shroud 931 intended to rotate about a longitudinal axis X and a stator stage 920 extending about the longitudinal axis X and located radially outside the shroud 931. The shroud 931 may have a cylindrical shape, at least in one longitudinal portion of the shroud. The shroud 931 is particularly devoid of a lip. Assembly 900 may also include two annular rows of moving blades 930 intended to rotate about the longitudinal axis X, these two annular rows of moving blades 930 being arranged longitudinally on either side of the stator blade annular row 920 and interconnected via the shroud 931.

[0204] The stator stage 920 includes an annular row of stator blades 921. More specifically, the annular row of stator blades 921 includes a radially outer annular platform and a radially inner annular platform 922, with a plurality of blades extending between them. The annular row of stator blades 921 includes a radial diaphragm 923 extending radially inward from the radially inner annular platform 922.

[0205] The stator assembly 920 also includes a hydrostatic annular seal 950 mounted on an annular row of stator blades 921 and facing the cover 931 radially upward. The hydrostatic annular seal 950 is configured to engage with the cover 931 in a non-contact sealing manner.

[0206] Furthermore, the stator 920, more specifically the annular seal, includes an abutment system capable of directly or indirectly contacting the cover 931 and limiting radial displacement of the seal.

[0207] In the event of overspeed start-up of the turbine rotor, including the shroud, the hydrostatic annular seal may come into contact with the shroud due to the radial expansion of the shroud during overspeed. The support system advantageously allows for enhanced contact between the stator stage 920 and the shroud 931 to aid in braking the rotor during overspeed. This assembly 910 thus enables passive braking of the rotor. The assembly therefore protects the mechanical integrity of the rotor during overspeed.

[0208] More specifically, see reference Figure 42 The hydrostatic annular seal 950 includes a radially outer annular wall 951, a radially inner annular wall 952, and a plurality of elastically deformable members, particularly distributed circumferentially around a longitudinal axis. The hydrostatic annular seal 950 preferably includes a ring 959 extending radially outward from the radially outer annular wall 951. For example, this ring may have a U-shaped cross-section, with two arms of the U-shape arranged on either side of a radial partition. The two arms of the U-shape and the radial partition can be positioned by a centering pin.

[0209] The radially inner annular wall 952 and the radially outer annular wall 951 may be specifically formed by a plurality of circumferentially end-to-end arranged inner wall segments and a plurality of circumferentially end-to-end arranged outer wall segments, respectively. Each segment of the inner and outer walls is specifically connected to one of a plurality of elastically deformable members.

[0210] refer to Figure 43 , 44 45, each of the plurality of elastically deformable members 953 includes a first generally radial leg 955 connected to the radially outer annular wall 951, a second generally radial leg 956 connected to the radially inner annular wall 952, and at least one circumferentially extending elastically deformable strip 954. Thus, only the strip 954 is deformable, while the legs 955 and 956 are not deformable.

[0211] The at least one strip 954 is connected at its circumferential end to a first leg 955 and at its opposite circumferential end to a second leg 956. In other words, the first leg 955 performs the connection between one circumferential end of the at least one strip 954 and the radially outer annular wall 951, and the second leg 956 performs the connection between the other circumferential end of the at least one strip 954 and the radially inner annular wall 952. The hydrostatic annular seal is thus able to deform radially by the flexibility provided by the at least one strip connecting the radially inner and radially outer annular walls.

[0212] The radial inner and outer annular walls, legs, and strips are specially sized to control the radial deformation of the hydrostatic annular seal, thereby controlling the gap between the hydrostatic annular seal and the cover. The first gap J1 (e.g.) Figure 41 (As shown) Defined between the hydrostatic annular seal 950 and the cover 931, corresponding to the nominal clearance between the hydrostatic annular seal and the cover during operation. Alternatively, the first clearance can be defined as the turbine's cold clearance.

[0213] More precisely, the first leg 955 includes a radially outer end that is directly connected to the radially inner surface of the radially outer annular wall, and a radially inner end that is not directly connected to the radially inner annular wall. Similarly, the second leg 956 includes a radially inner end that is directly connected to the radially outer surface of the radially inner annular wall, and a radially outer end that is not directly connected to the radially outer annular wall.

[0214] Furthermore, the first leg 955 and the second leg 956 are specifically adapted to not deform radially. Only leg 956 is capable of radial movement along the radially inner annular wall and toward (or away from) the radially outer annular wall.

[0215] Each of the plurality of elastically deformable members 953 may specifically include a plurality of radially spaced strips 954, such as two strips. In particular, the strips are generally parallel to each other.

[0216] The radially inner annular wall can support the abrasive shoe part 958, which is radially arranged facing the cover 931 and is able to wear out when in contact with the cover 931.

[0217] The abrasive foot section 958 can have a particularly aerodynamic shape. The negative and positive pressure on both sides of the foot section increases the gap between the cover and the hydrostatic annular seal when they are close together, and conversely, reduces the gap when they are far apart.

[0218] refer to Figure 43 The illustration schematically depicts an exemplary embodiment of the components according to this document. The support system 940 includes at least one first radial support element 941 mounted by a radially outer annular wall 951, radially facing a second leg 956 of one of a plurality of elastically deformable members 953. Thus, the first radial support element can abut against the second leg. The support element in this case is a radial protrusion.

[0219] The at least one first radial support element 941 may also be mounted on a radially inner annular wall 952, radially facing one of the first legs 955 of a plurality of elastically deformable members 953. Therefore, the first radial support element can abut against the first leg.

[0220] The at least one first radial support element 941 may also be mounted by a second leg 956 of one of a plurality of elastically deformable members 953, radially facing the radially outer annular wall 951, or by a first leg 955 of one of a plurality of elastically deformable members 953, radially facing the radially inner annular wall 952. Thus, the first radial support element 941 may abut against the radially inner annular wall when supported by the first leg, or against the radially outer annular wall when supported by the second leg.

[0221] The support system 940 may also include at least two first radial support elements 941, one supported by a second leg 956, radially facing the radially outer annular wall 951 and vice versa, and the other supported by a first leg 955, radially facing the radially inner annular wall 952 and vice versa.

[0222] The at least one first radial support element 941 enhances the radial contact between the hydrostatic annular seal and the cover, thereby improving the braking of the cover under overspeed conditions. Furthermore, the first radial support element is then advantageously integrated directly into the hydrostatic annular seal, which is easier to implement from a manufacturing assembly perspective. In particular, the first radial support element 941 can be integrated as a single unit with the hydrostatic annular seal.

[0223] The first radial support element 941 can form a radial protrusion.

[0224] The first radial support element 941 may have a first support surface 945, which is generally parallel to the surface that the first support surface can abut.

[0225] like Figure 43 As shown, the second gap J2 between the first support surface 945 and the surface that the first support surface can abut must be less than or equal to the first gap J1. Figure 43 As shown, the second gap J2 between the first support surface 945 and the surface that the first support surface can abut can be 0.2 mm or greater. Therefore, when the cover deforms radially outward under the influence of overspeed, the radial outward movement of the radially inner annular wall of the seal is restricted, which ensures contact between the wall and the cover 931.

[0226] The first radial support element 941 may extend partially or over the entire longitudinal dimension of the hydrostatic annular seal 950.

[0227] In particular, the support system 940 preferably includes a plurality of first radial support elements 941. For example, each of the plurality of elastically deformable members may include one of the plurality of first radial support elements 941.

[0228] Figure 44 and 45 An exemplary embodiment of the component according to this document is shown. The component may include at least one second radial support element 942, 943, which forms fingers extending radially inward from the stator blade annular row. The at least one second radial support element 942, 943 is capable of radially abutting against a radially inner annular wall 952 (e.g., Figure 45 The second leg 956 (as shown) and / or one of the multiple elastic deformation members 953 Figure 44 (As shown).

[0229] The second radial support elements 942, 943 may be connected to the radial partition 923 at the first end. The second radial support elements 942, 943 may include a second end opposite to the first end, the radial outer end facing the radial outer surface of the radial inner annular wall 952 or the radial outer end of the second leg 956 of one of a plurality of elastic deformation members.

[0230] The second radial support elements 942, 943 may extend particularly over a portion or the entire longitudinal dimension of the radial partition 923.

[0231] The second radial support element can pass radially through at least one opening 957a, 957b, 957b' arranged in the hydrostatic annular seal.

[0232] refer to Figure 44The second radial support element 942 is capable of radially abutting against the second leg 956. A first opening 957a is specifically arranged in the radially outer annular wall 951, facing the radially outer end of the second leg 56. Therefore, the second radial support element 942 passes through the first opening 957a.

[0233] refer to Figure 45 The second radial support element 943 is capable of radially abutting against the radially inner annular wall 952, particularly against the radially outer surface of the radially inner annular wall 952. The second radial support element 943 passes through a first opening 957a, which is arranged in the radially outer annular wall 951, and second openings 957b, 957b', which are arranged in each of the at least one strip 954. The second radial support element 943 can be particularly circumferentially positioned between the first leg 955 and the second leg 956, particularly generally between the first leg 955 and the second leg 956.

[0234] The second radial support elements 942 and 943 may have a second support surface 946, which is generally parallel to the surface that the second support surface can abut.

[0235] The third gap between the second support surface and the surfaces that can abut against the second support surface can preferably be of the same order of magnitude as the first gap. This technical feature ensures that when the shroud extends radially under overspeed, and then the hydrostatic annular seal contacts the shroud, the hydrostatic annular seal cannot deform radially sufficiently to allow gas to pass between the hydrostatic annular seal and the shroud.

[0236] The assembly may include a plurality of second radial support elements 942, 943. For example, each of the plurality of elastically deformable members may include one of the plurality of second radial support elements.

[0237] refer to Figure 46 At least one third longitudinal support element 944 of the support system 940 can advantageously extend longitudinally from the hydrostatic annular seal 950. The at least one third longitudinal support element 944 can longitudinally abut against the radial portion 932 of the longitudinally facing annular cover 931. This feature ensures contact between the cover and the hydrostatic annular seal in the event of relative longitudinal movement between the cover and the stator, particularly in the event of rotor shaft breakage. Therefore, the at least one third longitudinal support element can advantageously assist in braking the rotor in overspeed conditions.

[0238] The at least one third longitudinal support element 944 may preferably have an annular shape.

[0239] In the foregoing description, the support elements have been presented individually in a non-limiting manner, and the assembly can include a combination of the at least one first radial support element, the at least one second radial support element, and the at least one third longitudinal support element.

Claims

1. A seal (600) for an aircraft turbine engine, comprising a plurality of sealing segments circumferentially distributed around a longitudinal axis (X), each sealing segment comprising a radially outer annular wall segment and a radially inner annular wall segment (610), which are interconnected by an elastically deformable member (203), characterized in that, The radially outer annular wall segments form an integral outer cover, and the radially inner annular wall segments are arranged circumferentially end to end, wherein each radially inner annular wall segment (610) includes a first circumferential edge (612) and an opposite second circumferential edge, each having a slit (614), wherein a tongue (616) is partially installed in the slit (614) of the first circumferential edge (612) of the radially inner annular wall segment (610), and is partially installed in the circumferentially opposite slit (614) of the second circumferential edge of the circumferentially adjacent radially inner annular wall segment (610).

2. The seal according to claim 1, characterized in that, Each slit (614) has a radial dimension between 0.5 and 1.2 mm, preferably about 0.8 mm.

3. The seal according to any one of the preceding claims, characterized in that, Each tongue has a longitudinal dimension smaller than its circumferential dimension, and a radial dimension smaller than its longitudinal dimension.

4. The seal according to any one of the preceding claims, characterized in that, The tongue is positioned between the upstream end of the radially inner annular wall section and the longitudinal midline.

5. The seal according to any one of the preceding claims, characterized in that, The tongue has a roughly rectangular shape.

6. An assembly comprising a cylindrical rotor shroud intended to rotate about a longitudinal axis and a guide having a stator blade ring, the guide having a mounting foot (403) at a radially inner end thereof, a seal according to any one of the preceding claims being mounted on the mounting foot (403) of the guide, and the seal engaging with the cylindrical rotor shroud of a turbine engine in a non-contact sealing manner, the cylindrical rotor shroud being disposed radially below the guide.

7. A turbine for an aircraft turbine engine, the turbine including a casing, an assembly according to the preceding claim, and a rotor, the rotor including a cylindrical shroud that rotates about a longitudinal axis (X), the guide being mounted in the casing, and the cylindrical shroud being arranged radially below the guide.

8. A turbine engine, such as an aircraft turbojet engine or a turboprop engine, comprising the components of claim 6 or the turbine of claim 7.

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