Gas turbine interstage sealing structure, blade wheel disc assembly and gas turbine

Abstract

The invention discloses a gas turbine interstage sealing structure, a blade wheel disc assembly and a gas turbine, the gas turbine interstage sealing structure comprises a wheel disc, a stationary blade sealing ring, a stationary ring, a movable ring and an elastic piece, and the stationary blade sealing ring is arranged on the peripheral side of the wheel disc in a sleeving mode; the static ring is arranged on the static blade sealing ring and is continuously arranged by one circle or discontinuously arranged in the circumferential direction of the static blade sealing ring, the movable ring is arranged on the wheel disc and is continuously arranged by one circle or discontinuously arranged in the circumferential direction of the wheel disc, and the movable ring can move relative to the wheel disc in the axial direction of the wheel disc; the static ring and the moving ring are oppositely arranged in the axial direction, and are separated when being used, so that a gas film is formed between the static ring and the moving ring; the elastic piece is arranged between the movable ring and the wheel disc and used for elastically pushing the movable ring to the static ring. According to the interstage sealing structure of the gas turbine, sealing between the stationary blade sealing ring and the wheel disc can be achieved in a non-contact mode, the sealing effect is good, and the conditions of abrasion and heating caused by contact of labyrinth sealing, labyrinth sealing and honeycomb sealing and brush type sealing are avoided.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and in particular to a gas turbine interstage sealing structure, a blade wheel assembly and a gas turbine. Background Art

[0002] In the prior art, the interstage seals of gas turbines are mostly in the form of comb tooth seals, honeycomb seals combined with comb tooth seals, brush seals, etc., wherein a gap needs to be left between the sealing teeth of the comb tooth seal and the surface of the wheel disc or between the honeycomb seal and the comb tooth seal during installation. These two forms have a large leakage in actual use, and when the wheel disc moves radially, the sealing teeth or the honeycomb core are easily worn, which will lead to a further increase in leakage.

[0003] Although brush seals can avoid the problem of large leakage, the processing cost of existing brush seals is expensive. In addition, during use, the brush wire end of the brush seal and the rotor such as the wheel will cause wear and heat due to contact, which limits the service life of the existing brush seal and is not conducive to the long-term stable operation of the gas turbine. Summary of the invention

[0004] The present invention aims to solve one of the technical problems in the related art at least to a certain extent.

[0005] To this end, an embodiment of the present invention proposes a gas turbine interstage sealing structure, which can achieve sealing between the stationary blade sealing ring and the impeller in a non-contact manner, has a good overall sealing effect, and avoids the wear and heat caused by contact of the comb tooth seal, comb tooth seal + honeycomb seal, and brush seal in the prior art. The overall service life is high, which fully meets the long-term stable operation requirements of the gas turbine.

[0006] The embodiment of the present invention further provides a blade disk assembly including the above-mentioned combustion engine interstage sealing structure.

[0007] An embodiment of the present invention further provides a gas turbine including the blade wheel assembly described above.

[0008] The combustion engine interstage sealing structure of the embodiment of the present invention comprises:

[0009] A wheel disc and a stationary blade sealing ring, wherein the stationary blade sealing ring is sleeved on the outer peripheral side of the wheel disc;

[0010] a stationary ring and a dynamic ring, wherein the stationary ring is arranged on the stationary blade sealing ring and is arranged continuously or discontinuously along the circumference of the stationary blade sealing ring, and the dynamic ring is arranged on the wheel disc and is arranged continuously or discontinuously along the circumference of the wheel disc, and the dynamic ring is movable relative to the wheel disc along the axial direction of the wheel disc;

[0011] The stationary ring and the dynamic ring are arranged opposite to each other in the axial direction, and the stationary ring and the dynamic ring are separated when in use to form an annular gap filled with a gas film between the stationary ring and the dynamic ring;

[0012] An elastic member is disposed between the moving ring and the wheel disc, and is used to elastically push the moving ring toward the stationary ring to ensure the stability of the gas film.

[0013] In some embodiments, the stationary ring is provided with a first annular surface, the dynamic ring is provided with a second annular surface, the first annular surface and the second annular surface are arranged opposite to each other in the axial direction of the wheel disc, and the annular gap is formed between the first annular surface and the second annular surface.

[0014] In some embodiments, the stationary ring is provided with a first outer bevel and a first inner bevel, the first outer bevel and the first inner bevel are both provided with a circle along the circumference of the stationary ring, the radial distance between the first outer bevel and the first inner bevel gradually decreases along the direction approaching the dynamic ring, and the first annular surface is connected between the first outer bevel and the first inner bevel;

[0015] And / or, the moving ring is provided with a second outer bevel and a second inner bevel, the second outer bevel and the second inner bevel are both provided with a circle along the circumference of the moving ring, the spacing between the second outer bevel and the second inner bevel in the radial direction of the moving ring gradually decreases along the direction approaching the stationary ring, and the second annular surface is connected between the second outer bevel and the second inner bevel;

[0016] And / or, at least one of the first annular surface and the second annular surface is provided with a plurality of recesses, and the plurality of recesses are arranged at intervals along the circumference of the wheel disc;

[0017] And / or, the stationary blade sealing ring includes a plurality of sealing ring segments arranged sequentially along the circumferential direction, the stationary ring includes a plurality of stationary ring segments, the dynamic ring includes a plurality of dynamic ring segments, the plurality of stationary ring segments are respectively arranged on the plurality of sealing ring segments, and the number of the sealing ring segments is the same as the number of the stationary ring segments, and the number of the stationary ring segments is the same as the number of the dynamic ring segments.

[0018] In some embodiments, the stationary blade sealing ring is provided with a first annular groove, the first annular groove is arranged in a circle along the circumference of the stationary blade sealing ring, and the stationary ring is assembled in the first annular groove.

[0019] In some embodiments, at least one of the inner groove wall and the outer groove wall of the first annular groove is provided with an annular first sealing groove, and a first sealing member is installed in the first sealing groove. The first sealing member is used to seal against the outer wall or the inner wall of the stationary ring to achieve sealing between the stationary blade sealing ring and the stationary ring.

[0020] In some embodiments, a mounting seat is included, the wheel disc is provided with a second annular groove, the second annular groove is arranged in a circle along the circumference of the wheel disc, the mounting seat is annular and assembled in the second annular groove, and the moving ring is assembled on the mounting seat.

[0021] In some embodiments, at least one of the inner circumferential wall and the outer circumferential wall of the mounting seat is provided with an annular second sealing groove, a second sealing member is installed in the second sealing groove, and the second sealing member is used to seal between the mounting seat and the wheel disc to achieve sealing between the wheel disc and the mounting seat.

[0022] In some embodiments, the wheel disc is provided with a plurality of assembly grooves, the plurality of assembly grooves are arranged at intervals along the circumference of the wheel disc and are all connected to the second annular groove, there are a plurality of elastic members, the plurality of elastic members are respectively assembled in the plurality of assembly grooves and are all stopped against the mounting seat;

[0023] Alternatively, the wheel disc is provided with a mounting groove, the mounting groove is arranged along the circumference of the wheel disc, the mounting groove is communicated with the second annular groove, and the elastic member is assembled in the mounting groove and abuts against the mounting seat.

[0024] The blade disk assembly of the embodiment of the present invention comprises the inter-stage sealing structure of the combustion engine as described in any of the above embodiments, wherein there are two disks, a disk cavity is defined between the two disks, and the stationary blade sealing ring is assembled in the disk cavity;

[0025] The stationary blade sealing ring and at least one of the two wheel discs are sealed by arranging the stationary ring, the dynamic ring and the elastic member;

[0026] Alternatively, the stationary blade sealing ring and one of the two wheel discs are sealed by providing the stationary ring, the dynamic ring, and the elastic member, and the stationary blade sealing ring and the other of the two wheel discs are sealed by an inter-finger sealing structure.

[0027] The gas turbine according to the embodiment of the present invention comprises a blade disk assembly as described in any one of the above embodiments.

[0028] Beneficial effects: The interstage sealing structure, blade disc assembly and gas turbine of the embodiments of the present invention can achieve sealing between the stationary blade sealing ring and the disc in a non-contact manner, with good overall sealing effect, and also avoids the wear and heat caused by contact of the comb seal, comb seal + honeycomb seal, and brush seal in the prior art. The overall service life is high, which fully meets the long-term stable operation requirements of the gas turbine. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 It is a structural schematic diagram of a gas turbine interstage sealing structure according to an embodiment of the present invention.

[0030] Figure 2 It is a schematic structural diagram of a blade disk assembly according to an embodiment of the present invention.

[0031] Figure 3 It is a schematic structural diagram of a blade disk assembly according to another embodiment of the present invention.

[0032] Reference numerals:

[0033] 100- Gas turbine interstage sealing structure;

[0034] 1-wheel disc; 11-second ring groove; 12-assembly groove;

[0035] 2-Stator blade sealing ring; 21-First ring groove; 22-First sealing groove;

[0036] 3-static ring; 31-first ring surface; 32-first outer inclined surface; 33-first inner inclined surface;

[0037] 4-moving ring; 41-second annular surface; 42-second outer inclined surface; 43-second inner inclined surface;

[0038] 5- annular gap;

[0039] 6- elastic member;

[0040] 7- first sealing member;

[0041] 8-mounting seat; 81-second sealing groove;

[0042] 9- second sealing member;

[0043] 200-Fingertip seal structure. DETAILED DESCRIPTION

[0044] Embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and intended to be used to explain the present invention, but should not be understood as limiting the present invention.

[0045] like Figure 1 As shown, the gas turbine interstage sealing structure 100 according to the embodiment of the present invention includes a wheel disc 1 , a stationary blade sealing ring 2 , a stationary ring 3 , a dynamic ring 4 and an elastic member 6 .

[0046] The stationary blade sealing ring 2 is sleeved on the outer peripheral side of the wheel disc 1. For example, the stationary blade sealing ring 2 can be a circular ring structure as a whole, and the wheel disc 1 can be the wheel disc 1 of the moving blade. The stationary blade sealing ring 2 can be sleeved on the outer peripheral side of a part of the wheel disc 1. When in use, the wheel disc 1 can be regarded as a rotor and can rotate relative to the stationary blade sealing ring 2 sleeve.

[0047] The stationary ring 3 is arranged on the stationary blade sealing ring 2 and is arranged one circle along the circumference of the stationary blade sealing ring 2. The dynamic ring 4 is arranged on the wheel disc 1 and is arranged one circle along the circumference of the wheel disc 1. The dynamic ring 4 is movable relative to the wheel disc 1 along the axial direction of the wheel disc 1.

[0048] For example, the stationary ring 3 may be in a circular ring shape as a whole. Figure 1 As shown, the stationary ring 3 can be sleeved on the outer peripheral side of the wheel disc 1 and installed on the right side of the stationary blade sealing ring 2. The dynamic ring 4 can also be annular as a whole, such as Figure 1 As shown, the moving ring 4 can be sleeved on the outer peripheral side of a portion of the wheel disc 1, and the moving ring 4 can be installed on the left side of the wheel disc 1.

[0049] The stationary ring 3 and the dynamic ring 4 are arranged relative to each other in the axial direction, and the axial direction of the wheel disc 1 can be Figure 1 In the left and right directions, after the static ring 3 and the dynamic ring 4 are installed, the static ring 3 and the dynamic ring 4 can be arranged opposite to each other in the left and right directions. The dynamic ring 4 can reciprocate in the left and right directions relative to the wheel disc 1, and the movement of the dynamic ring 4 can realize the change and adjustment of the distance between the static ring 3 and the dynamic ring 4.

[0050] In some other embodiments, the above-mentioned stationary ring 3 and dynamic ring 4 may also be arranged discontinuously, for example, the stationary ring 3 may include multiple stationary ring segments, and the multiple stationary rings may be arranged at equal intervals along the circumference of the stationary blade sealing ring 2, and the dynamic ring 4 may include multiple dynamic ring segments, and the multiple dynamic ring segments may be arranged at intervals along the circumference of the stationary blade sealing ring 2. In this way, the arrangement forms of the stationary ring 3 and the dynamic ring 4 can be enriched, and the flexibility of the arrangement can also be improved.

[0051] The stationary ring 3 and the dynamic ring 4 are separated during use to form an annular gap 5 filled with a gas film between the stationary ring 3 and the dynamic ring 4. Specifically, as Figure 1 As shown, in actual use, along the radial direction of the wheel disc 1, the inner side of the stationary ring 3 and the dynamic ring 4 ( Figure 1 The lower side of the static ring 3 and the dynamic ring 4 can be a high-pressure area with a higher pressure. Figure 1 The upper side of the image may be a low-pressure area with lower air pressure.

[0052] Due to the pressure difference between the high-pressure area and the low-pressure area, and the laminar flow formed when the wheel disc 1 rotates relative to the stationary blade sealing ring 2, the dynamic ring 4 will move to the right under the action of the air pressure. At this time, the dynamic ring 4 and the stationary ring 3 will separate and form a circular annular gap 5 between the dynamic ring 4 and the stationary ring 3. The gas will fill the annular gap 5 and form a gas film, and a better sealing effect can be achieved through the formed gas film.

[0053] The elastic member 6 is disposed between the moving ring 4 and the wheel disc 1, and is used to elastically push the moving ring 4 toward the stationary ring 3 to ensure the stability of the gas film. Figure 1As shown, the elastic member 6 can be a spring or the like, and the elastic member 6 can be installed on the wheel disc 1 and clamped between the movable ring 4 and the wheel disc 1. Specifically, the elastic member 6 can generally extend along the left and right directions, and the left end of the elastic member 6 can stop against the movable ring 4, and the right end of the elastic member 6 can stop against the wheel disc 1.

[0054] During use, due to the air pressure difference between the static ring 3 and the dynamic ring 4, the thickness of the gas film between the static ring 3 and the dynamic ring 4 will also change. The setting of the elastic member 6 can enable the dynamic ring 4 to have the function of following the changes of the gas film. That is, when the sealing effect of the gas film is reduced, the elastic member 6 will elastically push the ring 4 to the left, thereby reducing the distance between the static ring 3 and the dynamic ring 4. When the sealing effect of the gas film is enhanced, the dynamic ring 4 will compress the elastic member 6 under the action of the gas film, thereby ensuring the stability of the gas film during use.

[0055] The gas turbine interstage sealing structure 100 of the embodiment of the present invention can achieve sealing between the stationary blade sealing ring 2 and the impeller 1 in a non-contact manner, that is, the stationary ring 3 and the dynamic ring 4 will be separated when in use, and sealing is achieved between the two through a gas film. The overall sealing effect is good, and the wear and heat generated by the brush seal due to contact in the prior art are avoided. The overall service life is high, which fully meets the long-term stable operation requirements of the gas turbine.

[0056] Secondly, the inter-stage sealing structure of the gas turbine in the embodiment of the present invention is in the form of an axial seal, that is, the dynamic ring and the static ring are arranged relative to each other in the axial direction of the wheel disc to form a seal. Compared with the radial sealing form in the prior art, it can effectively avoid the change of the sealing gap caused by the radial runout of the gas turbine rotor, and further avoid the problem of wear on the sealing surface due to the change of the gap. This more stable sealing gap can also better control the leakage of the seal.

[0057] In addition, due to factors such as thermal expansion, the engine will produce axial movement during operation. However, since elastic parts are installed on one side of the mechanical seal and there is pressure from the air film on the sealing surface, the dynamic ring can adaptively adjust the sealing gap, thereby having a good control effect on the leakage.

[0058] In some embodiments, the stationary ring 3 is provided with a first annular surface, the dynamic ring 4 is provided with a second annular surface, the first annular surface and the second annular surface are arranged opposite to each other in the axial direction of the wheel disc 1, and an annular gap 5 is formed between the first annular surface and the second annular surface.

[0059] For example, Figure 1As shown, the first annular surface can be a plane and can be annular, and the first annular surface can be arranged on the right side of the stationary ring 3, and the second annular surface can be a plane and can be annular, and the second annular surface can be arranged on the left side of the dynamic ring 4. The axial direction of the wheel disc 1 can be left and right, the radial dimensions of the first annular surface and the second annular surface can be substantially the same, and the first annular surface and the second annular surface can be arranged opposite to each other in the left and right direction as a whole.

[0060] When in use, the annular gap 5 is mainly distributed between the first annular surface and the second annular surface. Due to the consistency of the spacing between different positions of the first annular surface and the second annular surface in the left-right direction, the effective sealing of different positions of the annular gap 5 is fully guaranteed.

[0061] In some embodiments, the stationary ring 3 is provided with a first outer bevel 32 and a first inner bevel 33. The first outer bevel 32 and the first inner bevel 33 are both arranged in a circle along the circumference of the stationary ring 3. The radial spacing between the first outer bevel 32 and the first inner bevel 33 in the stationary ring 3 gradually decreases in the direction approaching the dynamic ring 4. The first annular surface is connected between the first outer bevel 32 and the first inner bevel 33.

[0062] For example, Figure 1 As shown, the first outer bevel 32 and the first inner bevel 33 can both be substantially conical circumferential surfaces and extend along the circumference of the stationary ring 3 to form a circle. The first outer bevel 32 can be arranged to be inclined toward the outer side of the stationary ring 3 from right to left, and the first inner bevel 33 can be arranged to be inclined toward the inner side of the stationary ring 3 from right to left. That is, the spacing between the first outer bevel 32 and the first inner bevel 33 in the vertical direction can gradually decrease from left to right. The above-mentioned first annular surface can be connected between the first outer bevel 32 and the first inner bevel 33.

[0063] The arrangement of the first outer inclined surface 32 and the first inner inclined surface 33 can limit a gap between the dynamic ring 4 and the static ring 3 , thereby facilitating the gas to enter between the dynamic ring 4 and the static ring 3 and form a gas film.

[0064] In some embodiments, the moving ring 4 is provided with a second outer bevel 42 and a second inner bevel 43. The second outer bevel 42 and the second inner bevel 43 are both arranged in a circle along the circumference of the moving ring 4. The radial spacing between the second outer bevel 42 and the second inner bevel 43 in the moving ring 4 gradually decreases in the direction approaching the stationary ring 3. The second annular surface is connected between the second outer bevel 42 and the second inner bevel 43.

[0065] For example, Figure 1As shown, both the second outer inclined surface 42 and the second inner inclined surface 43 can generally be conical circumferential surfaces and both extend circumferentially along the moving ring 4 to form a closed circle. Among them, the second outer inclined surface 42 can be inclined outward along the moving ring 4 in the left-to-right direction, and the second inner inclined surface 43 can be inclined inward along the moving ring 4 in the left-to-right direction. That is, the distance between the second outer inclined surface 42 and the second inner inclined surface 43 in the up-and-down direction can gradually decrease along the right-to-left direction. The above-mentioned second annular surface can be connected between the second outer inclined surface 42 and the second inner inclined surface 43.

[0066] It should be noted that the above-mentioned first outer inclined surface 32 and second outer inclined surface 42 can form a V-shaped notch with a V-shaped cross-section on the outer peripheral side of the annular gap 5, and the above-mentioned first inner inclined surface 33 and second inner inclined surface 43 can form a V-shaped notch with a V-shaped cross-section on the inner peripheral side of the annular gap 5. Thus, it is further convenient for gas to enter between the stationary ring 3 and the moving ring 4 and form a gas film.

[0067] In some embodiments, at least one of the first annular surface and the second annular surface is provided with a plurality of concave portions, and the plurality of concave portions are arranged at intervals along the circumferential direction of the wheel disc 1.

[0068] For example, the concave portion can be a spiral groove or the like, and the spiral groove can extend spirally along the circumferential direction of the wheel disc 1. Both the first annular surface and the second annular surface can be provided with a plurality of concave portions, wherein the plurality of concave portions on the first annular surface can be arranged at equal intervals along the circumferential direction of the first annular surface, and the plurality of concave portions on the second annular surface can be arranged at equal intervals along the circumferential direction of the second annular surface.

[0069] When the moving ring 4 rotates relative to the stationary ring 3, the setting of the concave portion can enhance the turbulence effect and can promote the formation of the gas film, thereby enhancing the overall airtightness.

[0070] In some embodiments, the stator blade seal ring 2 includes a plurality of seal ring segments arranged sequentially along the circumferential direction of the stator blade seal ring 2, the stationary ring 3 includes a plurality of stationary ring segments, the moving ring 4 includes a plurality of moving ring segments, and the number of seal ring segments is the same as the number of stationary ring segments, and the number of stationary ring segments is the same as the number of moving ring segments.

[0071] The plurality of stationary ring segments are respectively arranged in the plurality of seal ring segments, that is, the plurality of stationary ring segments can be arranged in the plurality of seal ring segments in a one-to-one correspondence, and the plurality of stationary ring segments and the plurality of moving ring segments are both arranged at equal intervals along the circumferential direction of the stator blade seal ring. Thus, the arrangement forms of the stationary ring 3 and the moving ring 4 are generally consistent with the seal ring segments of the stator blade seal ring 2, improving the adaptability to the stator blade seal ring 2. In some embodiments, the stator blade seal ring 2 is provided with a first ring groove 21, and the first ring groove 21 is provided in a circle along the circumferential direction of the stator blade seal ring 2, and the stationary ring 3 is assembled in the first ring groove 21.

[0072] For example, as Figure 1As shown, the first annular groove 21 can be provided on the right end surface of the stationary blade sealing ring 2, and the first annular groove 21 can be annular and can be arranged in a circle along the circumferential direction of the stationary blade sealing ring 2. The stationary ring 3 can be inserted into the first annular groove 21, and the stationary ring 3 can be fixed in the first annular groove 21 by interference fit, welding, etc., so as to facilitate the installation and arrangement of the stationary ring 3.

[0073] In some embodiments, at least one of the inner groove wall and the outer groove wall of the first annular groove 21 is provided with an annular first sealing groove 22, and a first seal 7 is installed in the first sealing groove 22. The first seal 7 is used to seal against the outer wall or the inner wall of the stationary ring 3 to achieve sealing between the stationary blade sealing ring 2 and the stationary ring 3.

[0074] For example, Figure 1 As shown, the first sealing groove 22 can be provided on the outer peripheral groove wall of the first annular groove 21. The first sealing groove 22 can be a rectangular groove and is arranged in a circle along the circumference of the stationary blade sealing ring 2. The first sealing member 7 can be a sealing ring or the like.

[0075] In order to facilitate the insertion of the stationary ring 3 into the first annular groove 21, the size of the first annular groove 21 is slightly larger than the size of the stationary ring 3. This means that after the stationary ring 3 is assembled into the first annular groove 21, there will be a large gap between the stationary ring 3 and the first annular groove 21, which will cause the gas to deflect and affect the overall airtightness.

[0076] By providing the first sealing groove 22 and the first sealing member 7, on the one hand, the gap between the stationary ring 3 and the first annular groove 21 can be sealed, thereby ensuring the overall air tightness. On the other hand, the squeezing and friction effects of the first sealing member 7 can also fix the stationary ring 3 in the first annular groove 21, thereby ensuring the structural stability of the assembly of the stationary ring 3.

[0077] In some embodiments, the interstage sealing structure 100 of the combustion engine includes a mounting seat 8, the wheel disc 1 is provided with a second annular groove 11, the second annular groove 11 is arranged in a circle along the circumference of the wheel disc 1, the mounting seat 8 is annular and is assembled in the second annular groove 11, and the dynamic ring 4 is assembled on the mounting seat 8.

[0078] For example, Figure 1 As shown, the mounting seat 8 can be generally an annular structure, and a second annular groove 11 can be provided on the left side of the wheel disc 1. The second annular groove 11 can also be annular and extend along the circumference of the wheel disc 1 to form a circle. The mounting seat 8 can be assembled in the second annular groove 11 as a whole, and an annular groove can also be provided on the left side of the mounting seat 8, and the dynamic ring 4 can be embedded in the annular groove. When in use, the mounting seat 8 can move relative to the wheel disc 1, thereby satisfying the use needs of driving the dynamic ring 4 to move in the left and right directions.

[0079] The arrangement of the mounting seat 8 can avoid the situation of processing the moving ring 4. That is, the mounting seat 8 only needs to be adapted to the wheel disc 1, so that the moving ring 4 can select the corresponding size specification according to the size of the static ring 3, avoiding the situation where it is difficult to process and design due to having to take into account both the size of the static ring 3 and the size of the wheel disc 1.

[0080] Secondly, since the mounting seat 8 is arranged independently of the moving ring 4, the whole mounting seat 8 can also be made of a material with self-lubricating characteristics. That is, the material selection of the mounting seat 8 is not restricted by the material selection of the moving ring 4, so that the friction between the mounting seat 8 and the wheel disc 1 can be reduced, facilitating the reciprocating movement of the moving ring 4 in the left and right directions.

[0081] In some embodiments, the above-mentioned second outer inclined surface 42 and second inner inclined surface 43 can also be provided on the mounting seat 8. Thereby, the processing of the moving ring 4 can be further simplified.

[0082] In some embodiments, at least one of the inner peripheral wall and the outer peripheral wall of the mounting seat 8 is provided with an annular second sealing groove 81, and a second sealing member 9 is assembled in the second sealing groove 81. The second sealing member 9 is used for sealing and abutting between the mounting seat 8 and the wheel disc 1 to achieve the sealing between the wheel disc 1 and the mounting seat 8.

[0083] For example, as Figure 1 shown, the second sealing groove 81 can be only provided on the inner peripheral wall of the mounting seat 8, and the second sealing member 9 can also be an O-ring. In order to facilitate the insertion and assembly of the mounting seat 8, the size specification of the second ring groove 11 is also slightly larger than the size of the mounting seat 8. Thus, after the mounting seat 8 is assembled into the second ring groove 11, there will also be a problem of clearance between the mounting seat 8 and the groove wall of the second ring groove 11. By providing the second sealing groove 81 and the second sealing member 9, the clearance can be sealed.

[0084] Secondly, since the second sealing groove 81 is provided on the mounting seat 8, during use, the second sealing member 9 will move left and right along with the mounting seat 8, thus meeting the use requirement of driving the mounting seat 8 to move in the left and right directions.

[0085] In some embodiments, the wheel disc 1 is provided with a plurality of assembly grooves 12. The plurality of assembly grooves 12 are arranged at intervals along the circumferential direction of the wheel disc 1 and are all communicated with the second ring groove 11. There are a plurality of elastic members 6, and the plurality of elastic members 6 are respectively assembled in the plurality of assembly grooves 12 and are all abutted against the mounting seat 8.

[0086] For example, as Figure 1As shown, the assembly groove 12 can be a circular groove, and the assembly groove 12 can extend in the left-right direction, and the left end of the assembly groove 12 can be connected to the second annular groove 11. There can be multiple assembly grooves 12, and the multiple assembly grooves 12 can be arranged at equal intervals along the circumference of the wheel disc 1. The elastic members 6 can all be springs and there can be multiple elastic members 6, and the multiple elastic members 6 can be assembled in the multiple assembly grooves 12 one by one. Therefore, in the circumferential direction of the wheel disc 1, different positions of the mounting seat 8 can have the corresponding pushing effect of the elastic member 6, thereby satisfying the translation effect of the mounting seat 8 in the left-right direction, and also improving the overall elastic force applied to the mounting seat 8.

[0087] In some embodiments, the wheel disc 1 is provided with a mounting groove, which is arranged along the circumference of the wheel disc 1 . The mounting groove is connected to the second annular groove 11 . The elastic member 6 is assembled in the mounting groove and abuts against the mounting seat 8 .

[0088] For example, the mounting groove as a whole may be annular and extend in a circle along the circumference of the wheel disc 1, and the groove width of the mounting groove in the radial direction of the wheel disc 1 may be smaller than the groove width of the second annular groove 11. The radial dimension of the elastic member 6 may be adapted to the radial dimension of the mounting groove. In this case, only one elastic member 6 may be provided and assembled in the mounting groove, and the left end of the elastic member 6 may elastically stop against the mounting seat 8.

[0089] The following describes a blade disk assembly according to an embodiment of the present invention.

[0090] The blade disk assembly of the embodiment of the present invention includes a gas turbine interstage sealing structure, and the gas turbine interstage sealing structure may be the gas turbine interstage sealing structure 100 described in any of the above embodiments.

[0091] like Figure 2 As shown, there are two wheel discs 1, and the two wheel discs 1 can be a front wheel disc and a rear wheel disc respectively, wherein the front wheel disc can be located on the left side of the rear wheel disc. A disc cavity is defined between the two wheel discs 1, and a stationary blade sealing ring 2 is assembled in the disc cavity. Stationary blades can be installed on the outer peripheral side of the stationary blade sealing ring 2, and moving blades can be installed on the outer peripheral side of each wheel disc 1.

[0092] The stationary blade sealing ring 2 and at least one of the two wheel discs 1 are sealed by arranging a stationary ring 3, a dynamic ring 4, and an elastic member 6. Figure 2 As shown, the stationary blade sealing ring 2 and the front wheel disc can be sealed by the above-mentioned gas interstage sealing structure, and the stationary blade sealing ring 2 and the rear wheel disc can also be sealed by the above-mentioned gas interstage sealing structure.

[0093] In some embodiments, the stationary blade sealing ring 2 and one of the two wheel discs 1 are sealed by providing a stationary ring 3, a dynamic ring 4, and an elastic member 6, and the stationary blade sealing ring 2 and the other of the two wheel discs 1 are sealed by an inter-finger sealing structure.

[0094] For example, Figure 3 As shown, the stationary blade sealing ring 2 and the rear wheel disc can be sealed by the engine interstage sealing structure 100, and the stationary blade sealing ring 2 and the front wheel disc can be sealed by the inter-finger sealing structure. The inter-finger sealing structure can be an existing sealing structure, for example, a fingertip sealing device with authorized patent number CN111120113B can be used, which will not be repeated here.

[0095] The fingertip seal structure can achieve better sealing in a relatively small space, and has better pressure bearing effect (greater pressure difference on both sides of the seal) and smaller leakage. By matching with the above-mentioned interstage seal structure of the gas turbine, a better sealing effect can be achieved, and the flexibility of the sealing form is also improved.

[0096] Next, a gas turbine according to an embodiment of the present invention will be described.

[0097] The gas turbine of the embodiment of the present invention comprises a blade disk assembly, and the blade disk assembly may be a blade disk assembly as described in any of the above embodiments.

[0098] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0099] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0100] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral one; it can be a mechanical connection, an electrical connection, or communication with each other; it can be a direct connection, or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0101] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, a first feature being "above", "above" or "above" a second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. A first feature being "below", "below" or "below" a second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.

[0102] In the present invention, the terms "one embodiment", "some embodiments", "examples", "specific examples", or "some examples" etc. mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the described specific features, structures, materials or characteristics may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.

[0103] Although the above embodiments have been shown and described, it is to be understood that the above embodiments are exemplary and are not to be construed as limitations on the present invention. Changes, modifications, substitutions and variations of the above embodiments by those of ordinary skill in the art are all within the scope of protection of the present invention.

Claims

1. A gas turbine interstage sealing structure, characterized in that: include: A wheel disc and a stationary blade sealing ring, wherein the stationary blade sealing ring is sleeved on the outer peripheral side of the wheel disc; a stationary ring and a dynamic ring, wherein the stationary ring is arranged on the stationary blade sealing ring and is arranged continuously or discontinuously along the circumference of the stationary blade sealing ring, and the dynamic ring is arranged on the wheel disc and is arranged continuously or discontinuously along the circumference of the wheel disc, and the dynamic ring is movable relative to the wheel disc along the axial direction of the wheel disc; The stationary ring and the dynamic ring are arranged opposite to each other in the axial direction, and the stationary ring and the dynamic ring are separated when in use to form an annular gap filled with a gas film between the stationary ring and the dynamic ring; An elastic member is disposed between the moving ring and the wheel disc, and is used to elastically push the moving ring toward the stationary ring to ensure the stability of the gas film.

2. The interstage sealing structure of a combustion engine according to claim 1, characterized in that: The stationary ring is provided with a first annular surface, and the dynamic ring is provided with a second annular surface. The first annular surface and the second annular surface are arranged opposite to each other in the axial direction of the wheel disc, and the annular gap is formed between the first annular surface and the second annular surface.

3. The interstage sealing structure of a combustion engine according to claim 2, characterized in that: The stationary ring is provided with a first outer bevel and a first inner bevel, the first outer bevel and the first inner bevel are both arranged along the circumference of the stationary ring, the distance between the first outer bevel and the first inner bevel in the radial direction of the stationary ring gradually decreases along the direction approaching the dynamic ring, and the first annular surface is connected between the first outer bevel and the first inner bevel; And / or, the moving ring is provided with a second outer bevel and a second inner bevel, the second outer bevel and the second inner bevel are both provided with a circle along the circumference of the moving ring, the spacing between the second outer bevel and the second inner bevel in the radial direction of the moving ring gradually decreases along the direction approaching the stationary ring, and the second annular surface is connected between the second outer bevel and the second inner bevel; And / or, at least one of the first annular surface and the second annular surface is provided with a plurality of recesses, and the plurality of recesses are arranged at intervals along the circumference of the wheel disc; And / or, the stationary blade sealing ring includes a plurality of sealing ring segments arranged sequentially along the circumferential direction, the stationary ring includes a plurality of stationary ring segments, the dynamic ring includes a plurality of dynamic ring segments, the plurality of stationary ring segments are respectively arranged on the plurality of sealing ring segments, and the number of the sealing ring segments is the same as the number of the stationary ring segments, and the number of the stationary ring segments is the same as the number of the dynamic ring segments.

4. The interstage sealing structure of a combustion engine according to claim 1, characterized in that: The stationary blade sealing ring is provided with a first annular groove, the first annular groove is arranged in a circle along the circumference of the stationary blade sealing ring, and the stationary ring is assembled in the first annular groove.

5. The interstage sealing structure of a combustion engine according to claim 4, characterized in that: At least one of the inner groove wall and the outer groove wall of the first annular groove is provided with an annular first sealing groove, and a first sealing member is installed in the first sealing groove. The first sealing member is used for sealing against the outer wall or the inner wall of the stationary ring to achieve sealing between the stationary blade sealing ring and the stationary ring.

6. The gas turbine interstage sealing structure according to any one of claims 1 to 5, characterized in that: It comprises a mounting seat, the wheel disc is provided with a second annular groove, the second annular groove is arranged in a circle along the circumference of the wheel disc, the mounting seat is annular and assembled in the second annular groove, and the moving ring is assembled on the mounting seat.

7. The interstage sealing structure of a combustion engine according to claim 6, characterized in that: At least one of the inner circumferential wall and the outer circumferential wall of the mounting seat is provided with an annular second sealing groove, in which a second sealing member is installed, and the second sealing member is used for sealing and stopping between the mounting seat and the wheel disc to achieve sealing between the wheel disc and the mounting seat.

8. The interstage sealing structure of a combustion engine according to claim 7, characterized in that: The wheel disc is provided with a plurality of assembly grooves, which are arranged at intervals along the circumference of the wheel disc and are all connected with the second annular groove. There are a plurality of elastic members, which are respectively assembled in the plurality of assembly grooves and abut against the mounting seat. Alternatively, the wheel disc is provided with a mounting groove, the mounting groove is arranged along the circumference of the wheel disc, the mounting groove is communicated with the second annular groove, and the elastic member is assembled in the mounting groove and abuts against the mounting seat.

9. A blade wheel assembly, characterized in that: It comprises a combustion engine interstage sealing structure as described in any one of claims 1 to 8 above, wherein there are two wheel discs, a disc cavity is defined between the two wheel discs, and the stationary blade sealing ring is assembled in the disc cavity; The stationary blade sealing ring and at least one of the two wheel discs are sealed by arranging the stationary ring, the dynamic ring and the elastic member; Alternatively, the stationary blade sealing ring and one of the two wheel discs are sealed by providing the stationary ring, the dynamic ring, and the elastic member, and the stationary blade sealing ring and the other of the two wheel discs are sealed by an inter-finger sealing structure.

10. A gas turbine, characterized in that: Comprising a blade disk assembly as claimed in claim 9 above.

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