CN107939455B - Gas turbine and seal assembly thereof - Google Patents
Gas turbine and seal assembly thereof Download PDFInfo
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- CN107939455B CN107939455B CN201711105678.6A CN201711105678A CN107939455B CN 107939455 B CN107939455 B CN 107939455B CN 201711105678 A CN201711105678 A CN 201711105678A CN 107939455 B CN107939455 B CN 107939455B
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- ring
- sealing ring
- face
- gas turbine
- annular groove
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- 238000007789 sealing Methods 0.000 claims abstract description 85
- 230000002093 peripheral effect Effects 0.000 claims abstract description 41
- 238000001816 cooling Methods 0.000 abstract description 18
- 230000000694 effects Effects 0.000 abstract description 6
- 238000000034 method Methods 0.000 abstract 1
- 230000007423 decrease Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Gasket Seals (AREA)
Abstract
The invention discloses a gas turbine and a sealing assembly thereof, wherein the gas turbine comprises a sealing assembly and at least two stator blade rings, each stator blade ring adjacent to the other stator blade ring comprises a front-stage stator blade ring and a rear-stage stator blade ring, the front side surface of the rear-stage stator blade ring is opposite to the rear side surface of the front-stage stator blade ring, and the front side surface of the rear-stage stator blade ring is provided with an annular groove; the sealing assembly comprises a sealing ring, a wave spring and a leaf spring, wherein the wave spring is arranged between the outer peripheral surface of the sealing ring and the outer peripheral wall surface of the annular groove so as to push the sealing ring to the inner peripheral wall surface of the annular groove, and the leaf spring is arranged between the sealing ring and the bottom surface of the annular groove so as to push the sealing ring to the front-stage stationary blade ring. The gas turbine does not need to process a spring mounting hole, the sealing ring is not easy to deform, the cooling effect is improved, and the assembly is simple.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to a sealing assembly of a turbine of a gas turbine and the gas turbine with the sealing assembly.
Background
When the gas turbine operates, the turbine stationary blade works in high-temperature gas, cooling air needs to be extracted from the compressor to enter a cavity formed by the stationary blade ring and the turbine cylinder so as to cool the turbine stationary blade, the safe and reliable work of the turbine stationary blade is ensured, and the service life of the blade is prolonged. In order to adapt to expansion caused by heating of the stator blade rings, gaps are arranged between adjacent stator blade rings. To avoid leakage of cooling air, a seal assembly is required at the gap between adjacent vane rings.
In the related art, the sealing component between the adjacent stationary blade rings comprises a sealing ring and a cylindrical spiral spring, one end face of the sealing ring is attached to the end face of one stationary blade ring, a spring mounting hole is formed in the other end face of the sealing ring along the axial direction, a spring mounting hole is formed in the outer peripheral face of the sealing ring along the radial direction, the cylindrical spiral spring is arranged in the spring mounting hole, and the extending end of the cylindrical spiral spring on the other end face of the sealing ring is attached to the other stationary blade ring. However, the above-mentioned seal assembly requires a plurality of spring mounting holes to be machined in the axial and radial directions, and is liable to cause deformation of the seal ring, reducing the sealing effect, and being difficult to assemble.
Disclosure of Invention
The present invention aims to solve at least one of the technical problems in the related art to some extent.
To this end, an aspect of the present invention provides a gas turbine which does not require machining of a spring mounting hole, is less likely to deform a seal ring, improves a cooling effect, and is simple to assemble.
In another aspect, the present invention is directed to a seal assembly for a gas turbine.
A gas turbine according to an embodiment of the first aspect of the present invention includes at least two vane rings, the vane rings adjacent to each other including a front stage vane ring and a rear stage vane ring, a front side surface of the rear stage vane ring being opposite to a rear side surface of the front stage vane ring, the front side surface of the rear stage vane ring being provided with an annular groove; the sealing assembly comprises a sealing ring, a wave spring and a leaf spring, wherein the wave spring is arranged between the outer peripheral surface of the sealing ring and the outer peripheral wall surface of the annular groove so as to push the sealing ring to the inner peripheral wall surface of the annular groove, and the leaf spring is arranged between the sealing ring and the bottom surface of the annular groove so as to push the sealing ring to the front-stage stationary blade ring.
According to the gas turbine, the wave spring arranged between the outer peripheral surface of the sealing ring and the outer peripheral wall surface of the annular groove and the plate spring arranged between the end surface of the sealing ring and the bottom surface of the annular groove respectively press the sealing ring to the inner peripheral wall surface of the annular groove and the front-stage stationary blade ring, and a spring mounting hole for mounting the cylindrical spiral spring is not required to be processed on the sealing ring between the stationary blade rings, so that the sealing ring is not easy to deform, cooling air can be effectively sealed, the stationary blade of the gas turbine is fully cooled, the cooling efficiency of a unit is improved, and the assembly difficulty is reduced.
In some embodiments, the gas turbine further comprises a fastener that mounts the seal ring.
In some embodiments, the fastener comprises: the front end of the stud is matched with the threaded hole of the sealing ring, and the rear end of the stud passes through the annular groove backwards and extends out of the rear-stage stationary blade ring; and the nut is matched with the rear end of the stud.
In some embodiments, the leaf springs are a plurality of the leaf springs being evenly spaced circumferentially about the center of the seal ring.
In some embodiments, the leaf spring includes a dome and an annular skirt portion extending radially outward from an outer periphery of the dome.
In some embodiments, the leaf spring includes an arcuate portion and a straight portion extending outwardly from both ends of the arcuate portion.
In some embodiments, the seal ring is formed by a plurality of arc segments connected along the circumference of the seal ring.
In some embodiments, each end face of the arc-shaped segment is stepped and includes a first end face, a second end face and a third end face, the first end face being a first line extending in an axial direction of the seal ring when the outer peripheral face of the seal ring is seen from the outside in a radial direction of the seal ring, the third end face being a third line extending in the axial direction of the seal ring, the second end face being a second line extending in a circumferential direction of the seal ring, both ends of the second line being connected to one end of the first line and one end of the third line, respectively, the first end faces of adjacent arc-shaped segments being opposed to each other and spaced apart by a first expansion gap, the third end faces of adjacent arc-shaped segments being opposed to each other and spaced apart by a third expansion gap, the second end faces of adjacent arc-shaped segments being in contact with each other.
In some embodiments, the wave springs are a plurality of, and the wave springs are in one-to-one correspondence with the arc segments.
According to the sealing assembly of the gas turbine of the embodiment of the second aspect of the invention, a gap between adjacent stator blade rings of the turbine of the gas turbine is sealed, an annular groove with an opening facing a front stage stator blade ring is arranged on a rear stage stator blade ring of the adjacent stator blade rings, the sealing assembly comprises a sealing ring, a wave spring arranged on the outer peripheral surface of the sealing ring and a leaf spring arranged on the rear side surface of the sealing ring, wherein the wave spring pushes the sealing ring to the inner peripheral wall surface of the annular groove when the sealing assembly is arranged in the annular groove, and the leaf spring pushes the sealing ring to the front stage stator blade ring.
According to the sealing component of the gas turbine, the wave spring and the leaf spring enable the sealing ring to be in close contact with the stator blade ring to achieve sealing, a spring mounting hole for mounting the cylindrical spiral spring is not required to be machined, the sealing ring is not easy to deform, cooling air can be effectively sealed, turbine stator blades in the gas turbine are fully cooled, cooling efficiency of a gas turbine unit is improved, and assembly is simple.
In some embodiments, the leaf springs are a plurality of the leaf springs being evenly spaced circumferentially about the center of the seal ring.
In some embodiments, the leaf spring includes a dome and an annular skirt portion extending radially outward from an outer periphery of the dome.
In some embodiments, the leaf spring includes an arcuate portion and a straight portion extending outwardly from both ends of the arcuate portion.
In some embodiments, the seal ring is formed by a plurality of arc segments connected along the circumference of the seal ring.
In some embodiments, each end face of the arc-shaped segment is stepped and includes a first end face, a second end face and a third end face, the first end face being a first line extending in an axial direction of the seal ring when the outer peripheral face of the seal ring is seen from the outside in a radial direction of the seal ring, the third end face being a third line extending in the axial direction of the seal ring, the second end face being a second line extending in a circumferential direction of the seal ring, both ends of the second line being connected to one end of the first line and one end of the third line, respectively, the first end faces of adjacent arc-shaped segments being opposed to each other and spaced apart by a first expansion gap, the third end faces of adjacent arc-shaped segments being opposed to each other and spaced apart by a third expansion gap, the second end faces of adjacent arc-shaped segments being in contact with each other.
In some embodiments, the wave springs are a plurality of, and the wave springs are in one-to-one correspondence with the arc segments.
Drawings
FIG. 1 is a schematic view of an overall structure of a gas turbine according to an embodiment of the present invention;
FIG. 2 is an enlarged view of a partial structure of a gas turbine according to an embodiment of the present invention;
FIG. 3 is a schematic structural view of a rear stage vane ring of a gas turbine according to an embodiment of the invention;
FIG. 4 is a cross-sectional view A-A of FIG. 3 of a gas turbine engine according to an embodiment of the present invention;
FIG. 5 is a B-B cross-sectional view of FIG. 3 of the gas turbine engine in accordance with an embodiment of the present invention;
FIG. 6 is a cross-sectional view C-C of FIG. 4 of a rear stage vane ring and seal assembly of a gas turbine according to an embodiment of the invention;
FIG. 7 is a D-view of FIG. 6 of a gas turbine engine in accordance with an embodiment of the present invention.
Reference numerals:
Vane ring 1, front stage vane ring 11, rear stage vane ring 12, annular groove 13, seal assembly 2, seal ring 21, arcuate segment 210, first end surface 211, second end surface 212, third end surface 213, first expansion gap 214, third expansion gap 215, wave spring 22, leaf spring 23, arcuate portion 231, flat portion 232, turbine cylinder 3, fastener 4, stud 41, nut 42, cooling hole 5, vane 6.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings. The embodiments described below by referring to the drawings are illustrative and intended to explain the present invention and should not be construed as limiting the invention.
As shown in fig. 1-7, a gas turbine according to an embodiment of the present invention includes a vane ring 1 and a seal assembly 2, in other words, the gas turbine includes a turbine having the vane ring 1 and the seal assembly 2.
At least two vane rings 1 are provided, each adjacent vane ring 1 includes a front vane ring 11 and a rear vane ring 12, a front side surface (left side surface in fig. 1 and 2) of the rear vane ring 12 is opposite to a rear side surface (right side surface in fig. 1 and 2) of the front vane ring 11, and an annular groove 13 is provided in the front side surface (left side surface in fig. 1 and 2) of the rear vane ring 12.
In order to cool each stage of vane during operation of the gas turbine, sufficient cooling air is required to enter the chamber formed by vane ring 1 and turbine cylinder 3. Cooling air within the chamber enters each stage of vanes 6 through cooling holes 5 in the vane ring 1 to cool the vanes 6.
As shown in fig. 1 and 2, in the turbine cylinder 3, the gas pressure gradually decreases in the direction of the gas flow indicated by the arrow, so that the vane ring inlet side (left side in fig. 1 and 2) pressure is greater than the vane ring outlet side (right side in fig. 1 and 2), the vane ring outlet side will abut against the cylinder under the operation condition of the gas turbine, each stage of vane ring will expand forward (inlet side) in operation, and for this purpose, an expansion gap for compensating expansion must be provided between adjacent vane rings. However, in order to prevent leakage of cooling air, the expansion gap needs to be sealed to ensure the cooling effect.
As shown in fig. 1, there are 4 vane rings 1, two adjacent vane rings, a front vane ring 11 on the left side and a rear vane ring 12 on the right side, in order from left to right, and it should be understood that the front and rear vane rings are relatively speaking. For example, two adjacent vane rings on the leftmost side are the front stage vane ring 11, the vane ring on the right side of the front stage vane ring 11 is the rear stage vane ring 12 adjacent to the front stage vane ring 11, and the rear stage vane ring 12 becomes the front stage vane ring with respect to the vane ring on the right side thereof. The right side surface of the front-stage stator blade ring 11 is opposite to the left side surface of the rear-stage stator blade ring 12, and an annular groove 13 is formed in the left side surface of the rear-stage stator blade ring 12.
The seal assembly 2 includes a seal ring 21, a wave spring 22 and a plate spring 23, the wave spring 22 being provided between an outer peripheral surface of the seal ring 21 and an outer peripheral wall surface (an upper wall surface in fig. 4) of the annular groove 13 to push the seal ring 21 toward an inner peripheral wall surface (a lower wall surface in fig. 4) of the annular groove 13, in other words, the inner peripheral surface of the seal ring 21 is brought into close contact with the inner peripheral wall surface of the annular groove 13 to achieve sealing. The plate spring 23 is provided between the seal ring 21 and the bottom surface (right side surface in fig. 4) of the annular groove 13 to push the seal ring 21 toward the front stage vane ring 11, in other words, the left end surface of the seal ring 21 is in close contact with the right side surface of the front stage vane ring 11 to achieve sealing.
As shown in fig. 4 and 6, a wave spring 22 may be provided on the outer peripheral wall surface of the seal ring 21 between the outer peripheral surface of the seal ring 21 and the outer peripheral wall surface of the annular groove 13 to push the seal ring 21 toward the inner peripheral wall surface of the annular groove 13. The leaf spring 23 is provided on the right side surface of the seal ring 21 between the seal ring 21 and the bottom surface of the annular groove 13 to push the seal ring 21 toward the front stage vane ring 11. Under the action of the wave spring 22 and the leaf spring 23, the seal ring 21 is respectively in contact and sealed with the rear stage stator blade ring 12 and the front stage stator blade ring 11, so that leakage of cooling air is prevented, and the stator blade 6 in the gas turbine is sufficiently cooled.
It will be appreciated that, as described above, the vane ring may be a vane ring in a turbine, the gas turbine comprising a turbine cylinder 3, the turbine cylinder 3 having the vane ring 1 and seal assembly 2 described above therein. In other words, the seal assembly 2 is used for sealing a gap between adjacent vane rings 1 of a turbine of a gas turbine, an annular groove 13 opening toward a front stage vane ring 11 is provided on a rear stage vane ring 12 of the adjacent vane rings 1, the seal assembly 2 includes a seal ring 21, a wave spring 22 provided on an outer peripheral surface of the seal ring 21, and a leaf spring 23 provided on a rear side surface of the seal ring 21, wherein the wave spring 22 pushes the seal ring 21 toward an inner peripheral wall surface of the annular groove 13 when the seal assembly 2 is provided in the annular groove 13, and the leaf spring 23 pushes the seal ring 21 toward the front stage vane ring 11. According to the gas turbine of the invention, the sealing of the vane ring 1 in the turbine cylinder 3 is achieved by the sealing assembly 2 to sufficiently cool the vanes 6 in the turbine.
According to the gas turbine, the wave spring and the leaf spring enable the sealing ring to be in close contact with the stator blade rings to achieve sealing, spring mounting holes are not required to be machined in the sealing ring between the stator blade rings, the sealing ring is not easy to deform, cooling air can be effectively sealed, stator blades of the gas turbine are fully cooled, cooling efficiency of a gas turbine unit is improved, and assembling difficulty of a sealing assembly is reduced.
In some embodiments, as shown in FIG. 5, the gas turbine also includes a fastener 4 that mounts a seal ring 21. In some alternative embodiments, the fastener 4 includes a stud 41 and a nut 42, the front end (left end in FIG. 5) of the stud 41 fitting within the threaded bore of the seal ring 21, the rear end (right end in FIG. 5) of the stud 41 passing rearwardly (right in FIG. 5) from within the annular groove 13 and protruding out of the rear stage vane ring 12. A nut 42 is fitted at the rear end of the stud 41. The seal ring 21 is fastened to the post-stage stationary blade ring 12 by the cooperation of the stud 41 and the nut 42 to prevent the seal ring 21 from falling off from the annular groove 13, and the elastic force of the leaf spring 23 can be adjusted by adjusting the screw-in depth of the stud 41 to adjust the degree of sealing of the seal ring 21 with the pre-stage stationary blade ring 11. Preferably, after the vane ring 1 is mounted in place and the seal ring 21 is in place, the fastener 4 may be removed, in other words, the fastener 4 is used to assemble the seal ring 21, e.g. by pulling the seal ring 21 to the right into the annular groove 13 via the stud 41 and the nut 42, to facilitate the mounting of the vane ring 1, then releasing the nut 42 and the stud 41, the seal ring 21 being abutted to the front stage vane ring 11 via the leaf spring 23, and finally the stud 41 may be removed.
In some embodiments, the plate springs 23 are plural, and the plurality of plate springs 23 are arranged at regular intervals in the circumferential direction around the center of the seal ring 21. The plurality of leaf springs 23 distributed uniformly can further improve the sealing effect between the seal ring 21 and the front stage vane ring 11, and sufficiently cool the vanes.
In some embodiments, as shown in fig. 4 and 5, leaf spring 23 includes a dome and an annular skirt portion that extends radially outward from an outer periphery of the dome. In the example shown in fig. 5, the dome portion of the leaf spring 23 is in the shape of a partial sphere bulging rightward, and the outer periphery of the dome portion has an annular skirt portion extending outward in the radial direction of the partial sphere. In other alternative embodiments, the plate spring 23 is plate-shaped and includes an arc-shaped portion 231 and a flat portion 232, the flat portion 232 extending outwardly from both ends of the arc-shaped portion 231, and in fig. 5, the flat portion 232 extending upwardly from an upper end of the arc-shaped portion 231 and downwardly from a lower end of the arc-shaped portion 231. When the seal assembly 2 is disposed within the annular groove 13, the arcuate portion 231 abuts against the bottom surface of the annular groove 13 to urge the seal ring 21 toward the front stage vane ring 11.
In some embodiments, as shown in FIG. 7, the seal ring 21 is formed from a plurality of arcuate segments 210 that are joined along the circumference of the seal ring 21.
In some embodiments, each end surface of the arcuate segment 210 is stepped and includes a first end surface 211, a second end surface 212, and a third end surface 213, the first end surface 211 being a first line extending in an axial direction (left-right direction in fig. 7) of the seal ring 21, the third end surface 213 being a third line extending in the axial direction of the seal ring 21, the second end surface 212 being a second line extending in a circumferential direction (up-down direction in fig. 7) of the seal ring 21 when the outer peripheral surface of the seal ring 21 is viewed from the outside in a radial direction of the seal ring 21, as shown in fig. 4. The two ends of the second wire are respectively connected with one end of the first wire and one end of the third wire, so that the three wires form a general Z shape. The first end surfaces 211 of adjacent arcuate segments 210 are opposite each other and spaced apart by a first expansion gap 214, the third end surfaces 213 of adjacent arcuate segments 210 are opposite each other and spaced apart by a third expansion gap 215, and the second end surfaces 212 of adjacent arcuate segments 210 are in contact with each other.
It will be appreciated that the adjacent arcuate segments 210 may be secured to each other in both the expansion gap, i.e., the first expansion gap 214 and the third expansion gap 215, and the second end face 212 of the adjacent arcuate segments 210 may be tightly sealed against leakage of cooling air by the leaf springs 23. Moreover, since the gas pressure acts on the end faces of the seal ring 21 in the axial direction thereof, the sealability between the second end faces 212 can be further improved by making the contact faces of the adjacent arcuate segments 210 substantially zigzag.
The term "first expansion gap" and "third expansion gap" are defined so as to correspond to the first end face and the third end face, and the first and third end faces are not in sequential relation. In other words, the definition of the "first expansion gap" and the "third expansion gap" does not present the possibility that the second expansion gap is also present.
In some embodiments, the wave springs 22 are a plurality, and the plurality of wave springs 22 are in one-to-one correspondence with the plurality of arcuate segments 210. In other words, each arcuate segment 210 is provided with one wave spring 22, i.e. how many arcuate segments 210 are connected to the seal ring 21 in the circumferential direction of the seal ring 21, and how many wave springs 22 are provided on the seal ring 21.
In addition, the gas pressure at the outer side A1 of the sealing ring 21 and the gas pressure at the right side A2 of the sealing ring 21 are equal to the gas pressure at the chamber A, the gas pressure at the inner side B1 of the sealing ring 21 is equal to the gas pressure at the chamber B, and the gas pressure at the chamber A in the turbine cylinder 3 is larger than the gas pressure at the chamber B, so that a gas pressure difference exists between the outer side A1 and the right side A2 of the sealing ring 21 and the inner side B1, and under the action of the gas pressure difference, one left side surface and the inner peripheral wall surface of the sealing ring 21 are respectively abutted against the front-stage stator blade ring 11 and the rear-stage stator blade ring 12, so that two contact surfaces can be better sealed, the sealing effect is further improved, and the stator blades are fully cooled.
A gas turbine according to an embodiment of the present invention is described below with reference to fig. 1-7.
As shown in fig. 1-7, a gas turbine according to an embodiment of the present invention includes a vane ring 1 disposed within a turbine cylinder 3, a seal assembly 2, and a fastener 4.
The number of the stator blade rings 1 is four, the four stator blade rings 1 are sequentially arranged from left to right, and the stator blade rings 1 adjacent to each other comprise a front stage stator blade ring 11 and a rear stage stator blade ring 12. The left side surface of the rear-stage stator blade ring 12 is opposite to the right side surface of the front-stage stator blade ring 11, and an annular groove 13 is formed in the left side surface of the rear-stage stator blade ring 12.
The seal assembly 2 includes a seal ring 21, a wave spring 22 and a leaf spring 23.
The seal ring 21 is formed by connecting a plurality of arcuate segments 210 in the circumferential direction of the seal ring 21.
The wave springs 22 are a plurality of, and the wave springs 22 are in one-to-one correspondence with the arc segments 210, i.e. one wave spring 22 is arranged on the outer peripheral surface of each arc segment 210. The wave spring 22 is located between the outer peripheral surface of the seal ring 21 and the outer peripheral wall surface of the annular groove 13 to urge the seal ring 21 toward the inner peripheral wall surface of the annular groove 13.
The plate spring 23 is provided on the right side surface of the seal ring 21 and includes an arc-shaped portion 231 and a flat portion 232, both ends of the arc-shaped portion 231 extending outward to form the flat portion 232. The plate springs 23 are plural, and the plural plate springs 23 are arranged at regular intervals in the circumferential direction around the center of the seal ring 21. The leaf spring 23 is located between the right side surface of the seal ring 21 and the bottom surface of the annular groove 13 to push the seal ring 21 toward the front stage vane ring 11.
Each end surface of the arcuate segment 210 of the seal ring 21 is stepped and includes a first end surface 211, a second end surface 212 and a third end surface 213, when the outer peripheral surface of the seal ring 21 is seen from the outside in the radial direction of the seal ring 21, as shown in fig. 7, the first end surface 211 is a first line extending in the axial direction of the seal ring 21, the third end surface 213 is a third line extending in the axial direction of the seal ring 21, the second end surface 212 is a second line extending in the circumferential direction of the seal ring 21, both ends of the second line are connected to one end of the first line and one end of the third line, respectively, the three lines constitute a substantially zigzag shape, that is, the contact surfaces of the adjacent arcuate segments 210 are substantially zigzag shape. The first end surfaces 211 of adjacent arcuate segments 210 are opposite each other and spaced apart by a first expansion gap 214, the third end surfaces 213 of adjacent arcuate segments 210 are opposite each other and spaced apart by a third expansion gap 215, and the second end surfaces 212 of adjacent arcuate segments 210 are in contact with each other under the influence of the leaf springs 23.
The fastener 4 includes a stud 41 and a nut 42, as shown in fig. 5, a left end of the stud 41 is fitted in a threaded hole of the seal ring 21, and a right end of the stud 41 passes through the annular groove 13 to the right and protrudes from the vane ring 12 of the subsequent stage. A nut 42 is fitted at the rear end of the stud 41. The seal ring 21 is fastened to the post-stage stationary blade ring 12 by the cooperation of the stud 41 and the nut 42 to prevent the seal ring 21 from falling off from the annular groove 13, and the elastic force of the leaf spring 23 can be adjusted by adjusting the screw-in depth of the stud 41 to adjust the degree of sealing of the seal ring 21 with the pre-stage stationary blade ring 11. Alternatively, after the vane ring 1 is in place and the seal ring 21 is in place, the stud 41 and nut 42 may be removed.
It will be appreciated that when the seal assembly 2 is assembled on the vane ring 12 of the subsequent stage, the seal ring 21 is placed in the annular groove 13 of the vane ring 12 of the subsequent stage, the outer side face of the wave spring 22 on the outer peripheral face of the seal ring 21 abuts against the inner peripheral wall face of the annular groove 13, and the outer side face of the leaf spring 23 on the end face of the seal ring 21 abuts against the bottom face of the annular groove 13.
In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element being referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In the description of the present invention, the meaning of "plurality" means at least two, for example, two, three, etc., unless specifically defined otherwise.
In the present invention, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; may be mechanically connected, may be electrically connected or may be in communication with each other; either directly or indirectly, through intermediaries, or both, may be in communication with each other or in interaction with each other, unless expressly defined otherwise. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
In the present invention, unless expressly stated or limited otherwise, a first feature "up" or "down" a second feature may be the first and second features in direct contact, or the first and second features in indirect contact via an intervening medium. Moreover, a first feature being "above," "over" and "on" a second feature may be a first feature being directly above or obliquely above the second feature, or simply indicating that the first feature is level higher than the second feature. The first feature being "under", "below" and "beneath" the second feature may be the first feature being directly under or obliquely below the second feature, or simply indicating that the first feature is less level than the second feature.
In the description of the present specification, a description referring to terms "one embodiment," "some embodiments," "examples," "specific examples," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present invention. In this specification, schematic representations of the above terms are not necessarily directed to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, the different embodiments or examples described in this specification and the features of the different embodiments or examples may be combined and combined by those skilled in the art without contradiction.
While embodiments of the present invention have been shown and described above, it will be understood that the above embodiments are illustrative and not to be construed as limiting the invention, and that variations, modifications, alternatives and variations may be made to the above embodiments by one of ordinary skill in the art within the scope of the invention.
Claims (10)
1. A gas turbine, comprising:
The stator blade rings adjacent to each other comprise a front-stage stator blade ring and a rear-stage stator blade ring, the front side surface of the rear-stage stator blade ring is opposite to the rear side surface of the front-stage stator blade ring, and the front side surface of the rear-stage stator blade ring is provided with an annular groove;
The sealing assembly comprises a sealing ring, a wave spring and a leaf spring, wherein the wave spring is arranged between the outer peripheral surface of the sealing ring and the outer peripheral wall surface of the annular groove so as to push the sealing ring to the inner peripheral wall surface of the annular groove, and the leaf spring is arranged between the sealing ring and the bottom surface of the annular groove so as to push the sealing ring to the front-stage stationary blade ring;
The plate springs are arranged at equal intervals along the circumferential direction around the center of the sealing ring;
the sealing ring is formed by connecting a plurality of arc-shaped sections along the circumferential direction of the sealing ring;
each end face of the arc-shaped segment is in a step shape and comprises a first end face, a second end face and a third end face, when the outer peripheral face of the sealing ring is seen from the outside along the radial direction of the sealing ring, the first end face is a first line extending along the axial direction of the sealing ring, the third end face is a third line extending along the axial direction of the sealing ring, the second end face is a second line extending along the circumferential direction of the sealing ring, two ends of the second line are respectively connected with one end of the first line and one end of the third line, the first end faces of adjacent arc-shaped segments are opposite to each other and are separated by a first expansion gap, the third end faces of adjacent arc-shaped segments are opposite to each other and are separated by a third expansion gap, and the second end faces of adjacent arc-shaped segments are in contact with each other.
2. The gas turbine of claim 1, further comprising a fastener to mount the seal ring.
3. The gas turbine of claim 2, wherein the fastener comprises:
the front end of the stud is matched with the threaded hole of the sealing ring, and the rear end of the stud passes through the annular groove backwards and extends out of the rear-stage stationary blade ring;
and the nut is matched with the rear end of the stud.
4. The gas turbine of claim 1, wherein the leaf spring includes a dome and an annular skirt portion extending radially outwardly from an outer periphery of the dome.
5. The gas turbine of claim 1, wherein the leaf spring includes an arcuate portion and a straight portion extending outwardly from both ends of the arcuate portion.
6. The gas turbine of claim 1, wherein said wave spring is a plurality of said wave springs in one-to-one correspondence with a plurality of said arcuate segments.
7. A seal assembly of a gas turbine for sealing a gap between adjacent vane rings of the turbine of the gas turbine, wherein an annular groove with an opening facing a preceding vane ring is arranged on a succeeding vane ring of the adjacent vane rings, characterized in that the seal assembly comprises a seal ring, a wave spring arranged on an outer peripheral surface of the seal ring and a leaf spring arranged on a rear side surface of the seal ring, wherein the wave spring pushes the seal ring to an inner peripheral wall surface of the annular groove and the leaf spring pushes the seal ring to the preceding vane ring when the seal assembly is arranged in the annular groove;
The plate springs are arranged at equal intervals along the circumferential direction around the center of the sealing ring;
the sealing ring is formed by connecting a plurality of arc-shaped sections along the circumferential direction of the sealing ring;
each end face of the arc-shaped segment is in a step shape and comprises a first end face, a second end face and a third end face, when the outer peripheral face of the sealing ring is seen from the outside along the radial direction of the sealing ring, the first end face is a first line extending along the axial direction of the sealing ring, the third end face is a third line extending along the axial direction of the sealing ring, the second end face is a second line extending along the circumferential direction of the sealing ring, two ends of the second line are respectively connected with one end of the first line and one end of the third line, the first end faces of adjacent arc-shaped segments are opposite to each other and are separated by a first expansion gap, the third end faces of adjacent arc-shaped segments are opposite to each other and are separated by a third expansion gap, and the second end faces of adjacent arc-shaped segments are in contact with each other.
8. The gas turbine seal assembly of claim 7, wherein the leaf spring includes a dome and an annular skirt portion extending radially outwardly from an outer periphery of the dome.
9. The gas turbine seal assembly of claim 7, wherein said leaf spring includes an arcuate portion and a flat portion extending outwardly from opposite ends of said arcuate portion.
10. The seal assembly of a gas turbine engine of claim 7, wherein said wave spring is a plurality of said wave springs in one-to-one correspondence with a plurality of said arcuate segments.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711105678.6A CN107939455B (en) | 2017-11-10 | 2017-11-10 | Gas turbine and seal assembly thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711105678.6A CN107939455B (en) | 2017-11-10 | 2017-11-10 | Gas turbine and seal assembly thereof |
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| CN107939455A CN107939455A (en) | 2018-04-20 |
| CN107939455B true CN107939455B (en) | 2024-05-17 |
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Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11021990B2 (en) * | 2018-12-19 | 2021-06-01 | General Electric Company | Shroud sealing for a gas turbine engine |
| KR102291086B1 (en) * | 2020-02-21 | 2021-08-18 | 두산중공업 주식회사 | Sealing assembly and gas turbine comprising the same |
| CN111561358B (en) * | 2020-05-12 | 2022-08-30 | 中国航发湖南动力机械研究所 | Test seal device and method of mounting test member |
| KR102440256B1 (en) * | 2020-08-27 | 2022-09-05 | 두산에너빌리티 주식회사 | Sealing assembly and turbo-machine comprising the same |
| KR102440257B1 (en) * | 2020-08-28 | 2022-09-05 | 두산에너빌리티 주식회사 | Sealing assembly and turbo-machine comprising the same |
| KR102566947B1 (en) * | 2021-09-15 | 2023-08-11 | 두산에너빌리티 주식회사 | Sealing assembly and turbo-machine comprising the same |
| KR102566946B1 (en) * | 2021-09-16 | 2023-08-11 | 두산에너빌리티 주식회사 | Sealing assembly and turbo-machine comprising the same |
| KR102659819B1 (en) * | 2021-09-29 | 2024-04-23 | 두산에너빌리티 주식회사 | Sealing assembly and turbo-machine comprising the same |
| CN114151143B (en) * | 2021-11-11 | 2023-11-10 | 中国联合重型燃气轮机技术有限公司 | Gas turbine and seal assembly thereof |
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| Publication number | Publication date |
|---|---|
| CN107939455A (en) | 2018-04-20 |
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