CN107939455A - Gas turbine and its seal assembly - Google Patents
Gas turbine and its seal assembly Download PDFInfo
- Publication number
- CN107939455A CN107939455A CN201711105678.6A CN201711105678A CN107939455A CN 107939455 A CN107939455 A CN 107939455A CN 201711105678 A CN201711105678 A CN 201711105678A CN 107939455 A CN107939455 A CN 107939455A
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- China
- Prior art keywords
- sealing ring
- face
- ring
- fixed blade
- gas turbine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- 238000007789 sealing Methods 0.000 claims abstract description 159
- 230000002093 peripheral effect Effects 0.000 claims abstract description 18
- 238000001816 cooling Methods 0.000 abstract description 17
- 230000000694 effects Effects 0.000 abstract description 5
- 239000007789 gas Substances 0.000 description 50
- 238000005516 engineering process Methods 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000037237 body shape Effects 0.000 description 1
- 235000013399 edible fruits Nutrition 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 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
-
- 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
-
- 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
Abstract
The invention discloses a kind of gas turbine and its seal assembly, the gas turbine includes seal assembly and at least two fixed blade rings, fixed blade ring adjacent to each other includes prime fixed blade ring and rear class fixed blade ring, the leading flank of the rear class fixed blade ring is opposite with the trailing flank of the prime fixed blade ring, and the leading flank of the rear class fixed blade ring is equipped with annular groove；The seal assembly includes sealing ring, wavy spring and leaf spring, the wavy spring is arranged between the outer circumferential surface of the sealing ring and the periphery wall of the annular groove so that the sealing ring to be pushed to the inner peripheral wall of the annular groove, and the leaf spring is arranged between the sealing ring and the bottom surface of the annular groove to push the sealing ring to the prime fixed blade ring.The gas turbine of the present invention is unlikely to deform without processed springs mounting hole, sealing ring, improves cooling effect, and is assembled simple.
Description
Technical field
The present invention relates to gas turbine technology field, more particularly to a kind of seal assembly and tool of the turbine of gas turbine
There is the gas turbine of the seal assembly.
Background technology
During gas turbine operation, turbine stator blade, which is operated in high-temperature fuel gas, it is necessary to extract cooling air from compressor, to be entered
The chamber being made of fixed blade ring and turbine cylinder is ensured that turbine stator blade securely and reliably works, is improved blade with cooling turbine stator blade
Service life.In order to adapt to fixed blade ring by thermogenetic expansion, gap is equipped between adjacent vane ring.To avoid letting out for cooling air
Reveal, the gap location between adjacent vane ring needs to be equipped with seal assembly.
In correlation technique, the seal assembly between adjacent vane ring includes sealing ring and cylindrically coiled spring, sealing ring
One end face is bonded with the end face of a fixed blade ring, opens up spring mounting hole, Er Qiemi on the other end of sealing ring vertically
Spring mounting hole is radially opened up on the outer circumferential surface of seal ring, cylindrically coiled spring is located in spring mounting hole, sealing ring it is another
The external part of cylindrically coiled spring on end face is bonded with another fixed blade ring.However, above-mentioned seal assembly need vertically and
Multiple spring mounting holes radially are processed, are easy to cause sealing ring deformation, reduce sealing effect, and assembly difficulty is big.
The content of the invention
It is contemplated that solve at least some of the technical problems in related technologies.
For this reason, one aspect of the present invention proposes a kind of gas turbine, the gas turbine is close without processed springs mounting hole
Seal ring is unlikely to deform, and improves cooling effect, and is assembled simple.
Another aspect of the present invention also proposed a kind of seal assembly of gas turbine.
The gas turbine of embodiment according to a first aspect of the present invention includes at least two fixed blade rings, stator blade adjacent to each other
Ring includes prime fixed blade ring and rear class fixed blade ring, the trailing flank phase of the leading flank of the rear class fixed blade ring and the prime fixed blade ring
Right, the leading flank of the rear class fixed blade ring is equipped with annular groove；Seal assembly, the seal assembly include sealing ring, waveform
Spring and leaf spring, the wavy spring are arranged between the outer circumferential surface of the sealing ring and the periphery wall of the annular groove to incite somebody to action
The sealing ring pushes the inner peripheral wall of the annular groove to, and the leaf spring is arranged on the bottom of the sealing ring and the annular groove
To push the sealing ring to the prime fixed blade ring between face.
Gas turbine according to the present invention, passes through the ripple being located between sealing ring outer circumferential surface and the periphery wall of annular groove
Shape spring and the leaf spring being located between sealing ring end face and the bottom surface of annular groove respectively press to sealing ring in annular groove
In peripheral wall surfaces and prime fixed blade ring, without bullet of the processing on the sealing ring between fixed blade ring for installing cylindrical helical spring
Spring mounting hole, sealing ring are unlikely to deform, and can effectively seal cooling air, are adequately cooled the stator blade of gas turbine, are carried
High unit cooling effectiveness, and reduce assembly difficulty.
In certain embodiments, the gas turbine further includes the fastener for installing the sealing ring.
In certain embodiments, the fastener includes：Stud, the front end of the stud coordinate the spiral shell in the sealing ring
In pit, the rear end of the stud backs through out of described annular groove and stretches out the rear class fixed blade ring；Nut, the spiral shell
Parent phase coordinates in the rear end of the stud.
In certain embodiments, the leaf spring is multiple that multiple leaf springs surround the center of the sealing ring circumferentially
Uniform intervals are arranged.
In certain embodiments, the leaf spring includes dome portion and is extended radially outward from the outer peripheral edge in the dome portion
Annular shirt rim portion.
In certain embodiments, the leaf spring includes curved portion and outwardly extending straight from the both ends of the curved portion
Portion.
In certain embodiments, the sealing ring is formed by connecting by multiple arcs section along the circumferential direction of the sealing ring.
In certain embodiments, each end face of the segmental arc is stepped and including first end face, second end face
With the 3rd end face, when the radial direction along the sealing ring sees the outer circumferential surface of the sealing ring from outside, the first end face is along institute
The axially extending First Line of sealing ring is stated, the 3rd end face is the 3rd axially extending line along the sealing ring, described
Second end face be along the sealing ring circumferentially extending the second line, the second-line both ends respectively with the First Line one
End is connected with one end of the 3rd line, and the first end face of adjacent segmental arc is toward each other and between the first expansion spaced apart
Gap, the 3rd end face of adjacent segmental arc is relative to each other and is spaced apart the 3rd expansion clearance, and described the second of adjacent segmental arc
End face is in contact with each other.
In certain embodiments, the wavy spring is multiple multiple wavy springs and multiple segmental arcs one
One corresponds to.
The seal assembly of the gas turbine of embodiment according to a second aspect of the present invention, for sealing the gas turbine
Gap between the adjacent vane ring of turbine, the rear class fixed blade ring in the adjacent vane ring are equipped with opening towards prime stator blade
The annular groove of ring, the seal assembly include sealing ring, arranged on the sealing ring outer circumferential surface wavy spring and arranged on institute
The leaf spring of the trailing flank of sealing ring is stated, wherein the wavy spring is by institute when the seal assembly is located in the annular groove
State that sealing ring pushes the inner peripheral wall of the annular groove to and the leaf spring pushes the sealing ring to the prime fixed blade ring.
The seal assembly of gas turbine according to the present invention, is made between sealing ring and fixed blade ring by wavy spring and leaf spring
It is in close contact and realizes sealing, without processing the spring mounting hole for being used for installing cylindrical helical spring, sealing ring is unlikely to deform, can
Effectively to seal cooling air, the turbine stator blade in gas turbine is adequately cooled, improves the cold of gas turbine unit
But efficiency, and assemble simple.
In certain embodiments, the leaf spring is multiple that multiple leaf springs surround the center of the sealing ring circumferentially
Uniform intervals are arranged.
In certain embodiments, the leaf spring includes dome portion and is extended radially outward from the outer peripheral edge in the dome portion
Annular shirt rim portion.
In certain embodiments, the leaf spring includes curved portion and outwardly extending straight from the both ends of the curved portion
Portion.
In certain embodiments, the sealing ring is formed by connecting by multiple arcs section along the circumferential direction of the sealing ring.
In certain embodiments, each end face of the segmental arc is stepped and including first end face, second end face
With the 3rd end face, when the radial direction along the sealing ring sees the outer circumferential surface of the sealing ring from outside, the first end face is along institute
The axially extending First Line of sealing ring is stated, the 3rd end face is the 3rd axially extending line along the sealing ring, described
Second end face be along the sealing ring circumferentially extending the second line, the second-line both ends respectively with the First Line one
End is connected with one end of the 3rd line, and the first end face of adjacent segmental arc is toward each other and between the first expansion spaced apart
Gap, the 3rd end face of adjacent segmental arc is relative to each other and is spaced apart the 3rd expansion clearance, and described the second of adjacent segmental arc
End face is in contact with each other.
In certain embodiments, the wavy spring is multiple multiple wavy springs and multiple segmental arcs one
One corresponds to.
Brief description of the drawings
Fig. 1 is the overall structure diagram of gas turbine according to an embodiment of the invention；
Fig. 2 is the partial structurtes enlarged drawing of gas turbine according to an embodiment of the invention；
Fig. 3 is the structure diagram of the rear class fixed blade ring of gas turbine according to an embodiment of the invention；
Fig. 4 be gas turbine according to an embodiment of the invention Fig. 3 in sectional view along A-A；
Fig. 5 be gas turbine according to an embodiment of the invention Fig. 3 in B-B direction sectional view；
Fig. 6 be in the rear class fixed blade ring of gas turbine according to an embodiment of the invention and Fig. 4 of seal assembly C-C to cuing open
View；
Fig. 7 be gas turbine according to an embodiment of the invention Fig. 6 in D direction views.
Reference numeral：
Fixed blade ring 1, prime fixed blade ring 11, rear class fixed blade ring 12, annular groove 13, seal assembly 2, sealing ring 21, arc
Section 210, first end face 211, second end face 212, the 3rd end face 213, the first expansion clearance 214, the 3rd expansion clearance 215, ripple
Shape spring 22, leaf spring 23, curved portion 231, flat part 232, turbine cylinder 3, fastener 4, stud 41, nut 42, cooling hole 5,
Stator blade 6.
Embodiment
The embodiment of the present invention is described below in detail, the example of the embodiment is shown in the drawings.Below with reference to
The embodiment of attached drawing description is exemplary, it is intended to for explaining the present invention, and is not considered as limiting the invention.
As shown in figs. 1-7, gas turbine according to embodiments of the present invention includes fixed blade ring 1 and seal assembly 2, in other words,
Gas turbine includes turbine, and turbine has fixed blade ring 1 and seal assembly 2.
Fixed blade ring 1 at least two, fixed blade ring 1 adjacent to each other include prime fixed blade ring 11 and rear class fixed blade ring 12, after
Trailing flank (right flank in Fig. 1,2) phase of the leading flank (left surface in Fig. 1,2) and prime fixed blade ring 11 of level fixed blade ring 12
Right, the leading flank (left surface in Fig. 1,2) of rear class fixed blade ring 12 is equipped with annular groove 13.
In gas turbine operation, in order to cool down stator blades at different levels, there need to be enough cooling airs to enter fixed blade ring 1 and turbine
The chamber that cylinder 3 forms.The indoor cooling air of chamber enters stator blades 6 at different levels by the cooling hole 5 in fixed blade ring 1, quiet to cool down
Leaf 6.
As depicted in figs. 1 and 2, it is gradually reduced, makes along the airflow direction shown in arrow, gas pressure in turbine cylinder 3
Obtain fixed blade ring air inlet side (left side in Fig. 1,2) pressure and go out gas side (right side in Fig. 1,2) pressure, gas turbine more than fixed blade ring
Under operating condition, fixed blade ring, which goes out gas side, will be adjacent to cylinder, and fixed blade rings at different levels (air inlet side) will expand forward at work, for this reason,
There must be the expansion clearance for being used for compensating expansion between adjacent fixed blade ring.However, in order to prevent cooling air leakage, it is necessary to
The expansion clearance is sealed, to ensure cooling effect.
As shown in fig. 1,4 fixed blade rings 1, adjacent two fixed blade rings, wherein positioned at left side are equipped with successively from left to right
For prime fixed blade ring 11, be rear class fixed blade ring 12 positioned at right side, it will be appreciated herein that prime fixed blade ring and rear class are quiet
In contrast leaf joint is.For example, two adjacent fixed blade rings of the leftmost side, the fixed blade ring of the leftmost side is prime fixed blade ring 11,
Positioned at the right side of the prime fixed blade ring 11 and adjacent with the prime fixed blade ring 11 for rear class fixed blade ring 12, and the rear class fixed blade ring
12 become prime fixed blade ring again relative to the fixed blade ring on the right side of it.The right flank of prime fixed blade ring 11 and a left side for rear class fixed blade ring 12
Side is opposite, and the left surface of rear class fixed blade ring 12 is equipped with annular groove 13.
Seal assembly 2 includes sealing ring 21, wavy spring 22 and leaf spring 23, and wavy spring 22 is arranged on the periphery of sealing ring 21
Sealing ring 21 to be pushed to the internal perisporium of annular groove 13 between the periphery wall of face and annular groove 13 (upper wall surface in Fig. 4)
Face (lower wall surface in Fig. 4), in other words, the inner peripheral surface of sealing ring 21 are in close contact with the inner peripheral wall of annular groove 13 to realize
Sealing.Leaf spring 23 is arranged between sealing ring 21 and the bottom surface (right flank in Fig. 4) of annular groove 13 so that sealing ring 21 to be pushed to
Prime fixed blade ring 11, in other words, the left side of sealing ring 21 are in close contact with the right flank of prime fixed blade ring 11 to realize sealing.
As shown in Figure 4 and Figure 6, wavy spring 22 can be arranged on the periphery wall of sealing ring 21, and is located at sealing ring 21
Outer circumferential surface and annular groove 13 periphery wall between, sealing ring 21 to be pushed to the inner peripheral wall of annular groove 13.Plate
Spring 23 is arranged on the right flank of sealing ring 21 and between sealing ring 21 and the bottom surface of annular groove 13, to by sealing ring 21
Push prime fixed blade ring 11 to.Under the action of wavy spring 22 and leaf spring 23, sealing ring 21 respectively with rear class fixed blade ring 12 and before
The level contact sealing of fixed blade ring 11, prevents cooling air from revealing, is adequately cooled the stator blade 6 in gas turbine.
It is understood that as described above, fixed blade ring can be the fixed blade ring in turbine, gas turbine includes turbine cylinder
3, turbine cylinder 3 is interior to have above-mentioned fixed blade ring 1 and seal assembly 2.In other words, which is used to seal gas turbine
Turbine adjacent vane ring 1 between gap, it is quiet towards prime that the rear class fixed blade ring 12 in adjacent vane ring 1 is equipped with opening
The annular groove 13 of leaf joint 11, seal assembly 2 include sealing ring 21, arranged on sealing ring 21 outer circumferential surface wavy spring 22 and set
Leaf spring 23 in the trailing flank of sealing ring 21, wherein, when seal assembly 2 is located in annular groove 13, wavy spring 22 will be close
Seal ring 21 pushes the inner peripheral wall of annular groove 13 to, and leaf spring 23 pushes sealing ring 21 to prime fixed blade ring 11.According to the present invention
Gas turbine, the sealing of fixed blade ring 1 in turbine cylinder 3 is realized by the seal assembly 2, with the stator blade 6 in sufficiently cool turbine.
Gas turbine according to the present invention, makes to be in close contact between sealing ring and fixed blade ring real by wavy spring and leaf spring
Now seal, without processed springs mounting hole on the sealing ring between fixed blade ring, sealing ring is unlikely to deform, and can effectively be sealed cold
But air, makes the stator blade of gas turbine sufficiently cool, improves the cooling effectiveness of gas turbine unit, and reduces sealing group
The assembly difficulty of part.
In certain embodiments, as shown in figure 5, gas turbine further includes the fastener 4 of installation sealing ring 21.Can at some
In the embodiment of choosing, fastener 4 includes stud 41 and nut 42, and the front end (left end in Fig. 5) of stud 41 coordinates in sealing ring
In 21 threaded hole, the rear end (right end in Fig. 5) of stud 41 passes through and stretches (in Fig. 5 to the right) backward out of annular groove 13
Go out rear class fixed blade ring 12.Nut 42 is engaged in the rear end of stud 41.By the cooperation of stud 41 and nut 42, by sealing ring 21
It is fastened on rear class fixed blade ring 12, comes off to avoid sealing ring 21 from annular groove 13, also, depth is screwed in by adjusting stud 41
Degree, can adjust the elastic force of leaf spring 23, to adjust the seal degree of sealing ring 21 and prime fixed blade ring 11.Preferably, in stator blade
Ring 1 be installed in place and sealing ring 21 it is in place after, fastener 4 can be removed, and in other words, fastener 4 is used to assemble sealing ring 21, example
Such as sealing ring 21 is moved to the right in annular groove 13 by stud 41 and nut 42, in order to the installation of fixed blade ring 1, is then released
Nut 42 and stud 41 are put, sealing ring 21 is abutted on prime fixed blade ring 11 by leaf spring 23, can finally remove stud 41.
In certain embodiments, leaf spring 23 is multiple, multiple leaf springs 23 around the center of sealing ring 21 circumferentially uniformly between
Every arrangement.By multiple equally distributed leaf springs 23, sealing ring 21 can be further improved and the sealing of prime fixed blade ring 11 is imitated
Fruit, sufficiently cool stator blade.
In certain embodiments, as shown in Figure 4 and Figure 5, leaf spring 23 includes dome portion and annular shirt rim portion, and shirt rim portion is from vault
The outer peripheral edge in shape portion extends radially outward.In the example depicted in fig. 5, the dome portion of leaf spring 23 is the part ball swelled to the right
Body shape, the outer peripheral edge in dome portion have along the annular shirt rim portion to extend radially outwardly of the part sphere.It is optional at other
In embodiment, leaf spring 23 is for tabular and including curved portion 231 and flat part 232, and the flat part 232 is from the both ends of curved portion 231
Stretch out, in Figure 5, flat part 232 upwardly extends and downward from the lower end of curved portion 231 from the upper end of curved portion 231
Extension.When seal assembly 2 is arranged in annular groove 13, curved portion 231 is resisted against on the bottom surface of annular groove 13 that will seal
Ring 21 pushes prime fixed blade ring 11 to.
In certain embodiments, as shown in fig. 7, sealing ring 21 is connected by multiple arcs section 210 along the circumferential direction of the sealing ring 21
Connect and form.
In certain embodiments, each end face of segmental arc 210 is stepped and including first end face 211, second end
212 and the 3rd end face 213 of face, when the radial direction along sealing ring 21 sees the outer circumferential surface of sealing ring 21 from outside, as shown in figure 4, first
End face 211 is the First Line extended along the axial direction (left and right directions in Fig. 7) of sealing ring 21, and the 3rd end face 213 is along sealing ring
21 the 3rd axially extending line, second end face 212 are second extended along the circumferential direction (above-below direction in Fig. 7) of sealing ring 21
Line.Second-line both ends are connected with one end of First Line and one end of the 3rd line respectively, so that three lines form substantially Z-shaped.
The first end face 211 of adjacent segmental arc 210 is relative to each other and is spaced apart the first expansion clearance 214, and the 3rd of adjacent segmental arc 210 the
End face 213 is toward each other and the 3rd expansion clearance 215 spaced apart, the second end face 212 of adjacent segmental arc 210 are in contact with each other.
It is understood that can both ensure expansion clearance to each other between adjacent segmental arc 210, i.e., the first expansion
214 and the 3rd expansion clearance 215 of gap, and it is adjacent under the action of leaf spring 23 second end face 212 of adjacent segmental arc 210
Sealing, to prevent cooling air from revealing.Gas pressure is additionally, since along the axial action of sealing ring 21 to the end face of sealing ring
On, by making the contact surface of adjacent segmental arc 210 to further improve the sealing between second end face 212 into substantially Z-shaped row
Property.
In addition, the restriction of " the first expansion clearance " and " the 3rd expansion clearance " be in order to first end face and the 3rd end face phase
Adapt to, the therein first, the 3rd and there is no order relation.In other words, " the first expansion clearance " and " the 3rd expansion clearance "
Restriction, be not in that also there are the possibility of the second expansion clearance.
In certain embodiments, wavy spring 22 is multiple that multiple wavy springs 22 are a pair of with multiple arcs section 210 1
Should.In other words, a wavy spring 22 is equipped with each segmental arc 210, i.e., sealing ring 21 is by how many a segmental arcs 210 along this
The circumferential direction of sealing ring 21 is formed by connecting, then with regard to how many wavy spring 22 on the sealing ring 21.
In addition, the gas pressure at the outside A1 of sealing ring 21, at the right side A2 of sealing ring 21 is equal to the gas at chamber A
Pressure, the gas pressure at the inner side B1 of sealing ring 21 are equal to the gas pressure at chamber B, and at 3 inner cavity chamber A of turbine cylinder
Gas pressure is more than the gas pressure at chamber B, then at the outside A1 of sealing ring 21 and at the A2 of right side with being deposited between the B1 of inner side
In gas differential pressure, under the action of the gas differential pressure, it is quiet that the left surface and inner peripheral wall of sealing ring 21 are adjacent to prime respectively
Leaf joint 11 and rear class fixed blade ring 12, can preferably seal two contact surfaces, so that sealing effect is further improved, it is sufficiently cool
Stator blade.
Below with reference to the accompanying drawings 1-7 describes the gas turbine of specific embodiment according to the present invention.
As shown in figs. 1-7, gas turbine according to embodiments of the present invention includes the fixed blade ring 1, close being arranged in turbine cylinder 3
Sealing assembly 2 and fastener 4.
Fixed blade ring 1 is four, and four fixed blade rings 1 are set gradually from left to right, and it is quiet that fixed blade ring 1 adjacent to each other includes prime
Leaf joint 11 and rear class fixed blade ring 12.The left surface of rear class fixed blade ring 12 is opposite with the right flank of prime fixed blade ring 11, rear class stator blade
The left surface of ring 12 is equipped with annular groove 13.
Seal assembly 2 includes sealing ring 21, wavy spring 22 and leaf spring 23.
Sealing ring 21 is formed by connecting by multiple arcs section 210 along the circumferential direction of the sealing ring 21.
Wavy spring 22 is multiple, and multiple wavy springs 22 are corresponded with multiple arcs section 210, i.e., each segmental arc
A wavy spring 22 is equipped with 210 outer circumferential surface.Wavy spring 22 is located at the outer circumferential surface and annular groove 13 of sealing ring 21
Periphery wall between sealing ring 21 to be pushed to the inner peripheral wall of annular groove 13.
Leaf spring 23 is arranged on the right flank of sealing ring 21 and including curved portion 231 and flat part 232, the curved portion 231
Both ends stretch out to form flat part 232.Leaf spring 23 is multiple, and multiple leaf springs 23 are circumferentially uniform around the center of sealing ring 21
Arranged for interval.Leaf spring 23 is located between the right flank of sealing ring 21 and the bottom surface of annular groove 13 to push sealing ring 21 to prime
Fixed blade ring 11.
Each end face of the segmental arc 210 of sealing ring 21 is stepped and including first end face 211, second end face 212
With the 3rd end face 213, when the radial direction along sealing ring 21 sees the outer circumferential surface of sealing ring 21 from outside, as shown in fig. 7, first end face
211 be the axially extending First Line along sealing ring 21, and the 3rd end face 213 is the 3rd axially extending line along sealing ring 21,
Second end face 212 be along the second line of the circumferentially extending of sealing ring 21, second-line both ends respectively with one end of First Line and the
One end of three lines is connected, and three lines form substantially zigzag, i.e., the contact surface of adjacent segmental arc 210 is substantially zigzag.Adjacent arcs
The first end face 211 of shape section 210 is relative to each other and is spaced apart the first expansion clearance 214, the 3rd end face of adjacent segmental arc 210
213 the 3rd expansion clearances 215 relative to each other and spaced apart, the second end face 212 of adjacent segmental arc 210 is under the action of leaf spring 23
It is in contact with each other.
Fastener 4 includes stud 41 and nut 42, as shown in figure 5, the left end of stud 41 coordinates the screw thread in sealing ring 21
In hole, the right end of stud 41 passes through to the right out of annular groove 13 and stretches out rear class fixed blade ring 12.Nut 42 is engaged in stud
41 rear end.By the cooperation of stud 41 and nut 42, sealing ring 21 is fastened on rear class fixed blade ring 12, to avoid sealing ring
21 come off from annular groove 13, also, by adjusting 41 screw-in depth of stud, can adjust the elastic force of leaf spring 23, close to adjust
Seal ring 21 and the seal degree of prime fixed blade ring 11.Alternatively, can be with after fixed blade ring 1 is installed in place and sealing ring 21 is in place
Remove stud 41 and nut 42.
It is understood that assembling seal assembly 2 when on rear class fixed blade ring 12, sealing ring 21 is first placed in rear class stator blade
In the annular groove 13 of ring 12, the lateral surface of the wavy spring 22 on 21 outer circumferential surface of sealing ring is resisted against the inner circumferential of annular groove 13
On wall, the lateral surface of the leaf spring 23 on the end face of sealing ring 21 is resisted against on the bottom surface of annular groove 13.
In the description of the present invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", " length ", " width ",
" thickness ", " on ", " under ", "front", "rear", "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outer ", " up time
The orientation or position relationship of the instruction such as pin ", " counterclockwise ", " axial direction ", " radial direction ", " circumferential direction " be based on orientation shown in the drawings or
Position relationship, is for only for ease of and describes the present invention and simplify description, rather than indicates or imply that signified device or element must
There must be specific orientation, with specific azimuth configuration and operation, therefore be not considered as limiting the invention.
In addition, term " first ", " second " are only used for description purpose, and it is not intended that instruction or hint relative importance
Or the implicit quantity for indicating indicated technical characteristic.Thus, define " first ", the feature of " second " can be expressed or
Implicitly include at least one this feature.In the description of the present invention, " multiple " are meant that at least two, such as two, three
It is a etc., unless otherwise specifically defined.
In the present invention, unless otherwise clearly defined and limited, term " installation ", " connected ", " connection ", " fixation " etc.
Term should be interpreted broadly, for example, it may be fixedly connected or be detachably connected, or integrally；Can be that machinery connects
Connect or be electrically connected or can communicate each other；It can be directly connected, can also be indirectly connected by intermediary, can be with
It is the interaction relationship of connection inside two elements or two elements, unless otherwise restricted clearly.For this area
For those of ordinary skill, the concrete meaning of above-mentioned term in the present invention can be understood as the case may be.
In the present invention, unless otherwise clearly defined and limited, fisrt feature can be with "above" or "below" second feature
It is that the first and second features directly contact, or the first and second features pass through intermediary mediate contact.Moreover, fisrt feature exists
Second feature " on ", " top " and " above " but fisrt feature are directly over second feature or oblique upper, or be merely representative of
Fisrt feature level height is higher than second feature.Fisrt feature second feature " under ", " lower section " and " below " can be
One feature is immediately below second feature or obliquely downward, or is merely representative of fisrt feature level height and is less than second feature.
In the description of this specification, reference term " one embodiment ", " some embodiments ", " example ", " specifically show
The description of example " or " some examples " etc. means specific features, structure, material or the spy for combining the embodiment or example description
Point is contained at least one embodiment of the present invention or example.In the present specification, schematic expression of the above terms is not
It must be directed to identical embodiment or example.Moreover, particular features, structures, materials, or characteristics described can be in office
Combined in an appropriate manner in one or more embodiments or example.In addition, without conflicting with each other, the skill of this area
Art personnel can be tied the different embodiments or example described in this specification and different embodiments or exemplary feature
Close and combine.
Although the embodiment of the present invention has been shown and described above, it is to be understood that above-described embodiment is example
Property, it is impossible to limitation of the present invention is interpreted as, those of ordinary skill in the art within the scope of the invention can be to above-mentioned
Embodiment is changed, changes, replacing and modification.
Claims (16)
- A kind of 1. gas turbine, it is characterised in that including：At least two fixed blade rings, fixed blade ring adjacent to each other include prime fixed blade ring and rear class fixed blade ring, the rear class fixed blade ring Leading flank it is opposite with the trailing flank of the prime fixed blade ring, the leading flank of the rear class fixed blade ring is equipped with annular groove；Seal assembly, the seal assembly include sealing ring, wavy spring and leaf spring, and the wavy spring is arranged on the sealing ring Outer circumferential surface and the annular groove periphery wall between the sealing ring to be pushed to the inner peripheral wall of the annular groove, The leaf spring is arranged between the sealing ring and the bottom surface of the annular groove to push the sealing ring to the prime stator blade Ring.
- 2. gas turbine according to claim 1, it is characterised in that further include the fastener for installing the sealing ring.
- 3. gas turbine according to claim 2, it is characterised in that the fastener includes：Stud, the front end of the stud coordinate in the threaded hole of the sealing ring, and the rear end of the stud is recessed from the annular Backed through in groove and stretch out the rear class fixed blade ring；Nut, the nut are engaged in the rear end of the stud.
- 4. gas turbine according to claim 1, it is characterised in that the leaf spring is multiple, and multiple leaf springs surround Circumferentially uniform intervals are arranged at the center of the sealing ring.
- 5. gas turbine according to claim 1, it is characterised in that the leaf spring includes dome portion and from described dome The annular shirt rim portion that the outer peripheral edge in portion extends radially outward.
- 6. gas turbine according to claim 1, it is characterised in that the leaf spring includes curved portion and from the arc The outwardly extending flat part in both ends in portion.
- 7. according to the gas turbine any one of claim 1-6, it is characterised in that the sealing ring is by multiple arcs section It is formed by connecting along the circumferential direction of the sealing ring.
- 8. gas turbine according to claim 7, it is characterised in that each end face of the segmental arc it is stepped and Including first end face, second end face and the 3rd end face, the outer circumferential surface of the sealing ring is seen from outside in the radial direction along the sealing ring When, the first end face is the axially extending First Line along the sealing ring, and the 3rd end face is along the sealing ring The 3rd axially extending line, the second end face be along the sealing ring circumferentially extending the second line, described second-line two End is connected with one end of the First Line and one end of the 3rd line respectively, the first end face of adjacent segmental arc phase each other Pair and be spaced apart the first expansion clearance, the 3rd end face of adjacent segmental arc toward each other and is spaced apart the 3rd expansion clearance, The second end face of adjacent segmental arc is in contact with each other.
- 9. gas turbine according to claim 7, it is characterised in that the wavy spring is multiple, multiple waveforms Spring is corresponded with multiple segmental arcs.
- A kind of 10. seal assembly of gas turbine, between the adjacent vane ring for the turbine for sealing the gas turbine Gap, the rear class fixed blade ring in the adjacent vane ring are equipped with annular groove of the opening towards prime fixed blade ring, it is characterised in that The seal assembly include sealing ring, arranged on the sealing ring outer circumferential surface wavy spring and the rear side arranged on the sealing ring The leaf spring in face, wherein the wavy spring pushes the sealing ring to institute when the seal assembly is located in the annular groove State the inner peripheral wall of annular groove and the leaf spring pushes the sealing ring to the prime fixed blade ring.
- 11. the seal assembly of gas turbine according to claim 10, it is characterised in that the leaf spring is multiple to be multiple The leaf spring around the center of the sealing ring, circumferentially arrange by uniform intervals.
- 12. the seal assembly of gas turbine according to claim 10, it is characterised in that the leaf spring include dome portion and The annular shirt rim portion extended radially outward from the outer peripheral edge in the dome portion.
- 13. the seal assembly of gas turbine according to claim 10, it is characterised in that the leaf spring include curved portion with And from the outwardly extending flat part in the both ends of the curved portion.
- 14. the seal assembly of the gas turbine according to any one of claim 10-13, it is characterised in that the sealing Ring is formed by connecting by multiple arcs section along the circumferential direction of the sealing ring.
- 15. the seal assembly of gas turbine according to claim 14, it is characterised in that each end face of the segmental arc It is stepped and including first end face, second end face and the 3rd end face, seen in the radial direction along the sealing ring from outside described close During the outer circumferential surface of seal ring, the first end face is the axially extending First Line along the sealing ring, and the 3rd end face is edge The 3rd axially extending line of the sealing ring, the second end face are along the second line of the circumferentially extending of the sealing ring, institute State second-line both ends respectively with one end of the First Line and one end of the 3rd line to be connected, described the of adjacent segmental arc End face toward each other and is spaced apart the first expansion clearance, and the 3rd end face of adjacent segmental arc toward each other and is spaced apart the Three expansion clearances, the second end face of adjacent segmental arc are in contact with each other.
- 16. the seal assembly of gas turbine according to claim 14, it is characterised in that the wavy spring to be multiple, Multiple wavy springs are corresponded with multiple segmental arcs.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711105678.6A CN107939455A (en) | 2017-11-10 | 2017-11-10 | Gas turbine and its seal assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711105678.6A CN107939455A (en) | 2017-11-10 | 2017-11-10 | Gas turbine and its seal assembly |
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| Publication Number | Publication Date |
|---|---|
| CN107939455A true CN107939455A (en) | 2018-04-20 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711105678.6A Pending CN107939455A (en) | 2017-11-10 | 2017-11-10 | Gas turbine and its seal assembly |
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| Country | Link |
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| CN (1) | CN107939455A (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111335973A (en) * | 2018-12-19 | 2020-06-26 | 通用电气公司 | Shroud seal for gas turbine engine |
| CN111561358A (en) * | 2020-05-12 | 2020-08-21 | 中国航发湖南动力机械研究所 | Test seal device and method of mounting test member |
| KR102291086B1 (en) * | 2020-02-21 | 2021-08-18 | 두산중공업 주식회사 | Sealing assembly and gas turbine comprising the same |
| KR20220027559A (en) * | 2020-08-27 | 2022-03-08 | 두산중공업 주식회사 | Sealing assembly and turbo-machine comprising the same |
| KR20220028378A (en) * | 2020-08-28 | 2022-03-08 | 두산중공업 주식회사 | Sealing assembly and turbo-machine comprising the same |
| CN114151143A (en) * | 2021-11-11 | 2022-03-08 | 中国联合重型燃气轮机技术有限公司 | Gas turbine and seal assembly therefor |
| KR20230040021A (en) * | 2021-09-15 | 2023-03-22 | 두산에너빌리티 주식회사 | Sealing assembly and turbo-machine comprising the same |
| KR20230040670A (en) * | 2021-09-16 | 2023-03-23 | 두산에너빌리티 주식회사 | Sealing assembly and turbo-machine comprising the same |
| US11913339B2 (en) * | 2021-09-29 | 2024-02-27 | Doosan Enerbility Co., Ltd. | Sealing assembly and turbomachine including same |
| KR102659819B1 (en) * | 2021-09-29 | 2024-04-23 | 두산에너빌리티 주식회사 | Sealing assembly and turbo-machine comprising the same |
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| CN111335973A (en) * | 2018-12-19 | 2020-06-26 | 通用电气公司 | Shroud seal for gas turbine engine |
| KR102291086B1 (en) * | 2020-02-21 | 2021-08-18 | 두산중공업 주식회사 | Sealing assembly and gas turbine comprising the same |
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| KR20230040670A (en) * | 2021-09-16 | 2023-03-23 | 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 |
| US11913339B2 (en) * | 2021-09-29 | 2024-02-27 | Doosan Enerbility Co., Ltd. | Sealing assembly and turbomachine including same |
| KR102659819B1 (en) * | 2021-09-29 | 2024-04-23 | 두산에너빌리티 주식회사 | Sealing assembly and turbo-machine comprising the same |
| CN114151143A (en) * | 2021-11-11 | 2022-03-08 | 中国联合重型燃气轮机技术有限公司 | Gas turbine and seal assembly therefor |
| 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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