CN104632414A - Sealing structure for gas turbine - Google Patents
Sealing structure for gas turbine Download PDFInfo
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- CN104632414A CN104632414A CN201510051715.4A CN201510051715A CN104632414A CN 104632414 A CN104632414 A CN 104632414A CN 201510051715 A CN201510051715 A CN 201510051715A CN 104632414 A CN104632414 A CN 104632414A
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- sealing
- sealing block
- gas turbine
- stator ring
- ring
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Abstract
The invention relates to the technical field of design and manufacture of gas turbines, and particularly relates to a sealing structure for a gas turbine. The sealing structure for the gas turbine comprises two stator rings to be sealed, and a sealing block, wherein one end of the sealing block is fit with the end face of one stator ring, and the other end of the sealing block is connected with the other stator ring in a left-right slidable manner. One end of the sealing block is fit with the end part of one stator ring, the other end of the sealing block is connected with the other stator ring in the slidable manner, and when axial thermal deformation and radial thermal deformation occur between the stator rings, the stator rings are always completely sealed by virtue of the sealing block without reserving a sealing gap, the sealing effect is better, and the problem that the sealing effect is poor because a large axial sealing gap and a large radial sealing gap are reserved for meeting a demand of axial thermal deformation and radial thermal deformation by a conventional labyrinth seal manner are solved.
Description
Technical field
The present invention relates to gas turbine design manufacturing technology field, particularly relate to a kind of gas turbine sealing configuration.
Background technique
At present, as shown in Figure 1, there is the sealing between a large amount of stator ring 1 ' parts and stator ring 1 ' parts in gas turbine, hermetic seal effect directly can have influence on the safe operation of gas turbine overall thermal cycle efficiency and unit; Simultaneously because gas turbine is at high temperature-end part, often there is cooling air and high-temperature fuel gas in stator ring 1 ' parts simultaneously, therefore need often there is the larger temperature difference between two stator ring 1 ' parts of sealing, under working state and normal temperature state, the axial clearance between stator ring 1 ' and radial dimension change are very greatly; Two need the stator ring 1 ' parts sealed, are limited to machining accuracy and assembly precision, and the axial clearance often when assembling also has larger tolerance value.
Prior art, when processing the sealing between stator ring 1 ' parts and stator ring 1 ' parts, often adopts the labyrinth seals with axis and radial clearance, to meet the gap change requirement that processing and assembling tolerance, Axial Thermal distortion and radial heat distortion bring; And existing labyrinth sealing is needing in axis with in the radial direction all with larger seal clearance 3 between two the stator rings 1 ' sealed, the effect of obturaging is poor.
Therefore, for above deficiency, need to provide a kind of can absorption axes to the gas turbine sealing configuration of size distortion and build-up tolerance, increase sealing effect.
Summary of the invention
(1) technical problem that will solve
The technical problem to be solved in the present invention is: the sealing between traditional stator ring, employing be labyrinth sealing, can cause axially with in the radial direction all with larger seal clearance between two stator rings of needs sealing, the effect of obturaging is poor.
(2) technological scheme
In order to solve the problems of the technologies described above, the invention provides a kind of gas turbine sealing configuration, comprise two stator rings to be sealed and sealing block, the end face of one end of described sealing block and a stator ring is fitted, and what the other end of described sealing block can horizontally slip is connected with another stator ring.
Wherein, also comprise pushing component, described pushing component horizontally slips for promoting sealing block.
Wherein, described pushing component comprises the chute that the stator ring that is connected with described sealing block is offered and the elastic component being positioned at chute, and described sealing block can horizontally slip under the effect of elastic component in chute.
Wherein, described elastic component is spring.
Wherein, described spring is sealed in chute by plug screw.
Wherein, described sealing block is connected with described spring by coupling shaft.
Wherein, described stator ring is the circular ring be made up of upper and lower two each and every one semi-rings, and described sealing block is the circular ring that at least two ring sections are formed, and each ring section is at least provided with one group of pushing component to seal ring.
Wherein, described sealing block is high temperature resistant material.
(3) beneficial effect
Technique scheme tool of the present invention has the following advantages: the invention provides a kind of gas turbine sealing configuration, comprise two stator rings to be sealed and sealing block, the end face of one end of described sealing block and a stator ring is fitted, and what the other end of described sealing block can horizontally slip is connected with another stator ring.One end of sealing block is fitted in the end of stator ring, the other end slidably connects, between stator ring, occur that Axial Thermal distortion and radial heat distortion are, all the time sealed completely by sealing block between stator ring, do not need reserved seal clearance, sealing effect is better, solves traditional labyrinth sealing to meet the demand of Axial Thermal distortion and radial heat distortion, reserved larger axial seal gap and radial seal gap, and the problem of the sealing effect difference caused.
Accompanying drawing explanation
The advantage of the above-mentioned and/or additional aspect of the present invention will become obvious and easy understand from accompanying drawing below combining to the description of embodiment, wherein:
Fig. 1 is the structural representation sealed between stator ring in prior art;
Fig. 2 is the schematic diagram of the gas turbine sealing configuration described in one embodiment of the invention;
Fig. 3 is the A portion structure for amplifying schematic diagram of Fig. 2;
Fig. 4 is the schematic diagram that sealing block coordinates with stator ring.
Corresponding relation wherein in Fig. 1 and Fig. 4 between reference character and component names is:
1 ' stator ring, 3, seal clearance, 1, stator ring, 11, chute, 12, elastic component, 13, coupling shaft, 14, plug screw, 2, sealing block.
Embodiment
In describing the invention, it should be noted that, term " " center ", " longitudinal direction ", " transverse direction ", " on ", D score, " front ", " afterwards ", " left side ", " right side ", " vertically ", " level ", " top ", " end ", " " interior ", orientation or the position relationship of the instruction such as " outward " are based on orientation shown in the drawings or position relationship, only the present invention for convenience of description and simplified characterization, instead of indicate or imply that the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore limitation of the present invention can not be interpreted as.In addition, term " first ", " second " only for describing object, and can not be interpreted as instruction or hint relative importance.
In describing the invention, it should be noted that, unless otherwise clearly defined and limited, term " installation ", " being connected ", " connection " should be interpreted broadly, and such as, can be fixedly connected with, also can be removably connect, or connect integratedly; Can be mechanical connection, also can be electrical connection; Can be directly be connected, also indirectly can be connected by intermediary, can be the connection of two element internals.For the ordinary skill in the art, concrete condition above-mentioned term concrete meaning in the present invention can be understood.In addition, in describing the invention, except as otherwise noted, the implication of " multiple " is two or more
For making the object of the embodiment of the present invention, technological scheme and advantage clearly, below in conjunction with the accompanying drawing in the embodiment of the present invention, technological scheme in the embodiment of the present invention is clearly and completely described, obviously, described embodiment is a part of embodiment of the present invention, instead of whole embodiments.Based on the embodiment in the present invention, the every other embodiment that those of ordinary skill in the art obtain under the prerequisite not making creative work, belongs to the scope of protection of the invention.
As shown in Figure 2, the invention provides a kind of gas turbine sealing configuration, comprise two stator rings 1 to be sealed and sealing block 2, described sealing block 2 is high temperature resistant material, one end of described sealing block 2 and the end face of a stator ring 1 are fitted, and what the other end of described sealing block 2 can horizontally slip is connected with another stator ring 1.One end of sealing block 2 is fitted in the end of stator ring 1, the other end slidably connects, between stator ring 1, occur that Axial Thermal distortion and radial heat distortion are, all the time sealed completely by sealing block 2 between stator ring 1, do not need reserved seal clearance, sealing effect is better, solves traditional labyrinth sealing to meet the demand of Axial Thermal distortion and radial heat distortion, reserved larger axial seal gap and radial seal gap, and the problem of the sealing effect difference caused.
As shown in Figure 3, preferably, also comprise pushing component, described pushing component comprises the chute 11 that the stator ring 1 that is connected with described sealing block 2 is offered and elastic component 12 spring being positioned at chute 11, described sealing block 2 can horizontally slip under the effect of elastic component 12 in chute 11, when stator ring 1 occurs that Axial Thermal is out of shape, sealing block 2 remains the laminating with stator ring 1 under the effect of elastic component 12 like this, perfectly can realize sealing, when occurring carrying out thermal distortion, relative sliding is produced between the section of sealing block 2 and stator ring 1, the normal work of gas turbine can not be affected, and can be good at realizing the sealing between stator ring 1.Particularly, described elastic component 12 is spring, and described sealing block 2 is connected with described spring by coupling shaft 13, and the structure of spring is simple, selection is easy, cheap.
Certainly, elastic component 12 can be also other devices, as long as can realize the object horizontally slipped of sealing block 2, its aim does not depart from design philosophy of the present invention, should belong to protection scope of the present invention
Preferably, described spring is sealed in chute 11 by plug screw 14, can promote the sealing effect between stator ring 1.
Further, as shown in Figure 4, described stator ring 1 is the circular ring be made up of upper and lower two each and every one semi-rings, described sealing block 2 is the circular ring that at least two ring sections are formed, and each ring section is at least provided with one group of pushing component to seal ring, intactly can form sealing configuration like this, and be provided with at least one group of pushing component in each ring section, the slip of sealing block 2 can be guaranteed, ensure the quality of sealing, first sealing block 2 is screwed in the semi-ring up and down of stator ring 1 when mounted, after screw-in sealing block 2, at installation step axle and spring, finally use plug screw 14 by spring sealed chute 11 on stator ring 1.
In sum, gas turbine sealing configuration provided by the invention, comprise two stator rings to be sealed and sealing block, the end face of one end of described sealing block and a stator ring is fitted, and what the other end of described sealing block can horizontally slip is connected with another stator ring.One end of sealing block is fitted in the end of stator ring, the other end slidably connects, between stator ring, occur that Axial Thermal distortion and radial heat distortion are, all the time sealed completely by sealing block between stator ring, do not need reserved seal clearance, sealing effect is better, solves traditional labyrinth sealing to meet the demand of Axial Thermal distortion and radial heat distortion, reserved larger axial seal gap and radial seal gap, and the problem of the sealing effect difference caused.
Last it is noted that above embodiment is only in order to illustrate technological scheme of the present invention, be not intended to limit; Although with reference to previous embodiment to invention has been detailed description, those of ordinary skill in the art is to be understood that: it still can be modified to the technological scheme described in foregoing embodiments, or carries out equivalent replacement to wherein portion of techniques feature; And these amendments or replacement, do not make the essence of appropriate technical solution depart from the spirit and scope of various embodiments of the present invention technological scheme.
Claims (8)
1. a gas turbine sealing configuration, it is characterized in that: comprise two stator rings (1) to be sealed and sealing block (2), one end of described sealing block (2) and the end face of a stator ring (1) are fitted, and what the other end of described sealing block (2) can horizontally slip is connected with another stator ring (1).
2. gas turbine sealing configuration according to claim 1, is characterized in that: also comprise pushing component, and described pushing component horizontally slips for promoting sealing block (2).
3. gas turbine sealing configuration according to claim 2, it is characterized in that: described pushing component comprises the chute (11) that the stator ring (1) that is connected with described sealing block (2) is offered and the elastic component (12) being positioned at chute (11), and described sealing block (2) can horizontally slip under the effect of elastic component (12) in chute (11).
4. gas turbine sealing configuration according to claim 3, is characterized in that: described elastic component (12) is spring.
5. gas turbine sealing configuration according to claim 4, is characterized in that: described spring is sealed in chute (11) by plug screw (14).
6. gas turbine sealing configuration according to claim 5, is characterized in that: described sealing block (2) is connected with described spring by coupling shaft (13).
7. gas turbine sealing configuration according to claim 2, it is characterized in that: described stator ring (1) is the circular ring be made up of upper and lower two each and every one semi-rings, described sealing block (2) is the circular ring that at least two ring sections are formed, and each ring section is at least provided with one group of pushing component to seal ring.
8. the gas turbine sealing configuration according to any one of claim 1-7, is characterized in that: described sealing block (2) is high temperature resistant material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510051715.4A CN104632414A (en) | 2015-01-30 | 2015-01-30 | Sealing structure for gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510051715.4A CN104632414A (en) | 2015-01-30 | 2015-01-30 | Sealing structure for gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104632414A true CN104632414A (en) | 2015-05-20 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510051715.4A Pending CN104632414A (en) | 2015-01-30 | 2015-01-30 | Sealing structure for gas turbine |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020168263A1 (en) * | 2001-04-04 | 2002-11-14 | Hans-Thomas Bolms | Seal element for sealing a gap and combustion turbine having a seal element |
| US20040223844A1 (en) * | 2003-05-07 | 2004-11-11 | Farrell Alison Carol | Method and apparatus to facilitate sealing within turbines |
| CN104196636A (en) * | 2014-07-31 | 2014-12-10 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Gas turbine with sealed structure |
| CN104234840A (en) * | 2014-09-03 | 2014-12-24 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Sealing structure for stator ring of gas turbine |
| CN204591492U (en) * | 2015-01-30 | 2015-08-26 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of gas turbine sealing configuration |
-
2015
- 2015-01-30 CN CN201510051715.4A patent/CN104632414A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020168263A1 (en) * | 2001-04-04 | 2002-11-14 | Hans-Thomas Bolms | Seal element for sealing a gap and combustion turbine having a seal element |
| US20040223844A1 (en) * | 2003-05-07 | 2004-11-11 | Farrell Alison Carol | Method and apparatus to facilitate sealing within turbines |
| CN104196636A (en) * | 2014-07-31 | 2014-12-10 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Gas turbine with sealed structure |
| CN104234840A (en) * | 2014-09-03 | 2014-12-24 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Sealing structure for stator ring of gas turbine |
| CN204591492U (en) * | 2015-01-30 | 2015-08-26 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of gas turbine sealing configuration |
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Application publication date: 20150520 |
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