CN204591364U - A kind of gas turbine self centering seal structure - Google Patents
A kind of gas turbine self centering seal structure Download PDFInfo
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- CN204591364U CN204591364U CN201520069146.1U CN201520069146U CN204591364U CN 204591364 U CN204591364 U CN 204591364U CN 201520069146 U CN201520069146 U CN 201520069146U CN 204591364 U CN204591364 U CN 204591364U
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- sealing
- gas turbine
- seal structure
- rotor
- self centering
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Abstract
The utility model relates to gas turbine design manufacturing technology field, particularly relates to a kind of gas turbine self centering seal structure.The first Sealing on it can slide up and down with described second Sealing and is connected, described second Sealing and described rotor are fitted and are not compressed, second Sealing is mainly with the contact of dish chamber air, and do not contact completely between the first Sealing with the second Sealing, but be connected by joint, effectively reduce the heat that stator transmits on the second Sealing, therefore the temperature difference under each operating mode between the second Sealing and rotor is less, can make between the second Sealing and rotor, to fit or only reserve less seal clearance can normally work, solve traditional sealing configuration and need reserved larger seal clearance, and cause sealing effect and the low problem of the unit operation thermal efficiency, sealing effect can be improved, improve the Security of unit simultaneously.
Description
Technical field
The utility model relates to gas turbine design manufacturing technology field, particularly relates to a kind of gas turbine self centering seal structure.
Background technique
At present, as shown in Figure 1, there is the sealing between a large amount of rotors 2 ' and stator 1 ' in gas turbine, its sealing effect directly can have influence on the overall thermal cycle efficiency of combustion engine and the safe operation of unit; Simultaneously because gas turbine is at high temperature-end part, turn stator ' often to there is cooling air between parts, between high-temperature fuel gas and parts simultaneously, what therefore need to seal turns stator ' often there is the larger temperature difference between parts, the temperature difference of ' be connected the temperature of Sealing 10 and rotor ' is comparatively large with stator, under working state and normal temperature state lower seal 10 and rotor ' between gap change very greatly.
Prior art calculates mainly through gap design and cold and hot, ensures that seal clearance 9 ' is unlikely to touch mill under bias and each operating mode thermal deformation conditions; Owing to preferentially will ensure unit safety, take into account each working condition lower seal gap 9 ' and be all unlikely to touch mill, therefore under cold conditions assembling and other operating modes, gap is often unsatisfactory, and then have impact on the operating thermal efficiency of sealing effect and unit
Therefore, for above deficiency, need the gas turbine self centering seal structure providing a kind of sealing effect good.
Model utility content
(1) technical problem that will solve
The technical problems to be solved in the utility model is: traditional gas turbine due to needs take into account each working condition under rotating-static clearance be all unlikely to touch mill, thus the seal clearance of stator and rotor is comparatively large, and sealing effect is bad, causes the operating thermal efficiency of unit to reduce.
(2) technological scheme
In order to solve the problems of the technologies described above, the utility model provides a kind of gas turbine self centering seal structure, the second Sealing comprising stator, rotor, the first Sealing and coordinate with the first Sealing, described first Sealing is connected with the lower end of stator, described second Sealing can slide up and down and is connected to the below of described first Sealing, and described second Sealing and described rotor are fitted and do not compressed.
Wherein, described second Sealing comprises the sealed department of fitting with described rotor and the joint coordinated with the first Sealing, and described joint offers elongate holes, and screw realizes the connection of the second Sealing and the first Sealing through described elongate holes.
Wherein, also elastic component is provided with between described screw and described joint.
Wherein, described elastic component is butterfly resilient pad.
Wherein, described elastic component is spring.
Wherein, also thermal insulating pad is provided with between described first Sealing and described joint.
Wherein, described first Sealing and joint all in the form of a ring, are also connected by least three pins be circumferentially arranged between described joint and the first Sealing.
Wherein, described first Sealing is provided with long strip pin-and-hole, the radial line of described pin-and-hole points to the center line of gas turbine unit, and described second Sealing is provided with cylindrical pin hole, and described pin coordinates with described long strip pin-and-hole and described cylindrical pin hole.
Wherein, described pin comprises the cylindrical section coordinated with cylindrical pin hole and the plat mill section coordinated with long strip pin-and-hole
(3) beneficial effect
Technique scheme tool of the present utility model has the following advantages: the utility model provides a kind of gas turbine self centering seal structure, the first Sealing on it is connected with the lower end of stator, described second Sealing is positioned at the downside of the first Sealing, and can slide up and down with described second Sealing and be connected, described second Sealing and described rotor are fitted and are not compressed.Sealing and rotor are fitted and do not compress, second Sealing is mainly with the contact of dish chamber air, and do not contact completely between the first Sealing with the second Sealing, but be connected (between the first Sealing and the second Sealing, can thermal insulating pad be set) by joint, effectively reduce the heat that stator transmits on the second Sealing, therefore the temperature difference under each operating mode between the second Sealing and rotor reduces, can make between the second Sealing and rotor, to fit or only reserve less seal clearance can normally work, solve traditional sealing configuration and need reserved larger seal clearance, and cause sealing effect and the low problem of the unit operation thermal efficiency, sealing effect can be improved, improve the Security of unit simultaneously.
Accompanying drawing explanation
The advantage of the above-mentioned and/or additional aspect of the utility model 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 and rotor in gas turbine in prior art;
Fig. 2 is the schematic diagram of gas turbine self centering seal structure described in the utility model embodiment;
Fig. 3 is the structural representation of elongate holes and screw fit in Fig. 2;
Fig. 4 is the structural representation that the first Sealing coordinates with joint;
Fig. 5 is the structural representation of Fig. 4 pin;
Fig. 6 is the structural representation that pin coordinates with long strip pin-and-hole;
Fig. 7 is the A portion structure for amplifying schematic diagram of Fig. 2.
Corresponding relation wherein in Fig. 1 and Fig. 2 between reference character and component names is:
1 ', stator, 2 ', rotor, 9 ', seal clearance, 10, Sealing, 1, stator, 2, rotor, the 3, first Sealing, 31, long strip pin-and-hole, the 4, second Sealing, 41, sealed department, 42, joint, 421, elongate holes, 5, screw, 6, butterfly resilient pad, 7, pin, 71, cylindrical section, 72, plat mill section, 8, pelvic cavity, 9, seal clearance.
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 utility model embodiment, technological scheme and advantage clearly, below in conjunction with the accompanying drawing in the utility model embodiment, technological scheme in the utility model embodiment is clearly and completely described, obviously, described embodiment is a part of embodiment of the present utility model, instead of whole embodiments.Based on the embodiment in the utility model, 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 the utility model protection.
As shown in Figure 2, the utility model provides a kind of gas turbine self centering seal structure, the second Sealing 4 comprising stator 1, rotor 2, first Sealing 3 and coordinate with the first Sealing 3, described first Sealing 3 is connected with the lower end of stator 1, described second Sealing 4 can slide up and down and is connected to the below of described first Sealing 3, and described second Sealing 4 is fitted with described rotor 2 and do not compressed.Sealing and rotor 2 are fitted and do not compress, second Sealing is mainly with air contact in dish chamber 8, and the first Sealing 3 does not contact completely with between the second Sealing, but be connected by joint, effectively reduce the heat that stator 1 transmits on the second Sealing, therefore the temperature difference under each operating mode between the second Sealing and rotor 2 reduces, can make to fit between the second Sealing and rotor 2 or only reserve very little gap, solve traditional sealing configuration and need reserved larger seal clearance 9, and cause sealing effect and the low problem of the unit operation thermal efficiency, sealing effect can be improved, improve the Security of unit simultaneously.
Preferably, as shown in Figure 7, described second Sealing comprises the sealed department of fitting with described rotor 2 and the joint coordinated with the first Sealing 3, described joint offers elongate holes 421, as shown in Figure 3, second Sealing to be can slide up and down with the first Sealing 3 by the cooperation of elongate holes 421 and screw 5 and is connected, the circumference of the second Sealing is provided with multiple screw 5, connected by the screw elasticity of elongate holes between first Sealing and the second Sealing and felt relieved by pin simultaneously, therefore be free to mobile between the first Sealing and the second Sealing, play the effect of heat centering, solve traditional sealing configuration when thermal distortion, stator part expands downwards, rotor part changes excessive problem in gap when upwards expanding and then cause hot shaping, because the temperature difference between the second Sealing and rotor 2 is less, therefore the distance upwards expanded of the two is almost identical, even if at different temperatures, the seal clearance 9 between the two also remains unchanged, and stator 1 is when driving the first Sealing 3 to move downward, joint and screw 5 produce relative sliding, thus make to produce between the first Sealing 3 and the second Sealing relative sliding there will not be the first Sealing 3 promote the second clips move down thus cause seal clearance 9 to diminish, even mutual extrusion friction between the first Sealing 3 and rotor 2, and cause the problem of rotor 2 or the second sealing part abrasion, preferably, also elastic component is provided with between described screw 5 and described joint, further, elastic component is butterfly resilient pad 6 as described in Figure 7, the butterfly resilient pad 6 of at least one is there is between screw 5 and the second Sealing, by the quantity of adjustment butterfly resilient pad 61, the assembling impacting force between screw 5 and the second Sealing can be controlled preferably, while playing the effect of axially fastening, frictional force between control second Sealing that can be good and stator 1, ensure in thermal distortion situation, be free to slide diametrically between two parts.
It should be noted that, elongate holes 421 also can be opened on the first Sealing 3, and equally can realize the object of the application, its aim does not depart from design philosophy of the present utility model yet, should belong to protection domain of the present utility model.
Certainly, described Sealing also can be after common resilient pad or spring, and equally can realize the object of adjustment assembly pressure in the application, its aim does not depart from design philosophy of the present utility model yet, should belong to protection domain of the present utility model.
Preferably, thermal insulating pad (not shown) is also provided with between 4 between described first Sealing 3 and the second Sealing, the heat that stator 1 transmits to the first Sealing 3 can be reduced so better, and then reduce the heat transmitted to the second Sealing, the temperature difference between the second Sealing and rotor 2 can be reduced better, thus ensure that seal clearance 9 therebetween remains unchanged at different temperatures.
Further, also connected (as shown in Figure 4) by least three pins 7 be circumferentially arranged between described joint and the second Sealing.Wherein, described first Sealing 3 is provided with long strip pin-and-hole 31 (not shown), the radial line of described pin-and-hole points to the center line of gas turbine unit, as shown in Figure 5 and Figure 6, described pin 7 comprises the cylindrical section 71 coordinated with the common cylinder shaped pin hole on the second Sealing linkage section and the plat mill section 72 that can slide in long strip pin-and-hole 31, plat mill section 72 coordinates with the runway nibs that the first Sealing 3 is opened, can be free to slide diametrically, because the radial line of long strip pin-and-hole 31 points to gas turbine unit center, when therefore can ensure that pin 7 slides in long strip pin-and-hole 31, concentric relation between second Sealing and the first Sealing 3 remains unchanged.
It should be noted that; also calculating in above-described embodiment can be arrange long strip pin-and-hole on the second Sealing; first Sealing arranges common cylinder shaped pin hole; equally also can realize the object of the application; its aim does not depart from design philosophy of the present utility model, should belong to protection domain of the present utility model.
In sum, the gas turbine self centering seal structure that the utility model provides, the first Sealing on it is connected with the lower end of stator, described second Sealing is positioned at the downside of the first Sealing, and can slide up and down with described second Sealing and be connected, described second Sealing and described rotor are fitted and are not compressed.Sealing and rotor are fitted and do not compress, second Sealing is mainly with the contact of dish chamber air, and do not contact completely between the first Sealing with the second Sealing, but be connected by joint, effectively reduce the heat that stator transmits on the second Sealing, therefore the temperature difference under each operating mode between the second Sealing and rotor reduces, can make to fit between the second Sealing and rotor or only reserve less seal clearance, solve traditional sealing configuration and need reserved larger seal clearance, and cause sealing effect and the low problem of the unit operation thermal efficiency, sealing effect can be improved, improve the Security of unit simultaneously, between the first Sealing and stator, adding thermal insulating pad simultaneously, the heat that stator transmits to the first Sealing and the second Sealing can reduced further, in addition, by being coordinated with long strip pin-and-hole by pin, the concentricity between the first Sealing and the second Sealing can be ensured.
Last it is noted that above embodiment is only in order to illustrate the technical solution of the utility model, be not intended to limit; Although be described in detail the utility model with reference to previous embodiment, 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 each embodiment's technological scheme of the utility model.
Claims (9)
1. a gas turbine self centering seal structure, it is characterized in that: the second Sealing (4) comprising stator (1), rotor (2), the first Sealing (3) and coordinate with the first Sealing (3), described first Sealing (3) is connected with the lower end of stator (1), described second Sealing (4) can slide up and down and is connected to the below of described first Sealing (3), and described second Sealing (4) and described rotor (2) are fitted and do not compressed.
2. gas turbine self centering seal structure according to claim 1, it is characterized in that: described second Sealing (4) comprises the sealed department (41) of fitting with described rotor (2) and the joint (42) coordinated with the first Sealing (3), described joint (42) offers elongate holes (421), screw (5) realizes the connection of the second Sealing (4) and the first Sealing (3) through described elongate holes (421).
3. gas turbine self centering seal structure according to claim 2, is characterized in that: be also provided with elastic component between described screw (5) and described joint (42).
4. gas turbine self centering seal structure according to claim 3, is characterized in that: described elastic component is butterfly resilient pad (6).
5. gas turbine self centering seal structure according to claim 3, is characterized in that: described elastic component is spring.
6. the gas turbine self centering seal structure according to claim 4 or 5, is characterized in that: be also provided with thermal insulating pad between described first Sealing (3) and described joint (42).
7. gas turbine self centering seal structure according to claim 6, it is characterized in that: described first Sealing and joint all in the form of a ring, are also connected by least three pins (7) be circumferentially arranged between described joint (42) and the first Sealing (3).
8. gas turbine self centering seal structure according to claim 7, it is characterized in that: described first Sealing (3) is provided with long strip pin-and-hole (31), the radial line of described pin-and-hole points to the center line of gas turbine unit, described second Sealing is provided with cylindrical pin hole, and described pin (7) coordinates with described long strip pin-and-hole (31) and described cylindrical pin hole.
9. gas turbine self centering seal structure according to claim 8, is characterized in that: described pin comprises the cylindrical section (71) coordinated with cylindrical pin hole and the plat mill section (72) coordinated with long strip pin-and-hole (31).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520069146.1U CN204591364U (en) | 2015-01-30 | 2015-01-30 | A kind of gas turbine self centering seal structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520069146.1U CN204591364U (en) | 2015-01-30 | 2015-01-30 | A kind of gas turbine self centering seal structure |
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| Publication Number | Publication Date |
|---|---|
| CN204591364U true CN204591364U (en) | 2015-08-26 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520069146.1U Active CN204591364U (en) | 2015-01-30 | 2015-01-30 | A kind of gas turbine self centering seal structure |
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| CN (1) | CN204591364U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US12046966B2 (en) * | 2019-11-11 | 2024-07-23 | Infinitum Electric Inc. | Axial field rotary energy device with PCB stator with thermal expansion capability |
-
2015
- 2015-01-30 CN CN201520069146.1U patent/CN204591364U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US12046966B2 (en) * | 2019-11-11 | 2024-07-23 | Infinitum Electric Inc. | Axial field rotary energy device with PCB stator with thermal expansion capability |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Gas turbine automatic centering seal structure Effective date of registration: 20161104 Granted publication date: 20150826 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
|
| PLDC | Enforcement, change and cancellation of contracts on pledge of patent right or utility model | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20191211 Granted publication date: 20150826 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |