CN204783278U - Gas turbine turbine and sealed tooth thereof - Google Patents
Gas turbine turbine and sealed tooth thereof Download PDFInfo
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- CN204783278U CN204783278U CN201520230971.5U CN201520230971U CN204783278U CN 204783278 U CN204783278 U CN 204783278U CN 201520230971 U CN201520230971 U CN 201520230971U CN 204783278 U CN204783278 U CN 204783278U
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Abstract
The utility model relates to a gas turbine mechanical structure design technical field provides a gas turbine turbine and sealed tooth thereof. Should include active section and the construction section that interconnects by sealed tooth, the wing that stretches out of active section and rotor rim plate matches in order to form high pressure disk chamber and low pressure disk chamber, be provided with on quiet leaf sealing ring with construction section matched with mounting groove, the construction section passes through the mounting groove with quiet leaf sealing ring is connected. The utility model discloses a gas turbine turbine seals the tooth, and its simple structure, installation and dismantlement are convenient. Its during operation disappearance seal failure's the condition can be guaranteed through the axial dimensions who adjusts sealed tooth, in addition, damage the back at sealed tooth, only need with the ring packing tooth change can, and need not to change quiet leaf sealing ring, solved high, the cycle length scheduling problem of the sealed tooth replacement cost of traditional turbine, guarantee that gas turbine is reliably, work steadily.
Description
Technical field
The utility model relates to gas turbine mechanical structure-design technique field, particularly relates to a kind of gas turbine turbine and sealing tooth thereof.
Background technique
During gas turbine work, turbine stator blade 1 directly contacts with high-temperature fuel gas with turbine rotor vane, and turbine rotor vane is arranged on rotor disk, and when this causes work, the temperature of rotor disk 3 is higher.Because rotor disk 3 is high-speed rotary turntable, effectively reduce its temperature and not only concern its working life and working efficiency, also directly affect the safe operation of unit.Therefore, cooled gas need be introduced from other positions of combustion engine to cool rotor disk 3.Conventional cooling setting type passes into cooled gas from turbine stator blade 1 upper end, after flowing out, cools corresponding rotor disk 3 from the stator blade seal ring 2 of turbine stator blade 1 lower end.But be subject to the structure influence of rotor disk 3, cooled gas directly cannot arrive the packing place of rotor disk 3.
In view of this, prior art proposes a kind of gas turbine turbine structure, refers to Fig. 1, and on rotor disk, the wing 4 is stretched out in 3 settings, and stator blade seal ring 2 processes sealing tooth 5; Sealing tooth 5 and rotor disk 3 to stretch out the wing 4 directly relative, between rotor disk and stator, form high platen chamber 10 and low platen chamber 6, thus realization cools to the position that cold air cannot directly arrive.Wherein, maintaining the pressure reduction in high platen chamber 10 and low platen chamber 6, is the key of wheel disc effective cooling.
But prior art Problems existing is, operationally, because rotor is different by thermogenetic axial expansion amount with stator, the axial position of sealing tooth 5 can move backward along turbine spindle.Because axial position when installing by stator blade seal ring 2 limits, the axial length stretching out the wing 4 of rotor disk 3 can not be long, therefore occur sealing tooth 5 cannot with rotor disk 3 stretch out the wing 4 directly relative time, do not reach sealing effect.In addition, due to sealing tooth 5 be directly processing on stator blade seal ring 2, after rotor radial is beated and caused damage to sealing tooth 5, directly cannot change sealing tooth 5, stator blade seal ring 2 can only be changed, cause the prolongation of combustion engine service cycle and the increase of cost.
Model utility content
(1) technical problem that will solve
The technical problems to be solved in the utility model is just to provide a kind of gas turbine turbine and sealing tooth thereof, the problems such as industry gas turbine turbine seal tooth functional reliability is not high to solve, inconvenient maintenance, improve gas turbine Turbine section functional reliability, stability and life-span.
(2) technological scheme
In order to solve the problems of the technologies described above, the utility model provides a kind of gas turbine turbine seal tooth, comprises the active section and construction section that are connected to each other; Described active section and construction section are solid of rotation and coaxially arrange; The wing that stretches out of described active section and rotor disk matches to form high platen chamber and low platen chamber; Stator blade seal ring is provided with the mounting groove matched with described construction section; Described construction section is connected with described stator blade seal ring by described mounting groove.
Preferably, described active section and described construction section are integral one-step molding.
Preferably, described active section is connected removably with described construction section.
Preferably, described construction section and mounting groove are L-type.
Preferably, described construction section and mounting groove T-shaped.
The utility model also provides a kind of gas turbine turbine, comprises gas turbine turbine seal tooth described in the utility model.
(3) beneficial effect
The technical solution of the utility model has the following advantages: gas turbine turbine seal tooth of the present utility model, and its structure is simple, installation and removal are convenient.The situation of seal failure is there is not when can ensure its work by regulating the axial dimension of sealing tooth; In addition, after sealing tooth damages, only the sealing tooth of annular need be changed, and without the need to changing stator blade seal ring, solve the problems such as traditional turbine seal tooth replacement cost is high, the cycle is long, ensure that gas turbine reliably, stably works.
Accompanying drawing explanation
In order to be illustrated more clearly in the utility model embodiment or technological scheme of the prior art, be briefly described to the accompanying drawing used required in embodiment or description of the prior art below, apparently, accompanying drawing in the following describes is only embodiments more of the present utility model, for those of ordinary skill in the art, under the prerequisite not paying creative work, other accompanying drawing can also be obtained according to these accompanying drawings.
Fig. 1 is the working state schematic representation of the gas turbine turbine seal tooth of prior art;
Fig. 2 is the working state schematic representation of gas turbine turbine seal tooth of the present utility model;
Fig. 3 is the assembling schematic diagram comprising the gas turbine turbine seal tooth of L-type construction section of the present utility model;
Fig. 4 is the assembling schematic diagram comprising the gas turbine turbine seal tooth of T-shaped construction section of the present utility model;
In figure: 1, turbine stator blade; 2, stator blade seal ring; 3, rotor disk; 4, the wing is stretched out; 5, tooth is sealed; 6, low platen chamber; 7, mounting groove; 8, construction section; 9, active section; 10, high platen chamber.
Embodiment
Below in conjunction with drawings and Examples, mode of execution of the present utility model is described in further detail.Following examples for illustration of the utility model, but can not be used for limiting scope of the present utility model.
In description of the present utility model, it should be noted that, term " on ", the orientation of the instruction such as D score or position relationship be based on orientation shown in the drawings or position relationship, only the utility model and simplified characterization for convenience of description, instead of the device of instruction or hint indication or element must have specific orientation, with specific azimuth configuration and operation, therefore can not be interpreted as restriction of the present utility model.
First it should be noted that, the axial direction of the active section axially referred in the present embodiment, linkage section and construction section, also i.e. direction from left to right in diagram; Radial then refer to the radial direction of active section, linkage section and construction section.In addition, although following examples accompanying drawing is only described the cross-section structure of gas turbine turbine seal tooth, the restriction of the stereochemical structure to gas turbine turbine seal tooth is not formed with this.
Refer to Fig. 2, the gas turbine turbine seal tooth 5 of the present embodiment, comprise the active section 9 and construction section 8 that are connected to each other; Described active section 9 and construction section 8 are solid of rotation and coaxially arrange; Described active section 9 and stretch out the wing 4 and match to form high platen chamber 10 and low platen chamber 6, cools rotor disk 3 respectively.Described construction section 8 is connected removably with stator blade seal ring 2.In the present embodiment, described construction section is connected with described stator blade seal ring 2 by the mounting groove 7 be arranged on stator blade seal ring 2.
Wherein, active section 9 and construction section 8 can be integral one-step molding, also can connect removably.
With sprue fuel gas flow direction for turbine spindle to, stator blade seal ring 2 is arranged on the lower end of turbine stator blade 1.Stator blade seal ring 2 offers the groove matched with construction section 8, refers to Fig. 3 and Fig. 4.In Fig. 3, construction section 8 is in L-type; Described stator blade seal ring 2 is provided with the L-type mounting groove 7 matched with described construction section 8.In Fig. 4, construction section 8 is T-shaped; Described stator blade seal ring 2 is provided with the T-shaped mounting groove 7 matched with described construction section 8.When mounted, along the circumferential direction slipped in mounting groove 7 by sealing tooth 5, realize the locking between construction section 8 and mounting groove 7, it is located and installs simple and reliable.
It is emphasized that the structure of construction section 8 and active section 9 is not by the restriction of the present embodiment, any feasible active section 9 and construction section 8 structure all should comprise in the present embodiment.In like manner, the structure of mounting groove 7 is not also by the restriction of the present embodiment.
The gas turbine turbine seal tooth 5 of the present embodiment, its structure is simple, installation and removal are convenient.The situation of seal failure is there is not when can ensure its work by regulating the axial dimension of sealing tooth 5.Further, after sealing tooth 5 damages, only sealing tooth 5 need be changed, and without the need to changing stator blade seal ring 2, solve the problems such as traditional turbine seal tooth 5 replacement cost is high, the cycle is long, ensure that gas turbine reliably, stably works.
Above mode of execution only for illustration of the utility model, but not to restriction of the present utility model.Although be described in detail the utility model with reference to embodiment, those of ordinary skill in the art is to be understood that, various combination, amendment or equivalent replacement are carried out to the technical solution of the utility model, do not depart from the spirit and scope of technical solutions of the utility model, all should be encompassed in the middle of right of the present utility model.
Claims (6)
1. a gas turbine turbine seal tooth, is characterized in that, comprises the active section and construction section that are connected to each other; Described active section and construction section are solid of rotation and coaxially arrange; The wing that stretches out of described active section and rotor disk matches to form high platen chamber and low platen chamber; Stator blade seal ring is provided with the mounting groove matched with described construction section; Described construction section is connected with described stator blade seal ring by described mounting groove.
2. gas turbine turbine seal tooth according to claim 1, is characterized in that, described active section and described construction section are integral one-step molding.
3. gas turbine turbine seal tooth according to claim 1, it is characterized in that, described active section is connected removably with described construction section.
4. gas turbine turbine seal tooth according to claim 1, it is characterized in that, described construction section and mounting groove are L-type.
5. gas turbine turbine seal tooth according to claim 1, is characterized in that, described construction section and mounting groove T-shaped.
6. a gas turbine turbine, is characterized in that, comprises the gas turbine turbine seal tooth in claim 1-5 described in any one.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520230971.5U CN204783278U (en) | 2015-04-16 | 2015-04-16 | Gas turbine turbine and sealed tooth thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520230971.5U CN204783278U (en) | 2015-04-16 | 2015-04-16 | Gas turbine turbine and sealed tooth thereof |
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| Publication Number | Publication Date |
|---|---|
| CN204783278U true CN204783278U (en) | 2015-11-18 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520230971.5U Active CN204783278U (en) | 2015-04-16 | 2015-04-16 | Gas turbine turbine and sealed tooth thereof |
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| Country | Link |
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| CN (1) | CN204783278U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113047914A (en) * | 2021-04-22 | 2021-06-29 | 浙江燃创透平机械股份有限公司 | Sealing structure between turbine stages of gas turbine |
-
2015
- 2015-04-16 CN CN201520230971.5U patent/CN204783278U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113047914A (en) * | 2021-04-22 | 2021-06-29 | 浙江燃创透平机械股份有限公司 | Sealing structure between turbine stages of gas turbine |
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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 turbine and sealed tooth thereof Effective date of registration: 20161104 Granted publication date: 20151118 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 |
Date of cancellation: 20191211 Granted publication date: 20151118 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right |