CN204716305U - A kind of gas turbine turbine and sealing tooth thereof - Google Patents
A kind of gas turbine turbine and sealing tooth thereof Download PDFInfo
- Publication number
- CN204716305U CN204716305U CN201520231746.3U CN201520231746U CN204716305U CN 204716305 U CN204716305 U CN 204716305U CN 201520231746 U CN201520231746 U CN 201520231746U CN 204716305 U CN204716305 U CN 204716305U
- Authority
- CN
- China
- Prior art keywords
- turbine
- section
- gas turbine
- tooth
- stator blade
- 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.)
- Active
Links
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The utility model relates to gas turbine mechanical structure-design technique field, provides a kind of gas turbine turbine and sealing tooth thereof.Wherein, gas turbine turbine seal tooth comprises the active section, linkage section and the construction section that connect successively; Described active section, linkage 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; Described construction section is connected with the mounting groove be opened on stator blade seal ring, and is fixed on described stator blade seal ring by locating piece.Gas turbine turbine seal tooth of the present utility model, 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.
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 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 is higher.Because rotor disk 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.Conventional cooling setting type passes into cooled gas from turbine stator blade upper end, after flowing out, cools corresponding rotor disk from the stator blade seal ring of turbine stator blade lower end.But be subject to the structure influence of rotor disk, cooled gas directly cannot arrive the packing place of rotor disk.
In view of this, prior art proposes a kind of gas turbine turbine structure, refers to Fig. 1, rotor disk 3 is arranged and stretches out the wing 4, and stator blade seal ring 2 processes sealing tooth 6; Sealing tooth 6 and rotor disk 3 to stretch out the wing 4 directly relative, between rotor disk 3 and stator, form high platen chamber 9 and low platen chamber 10, thus realization cools to the position that cold air cannot directly arrive.Wherein, maintaining the pressure reduction in high platen chamber 9 and low platen chamber 10, 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 6 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 6 cannot with rotor disk 3 stretch out the wing 4 directly relative time, do not reach sealing effect.In addition, due to sealing tooth 6 be directly processing on stator blade seal ring 2, after rotor radial is beated and caused damage to sealing tooth 6, directly cannot change sealing tooth 6, 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, linkage section and the construction section that connect successively; Described active section, linkage 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; Described construction section is connected with the mounting groove be opened on stator blade seal ring, and is fixed on described stator blade seal ring by locating piece.
Preferably, the longitudinal section entirety of the described active section, linkage section and the construction section that connect successively is in class Z-type.
Preferably, along on the axial direction of described active section, described active section stretches out the end face of described stator blade seal ring.
Preferably, along on the axial direction of described active section, described active section is positioned at inside the end face of described stator blade seal ring.
Preferably, described mounting groove is rectangular; Described construction section is fixed in the described mounting groove of rectangle by described locating piece.
Preferably, described locating piece is positioning block, positioning screwn or locating stud.
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 cross-sectional schematic of gas turbine turbine seal tooth of the present utility model;
Fig. 4 is the first rigging position schematic diagram of gas turbine turbine seal tooth of the present utility model;
Fig. 5 is the second rigging position schematic diagram of gas turbine turbine seal tooth 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, linkage section; 6, tooth is sealed; 7, positioning block; 8, mounting groove; 9, high platen chamber; 10, low platen chamber; 11, active section; 12, construction section.
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 11 axially referred in the present embodiment, linkage section 5 and construction section 12, also i.e. direction from left to right in diagram; Radial then refer to the radial direction of active section 11, linkage section 5 and construction section 12.In addition, although following examples accompanying drawing is only described the cross-section structure of gas turbine turbine seal tooth 6, the restriction of the stereochemical structure to gas turbine turbine seal tooth 6 is not formed with this.
Refer to Fig. 2, gas turbine turbine seal tooth 6 of the present utility model, comprise the active section 11, linkage section 5 and the construction section 12 that connect successively; Described active section 11, linkage section 5 and construction section 12 are solid of rotation and coaxially arrange; The wing 4 that stretches out of described active section 11 and rotor disk 3 matches to form high platen chamber 9 and low platen chamber 10; Described construction section 12 is connected with the mounting groove 8 be opened on stator blade seal ring 2, and is fixed on described stator blade seal ring 2 by locating piece.
Generally speaking, turbine stator blade 1 lower end is provided with stator blade seal ring 2, stator blade seal ring 2 is provided with sealing tooth 6, radially stretch out the wing 4 with wheel disc relative for the active section 11 of sealing tooth 6, make to define high platen chamber 9 and low platen chamber 10 between turbine stator blade 1 and rotor disk 3, for cooled rotor wheel disc 3 root.
In the present embodiment, locating piece can regioselective block 7, positioning screwn, locating stud or other known elements.Carry out by positioning block 7 installation sealing tooth 6 in the present embodiment, specifically sealing tooth 6 is radially put into mounting groove 8, after being installed by positioning block 7, rush riveting positioning block 7 with locking, it is installed and locates simple and reliable.Construction section 12 is fixed on after in mounting groove 8 by locating piece, preferably ensures that linkage section 5 exists diametrically with stator blade seal ring 2 and contacts, thus ensure the installation stability of sealing tooth 6 further.
Wherein, mounting groove 8 is rectangular; Described construction section 12 is fixed in the described mounting groove 8 of rectangle by described locating piece.Certainly, mounting groove 8 can also be any structural type being convenient to the dismounting sealing tooth 6.
The structure of the gas turbine turbine seal tooth 6 of the present embodiment, refers to Fig. 3, and the described active section 11 connected successively, linkage section 5 and the longitudinal section entirety of installing are class Z-type.When linkage section 5 does not stretch out the end face of stator blade seal ring 2, then now active section 11 is positioned at inside the end face of described stator blade seal ring 2, certainly also comprises active section 11 situation concordant with the end face of stator blade seal ring 2, specifically refers to Fig. 4.Wherein, because mounting groove 8 position is fixed, when sealing tooth 6 axial dimension and not meeting the demands, the length of replaceable axial linkage section 5 meets the demands.Now along on the axial direction of described active section 11, linkage section 5 active section 11 is stretched out the end face of described stator blade seal ring 2, and close toward the inwall of rotor disk 3, specifically refer to Fig. 5.When structure allows, the second situation, when also namely linkage section 5 stretches out the end face of stator blade seal ring 2, more can ensure sealing tooth 6 and stretch out the wing 4 not depart from, ensure sealing effect.
The gas turbine turbine seal tooth 6 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 6; In addition, after sealing tooth 6 damages, only the sealing tooth 6 of annular need be changed, and without the need to changing stator blade seal ring 2, solve the problems such as traditional turbine seal tooth 6 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 (7)
1. a gas turbine turbine seal tooth, is characterized in that, comprises the active section, linkage section and the construction section that connect successively; Described active section, linkage 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; Described construction section is connected with the mounting groove be opened on stator blade seal ring, and is fixed on described stator blade seal ring by locating piece.
2. gas turbine turbine seal tooth according to claim 1, is characterized in that, the longitudinal section entirety of the described active section, linkage section and the construction section that connect successively is in class Z-type.
3. gas turbine turbine seal tooth according to claim 1, is characterized in that, along on the axial direction of described active section, described active section stretches out the end face of described stator blade seal ring.
4. gas turbine turbine seal tooth according to claim 1, is characterized in that, along on the axial direction of described active section, described active section is positioned at inside the end face of described stator blade seal ring.
5. gas turbine turbine seal tooth according to claim 1, it is characterized in that, described mounting groove is rectangular; Described construction section is fixed in the described mounting groove of rectangle by described locating piece.
6. according to the gas turbine turbine seal tooth in claim 1-5 described in any one, it is characterized in that, described locating piece is positioning block, positioning screwn or locating stud.
7. a gas turbine turbine, is characterized in that, comprises the gas turbine turbine seal tooth in claim 1-6 described in any one.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520231746.3U CN204716305U (en) | 2015-04-16 | 2015-04-16 | A kind of gas turbine turbine and sealing tooth thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520231746.3U CN204716305U (en) | 2015-04-16 | 2015-04-16 | A kind of gas turbine turbine and sealing tooth thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204716305U true CN204716305U (en) | 2015-10-21 |
Family
ID=54315308
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520231746.3U Active CN204716305U (en) | 2015-04-16 | 2015-04-16 | A kind of gas turbine turbine and sealing tooth thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204716305U (en) |
-
2015
- 2015-04-16 CN CN201520231746.3U patent/CN204716305U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109139122B (en) | Internal cooling system of 2-stage turbine rotor of gas turbine | |
| US20120195746A1 (en) | Turbomachine service assembly | |
| CN204663669U (en) | Gas turbine rotor axial thrust balancing bleed structure | |
| CN112610335B (en) | Sealing structure for turbine disk cavity of gas turbine | |
| CN104595926A (en) | Integral combustion chamber for heat-channel components | |
| CN204716307U (en) | Air seal structure between gas turbine turbine wheel disc and turbine stator blade | |
| JP2016061294A (en) | Sealing arrangement at interface between combustor and turbine of gas turbine, and gas turbine with such sealing arrangement | |
| CN201144714Y (en) | Disc draft type capacity-adjustable TRT | |
| CN113653539B (en) | Turbine rotor arrangement system | |
| CN204783278U (en) | Gas turbine turbine and sealed tooth thereof | |
| CN204716305U (en) | A kind of gas turbine turbine and sealing tooth thereof | |
| CN109519225B (en) | Centripetal turbine device with vibration damping and sealing structure | |
| JP6475239B2 (en) | Cover of a turbomachine centrifugal compressor that can be securely connected through its downstream side near the upstream edge, and a turbomachine comprising this cover | |
| CN204402578U (en) | A kind of gas turbine turbine stator blade elastic sealing structure | |
| CN104074795B (en) | A kind of high speed shaft seal structure | |
| CN104696031A (en) | Steam turbine and methods of assembling the same | |
| CN106271378B (en) | Movable vane piece assembly method on turbine rotor | |
| CN203614599U (en) | Pulley bearing box | |
| CN204783122U (en) | Gas turbine turbine flow control structure | |
| CN204984606U (en) | Air separation ring and gas turbine | |
| CN202228133U (en) | Steam turbine nozzle | |
| CN208396752U (en) | A kind of combustion engine turbine wheel disc and air cooled guide apparatus structure | |
| RU2614909C1 (en) | Cooled high-pressure turbine | |
| CN210483821U (en) | Casing cooling and sealing structure for gas turbine | |
| CN204593459U (en) | A kind of combustion turbine transitory section structure and gas turbine |
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: 20151021 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: 20151021 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |