CN204436482U - A kind of gas turbine turbine stator blade position structure - Google Patents
A kind of gas turbine turbine stator blade position structure Download PDFInfo
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- CN204436482U CN204436482U CN201420818496.9U CN201420818496U CN204436482U CN 204436482 U CN204436482 U CN 204436482U CN 201420818496 U CN201420818496 U CN 201420818496U CN 204436482 U CN204436482 U CN 204436482U
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Abstract
The utility model relates to gas turbine technology field, discloses a kind of gas turbine turbine stator blade position structure.This gas turbine turbine stator blade position structure comprises: turbine holds ring, one-level stator blade and rear locating stud; The circumference that described second prelocalization pin and rear locating stud hold ring along described turbine is respectively arranged at described turbine and holds on ring, described one-level stator blade is arranged between described second prelocalization pin and rear locating stud, and the axis that described second prelocalization pin holds ring along described turbine is removable installed in the top that ring held by described turbine.In the gas turbine turbine stator blade position structure that the utility model provides, the second prelocalization pin can hold the axial dismounting of ring along turbine, compare with traditional gas turbine turbine stator blade position structure, eliminate the cover plate of radial peg, bolt and locking device, dismounting one-level stator blade is convenient and structure is simple.
Description
Technical field
The utility model relates to gas turbine technology field, particularly relates to a kind of gas turbine turbine stator blade position structure, and particularly one is removed conveniently and structure simple gas turbine turbine stator blade position structure.
Background technique
Current heavy duty gas turbine turbine section cylinder many employings double shell structure, outer shell is the load bearing frame of unit, and it carries the weight of unit, compressed-air actuated internal pressure and other active force; Turbine is held ring and is played inner casing effect, adopts the good material of heat resistance, and has air to cool, be mainly used in holding heat.Discord contacts fuel gas turbine hold ring, second cylinder structure in employing, horizontal flange with Bolt Connection integrally.Hold on ring at turbine and heat insulation loop and stator blade are housed, the cooling air hole that cooling-air is held on ring by turbine flows into, to cool stator blade.
The operating conditions of one-level stator blade is very severe, at unit operation with when safeguarding, is the check object of emphasis, traditional gas turbine turbine stator blade position structure holds ring, it is processed with some circular grooves, heat insulation loop adopts sector structure, and the circular groove held on ring along turbine during assembling slips into successively.Turbine is held the circumference that ring 1 holds ring 1 along turbine and is processed with some first prelocalization pins 7 and rear locating stud 8 as shown in Figure 4, specifies that the left and right directions in Fig. 4 is circumference.One-level stator blade 2, between the first prelocalization pin 7 and rear locating stud 8, then fixes the first prelocalization pin 7 and rear locating stud 8 with cover plate and bolt, and additional necessarily loosens measure.The installation of the first prelocalization pin 7 and rear locating stud 8 is the circumferential dismounting of holding ring 1 along whole turbine, first need remove first cylinder of turbine cylinder during dismounting, removes inconvenient.Also will by the cover plate of each locating stud and bolt dismounting one time.Except indivedual gas turbine, one-level stator blade all takes above-mentioned assembling form, and therefore dismounting one-level stator blade removes inconvenience and complex structure.
In view of the defect of above-mentioned prior art, need to provide a kind of and remove conveniently and structure simple gas turbine turbine stator blade position structure.
Model utility content
(1) technical problem that will solve
The technical problems to be solved in the utility model is that existing gas turbine turbine stator blade position structure holds ring, it is processed with some circular grooves, and heat insulation loop adopts sector structure, and the circular groove held on ring along turbine during assembling slips into successively.Turbine is held the circumference that ring holds ring along turbine and is processed with some first prelocalization pins and rear locating stud, one-level stator blade is between the first prelocalization pin and rear locating stud, then fix the first prelocalization pin and rear locating stud with cover plate and bolt, and additional necessarily loosen measure.The installation of the first prelocalization pin and rear locating stud is the circumferential dismounting of holding ring along whole turbine, first need remove first cylinder of turbine cylinder during dismounting, removes inconvenient.Also will by the cover plate of each locating stud and bolt dismounting one time.Except indivedual gas turbine, one-level stator blade all takes above-mentioned assembling form, and therefore dismounting one-level stator blade removes inconvenience and baroque problem.
(2) technological scheme
In order to solve the problems of the technologies described above, the utility model provides a kind of gas turbine turbine stator blade position structure.This gas turbine turbine stator blade position structure comprises: turbine holds ring, one-level stator blade and rear locating stud; The circumference that described second prelocalization pin and rear locating stud hold ring along described turbine is respectively arranged at described turbine and holds on ring, described one-level stator blade is arranged between described second prelocalization pin and rear locating stud, and the axis that described second prelocalization pin holds ring along described turbine is removable installed in the top that ring held by described turbine.
Wherein, also comprise hold ring along described turbine be axially set in the fixed block that the top of ring held by described turbine, described fixed block is fixedly connected with the second prelocalization pin.
Wherein, described fixed block is prelocalization pin bolt.
Wherein, also comprise the axis of holding ring along described turbine and be removable installed in the trim ring that the top of ring held by described turbine.
Wherein, the trim ring bolt be axially set on described trim ring holding ring along described turbine is also comprised.
Wherein, the material of described trim ring is refractory alloy.
Wherein, described one-level stator blade adopts sector structure.
(3) beneficial effect
Technique scheme tool of the present utility model has the following advantages: the circumference that in the gas turbine turbine stator blade position structure that the utility model provides, the second prelocalization pin and rear locating stud hold ring along turbine is respectively arranged at turbine and holds on ring, one-level stator blade is arranged between the second prelocalization pin and rear locating stud, and the axis that the second prelocalization pin holds ring along turbine is removable installed in the top that ring held by turbine.In the gas turbine turbine stator blade position structure that the utility model provides, the second prelocalization pin can hold the axial dismounting of ring along turbine, compare with traditional gas turbine turbine stator blade position structure, eliminate the cover plate of radial peg, bolt and locking device, dismounting one-level stator blade is convenient and structure is simple.
Accompanying drawing explanation
Fig. 1 is the structural representation of the utility model embodiment gas turbine turbine stator blade position structure;
Fig. 2 is the close-up schematic view of the utility model embodiment gas turbine turbine stator blade position structure;
Fig. 3 is the structural representation that in the utility model embodiment gas turbine turbine stator blade position structure, turbine holds ring, one-level stator blade and trim ring;
Fig. 4 is the structural representation that in the utility model background technique gas turbine turbine stator blade position structure, turbine holds ring and one-level stator blade.
In figure: 1: ring held by turbine; 2: one-level stator blade; 3: trim ring bolt; 4: trim ring; 5: the second prelocalization pins; 6: prelocalization pin bolt; 7: the first prelocalization pins; 8: rear locating stud.
Embodiment
In description of the present utility model, except as otherwise noted, the implication of " multiple " is two or more; Term " on ", D score, "left", "right", " interior ", the orientation of the instruction such as " outward " 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 machine 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.
In description of the present utility model, 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.For the ordinary skill in the art, concrete condition the concrete meaning of above-mentioned term in the utility model can be understood.
Below in conjunction with drawings and Examples, embodiment of the present utility model is described in further detail.Following examples for illustration of the utility model, but are not used for limiting scope of the present utility model.
As shown in Figure 1 to Figure 3, the gas turbine turbine stator blade position structure that the utility model embodiment provides comprises: turbine holds ring 1, one-level stator blade 2 and rear locating stud 8; One-level stator blade 2 adopts sector structure.The circumference that second prelocalization pin 5 and rear locating stud 8 hold ring 1 along turbine is respectively arranged at turbine and holds on ring 1, one-level stator blade 2 is arranged between the second prelocalization pin 5 and rear locating stud 8, and the axis that the second prelocalization pin 5 holds ring 1 along turbine is removable installed in the top that ring 1 held by turbine.To specify in the utility model in Fig. 1 and Fig. 2 that circular arc direction be circumferential perpendicular to paper direction for axially.In Fig. 3 and Fig. 4, vertical direction is axially, and left and right directions is circumference.The the second prelocalization pin 5 that the invention provides one-level stator blade 2 in a kind of gas turbine turbine stator blade position structure can hold the axial dismounting of ring 1 along turbine.
In the present embodiment, the second prelocalization pin 5 and rear locating stud 8 are located for the circumference of one-level stator blade 2, second prelocalization pin 5 can hold the axial dismounting of ring 1 along turbine, by comparing with traditional gas turbine turbine stator blade position structure, eliminate the cover plate of radial peg along the circumferential dismounting that ring 1 held by turbine compared with the first prelocalization pin 7 in Fig. 4, bolt and locking device, dismounting one-level stator blade is convenient and structure is simple.
In the gas turbine turbine stator blade position structure that the present embodiment provides, also comprise hold ring 1 along turbine be axially set in the fixed block that the top of ring 1 held by described turbine, fixed block is fixedly connected with the second prelocalization pin 5, and fixed block is prelocalization pin bolt 6.Also comprise hold ring 1 along turbine be axially set in the trim ring 4 that the top of ring 1 held by turbine, the material of trim ring 4 be refractory alloy or other there is flexible material.Trim ring 4 is removable installed in the top that ring 1 held by turbine.Also comprise the trim ring bolt 3 be axially set on trim ring 4 holding ring 1 along turbine.By removing trim ring bolt 3 thus removing trim ring 4.Trim ring 4 and trim ring bolt 3 hold ring 1 for fixing the second prelocalization pin 5 in turbine.By this structure, can realize the dismounting vertically of turbine one-level stator blade, the second prelocalization pin 5 is pushed down and is connected into one by the axis that trim ring 4 holds ring 1 along turbine.
When the utility model gas turbine turbine stator blade position structure uses: in the gas turbine turbine stator blade position structure that the utility model provides, the second prelocalization pin 5 is located for the circumference of one-level stator blade 2, and trim ring 4 and trim ring bolt 3 hold ring 1 for fixing the second prelocalization pin 5 in turbine.By this structure, one-level stator blade 2 dismounting vertically can be realized, during assembling, second prelocalization pin 5 loads turbine vertically and holds ring 1, with trim ring bolt 3, second prelocalization pin 5 and turbine are held ring 1 to connect, second prelocalization pin 5 is pushed down by trim ring 4 vertically, holds ring 1 be connected into one finally by trim ring bolt 3 and turbine.Second prelocalization pin 5 can hold the axial dismounting of ring 1 along turbine, after removing trim ring 4, can remove the second prelocalization pin 5 axially installed easily.
In sum, the utility model has the following advantages: the circumference that in the gas turbine turbine stator blade position structure that the utility model provides, the second prelocalization pin and rear locating stud hold ring along turbine is respectively arranged at turbine and holds on ring, one-level stator blade is arranged between the second prelocalization pin and rear locating stud, and the axis that the second prelocalization pin holds ring along turbine is removable installed in the top that ring held by turbine.In the gas turbine turbine stator blade position structure that the utility model provides, the second prelocalization pin can hold the axial dismounting of ring along turbine, compare with traditional gas turbine turbine stator blade position structure, eliminate the cover plate of radial peg, bolt and locking device, dismounting one-level stator blade is convenient and structure is simple.
Further, the second prelocalization pin is pushed down and is connected into one by the axis that trim ring holds ring along turbine.
Above embodiment only in order to the technical solution of the utility model to be described, is 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 (7)
1. a gas turbine turbine stator blade position structure, is characterized in that, comprising: turbine holds ring (1), one-level stator blade (2), the second prelocalization pin (5) and rear locating stud (8); The circumference that described second prelocalization pin (5) and rear locating stud (8) hold ring (1) along described turbine is respectively arranged at described turbine and holds on ring (1), described one-level stator blade (2) is arranged between described second prelocalization pin (5) and rear locating stud (8), and the axis that described second prelocalization pin (5) holds ring (1) along described turbine is removable installed in the top that ring (1) held by described turbine.
2. gas turbine turbine stator blade position structure according to claim 1, it is characterized in that: also comprise hold ring (1) along described turbine be axially set in the fixed block that the top of ring (1) held by described turbine, described fixed block is fixedly connected with the second prelocalization pin (5).
3. gas turbine turbine stator blade position structure according to claim 2, is characterized in that: described fixed block is prelocalization pin bolt (6).
4. gas turbine turbine stator blade position structure according to claim 1, is characterized in that: also comprise the axis of holding ring (1) along described turbine and be removable installed in the trim ring (4) that the top of ring (1) held by described turbine.
5. gas turbine turbine stator blade position structure according to claim 4, is characterized in that: also comprise the trim ring bolt (3) be axially set on described trim ring (4) holding ring (1) along described turbine.
6. gas turbine turbine stator blade position structure according to claim 4, is characterized in that: the material of described trim ring (4) is refractory alloy.
7. gas turbine turbine stator blade position structure according to claim 1, is characterized in that: described one-level stator blade (2) adopts sector structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420818496.9U CN204436482U (en) | 2014-12-19 | 2014-12-19 | A kind of gas turbine turbine stator blade position structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420818496.9U CN204436482U (en) | 2014-12-19 | 2014-12-19 | A kind of gas turbine turbine stator blade position structure |
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| CN204436482U true CN204436482U (en) | 2015-07-01 |
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| CN201420818496.9U Active CN204436482U (en) | 2014-12-19 | 2014-12-19 | A kind of gas turbine turbine stator blade position structure |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109209518A (en) * | 2018-10-29 | 2019-01-15 | 江苏海事职业技术学院 | A kind of gas turbine turbine stator blade location structure |
| CN114198151A (en) * | 2021-11-25 | 2022-03-18 | 沈阳透平机械股份有限公司 | Blade top gap control method for ORC turbine unit |
| CN114542210A (en) * | 2022-03-09 | 2022-05-27 | 中国船舶重工集团公司第七0三研究所 | Positioning structure of steam turbine clapboard retaining ring |
-
2014
- 2014-12-19 CN CN201420818496.9U patent/CN204436482U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109209518A (en) * | 2018-10-29 | 2019-01-15 | 江苏海事职业技术学院 | A kind of gas turbine turbine stator blade location structure |
| CN114198151A (en) * | 2021-11-25 | 2022-03-18 | 沈阳透平机械股份有限公司 | Blade top gap control method for ORC turbine unit |
| CN114198151B (en) * | 2021-11-25 | 2024-04-30 | 沈阳透平机械股份有限公司 | ORC turbine unit blade tip clearance control method |
| CN114542210A (en) * | 2022-03-09 | 2022-05-27 | 中国船舶重工集团公司第七0三研究所 | Positioning structure of steam turbine clapboard retaining ring |
| CN114542210B (en) * | 2022-03-09 | 2023-12-05 | 中国船舶重工集团公司第七0三研究所 | Positioning structure of steam turbine partition plate retaining ring |
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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: Turbine stationary blade locating structure of gas turbine Effective date of registration: 20161104 Granted publication date: 20150701 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
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| 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: 20150701 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
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| PC01 | Cancellation of the registration of the contract for pledge of patent right |