CN104613499A - Gas turbine transition section structure - Google Patents
Gas turbine transition section structure Download PDFInfo
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- CN104613499A CN104613499A CN201410842822.4A CN201410842822A CN104613499A CN 104613499 A CN104613499 A CN 104613499A CN 201410842822 A CN201410842822 A CN 201410842822A CN 104613499 A CN104613499 A CN 104613499A
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- section structure
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- wall
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Abstract
The invention relates to the technical field of gas turbines and provides a gas turbine transition section structure. The gas turbine transition section structure comprises an upper wall and a lower wall, the outlet end of the upper wall is separated from the outlet end of the lower wall and the upper wall and the lower wall are each of a fan shape. Side sealing elements are arranged at the outer sides of the upper wall and the lower wall and enable sealing to be achieved between the two sides of the upper wall and the lower wall; first connecting pieces are fixed on the upper wall and used for fixedly connecting the upper wall and a turbine inner casing; limiting pieces are fixed on the lower wall and used for limiting the radial movement of the lower wall; the side sealing elements comprise second connecting pieces used for connecting with the turbine inner casing. The gas turbine transition section structure can effectively prevent an opening of an outlet end of a transition section from getting smaller as a result of a ratchet effect, and complexity of the structure is reduced, so that the disassembly is facilitated. In addition, as an original side wall structure prone to be deformed due to heat stress does not exist any longer, side wall warping and even fracture at the outlet end of the transition section structure caused by low-cycle fatigue as well as dropping of a sealing structure are avoided; air is prevented from entering a thermal channel directly.
Description
Technical field
The present invention relates to gas turbine technology field, particularly relate to a kind of combustion turbine transitory section structure.
Background technology
Traditional combustion turbine transitory section comprises round entrance 101 and fan-shaped outlet 102, refers to Fig. 1.The fan-shaped outlet 102 of changeover portion due to structure special, in the long-term course of work, easily there is the distortion caused by low-cycle fatigue.When starting and the operation of stopping gas turbine is repeated, fan-shaped outlet 102 thermal stress of changeover portion easily causes low-cycle fatigue.Now at fan-shaped outlet 102 place of changeover portion, thickness due to sidewall is less than the sidewall of upper and lower wall, therefore the upper and lower wall that hardness is higher is less likely to occur distortion because intensity is higher, then can cause pressure thermal deformation, i.e. so-called " ratcheting " in sidewall.
Further, when gas-turbine combustion chamber repeated priming with when stopping, the metal fatigue caused due to thermal deformation is accumulated, thus in sidewall, produces warpage even break.On this basis, the distortion at changeover portion fan-shaped outlet 102 place also easily causes coming off of hermetically-sealed construction, makes compressed air directly enter the passage of heat, causes the extra pressure loss, thus is unfavorable for the raising of thermal efficiency of gas turbine.
In view of this, urgently the structure of existing combustion turbine transitory section is improved.
Summary of the invention
(1) technical problem that will solve
The technical problem to be solved in the present invention is exactly improve the structure of the combustion turbine transitory section of prior art, solves changeover portion sidewall and holds yielding situation.
(2) technical scheme
In order to solve the problems of the technologies described above, the invention provides a kind of combustion turbine transitory section structure, it is characterized in that, comprise the port of export disconnected from each other in fan-shaped upper wall and lower wall; The arranged outside of described upper wall and lower wall has side seal, makes to realize sealing between described upper wall and the both sides of lower wall;
Described upper wall is fixed with the first connector, for being fixedly connected with turbine inner casing by described upper wall; Described lower wall is fixed with locating part, for limiting moving radially of described lower wall; Described side seal comprises the second connector, for being connected with turbine inner casing.
Preferably, described first connector comprises the multiple upper draw ring be fixed on upper wall, multiple fastening bolt, and after-poppet; One end of described fastening bolt is connected with described upper draw ring through after the first fastening bolt holes on described after-poppet; Described after-poppet also offering the second fastening bolt holes, being connected with the fastening bolt of turbine inner casing for realizing after-poppet.
Preferably, described locating part comprises multiple lower draw ring, stop pin and guide finger; Described stop pin is connected with turbine inner casing through after described lower draw ring with one end of guide finger.
Preferably, the length of described guide finger is greater than the length of described stop pin.
Preferably, described second connector is suspension plate, in order to be fixedly suspended on turbine inner casing by described side seal.
Preferably, described side seal offers the second cooling through hole.
Preferably, described second cooling through hole is communicated with the port of export of changeover portion.
Preferably, described side seal is the shape gradually opened along the axis of described upper wall or lower wall.
Preferably, described upper wall and lower wall all offer the first cooling through hole near the position of the port of export.
A kind of gas turbine, comprises combustion turbine transitory section structure of the present invention.
(3) beneficial effect
Technical scheme of the present invention has the following advantages: combustion turbine transitory section structure of the present invention, disconnected from each other in port of export position owing to being fan-shaped upper wall and lower wall, and realize sealing by the side seal outside upper wall and lower wall, this structure can effectively prevent changeover portion from exporting because ratcheting causes openings get smaller, and reduce the complexity of structure, easy disassembly.In addition, because the side wall construction originally easily by thermal stress deformation has not existed, thus the sidewall warpage avoiding the exit low-cycle fatigue of transition section structure to cause even is broken, and the coming off of hermetically-sealed construction; Air is prevented directly to enter the passage of heat.
Accompanying drawing explanation
In order to be illustrated more clearly in the embodiment of the present invention or technical 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 some embodiments of the present invention, 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 structural representation of the transition section structure of prior art;
Fig. 2 is the structural representation of combustion turbine transitory section structure of the present invention removing after-poppet and side seal;
Fig. 3 is the structural representation of combustion turbine transitory section structure of the present invention removing side seal;
Fig. 4 is the using state schematic perspective view of combustion turbine transitory section structure of the present invention;
Fig. 5 is the cross-sectional schematic of the using state of combustion turbine transitory section structure of the present invention;
In figure: 1, transition section structure; 2, turbine one-level stator blade; 3, turbine inner casing; 4, upper wall; 5, lower wall; 6, upper draw ring; 7, lower draw ring; 8, guide finger; 9, the first cooling through hole; 10, stop pin; 11, after-poppet; 12, fastening bolt; 13, side seal; 14, suspension plate; 15, the second cooling through hole.
Detailed description of the invention
Below in conjunction with drawings and Examples, embodiments of the present invention are described in further detail.Following examples for illustration of the present invention, but can not be used for limiting the scope of the invention.
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.
Refer to Fig. 2, this figure is the combustion turbine transitory section structure 1 of the present embodiment, comprise the port of export disconnected from each other in fan-shaped upper wall 4 and lower wall 5.Because upper wall 4 is separated with lower wall 5, therefore the radial dimension of the port of export and position are organized structure by upper wall 4 and lower wall 5 liang and are separately controlled.In order to reduce the temperature of the port of export of transition section structure 1, and certain protective effect being played to the turbine one-level stator blade 2 in downstream, preferably all offering the first cooling through hole 9 at upper wall 4 and lower wall 5 near the position of the port of export.In addition, described upper wall 4 is fixed with the first connector, for being fixedly connected with turbine inner casing 3 by described upper wall 4; Described lower wall 5 is fixed with locating part, for limiting moving radially of described lower wall 5.
In the present embodiment, preferably but must not comprise the multiple upper draw ring 6 be fixed on upper wall 4, multiple fastening bolt 12, and after-poppet 11, refer to Fig. 3 to described first connector.One end of described fastening bolt 12 is connected with described upper draw ring 6 through after the first bolt hole on described after-poppet 11; Described after-poppet 11 also offering the second bolt hole, being connected with the bolt of turbine inner casing 3 for realizing after-poppet 11.Locating part fixing on described lower wall 5, preferably includes multiple lower draw ring 7, stop pin 10 and guide finger 8; Described stop pin 10 is connected with turbine inner casing 3 through after described lower draw ring 7 with one end of guide finger 8.The axial length of guide finger 8 is greater than the axial length of stop pin 10, and object is the installation facilitating stop pin 10; The object of stop pin 10 is the radial position limiting lower wall 5.
After passing changeover portion inside by the high-temperature fuel gas of combustion turbine transitory section structure 1, the port of export through transition section structure 1 enters turbine one-level stator blade 2, in order to prevent compressed air from entering the inner build-up of pressure loss of transition section structure 1, need between the upper and lower wall 5 of transition section structure 1 port of export to realize sealing.Side seal 13 is had in the arranged outside of upper wall 4 and lower wall 5 in the present embodiment, and described side seal 13 is close to the both sides of described upper wall and lower wall, make to realize sealing between described upper wall 4 and the both sides of lower wall 5, refer to Fig. 4, wherein, " outside " refers to the position at the center away from described combustion turbine transitory section structure 1.Side seal 13 upper and lower wall of getting along well directly connects, but is connected with turbine inner casing 3 by the second connector, and therefore it can move relative to upper and lower wall.In addition, side seal 13 can cover the region be separated between upper wall 4 and lower wall 5, ensures sealing.By adopting the structure that in the present embodiment, upper and lower wall is separated, sealing in conjunction with side seal 13, thus the distortion of changeover portion can be weakened, avoid changeover portion to export because ratcheting causes opening to shrink, and extend the service life of changeover portion.
In the present embodiment, preferably described second connector is preferably suspension plate 14, in order to be fixedly suspended on turbine inner casing 3 by described side seal 13.In addition, cause ablation in order to the part Yin Wendu preventing side seal 13 and combustion gas from directly contacting is too high, side seal 13 offers the second cooling through hole 15; And preferably described second cooling through hole 15 is communicated with the port of export of changeover portion, thus the cooling of changeover portion can be realized further.This side seal 13 is in order to play the effect of the side seal in conventional transition segment structure 1, and obviously its medial surface is preferably plane, and its global shape is preferably suitable with the shape of changeover portion end, and the axis along described upper wall or lower wall is the shape gradually opened; After installing transition section structure 1 and side seal 13, do not need inserting side diaphragm seal again, therefore reduce the complexity of installation.
The combustion turbine transitory section structure 1 provided by the present embodiment is connected with turbine inner casing 3, refer to Fig. 5, owing to originally easily not existed by the side wall construction of thermal stress deformation, thus the sidewall warpage avoiding the exit low-cycle fatigue of transition section structure 1 to cause even is broken, and the coming off of hermetically-sealed construction; On this basis, prevent compressed air from entering the inner build-up of pressure loss of changeover portion.
Above embodiment is only for illustration of the present invention, but not limitation of the present invention.Although with reference to embodiment to invention has been detailed description, those of ordinary skill in the art is to be understood that, various combination, amendment or equivalent replacement are carried out to technical scheme of the present invention, do not depart from the spirit and scope of technical solution of the present invention, all should be encompassed in the middle of right of the present invention.
Claims (10)
1. a combustion turbine transitory section structure, is characterized in that, comprise the port of export disconnected from each other in fan-shaped upper wall and lower wall; The arranged outside of described upper wall and lower wall has side seal, makes to realize sealing between described upper wall and the both sides of lower wall;
Described upper wall is fixed with the first connector, for being fixedly connected with turbine inner casing by described upper wall; Described lower wall is fixed with locating part, for limiting moving radially of described lower wall; Described side seal comprises the second connector, for being connected with turbine inner casing.
2. combustion turbine transitory section structure according to claim 1, is characterized in that, described first connector comprises the multiple upper draw ring be fixed on upper wall, multiple fastening bolt, and after-poppet; One end of described fastening bolt is connected with described upper draw ring through after the first fastening bolt holes on described after-poppet; Described after-poppet also offering the second fastening bolt holes, being connected with the fastening bolt of turbine inner casing for realizing after-poppet.
3. combustion turbine transitory section structure according to claim 1, is characterized in that, described locating part comprises multiple lower draw ring, stop pin and guide finger; Described stop pin is connected with turbine inner casing through after described lower draw ring with one end of guide finger.
4. combustion turbine transitory section structure according to claim 3, is characterized in that, the length of described guide finger is greater than the length of described stop pin.
5. combustion turbine transitory section structure according to claim 1, is characterized in that, described second connector is suspension plate, in order to be fixedly suspended on turbine inner casing by described side seal.
6. combustion turbine transitory section structure according to claim 1, is characterized in that, described side seal offers the second cooling through hole.
7. combustion turbine transitory section structure according to claim 6, is characterized in that, described second cooling through hole is communicated with the port of export of changeover portion.
8. combustion turbine transitory section structure according to claim 1, is characterized in that, described side seal is the shape gradually opened along the axis of described upper wall or lower wall.
9. combustion turbine transitory section structure as claimed in any of claims 1 to 8, is characterized in that, described upper wall and lower wall all offer the first cooling through hole near the position of the port of export.
10. a gas turbine, is characterized in that, comprises the combustion turbine transitory section structure in claim 1 to 9 described in any one.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410842822.4A CN104613499B (en) | 2014-12-30 | 2014-12-30 | A kind of combustion turbine transitory section structure and gas turbine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410842822.4A CN104613499B (en) | 2014-12-30 | 2014-12-30 | A kind of combustion turbine transitory section structure and gas turbine |
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| CN104613499A true CN104613499A (en) | 2015-05-13 |
| CN104613499B CN104613499B (en) | 2018-10-16 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110578934A (en) * | 2018-06-07 | 2019-12-17 | 赛峰航空器发动机 | Combustion chamber for a turbomachine |
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| JP2010261318A (en) * | 2009-04-30 | 2010-11-18 | Mitsubishi Heavy Ind Ltd | Method of manufacturing plate-shaped body, plate-shaped body, gas turbine combustor, and gas turbine |
| CN103244199A (en) * | 2012-02-13 | 2013-08-14 | 通用电气公司 | Transition piece seal assembly for a turbomachine |
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| DE102013202695A1 (en) * | 2013-02-20 | 2014-08-21 | Siemens Aktiengesellschaft | Combustion chamber outer shell for gas turbine, has seals, which are arranged between half shells for sealing parting lines, where seal strip is housed in mutually corresponding sealing grooves in joining areas of abutting half-shells |
| CN104061596A (en) * | 2013-03-18 | 2014-09-24 | 通用电气公司 | Flow Sleeve Assembly For A Combustion Module Of A Gas Turbine Combustor |
| CN204593459U (en) * | 2014-12-30 | 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 combustion turbine transitory section structure and gas turbine |
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2014
- 2014-12-30 CN CN201410842822.4A patent/CN104613499B/en active Active
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050132573A1 (en) * | 2002-05-06 | 2005-06-23 | Norek Richard S. | Forming gas turbine transition duct bodies without longitudinal welds |
| US20090260364A1 (en) * | 2008-04-16 | 2009-10-22 | Siemens Power Generation, Inc. | Apparatus Comprising a CMC-Comprising Body and Compliant Porous Element Preloaded Within an Outer Metal Shell |
| US20100054928A1 (en) * | 2008-08-26 | 2010-03-04 | Schiavo Anthony L | Gas turbine transition duct apparatus |
| JP2010261318A (en) * | 2009-04-30 | 2010-11-18 | Mitsubishi Heavy Ind Ltd | Method of manufacturing plate-shaped body, plate-shaped body, gas turbine combustor, and gas turbine |
| CN103244199A (en) * | 2012-02-13 | 2013-08-14 | 通用电气公司 | Transition piece seal assembly for a turbomachine |
| US20130255276A1 (en) * | 2012-03-27 | 2013-10-03 | Alstom Technology Ltd. | Transition Duct Mounting System |
| DE102013202695A1 (en) * | 2013-02-20 | 2014-08-21 | Siemens Aktiengesellschaft | Combustion chamber outer shell for gas turbine, has seals, which are arranged between half shells for sealing parting lines, where seal strip is housed in mutually corresponding sealing grooves in joining areas of abutting half-shells |
| CN104061596A (en) * | 2013-03-18 | 2014-09-24 | 通用电气公司 | Flow Sleeve Assembly For A Combustion Module Of A Gas Turbine Combustor |
| CN204593459U (en) * | 2014-12-30 | 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 combustion turbine transitory section structure and gas turbine |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110578934A (en) * | 2018-06-07 | 2019-12-17 | 赛峰航空器发动机 | Combustion chamber for a turbomachine |
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| CN104613499B (en) | 2018-10-16 |
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Effective date of registration: 20200117 Address after: 102209 Beijing Changping District in the future of the national electric investment group Park in the future science city south of Beijing Patentee after: China United heavy-duty gas turbine technology Co., Ltd. Address before: 100084, Beijing, Haidian District science and Technology Park, Tsinghua Science and technology building, block C, 10 Patentee before: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. |
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