CN103398398A - Double-seal connection structure of flame tube and transition section of combustion gas turbine combustion chamber - Google Patents
Double-seal connection structure of flame tube and transition section of combustion gas turbine combustion chamber Download PDFInfo
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- CN103398398A CN103398398A CN2013103496470A CN201310349647A CN103398398A CN 103398398 A CN103398398 A CN 103398398A CN 2013103496470 A CN2013103496470 A CN 2013103496470A CN 201310349647 A CN201310349647 A CN 201310349647A CN 103398398 A CN103398398 A CN 103398398A
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- elastic sealing
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- inner liner
- rearmounted
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 35
- 239000000567 combustion gas Substances 0.000 title abstract description 5
- 230000007704 transition Effects 0.000 title abstract 8
- 238000007789 sealing Methods 0.000 claims abstract description 99
- 238000001816 cooling Methods 0.000 claims abstract description 46
- 238000010276 construction Methods 0.000 claims description 24
- 238000012856 packing Methods 0.000 claims description 5
- 230000015572 biosynthetic process Effects 0.000 claims description 4
- 125000006850 spacer group Chemical group 0.000 claims description 3
- 238000011144 upstream manufacturing Methods 0.000 claims description 3
- 238000005299 abrasion Methods 0.000 abstract 1
- 239000007789 gas Substances 0.000 description 6
- 238000010586 diagram Methods 0.000 description 2
- 239000008358 core component Substances 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
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Abstract
The invention provides a double-seal connection structure of a flame tube and a transition section of a combustion gas turbine combustion chamber, and relates to the structural design of the combustion gas turbine combustion chamber. The double-seal connection structure comprises the flame tube, the transition section and a seal structure; the flame tube is inserted into the transition section, a combustion flow channel is defined by the inner wall surface of the flame tube and the inner wall surface of the transition section together, and the seal structure is arranged between the flame tube and the transition section; the seal structure comprises a seal supporting part, a front elastic seal part and a rear elastic seal part. According to the double-seal connection structure, due to the fact that the structural mode of the front elastic seal part and the rear elastic seal part and a correspondingly suitable channel cooling structure are utilized, cold air passes through a cooling channel and a seal cavity and cools the flame tube, the transition section and the seal structure respectively, and the seal structure between the flame tube and the transition section can achieve the double functions of sealing and cooling. The two-level elastic seal parts reinforce the seal function of the seal structure, and therefore the cold air can be controlled more easily when passing, and possibility of complete failure caused by abrasion of single elastic seal parts is reduced.
Description
Technical field
The present invention relates to the structural design of gas-turbine combustion chamber, relate in particular to the hermetically-sealed construction that combustion chamber flame drum is connected with changeover portion, belong to the chain drive technical field.
Background technology
Gas turbine is the indispensable great chain drive of energy field.Combustion chamber is as one of three large core components of gas turbine, and its task is heating working medium, the chemical energy of fuel is converted into to the heat energy of high-temperature fuel gas, and then the combustion gas that formation temperature and temperature field all meet the demands is delivered in turbine and done merit.The structure of combustion chamber generally comprises the parts such as shell, spray group, burner inner liner and changeover portion, and wherein the coupling part of burner inner liner and changeover portion is provided with hermetically-sealed construction usually.
The effect of hermetically-sealed construction is in order to prevent that air from leaking in combustion channels in the position of not expecting, but it is very difficult that complete hermetic hermetically-sealed construction implements, adopt at present usually the hermetically-sealed construction that a small amount of leakage is arranged, this leakage is in the situation that suitablely can play cooling effect.Hermetically-sealed construction is due to the HTHP that stands the inboard combustion gas of combustion channels, and it exists high thermograde and pressure to change, thus obtain suitable cooling be very important.
Due to reasons such as machining accuracy and thermal expansion distortion, the aisle spare that in actual moving process, hermetically-sealed construction limits is difficult to obtain assurance, thereby the cold air flow that causes entering combustion zone by hermetically-sealed construction easily changes, affect the cooling performance of burner inner liner and changeover portion junction, the Temperature Distribution of expectation be may not reach, variety of issue and fault occurred.
In prior art, managed to avoid the problem of above-mentioned existence as far as possible, as Chinese patent literature (publication number is CN101713539A), disclose a kind of wall by the burner inner liner junction and be made as double-wall structure, and adopt to impact and coolingly to play main cooling effect, and elastic sealing element plays main sealing function.Although the tolerance of the elastic sealing element by hermetically-sealed construction in this technical scheme is very little, but still be to have cold air to pass through and wayward, and elastic sealing element is vulnerable part, its damage will directly have influence on life-span of combustion chamber and time between overhauls(TBO) etc.
Summary of the invention
For solving problems of the prior art, the purpose of this invention is to provide the two-stage hermetically-sealed construction that a kind of gas-turbine combustion chamber burner inner liner is connected with changeover portion, make cold air pass through more easy to control, reduce simultaneously the impact of adopting the unfavorable factor that may cause after single elastic sealing element wear out failure.
The technical solution adopted in the present invention is as follows:
The double containment syndeton of a kind of gas-turbine combustion chamber burner inner liner and changeover portion, this syndeton comprises burner inner liner, changeover portion and hermetically-sealed construction; Described burner inner liner inserts in changeover portion, by the internal face of burner inner liner and changeover portion, forms combustion channels, and hermetically-sealed construction is arranged between burner inner liner and changeover portion; , hermetically-sealed construction is arranged between burner inner liner and changeover portion; It is characterized in that: described hermetically-sealed construction comprises seal support part, is arranged on the preposition elastic sealing element on burner inner liner and is arranged on the rearmounted elastic sealing element on changeover portion; Described seal support part is arranged on the burner inner liner outside wall surface, and leaves formation cooling duct, gap with outer wall, on seal support part, along the upstream of gas flow in combustion channels, circumferentially arranges at least row's air admission hole, and air admission hole is connected with cooling duct; Described preposition elastic sealing element and seal support part form preposition annular seal space, and rearmounted elastic sealing element and changeover portion form rearmounted annular seal space.
Preferred version of the present invention is: in described cooling duct, arrange vertically two with upper spacer, it is several fan-shaped subchannels that cooling duct is divided into to section.The cross-sectional area of described cooling duct is less than the gross area of described air admission hole.
Another preferred version of the present invention is: described preposition elastic sealing element is comprised of preposition locating sealing ring and at least one preposition circular-arc elastic sealing strip, preposition circular-arc elastic sealing strip is arranged on preposition locating sealing ring, and this preposition locating sealing ring is fixed on seal support part; Rearmounted elastic sealing element is comprised of rearmounted locating sealing ring and at least one rearmounted circular-arc elastic sealing strip, and rearmounted circular-arc elastic sealing strip is arranged on rearmounted locating sealing ring, and this postposition locating sealing ring is fixed on the inwall of changeover portion.
Another preferred version of the present invention is: described preposition circular-arc elastic sealing strip and rearmounted circular-arc elastic sealing strip number are all between 36～72.More than two during circular-arc elastic sealing strip, the gap between the gap between adjacent two preposition circular-arc elastic sealing strips or adjacent two circular-arc elastic sealing strips of postposition is in 1mm～3mm scope when preposition circular-arc elastic sealing strip or rearmounted circular-arc elastic packing strip adoption.
This invention compared with prior art, have the following advantages and the high-lighting effect: the present invention is by arranging corresponding suitable cooling duct the version that adopts the two-stage elastic sealing element to seal, make the hermetically-sealed construction between burner inner liner and changeover portion play sealing, cooling dual-use function, the controllability of cooling performance strengthens; Two elastic sealing element structures that two-stage is set play safety effect to contingent damage, effectively reduce after adopting single elastic sealing element wearing and tearing thoroughly to lose efficacy the impact of the unfavorable factor that may cause; Cooling duct is divided into to some fan-shaped subchannels corresponding with the air admission hole position with dividing plate, make the cold air flow velocity in passage increase, heat convection strengthens, more be suitable for taking away the heat of junction flame tube wall, effective cooling burner inner liner wall herein, can also make it simultaneously to flow in combustion channels flow more regular, thereby form the one section changeover portion wall of air film after cooling.
The accompanying drawing explanation
Fig. 1 is the structural principle schematic diagram of the double containment syndeton of a kind of gas-turbine combustion chamber burner inner liner provided by the invention and changeover portion.
Fig. 2 is the structure three-dimensional cutaway view of double containment syndeton.
Fig. 3 is the structural representation that cooling duct is divided into several subchannels.
In figure, symbol description is as follows: the 11-burner inner liner; The 13-changeover portion; The 21-hermetically-sealed construction; The 32-seal support part; The preposition elastic sealing element of 33-; The rearmounted elastic sealing element of 34-; The 15-combustion channels; The 42-air admission hole; The 44-dividing plate; The 16-cooling duct; 47-burner inner liner outside wall surface; 48-changeover portion internal face; The preposition locating sealing ring of 56-; The preposition circular-arc elastic sealing strip of 57-; Gap between the preposition sealing strip of 58-; The preposition annular seal space of 59-; The rearmounted locating sealing ring of 63-; The rearmounted circular-arc elastic sealing strip of 64-; Gap between the rearmounted sealing strip of 65-; The rearmounted annular seal space of 66-.
The specific embodiment
Below in conjunction with accompanying drawing, principle of the present invention, structure and the specific embodiment are described further.
Fig. 1 is the structural principle schematic diagram of the double containment syndeton of a kind of gas-turbine combustion chamber burner inner liner provided by the invention and changeover portion.This syndeton comprises burner inner liner 11, changeover portion 13 and hermetically-sealed construction 21; Burner inner liner is inserted 11 and is entered in changeover portion 13, by the internal face of burner inner liner 11 and changeover portion 13, forms combustion channels 15, and hermetically-sealed construction 21 is arranged between burner inner liner 11 and changeover portion 13.
Hermetically-sealed construction 21 comprises seal support part 32, is arranged on the preposition elastic sealing element 33 on burner inner liner and is arranged on the rearmounted elastic sealing element 34 on changeover portion; Seal support part 32 is arranged on burner inner liner outside wall surface 47, and leave formation cooling duct, gap 16 with outer wall, on seal support part, along the upstream of combustion channels 15 interior gas flows, circumferentially arrange at least row's air admission hole 42, air admission hole 42 is connected with cooling duct 16; Described preposition elastic sealing element and seal support part form preposition annular seal space 59, and rearmounted elastic sealing element and changeover portion form rearmounted annular seal space 66.
In cooling duct 16, arrange vertically two with upper spacer 44, it is fan-shaped several subchannels (referring to Fig. 2, Fig. 3) that cooling duct is divided into to section.
Preposition elastic sealing element 33 is comprised of preposition locating sealing ring 56 and at least one preposition circular-arc elastic sealing strip 57, and preposition circular-arc elastic sealing strip is arranged on preposition locating sealing ring, and this preposition locating sealing ring is fixed on seal support part 32; Rearmounted elastic sealing element 34 is comprised of rearmounted locating sealing ring 63 and at least one rearmounted circular-arc elastic sealing strip 64, rearmounted circular-arc elastic sealing strip is arranged on rearmounted locating sealing ring 63, and this postposition locating sealing ring is fixed on the inwall of changeover portion (referring to Fig. 2).Preposition circular-arc elastic sealing strip 57 and the preferred number of rearmounted circular-arc elastic sealing strip 64 are all between 36～72.More than two during circular-arc elastic sealing strip, the gap between the gap between adjacent two preposition circular-arc elastic sealing strips or adjacent two circular-arc elastic sealing strips of postposition is in 1mm～3mm scope when preposition circular-arc elastic sealing strip or rearmounted circular-arc elastic packing strip adoption.
Preposition circular-arc elastic sealing strip 57 highest points are subject to changeover portion internal face 48, when the highest point pressurized, can extend to the opposite direction of preposition locating sealing ring 56, play the effect of elastic packing; Rearmounted circular-arc elastic sealing strip 64 highest points are subject to seal support part 32, when the highest point pressurized, can extend to the opposite direction of rearmounted locating sealing ring 63, play the effect of elastic packing.
Operation principle of the present invention is as follows:
Cold air enters preposition annular seal space 59 by air admission hole 42 by the gap 58 between preposition circular-arc elastic sealing strip, and cooling and sealing structure lost efficacy to prevent hermetically-sealed construction, and this part gas that completes cooling effect continues to flow to rearmounted elastic sealing element 34 directions subsequently.
The cold air that is flowed out by the gap between preposition seal 33 can be entered by the gap 65 between the circular-arc elastic sealing strip of postposition rearmounted annular seal space 66, cooling and sealing structure lost efficacy to prevent hermetically-sealed construction, and this part gas that completes cooling effect flows into combustion channels 15 subsequently.
preposition elastic sealing element 33 forms the two-stage sealing function with rearmounted elastic sealing element 34, it is very little that two-stage seals the cold air flow that makes by therebetween, sealing effectiveness is fine, thereby the more cold air that enters from air admission hole 42 that relies on of cooling effect, cold air finally enters combustion channels 15 by cooling duct 16, the cold air flow is here limited by the discharge area of cooling duct 16, the perforated area of the air admission hole 42 on seal support part need to coordinate the discharge area of cooling duct 16, it is the gross area that the cross-sectional area of cooling duct 16 is less than described air admission hole 42, make the cold air in passage have higher flow velocity, to reach the convection current cooling performance that has possessed in passage, carry out cooling flame drum outer wall face 47.Cooling duct is divided into to some fan-shaped subchannels corresponding with the air admission hole position with dividing plate, can also make it in rear inflow combustion channels flow more regular, thereby form the one section changeover portion wall of air film after cooling.
Claims (6)
1. the double containment syndeton of a gas-turbine combustion chamber burner inner liner and changeover portion, this syndeton comprises burner inner liner (11), changeover portion (13) and hermetically-sealed construction (21); Described burner inner liner (11) inserts in changeover portion (13), and the internal face of burner inner liner (11) and changeover portion (13) forms combustion channels (15), and hermetically-sealed construction (21) is arranged between burner inner liner (11) and changeover portion (13); It is characterized in that: described hermetically-sealed construction comprises seal support part (32), is arranged on the preposition elastic sealing element (33) on burner inner liner and is arranged on the rearmounted elastic sealing element (34) on changeover portion; Described seal support part (32) is arranged on burner inner liner outside wall surface (47), and leave formation cooling duct, gap (16) with outer wall, on seal support part, along the upstream of gas flow in combustion channels (15), circumferentially arrange at least row's air admission hole (42), air admission hole (42) is connected with cooling duct (16); Described preposition elastic sealing element and seal support part form preposition annular seal space (59), and rearmounted elastic sealing element and changeover portion form rearmounted annular seal space (66).
2. the double containment syndeton of a kind of gas-turbine combustion chamber burner inner liner as claimed in claim 1 and changeover portion, it is characterized in that: in described cooling duct (16), arrange vertically two with upper spacer (44), it is several fan-shaped subchannels that cooling duct is divided into to section.
3. the double containment syndeton of a kind of gas-turbine combustion chamber burner inner liner as claimed in claim 1 or 2 and changeover portion, it is characterized in that: the cross-sectional area of described cooling duct (16) is less than the gross area of described air admission hole (42).
4. the double containment syndeton of a kind of gas-turbine combustion chamber burner inner liner and changeover portion as claimed in claim 1, it is characterized in that: preposition elastic sealing element (33) is comprised of preposition locating sealing ring (56) and at least one preposition circular-arc elastic sealing strip (57), preposition circular-arc elastic sealing strip is arranged on preposition locating sealing ring, and this preposition locating sealing ring is fixed on seal support part (32); Rearmounted elastic sealing element (34) is comprised of rearmounted locating sealing ring (63) and at least one rearmounted circular-arc elastic sealing strip (64), rearmounted circular-arc elastic sealing strip is arranged on rearmounted locating sealing ring, and this postposition locating sealing ring is fixed on the inwall of changeover portion.
5. the double containment syndeton of a kind of gas-turbine combustion chamber burner inner liner as claimed in claim 4 and changeover portion, it is characterized in that: described preposition circular-arc elastic sealing strip (57) and rearmounted circular-arc elastic sealing strip (64) number are all between 36～72.
6. the double containment syndeton of a kind of gas-turbine combustion chamber burner inner liner as described as claim 4 or 5 and changeover portion is characterized in that: when preposition circular-arc elastic sealing strip or rearmounted circular-arc elastic packing strip adoption more than two during circular-arc elastic sealing strip,
Gap between gap between adjacent two preposition circular-arc elastic sealing strips or adjacent two circular-arc elastic sealing strips of postposition is in 1mm～3mm scope.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310349647.0A CN103398398B (en) | 2013-08-12 | 2013-08-12 | The double containment syndeton of a kind of gas-turbine combustion chamber burner inner liner and changeover portion |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310349647.0A CN103398398B (en) | 2013-08-12 | 2013-08-12 | The double containment syndeton of a kind of gas-turbine combustion chamber burner inner liner and changeover portion |
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| CN103398398B CN103398398B (en) | 2016-01-20 |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104359127A (en) * | 2014-10-31 | 2015-02-18 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Channel type cooling structure of flame tube in combustion chamber of gas turbine |
| CN104864416A (en) * | 2015-04-22 | 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 | Connecting structure of combustion liner and transition section |
| CN106089446A (en) * | 2015-03-27 | 2016-11-09 | 安萨尔多能源瑞士股份公司 | Hula Seal |
| CN107975821A (en) * | 2016-10-24 | 2018-05-01 | 三菱日立电力系统株式会社 | Gas turbine burner |
| CN111750380A (en) * | 2019-03-28 | 2020-10-09 | 中国航发湖南动力机械研究所 | Flame tube outlet connecting device |
| CN114412645A (en) * | 2021-12-26 | 2022-04-29 | 西北工业大学 | Cooling structure and cooling method of laminated plate with slit ribs for turbofan engine combustion chamber |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104359127A (en) * | 2014-10-31 | 2015-02-18 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Channel type cooling structure of flame tube in combustion chamber of gas turbine |
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| CN111750380A (en) * | 2019-03-28 | 2020-10-09 | 中国航发湖南动力机械研究所 | Flame tube outlet connecting device |
| CN114412645A (en) * | 2021-12-26 | 2022-04-29 | 西北工业大学 | Cooling structure and cooling method of laminated plate with slit ribs for turbofan engine combustion chamber |
| CN114412645B (en) * | 2021-12-26 | 2023-01-31 | 西北工业大学 | Cooling structure and cooling method of laminated plate with slit ribs for turbofan engine combustion chamber |
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Denomination of invention: Double-seal connection structure of flame tube and transition section of combustion gas turbine combustion chamber Effective date of registration: 20161104 Granted publication date: 20160120 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
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Date of cancellation: 20191211 Granted publication date: 20160120 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
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Date of cancellation: 20191230 Granted publication date: 20160120 |
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Effective date of registration: 20200116 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 No. 8, building 1, No. 1001, Zhongguancun East Road, Beijing, Haidian District Patentee before: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. |