CN114484498A - Fan-shaped combustion chamber structure - Google Patents
Fan-shaped combustion chamber structure Download PDFInfo
- Publication number
- CN114484498A CN114484498A CN202210088019.0A CN202210088019A CN114484498A CN 114484498 A CN114484498 A CN 114484498A CN 202210088019 A CN202210088019 A CN 202210088019A CN 114484498 A CN114484498 A CN 114484498A
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- China
- Prior art keywords
- combustion chamber
- flame tube
- main pipe
- chamber casing
- side wall
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- 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.)
- Pending
Links
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 54
- 239000000446 fuel Substances 0.000 claims abstract description 26
- 238000001816 cooling Methods 0.000 claims abstract description 25
- 238000007789 sealing Methods 0.000 claims description 11
- 239000011148 porous material Substances 0.000 claims description 6
- 239000010425 asbestos Substances 0.000 claims description 4
- 238000005192 partition Methods 0.000 claims description 4
- 229910052895 riebeckite Inorganic materials 0.000 claims description 4
- 238000010276 construction Methods 0.000 claims 1
- 230000000694 effects Effects 0.000 abstract description 12
- 238000002679 ablation Methods 0.000 abstract description 5
- 239000007789 gas Substances 0.000 description 6
- 238000012360 testing method Methods 0.000 description 6
- 238000011161 development Methods 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000004888 barrier function Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000112 cooling gas Substances 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000011056 performance test Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
Abstract
The invention provides a fan-shaped combustion chamber structure which comprises a combustion chamber casing and a flame tube, wherein the flame tube is positioned in the combustion chamber casing, the rear part of the flame tube is mutually positioned and connected with the combustion chamber casing through a mounting edge, and flanges are arranged at the front end and the rear end of the combustion chamber casing; the front end of the combustion chamber casing is fixedly provided with a fuel main pipe, the rear end of the fuel main pipe extends into the flame tube, the upper part of the combustion chamber casing is provided with an ignition mechanism, and the lower end of the ignition mechanism extends into the flame tube; cooling holes are distributed on the left side wall and the right side wall of the flame tube. According to the invention, the left side wall and the right side wall of the flame tube are fully distributed with the cooling holes, so that cooling air passes through the cooling holes, and impact air films are formed on the left side wall and the right side wall of the flame tube, thus not only improving the cooling effect of the flame tube, but also forming a good protection effect on the flame tube, avoiding ablation of the flame tube and ensuring the safety of the long-time work of the flame tube.
Description
Technical Field
The invention relates to the technical field of aero-engine combustion chambers; in particular to a fan-shaped combustion chamber structure.
Background
The development of an aircraft engine combustion chamber is mainly based on experiments and is a process of experiment-modification-retest-modification. The fan-shaped test piece is easy to change the structure for debugging, the period is short, contradictions can be highlighted during the test, and the test is flexible, so that a preliminary design scheme for verifying the performance test of the fan-shaped combustion chamber is often developed for saving the cost and the development period. The sector combustion chamber test piece is the same as a real combustion chamber, and generally mainly comprises a sector combustion chamber casing, a sector flame tube, a sector fuel manifold and an ignition mechanism.
The combustion chamber works under the high-pressure high-temperature environment, the flame tube belongs to the temperature-bearing part, the ablation phenomenon is generally found on the left side wall and the right side wall of the flame tube in the test, the fact that the original structure has certain potential safety hazards when being used for a long time is proved, and the combustion chamber cannot adapt to the working condition of a new generation of combustion chamber with higher temperature. The combustion chamber casing belongs to a pressure-bearing part, and the sealing of a mounting seat on the casing needs to be ensured to avoid air leakage. In addition, in the processes of testing, product assembly and the like, the ignition position needs to be correspondingly adjusted under different conditions, and the original structure cannot be adjusted.
Disclosure of Invention
In order to solve the technical problem, the invention provides a fan-shaped combustion chamber structure.
The invention is realized by the following technical scheme.
The invention provides a fan-shaped combustion chamber structure, which comprises a combustion chamber casing and a flame tube, wherein the flame tube is positioned in the combustion chamber casing, the rear part of the flame tube is mutually positioned and connected with the combustion chamber casing through a mounting edge, and flanges are arranged at the front end and the rear end of the combustion chamber casing; the front end of the combustion chamber casing is fixedly provided with a fuel main pipe, the rear end of the fuel main pipe extends into the flame tube, the upper part of the combustion chamber casing is provided with an ignition mechanism, and the lower end of the ignition mechanism extends into the flame tube; cooling holes are distributed on the left side wall and the right side wall of the flame tube.
The combustion chamber casing is fixed with a main pipe mounting seat corresponding to the main fuel pipe, a main pipe lower base and a main pipe upper cover plate are sequentially overlapped on the main pipe mounting seat, the main pipe upper cover plate, the main pipe lower base and the main pipe mounting seat are sequentially connected through bolts in a fastened mode, and the main fuel pipe penetrates through the main pipe upper cover plate and the main pipe lower base.
The middle of one end, close to the main pipe upper cover plate, of the main pipe lower base is provided with a groove, a sealing gasket is arranged in the groove around the fuel main pipe, and a boss is arranged on the main pipe upper cover plate and corresponds to the groove.
The fuel manifold is close to one end of the lower base of the main pipe and is provided with threads, and the overlapped part of the fuel manifold and the sealing gasket is wound with an asbestos rope.
The ignition mechanism comprises an igniter and a supporting seat, an ignition seat is fixed on the igniter, the supporting seat is fixed on a combustion chamber casing, a waist-shaped hole is formed in the upper end of the supporting seat, a bolt connection point ignition seat is arranged at the waist-shaped hole, a sliding block is arranged at the lower end of the igniter, a lining is arranged on the flame tube corresponding to the lower end of the igniter, and the upper end of the lining is in contact with the end face of the sliding block.
And a limiting piece is further arranged around the sliding block and fixed on the flame tube.
The limiting pieces are uniformly distributed in four directions of the sliding block, the upper ends of the limiting pieces are bent towards the direction of the sliding block, and the height of the bent parts is the same as that of the upper ends of the sliding block.
The double-layer pore plate structure is arranged on the left side wall and the right side wall of the flame tube.
The double-layer pore plate structure comprises an inclined hole inner plate and a straight hole outer plate, wherein a partition plate is arranged at the edge of the inclined hole inner plate and the edge of the straight hole outer plate at intervals, inclined air holes are distributed in the inclined hole inner plate, and straight air holes are distributed in the straight hole outer plate.
And a support column is also arranged between the inclined hole inner plate and the straight hole outer plate.
The angle of the inclined air holes is 30-45 degrees.
The aperture of each inclined air hole and the aperture of each straight air hole are both 0.8-1.5 mm.
The invention has the beneficial effects that:
according to the invention, the left side wall and the right side wall of the flame tube are fully distributed with the cooling holes, so that cooling air passes through the cooling holes, and impact air films are formed on the left side wall and the right side wall of the flame tube, thus not only improving the cooling effect of the flame tube, but also forming a good protection effect on the flame tube, avoiding ablation of the flame tube and ensuring the safety of the long-time work of the flame tube.
Drawings
Fig. 1 is a schematic structural view of the present invention.
Fig. 2 is a schematic view of the mounting structure of the fuel manifold.
Fig. 3 is a schematic view of the mounting structure of the igniter.
FIG. 4 is a schematic view of the side wall structure of the combustor basket.
Fig. 5 is a sectional view taken along line a-a of fig. 4.
In the figure: 1-a pre-measurement section; 2-post measurement section; 3-a combustor casing; 4-a flame tube; 5-mounting edges; 6-fuel oil main pipe; 7-an ignition mechanism; 8-cooling holes; 9-header pipe mounting seat; 10-manifold lower base; 11-header pipe upper cover plate; 12-a groove; 13-a sealing gasket; 14-asbestos cord; 15-an igniter; 16-an ignition seat; 17-a support base; 18-kidney shaped holes; 19-a slide block; 20-a liner; 21-a limiting sheet; 22-inclined hole inner plate; 23-straight hole outer plates; 24-a separator; 25-support column.
Detailed Description
The technical solution of the present invention is further described below, but the scope of the claimed invention is not limited to the described.
Fig. 1 shows a schematic structural diagram of the present invention:
the invention provides a fan-shaped combustion chamber structure, which comprises a combustion chamber casing 3 and a flame tube 4, wherein the flame tube 4 is positioned in the combustion chamber casing 3, the rear part of the flame tube 4 is mutually positioned and connected with the combustion chamber casing 3 through a mounting edge 5, and flanges are arranged at the front end and the rear end of the combustion chamber casing 3; a fuel manifold 6 is fixed at the front end of the combustion chamber casing 3, the rear end of the fuel manifold 6 extends into the flame tube 4, an ignition mechanism 7 is arranged at the upper part of the combustion chamber casing 3, and the lower end of the ignition mechanism 7 extends into the flame tube 4; cooling holes 8 are distributed on the left side wall and the right side wall of the flame tube 4.
The principle is as follows: flanges at the front end and the rear end of the combustion chamber casing 3 are used for being respectively connected with the front measuring section 1 and the rear measuring section 2 in a laboratory or are arranged on a machine body when in use; the sealing performance is ensured. During operation, cooling air is introduced between the combustion chamber casing 3 and the flame tube 4, and in the prior art, the outer surface of the flame tube 4 is cooled by the cooling air, but the left side wall and the right side wall of the flame tube 4 of the sector combustion chamber generally have ablation phenomena. The left side wall and the right side wall of the flame tube 4 are fully distributed with the cooling holes 8, cooling gas enters the rear portion from the cooling holes 8, a layer of impact gas film is formed on the two side walls, the impact gas film isolates high-temperature gas from the side wall of the flame tube 4, the barrier protection effect is achieved, experiments show that the cooling holes 8 are arranged, and the flame tube 4 is not ablated.
According to the invention, the left side wall and the right side wall of the flame tube 4 are fully distributed with the cooling holes 8, so that cooling air passes through the cooling holes 8, and impact air films are formed on the left side wall and the right side wall of the flame tube 4, thereby not only improving the cooling effect of the flame tube 4, but also forming a good protection effect on the flame tube 4, avoiding ablation of the flame tube 4 and ensuring the safety of long-time work of the flame tube 4.
Fig. 2 shows the mounting structure of the fuel manifold 6:
the combustion chamber casing 3 is fixed with a main pipe mounting seat 9 corresponding to the fuel main pipe 6, a main pipe lower base 10 and a main pipe upper cover plate 11 are sequentially overlapped on the main pipe mounting seat 9, the main pipe upper cover plate 11, the main pipe lower base 10 and the main pipe mounting seat 9 are sequentially connected in a fastening mode through bolts, and the fuel main pipe 6 penetrates through the main pipe upper cover plate 11 and the main pipe lower base 10. Easy dismounting fastens effectually.
The middle of one end, close to the main pipe upper cover plate 11, of the main pipe lower base 10 is provided with a groove 12, a sealing gasket 13 is arranged in the groove 12 and surrounds the fuel main pipe 6, and a boss is arranged on the main pipe upper cover plate 11 and corresponds to the groove 12. Seal gasket 13 is compressed tightly through the boss, has improved sealed effect, avoids the gas to leak, and the bearing capacity is good.
Threads are arranged at one end, close to the main pipe lower base 10, of the fuel main pipe 6, and an asbestos rope 14 is wound at the overlapped part of the fuel main pipe 6 and the sealing gasket 13. The sealing effect is improved.
Fig. 3 shows a mounting structure of the ignition mechanism 7:
the ignition mechanism 7 comprises an igniter 15 and a supporting seat 17, an ignition seat 16 is fixed on the igniter 15, the supporting seat 17 is fixed on the combustion chamber casing 3, a kidney-shaped hole 18 is formed in the upper end of the supporting seat 17, a bolt connection point ignition seat 16 is arranged at the position of the kidney-shaped hole 18, a sliding block 19 is arranged at the lower end of the igniter 15, a bushing 20 is arranged at the lower end of the flame tube 4 corresponding to the igniter 15, and the upper end of the bushing 20 is in contact with the end face of the sliding block 19. The upper end of the lining 20 is contacted with the end surface of the sliding block 19, so that the sealing effect of the combustion chamber is ensured, and the gas leakage is prevented; the igniter 15 can be integrally adjusted in position along with the supporting seat 17 through the kidney-shaped hole 18, and the igniter is pressed through a bolt after being adjusted in position, so that the optimal ignition position can be conveniently obtained.
And a limiting piece 21 is further arranged around the sliding block 19, and the limiting piece 21 is fixed on the flame tube 4. Facilitating the limiting of the position of the slider 19.
The limiting pieces 21 are uniformly distributed in four directions of the sliding block 19, the upper end of each limiting piece 21 is bent towards the sliding block 19, and the height of the bent part is the same as that of the upper end of the sliding block 19. The falling of the slider 19 during the assembly is avoided.
As shown in FIGS. 4-5, the two side walls of the flame tube 4 are structured as follows:
the double-layer pore plate structure is arranged on the left side wall and the right side wall of the flame tube 4. The temperature gradient is reduced, the cooling effect is good, and the safety is improved.
The double-layer pore plate structure comprises an inclined hole inner plate 22 and a straight hole outer plate 23, partition plates 24 are arranged at intervals on the edges of the inclined hole inner plate 22 and the straight hole outer plate 23, inclined air holes are distributed in the inclined hole inner plate 22, and straight air holes are distributed in the straight hole outer plate 23. The distance between the inclined hole inner plate 22 and the straight hole outer plate 23 is kept through the partition plate 24, the gas layer between the inclined hole inner plate 22 and the straight hole outer plate 23 reduces the temperature gradient, the flowability is good, and the cooling effect is improved.
And a strut 25 is also arranged between the inclined hole inner plate 22 and the straight hole outer plate 23. The rigidity is improved, and the distance between the inclined hole inner plate 22 and the straight hole outer plate 23 is convenient to maintain.
The angle of the inclined air holes is 30-45 degrees.
The aperture of each inclined air hole and the aperture of each straight air hole are both 0.8-1.5 mm. The number and the aperture are adjusted according to the actually required cooling air amount, and are preferably 1 mm.
Claims (10)
1. A sector combustion chamber construction characterized by: the combustion chamber casing structure comprises a combustion chamber casing (3) and a flame tube (4), wherein the flame tube (4) is positioned in the combustion chamber casing (3), the rear part of the flame tube (4) is mutually positioned and connected with the combustion chamber casing (3) through a mounting edge (5), and flanges are arranged at the front end and the rear end of the combustion chamber casing (3); a fuel main pipe (6) is fixed at the front end of the combustion chamber casing (3), the rear end of the fuel main pipe (6) extends into the flame tube (4), an ignition mechanism (7) is arranged at the upper part of the combustion chamber casing (3), and the lower end of the ignition mechanism (7) extends into the flame tube (4); cooling holes (8) are distributed on the left side wall and the right side wall of the flame tube (4).
2. The sector combustor structure of claim 1, wherein: the combustion chamber casing (3) is fixed with a main pipe mounting seat (9) corresponding to the main fuel pipe (6), the main pipe mounting seat (9) is sequentially overlapped with a main pipe lower base (10) and a main pipe upper cover plate (11), the main pipe lower base (10) and the main pipe mounting seat (9) are sequentially connected through bolts, and the main fuel pipe (6) penetrates the main pipe upper cover plate (11) and the main pipe lower base (10).
3. The sector combustor structure of claim 2, wherein: the middle of one end, close to the main pipe upper cover plate (11), of the main pipe lower base (10) is provided with a groove (12), a sealing gasket (13) is arranged in the groove (12) and surrounds the fuel main pipe (6), and a boss is arranged on the main pipe upper cover plate (11) and corresponds to the groove (12).
4. The sector combustor structure of claim 3, wherein: the fuel manifold (6) is close to one end of the manifold lower base (10) and is provided with threads, and the overlapped part of the fuel manifold (6) and the sealing gasket (13) is wound with an asbestos rope (14).
5. The sector combustor structure of claim 1, wherein: the ignition mechanism (7) comprises an igniter (15) and a supporting seat (17), an ignition seat (16) is fixed on the igniter (15), the supporting seat (17) is fixed on the combustion chamber casing (3), a waist-shaped hole (18) is formed in the upper end of the supporting seat (17), a bolt connection point ignition seat (16) is arranged in the waist-shaped hole (18), a sliding block (19) is arranged at the lower end of the igniter (15), a bushing (20) is arranged at the lower end, corresponding to the igniter (15), of the flame tube (4), and the upper end of the bushing (20) is in end face contact with the sliding block (19).
6. The sector combustor structure of claim 5, wherein: and a limiting sheet (21) is further arranged around the sliding block (19), and the limiting sheet (21) is fixed on the flame tube (4).
7. The sector combustor structure of claim 6, wherein: spacing piece (21) equipartition is in four directions of slider (19), and spacing piece (21) upper end is buckled to slider (19) direction, and the height of the part of buckling is the same with slider (19) upper end.
8. The sector combustor structure of claim 1, wherein: the double-layer pore plate structure is arranged on the left side wall and the right side wall of the flame tube (4).
9. The sector combustion chamber structure of claim 8, wherein: the double-layer pore plate structure comprises an inclined hole inner plate (22) and a straight hole outer plate (23), partition plates (24) are arranged at intervals between the edges of the inclined hole inner plate (22) and the edges of the straight hole outer plate (23), inclined air holes are distributed in the inclined hole inner plate (22), and straight air holes are distributed in the straight hole outer plate (23).
10. The sector combustor structure of claim 9, wherein: a strut (25) is also arranged between the inclined hole inner plate (22) and the straight hole outer plate (23).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210088019.0A CN114484498A (en) | 2022-01-25 | 2022-01-25 | Fan-shaped combustion chamber structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210088019.0A CN114484498A (en) | 2022-01-25 | 2022-01-25 | Fan-shaped combustion chamber structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114484498A true CN114484498A (en) | 2022-05-13 |
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ID=81475496
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210088019.0A Pending CN114484498A (en) | 2022-01-25 | 2022-01-25 | Fan-shaped combustion chamber structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114484498A (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002257334A (en) * | 2001-03-01 | 2002-09-11 | Natl Aerospace Lab | Combustion tester |
| US20040221582A1 (en) * | 2003-05-08 | 2004-11-11 | Howell Stephen John | Sector staging combustor |
| CN203259346U (en) * | 2013-04-09 | 2013-10-30 | 中国航空动力机械研究所 | Fan-shaped combustion chamber outlet measurement device |
| CN203615366U (en) * | 2013-12-12 | 2014-05-28 | 中航商用航空发动机有限责任公司 | Combustion chamber |
| CN105042640A (en) * | 2015-08-11 | 2015-11-11 | 南京航空航天大学 | Cooling structure of flame tube of aero-engine combustor |
| CN209774516U (en) * | 2019-03-14 | 2019-12-13 | 中国航发商用航空发动机有限责任公司 | Assembly tool for fuel header pipe |
| CN110763474A (en) * | 2018-07-25 | 2020-02-07 | 中国航发商用航空发动机有限责任公司 | Combustion chamber test device |
| CN111520760A (en) * | 2020-04-10 | 2020-08-11 | 西北工业大学 | Combustion chamber flame tube wall surface structure adopting impact/gas film double-wall composite cooling mode |
| CN111623991A (en) * | 2020-06-11 | 2020-09-04 | 杭州汽轮动力集团有限公司 | Igniter position adjusting mechanism for gas turbine combustion chamber test |
-
2022
- 2022-01-25 CN CN202210088019.0A patent/CN114484498A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002257334A (en) * | 2001-03-01 | 2002-09-11 | Natl Aerospace Lab | Combustion tester |
| US20040221582A1 (en) * | 2003-05-08 | 2004-11-11 | Howell Stephen John | Sector staging combustor |
| CN203259346U (en) * | 2013-04-09 | 2013-10-30 | 中国航空动力机械研究所 | Fan-shaped combustion chamber outlet measurement device |
| CN203615366U (en) * | 2013-12-12 | 2014-05-28 | 中航商用航空发动机有限责任公司 | Combustion chamber |
| CN105042640A (en) * | 2015-08-11 | 2015-11-11 | 南京航空航天大学 | Cooling structure of flame tube of aero-engine combustor |
| CN110763474A (en) * | 2018-07-25 | 2020-02-07 | 中国航发商用航空发动机有限责任公司 | Combustion chamber test device |
| CN209774516U (en) * | 2019-03-14 | 2019-12-13 | 中国航发商用航空发动机有限责任公司 | Assembly tool for fuel header pipe |
| CN111520760A (en) * | 2020-04-10 | 2020-08-11 | 西北工业大学 | Combustion chamber flame tube wall surface structure adopting impact/gas film double-wall composite cooling mode |
| CN111623991A (en) * | 2020-06-11 | 2020-09-04 | 杭州汽轮动力集团有限公司 | Igniter position adjusting mechanism for gas turbine combustion chamber test |
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Application publication date: 20220513 |