CN113154445A - Combustor import rectification structure - Google Patents
Combustor import rectification structure Download PDFInfo
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- CN113154445A CN113154445A CN202110439426.7A CN202110439426A CN113154445A CN 113154445 A CN113154445 A CN 113154445A CN 202110439426 A CN202110439426 A CN 202110439426A CN 113154445 A CN113154445 A CN 113154445A
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- rectifying
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- rectification
- combustor
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- 230000008676 import Effects 0.000 title claims description 3
- 230000007704 transition Effects 0.000 claims abstract description 47
- 238000000034 method Methods 0.000 claims description 10
- 239000000295 fuel oil Substances 0.000 claims description 3
- 230000000694 effects Effects 0.000 abstract description 13
- 239000012530 fluid Substances 0.000 abstract description 4
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 238000002485 combustion reaction Methods 0.000 description 6
- 239000002131 composite material Substances 0.000 description 2
- 230000001788 irregular Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
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Classifications
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- 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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to a combustor inlet rectifying structure, which comprises a volute, a transition section, a combustor and a rectifying structure, wherein the volute is arranged on the combustor inlet; the volute is connected with one end of the transition section, the other end of the transition section is connected with the combustor, a rectifying structure is arranged in an area with large air flow at the joint of the transition section and the combustor, the rectifying structure comprises a rectifying plate, a rectifying positioning hole and a rectifying air hole, and the rectifying positioning hole and the rectifying air hole are located on the rectifying plate. The invention has the beneficial effects that: the rectifying structure is provided with the rectifying air holes, so that a better rectifying effect can be realized on the fluid with poor circumferential uniformity; the two-stage rectifying plate structure is arranged in an area with large air flow, the circumferential positions of the two-stage rectifying plate can be freely adjusted through the positioning holes, and the air rectifying holes in the two-stage rectifying plate structure are distributed in a staggered manner, so that a good rectifying effect can be realized on the premise of keeping small pressure loss; no rectifying structure is arranged in the area with small air flow, so that the smooth flow is kept.
Description
Technical Field
The invention relates to a rectifying structure, in particular to a rectifying structure for an inlet of a combustor.
Background
For small and medium-sized gas turbines, one or two single-tube combustor structures are generally adopted for simple maintenance and cost reduction. The burner can be upright or horizontal above and to the side of the combustion engine, the central axis of the burner being perpendicular to the engine axis. The compressor is usually of the centrifugal or axial type, and the outlet flow of the compressor is parallel to the axis of the engine. Therefore, high-pressure airflow at the outlet of the gas compressor can enter the combustor to participate in combustion only after turning by 90 degrees, and the circumferential distribution of the airflow at the annular cavity channel at the inlet of the combustor is not uniform, the flow of the annular cavity area with large turning radius is large, the flow of the annular cavity area with small turning radius is small, and the circumferential uniformity is poor. Non-uniformity of combustor inlet flow can seriously affect the local equivalence ratio distribution in the flame tube, resulting in NOXThe emissions increase and the burner outlet temperature distribution worsens. Therefore, a flow straightener structure must be employed to adjust the circumferential uniformity of the inlet airflow flow.
The traditional gas rectifier is divided into a plate rectifier and a sheet rectifier, and the two rectifiers are widely used for guiding gas and adjusting the speed distribution form. However, both are mostly designed for round or square pipes, and the design for the annular pipe is less. And the simple plate-shaped and sheet-shaped structures hardly have good rectification effect on the fluid with poor circumferential uniformity.
Disclosure of Invention
The invention aims to overcome the defects in the prior art and provides a combustor inlet rectifying structure.
The combustor inlet rectifying structure comprises a volute, a transition section, a combustor and a rectifying structure; the volute is connected with one end of the transition section, the other end of the transition section is connected with the combustor, a rectifying structure is arranged in an area with large air flow at the joint of the transition section and the combustor, the rectifying structure comprises a rectifying plate, a rectifying positioning hole and a rectifying air hole, and the rectifying positioning hole and the rectifying air hole are located on the rectifying plate.
Preferably, the method comprises the following steps: the rectifying plate comprises a first-stage rectifying plate and a second-stage rectifying plate, the rectifying positioning hole comprises a first-stage rectifying positioning hole and a second-stage rectifying positioning hole, the rectifying air hole comprises a first-stage rectifying air hole and a second-stage rectifying air hole, the first-stage rectifying positioning hole and the first-stage rectifying air hole are positioned on the first-stage rectifying plate, and the second-stage rectifying positioning hole and the second-stage rectifying air hole are positioned on the second-stage rectifying plate; the first-stage rectifying plate and the second-stage rectifying plate are both of fan-shaped structures, the coverage area is 90-270 degrees, and the axial interval between the first-stage rectifying plate and the second-stage rectifying plate is 10-50 mm.
Preferably, the method comprises the following steps: the plurality of first-stage rectification positioning holes are uniformly distributed in the circumferential direction at the position with larger radius of the first-stage rectification plate, and the circumferential interval between every two adjacent first-stage rectification positioning holes is 10-30 degrees; the plurality of first-stage rectification air holes are uniformly distributed in the circumferential direction at the positions with smaller radius of the first-stage rectification plate, and the circumferential interval between every two adjacent first-stage rectification air holes is 2-6 degrees.
Preferably, the method comprises the following steps: the two rows of primary rectification air holes distributed in a staggered manner are arranged, and the primary rectification air holes are identical in shape and size.
Preferably, the method comprises the following steps: the first-stage rectification air holes comprise air holes with large sizes and air holes with small sizes, the air holes with large sizes are distributed in two rows of fork rows, and the air holes with small sizes are arranged in the gaps of the air holes with large sizes.
Preferably, the method comprises the following steps: the plurality of second-stage rectification positioning holes are uniformly distributed in the circumferential direction at the position with larger radius of the second-stage rectification plate, and the circumferential interval between every two adjacent second-stage rectification positioning holes is 10-30 degrees; the secondary rectification air holes are uniformly distributed in the circumferential direction at the positions with smaller radius of the secondary rectification plate, the circumferential interval between two adjacent secondary rectification air holes is 2-6 degrees, and the secondary rectification air holes and the primary rectification air holes are distributed in a staggered manner.
Preferably, the method comprises the following steps: two rows of secondary rectification air holes distributed in a staggered manner are arranged, and the shapes and the sizes of the secondary rectification air holes are the same.
Preferably, the method comprises the following steps: the two-stage rectification air holes comprise air holes with larger sizes and air holes with smaller sizes, the air holes with larger sizes are arranged in two rows of staggered rows, and the air holes with smaller sizes are arranged in the gap of the air holes with larger sizes.
Preferably, the method comprises the following steps: the first-stage rectification positioning hole on the first-stage rectification plate is in positioning connection with the transition section rectification plate positioning hole on the outer wall of the transition section through a screw; and the second-stage rectification positioning hole on the second-stage rectification plate is in positioning connection with the combustor rectification plate positioning hole on the outer wall of the combustor through a screw.
The method for rectifying the inlet rectifying structure of the combustor comprises the steps that high-pressure air discharged from a gas compressor enters a volute outer cavity, wherein most of the air enters the combustor outer cavity through a transition section outer cavity, and is rectified by a first-stage rectifying plate and a second-stage rectifying plate in sequence in a region with large air flow at the inlet of the combustor outer cavity, then the air is fully and uniformly mixed with fuel oil in a combustor inner cavity and then enters the volute inner cavity through the transition section inner cavity, and finally enters a turbine to do work.
The invention has the beneficial effects that:
1. the rectifying structure is provided with the rectifying air holes, so that a better rectifying effect can be realized on the fluid with poor circumferential uniformity. The two-stage rectifying plate structure is arranged in an area with large air flow, the circumferential positions of the two-stage rectifying plate can be freely adjusted through the positioning holes, and the air rectifying holes in the two-stage rectifying plate structure are distributed in a staggered manner, so that a good rectifying effect can be realized on the premise of keeping small pressure loss; no rectifying structure is arranged in the area with small air flow, so that the smooth flow is kept.
2. The rectifying positioning holes on the rectifying structure are uniformly distributed along the circumferential direction, the angle position can be freely adjusted, the assembly and disassembly are convenient, the structure is reasonable, and the pressure loss is small.
Drawings
FIG. 1 is a partial perspective view of a combustion engine;
FIG. 2 is a partial cross-sectional view of a combustion engine;
FIG. 3 is a schematic view of a burner inlet (with inlet fairing);
FIG. 4 is a schematic view of a fairing installation;
FIG. 5 is a schematic view of a rectifying structure;
fig. 6 is a schematic view of a rectifying structure (another alternative embodiment).
Description of reference numerals: 1, a volute; 11, the outer wall of the volute; 12 a volute outer cavity; 13, inner wall of the volute; 14 a volute inner cavity; 2, a transition section; 21 transition section outer wall; 22 transition section outer cavity; 23 transition section inner wall; 24 inner cavity of transition section; 3, a burner; 31 a burner outer wall; 32 a burner outer cavity; 33 inner wall of the burner; 34 an inner burner cavity; 35 combustor flange bolt holes; 36 combustor fairing locating holes; 4, a rectifying structure; 41 a first-stage rectifying plate; 42 a two-stage rectifying plate; 43 primary rectification positioning holes; 44 secondary rectification positioning holes; 45 primary rectifying air holes; 46 two-stage rectification air holes.
Detailed Description
The present invention will be further described with reference to the following examples. The following examples are set forth merely to aid in the understanding of the invention. It should be noted that, for those skilled in the art, it is possible to make various improvements and modifications to the present invention without departing from the principle of the present invention, and those improvements and modifications also fall within the scope of the claims of the present invention.
Example one
The combustor inlet rectifying structure can achieve a good rectifying effect on fluid with poor circumferential uniformity, and is capable of freely adjusting angles, convenient to assemble and disassemble, reasonable in structure and small in pressure loss. The volute 1 is connected with one end of the transition section 2, the other end of the transition section 2 is connected with the combustor 3, a rectifying structure 4 is arranged in an area with large air flow at the joint of the transition section 2 and the combustor 3, the rectifying structure 4 comprises a first-stage rectifying plate 41, a second-stage rectifying plate 42, a first-stage rectifying positioning hole 43, a second-stage rectifying positioning hole 44, a first-stage rectifying air hole 45 and a second-stage rectifying air hole 46, the first-stage rectifying positioning hole 43 and the first-stage rectifying air hole 45 are located on the first-stage rectifying plate 41, and the second-stage rectifying positioning hole 44 and the second-stage rectifying air hole 46 are located on the second-stage rectifying plate 42. The volute 1 comprises a volute outer wall 11, a volute outer cavity 12, a volute inner wall 13 and a volute inner cavity 14, the volute outer cavity 12 is arranged between the volute outer wall 11 and the volute inner wall 13, and the volute inner cavity 14 is arranged inside the volute inner wall 13. The transition section 2 comprises a transition section outer wall 21, a transition section outer cavity 22, a transition section inner wall 23 and a transition section inner cavity 24, the transition section outer cavity 22 is arranged between the transition section outer wall 21 and the transition section inner wall 23, the transition section inner wall 23 is internally provided with the transition section inner cavity 24, and a transition section rectifying plate positioning hole is formed in the transition section outer wall 21. The combustor 3 comprises a combustor outer wall 31, a combustor outer cavity 32, a combustor inner wall 33, a combustor inner cavity 34, a combustor flange bolt hole 35 and a combustor fairing positioning hole 36, the combustor outer cavity 32 is arranged between the combustor outer wall 31 and the combustor inner wall 33, the combustor inner wall 33 is internally provided with the combustor inner cavity 34, the combustor outer wall 31 is provided with the combustor fairing positioning hole 36, and the flange of the combustor 3 is provided with the combustor flange bolt hole 35.
As a preferred embodiment, the first-stage rectifying plate 41 and the second-stage rectifying plate 42 are both fan-shaped structures, the coverage area is 90-270 degrees, the axial interval between the first-stage rectifying plate 41 and the second-stage rectifying plate 42 is 10-50mm, and the structures of the first-stage rectifying plate 41 and the second-stage rectifying plate 42 are the same.
As a preferred embodiment, a plurality of first-stage rectification positioning holes 43 are uniformly distributed in the circumferential direction at the position with larger radius of the first-stage rectification plate 41, and the circumferential interval between two adjacent first-stage rectification positioning holes 43 is 10-30 degrees. The plurality of first-stage rectification air holes 45 are circumferentially and uniformly distributed at positions with smaller radius of the first-stage rectification plate 41, and two adjacent first-stage rectification air holes 45 are circumferentially spaced by 2-6 degrees.
As a more specific example, as shown in fig. 5, two rows of primary rectification air holes 45 arranged in a staggered manner are provided, and the primary rectification air holes 45 have the same shape and size, but the shape is not limited to the above shape, and may be circular, oval, drop-shaped, rectangular, or irregular, and is circular as shown in fig. 5. As an alternative embodiment, as shown in fig. 6, the primary rectification air holes 45 include air holes with a larger size and air holes with a smaller size, the air holes with a larger size are arranged in two rows of staggered rows, and the air holes with a smaller size are arranged at the gap between the air holes with a larger size, so that the pressure loss is reduced as much as possible while the rectification effect is ensured.
In a preferred embodiment, the second-stage rectification positioning holes 44 are uniformly distributed in the circumferential direction at the positions with larger radius of the second-stage rectification plate 42, and the circumferential interval between two adjacent second-stage rectification positioning holes 44 is 10-30 degrees. The secondary rectification air holes 46 are circumferentially and uniformly distributed at positions with smaller radius of the secondary rectification plate 42, and two adjacent secondary rectification air holes 46 are circumferentially spaced by 2-6 degrees and are distributed in a staggered manner (namely staggered) with the primary rectification air holes 45 to ensure the rectification effect.
As a more specific example, as shown in fig. 5, two rows of secondary straightening air holes 46 are arranged in a staggered manner, and the secondary straightening air holes 46 have the same shape and size, but the shape is not limited to the above shape, and may be circular, oval, drop-shaped, rectangular, or irregular, and is circular as shown in fig. 5. As an alternative embodiment, as shown in fig. 6, the secondary rectification air holes 46 include air holes with larger size and air holes with smaller size, the air holes with larger size are arranged in two rows of staggered rows, and the air holes with smaller size are arranged at the gap of the air holes with larger size, so that the pressure loss is reduced as much as possible while the rectification effect is ensured.
As a preferred embodiment, the first-stage rectification positioning hole 43 on the first-stage rectification plate 41 is connected with the transition section rectification plate positioning hole on the transition section outer wall 21 through screw positioning; the second-stage rectification positioning hole 44 on the second-stage rectification plate 42 is in positioning connection with the combustor rectification plate positioning hole 36 on the combustor outer wall 31 through a screw.
Example two
The high-pressure air from the compressor enters the volute outer cavity 12 between the volute outer wall 11 and the volute inner wall 13, wherein most of the air enters the combustor outer cavity 32 through the transition section outer cavity 22, is fully mixed and combusted with fuel oil in the combustor inner cavity 34, then enters the volute inner cavity 14 through the transition section inner cavity 24, and finally enters the turbine to do work. When the high-pressure air enters the transition section outer cavity 22 from the volute outer cavity 12, the high-pressure air flow deflects by 90 degrees, so that the high-pressure air flow is seriously unevenly distributed in the inner circumference of the transition section outer cavity 22, the air flow in a region with a small turning radius is small, and the air flow in a region with a large turning radius is large. The conventional rectifier is difficult to realize a good rectification effect. The air entering the combustor outer cavity 32 from the transition section outer cavity 22 is rectified through the combustor inlet rectifying structure, and the circumferential uniformity of the air in the annular cavity is improved through the rectifying air holes distributed in the staggered manner.
The composite rectifier structure provided by the invention can realize better rectification effect on air flow with poor uniformity in the annular cavity, has a reasonable structure and is convenient to install, the two-stage rectifier plate structure is arranged in the annular cavity area with large air flow, the circumferential position of the two-stage rectifier plate can be freely adjusted through the positioning hole, and the adjustment has two layers of adjustment: the adjusting device comprises a first rectifying plate, a second rectifying plate and a third rectifying plate, wherein the first rectifying plate is used for adjusting the position of the combustion engine (namely the area with large air flow), and the second rectifying plate is used for adjusting the relative angle position between the first rectifying plate and the second rectifying plate so as to determine the size of the overlapping area of the first rectifying plate and the second rectifying plate. Air rectification holes in the double-stage rectifier plate structure are distributed in a staggered mode, and a good rectification effect can be achieved on the premise that small pressure loss is kept. No rectifying structure is arranged in the area with small air flow, so that the smooth flow is kept. After passing through the composite rectifying structure, the circumferential uniformity of the air in the annular cavity is greatly improved, the uniform combustion in the cavity of the combustor is promoted, and NO is reducedXAnd (4) discharging, and improving the temperature distribution at the outlet of the combustor. Traditional rectification structure adopts the full ring structure usually, and the fan-shaped structure of this patent, and this patent has abandoned the even characteristics that set up in traditional rectification structure, adopts the form as simple as possible to reach good effect.
Claims (10)
1. A combustor import rectification structure which characterized in that: the device comprises a volute (1), a transition section (2), a combustor (3) and a rectifying structure (4); one end of a transition section (2) is connected with a volute (1), the other end of the transition section (2) is connected with a combustor (3), a rectifying structure (4) is arranged in a region with large air flow at the joint of the transition section (2) and the combustor (3), the rectifying structure (4) comprises a rectifying plate, a rectifying positioning hole and a rectifying air hole, and the rectifying positioning hole and the rectifying air hole are located on the rectifying plate.
2. The combustor inlet fairing structure of claim 1, wherein: the rectifying plate comprises a first-stage rectifying plate (41) and a second-stage rectifying plate (42), the rectifying positioning holes comprise a first-stage rectifying positioning hole (43) and a second-stage rectifying positioning hole (44), the rectifying air holes comprise a first-stage rectifying air hole (45) and a second-stage rectifying air hole (46), the first-stage rectifying positioning hole (43) and the first-stage rectifying air hole (45) are located on the first-stage rectifying plate (41), and the second-stage rectifying positioning hole (44) and the second-stage rectifying air hole (46) are located on the second-stage rectifying plate (42); the first-stage rectifying plate (41) and the second-stage rectifying plate (42) are both of fan-shaped structures, the coverage area is 90-270 degrees, and the axial interval between the first-stage rectifying plate (41) and the second-stage rectifying plate (42) is 10-50 mm.
3. The combustor inlet fairing structure of claim 2, wherein: the plurality of first-stage rectification positioning holes (43) are uniformly distributed in the circumferential direction at the position with larger radius of the first-stage rectification plate (41), and the circumferential interval between every two adjacent first-stage rectification positioning holes (43) is 10-30 degrees; the primary rectification air holes (45) are uniformly distributed in the circumferential direction at the positions with smaller radius of the primary rectification plate (41), and the circumferential interval between every two adjacent primary rectification air holes (45) is 2-6 degrees.
4. The combustor inlet fairing structure of claim 3, wherein: the primary rectifying air holes (45) distributed in two rows of the fork rows are arranged, and the primary rectifying air holes (45) are identical in shape and size.
5. The combustor inlet fairing structure of claim 3, wherein: the first-stage rectification air holes (45) comprise air holes with large sizes and air holes with small sizes, the air holes with large sizes are arranged in two rows of staggered rows, and the air holes with small sizes are arranged in the gaps of the air holes with large sizes.
6. The combustor inlet fairing structure of claim 2, wherein: the secondary rectification positioning holes (44) are uniformly distributed in the circumferential direction at the positions with larger radius of the secondary rectification plate (42), and the circumferential interval between every two adjacent secondary rectification positioning holes (44) is 10-30 degrees; the secondary rectification air holes (46) are uniformly distributed in the circumferential direction at the positions with smaller radius of the secondary rectification plate (42), two adjacent secondary rectification air holes (46) are circumferentially spaced by 2-6 degrees, and the secondary rectification air holes (46) and the primary rectification air holes (45) are distributed in a staggered manner.
7. The combustor inlet fairing structure of claim 6, wherein: two rows of secondary rectification air holes (46) which are distributed in a staggered manner are arranged, and the shapes and the sizes of the secondary rectification air holes (46) are the same.
8. The combustor inlet fairing structure of claim 6, wherein: the two-stage rectification air holes (46) comprise air holes with larger sizes and air holes with smaller sizes, the air holes with larger sizes are arranged in two rows of staggered rows, and the air holes with smaller sizes are arranged at the gap of the air holes with larger sizes.
9. The combustor inlet fairing structure of claim 1, wherein: a first-stage rectification positioning hole (43) on the first-stage rectification plate (41) is in positioning connection with a transition section rectification plate positioning hole on the transition section outer wall (21) through a screw; the second-stage rectification positioning hole (44) on the second-stage rectification plate (42) is in positioning connection with the combustor rectification plate positioning hole (36) on the combustor outer wall (31) through a screw.
10. A method of fairing a combustor inlet fairing as recited in claim 1, further comprising: the high-pressure air from the compressor enters the volute outer cavity (12), wherein most of the air enters the combustor outer cavity (32) through the transition section outer cavity (22), is rectified by the first-stage rectifying plate (41) and the second-stage rectifying plate (42) in sequence in the area with larger air flow at the inlet of the combustor outer cavity (32), is fully and uniformly mixed with fuel oil in the combustor inner cavity (34), is combusted, enters the volute inner cavity (14) through the transition section inner cavity (24), and finally enters the turbine to do work.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110439426.7A CN113154445A (en) | 2021-04-23 | 2021-04-23 | Combustor import rectification structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110439426.7A CN113154445A (en) | 2021-04-23 | 2021-04-23 | Combustor import rectification structure |
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| CN113154445A true CN113154445A (en) | 2021-07-23 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110439426.7A Pending CN113154445A (en) | 2021-04-23 | 2021-04-23 | Combustor import rectification structure |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102562309A (en) * | 2010-12-21 | 2012-07-11 | 株式会社东芝 | Transition piece and gas turbine |
| CN204438185U (en) * | 2014-12-19 | 2015-07-01 | 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 chamber water conservancy diversion lining |
| CN106286007A (en) * | 2016-09-23 | 2017-01-04 | 北京动力机械研究所 | A kind of gas collection ring cavity rectifier structure improving cooling edema caused by disorder of QI cloth |
| CN207554125U (en) * | 2017-12-14 | 2018-06-29 | 中国航发沈阳发动机研究所 | Large flow-rate gas stream turnover rectification volute casing device |
| CN109724109A (en) * | 2017-10-30 | 2019-05-07 | 斗山重工业建设有限公司 | Fuel nozzle, burner and gas turbine comprising it |
| CN112197294A (en) * | 2020-09-21 | 2021-01-08 | 中国航发沈阳发动机研究所 | Rectifying plate |
| CN214745903U (en) * | 2021-04-23 | 2021-11-16 | 浙江浙能技术研究院有限公司 | Combustor inlet rectifying structure |
-
2021
- 2021-04-23 CN CN202110439426.7A patent/CN113154445A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102562309A (en) * | 2010-12-21 | 2012-07-11 | 株式会社东芝 | Transition piece and gas turbine |
| CN204438185U (en) * | 2014-12-19 | 2015-07-01 | 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 chamber water conservancy diversion lining |
| CN106286007A (en) * | 2016-09-23 | 2017-01-04 | 北京动力机械研究所 | A kind of gas collection ring cavity rectifier structure improving cooling edema caused by disorder of QI cloth |
| CN109724109A (en) * | 2017-10-30 | 2019-05-07 | 斗山重工业建设有限公司 | Fuel nozzle, burner and gas turbine comprising it |
| CN207554125U (en) * | 2017-12-14 | 2018-06-29 | 中国航发沈阳发动机研究所 | Large flow-rate gas stream turnover rectification volute casing device |
| CN112197294A (en) * | 2020-09-21 | 2021-01-08 | 中国航发沈阳发动机研究所 | Rectifying plate |
| CN214745903U (en) * | 2021-04-23 | 2021-11-16 | 浙江浙能技术研究院有限公司 | Combustor inlet rectifying structure |
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Application publication date: 20210723 |