CN112050255B - Flame tube adopting clearance rotational flow cooling - Google Patents
Flame tube adopting clearance rotational flow cooling Download PDFInfo
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- CN112050255B CN112050255B CN202010988330.1A CN202010988330A CN112050255B CN 112050255 B CN112050255 B CN 112050255B CN 202010988330 A CN202010988330 A CN 202010988330A CN 112050255 B CN112050255 B CN 112050255B
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- flame tube
- spiral
- sheet body
- spiral sheet
- piece
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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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/56—Combustion chambers having rotary flame tubes
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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
- F23R3/28—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
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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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
Abstract
The invention belongs to the field of aeroengines, and relates to a flame tube cooled by gap rotational flow, wherein the main body of the flame tube is cup-shaped or cylindrical and comprises: the head part of each spiral sheet body is fixed on the same circular ring, and the tail part of each spiral sheet body is fixed on another circular ring and used for forming a main body of the flame tube; the fins are continuously distributed on the outer edge of the spiral sheet body and are used for enhancing the heat exchange efficiency between the spiral sheet body and cooling air; the oblique sheet bodies are continuously distributed on the inner edge of the spiral sheet body and are used for forming a cooling air film on the inner wall of the flame tube; wherein, be provided with the installation clearance between each spiral lamellar body. The invention can effectively reduce the occurrence of local high-temperature areas of the flame tube, greatly improve the cooling efficiency of the wall surface of the flame tube, thereby prolonging the service life of the flame tube, and the processing is simple and efficient.
Description
Technical Field
The invention belongs to the field of aero-engines, and relates to a flame tube cooled by clearance rotational flow.
Background
With the development of high-performance aircraft gas turbine engine technology, the improvement of the overall performance of aircraft engines puts higher demands on the design of main combustion chambers. The main combustion chamber is a device for converting chemical energy in gas into heat energy, and heating high-pressure air pressurized by the air compressor to a temperature allowed in front of the turbine so as to enter the turbine to do work. The flame tube is a main component of the combustion chamber and is one of the most important heat-receiving components of the engine, and the flame tube is the most faulty component in the combustion chamber and is a key component for limiting the service life of the engine.
Due to the development requirements of modern flame tube cooling technology, the structure of the flame tube becomes more and more complex. The flame tube is of an open-pore thin-wall structure, the geometric size difference of the tube body is large, and a plurality of cooling gas film holes and mixing holes with different apertures are formed in the tube wall so as to ensure that the cooling gas accounting for 20 percent of the total gas quantity enters from the side wall of the flame tube. The open pore structure is complex to process, so that a large temperature gradient exists in the temperature distribution of the flame tube, and the stress concentration phenomenon is easy to occur.
For a future high-temperature-rise combustion chamber, the inlet temperature and the outlet temperature of the combustion chamber greatly rise on the basis of the existing combustion chamber, the temperature rise and the heat capacity of the combustion chamber are obviously improved, and the stable working range of the combustion chamber is wider; however, as the temperature of the combustion chamber increases, fuel is required to be burnt under the condition of approaching the chemical correct ratio, so most of air entering the combustion chamber is used for combustion, the air quantity for cooling and mixing the wall surface is obviously reduced, and the reliable operation of the flame tube wall surface needs to be ensured under the condition of few relative cooling air quantity.
Disclosure of Invention
The invention provides a flame tube cooled by adopting clearance rotational flow, which can effectively reduce the occurrence of a local high-temperature area of the flame tube and greatly improve the cooling efficiency of cold air on the wall surface of the flame tube, thereby prolonging the service life of the flame tube and being simple and efficient to process.
In order to achieve the technical purpose, the invention adopts the following specific technical scheme:
a flame tube adopting clearance rotational flow cooling is characterized in that the main body of the flame tube is cup-shaped or cylindrical; the method comprises the following steps:
the head part of each spiral sheet body is fixed on the same circular ring, and the tail part of each spiral sheet body is fixed on another circular ring and used for forming a main body of the flame tube;
the fins are continuously distributed on the outer edge of the spiral sheet body and are used for enhancing the heat exchange efficiency between the spiral sheet body and cooling air;
the oblique sheet bodies are continuously distributed on the inner edge of the spiral sheet body and are used for forming a cooling air film on the inner wall of the flame tube;
wherein, be provided with the installation clearance between each spiral lamellar body.
Further, the rotation angle of the spiral sheet body is
The number of the spiral sheet bodies is 45-50.
Further, the installation clearance is 0.6-1.2 mm.
Furthermore, the included angle between the fins and the spiral sheet body is
The length of the spiral piece is 0.3-0.7 times of the width of the spiral piece.
Further, the inclined piece body comprises a flow deflector and a gas film forming piece which are fixedly connected, and the flow deflector is used for guiding cold air to the gas film forming piece in the axial direction of the flame tube; the film forming sheet is used for forming a cooling film on the inner wall of the flame tube.
Furthermore, the included angle of the flow deflector and the spiral sheet body is
The air film forming sheet is parallel to the spiral sheet body, and the distance between the air film forming sheet and the spiral sheet body is half of the shortest distance between the upper end part of the rib and the spiral sheet body.
Further, the oblique lamellar body still includes the transition piece, the transition piece sets up the water conservancy diversion piece with between the air film forms the piece, forms the water conservancy diversion piece with chamfer between the air film forms the piece.
Further, the width of the air film forming sheet is 1/6-1/5 of the width of the spiral body.
By adopting the technical scheme, the invention can bring the following beneficial effects:
the invention adopts a plurality of flame tubes with the main bodies of spiral sheet bodies, a gap is arranged between every two spiral sheet bodies, the outer side of each spiral sheet body is also provided with fins which can strengthen heat dissipation and flow guiding, and the inner side is provided with inclined sheet bodies which are used for guiding to form a cooling air model, thus achieving the following beneficial effects during the specific work:
1) the fins on the outer side of the flame tube can enhance the heat exchange of the wall surface of the flame tube and cold air of the cooling channel, and the inclined fin structure on the inner side can generate a cooling air film which is more uniform and has a certain rotation direction, so that the uniformity of a temperature field near the wall surface of a combustion chamber can be promoted while the cooling efficiency is greatly improved, and the generation of a local high-temperature area is effectively avoided, thereby prolonging the service life of the flame tube.
2) The flame tube assembled by the split spiral sheets can provide buffering and damping effects on abnormal vibration of the combustion chamber.
3) Compared with the traditional combustor flame tube, the combustor flame tube only needs to be processed separately and assembled by sheet bodies, and the production efficiency can be greatly improved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a schematic cross-sectional view of the outer ring of the flame tube of the present invention taken perpendicular to the axial direction;
FIG. 2 is a schematic cross-sectional view of the unit bodies constituting the combustor basket;
fig. 3 is a sectional view of an installation structure of an example of the present invention.
1-a helical sheet body; 2-ribs; 3-oblique sheet body; 4-front end annular mounting seat; 5-rear annular mounting seat; 6-a diffuser; 7-a swirler; 8-casing.
Detailed Description
Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
The embodiments of the present invention are described below with reference to specific embodiments, and other advantages and effects of the present invention will be easily understood by those skilled in the art from the disclosure of the present specification. It is to be understood that the described embodiments are merely exemplary of the invention, and not restrictive of the full scope of the invention. The invention is capable of other and different embodiments and of being practiced or of being carried out in various ways, and its several details are capable of modification in various respects, all without departing from the spirit and scope of the present invention. It is to be noted that the features in the following embodiments and examples may be combined with each other without conflict. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It is noted that various aspects of the embodiments are described below within the scope of the appended claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the disclosure, one skilled in the art should appreciate that one aspect described herein may be implemented independently of any other aspects and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. Additionally, such an apparatus may be implemented and/or such a method may be practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
It should be noted that the drawings provided in the following embodiments are only for illustrating the basic idea of the present invention, and the drawings only show the components related to the present invention rather than the number, shape and size of the components in practical implementation, and the type, quantity and proportion of the components in practical implementation can be changed freely, and the layout of the components can be more complicated.
In addition, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects may be practiced without these specific details.
The embodiment of the invention provides a flame tube adopting clearance rotational flow cooling, wherein the main body of the flame tube is cup-shaped or cylindrical; as shown in fig. 3, includes:
the head part of each spiral sheet body 1 is fixed on the same circular ring, and the tail part of each spiral sheet body 1 is fixed on another circular ring and used for forming a main body of the flame tube;
the fins 2 are continuously distributed on the outer edge of the spiral sheet body 1 and are used for enhancing the heat exchange efficiency between the spiral sheet body 1 and cooling air;
the oblique sheet bodies 3 are continuously distributed on the inner edge of the spiral sheet body 1 and used for forming a cooling air film on the inner wall of the flame tube;
wherein, an installation gap is arranged between each spiral sheet body 1.
In this embodiment, all be provided with fin 2 and the flight body 3 on every spiral lamellar body 1, fin 2 and the flight body 3 extend and set up on each side of flight body 3, and fin 2 and flight body 3 are the flight structure, extend and set up on flight body 1, for convenient processing three structure as an organic whole, fin 2 is in air conditioning one side, and the flight body 3 sets up at the flame tube inner wall.
In the present embodiment, as shown in fig. 3, the head portion of each spiral sheet 1 is disposed in the front annular mounting seat 4, and the tail portion is disposed in the rear annular mounting seat 5, and after the installation is completed, as shown in fig. 1, the head portion and the tail portion of each spiral sheet 1 form an annular shape; meanwhile, the front end annular mounting seat 4 is arranged at the front end of the casing 8, a swirler 7 is arranged at the upstream, and the outlet of a diffuser 6 on the swirler 7 is arranged in the flame tube; the rear annular mount 5 is disposed at the rear end of the case 8.
In one embodiment, the rotation angle of the spiral sheet 1 is
The number of the spiral sheet bodies 1 is 45-50.
In one embodiment, the mounting gap is 0.6-1.2 mm.
In one embodiment of the present invention,as shown in FIG. 2, the included angle between the fins 2 and the spiral sheet body 1 is
The length of the spiral piece body is 0.3-0.7 times of the width of the spiral piece body 1.
In one embodiment, as shown in fig. 2, the swash plate body 3 includes a fixedly connected guide plate and a film forming plate, the guide plate is used for guiding the cold air to the film forming plate in the axial direction of the liner; the film forming sheet is used for forming a cooling film on the inner wall of the flame tube.
In one embodiment, as shown in fig. 2, the included angle of the spiral sheet body 1 of the flow deflector is
The air film forming sheet is parallel to the spiral sheet body 1, and the distance between the air film forming sheet and the spiral sheet body 1 is half of the shortest distance between the upper end part of the fin 2 and the spiral sheet body 1.
In one embodiment, as shown in fig. 2, the swash plate body 3 further includes a transition piece disposed between the guide plate and the film forming plate to form a chamfer therebetween.
In one embodiment, as shown in FIG. 2, the width of the film forming sheet is 1/6-1/5 of the width of the spiral.
The above description is only for the specific embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (8)
1. A flame tube adopting clearance rotational flow cooling is characterized in that the main body of the flame tube is cup-shaped or cylindrical; it is characterized by comprising:
the head part of each spiral sheet body is fixed on the same circular ring, and the tail part of each spiral sheet body is fixed on another circular ring and used for forming a main body of the flame tube;
the fins are continuously distributed on the outer edge of the spiral sheet body and are used for enhancing the heat exchange efficiency between the spiral sheet body and cooling air;
the oblique sheet bodies are continuously distributed on the inner edge of the spiral sheet body and are used for forming a cooling air film on the inner wall of the flame tube;
wherein, be provided with the installation clearance between each spiral lamellar body.
2. The flame tube of claim 1, wherein: the rotation angle of the spiral sheet body is
The number of the spiral sheet bodies is 45-50.
3. The flame tube of claim 1, wherein: the installation clearance is 0.6-1.2 mm.
4. The flame tube of claim 1, wherein: the included angle between the fins and the spiral sheet body is
The length of the spiral piece is 0.3-0.7 times of the width of the spiral piece.
5. The flame tube of claim 1, wherein: the inclined piece body comprises a flow guide piece and a gas film forming piece which are fixedly connected, and the flow guide piece is used for guiding cold air to the gas film forming piece in the axial direction of the flame tube; the film forming sheet is used for forming a cooling film on the inner wall of the flame tube.
6. The combustor basket of claim 5, wherein: the included angle of the flow deflector and the spiral sheet body is
The air film forming sheet is parallel to the spiral sheet body, and the distance between the air film forming sheet and the spiral sheet body is half of the shortest distance between the upper end part of the rib and the spiral sheet body.
7. The combustor basket of claim 5, wherein: the oblique lamellar body still includes the transition piece, the transition piece sets up the water conservancy diversion piece with between the air film forms the piece, forms the water conservancy diversion piece with chamfer between the air film forms the piece.
8. The combustor basket of claim 5, wherein: the width of the air film forming sheet is 1/6-1/5 of the width of the spiral sheet body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010988330.1A CN112050255B (en) | 2020-09-18 | 2020-09-18 | Flame tube adopting clearance rotational flow cooling |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010988330.1A CN112050255B (en) | 2020-09-18 | 2020-09-18 | Flame tube adopting clearance rotational flow cooling |
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| Publication Number | Publication Date |
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| CN112050255A CN112050255A (en) | 2020-12-08 |
| CN112050255B true CN112050255B (en) | 2022-04-22 |
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| CN202010988330.1A Active CN112050255B (en) | 2020-09-18 | 2020-09-18 | Flame tube adopting clearance rotational flow cooling |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113483361A (en) * | 2021-08-18 | 2021-10-08 | 中国联合重型燃气轮机技术有限公司 | Combustor liner for gas turbine and gas turbine |
| CN113483362B (en) * | 2021-08-18 | 2023-06-16 | 中国联合重型燃气轮机技术有限公司 | Flame tube and gas turbine |
| CN115247575A (en) * | 2022-05-12 | 2022-10-28 | 中国航发四川燃气涡轮研究院 | Spiral turbine blade cooling unit and cooling structure |
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| ES2307834T3 (en) * | 2003-01-29 | 2008-12-01 | Siemens Aktiengesellschaft | COMBUSTION CHAMBER. |
| CN204227467U (en) * | 2014-10-28 | 2015-03-25 | 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 flame combustion chamber barrel structure |
| CN105423344A (en) * | 2016-01-12 | 2016-03-23 | 西北工业大学 | Flame tube structure of combustion chamber of ground gas turbine |
| CN105650680A (en) * | 2016-01-19 | 2016-06-08 | 西北工业大学 | Head design of combustion chamber of twin-stage premixing ground-based gas turbine |
| CN108317542A (en) * | 2018-01-03 | 2018-07-24 | 南方科技大学 | The cooling structure of aeroengine combustor buring room and aeroengine combustor buring room |
| CN109340825A (en) * | 2018-09-20 | 2019-02-15 | 西北工业大学 | A kind of flame combustion chamber tube wall surface using novel convex wall inclined hole |
| CN208566749U (en) * | 2018-06-05 | 2019-03-01 | 中国航发沈阳发动机研究所 | A kind of burner inner liner outer wall construction |
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2020
- 2020-09-18 CN CN202010988330.1A patent/CN112050255B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ES2307834T3 (en) * | 2003-01-29 | 2008-12-01 | Siemens Aktiengesellschaft | COMBUSTION CHAMBER. |
| CN204227467U (en) * | 2014-10-28 | 2015-03-25 | 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 flame combustion chamber barrel structure |
| CN105423344A (en) * | 2016-01-12 | 2016-03-23 | 西北工业大学 | Flame tube structure of combustion chamber of ground gas turbine |
| CN105650680A (en) * | 2016-01-19 | 2016-06-08 | 西北工业大学 | Head design of combustion chamber of twin-stage premixing ground-based gas turbine |
| CN108317542A (en) * | 2018-01-03 | 2018-07-24 | 南方科技大学 | The cooling structure of aeroengine combustor buring room and aeroengine combustor buring room |
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| CN112050255A (en) | 2020-12-08 |
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