CN109210573B - Novel variable cross-section aeroengine combustion chamber - Google Patents
Novel variable cross-section aeroengine combustion chamber Download PDFInfo
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- CN109210573B CN109210573B CN201810909112.7A CN201810909112A CN109210573B CN 109210573 B CN109210573 B CN 109210573B CN 201810909112 A CN201810909112 A CN 201810909112A CN 109210573 B CN109210573 B CN 109210573B
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- combustion chamber
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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
- F23R3/58—Cyclone or vortex type combustion chambers
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Combustion Methods Of Internal-Combustion Engines (AREA)
Abstract
The invention discloses a novel variable-section aeroengine combustion chamber, which comprises a front blunt body, a concave cavity and a rear blunt body which are arranged in the combustion chamber, wherein the positions of the front blunt body and the rear blunt body in the combustion chamber are respectively a front combustion chamber and a rear combustion chamber; the concave cavity is formed between the front blunt body and the rear blunt body, a folding angle is arranged on the gas channel, and the jet hole with the cyclone is arranged on the side surface of the rear blunt body parallel to the combustion chamber channel, so that the problems existing in the existing combustion chamber can be optimized, and the efficient combustion, low emission and low total pressure loss are realized.
Description
Technical Field
The invention belongs to the field of aero-engine combustion chambers, and particularly relates to a novel variable-section aero-engine combustion chamber.
Background
In recent years, the civil aviation industry has rapidly developed and the development of aeroengines has been strived towards high thrust, low emissions. Currently, low emission combustors are mainly studied in Trapped Vortex Combustors (TVCs), which have the advantages of higher combustion efficiency, lower pollutant emissions, lower temperature rise in the combustors, and lower total pressure loss. However, if the above advantages are to be achieved, the ideal conditions of TVC operation, such as rapid and uniform mixing of oil and gas, formation of ideal double vortex structure in the cavity, etc., are to be satisfied.
In order to realize the ideal double-vortex structure, a learner proposes to spray the oil-gas mixture on the upper part of the front wall surface of the concave cavity and spray air on the middle part of the rear wall surface, but the spraying speed of the air and the oil gas is difficult to control at a better level. In addition, scholars propose a TVC using a flow deflector and a rear blunt body, and use the flow deflector to introduce a part of the oil gas in the main flow into the cavity to form a more ideal double vortex structure, and then use the turbulence effect of the rear blunt body to make the oil gas be mixed more uniformly, but the cavity is a more complex component, the size of which has a great influence on the combustion performance, and especially the TVC spraying oil gas and air on the front and rear walls is more difficult to realize. In addition, there are combustion chambers without using a concave cavity, and although the combustion chamber is provided with a deflector and a rear blunt body, the mixing degree of oil gas in the flowing process is still low, so that the combustion efficiency is low, and meanwhile, uneven temperature distribution in a combustion area is easily caused, so that the reduction of emission is not facilitated.
Disclosure of Invention
According to the defects and the shortcomings of the prior art, the invention provides a novel variable cross-section aeroengine combustion chamber, and aims to avoid using a concave cavity with a complex structure, optimize the problems existing in the existing combustion chamber and realize efficient combustion, low emission and low total pressure loss.
The novel variable-section aeroengine combustion chamber comprises a front blunt body, a concave cavity and a rear blunt body which are arranged in the combustion chamber, wherein the positions of the front blunt body and the rear blunt body in the combustion chamber are respectively a front combustion chamber and a rear combustion chamber; the concave cavity is formed between a front blunt body and a rear blunt body, a folding angle is arranged on the gas channel, and a jet hole with a cyclone is arranged on the side surface of the rear blunt body parallel to the combustion chamber channel;
further, 2 rows of jet holes are formed in the rear blunt body, 4 jet holes are formed in each row, and the diameter of each jet hole is 4mm;
further, the cyclone is a vane type axial cyclone;
further, the folded angles are symmetrically arranged on the gas channel and are used for connecting the front combustion chamber and the rear combustion chamber, so that the width of the rear combustion chamber channel is narrower than that of the front combustion chamber, and the angle of the folded angle 3 is 30 degrees;
further, the folded angle is arranged at a position, which is 0.4 times of the length of the whole combustion chamber, away from the inlet, the height of the folded angle is 0.5 times of the width of the air inlet channel of the combustion chamber, and the width of the air inlet channel of the combustion chamber is the width between the upper surface of the front combustion chamber and the upper surface of the front blunt body;
further, the connection position of the bottom end of the bevel and the rear combustion chamber channel is on the same vertical plane with the front end face of the rear blunt body.
Further, the preheating device of the arc-shaped front wall surface of the front blunt body preheats the air flow; the preheating device is arranged in the front blunt body, and the preheating mode is that a heating element is used in the arc surface of the front blunt body and is clung to the front wall surface, for example, metal materials such as iron-aluminum alloy, nichrome and the like and nonmetallic materials such as silicon carbide, molybdenum disilicide and the like, and the heating element is electrified to heat the element, so that the front wall surface of the front blunt body is heated, and the effect of preheating main flow is achieved.
The invention has the beneficial effects that:
the novel variable-section aeroengine combustion chamber adopts the angle and the jet hole with the swirler, so that the incoming flow is well turbulent, and the preheating device is used for increasing the temperature of the incoming flow, thereby improving the fuel utilization rate, improving the temperature distribution of the outlet of the combustion chamber, keeping the generation of NO at a lower level, and obviously improving the outlet flow velocity of the combustion chamber, so as to improve the performance of the gas turbine.
Drawings
FIG. 1 is a perspective view of a novel variable cross-section aircraft engine combustion chamber of the present invention;
FIG. 2 is a top view of the combustion chamber of the present invention;
FIG. 3 is a schematic view of a swirler vane of the present invention;
fig. 4 is a schematic view of the cyclone structure of the present invention.
In the figure, 1 is a combustion chamber inlet, 2, a heating surface, 3, a front blunt body, 4, a bevel, 5, a rear blunt body, 6, a combustion chamber outlet, 7, a combustion chamber channel, 8, jet holes, 9 and a concave cavity.
Detailed Description
The present invention will be described in further detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present invention more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention.
As shown in fig. 1 and 2, the novel variable-section aeroengine combustion chamber of the embodiment of the invention comprises a front blunt body 3, a concave cavity 9 and a rear blunt body 5 which are arranged in a combustion chamber channel, wherein a preheating device of the front wall surface of the front blunt body is arranged in the front blunt body, and the preheating mode is that a heating element is used in the arc surface of the front blunt body and is tightly attached to the front wall surface, for example, a metal material such as iron-aluminum alloy, nichrome and the like and a nonmetallic material such as silicon carbide, molybdenum disilicide and the like, and current is conducted on the heating element to heat the element, so that the front wall surface of the front blunt body is heated, and the preheating of air flow entering the combustion chamber can be realized; the front blunt body 3 and the rear blunt body 5 are arranged in parallel in the combustion chamber channel, the positions of the front blunt body 3 and the rear blunt body 5 in the combustion chamber are respectively a front combustion chamber and a rear combustion chamber, a concave cavity 9 is formed between the front blunt body 3 and the rear blunt body 5, the folded angle 3 is symmetrically arranged on the gas channel, the folded angle 3 is connected with the front combustion chamber and the rear combustion chamber, the width of the rear combustion chamber channel is narrower than that of the front combustion chamber, the angle of the folded angle 4 is 30 degrees, the combustion condition in the combustion chamber is optimal, the combustion temperature is higher, but the temperature distribution is more uniform, so that the generation of NO is kept at a lower level; the folded angle 4 is arranged at the position with the length being 0.4 times of the length of the whole combustion chamber from the inlet, so that the main flow is more turbulent, and the main flow is more fully combusted at the rear section of the combustion chamber, thereby improving the combustion efficiency; the height of the folded angle 4 is 0.5 times of the total height of the air inlet of the combustion chamber, the air flow is influenced by the too high height, the total pressure loss is excessive, and the turbulence effect is not obvious due to the too low height; the position of the bottom end of the folded angle 3 and the front end face of the rear blunt body 5 are on a vertical plane, so that the gas after the diversion effect of the folded angle is close to the positions of the upper side and the lower side of the rear blunt body 5, the optimal turbulence effect of the folded angle 4 and jet flow can be ensured, and the disturbance effect is more obvious.
As shown in fig. 1, the rear blunt body 5 is provided with jet holes 8 with swirlers on the side parallel to the combustion chamber channel; the jet holes 8 on the rear blunt body 5 are provided with 2 rows, each row is provided with 4 jet holes, and the diameter of each jet hole is 4mm; the cyclone is a vane type axial cyclone as shown in fig. 3 and 4; is installed in the jet hole 8.
The working process of the invention is further explained below:
the main stream air flows into the combustion chamber from the inlet 1 of the combustion chamber, and after being preheated by the preheating surface 2 at the circular arc wall surface of the front bluff body 3, the air flows into the main combustion zone of the combustion chamber from the inlet passages of the combustion chamber at both sides of the front bluff body 3. Before entering the main combustion area, the air flow can meet a folded angle 4 of 30 degrees in the flowing process, after meeting the folded angle 4, the flowing direction of the air flow can be changed, the flowing can be disturbed, the turbulence degree can be increased, the disturbed air flow can meet jet flow on the upper side wall surface and the lower side wall surface of the rear blunt body 5 in the moving process towards the middle part of the combustion chamber, the turbulence degree of the air flow is further enhanced, the fuel is combusted more fully, and the combustion efficiency is improved. As the wall surface of the combustion chamber is narrowed, the airflow velocity is accelerated, the outlet flow velocity of the combustion chamber is correspondingly improved, and the performance of the gas turbine can be improved.
The height and thickness of the rear bluff body 5 cause vortex of different sizes, which has important influence on the air flow state in the combustion chamber and the combustion process, so that the size selection of the rear bluff body 5 is important and is determined according to the size, combustion and discharge requirements of the whole combustion chamber in the actual process.
In the description of the present specification, reference to the terms "one embodiment," "some embodiments," "illustrative embodiments," "examples," "specific examples," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, schematic representations of the above terms do not necessarily refer to the same embodiments or examples. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
The above embodiments are merely for illustrating the design concept and features of the present invention, and are intended to enable those skilled in the art to understand the content of the present invention and implement the same, the scope of the present invention is not limited to the above embodiments. Therefore, all equivalent changes or modifications according to the principles and design ideas of the present invention are within the scope of the present invention.
Claims (3)
1. The novel variable-section aeroengine combustion chamber is characterized by comprising a front blunt body (3), a concave cavity (9) and a rear blunt body (5) which are arranged in the combustion chamber, wherein the positions of the front blunt body (3) and the rear blunt body (5) in the combustion chamber are respectively a front combustion chamber and a rear combustion chamber; the concave cavity (9) is formed between the front blunt body (3) and the rear blunt body (5), a folding angle (4) is arranged on the gas channel, and a jet hole (8) with a cyclone is arranged on the side surface of the rear blunt body (5) parallel to the combustion chamber channel; the folded angle (4) is symmetrically arranged on the gas channel and is used for connecting the front combustion chamber and the rear combustion chamber, so that the width of the channel of the rear combustion chamber is narrower than that of the front combustion chamber, and the angle of the folded angle (4) is 30 degrees; the length of the folded angle (4) at the inlet is 0.4 times of the length of the whole combustion chamber, the height of the folded angle (4) is 0.5 times of the width of a combustion chamber air inlet channel, and the width of the combustion chamber air inlet channel is the width between the upper surface of the front combustion chamber and the upper surface of the front blunt body; the connecting position of the bottom end of the folded angle (4) and the rear combustion chamber channel is on the same vertical plane with the front end surface of the rear blunt body; the cyclone is a vane type axial cyclone.
2. The novel variable cross-section aeroengine combustion chamber according to claim 1, wherein the rear blunt body (5) is provided with 2 rows of jet holes, 4 jet holes are arranged in each row, and the diameter of each jet hole is 4mm.
3. A new variable cross-section aeroengine combustion chamber according to claim 1, wherein the preheating means of the circular arc shaped front wall of the front bluff body (3) preheats the air flow.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810909112.7A CN109210573B (en) | 2018-08-10 | 2018-08-10 | Novel variable cross-section aeroengine combustion chamber |
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| CN201810909112.7A CN109210573B (en) | 2018-08-10 | 2018-08-10 | Novel variable cross-section aeroengine combustion chamber |
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| CN109210573A CN109210573A (en) | 2019-01-15 |
| CN109210573B true CN109210573B (en) | 2023-08-18 |
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| CN114777158A (en) * | 2022-05-13 | 2022-07-22 | 哈尔滨工程大学 | Combustion chamber mixing structure based on blunt body group |
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| CN109210573A (en) | 2019-01-15 |
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