CN116658934A - Combustion chamber based on plane jet flame stabilizer - Google Patents
Combustion chamber based on plane jet flame stabilizer Download PDFInfo
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- CN116658934A CN116658934A CN202310743016.0A CN202310743016A CN116658934A CN 116658934 A CN116658934 A CN 116658934A CN 202310743016 A CN202310743016 A CN 202310743016A CN 116658934 A CN116658934 A CN 116658934A
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- Prior art keywords
- jet
- combustion chamber
- fuel
- flame stabilizer
- planar
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 169
- 239000003381 stabilizer Substances 0.000 title claims abstract description 161
- 239000000446 fuel Substances 0.000 claims abstract description 141
- 230000004888 barrier function Effects 0.000 claims abstract description 40
- 238000002347 injection Methods 0.000 claims description 39
- 239000007924 injection Substances 0.000 claims description 39
- 239000000203 mixture Substances 0.000 claims description 29
- 238000002955 isolation Methods 0.000 claims description 9
- 230000009471 action Effects 0.000 claims description 8
- 238000005507 spraying Methods 0.000 claims description 7
- 239000007788 liquid Substances 0.000 claims description 3
- 239000007789 gas Substances 0.000 description 45
- 239000003921 oil Substances 0.000 description 38
- 238000010586 diagram Methods 0.000 description 16
- 230000001105 regulatory effect Effects 0.000 description 8
- 230000000903 blocking effect Effects 0.000 description 5
- 239000002737 fuel gas Substances 0.000 description 5
- 230000000694 effects Effects 0.000 description 4
- 230000000087 stabilizing effect Effects 0.000 description 4
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 3
- 239000001301 oxygen Substances 0.000 description 3
- 229910052760 oxygen Inorganic materials 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 2
- 238000009413 insulation Methods 0.000 description 2
- 230000010355 oscillation Effects 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 239000000956 alloy Substances 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
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
- F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
- F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
-
- 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
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
Abstract
The application relates to a combustion chamber based on a planar jet flame stabilizer. The combustion chamber comprises a combustion chamber inlet, a plurality of plane jet flame stabilizers and an oil gas input device connected with each plane jet flame stabilizer; under the condition that the combustion chamber works, the oil gas input device acquires air and/or fuel and transmits the air and/or fuel to the corresponding planar jet flame stabilizer; the planar jet flame stabilizer ejects air and/or fuel to form a planar jet for forming a aerodynamic barrier under the high velocity incoming flow in the combustion chamber inlet and forming a recirculation zone behind the aerodynamic barrier, reducing the overall pressure loss of the combustion chamber.
Description
Technical Field
The application relates to the technical field of aeroengines, in particular to a combustion chamber based on a planar jet flame stabilizer.
Background
The combustion chamber is a device in which fuel or propellant is combusted to generate high-temperature fuel gas, and is combustion equipment made of high-temperature resistant alloy materials. The fuel is burned in this chamber. It is an important component of gas turbine engines, ramjet engines, rocket engines. Because the air entering the combustion chamber has the characteristics of high flow speed, uneven inlet temperature and the like, the flame stabilizing device is required to be used for organizing combustion.
In the conventional art, a flame stabilizer of a bluff body structure is installed inside a combustion chamber to stabilize flames in the combustion chamber, however, since a windward area of the flame stabilizer of the bluff body structure is large, a total pressure loss of the combustion chamber of the flame stabilizer based on the bluff body structure is large.
Disclosure of Invention
In view of the above, it is desirable to provide a planar jet flame stabilizer-based combustion chamber that can reduce the total pressure loss of the combustion chamber.
The application provides a combustion chamber based on a planar jet flame stabilizer. The combustion chamber comprises a combustion chamber inlet, a plurality of plane jet flame stabilizers and an oil gas input device connected with each plane jet flame stabilizer;
the oil gas input device is used for acquiring jet air and fuel under the condition that the combustion chamber works and conveying the jet air and the fuel to the corresponding plane jet flame stabilizer;
the planar jet flame stabilizer is used for jetting the air and the fuel to form a planar jet, and the planar jet is used for forming a pneumatic barrier and forming a backflow zone behind the pneumatic barrier under the action of high-speed inflow of the combustion chamber.
In one embodiment, the oil gas input device is used for stopping air and fuel from being delivered to the planar jet flame stabilizer under the condition that the combustion chamber stops working so as to prevent the planar jet from being formed, and the high-speed incoming flow smoothly flows through the combustion chamber.
In one embodiment, the combustion chamber includes a first mixer; the first mixer is arranged in the oil gas input device, or the first mixer is arranged in the plane jet flame stabilizer;
the first mixer for atomizing and mixing the air and the fuel to form a combustible mixture and delivering the combustible mixture to the planar jet flame stabilizer;
the planar jet flame stabilizer is used for acquiring the combustible mixture and spraying the combustible mixture to form the planar jet.
In one embodiment, the interior of the oil and gas input device includes a first passage and a second passage, the first mixer being disposed within the planar jet flame stabilizer;
the first channel is used for conveying the air to the plane jet flame stabilizer;
the second channel is used for transmitting the fuel to the plane jet flame stabilizer;
the planar jet flame stabilizer is used for acquiring the air conveyed by the first channel and the fuel conveyed by the second channel, and atomizing and mixing the air and the fuel through the first mixer to form a combustible mixture.
In one embodiment, the combustor inlet includes a combustor bypass inlet and a combustor bypass inlet;
a bypass inlet in the combustion chamber for introducing a bypass airflow into the combustion chamber;
the combustion chamber includes an outer duct inlet for introducing an outer duct airflow into the combustion chamber.
In one embodiment, the combustion chamber further comprises a second mixer;
and the second mixer is used for mixing the acquired inclusion airflow and the acquired outer inclusion airflow to form high-speed inflow.
In one embodiment, the combustion chamber further comprises a tail cone, and the planar jet flame stabilizers are uniformly distributed in an annular shape;
each plane jet flame stabilizer is arranged behind the tail cone, or is arranged around the tail cone by taking the tail cone as a center ring.
In one embodiment, the oil gas input device and the planar jet flame stabilizer each have a third passage and a fourth passage;
the third channel is used for conveying the air to the plane jet flame stabilizer;
the fourth passage is used for conveying the fuel to the planar jet flame stabilizer.
In one embodiment, a planar jet flame stabilizer includes a jet injection device having a jet nozzle disposed thereon, the jet nozzle including a first jet nozzle and a second jet nozzle disposed along a spanwise direction of the jet injection device;
the jet injection device is used for delivering air and fuel to the first jet nozzle and the second jet nozzle;
the first jet nozzle is used for jetting air and fuel conveyed by the jet injection device along a first direction so as to form a first plane jet;
the second jet nozzle is used for jetting air and fuel conveyed by the jet injection device along a second direction so as to form a second plane jet;
wherein the first planar jet and the second planar jet are configured to form a pneumatic barrier under the influence of a high velocity incoming flow and to form a recirculation zone behind the pneumatic barrier.
In one embodiment, the combustion chamber further comprises a thermal isolation barrier and a casing disposed outside the thermal isolation barrier.
In one embodiment, the combustion chamber includes a fuel injection device;
the fuel injection device is used for acquiring fuel under the condition that the combustion chamber works and spraying the fuel.
In one embodiment, the fuel comprises a gaseous fuel or a liquid fuel.
The combustion chamber based on the planar jet flame stabilizer comprises a combustion chamber inlet, a plurality of planar jet flame stabilizers and an oil gas input device connected with each planar jet flame stabilizer. The oil gas input device acquires air and fuel under the condition that the combustion chamber works, and transmits the acquired air and fuel to the corresponding plane jet flame stabilizer; the planar jet flame stabilizer ejects air and fuel to form a planar jet, which under the action of the high-speed incoming flow forms a pneumatic barrier and forms a recirculation zone behind the pneumatic barrier. The conventional combustion chamber adopts the blunt body structure flame stabilizer to stabilize the flame, the blunt body structure flame stabilizer needs to block high-speed incoming flow through the blunt body structure with larger area of the flame stabilizer itself so as to ensure that the flame in the combustion chamber can be continuously stabilized, therefore, the windward area of the blunt body structure-based flame stabilizer is larger, and the total pressure loss of the combustion chamber arranged by the blunt body structure-based flame stabilizer is larger. In the application, the planar jet flame stabilizer is arranged in the combustion chamber to stabilize flame, and because the windward area of the planar jet flame stabilizer is smaller, the total pressure loss of the combustion chamber designed based on the planar jet flame stabilizer is smaller, and the flow of the planar jet can be regulated according to the requirements of the combustion chamber under different working conditions, so that the size of a pneumatic barrier formed by the planar jet can be regulated to adapt to the requirements of different working conditions on the pneumatic blocking ratio.
Drawings
FIG. 1 is one of the block diagrams of a combustion chamber provided by an embodiment of the present application;
FIG. 2 is a block diagram of an oil and gas input device according to an embodiment of the present application;
FIG. 3 is one of the block diagrams of a planar jet flame stabilizer provided by an embodiment of the present application;
FIG. 4 is a second internal block diagram of an oil and gas input device according to an embodiment of the present application;
FIG. 5 is a second block diagram of a combustion chamber provided in an embodiment of the present application;
FIG. 6 is a third block diagram of a combustion chamber provided in an embodiment of the present application;
FIG. 7 is a fourth block diagram of a combustion chamber provided by an embodiment of the present application;
FIG. 8 is a diagram of one of the arrangements of a planar jet stabilizer provided by an embodiment of the present application;
FIG. 9 is a second diagram of an arrangement of a planar jet stabilizer according to an embodiment of the present application;
FIG. 10 is a second block diagram of a planar jet flame stabilizer provided in an embodiment of the application;
FIG. 11 is a third block diagram of a planar jet flame stabilizer provided in an embodiment of the application;
FIG. 12 is a fifth block diagram of a combustion chamber provided in the present embodiment.
Detailed Description
The present application 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 application 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 application.
In the description of the present application, it should be understood that, if any, these terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc., are used herein with respect to the orientation or positional relationship shown in the drawings, these terms refer to the orientation or positional relationship for convenience of description and simplicity of description only, and do not indicate or imply that the apparatus or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore should not be construed as limiting the application.
Furthermore, the terms "first," "second," and the like, if any, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In the description of the present application, the terms "plurality" and "a plurality" if any, mean at least two, such as two, three, etc., unless specifically defined otherwise.
In the present application, unless explicitly stated and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly. For example, the two parts can be fixedly connected, detachably connected or integrated; can be mechanically or electrically connected; either directly or indirectly, through intermediaries, or both, may be in communication with each other or in interaction with each other, unless expressly defined otherwise. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art according to the specific circumstances.
In the present application, unless expressly stated or limited otherwise, the meaning of a first feature being "on" or "off" a second feature, and the like, is that the first and second features are either in direct contact or in indirect contact through an intervening medium. Moreover, a first feature being "above," "over" and "on" a second feature may be a first feature being directly above or obliquely above the second feature, or simply indicating that the first feature is level higher than the second feature. The first feature being "under", "below" and "beneath" the second feature may be the first feature being directly under or obliquely below the second feature, or simply indicating that the first feature is less level than the second feature.
It will be understood that if an element is referred to as being "fixed" or "disposed" on another element, it can be directly on the other element or intervening elements may also be present. If an element is referred to as being "connected" to another element, it can be directly connected to the other element or intervening elements may also be present. The terms "vertical," "horizontal," "upper," "lower," "left," "right," and the like as used herein, if any, are for descriptive purposes only and do not represent a unique embodiment.
First, before the technical scheme of the embodiment of the present application is specifically described, a description is first given of a technical background or a technical evolution context on which the embodiment of the present application is based. Because the high-speed incoming flow entering the combustion chamber has the characteristics of low oxygen content, high flow speed, low total pressure, uneven inlet temperature and the like, the combustion of fuel in the combustion chamber cannot be continuously and stably carried out. Therefore, a flame stabilizer with a blunt body structure is usually installed in the combustion chamber, the blunt body structure of the flame stabilizer is used for blocking high-speed incoming flow, and a backflow area consisting of high-temperature fuel gas is formed behind the flame stabilizer, so that the high-temperature fuel gas can continuously ignite fuel in the combustion chamber, and the effect of stabilizing flame is achieved. However, the blunt flame stabilizer has a large flow resistance due to a large area, and thus a large flow loss is generated, and thus the total pressure loss and thrust loss of the combustion chamber based on the blunt flame stabilizer are large.
In the application, the planar jet flame stabilizer is arranged in the combustion chamber to stabilize flame, and the planar jet flame stabilizer has smaller volume, and the pneumatic barrier and the backflow area formed by the high-speed planar jet ejected from the stabilizer are used for realizing the effect of stabilizing flame.
In one embodiment, as shown in FIG. 1, a planar jet flame stabilizer based combustion chamber 100 is provided that includes a combustion chamber inlet 110, a plurality of planar jet flame stabilizers 120, and an oil and gas input device 130 coupled to each planar jet flame stabilizer 120.
The oil and gas input device 130 is used for acquiring air and fuel under the condition of the combustion chamber operation and transmitting the air and the fuel to the corresponding planar jet flame stabilizer 120.
The planar jet flame stabilizer 120 is used for ejecting air and fuel to form a planar jet, which is used for forming a pneumatic barrier and forming a backflow zone behind the pneumatic barrier under the action of high-speed incoming flow in the duct 110.
The combustion chamber in this embodiment may be an afterburner or a ram combustor. When the combustion chamber is a turbofan engine afterburner, the high-speed incoming flow is high-speed air flow formed by mixing the outer culvert air and the inner culvert gas, and when the combustion chamber is a turbojet engine afterburner, only one culvert exists at the moment, and the high-speed incoming flow is high-speed gas entering the combustion chamber from the engine; when the combustion chamber is a ramjet combustion chamber, the high-speed incoming flow is high-speed air entering the combustion chamber from the air inlet passage.
In this embodiment, taking the combustion chamber 100 as an afterburner as an example, the external air and the internal fuel gas enter the combustion chamber 100 through the combustion chamber inlet 110 to form high-speed inflow, and the oil gas channels inside each oil gas input device 130 are connected with the oil gas channels inside the corresponding planar jet flame stabilizer 120. In the case of the operation of the combustion chamber, the oil and gas input device 130 may obtain fuel and air through a conduit outside the combustion chamber 100, the fuel may be liquid fuel, and the obtained fuel and air may be delivered to the planar jet flame stabilizer 120 through an oil and gas channel, and the planar jet flame stabilizer 120 is provided with a jet nozzle in an axial direction, and the jet nozzle jets the fuel and air to form a planar jet under the effect of a pressure difference. Alternatively, the pressure device is arranged inside the plane jet flame stabilizer 120, the pressure in the plane jet flame stabilizer 120 is regulated by the pressure device, and then fuel and air are ejected out through the jet nozzle under the action of the pressure to form plane jet; the planar jet forms a pneumatic barrier under the action of the high-speed incoming flow and a backflow area behind the pneumatic barrier, the pneumatic barrier prevents most of the high-speed incoming flow from entering the combustion chamber 100, and high-temperature fuel gas in the backflow area continuously ignites fuel in the combustion chamber 100, so that the effect of stabilizing flame is achieved.
Alternatively, the fuel may be a gaseous fuel, in which case a conduit external to the combustion chamber 100 may capture only the gaseous fuel or capture both the gaseous fuel and a small amount of air and deliver the captured gaseous fuel through an oil and gas passage to the planar jet flame stabilizer 120, the planar jet flame stabilizer 120 being provided with a jet nozzle in an axial direction, the jet nozzle ejecting the gaseous fuel under pressure differential to form a planar jet.
The combustion chamber based on the planar jet flame stabilizer comprises a combustion chamber inlet, a plurality of planar jet flame stabilizers and an oil gas input device connected with each planar jet flame stabilizer. The oil gas input device acquires air and fuel under the condition that the combustion chamber works, and transmits the acquired air and fuel to the corresponding plane jet flame stabilizer; the planar jet flame stabilizer ejects air and fuel to form a planar jet, which under the action of the high-speed incoming flow forms a pneumatic barrier and forms a recirculation zone behind the pneumatic barrier. The conventional combustion chamber adopts the blunt body structure flame stabilizer to stabilize the flame, the blunt body structure flame stabilizer needs to block high-speed incoming flow through the blunt body structure with larger area of the flame stabilizer itself so as to ensure that the flame in the combustion chamber can be continuously stabilized, therefore, the windward area of the blunt body structure-based flame stabilizer is larger, and the total pressure loss of the combustion chamber arranged by the blunt body structure-based flame stabilizer is larger. In the application, the planar jet flame stabilizer is arranged in the combustion chamber to stabilize flame, and because the windward area of the planar jet flame stabilizer is smaller, the total pressure loss of the combustion chamber designed based on the planar jet flame stabilizer is smaller, and the flow of the planar jet can be regulated according to the requirements of the combustion chamber under different working conditions, so that the size of a pneumatic barrier formed by the planar jet can be regulated to adapt to the requirements of different working conditions on the pneumatic blocking ratio.
In one embodiment, the oil and gas input device 130 is used to stop delivering air and fuel to the planar jet flame stabilizer 120 in the event that the combustion chamber 100 is deactivated, to prevent the formation of a planar jet, to facilitate high velocity incoming flow through the combustion chamber 100 and to generate thrust for the engine.
In this embodiment, if the combustion chamber 100 stops operating, the oil gas input device 130 stops acquiring air and fuel and stops delivering air and fuel to the planar jet flame stabilizer 120. Alternatively, if the combustion chamber 100 is deactivated, the valves on the conduits carrying the fuel and air are closed, and no air or fuel enters the fuel and air input 130. At this time, the aerodynamic barrier and the backflow area of the planar jet flame stabilizer 120 disappear, and the windward area is smaller due to the smaller structure of the planar jet flame stabilizer 120, so that the high-speed incoming flow can smoothly pass through the combustion chamber 100, so as to reduce the thrust loss of the combustion chamber 100, and the engine obtains larger thrust.
In the embodiment of the application, the oil gas input device stops transmitting air and fuel to the planar jet flame stabilizer under the condition that the combustion chamber stops working so as to prevent the formation of planar jet, so that high-speed incoming flow enters the combustion chamber and provides thrust for the combustion chamber. Because the windward area of the planar jet flame stabilizer is smaller, high-speed incoming flow can smoothly pass through the combustion chamber, and the total pressure loss of the combustion chamber is reduced.
In one embodiment, as shown in FIG. 2, the combustion chamber 100 includes a first mixer 140, the first mixer 140 being disposed inside the oil and gas input device 130, or, as shown in FIG. 3, the first mixer 140 being disposed inside the planar jet flame stabilizer 120.
A first mixer 140 for atomizing and mixing air and fuel to form a combustible mixture and delivering the combustible mixture to the planar jet flame stabilizer 120.
A planar jet flame stabilizer 120 for capturing the combustible mixture and ejecting the combustible mixture to form a planar jet.
Illustratively, to achieve better combustion, the fuel and air need to be atomized and mixed to form a combustible mixture. Thus, the fuel and air may be blended by providing a first mixer 140, the first mixer 140 being an oil and gas mixer, the first mixer 140 may be provided inside the oil and gas input device 130, or the first mixer 140 may be provided inside the planar jet flame stabilizer 120. If the first mixer 140 is disposed inside the oil-gas input device 130, after the oil-gas input device 130 obtains the fuel and the air, the fuel and the air are atomized and mixed by the first mixer 140 to form a combustible mixture, the combustible mixture is delivered to the planar jet flame stabilizer 120, and after the planar jet flame stabilizer 120 receives the combustible mixture, the combustible mixture is ejected from the direction of the planar jet flame stabilizer 120 and at an angle to the direction of the high-speed incoming flow, so as to form a planar jet.
If the first mixer 140 is disposed inside the planar jet flame stabilizer 120. The oil and gas input means 130 respectively delivers fuel and air to the planar jet flame stabilizer 120, and the planar jet flame stabilizer 120 mixes the fuel and air delivered by the oil and gas input means 120 through the first mixer 140 to form a combustible mixture and ejects the combustible mixture from the direction of the planar jet flame stabilizer 120 and at an angle to the direction of the high-speed incoming flow to form a planar jet.
In an embodiment of the application, the combustion chamber comprises a first mixer; the first mixer can be arranged inside the oil gas input device or inside the plane jet flame stabilizer, and the first mixer is used for atomizing and mixing air and fuel to form a combustible mixture and delivering the combustible mixture to the plane jet flame stabilizer; the planar jet flame stabilizer captures the combustible mixture and ejects the combustible mixture to form a planar jet. By arranging the first mixer, the mixing efficiency of fuel oil and air is improved, and the combustion efficiency of fuel is further improved.
In one embodiment, fig. 4 is a second internal structure diagram of the oil and gas input device according to the embodiment of the present application, and as shown in fig. 4, the inside of the oil and gas input device 130 includes a first channel 131 and a second channel 132, and the first mixer 140 is disposed inside the planar jet flame stabilizer 120.
A first passage 131 for delivering air to the planar jet flame holder 120.
A second passage 132 for delivering fuel to the planar jet flame stabilizer 120.
The planar jet flame stabilizer 120 is used for acquiring the air conveyed by the first channel 131 and the fuel conveyed by the second channel 132, and atomizing and mixing the air and the fuel through the first mixer 140 to form a combustible mixture.
In order to improve the fuel and air delivery efficiency, a first passage 131 and a second passage 132 may be provided inside the oil and gas input device 130; the first channel 131 transmits air to the planar jet flame stabilizer 120, and the second channel 132 transmits fuel to the planar jet flame stabilizer 120, thereby achieving simultaneous delivery of fuel and air and improving delivery efficiency of fuel and air. The planar jet flame stabilizer 120 is internally provided with a first mixer 140, and the first mixer 140 atomizes and mixes the air and fuel delivered by the oil and gas input device 130 to form a combustible mixture.
In the embodiment of the application, the oil gas input device comprises a first channel and a second channel, and the first mixer is arranged in the plane jet flame stabilizer; delivering air to the planar jet flame stabilizer through the first passage; delivering fuel to the planar jet flame stabilizer through the second passage; the planar jet flame stabilizer captures air delivered by the first passage and fuel delivered by the second passage and atomizes and mixes the air and fuel through the first mixer to form a combustible mixture. The fuel and air delivery efficiency is improved.
In one embodiment, FIG. 5 is a second block diagram of a combustor provided in an embodiment of the present application, and as shown in FIG. 5, the combustor inlet 110 includes a combustor bypass inlet 111 and a combustor bypass inlet 112.
A combustion chamber bypass inlet 111 for introducing a bypass airflow into the combustion chamber; .
An outer bypass inlet 112 for introducing an outer bypass airflow into the combustion chamber.
Wherein, after the air is compressed by the fan, a part of the air flows into the gas generator, which is called connotation air flow; the other part flows around the outer ring of the gas generator to directly generate thrust, which is called as external air flow.
In this embodiment, the combustion chamber 100 includes two combustion chamber inlets, namely a combustion chamber inner duct inlet 111 and a combustion chamber outer duct inlet 112, and the inner duct inlet 111 is used to obtain the inner duct airflow so that the inner duct airflow enters the combustion chamber; the outer culvert air flow is obtained through the inlet of the culvert outside the combustion chamber, so that the outer culvert air flow enters the combustion chamber 100, and the outer culvert air flow and the inner culvert air flow are mixed to form high-speed incoming flow.
In the embodiment of the application, the duct comprises the inner duct inlet and the outer duct inlet of the combustion chamber, the inner duct inlet of the combustion chamber acquires the inner duct air flow, the outer duct air flow is acquired by the outer duct inlet of the combustion chamber, and the stability of fuel combustion in the combustion chamber is improved by conveying the inner duct air flow and the outer duct air flow separately.
In one embodiment, FIG. 6 is a third block diagram of a combustion chamber provided in accordance with an embodiment of the present application, the combustion chamber 100 further including a second mixer 150.
The second mixer 150 is configured to obtain the content airflow delivered by the inner duct inlet 111 and the outer duct airflow delivered by the outer duct inlet 112 according to a preset ratio of the content airflow to the outer duct airflow, and mix the obtained content airflow and the obtained outer duct airflow to form a high-speed incoming flow.
In this embodiment, it should be noted that, because the oxygen content, the air flow speed, the temperature, etc. in the external air flow and the internal air flow are different, in order to improve the combustion efficiency of the fuel in the combustion chamber 100, the internal air flow and the external air flow need to be mixed according to the preset ratio of the internal air flow and the external air flow; a second mixer 150 may be disposed at the rear of the combustion chamber inner duct inlet 111 and the combustion chamber outer duct inlet 112, where the second mixer 150 is configured to receive the combustion chamber inner duct inlet 111 and the inner duct airflow and the outer duct airflow, and mix the inner duct airflow and the outer duct airflow according to a preset ratio, so as to form a high-speed incoming flow.
In the embodiment of the application, the second mixer obtains the inner culvert airflow conveyed by the inner culvert inlet of the combustion chamber and the outer culvert airflow conveyed by the outer culvert inlet of the combustion chamber according to the preset proportion of the inner culvert airflow and the outer culvert airflow, and mixes the obtained inner culvert airflow and the obtained outer culvert airflow to form high-speed incoming flow. Further improving the combustion efficiency of the fuel in the combustion chamber.
In one embodiment, as shown in FIG. 7, if the combustion chamber 100 is an afterburner, the combustion chamber 100 further includes a tailcone 160, with each of the planar jet flame holders 120 being uniformly distributed in an annular shape.
Each planar jet flame stabilizer 120 is disposed behind the tail cone 160 or around the tail cone 160 with the tail cone 160 as a center.
In this embodiment, the size of each of the planar jet flame holders 120 is not limited, and as shown in fig. 8, the size of each of the planar jet flame holders 120 may be uniform, and the planar jet flame holders 120 may be disposed behind the tail cone 160 or may be disposed around the tail cone 160 with the tail cone 160 as a center. Alternatively, as shown in fig. 9, the dimensions of the planar jet flame holders 120 may be different, and the planar jet flame holders 120 may be alternately arranged in order behind the tail cone 160 according to their own dimensions, or the planar jet flame holders 120 may be alternately arranged around the tail cone 160 according to their own dimensions around the tail cone as a center.
In the embodiment of the application, the distribution of each plane jet flame stabilizer is annular; each plane jet flame stabilizer is arranged behind the tail cone, or is arranged around the tail cone by taking the tail cone as a center ring. The efficiency of blocking high-speed incoming flow of the combustion chamber during working is improved, and the stability of flame combustion in the combustion chamber is further improved.
In one embodiment, the oil and gas input device 130 and the planar jet flame stabilizer 120 each have a third passage and a fourth passage;
and a third passage for delivering air to the planar jet flame stabilizer 120.
And a fourth passage for delivering fuel to the planar jet flame stabilizer 120.
In this embodiment, if the first mixer is not present in the combustion chamber 100, the oil gas input device 130 and the planar jet flame stabilizer 120 may be provided with a third channel and a fourth channel, where the third channel transmits air to the planar jet flame stabilizer 120 and the fourth channel transmits fuel to the planar jet flame stabilizer 120. The planar jet flame stabilizer 120 ejects fuel and air toward both sides of the high-speed inflow direction, and the fuel and air are atomized and mixed after being ejected to form a planar jet.
In the embodiment of the application, the oil gas input device and the plane jet flame stabilizer are provided with a third channel and a fourth channel; the third channel delivers air to the planar jet flame stabilizer and the fourth channel delivers fuel to the planar jet flame stabilizer. Through the arrangement of the third channel and the fourth channel, fuel and air can be simultaneously transmitted, and the transmission efficiency of the fuel and the air is improved.
In one embodiment, FIG. 10 is a second block diagram of a planar jet flame stabilizer according to an embodiment of the present application, where the flame stabilizer 120 includes a jet injection device 121 with jet nozzles disposed thereon, the jet nozzles including a first jet nozzle 122 and a second jet nozzle 123, the jet nozzles disposed along a spanwise direction of the jet injection device 121.
Jet injection means 121 for delivering air and fuel to first jet nozzle 122 and second jet nozzle 123.
A first jet nozzle 122 for ejecting air and fuel delivered by the jet injection device 121 in a first direction to form a first planar jet.
A second jet nozzle 123 for ejecting air and fuel delivered by the jet injection device 121 in a second direction to form a second planar jet; the second direction is opposite to the first direction.
Wherein the first and second planar jets are used to form a pneumatic barrier 124 and a recirculation zone 125 behind the pneumatic barrier under the influence of high velocity incoming flow.
The high-speed incoming flow is a high-speed air flow flowing to the flame stabilizer 200, and has the characteristics of low oxygen content, high flow speed, low total pressure, uneven inlet temperature and the like.
In this embodiment, the flame stabilizer 120 includes a jet injection device 121, and a jet nozzle is disposed on the jet injection device 121, and includes a first jet nozzle 122 and a second jet nozzle 123, which are disposed along an axial direction of the jet injection device 121. As shown in fig. 11, the fluidic device 210 may be rectangular parallelepiped in shape, and the first and second fluidic nozzles 122 and 123 are disposed on both sides of the fluidic device 121 in a spanwise direction, respectively. The jet injection device 121 may be internally provided with a fuel delivery passage and an air flow delivery passage, respectively, the fuel delivery passage delivering fuel to the first jet nozzle 122 and the second jet nozzle 123, respectively, and the air flow delivery passage delivering air to the first jet nozzle 122 and the second jet nozzle 123, respectively; the first jet nozzle 122 jets air and fuel in a first direction to form a first planar jet and the second jet nozzle 123 jets air and fuel in a second direction to form a second planar jet under the influence of a pressure difference between the inside and outside of the jet injection device 121.
The jet injection device 121 may be further provided therein with a pressure adjusting device, by which pressure is generated, so that the first jet nozzle 122 ejects air and fuel in a first direction to form a first planar jet, and the second jet nozzle 123 ejects air and fuel in a second direction to form a second planar jet; alternatively, the pressure regulating device may be disposed outside the jet spraying device 121, in which case the jet spraying device 121 and the pressure regulating device need to be connected by a conduit, and the pressure regulating device provides pressure to the jet spraying device 121, so that the first jet nozzle 122 and the second jet nozzle 123 form a first planar jet and a second planar jet. The first and second planar jets form the aerodynamic barrier 124 under the influence of the high velocity incoming flow and form the recirculation zone 250 behind the aerodynamic barrier 124; the high-velocity incoming flow through the pneumatic barrier 240 resists the majority of the high-velocity incoming flow, the continuous ignition of fresh fuel is achieved by the generation of high-temperature combustion gases through the recirculation zone 125, and a small portion of the high-velocity incoming flow can still enter the recirculation zone 125 from both sides of the pneumatic barrier 124, causing the fuel and air in the recirculation zone 125 to mix.
In the embodiment of the application, the flame stabilizer comprises a jet injection device, a jet nozzle is arranged on the jet injection device, the jet nozzle comprises a first jet nozzle and a second jet nozzle, and the jet nozzle is arranged along the axial direction of the jet injection device; the jet injection device delivers air and fuel to the first jet nozzle and the second jet nozzle; the first jet nozzle sprays air and fuel conveyed by the jet injection device along a first direction so as to form a first plane jet; the second jet nozzle sprays air and fuel conveyed by the jet injection device along a second direction so as to form a second plane jet; the second direction is opposite to the first direction; wherein the first planar jet and the second planar jet are used to form a pneumatic barrier under the action of the high-speed incoming flow and to form a recirculation zone behind the pneumatic barrier. In the conventional blunt flame stabilizer, a large-area blunt body structure is used as a barrier for blocking high-speed air flow, and a backflow area is formed behind the barrier so as to realize stable combustion of flame. However, the existing blunt flame stabilizer has a large windward area due to the blunt body structure, and the flow loss of high-speed air flow passing through the flame stabilizer is large due to the large windward area of the blunt body structure, so that the total pressure loss of the combustion chamber is large. The windward area of the blunt body structure is larger, so that the flow loss of the flame stabilizer is larger, and the total pressure loss of the combustion chamber is larger; in addition, the poor oil and gas mixing capability of the blunt body stabilizer results in lower combustion efficiency of the fuel in the combustion chamber. Compared with the flame stabilizer with a blunt body structure, the flame stabilizer based on the plane jet flow has smaller volume, and if the combustion chamber stops working, the plane jet flow flame stabilizer can not generate plane jet flow, and further, high-speed incoming flow can smoothly pass through the combustion chamber, so that the flow resistance and the total pressure loss are reduced. Compared with the annular transverse jet stabilizer, the annular transverse jet stabilizer is different in that most of high-speed incoming flows are blocked by the pneumatic barrier, and part of high-speed incoming flows still can enter the backflow area through the two sides of the pneumatic barrier due to the fact that the pneumatic barrier is not arranged at the two ends of the jet injection device, so that the mixing rate of fuel and air in the backflow area is further improved, and the combustion efficiency of the fuel is improved.
In one embodiment, as shown in fig. 12, the combustion chamber 100 further includes a heat insulating vibration isolation screen 170 and a casing 180 disposed outside the heat insulating vibration isolation screen 170. The heat insulating vibration isolation screen 170 is disposed around the combustion chamber 100 to isolate high temperature and oscillations generated by the combustion of fuel in the combustion chamber 100. The casing 180 is disposed outside the heat insulation and vibration isolation panel 170.
In the embodiment of the application, the heat insulation and vibration isolation screen and the casing are arranged around the combustion chamber so as to isolate high temperature and oscillation generated by the combustion of fuel in the combustion chamber. The safety of the combustion chamber under the working condition is improved.
In one embodiment, the combustion chamber includes a fuel injection device; and the fuel injection device is used for acquiring fuel under the condition that the combustion chamber works and spraying the fuel.
Wherein the fuel injection device may be a fuel injection rod.
A fuel injection device may be provided at the front end of the planar jet flame stabilizer 120 for taking fuel and injecting the fuel in the case of the combustion chamber operation. The fuel injection device may inject a portion of the fuel required by the combustion chamber, and the planar jet flame stabilizer 120 may inject the remaining fuel. Alternatively, the fuel injection device may inject all of the fuel required by the combustion chamber, in which case the planar jet flame stabilizer 120 may inject only air.
In the present embodiment, by providing the fuel injection device, the combustion efficiency of the fuel in the combustion chamber can be further improved.
It should be understood that, although the steps in the flowcharts related to the above embodiments are sequentially shown as indicated by arrows, these steps are not necessarily sequentially performed in the order indicated by the arrows. The steps are not strictly limited to the order of execution unless explicitly recited herein, and the steps may be executed in other orders. Moreover, at least some of the steps in the flowcharts described in the above embodiments may include a plurality of steps or a plurality of stages, which are not necessarily performed at the same time, but may be performed at different times, and the order of the steps or stages is not necessarily performed sequentially, but may be performed alternately or alternately with at least some of the other steps or stages.
The technical features of the above embodiments may be arbitrarily combined, and all possible combinations of the technical features in the above embodiments are not described for brevity of description, however, as long as there is no contradiction between the combinations of the technical features, they should be considered as the scope of the description.
The foregoing examples illustrate only a few embodiments of the application, which are described in detail and are not to be construed as limiting the scope of the application. It should be noted that it will be apparent to those skilled in the art that several variations and modifications can be made without departing from the spirit of the application, which are all within the scope of the application. Accordingly, the scope of the application should be assessed as that of the appended claims.
Claims (12)
1. A combustion chamber based on a planar jet flame stabilizer, characterized in that the combustion chamber comprises a combustion chamber inlet, a plurality of planar jet flame stabilizers and an oil gas input device connected with each planar jet flame stabilizer;
the oil gas input device is used for acquiring air and/or fuel under the condition that the combustion chamber works and transmitting the air and/or the fuel to the corresponding plane jet flame stabilizer;
the planar jet flame stabilizer is used for jetting the air and/or the fuel to form a planar jet, and the planar jet is used for forming a pneumatic barrier and forming a backflow zone behind the pneumatic barrier under the action of high-speed incoming flow entering the inlet of the combustion chamber.
2. A combustion chamber according to claim 1, wherein,
the oil gas input device is used for stopping delivering air and fuel to the plane jet flame stabilizer under the condition that the combustion chamber stops working so as to prevent the plane jet from being formed, so that the high-speed incoming flow smoothly flows through the combustion chamber.
3. The combustor of claim 1, wherein the combustor comprises a first mixer; the first mixer is arranged inside the oil gas input device, or the first mixer is arranged inside the plane jet flame stabilizer;
the first mixer for atomizing and mixing the air and the fuel to form a combustible mixture and delivering the combustible mixture to the planar jet flame stabilizer;
the planar jet flame stabilizer is configured to eject the combustible mixture to form the planar jet.
4. The combustor of claim 2, wherein the interior of the oil and gas input device comprises a first passage and a second passage, the first mixer being disposed within the interior of the planar jet flame stabilizer;
the first channel is used for conveying the air to the plane jet flame stabilizer;
the second passage is used for conveying the fuel to the plane jet flame stabilizer;
the planar jet flame stabilizer is used for acquiring the air conveyed by the first channel and the fuel conveyed by the second channel, and atomizing and mixing the air and the fuel through the first mixer to form a combustible mixture.
5. The combustor as set forth in claim 1, wherein said combustor inlet comprises a combustor bypass inlet and a combustor bypass inlet;
the bypass inlet in the combustion chamber is used for introducing the bypass airflow into the combustion chamber;
the combustion chamber outer duct inlet is used for introducing an outer duct airflow into the combustion chamber.
6. The combustor of claim 5, further comprising a second mixer;
the second mixer is configured to mix the obtained content airflow and the obtained content airflow to form the high-speed incoming flow.
7. The combustor of claim 1, wherein if the combustor is an afterburner, the combustor further comprises a tailcone, each of the planar jet flame holders being annularly and uniformly distributed;
each plane jet flame stabilizer is arranged behind the tail cone, or is arranged around the tail cone by taking the tail cone as a center.
8. A combustion chamber according to claim 1, wherein,
the oil gas input device and the plane jet flame stabilizer are provided with a third channel and a fourth channel;
the third channel is used for conveying the air to the plane jet flame stabilizer;
the fourth passage is configured to deliver the fuel to the planar jet flame stabilizer.
9. The combustor of claim 1, wherein the planar jet flame stabilizer comprises a jet injection device having a jet nozzle disposed thereon, the jet nozzle comprising a first jet nozzle and a second jet nozzle, the jet nozzle disposed in a spanwise direction of the jet injection device;
the jet injection device is used for delivering air and fuel to the first jet nozzle and the second jet nozzle;
the first jet nozzle is used for jetting air and fuel conveyed by the jet injection device along a first direction so as to form a first plane jet;
the second jet nozzle is used for jetting air and fuel conveyed by the jet jetting device along a second direction so as to form a second plane jet;
wherein the first planar jet and the second planar jet are configured to form a pneumatic barrier under the influence of a high velocity incoming flow and to form a recirculation zone behind the pneumatic barrier.
10. The combustor of claim 1, further comprising a thermal isolation barrier and a casing disposed outside the thermal isolation barrier.
11. The combustion chamber according to any one of claims 1-10, wherein the combustion chamber comprises a fuel injection device;
the fuel injection device is used for acquiring the fuel under the condition that the combustion chamber works and spraying the fuel.
12. The combustor according to claim 1, wherein the fuel comprises a gaseous fuel and/or a liquid fuel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310743016.0A CN116658934A (en) | 2023-06-21 | 2023-06-21 | Combustion chamber based on plane jet flame stabilizer |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310743016.0A CN116658934A (en) | 2023-06-21 | 2023-06-21 | Combustion chamber based on plane jet flame stabilizer |
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| Publication Number | Publication Date |
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| CN116658934A true CN116658934A (en) | 2023-08-29 |
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| CN202310743016.0A Pending CN116658934A (en) | 2023-06-21 | 2023-06-21 | Combustion chamber based on plane jet flame stabilizer |
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| Country | Link |
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| CN (1) | CN116658934A (en) |
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- 2023-06-21 CN CN202310743016.0A patent/CN116658934A/en active Pending
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