Combustion chamber based on planar jet flame holder

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 planar jet flame stabilizers, and oil-gas input devices connected with the planar jet flame stabilizers; the oil-gas input devices obtain air and / or fuel under the working condition of the combustion chamber, and deliver the air and / or fuel to the corresponding planar jet flame stabilizers; the planar jet flame stabilizers spray out the air and / or fuel to form planar jets, the planar jets are used to form an aerodynamic screen under the action of a high-speed incoming flow in the combustion chamber inlet, and a backflow area is formed behind the aerodynamic screen, so that the total pressure loss of the combustion chamber is reduced.

Description

Technical Field

[0001] This application relates to the field of aero-engine technology, and in particular to a combustion chamber based on a planar jet flame stabilizer. Background Technology

[0002] The combustion chamber is a device in which fuel or propellant burns to generate high-temperature combustion gases. It is a combustion device made of high-temperature resistant alloy materials. Fuel burns in this chamber. It is an important component of gas turbine engines, ramjet engines, and rocket engines. Due to the high velocity and uneven inlet temperature of the air entering the combustion chamber, flame stabilization devices are required to organize combustion.

[0003] In traditional technology, a bluff body flame stabilizer is installed inside the combustion chamber to stabilize the flame. However, because the bluff body flame stabilizer has a large frontal area, the total pressure loss in the combustion chamber is relatively large. Summary of the Invention

[0004] Therefore, it is necessary to provide a combustion chamber based on a planar jet flame stabilizer that can reduce the total pressure loss of the combustion chamber, in order to address the above-mentioned technical problems.

[0005] This application provides a combustion chamber based on a planar jet flame stabilizer. The combustion chamber includes a combustion chamber inlet, multiple planar jet flame stabilizers, and an oil / gas input device connected to each planar jet flame stabilizer;

[0006] The oil and gas input device is used to obtain jet air and fuel when the combustion chamber is working, and to deliver the jet air and fuel to the corresponding planar jet flame stabilizer;

[0007] The planar jet flame stabilizer is used to eject the air and fuel to form a planar jet, which, under the action of the high-speed incoming flow in the combustion chamber, forms an aerodynamic barrier and a recirculation zone behind the aerodynamic barrier.

[0008] In one embodiment, the fuel input device is used to stop supplying air and fuel to the planar jet flame stabilizer when the combustion chamber stops operating, in order to prevent the formation of the planar jet and allow the high-speed incoming flow to pass smoothly through the combustion chamber.

[0009] In one embodiment, the combustion chamber includes a first mixer; the first mixer is disposed inside the fuel-air input device, or the first mixer is disposed inside the planar jet flame stabilizer;

[0010] The first mixer is used to atomize and mix the air and the fuel to form a combustible mixture, and to deliver the combustible mixture to the planar jet flame stabilizer;

[0011] The planar jet flame stabilizer is used to acquire the combustible mixture and eject the combustible mixture to form the planar jet.

[0012] In one embodiment, the interior of the oil and gas input device includes a first channel and a second channel, and the first mixer is disposed inside the planar jet flame stabilizer;

[0013] The first channel is used to transmit the air to the planar jet flame stabilizer;

[0014] The second channel is used to transfer the fuel to the planar jet flame stabilizer;

[0015] The planar jet flame stabilizer is used to acquire the air delivered by the first channel and the fuel delivered by the second channel, and to atomize and mix the air and fuel through the first mixer to form a combustible mixture.

[0016] In one embodiment, the combustion chamber inlet includes an inner combustion chamber duct inlet and an outer combustion chamber duct inlet;

[0017] The combustion chamber inlet is used to introduce the airflow from the inlet into the combustion chamber;

[0018] The outer duct inlet of the combustion chamber is used to introduce the airflow from the outer duct into the combustion chamber.

[0019] In one embodiment, the combustion chamber further includes a second mixer;

[0020] The second mixer is used to mix the acquired inner and outer airflows to form a high-speed incoming flow.

[0021] In one embodiment, the combustion chamber further includes a tail cone, with each planar jet flame stabilizer evenly distributed in a ring;

[0022] Each planar jet flame stabilizer is located behind the tail vertebra or is arranged around the tail vertebra with the tail vertebra as the center.

[0023] In one embodiment, both the oil and gas input device and the planar jet flame stabilizer have a third channel and a fourth channel;

[0024] The third channel is used to transmit the air to the planar jet flame stabilizer;

[0025] The fourth channel is used to transfer the fuel to the planar jet flame stabilizer.

[0026] In one embodiment, the planar jet flame stabilizer includes a jet injection device with a jet nozzle, the jet nozzle including a first jet nozzle and a second jet nozzle, the jet nozzle being arranged along the spanwise direction of the jet injection device;

[0027] The jet injection device is used to deliver air and fuel to the first jet nozzle and the second jet nozzle;

[0028] The first jet nozzle is used to eject the air and fuel delivered by the jet injection device in a first direction to form a first planar jet;

[0029] The second jet nozzle is used to eject the air and fuel delivered by the jet injection device in a second direction to form a second planar jet;

[0030] The first planar jet and the second planar jet are used to form an aerodynamic barrier and a recirculation zone behind the aerodynamic barrier under the action of the high-speed incoming flow.

[0031] In one embodiment, the combustion chamber further includes a heat-insulating and vibration-damping screen and a casing disposed outside the heat-insulating and vibration-damping screen.

[0032] In one embodiment, the combustion chamber includes a fuel injection device;

[0033] The fuel injection device is used to obtain fuel and inject the fuel when the combustion chamber is in operation.

[0034] In one embodiment, the fuel includes a gaseous fuel or a liquid fuel.

[0035] The aforementioned combustion chamber based on a planar jet flame stabilizer includes a combustion chamber inlet, multiple planar jet flame stabilizers, and an oil / gas input device connected to each planar jet flame stabilizer. The oil / gas input device acquires air and fuel during combustion chamber operation and transmits the acquired air and fuel to the corresponding planar jet flame stabilizer. The planar jet flame stabilizer ejects air and fuel to form a planar jet. Under the action of the high-speed incoming flow, the planar jet forms an aerodynamic barrier and a recirculation zone behind the aerodynamic barrier. Traditional combustion chambers use bluff body flame stabilizers to stabilize the flame. Bluff body flame stabilizers require a large area of ​​bluff body structure to block the high-speed incoming flow to ensure continuous flame stability in the combustion chamber. Therefore, bluff body flame stabilizers have a large frontal area, resulting in a larger total pressure loss in the combustion chamber. In this application, a planar jet flame stabilizer is installed in the combustion chamber to stabilize the flame. Since the planar jet flame stabilizer has a small frontal area, the total pressure loss of the combustion chamber designed based on the planar jet flame stabilizer is small. Furthermore, the flow rate of the planar jet can be adjusted according to the needs of different operating conditions of the combustion chamber, thereby adjusting the size of the aerodynamic barrier formed by the planar jet to meet the requirements of the aerodynamic blockage ratio under different operating conditions. Attached Figure Description

[0036] Figure 1 This is one of the structural diagrams of the combustion chamber provided in the embodiments of this application;

[0037] Figure 2 This is a structural diagram of an oil and gas input device provided in an embodiment of this application;

[0038] Figure 3 This is one of the structural diagrams of the planar jet flame stabilizer provided in the embodiments of this application;

[0039] Figure 4 This is the second internal structure diagram of the oil and gas input device provided in the embodiments of this application;

[0040] Figure 5 This is the second structural diagram of the combustion chamber provided in the embodiments of this application;

[0041] Figure 6 This is the third structural diagram of the combustion chamber provided in the application embodiment;

[0042] Figure 7 This is the fourth structural diagram of the combustion chamber provided in the application embodiment;

[0043] Figure 8 This is one of the arrangement diagrams of the planar jet stabilizer provided in the embodiments of this application;

[0044] Figure 9This is the second arrangement diagram of the planar jet stabilizer provided in the embodiments of this application;

[0045] Figure 10 This is the second structural diagram of the planar jet flame stabilizer provided in the embodiments of this application;

[0046] Figure 11 This is the third structural diagram of the planar jet flame stabilizer provided in the embodiments of this application;

[0047] Figure 12 This is the fifth structural diagram of the combustion chamber provided in the application embodiment. Detailed Implementation

[0048] To make the objectives, technical solutions, and advantages of this application clearer, the following detailed description is provided in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the scope of this application.

[0049] In the description of this application, it should be understood that if terms such as "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential" appear, these terms indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this application.

[0050] Furthermore, where the terms "first" and "second" appear, these terms are for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined with "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this application, where the term "multiple" appears, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0051] In this application, unless otherwise expressly specified and limited, the terms "installation," "connection," "joining," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0052] In this application, unless otherwise expressly specified and limited, the use of descriptions such as "above" or "below" the second feature indicates that the first and second features are in direct contact or indirect contact via an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. Similarly, "below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0053] It should be noted that if an element is referred to as being "fixed to" or "set on" another element, it can be directly on the other element or there may be an intervening element. If an element is considered to be "connected to" another element, it can be directly connected to the other element or there may be an intervening element. If so, the terms "vertical," "horizontal," "upper," "lower," "left," "right," and similar expressions used in this application are for illustrative purposes only and do not represent the only possible implementation.

[0054] First, before introducing the technical solutions of the embodiments of this application, the technical background or evolution of the embodiments of this application will be introduced. Because the high-speed incoming flow into the combustion chamber has characteristics such as low oxygen content, high flow velocity, low total pressure, and uneven inlet temperature, the combustion of fuel inside the combustion chamber cannot proceed continuously and stably. Therefore, a bluff body flame stabilizer is usually installed inside the combustion chamber. The bluff body structure of the flame stabilizer blocks the high-speed incoming flow and forms a recirculation zone composed of high-temperature combustion gases behind the flame stabilizer, allowing the high-temperature combustion gases to continuously ignite the fuel in the combustion chamber, thereby achieving a stable flame. However, the bluff body flame stabilizer has a large area, which means that the flow resistance is large, resulting in large flow losses. Therefore, the total pressure loss and thrust loss of the combustion chamber based on the bluff body flame stabilizer are large.

[0055] In this application, a planar jet flame stabilizer is installed in the combustion chamber to stabilize the flame. Since the planar jet flame stabilizer is small in size, it achieves the function of stabilizing the flame by forming an aerodynamic barrier and a recirculation zone through the high-speed planar jet ejected from the stabilizer. Since the planar jet formed by the planar jet flame stabilizer can be opened, closed and adjusted according to the working state of the combustion chamber, if the combustion chamber is not working, the planar jet flame stabilizer can stop ejecting the planar jet. At this time, the high-speed incoming flow can flow smoothly through the combustion chamber, thereby reducing the total pressure loss of the combustion chamber, reducing the thrust loss of the combustion chamber, and enabling the combustion chamber to obtain greater thrust.

[0056] In one embodiment, such as Figure 1 As shown, a combustion chamber 100 based on a planar jet flame stabilizer is provided, including a combustion chamber inlet 110, a plurality of planar jet flame stabilizers 120, and an oil and gas input device 130 connected to each planar jet flame stabilizer 120.

[0057] The oil and gas input device 130 is used to obtain air and fuel when the combustion chamber is in operation, and to transfer the air and fuel to the corresponding planar jet flame stabilizer 120.

[0058] The planar jet flame stabilizer 120 is used to eject air and fuel to form a planar jet, which is used to form an aerodynamic barrier and a recirculation zone behind the aerodynamic barrier under the action of the high-speed incoming flow in the duct 110.

[0059] In this embodiment, the combustion chamber can be either an afterburner or a ramjet combustion chamber. When the combustion chamber is an afterburner of a turbofan engine, the high-speed incoming flow is a high-speed airflow formed by the mixing of bypass air and internal combustion gas. When the combustion chamber is an afterburner of a turbojet engine, there is only one bypass duct, and the high-speed incoming flow is the high-speed combustion gas entering the combustion chamber from the engine. When the combustion chamber is a ramjet engine combustion chamber, the high-speed incoming flow is the high-speed air entering the combustion chamber from the intake duct.

[0060] In this embodiment, the combustion chamber 100 is described as an afterburner. External air and internal combustion gas enter the combustion chamber 100 through the combustion chamber inlet 110 to form a high-speed flow. The oil and gas channels inside each oil and gas input device 130 are connected to the oil and gas channels inside the corresponding planar jet flame stabilizer 120. When the combustion chamber is operating, the oil and gas input device 130 can obtain fuel and air through a conduit outside the combustion chamber 100. The fuel can be liquid fuel. The obtained fuel and air are then transported to the planar jet flame stabilizer 120 through the oil and gas channels. The planar jet flame stabilizer 120 has jet nozzles arranged in the axial direction. Under the action of a pressure difference, the jet nozzles spray fuel and air to form a planar jet. Alternatively, the planar jet flame stabilizer 120 may be equipped with a pressure device. The pressure in the planar jet flame stabilizer 120 may be adjusted by the pressure device, and fuel and air may be ejected through the jet nozzle under the action of the pressure to form a planar jet. The planar jet forms an aerodynamic barrier and a recirculation zone behind the aerodynamic barrier under the action of the high-speed incoming flow. The aerodynamic barrier blocks most of the high-speed incoming flow from entering the combustion chamber 100. The high-temperature gas in the recirculation zone continuously ignites the fuel in the combustion chamber 100, thereby achieving the effect of stabilizing the flame.

[0061] Optionally, the fuel can be gaseous fuel. In this case, the duct outside the combustion chamber 100 can only obtain gaseous fuel or obtain gaseous fuel and a small amount of air, and transport the obtained gaseous fuel to the planar jet flame stabilizer 120 through the oil and gas channel. The planar jet flame stabilizer 120 is provided with a jet nozzle in the axial direction. Under the action of pressure difference, the jet nozzle sprays out gaseous fuel to form a planar jet.

[0062] The aforementioned combustion chamber based on a planar jet flame stabilizer includes a combustion chamber inlet, multiple planar jet flame stabilizers, and an oil / gas input device connected to each planar jet flame stabilizer. The oil / gas input device acquires air and fuel during combustion chamber operation and transmits the acquired air and fuel to the corresponding planar jet flame stabilizer. The planar jet flame stabilizer ejects air and fuel to form a planar jet. Under the action of the high-speed incoming flow, the planar jet forms an aerodynamic barrier and a recirculation zone behind the aerodynamic barrier. Traditional combustion chambers use bluff body flame stabilizers to stabilize the flame. Bluff body flame stabilizers require a large area of ​​bluff body structure to block the high-speed incoming flow to ensure continuous flame stability in the combustion chamber. Therefore, bluff body flame stabilizers have a large frontal area, resulting in a larger total pressure loss in the combustion chamber. In this application, a planar jet flame stabilizer is installed in the combustion chamber to stabilize the flame. Since the planar jet flame stabilizer has a small frontal area, the total pressure loss of the combustion chamber designed based on the planar jet flame stabilizer is small. Furthermore, the flow rate of the planar jet can be adjusted according to the needs of different operating conditions of the combustion chamber, thereby adjusting the size of the aerodynamic barrier formed by the planar jet to meet the requirements of the aerodynamic blockage ratio under different operating conditions.

[0063] In one embodiment, the fuel inlet device 130 is used to stop supplying air and fuel to the planar jet flame stabilizer 120 when the combustion chamber 100 is not in operation, so as to prevent the formation of a planar jet and allow the high-speed incoming flow to pass smoothly through the combustion chamber 100 and generate thrust for the engine.

[0064] In this embodiment, it should be noted that if the combustion chamber 100 stops working, the fuel-air input device 130 stops acquiring air and fuel, and stops supplying air and fuel to the planar jet flame stabilizer 120. Alternatively, if the combustion chamber 100 stops working, the valves on the fuel and air delivery conduits are closed, and no air or fuel enters the fuel-air input device 130. At this time, the aerodynamic barrier and recirculation zone of the planar jet flame stabilizer 120 disappear. Due to the small structure and small frontal area of ​​the planar jet flame stabilizer 120, the high-speed incoming flow can pass smoothly through the combustion chamber 100, thereby reducing the thrust loss of the combustion chamber 100 and enabling the engine to obtain greater thrust.

[0065] In this embodiment, when the combustion chamber stops operating, the oil and gas input device stops supplying air and fuel to the planar jet flame stabilizer to prevent the formation of a planar jet, allowing the high-speed incoming flow to enter the combustion chamber and provide thrust. Because the planar jet flame stabilizer has a small frontal area, the high-speed incoming flow can pass smoothly through the combustion chamber, reducing the total pressure loss in the combustion chamber.

[0066] In one embodiment, such as Figure 2 As shown, the combustion chamber 100 includes a first mixer 140, which is disposed inside the fuel-air input device 130, or, as... Figure 3 As shown, the first mixer 140 is disposed inside the planar jet flame stabilizer 120.

[0067] The first mixer 140 is used to atomize and mix air and fuel to form a combustible mixture and to deliver the combustible mixture to the planar jet flame stabilizer 120.

[0068] Planar jet flame stabilizer 120 is used to acquire a combustible mixture and eject the combustible mixture to form a planar jet.

[0069] For example, to achieve better combustion, fuel and air need to be atomized and mixed to form a combustible mixture. Therefore, a first mixer 140 can be used to mix the fuel and air. The first mixer 140 is an oil-air mixer, which can be located inside the oil-air input device 130, or it can be located inside the planar jet flame stabilizer 120. If the first mixer 140 is located inside the oil-air input device 130, after the oil-air input device 130 receives fuel and air, it atomizes and mixes the fuel and air through the first mixer 140 to form a combustible mixture. This combustible mixture is then delivered to the planar jet flame stabilizer 120. Upon receiving the combustible mixture, the planar jet flame stabilizer 120 ejects the combustible mixture from its span and at a certain angle to the direction of the high-speed incoming flow to form a planar jet.

[0070] If the first mixer 140 is located inside the planar jet flame stabilizer 120, then the oil and gas input device 130 supplies fuel and air to the planar jet flame stabilizer 120 respectively. The planar jet flame stabilizer 120 mixes the fuel and air supplied by the oil and gas input device 120 through the first mixer 140 to form a combustible mixture, and then ejects the combustible mixture from the span of the planar jet flame stabilizer 120 at a certain angle to the direction of the high-speed incoming flow to form a planar jet.

[0071] In this embodiment, the combustion chamber includes a first mixer. The first mixer can be disposed inside the fuel-air input device or inside the planar jet flame stabilizer. The first mixer atomizes and mixes air and fuel to form a combustible mixture, and then delivers the combustible mixture to the planar jet flame stabilizer. The planar jet flame stabilizer acquires the combustible mixture and ejects it to form a planar jet. By providing the first mixer, the mixing efficiency of fuel and air is improved, thereby improving the combustion efficiency of the fuel.

[0072] In one embodiment, Figure 4 This is the second internal structural diagram of the oil and gas input device provided in the embodiments of this application, as shown below. Figure 4 As shown, the interior 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.

[0073] The first channel 131 is used to transmit air to the planar jet flame stabilizer 120.

[0074] The second channel 132 is used to transfer fuel to the planar jet flame stabilizer 120.

[0075] The planar jet flame stabilizer 120 is used to obtain air delivered by the first channel 131 and fuel delivered by the second channel 132, and atomizes and mixes the air and fuel through the first mixer 140 to form a combustible mixture.

[0076] To improve the efficiency of fuel and air delivery, a first channel 131 and a second channel 132 can be provided inside the oil and gas input device 130. The first channel 131 delivers air to the planar jet flame stabilizer 120, and the second channel 132 delivers fuel to the planar jet flame stabilizer 120, thereby achieving simultaneous delivery of fuel and air and improving the efficiency of fuel and air delivery. A first mixer 140 is provided inside the planar jet flame stabilizer 120. 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.

[0077] In this embodiment, the oil and gas input device includes a first channel and a second channel, and a first mixer is disposed inside the planar jet flame stabilizer. Air is supplied to the planar jet flame stabilizer through the first channel; fuel is supplied to the planar jet flame stabilizer through the second channel; the planar jet flame stabilizer receives the air supplied by the first channel and the fuel supplied by the second channel, and atomizes and mixes the air and fuel through the first mixer to form a combustible mixture. This improves the efficiency of fuel and air delivery.

[0078] In one embodiment, Figure 5 This is a second structural diagram of the combustion chamber provided in the embodiments of this application, as shown below. Figure 5 As shown, the combustion chamber inlet 110 includes an inner combustion chamber duct inlet 111 and an outer combustion chamber duct inlet 112.

[0079] The combustion chamber inner duct inlet 111 is used to introduce the inner duct airflow into the combustion chamber.

[0080] The outer duct inlet 112 of the combustion chamber is used to introduce the airflow from the outer duct into the combustion chamber.

[0081] In this process, after the air is compressed by the fan, part of it flows into the gas generator, which is called the inner airflow; the other part flows around the outer ring of the gas generator, directly generating thrust, which is called the outer airflow.

[0082] In this embodiment, the combustion chamber 100 includes two combustion chamber inlets, namely the combustion chamber inner duct inlet 111 and the combustion chamber outer duct inlet 112. The inner airflow is obtained through the combustion chamber inner duct inlet 111 so that the inner airflow enters the combustion chamber; the outer duct airflow is obtained through the combustion chamber outer duct inlet so that the outer duct airflow enters the combustion chamber 100. After the outer duct airflow and the inner airflow are mixed, a high-speed incoming flow is formed.

[0083] In this embodiment, the duct includes an inner duct inlet of the combustion chamber and an outer duct inlet of the combustion chamber. The inner duct inlet of the combustion chamber receives the inner airflow, and the outer duct inlet of the combustion chamber receives the outer airflow. By transporting the inner airflow and the outer airflow separately, the stability of fuel combustion in the combustion chamber is improved.

[0084] In one embodiment, Figure 6 This is the third structural diagram of the combustion chamber provided in the embodiments of this application. The combustion chamber 100 also includes a second mixer 150.

[0085] The second mixer 150 is used to obtain the inner airflow delivered by the inner duct inlet 111 of the combustion chamber and the outer duct inlet 112 of the combustion chamber according to the preset ratio of the inner airflow and the outer duct airflow, and mix the obtained inner airflow and outer duct airflow to form a high-speed incoming flow.

[0086] In this embodiment, it should be noted that since the oxygen content, airflow velocity, temperature, etc. of the bypass airflow and the internal airflow are different, in order to improve the combustion efficiency of the fuel in the combustion chamber 100, the internal airflow and the bypass airflow need to be mixed according to a preset ratio. A second mixer 150 can be provided behind the combustion chamber internal duct inlet 111 and the combustion chamber external duct inlet 112. The second mixer 150 is used to receive the internal airflow and the bypass airflow delivered by the combustion chamber internal duct inlet 111 and the combustion chamber external duct inlet 112, and mix the internal airflow and the bypass airflow according to a preset ratio to form a high-speed incoming flow.

[0087] In this embodiment, the second mixer acquires the inner airflow delivered to the inner duct inlet of the combustion chamber and the outer airflow delivered to the outer duct inlet of the combustion chamber according to a preset ratio of inner airflow to outer airflow, and mixes the acquired inner and outer airflows to form a high-speed inflow. This further improves the combustion efficiency of fuel in the combustion chamber.

[0088] In one embodiment, such as Figure 7As shown, if the combustion chamber 100 is an afterburner, the combustion chamber 100 also includes a tail cone 160, and each planar jet flame stabilizer 120 is evenly distributed in a ring.

[0089] Each planar jet flame stabilizer 120 is located behind the tail vertebra 160, or is arranged around the tail vertebra 160 with the tail vertebra 160 as the center.

[0090] In this embodiment, it should be noted that there are no limitations on the size of each planar jet flame stabilizer 120, such as... Figure 8 As shown, the dimensions of each planar jet flame stabilizer 120 can be identical. The planar jet flame stabilizer 120 is disposed behind the tail cone 160, or it is disposed around the tail cone 160 with the tail cone 160 as the center. Or, as... Figure 9 As shown, the dimensions of each planar jet flame stabilizer 120 may be different. Each planar jet flame stabilizer 120 is arranged alternately behind the tail vertebra 160 according to its own size. Alternatively, each planar jet flame stabilizer 120 is arranged alternately around the tail vertebra 160 with its own size as the center.

[0091] In this embodiment, the planar jet flame stabilizers are distributed in a ring shape; each planar jet flame stabilizer is located behind the tail cone, or is arranged around the tail cone with the tail cone as the center. This improves the efficiency of the combustion chamber in blocking high-speed incoming flow during operation, and further improves the stability of flame combustion in the combustion chamber.

[0092] In one embodiment, both the oil and gas input device 130 and the planar jet flame stabilizer 120 have a third channel and a fourth channel;

[0093] The third channel is used to transmit air to the planar jet flame stabilizer 120.

[0094] The fourth channel is used to transfer fuel to the planar jet flame stabilizer 120.

[0095] In this embodiment, if the combustion chamber 100 does not contain a first mixer, both the fuel-air input device 130 and the planar jet flame stabilizer 120 can be equipped with a third channel and a fourth channel. The third channel supplies air to the planar jet flame stabilizer 120, and the fourth channel supplies fuel to the planar jet flame stabilizer 120. The planar jet flame stabilizer 120 sprays fuel and air towards both sides in the direction of the high-speed incoming flow. After being sprayed, the fuel and air are atomized and mixed to form a planar jet.

[0096] In this embodiment, both the oil / gas input device and the planar jet flame stabilizer have a third channel and a fourth channel; the third channel transmits air to the planar jet flame stabilizer, and the fourth channel transmits fuel to the planar jet flame stabilizer. The arrangement of the third and fourth channels allows for the simultaneous transmission of fuel and air, improving the transmission efficiency of both.

[0097] In one embodiment, Figure 10 This is a second structural diagram of a planar jet flame stabilizer provided in this application embodiment. The flame stabilizer 120 includes a jet injection device 121, on which a jet nozzle is provided. The jet nozzle includes a first jet nozzle 122 and a second jet nozzle 123, and the jet nozzle is arranged along the spanwise direction of the jet injection device 121.

[0098] The jet injection device 121 is used to deliver air and fuel to the first jet nozzle 122 and the second jet nozzle 123.

[0099] The first jet nozzle 122 is used to eject air and fuel delivered by the jet injection device 121 along a first direction to form a first planar jet.

[0100] The second jet nozzle 123 is used to eject the 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.

[0101] The first planar jet and the second planar jet are used to form an aerodynamic barrier 124 and a return flow zone 125 behind the aerodynamic barrier under the action of the high-speed incoming flow.

[0102] Among them, the high-speed incoming flow is a high-speed airflow flowing towards the flame stabilizer 200. The high-speed incoming flow has the characteristics of low oxygen content, high flow velocity, low total pressure and uneven inlet temperature.

[0103] In this embodiment, the flame stabilizer 120 includes a jet injection device 121, on which jet nozzles are provided. The jet nozzles include a first jet nozzle 122 and a second jet nozzle 123, and the jet nozzles are arranged along the axial direction of the jet injection device 121. Figure 11As shown, the jet device 210 can be rectangular in shape, with the first jet nozzle 122 and the second jet nozzle 123 extending outwards on two sides of the jet device 121. The jet device 121 can have a fuel delivery channel and an air delivery channel inside. The fuel delivery channel supplies fuel to the first jet nozzle 122 and the second jet nozzle 123, and the air delivery channel supplies air to the first jet nozzle 122 and the second jet nozzle 123. Under the pressure difference between the inside and outside of the jet device 121, the first jet nozzle 122 ejects air and fuel along a first direction to form a first planar jet, and the second jet nozzle 123 ejects air and fuel along a second direction to form a second planar jet.

[0104] The jet injection device 121 may also be equipped with a pressure regulating device. The pressure regulating device generates pressure, so that the first jet nozzle 122 sprays air and fuel in a first direction to form a first planar jet, and the second jet nozzle 123 sprays air and fuel in a second direction to form a second planar jet. Alternatively, the pressure regulating device may be located outside the jet injection device 121. In this case, the jet injection device 121 and the pressure regulating device need to be connected by a conduit. The pressure regulating device provides pressure to the jet injection device 121, so that the first jet nozzle 122 and the second jet nozzle 123 form the first planar jet and the second planar jet. Under the action of the high-speed incoming flow, the first and second planar jets form an aerodynamic barrier 124 and a return flow zone 250 behind the aerodynamic barrier 124. The aerodynamic barrier 240 blocks most of the high-speed incoming flow, and the high-temperature combustion gas generated in the return flow zone 125 achieves continuous ignition of fresh fuel. In addition, a small portion of the high-speed incoming flow can still enter the return flow zone 125 from both sides of the aerodynamic barrier 124, so that the fuel and air in the return flow zone 125 can be mixed.

[0105] In this embodiment, the flame stabilizer includes a jet injection device with jet nozzles. The jet nozzles include a first jet nozzle and a second jet nozzle, which are arranged along the axial direction of the jet injection device. The jet injection device supplies air and fuel to the first and second jet nozzles. The first jet nozzle ejects the air and fuel supplied by the jet injection device along a first direction to form a first planar jet. The second jet nozzle ejects the air and fuel supplied by the jet injection device along a second direction to form a second planar jet. The second direction is opposite to the first direction. The first and second planar jets are used to form an aerodynamic barrier and a recirculation zone behind the aerodynamic barrier under the action of a high-speed incoming flow. Traditional blunt-body flame stabilizers rely on a large-area blunt-body structure as a barrier to block high-speed airflow, forming a recirculation zone behind the barrier to achieve stable flame combustion. However, existing bluff body flame stabilizers suffer from significant flow losses due to the large frontal area of ​​the bluff body structure, resulting in a substantial total pressure loss in the combustion chamber. Furthermore, the poor fuel-air mixing capability of bluff body stabilizers leads to lower fuel combustion efficiency. The planar jet-based flame stabilizer provided in this application is smaller in size compared to bluff body flame stabilizers. If the combustion chamber stops operating, the planar jet flame stabilizer does not generate a planar jet, allowing high-speed airflow to pass smoothly through the combustion chamber, thereby reducing flow resistance and total pressure loss. Compared to annular transverse jet stabilizers, it differs in that it uses aerodynamic barriers to block most of the high-speed airflow. Since there are no aerodynamic barriers at the ends of the jet injection device, some high-speed airflow can still enter the recirculation zone through the sides of the aerodynamic barriers, further improving the fuel-air mixing rate in the recirculation zone and thus improving fuel combustion efficiency.

[0106] In one embodiment, such as Figure 12 As shown, the combustion chamber 100 also includes a heat insulation and vibration isolation screen 170 and a casing 180 disposed outside the heat insulation and vibration isolation screen 170. The heat insulation and vibration isolation screen 170 is disposed around the combustion chamber 100 to isolate the high temperature and vibration generated by fuel combustion in the combustion chamber 100. The casing 180 is disposed outside the heat insulation and vibration isolation screen 170.

[0107] In this embodiment, by providing heat-insulating and vibration-damping screens and a casing around the combustion chamber, the high temperatures and vibrations generated by fuel combustion in the combustion chamber are isolated, thus improving the safety of the combustion chamber during operation.

[0108] In one embodiment, the combustion chamber includes a fuel injection device for acquiring and injecting fuel when the combustion chamber is in operation.

[0109] Among them, the fuel injection device can be a fuel injection rod.

[0110] A fuel injection device can be installed at the front end of the planar jet flame stabilizer 120 to acquire and inject fuel when the combustion chamber is operating. The fuel injection device can inject a portion of the fuel required by the combustion chamber, in which case the planar jet flame stabilizer 120 can inject the remaining fuel. Alternatively, the fuel injection device can inject all the fuel required by the combustion chamber, in which case the planar jet flame stabilizer 120 can inject only air.

[0111] In this embodiment, by setting up a fuel injection device, the combustion efficiency of the fuel in the combustion chamber can be further improved.

[0112] It should be understood that although the steps in the flowcharts of the above embodiments are shown sequentially according to the arrows, these steps are not necessarily executed in the order indicated by the arrows. Unless explicitly stated herein, there is no strict order restriction on the execution of these steps, and they can be executed in other orders. Moreover, at least some steps in the flowcharts of the above embodiments may include multiple steps or multiple stages. These steps or stages are not necessarily completed at the same time, but can be executed at different times. The execution order of these steps or stages is not necessarily sequential, but can be performed alternately or in turn with other steps or at least some of the steps or stages of other steps.

[0113] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0114] The above embodiments are merely illustrative of several implementation methods of this application, and their descriptions are relatively specific and detailed. However, they should not be construed as limiting the scope of this application. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this application should be determined by the appended claims.

Claims

1. A combustion chamber based on a planar jet flame stabilizer, characterized in that, The combustion chamber includes a combustion chamber inlet, multiple planar jet flame stabilizers, and an oil and gas input device connected to each of the planar jet flame stabilizers; each planar jet flame stabilizer includes a jet injection device, and the jet injection device is provided with a jet nozzle, the jet nozzle including a first jet nozzle and a second jet nozzle, the jet nozzle being arranged along the spanwise direction of the jet injection device; The oil and gas input device is used to acquire air and / or fuel when the combustion chamber is operating, and to deliver the air and / or fuel to the corresponding planar jet flame stabilizer; and to stop supplying air and fuel to the planar jet flame stabilizer when the combustion chamber is not operating, so as to prevent the formation of the planar jet and allow the high-speed incoming flow to flow smoothly through the combustion chamber. The planar jet flame stabilizer is used to spray the air and / or the fuel to form a planar jet, which is used to form an aerodynamic barrier and a recirculation zone behind the aerodynamic barrier under the action of the high-speed incoming flow into the combustion chamber inlet. The jet injection device is used to deliver air and / or fuel to the first jet nozzle and the second jet nozzle; The first jet nozzle is used to eject the air and / or fuel delivered by the jet injection device along a first direction to form a first planar jet; The second jet nozzle is used to eject the air and / or fuel delivered by the jet injection device in a second direction to form a second planar jet; The first planar jet and the second planar jet are used to form an aerodynamic barrier and a recirculation zone behind the aerodynamic barrier under the action of the high-speed incoming flow.

2. The combustion chamber according to claim 1, characterized in that, The combustion chamber includes a first mixer; the first mixer is disposed inside the oil and gas input device, or the first mixer is disposed inside the planar jet flame stabilizer; The first mixer is used to atomize and mix the air and the fuel to form a combustible mixture, and to deliver the combustible mixture to the planar jet flame stabilizer; The planar jet flame stabilizer is used to eject the combustible mixture to form the planar jet.

3. The combustion chamber according to claim 1, characterized in that, The internal components of the oil and gas input device include a first channel and a second channel, and the first mixer is disposed inside the planar jet flame stabilizer; The first channel is used to transmit the air to the planar jet flame stabilizer; The second channel is used to transfer the fuel to the planar jet flame stabilizer; The planar jet flame stabilizer is used to acquire the air delivered by the first channel and the fuel delivered by the second channel, and to atomize and mix the air and the fuel through the first mixer to form a combustible mixture.

4. The combustion chamber according to claim 1, characterized in that, The combustion chamber inlet includes an internal combustion chamber duct inlet and an external combustion chamber duct inlet; The combustion chamber inlet is used to introduce the airflow from the inlet into the combustion chamber; The outer duct inlet of the combustion chamber is used to introduce the airflow from the outer duct into the combustion chamber.

5. The combustion chamber according to claim 4, characterized in that, The combustion chamber also includes a second mixer; The second mixer is used to mix the acquired inner duct airflow and outer duct airflow to form the high-speed incoming flow.

6. The combustion chamber according to claim 1, characterized in that, If the combustion chamber is an afterburner, the combustion chamber also includes a tail cone, and each of the planar jet flame stabilizers is evenly distributed in a ring; Each of the planar jet flame stabilizers is disposed behind the tail vertebra, or is disposed around the tail vertebra with the tail vertebra as the center.

7. The combustion chamber according to claim 1, characterized in that, Both the oil and gas input device and the planar jet flame stabilizer have a third channel and a fourth channel; The third channel is used to transmit the air to the planar jet flame stabilizer; The fourth channel is used to transfer the fuel to the planar jet flame stabilizer.

8. The combustion chamber according to claim 1, characterized in that, The combustion chamber also includes a heat insulation and vibration isolation screen and a casing disposed outside the heat insulation and vibration isolation screen.

9. The combustion chamber according to any one of claims 1-8, characterized in that, The combustion chamber includes a fuel injection device; The fuel injection device is used to acquire the fuel and inject the fuel when the combustion chamber is in operation.

10. The combustion chamber according to claim 1, characterized in that, The fuel includes gaseous fuels and / or liquid fuels.

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