A direct connection burner and engine

Abstract

The application provides a direct connection combustor and engine, which comprises a combustor body, and the inside of the combustor body is sequentially divided into a gas flow conversion section, a fuel injection section and a fuel injection section which are communicated with each other according to the gas flow direction; the gas flow conversion section comprises ram channels, turbofan gas flow channels and turbine gas flow channels which are sequentially arranged in the inside of the combustor body and are communicated with each other in the circumferential direction; the outlets of any channel of the ram channels, the turbofan gas flow channels and the turbine gas flow channels are closed or opened, the mixing section, the ram channels, the turbofan gas flow channels and the turbine gas flow channels are blocked or communicated with each other, the gas flow in the communicated channels and the fuel injected from the fuel injection section enter the fuel injection section to mix and burn together, and the burned gas is sprayed out. By arranging three gas channels which are communicated with each other and can be combined to communicate with each other, a multi-channel direct connection combustor is formed, which can not only complete various cycle independent working combustion tests, but also complete the combustion test of common working during cycle switching.

Description

Technical Field

[0001] This invention belongs to the field of combined cycle engine technology, specifically relating to a direct-drive combustor and engine. Background Technology

[0002] Wide-range hypersonic flight is the next important direction for the development of aerospace technology. Combined propulsion is an important technical approach to achieve horizontal takeoff and landing, reusability, and efficient operation across a wide speed range for aircraft. Turbine-based combined propulsion combines turbine and ramjet cycles, enabling zero-speed takeoff, high specific impulse, and wide-range flight capabilities. Series turbine-based combined propulsion uses the same combustor in all cycles across the entire speed range, significantly reducing engine weight and increasing thrust-to-weight ratio compared to parallel combined propulsion, making it a superior hypersonic propulsion solution. In the design of air-breathing engine combustors, direct-drive testing is an important method for verifying the wide-range performance of the combustor. Direct-drive combustors are used to simulate the combustors of different engines in direct-drive tests. The test simulates high-enthalpy incoming airflow under different flight altitude and speed conditions using fuel gas produced by burning alcohol, air, and oxygen in a certain proportion. This simulated air is then introduced into the direct-drive combustor for combustion, thus simulating the combustion state of different engine combustors under real flight conditions on the ground.

[0003] Traditional direct-drive combustors only consider a single power cycle and do not require switching between cycles. However, direct-drive combustors in series turbine-based combined cycle power systems need to accommodate multiple cycle modes. The combustor must not only meet the independent combustion test requirements of the turbine cycle and the ramjet cycle, but also the joint combustion test requirements when switching between the two cycles. Therefore, designing a direct-drive combustor that can not only complete combustion tests for each cycle independently, but also for the combined combustion test requirements when switching between cycles is the main challenge in the design of series turbine-based combined cycle power combustors. Summary of the Invention

[0004] To address the issue of insufficient flexibility in the use of existing burners, this invention provides a multi-channel direct-connected burner and engine applicable to series turbine-based combined power systems, capable of performing combustion tests not only for independent operation of various cycles but also for joint operation during cycle switching.

[0005] To achieve the above objectives, the present invention provides the following technical solution:

[0006] A direct-drive burner includes a burner body, wherein the interior of the burner body is divided into an interconnected airflow conversion section, a fuel injection section, and a fuel injection section according to the airflow direction.

[0007] The airflow conversion section includes a ramming channel, a turbofan airflow channel, and a turbine airflow channel that are sequentially arranged and interconnected inside the burner body along the circumferential direction; the burner body is provided with inlets that are respectively connected to the ramming channel, the turbofan airflow channel, and the turbine airflow channel.

[0008] By closing or opening the outlet of any of the ram channel, turbofan airflow channel and turbine airflow channel, the fuel injection section, ram channel, turbofan airflow channel and turbine airflow channel are controlled to block or connect with each other. The airflow in the connected channel enters the fuel injection section together with the fuel injected by the fuel injection section for mixing and combustion, and then the gas is ejected.

[0009] Preferably, the fuel injection section includes a mixing section, a combustion section, and a tail nozzle that are sequentially connected to the fuel injection section.

[0010] Preferably, a first electromagnet and a first slider with a permanent magnet inside are provided on the side wall at the outlet of the stamping channel. The first electromagnet controls the first slider to move forward and backward, connecting or blocking the stamping channel with other channels.

[0011] The side wall at the outlet of the turbofan airflow channel is provided with a second electromagnet and a second slider with a permanent magnet inside. The second electromagnet controls the second slider to move forward and backward, connecting or blocking the turbofan airflow channel with other channels.

[0012] A third electromagnet and a third slider with a permanent magnet inside are provided on the side wall at the outlet of the turbine airflow channel. The third electromagnet controls the third slider to move forward and backward, connecting or blocking the turbine airflow channel with other channels.

[0013] Preferably, the burner body has a central cavity biased towards the airflow conversion section, and the outlets of the ram airflow channel, the turbofan airflow channel, and the turbine airflow channel are all close to the sidewall of the central cavity.

[0014] Preferably, the first electromagnet is disposed within the burner body wall at the junction of the stamping channel and the blending section, the first slider is disposed on the inner sidewall of the stamping channel, and the second electromagnet, the second slider, the third electromagnet, and the third slider are all disposed on the sidewall of the central cavity, with the second electromagnet and the third electromagnet close to the blending section, and the second slider and the third slider far from the blending section.

[0015] Preferably, the fuel injection section includes an injection channel surrounding the central cavity and multiple secondary support plates arranged circumferentially along the injection channel. The secondary support plates are inclined and have multiple fuel injection holes.

[0016] Preferably, the burner body has at least one main support plate that communicates with the outside along the circumferential direction, and the main support plate is connected to the wall of the stamping channel, the turbofan airflow channel and the turbine airflow channel.

[0017] Preferably, a first cable channel is provided on the outer wall of the burner body above the first electromagnet, and the power supply line supplies power to the first electromagnet through the first cable channel;

[0018] The outer wall of the central cavity is provided with a second cable channel and a third cable channel below the second and third electromagnets. The main support plate has a fourth cable channel communicating with the central cavity. The power supply line supplies power to the second and third electromagnets through the second, third and fourth cable channels.

[0019] Preferably, the stamping channel is provided with a device nozzle and an isolation section in sequence along the airflow direction. The device nozzle is used to accelerate the airflow passing through it to supersonic speed, and the isolation section is used to decelerate the supersonic airflow passing through it.

[0020] The present invention also provides an engine including a combustion chamber and a direct-drive burner disposed in the combustion chamber as described above.

[0021] The direct-drive burner provided by this invention has the following beneficial effects:

[0022] The airflow conversion section of the present invention includes a ramming channel, a turbofan airflow channel, and a turbine airflow channel that are sequentially arranged and interconnected inside the burner body along the circumferential direction. By closing or opening the outlet of any of the ramming channel, turbofan airflow channel, and turbine airflow channel, the mixing section, ramming channel, turbofan airflow channel, and turbine airflow channel are controlled to be mutually blocked or connected. The airflow in the connected channel enters the fuel injection section together with the fuel injected by the fuel injection section for mixing and combustion, and then the gas is ejected.

[0023] By setting up three interconnected gas channels, which can be arbitrarily combined and connected, a multi-channel direct-connected burner is formed. It can not only complete combustion tests of various cycles working independently, but also complete combustion tests of working together when switching cycles. Attached Figure Description

[0024] To more clearly illustrate the embodiments and design schemes of the present invention, the accompanying drawings required for this embodiment will be briefly described below. The drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0025] Figure 1This is a schematic diagram of the flow channel for the cyclic switching state of the direct-connected burner in Embodiment 1 of the present invention;

[0026] Figure 2 This is a schematic diagram of the flow channel of the present invention in a turbofan cycle state;

[0027] Figure 3 This is a schematic diagram of the present invention in the stamping cycle state.

[0028] Explanation of reference numerals in the attached figures:

[0029] 1. Stamping channel, 2. Turbine airflow channel, 3. Turbine airflow channel, 4. Equipment nozzle, 5. Isolation section, 6. Injection channel, 7. Mixing section, 8. Diffusion section, 9. Combustion section, 10. Tail nozzle, 11. Main support plate A, 12. Secondary support plate B, 11. First slider, 12. First electromagnet, 13. First cable channel, 21. Second slider, 22. Second electromagnet, 23. Second cable channel, 31. Third slider, 32. Third electromagnet, 33. Third cable channel, 34. Central cavity C. Detailed Implementation

[0030] To enable those skilled in the art to better understand and implement the technical solutions of the present invention, the present invention will be described in detail below with reference to the accompanying drawings and specific embodiments. The following embodiments are only used to more clearly illustrate the technical solutions of the present invention and should not be construed as limiting the scope of protection of the present invention.

[0031] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing the technical solution of this invention 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. Therefore, they should not be construed as limitations on this invention.

[0032] Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance. In the description of this invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "connected" or "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; 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. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances. In the description of this invention, unless otherwise stated, "a plurality of" means two or more, which will not be elaborated further here.

[0033] Example 1

[0034] This invention provides a direct-drive combustor, specifically a series-connected turbine-based combined power multi-mode shared direct-drive combustor. The series connection in this invention is reflected in the fact that multiple modes of the combustor use the same combustion chamber, such as... Figure 1 As shown, it includes the burner body, and the interior of the burner body is divided into an interconnected airflow conversion section, a fuel injection section and a fuel injection section according to the airflow direction.

[0035] Specifically, in this embodiment, the fuel injection section includes a mixing section 7, a combustion section 9, and a tail nozzle 10, which are sequentially connected to the fuel injection section. In this embodiment, a diffuser section 8 is provided between the mixing section 7 and the combustion section 9. The diameters of the mixing section 7, the diffuser section 8, and the combustion section 9 increase sequentially, and the diameter of the tail nozzle 10 is smaller than the diameter of the mixing section 7. The diffuser section 8 is located downstream of the mixing section 7, the combustion section 9 is located downstream of the diffuser section 8, and the tail nozzle 10 is located downstream of the combustion section 9.

[0036] To achieve the mixing of multiple airflows, in this embodiment, the airflow conversion section includes a ram channel 1, a turbo fan airflow channel 2, and a turbine airflow channel 3, which are arranged sequentially and interconnected inside the burner body along the circumferential direction. The burner body is provided with inlets that are respectively connected to the ram channel 1, the turbo fan airflow channel 2, and the turbine airflow channel 3. By closing or opening the outlet of any of the channels in the ram channel 1, the turbo fan airflow channel 2, and the turbine airflow channel 3, the mixing section 7, the ram channel 1, the turbo fan airflow channel 2, and the turbine airflow channel 3 are controlled to be mutually blocked or connected. The airflow in the connected channel enters the fuel injection section together with the fuel injected by the fuel injection section 6 for mixing and combustion, and then the gas is ejected.

[0037] Furthermore, in this embodiment, the opening or closing of any channel outlet is achieved through the following structure: A first electromagnet 12 and a first slider 11 with a permanent magnet are provided on the side wall of the outlet of the stamping channel 1. The first electromagnet 12 controls the forward and reverse movement of the first slider 11, connecting or blocking the stamping channel 1 with the other channels. A second electromagnet 22 and a second slider 21 with a permanent magnet are provided on the side wall of the outlet of the turbofan airflow channel 2. The second electromagnet 22 controls the forward and reverse movement of the second slider 21, connecting or blocking the turbofan airflow channel 2 with the other channels. A third electromagnet 32 ​​and a third slider 31 with a permanent magnet are provided on the side wall of the outlet of the turbine airflow channel 3. The third electromagnet 32 ​​controls the forward and reverse movement of the third slider 31, connecting or blocking the turbine airflow channel 3 with the other channels. In addition, the present invention can also achieve the opening and closing of each channel through other components such as a switching valve at the outlet. The present invention is not limited to this structure for achieving the opening or closing of any channel outlet; any structure capable of achieving the opening or closing of any channel outlet is applicable to the present invention.

[0038] Furthermore, in this embodiment, the intermediate biased airflow conversion section of the burner body has a central cavity C, and the outlets of the ram channel 1, the turbofan airflow channel 2, and the turbine airflow channel 3 are all close to the side wall of the central cavity C.

[0039] To ensure the electromagnets are aligned horizontally with the permanent magnets, maximizing the force generated in the direction of slider movement and minimizing the force perpendicular to it, thereby improving energy efficiency, in this embodiment, the first electromagnet 12 is disposed within the burner body wall at the junction of the stamping channel 1 and the mixing section 7. The first slider 11 is disposed on the inner wall of the stamping channel 1. The second electromagnet 22, the second slider 21, the third electromagnet 32, and the third slider 31 are all disposed on the side wall of the central cavity C. The second electromagnet 22 and the third electromagnet 32 ​​are closer to the mixing section 7, while the second slider 21 and the third slider 31 are farther away from the mixing section 7. In other words, the first electromagnet 12, the second electromagnet 22, and the third electromagnet 32 ​​are fixed within the wall behind each slider.

[0040] Furthermore, in this embodiment, the fuel injection section includes an injection channel 6 surrounding the central cavity C and multiple auxiliary support plates B arranged circumferentially along the injection channel 6. The auxiliary support plates B are inclined and have multiple fuel injection holes. A kerosene channel is provided inside the auxiliary support plate B, and kerosene enters the channel from outside the burner. The leading edge of the auxiliary support plate B is set as an inclined surface, and fuel injection holes are opened on the inclined surface. Kerosene enters the injection holes from the channel and is injected into the mixing section 7 of the burner.

[0041] To improve the overall stability of the burner, in this embodiment, at least three main support plates A, communicating with the outside, are arranged circumferentially inside the burner body. The main support plates A are connected to the walls of the stamping channel 1, the turbofan airflow channel 2, and the turbine airflow channel 3. In this embodiment, the three main support plates are distributed at equal intervals of 120 degrees, and the main support plates A are fixedly connected to the walls of the three channels in a certain way, such as by screws or by welding.

[0042] To power the electromagnets, in this embodiment, a first cable channel 13 is provided on the outer wall of the burner body above the first electromagnet 12, and the power supply line powers the first electromagnet 12 through the first cable channel 13. A second cable channel 23 and a third cable channel 33 are provided on the outer wall of the central cavity C below the second electromagnet 22 and the third electromagnet 32. A fourth cable channel communicating with the central cavity C is located inside the main support plate A. The power supply line powers the second electromagnet 22 and the third electromagnet 32 ​​through the second cable channel 23, the third cable channel 33, and the fourth cable channel. The central cavity C greatly reduces the weight of the burner. Furthermore, the main support plate A not only provides support, but the structure of the main support plate A and the central cavity C also serves as the cable channel for the second electromagnet 22 and the third electromagnet 32, greatly improving space utilization.

[0043] Furthermore, in this embodiment, a nozzle 4 and an isolation section 5 are sequentially arranged along the airflow direction within the ramjet channel 1. The nozzle 4 is used to accelerate the airflow passing through it to supersonic speeds, while the isolation section 5 is used to decelerate the supersonic airflow passing through it. The nozzle acceleration simulates the conditions of a ramjet engine intake during high-altitude flight, and the isolation section contains a series of oblique shock waves, which have a certain deceleration and pressurization effect. The multi-channel direct-drive combustor operates within a wide speed range, with the low-speed burner operating in a turbofan cycle and the high-speed burner operating in a ramjet cycle.

[0044] Specifically, the function of the nozzle 4 and the isolation section 5 is to provide the velocity field required for the combustion chamber inlet. Specifically, the nozzle 4 is equivalent to a Laval nozzle. The airflow from the ramjet passage 1 is subsonic, but after passing through the Laval nozzle, it is accelerated to supersonic speed, simulating the airflow at the throat of a real ramjet engine inlet. The air entering the ramjet passage is subsonic, while the air exiting the nozzle 4 is supersonic. A series of oblique shock waves is formed within the isolation section 5 to decelerate the supersonic airflow to subsonic speed.

[0045] The working principle of the direct-drive burner in this embodiment is as follows:

[0046] By controlling the switching of the power supply and the direction of the current to the first electromagnet 12, the second electromagnet 22, and the third electromagnet 32, the magnetic poles inside the electromagnets can be changed, thereby exerting a force on each slider to open or close each airflow channel, thus switching the engine's circulation mode. In the circulation switching state, such as... Figure 1 Each slider moves from one end to the other under the force of the electromagnet. At this time, the stamping channel 1, the turbofan airflow channel 2, and the turbine airflow channel 3 are all open, and the three airflows converge and mix and burn in the mixing section 7 and the combustion section 8. Figure 2In turbofan cycle mode, the first electromagnet 12 generates a pulling force to move the first slider 11 to the right end position, closing the ram channel 1; the second electromagnet 22 and the third electromagnet 32 ​​generate a pulling force to move the second slider 21 and the third slider 31 to the right end position, opening the turbofan airflow channel 2 and the turbine airflow channel 3. Figure 3 In the ramming cycle state, the first electromagnet 12 generates a repulsive force to push the first slider 11 to the left end position, opening the ramming channel 1; the second electromagnet 22 and the third electromagnet 32 ​​generate a thrust to push the second slider 21 and the third slider 31 to the right end position, closing the turbofan airflow channel 2 and the turbine airflow channel 3. In all cycle modes, after the airflow passes through the injection channel 6, it mixes with the kerosene injected from the auxiliary support plate B in the mixing section 7, decelerates and pressurizes in the diffuser section 8, undergoes combustion reaction and heat release in the combustion section 9, and converts internal energy into kinetic energy in the tail nozzle 10, which is then ejected at high speed to form thrust.

[0047] Example 2

[0048] Based on this, the present invention also provides an engine, which includes a combustion chamber and a direct-connected burner disposed in the combustion chamber as described in Example 1. The structure of the burner will not be further described here.

[0049] The direct-drive burner provided by this invention has the following advantages:

[0050] (1) A multi-channel direct-drive burner for use in series turbine-based combined power is provided, which can not only complete combustion tests of various cycles working independently, but also complete combustion tests of working together when switching cycles.

[0051] (2) A simple and fast-response cyclic switching method is provided. By changing the direction of the current in the electromagnet, the magnetic poles are changed, thereby generating a pulling or pushing force on the channel isolation slider equipped with a permanent magnet to open or close the airflow channel.

[0052] (3) It provides a simple, multi-functional main support plate and central cavity structure. The main support plate supports the multiple layers of walls inside and outside the burner, and the central cavity can greatly reduce the weight of the burner. In addition, the main support plate and central cavity structure also serve as the cable channel for the second and third electromagnets, greatly improving space utilization.

[0053] It should be noted that the specific embodiments described above enable those skilled in the art to more fully understand the present invention, but do not limit the present invention in any way. Therefore, although the present invention has been described in detail in this specification and embodiments, those skilled in the art should understand that modifications or equivalent substitutions can still be made to the present invention; and all technical solutions and improvements that do not depart from the spirit and scope of the present invention are covered within the protection scope of the present invention patent. No reference numerals in the claims should be construed as limiting the scope of the claims. Any simple variations or equivalent substitutions of technical solutions that can be readily obtained by those skilled in the art within the scope of the technology disclosed in the present invention are within the protection scope of the present invention.

Claims

1. A direct-drive burner, characterized in that, It includes a burner body, the interior of which is divided into an interconnected airflow conversion section, a fuel injection section and a fuel injection section according to the airflow direction; The airflow conversion section includes a ramming channel (1), a turbofan airflow channel (2), and a turbine airflow channel (3) that are sequentially arranged and interconnected inside the burner body along the circumferential direction; the burner body is provided with inlets that are respectively connected to the ramming channel (1), the turbofan airflow channel (2), and the turbine airflow channel (3); By closing or opening the outlet of any of the channels in the ramming channel (1), the turbofan airflow channel (2) and the turbine airflow channel (3), the fuel injection section, the ramming channel (1), the turbofan airflow channel (2) and the turbine airflow channel (3) are controlled to block or connect with each other. The airflow in the connected channel and the fuel injected by the fuel injection section enter the fuel injection section together for mixing and combustion before the gas is ejected. The side wall at the outlet of the stamping channel (1) is provided with a first electromagnet (12) and a first slider (11) with a permanent magnet inside. The first electromagnet (12) controls the first slider (11) to move forward and backward, connecting or blocking the stamping channel (1) with other channels. The side wall at the outlet of the turbofan airflow channel (2) is provided with a second electromagnet (22) and a second slider (21) with a permanent magnet inside. The second electromagnet (22) controls the second slider (21) to move forward and backward, connecting or blocking the turbofan airflow channel (2) with other channels. The turbine airflow channel (3) has a third electromagnet (32) and a third slider (31) with a permanent magnet inside on the side wall at the outlet. The third electromagnet (32) controls the third slider (31) to move forward and backward, connecting or blocking the turbine airflow channel (3) with other channels.

2. The direct-drive burner according to claim 1, characterized in that, The fuel injection section includes a mixing section (7), a combustion section (9), and a tail nozzle (10) that are sequentially connected to the fuel injection section.

3. The direct-drive burner according to claim 2, characterized in that, The burner body has a central cavity (C) in the middle of the airflow conversion section, and the outlets of the ram air passage (1), the turbo fan airflow passage (2) and the turbine airflow passage (3) are all close to the side wall of the central cavity (C).

4. The direct-drive burner according to claim 3, characterized in that, The first electromagnet (12) is disposed in the burner body wall at the junction of the stamping channel (1) and the mixing section (7). The first slider (11) is disposed on the inner side wall of the stamping channel (1). The second electromagnet (22), the second slider (21), the third electromagnet (32) and the third slider (31) are all disposed on the side wall of the central cavity (C). The second electromagnet (22) and the third electromagnet (32) are close to the mixing section (7), and the second slider (21) and the third slider (31) are far away from the mixing section (7).

5. The direct-drive burner according to claim 3, characterized in that, The fuel injection section includes an injection channel (6) surrounding the central cavity (C) and multiple auxiliary support plates (B) arranged circumferentially along the injection channel (6). The auxiliary support plates (B) are inclined and have multiple fuel injection holes.

6. The direct-drive burner according to claim 5, characterized in that, The burner body has at least three main support plates (A) arranged circumferentially inside, which are connected to the outside. The main support plates (A) are connected to the walls of the stamping channel (1), the turbofan airflow channel (2), and the turbine airflow channel (3).

7. The direct-drive burner according to claim 6, characterized in that, The outer wall of the burner body is provided with a first cable channel (13) above the first electromagnet (12), and the power line supplies power to the first electromagnet (12) through the first cable channel (13); The outer wall of the central cavity (C) is provided with a second cable channel (23) and a third cable channel (33) located below the second electromagnet (22) and the third electromagnet (32). The main support plate (A) has a fourth cable channel inside that communicates with the central cavity (C). The power supply line supplies power to the second electromagnet (22) and the third electromagnet (32) through the second cable channel (23), the third cable channel (33) and the fourth cable channel.

8. The direct-drive burner according to claim 1, characterized in that, The stamping channel (1) is provided with a device nozzle (4) and an isolation section (5) in sequence along the airflow direction. The device nozzle (4) is used to accelerate the airflow passing through it to supersonic speed, and the isolation section (5) is used to decelerate the supersonic airflow passing through it.

9. An engine comprising a combustion chamber, characterized in that, It also includes a direct-connected burner as described in any one of claims 1 to 8 disposed in the combustion chamber.

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