A compact dual-combustion chamber turbo-ramjet combined engine and engine

Abstract

This invention relates to a compact dual-combustion chamber and engine of a turbo-ramjet combined engine. The dual combustion chamber includes an outer bypass casing with multiple sets of casing fuel supply channels running through its circular outer wall at equal angles. The area between the intermediate casing and the outer bypass casing forms an annular outer bypass duct. The outer wall of the intermediate casing has an outer concave cavity, and the ramjet combustion chamber is formed between the outer concave cavity and the outer bypass casing. The turbine combustion chamber is located inside the intermediate casing and has a flow divider ring assembly. The area between its outer shell and the inner wall of the intermediate casing forms an annular inner duct. Its outer shell has an inner concave cavity, and the turbine combustion chamber and the ramjet combustion chamber share an integrated fuel supply device, which is connected to the casing fuel supply channels. This invention, with its combined combustion chambers sharing an integrated fuel supply device and a portion of the casing being shared, can effectively improve the engine's compactness, reduce overall weight, and increase thrust-to-weight ratio.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and more specifically to a compact dual-combustion chamber turbo-ramjet combined engine and engine. Background Technology

[0002] Thrust-to-weight ratio is an important indicator for measuring the technological level of aero engines. As the thrust-to-weight ratio increases, the maneuverability of aircraft is significantly improved. In order to further improve the thrust-to-weight ratio of engines, more and more integrated technologies are being applied to the main combustion chamber and afterburner of aero engines. The fundamental purpose is to achieve a higher space utilization rate inside the engine, improve compactness, and reduce the overall weight of the engine.

[0003] In existing turbo-ramjet combined engines, the fuel supply and flame stabilization devices of the main combustion chamber and the afterburner are independent. In turbine mode, the main combustion chamber and the afterburner work together, but in ramjet mode, the afterburner is used as the ramjet combustion chamber. Because the two combustion chambers are independently distributed and operate, the system has many components, low space utilization, and a long overall engine length, making it difficult to reduce the overall weight.

[0004] Therefore, how to provide a compact dual-combustion chamber for a turbo-ramjet combined engine is a problem that urgently needs to be solved by those skilled in the art. Summary of the Invention

[0005] Therefore, one objective of this invention is to propose a compact dual-combustion chamber for a turbo-ramjet combined engine, which solves the problem of numerous components and low space utilization in existing engines with two combustion chambers.

[0006] Another object of the present invention is to provide a compact dual-combustion chamber engine with a turbo-ramjet combined engine.

[0007] The present invention provides a compact dual-combustion chamber for a turbo-ramjet combined engine, comprising:

[0008] The outer bypass casing has multiple sets of casing oil supply channels that are equally spaced through its circular outer wall, and it has an air inlet and an air outlet.

[0009] An intermediate casing, wherein the area between the intermediate casing and the outer bypass casing forms an annular outer bypass; the outer wall of the intermediate casing has an external cavity, and a ramjet combustion chamber is formed between the external cavity and the outer bypass casing;

[0010] A turbine combustion chamber is located inside the intermediate casing and has a flow splitting ring assembly. The area between its outer shell and the inner wall of the intermediate casing forms an annular inner channel. Its outer shell has a concave cavity, and the concave cavity and the inner shell form a turbine combustion chamber.

[0011] An integrated oil supply device is provided, which is shared by the ramjet combustion chamber and the turbine combustion chamber, and is connected to the oil supply channel of the casing.

[0012] Furthermore, the integrated fuel supply device is located inside the outer bypass casing and is installed on the ramjet combustion chamber and the turbine combustion chamber.

[0013] Furthermore, the integrated oil supply device includes:

[0014] Multiple outer support plates are distributed at equal angles between the outer bypass casing and the intermediate casing. Each outer support plate has a main combustion fuel supply pipe, an inner cavity fuel supply pipe, and an outer cavity fuel supply pipe installed in parallel inside, and is connected to the fuel supply channel of the casing. The number and included angle of the main combustion fuel supply pipe, the inner cavity fuel supply pipe, and the outer cavity fuel supply pipe are consistent with those of the outer support plates.

[0015] There are multiple inner support plates, which correspond to the number and angle of the outer support plates and are located between the inner shell and the outer shell. Each inner support plate has a circular channel II for inserting the main fuel supply pipe. The circular channel II has turbine combustion chamber main fuel injection holes on both radial sides opposite to the turbine combustion chamber.

[0016] Furthermore, the included angle between two adjacent outer support plates is 15°-30°. The outer support plates are provided with main fuel injection holes for the ramjet combustion chamber on both sides opposite to the ramjet combustion chamber. Each outer support plate is provided with holes I, holes II and a circular channel I for installing the main fuel supply pipe, the inner cavity fuel supply pipe and the outer cavity fuel supply pipe. The main fuel injection hole for the ramjet combustion chamber is located in the circular channel I. Most of the fuel passes through the main fuel injection hole for the ramjet combustion chamber and the main fuel injection hole for the turbine combustion chamber and is mixed into the ramjet combustion chamber and the turbine combustion chamber by lateral side injection.

[0017] Furthermore, the main fuel supply pipe is a straight pipe; the inner concave cavity fuel supply pipe includes an L-shaped fuel pipe and an inner concave cavity annular fuel pipe connected in sequence, and the inner concave cavity annular fuel pipe is provided with an inner concave cavity nozzle facing the inner concave cavity; the outer concave cavity fuel supply pipe includes a short fuel pipe and an outer concave cavity annular fuel pipe connected in sequence, and the outer concave cavity annular fuel pipe is provided with an outer concave cavity nozzle facing the outer concave cavity; a small portion of fuel passes through the inner concave cavity nozzle and the outer concave cavity nozzle, and enters the inner concave cavity and the outer concave cavity respectively in a direct injection manner.

[0018] Furthermore, both the inner and outer walls of the intermediate casing are provided with cavities. The inner wall cavity is used to assemble the inner cavity, and the outer wall cavity serves as the outer cavity. An oil pipe channel is provided at the assembly point of the intermediate casing and the outer support plate for inserting the main combustion fuel supply pipe and the inner cavity fuel supply pipe. The axial position of the inner cavity is consistent with the position of the outer cavity, and the two are symmetrically distributed. The front wall of the inner cavity is on the same plane as the tail edge of the inner support plate. An outer cavity fuel supply hole is opened on the front wall of the outer cavity for installing the outer cavity nozzle. The number of outer cavity fuel supply holes is twice that of the outer support plate. The outer cavity and the outer support plate work together to achieve stable combustion in the ramjet combustion chamber.

[0019] Furthermore, the flow splitter ring assembly includes: an outer flow splitter ring connected to the outer shell, and an inner flow splitter ring connected to the inner shell. The outer flow splitter ring, the inner flow splitter ring, and the intermediate casing divide the internal airflow into an internal mainstream, a cavity secondary flow, and an internal secondary flow. The internal mainstream flows between the outer flow splitter ring and the inner flow splitter ring, and the cavity secondary flow flows between the outer flow splitter ring and the intermediate casing.

[0020] Furthermore, both the inner and outer split rings are composed of a straight section and a diffuser section. The straight section is used to guide the main flow, and the diffuser section diffuses and decelerates the main flow.

[0021] Furthermore, the concave cavity has a front air passage gap, a rear air passage gap, and an oil supply hole for the concave cavity. The front air passage gap and the rear air passage gap inject the secondary flow of the concave cavity into the concave cavity to form a stable vortex structure. The concave cavity nozzle is installed in the oil supply hole for the concave cavity.

[0022] Furthermore, the inner shell includes an inner shell layer and an outer shell layer. The outer shell layer is connected to the inner flow divider ring. The inner shell layer is the innermost layer of the combustion chamber and forms an interlayer with the outer shell layer. After the secondary flow enters the interlayer, it flows into the main flow through the cooling holes and mixing holes of the inner shell layer, thereby cooling the inner shell and improving combustion performance.

[0023] The outer shell is provided with cooling holes and mixing holes of the same size as the cooling holes and mixing holes of the inner shell; a portion of the secondary flow in the concave cavity cools the outer shell through the cooling holes; the inner concave cavity and the inner support plate work together to achieve stable combustion in the turbine combustion chamber;

[0024] The outer casing and the intermediate casing form a closed space, and the secondary flow in the concave cavity can only be drawn into the main flow of the inner cavity by the front and rear air gaps, the cooling holes of the outer casing, and the mixing holes of the outer casing.

[0025] Furthermore, the cooling holes of the outer shell and the cooling holes of the inner shell are at a 45° angle to the wall surface of the outer shell and the wall surface of the inner shell, respectively, and the included angle between two adjacent cooling holes in each row in the circumferential direction is 7.5°; the mixing holes of the outer shell and the mixing holes of the inner shell are perpendicular to the wall surface of the outer shell and the wall surface of the inner shell, respectively, and the included angle between two adjacent mixing holes in each row in the circumferential direction is 30°.

[0026] The present invention also provides an engine having a compact dual combustion chamber of a turbo-ramjet combined engine, comprising an engine body and a compact dual combustion chamber of a turbo-ramjet combined engine as described in any of the preceding claims disposed therein.

[0027] As can be seen from the above technical solution, compared with the prior art, the present invention has the following beneficial effects:

[0028] The combined combustion chamber provided by this invention is based on ultra-compact combustion technology and features an integrated design. The combined combustion chamber shares an integrated fuel supply device and some shell components, which can effectively improve the compactness of the engine, thereby reducing the overall mass, increasing the thrust-to-weight ratio, and widening the flight envelope of the turbine engine. This helps the aircraft solve the thrust trap problem and achieve subsonic to hypersonic flight objectives.

[0029] In this invention, the outer bypass casing is the outermost layer of the turbine-ramjet compact combined combustion chamber. An intermediate casing and an inner casing are arranged inside the outer casing, and the outer bypass and inner bypass are formed sequentially from the outside to the inside. In the inner and outer bypass, there are concave cavity support plate flame stabilization devices, namely inner support plate and inner cavity, and outer support plate and outer cavity. The integrated fuel supply device can supply fuel to the combined combustion chamber in different working modes. In turbine mode, only the turbine combustion chamber is supplied with fuel, and the inner main combustion zone is formed in the backflow area of ​​the inner support plate trailing edge, and stable vortex combustion is formed in the inner cavity. In transition mode, the turbine combustion chamber and the ramjet combustion chamber are supplied with fuel simultaneously. Based on the stable combustion in the turbine combustion chamber, the outer support plate and the outer cavity form a stable combustion zone. In ramjet mode, since the inner cavity is closed, no airflow passes through, and only the outer bypass flows. At this time, the ramjet combustion chamber is supplied with fuel alone. The turbine-ramjet combined combustion chamber based on the dual-cavity structure utilizes ultra-compact combustion technology and integrates the fuel supply device of the combined combustion chamber with a shared casing structure, which greatly improves the engine space utilization and thrust-to-weight ratio. The combustion chamber operates successively in different modes, enabling the aircraft to fly from subsonic to hypersonic speeds. Attached Figure Description

[0030] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0031] Figure 1 A schematic diagram (half-sectional view) of a compact dual-combustion chamber in a turbo-ramjet combined engine provided by the present invention.

[0032] Figure 2 This is a two-dimensional cross-sectional schematic diagram of a compact dual combustion chamber in a turbo-ramjet combined engine according to the present invention;

[0033] Figure 3 The schematic diagram of the integrated oil supply device is shown.

[0034] Figure 4 The cross-sectional view of the external support structure is shown.

[0035] Figure 5 The sectional view of the internal support structure is shown.

[0036] Figure 6 The diagram shows a half-section of the ramjet combustion chamber and the turbine combustion chamber;

[0037] Figure 7 for Figure 6 Enlarged schematic diagram of part A;

[0038] Figure 8 for Figure 6 Enlarged schematic diagram of part B;

[0039] Figure 9 for Figure 6 Enlarged schematic diagram of part C;

[0040] Figure 10 The diagram illustrates the airflow and fuel flow trajectory.

[0041] Figure 11 The schematic diagram of turbine mode operation is shown.

[0042] Figure 12 The schematic diagram of the transition mode operation is shown.

[0043] Figure 13 The schematic diagram of the stamping mode is shown.

[0044] In the diagram: 1. Outer bypass casing; 2. Integrated fuel supply device; 21. Outer support plate; 211. Hole I; 212. Hole II; 213. Circular channel I; 214. Main injection hole of ramjet combustion chamber; 22. Main combustion fuel supply pipe; 23. Inner cavity fuel supply pipe; 231. L-shaped fuel pipe; 232. Inner cavity annular fuel pipe; 233. Inner cavity nozzle; 24. Outer cavity fuel supply pipe; 241. Short fuel pipe; 242. Outer cavity annular fuel pipe; 243. Outer cavity nozzle; 25. Inner support plate; 251. Circular channel II; 252. Main injection hole of turbine combustion chamber; 3. Ramjet combustion chamber; 31. Intermediate casing; 311. Fuel pipe channel; 32. Outer cavity; 321. Outer cavity fuel supply hole; 4. Turbine combustion chamber; 41. Flow splitter ring assembly; 411. Outer flow splitter ring; 412. Inner flow splitter ring; 42. Inner cavity; 421. Front air passage gap; 422. Rear air passage gap. 423 Inner cavity oil supply hole, 43 Inner shell, 431 Inner shell inner layer, 432 Inner shell outer layer, 433 Inner shell cooling hole, 434 Inner shell mixing hole, 44 Outer shell, 441 Outer shell cooling hole, 442 Outer shell mixing hole;

[0045] Figure 10 The meanings of the arrows in the middle are as follows:

[0046] Detailed Implementation

[0047] Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the present invention, and should not be construed as limiting the present invention.

[0048] In the description of this invention, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., 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 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.

[0049] In this invention, unless otherwise explicitly specified and limited, the terms "installed," "connected," "joined," and "fixed," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part. In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature include the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" of the second feature include the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0050] In existing turbo-ramjet combined engines, the fuel supply and flame stabilization devices for the two combustion chambers are independent, resulting in numerous system components, low space utilization, and a long overall engine length, making it difficult to reduce the overall weight. Therefore, this invention discloses a compact dual-combustion chamber turbo-ramjet combined engine.

[0051] See appendix Figure 1-9 It includes: an outer bypass casing 1, which is a cylindrical structure with multiple sets of casing oil supply channels passing through its circular outer wall at equal angles, and has an air inlet and an air outlet; an intermediate casing 31, the area between the intermediate casing 31 and the outer bypass casing 1 forming an annular outer bypass; the outer wall of the intermediate casing 31 has an outer concave cavity 32, and the outer concave cavity 32 and the outer bypass casing 1 form a ramjet combustion chamber 3;

[0052] The turbine combustion chamber 4 is located inside the intermediate casing 31 and has a flow splitting ring assembly 41. The area between its outer shell 44 and the inner wall of the intermediate casing 31 forms an annular inner channel. Its outer shell 44 has an inner cavity 42, and the inner cavity 42 and the inner shell 43 form the turbine combustion chamber 4. The integrated fuel supply device 2 is shared by the ram combustion chamber 3 and the turbine combustion chamber 4. The integrated fuel supply device 2 is connected to the fuel supply channel of the casing.

[0053] In an embodiment of the present invention, the integrated fuel supply device 2 is located inside the outer bypass casing 1 and is installed on the ramjet combustion chamber 3 and the turbine combustion chamber 4.

[0054] Specifically, see Appendix Figure 3The integrated fuel supply device 2 includes: multiple outer support plates 21, which are distributed at equal angles between the outer bypass casing 1 and the intermediate casing 31; each outer support plate 21 has a main combustion fuel supply pipe 22, an inner cavity fuel supply pipe 23, and an outer cavity fuel supply pipe 24 installed in parallel inside, and connected to the fuel supply channel of the casing; wherein the number and angle of the main combustion fuel supply pipe 22, the inner cavity fuel supply pipe 23, and the outer cavity fuel supply pipe 24 are the same as those of the outer support plates 21; multiple inner support plates 25, which correspond to the number and angle of the outer support plates 21, and are located between the inner casing 43 and the outer casing 44; each inner support plate 25 has a circular channel II 251 for inserting the main combustion fuel supply pipe 22, and the circular channel II 251 has turbine combustion chamber main injection holes 252 on both radial sides opposite to the turbine combustion chamber 4.

[0055] The outer support plate is located between the outer duct casing and the intermediate casing. Its cross-section is U-shaped, and there are 12-24 of them. They are distributed at equal angles in the circumferential direction, that is, the circumferential angle between two adjacent outer support plates is 15°-30°.

[0056] Advantageously, see appendix. Figure 1 and 3 The included angle between two adjacent outer support plates 21 is 15°-30°. The outer support plates 21 are provided with ramjet combustion chamber main injection holes 214 on both sides opposite to the ramjet combustion chamber 3. Each outer support plate 21 is provided with holes I 211, holes II 212 and circular channel I 213 for installing the main fuel supply pipe 22, the inner cavity fuel supply pipe 23 and the outer cavity fuel supply pipe 24. The ramjet combustion chamber main injection hole 214 is located in the circular channel I 213. Most of the fuel passes through the ramjet combustion chamber main injection hole 214 and the turbine combustion chamber main injection hole 252 and is mixed into the ramjet combustion chamber 3 and the turbine combustion chamber 4 in a lateral side injection manner.

[0057] Advantageously, see appendix. Figure 1 and 2 The main fuel supply pipe 22 is a straight pipe; the inner concave cavity fuel supply pipe 23 includes an L-shaped oil pipe 231 and an inner concave cavity annular oil pipe 232 connected in sequence, and the inner concave cavity annular oil pipe 232 is provided with an inner concave cavity nozzle 233 facing the inner concave cavity 42; the outer concave cavity fuel supply pipe 24 includes a short oil pipe 241 and an outer concave cavity annular oil pipe 242 connected in sequence, and the outer concave cavity annular oil pipe 242 is provided with an outer concave cavity nozzle 243 facing the outer concave cavity 32; a small portion of fuel passes through the inner concave cavity nozzle 233 and the outer concave cavity nozzle 243 and enters the inner concave cavity 42 and the outer concave cavity 32 respectively in a direct injection manner.

[0058] See appendix Figure 6-9The intermediate casing 31 has cavities on both its inner and outer walls. The inner wall cavity is used to assemble the inner cavity 42, and the outer wall cavity serves as the outer cavity 32. An oil pipe channel 311 is provided at the assembly point of the intermediate casing 31 and the outer support plate 21 for inserting the main combustion fuel supply pipe 22 and the inner cavity fuel supply pipe 23. The axial position of the inner cavity 42 is consistent with the position of the outer cavity 32, and the two are symmetrically distributed. The front wall of the inner cavity 42 is on the same plane as the tail edge of the inner support plate 25. An outer cavity fuel supply hole 321 is opened on the front wall of the outer cavity 32 for installing the outer cavity nozzle 243. The number of outer cavity fuel supply holes 321 is twice that of the outer support plate 21. The outer cavity 32 and the outer support plate 21 work together to achieve stable combustion in the ramjet combustion chamber 3.

[0059] Because the outer duct has a larger diameter, circumferential flame connection is difficult. Therefore, the number of oil injection holes in the outer concave cavity is twice that of the outer support plate, that is, the circumferential angle between two adjacent oil injection holes in the outer concave cavity is 7.5°-15°, which improves the reliability of flame connection in the outer concave cavity.

[0060] Advantageously, the flow divider ring assembly 41 includes: an outer flow divider ring 411 connected to the outer casing 44, and an inner flow divider ring 412 connected to the inner casing 43. The outer flow divider ring 411, the inner flow divider ring 412, and the intermediate casing 31 divide the internal airflow into an internal mainstream, a cavity secondary flow, and an internal secondary flow. The internal mainstream flows between the outer flow divider ring 411 and the inner flow divider ring 412, and the cavity secondary flow flows between the outer flow divider ring 411 and the intermediate casing 31.

[0061] Even more advantageous, see appendix Figure 6 The inner diversion ring 412 and the outer diversion ring 411 both include a straight section and a diffuser section combined together. The straight section is used to guide the inner mainstream, and the diffuser section diffuses and decelerates the inner mainstream.

[0062] The concave cavity 42 of the present invention has a front air passage 421, a rear air passage 422 and an inner concave cavity oil supply hole 423. The front air passage 421 and the rear air passage 422 inject the concave cavity secondary flow into the concave cavity 42 to form a stable vortex structure. The inner concave cavity nozzle 233 is installed in the inner concave cavity oil supply hole 423.

[0063] See appendix Figure 6-9The inner shell 43 includes an inner shell layer 431 and an outer shell layer 432. The outer shell layer 432 is connected to the inner flow divider ring 412. The inner shell layer 431 is the innermost layer of the combustion chamber and forms a sandwich with the outer shell layer 432. After the secondary flow enters the sandwich, it flows into the main flow through the inner shell cooling holes 433 and the inner shell mixing holes 434 provided on the outer shell layer 432, thereby cooling the inner shell 43 and improving combustion performance. The outer shell 44 is provided with cooling holes for the inner shell. The outer shell cooling hole 441 and outer shell mixing hole 442 are of the same size as the inner shell mixing hole 433 and the inner shell mixing hole 434; part of the concave cavity secondary flow cools the outer shell 44 through the outer shell cooling hole 441; the inner concave cavity 42 and the inner support plate 25 work together to achieve stable combustion in the turbine combustion chamber 4; the outer shell 44 and the intermediate casing 31 form a closed space, and the concave cavity secondary flow can only be merged into the inner mainstream by the front air gap 421 and the rear air gap 422, the outer shell cooling hole 441, and the outer shell mixing hole 442.

[0064] Advantageously, see appendix. Figure 6-9 The cooling holes 441 of the outer shell and 433 of the inner shell are at a 45° angle to the wall surface of the outer shell 44 and the wall surface of the inner shell 43, respectively, and the included angle between two adjacent cooling holes in each row in the circumferential direction is 7.5°; the mixing holes 442 of the outer shell and 434 of the inner shell are perpendicular to the wall surface of the outer shell 44 and the wall surface of the inner shell 43, respectively, and the included angle between two adjacent mixing holes in each row in the circumferential direction is 30°.

[0065] The present invention also provides an engine with a compact dual combustion chamber of a turbo-ramjet combined engine, comprising an engine body and a compact dual combustion chamber of a turbo-ramjet combined engine as described in any of the above embodiments disposed therein.

[0066] The working process of a compact dual-combustion chamber engine with a turbo-ramjet combination engine is as follows:

[0067] When the turbo-ramjet combined combustion chamber operates in turbine mode, such as Figure 1-11As shown, the inner airflow and the outer bypass airflow enter the inner duct and the outer bypass duct respectively. The airflow in the inner duct is divided into the inner mainstream, the cavity secondary flow and the inner secondary flow by the action of the intermediate casing 31, the inner split ring 411, the outer split ring 412 and the inner shell inner layer 431. The cavity secondary flow flows into the middle area between the intermediate casing 31 and the outer split ring 412, the inner mainstream flows into the middle area between the inner split ring 411 and the outer split ring 412, and the inner secondary flow flows into the middle area between the inner split ring 411 and the inner shell inner layer 431. In this operating mode, fuel is transported to the inner support plate 25 and the inner concave cavity 42 through the main combustion fuel supply pipe 22 and the inner concave cavity fuel supply pipe 23. The fuel entering the inner support plate 25 is mixed with the main internal flow through the turbine combustion chamber main injection hole 252 in a lateral side injection manner. The main internal flow has a high velocity, and the fuel droplets are subjected to strong shear force, which can achieve atomization and breakage in a short distance and be entrained into the backflow zone at the tail edge of the inner support plate 25 to form the stable flame zone of the main internal flow. The fuel transported to the inner concave cavity 42 is directly injected through the inner concave cavity nozzle 233 and mixed with the secondary flow of the concave cavity. Due to the slow airflow velocity inside the inner concave cavity 42 and the formation of a relatively stable vortex structure, the fuel-air residence time is long. Although the shear force on the fuel droplets is not as strong as that of the main internal flow, the long residence time is sufficient to achieve atomization and evaporation of the droplets, forming a fuel-air mixture, and stably burning in the inner concave cavity 42 to achieve flame connection in the annular cavity. Meanwhile, the main flow in the low-speed recirculation zone of the inner support plate 25 and the secondary flow in the concave cavity 42 have component transport, which further enhances the combustion stability of the main combustion zone and the concave cavity flame stabilization zone, and improves the combustion performance of the turbine combustion chamber.

[0068] like Figure 1-10 As shown in Figure 12, and Figure 11 The difference in the process is the change in the working mode;

[0069] When the turbo-ramjet combined combustor transitions from turbine mode to ramjet mode, it first enters a transition mode. During this transition, the turbine and ramjet combustors work together to help the turbine engine increase its upper speed limit, facilitating a smooth transition into ramjet mode. Figure 12 It can be seen that in the transition mode, fuel is supplied simultaneously through the three fuel supply pipes in the integrated fuel supply device 2, wherein the operating mode of the turbine combustion chamber is the same as that of the turbine combustion chamber. Figure 11 The conditions are the same. Fuel in the ramjet combustion chamber first enters the short fuel line 241. Most of the fuel is laterally injected into the outer bypass duct through the main injection port 214 on the outer support plate 21. A small portion of the fuel is transported to the entire circumference through the annular fuel line 242 in the outer concave cavity, and finally directly injected into the outer concave cavity 32 through the outer concave cavity nozzle 243. The flame stabilization and flame connection mechanisms of the ramjet combustion chamber are similar to those of the turbine combustion chamber, both involving a standby flame forming within the concave cavity and the main combustion zone forming within the recirculation area at the trailing edge of the support plate. (See reference...) Figure 11 The work process.

[0070] like Figure 1-10 As shown in Figure 13, compared with the embodiment Figure 11 and Figure 12 The difference is that the working mode has been changed;

[0071] After the turbine-ramjet combined combustion chamber enters the ramjet mode, such as Figure 13 As shown, the turbine combustion chamber stops working, no airflow passes through the inner duct, only the outer bypass duct intakes air, and the ramjet combustion chamber 3 operates independently. Its fuel supply method and flame stabilization can be referenced. Figure 11 and Figure 12 work status, and Figure 12 Unlike the transition mode, the ramming mode has a higher flow rate and incoming velocity, so the fuel supply is much higher than that of the transition mode.

[0072] The combined combustion chamber provided by this invention is based on ultra-compact combustion technology and features an integrated design. The combined combustion chamber shares an integrated fuel supply device and some shell components, which can effectively improve the compactness of the engine, thereby reducing the overall mass, increasing the thrust-to-weight ratio, and widening the flight envelope of the turbine engine. This helps the aircraft solve the thrust trap problem and achieve subsonic to hypersonic flight objectives.

[0073] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. In addition, those skilled in the art can combine and integrate the different embodiments or examples described in this specification.

[0074] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention.

Claims

1. A compact dual-combustion chamber for a turbo-ramjet combined engine, characterized in that, include: The outer bypass casing (1) has multiple sets of casing oil supply channels that pass through its circular outer wall at equal angles, and has an air inlet end and an air outlet end. An intermediate casing (31) is provided, and the area between the intermediate casing (31) and the outer bypass casing (1) forms an annular outer bypass; the outer wall of the intermediate casing (31) has an outer concave cavity (32), and the outer concave cavity (32) and the outer bypass casing (1) form a ramjet combustion chamber (3); The turbine combustion chamber (4) is located inside the intermediate casing (31) and has a flow splitting ring assembly (41). The area between its outer shell (44) and the inner wall of the intermediate casing (31) forms an annular inner channel. Its outer shell (44) has a concave cavity (42). The turbine combustion chamber (4) is formed between the concave cavity (42) and the inner shell (43). An integrated oil supply device (2) is provided, wherein the ramjet combustion chamber (3) and the turbine combustion chamber (4) share the integrated oil supply device (2), and the integrated oil supply device (2) is connected to the oil supply channel of the casing; The integrated oil supply device (2) includes: There are multiple outer support plates (21), which are distributed at equal angles between the outer bypass casing (1) and the intermediate casing (31). Each outer support plate (21) has a main combustion fuel supply pipe (22), an inner cavity fuel supply pipe (23), and an outer cavity fuel supply pipe (24) installed in parallel inside, and is connected to the fuel supply channel of the casing. The number and included angle of the main combustion fuel supply pipe (22), the inner cavity fuel supply pipe (23), and the outer cavity fuel supply pipe (24) are the same as those of the outer support plates (21). There are multiple inner support plates (25), which correspond to the number and angle of the outer support plates (21) and are located between the inner shell (43) and the outer shell (44). Each inner support plate (25) has a circular channel II (251) for inserting the main combustion fuel supply pipe (22). The circular channel II (251) has a turbine combustion chamber main fuel injection hole (252) on both radial sides opposite to the turbine combustion chamber (4). The outer support plate (21) is provided with main fuel injection holes (214) for the stamping combustion chamber on both sides opposite to the stamping combustion chamber (3); The inner concave cavity oil supply pipe (23) includes an L-shaped oil pipe (231) and an inner concave cavity annular oil pipe (232) connected in sequence. The inner concave cavity annular oil pipe (232) is provided with an inner concave cavity nozzle (233) facing the inner concave cavity (42). The outer concave cavity oil supply pipe (24) includes a short oil pipe (241) and an outer concave cavity annular oil pipe (242) connected in sequence. The outer concave cavity annular oil pipe (242) is provided with an outer concave cavity nozzle (243) facing the outer concave cavity (32). Most of the fuel passes through the main injection port (214) of the ramjet combustion chamber and the main injection port (252) of the turbine combustion chamber, and is mixed into the ramjet combustion chamber (3) and the turbine combustion chamber (4) by lateral side injection; a small portion of the fuel passes through the inner concave cavity nozzle (233) and the outer concave cavity nozzle (243), and is directly injected into the inner concave cavity (42) and the outer concave cavity (32) respectively.

2. The compact dual-combustion chamber of a turbo-ramjet combined engine according to claim 1, characterized in that, The integrated fuel supply device (2) is located inside the outer bypass casing (1) and is installed on the ramjet combustion chamber (3) and the turbine combustion chamber (4).

3. The compact dual-combustion chamber of a turbo-ramjet combined engine according to claim 1, characterized in that, The circumferential angle between two adjacent outer support plates (21) is 15°-30°. Each outer support plate (21) is provided with holes I (211), holes II (212) and circular channel I (213) for installing the main combustion fuel supply pipe (22), the inner cavity fuel supply pipe (23) and the outer cavity fuel supply pipe (24). The main fuel injection hole (214) of the ramjet combustion chamber is located in the circular channel I (213).

4. The compact dual-combustion chamber of a turbo-ramjet combined engine according to claim 1, characterized in that, The main fuel supply pipe (22) is a straight pipe.

5. A compact dual-combustion chamber turbo-ramjet combined engine according to claim 4, characterized in that, The intermediate casing (31) has cavities on both its inner and outer walls. The inner wall cavity is used to assemble the inner cavity (42), and the outer wall cavity serves as the outer cavity (32). An oil pipe channel (311) is provided at the assembly point between the intermediate casing (31) and the outer support plate (21) for inserting the main combustion fuel supply pipe (22) and the inner cavity fuel supply pipe (23). The axial position of the inner cavity (42) is consistent with the position of the outer cavity (32). The two are symmetrically distributed, and the front wall of the inner cavity (42) and the tail edge of the inner support plate (25) are on the same plane; the front wall of the outer cavity (32) is provided with an outer cavity oil supply hole (321) for installing the outer cavity nozzle (243), and the number of outer cavity oil supply holes (321) is twice that of the outer support plate (21); the outer cavity (32) and the outer support plate (21) work together to achieve stable combustion in the ramjet combustion chamber (3).

6. A compact dual-combustion chamber turbo-ramjet combined engine according to claim 1, characterized in that, The flow divider ring assembly (41) includes: an outer flow divider ring (411) connected to the outer shell (44), and an inner flow divider ring (412) connected to the inner shell (43). The outer flow divider ring (411), the inner flow divider ring (412), and the intermediate casing (31) divide the internal airflow into the internal mainstream, the cavity secondary flow, and the internal secondary flow. The internal mainstream flows between the outer flow divider ring (411) and the inner flow divider ring (412), and the cavity secondary flow flows between the outer flow divider ring (411) and the intermediate casing (31).

7. A compact dual-combustion chamber turbo-ramjet combined engine according to claim 6, characterized in that, The inner diversion ring (412) and the outer diversion ring (411) both include a straight section and a diffuser section combined together. The straight section is used to guide the main flow of the inner flow, and the diffuser section diffuses and decelerates the main flow of the inner flow.

8. A compact dual-combustion chamber turbo-ramjet combined engine according to claim 6, characterized in that, The concave cavity (42) has a front air passage gap (421), a rear air passage gap (422) and an inner concave cavity oil supply hole (423). The front air passage gap (421) and the rear air passage gap (422) inject the concave cavity secondary flow into the concave cavity (42) to form a stable vortex structure. The inner concave cavity nozzle (233) is installed in the inner concave cavity oil supply hole (423).

9. A compact dual-combustion chamber turbo-ramjet combined engine according to claim 8, characterized in that, The inner shell (43) includes an inner shell inner layer (431) and an inner shell outer layer (432). The inner shell outer layer (432) is connected to the inner flow divider ring (412). The inner shell inner layer (431) is the innermost layer of the combustion chamber and forms a sandwich with the inner shell outer layer (432). After the secondary flow enters the sandwich, it flows into the main flow through the inner shell cooling holes (433) and inner shell mixing holes (434) provided on the inner shell outer layer (432), thereby cooling the inner shell (43) and improving the combustion performance. The outer shell (44) is provided with an outer shell cooling hole (441) and an outer shell mixing hole (442) of the same size as the inner shell cooling hole (433) and the inner shell mixing hole (434); a portion of the secondary flow in the concave cavity cools the outer shell (441) through the outer shell cooling hole (441); the inner concave cavity (42) and the inner support plate (25) work together to achieve stable combustion in the turbine combustion chamber (4); The outer shell (44) and the intermediate casing (31) form a closed space, and the secondary flow in the concave cavity can only be drawn into the main flow of the inner cavity by the front air gap (421), the rear air gap (422), the cooling hole (441) of the outer shell, and the mixing hole (442) of the outer shell.

10. A compact dual-combustion chamber turbo-ramjet combined engine according to claim 9, characterized in that, The cooling holes (441) of the outer shell and the cooling holes (433) of the inner shell are at a 45° angle to the wall of the outer shell (44) and the wall of the inner shell (43), respectively, and the included angle between two adjacent cooling holes in each row in the circumferential direction is 7.5°; the mixing holes (442) of the outer shell and the mixing holes (434) of the inner shell are perpendicular to the wall of the outer shell (44) and the wall of the inner shell (43), respectively, and the included angle between two adjacent mixing holes in each row in the circumferential direction is 30°.

11. A compact dual-combustion chamber engine having a turbo-ramjet combined engine, characterized in that, A compact dual combustion chamber comprising an engine body and a turbo-ramjet combined engine as described in any one of claims 1-10 disposed therein.

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