A multi-stage telescopic strut structure applicable to large-scale wide-field ramjet combustors

Abstract

The present invention discloses a multi-stage telescopic strut structure applicable to a large-scale wide-field ram combustion chamber, which includes an injector housing, an injection strut, and an elastic element. The injector housing is connected to the combustion chamber wall, and an injector inner cavity is formed therebetween. A fuel inlet and outlet is provided on the injector housing, and a wall through-hole communicating with the injector inner cavity is provided on the combustion chamber wall. The injection strut is arranged in the injector inner cavity and can extend into the combustion chamber through the wall through-hole. The injection strut includes n stages of struts sleeved and connected in sequence from outside to inside, where n≥2. Each stage of strut includes a strut wall surface, and a plurality of injection holes are provided on each strut wall surface. The inner strut can slide downward and extend out of the outer strut. One end of the elastic element is connected to the upper inner wall of the injector inner cavity, and the other end extends into the inner cavity of the innermost strut wall surface and is connected to the lower limit baffle at its lower end. The present invention provides a solution for fuel supply and combustion organization in a large-scale wide-speed-range ram combustion chamber.

Description

Technical Field

[0001] The present invention relates to the technical field of scramjet engines, and particularly to a multi-stage telescopic strut structure applicable to a large-scale wide-range ram combustion chamber. Background Art

[0002] Hypersonic aircrafts affect the current world with their super strong penetration, strike and destruction capabilities, and have been widely studied by scholars at home and abroad. Currently, the best power plant to achieve hypersonic flight is the scramjet engine, which has become a research hotspot due to its advantages of high specific impulse and high speed. As the core component of the ramjet engine, the complex flow state inside the combustion chamber brings difficulties to the mixing and reliable combustion organization. In particular, it faces huge challenges in transonic Mach number flight, multi-modal and long-term operation. Wide speed range, large airspace and large thrust have become the key issues for future research on ramjet engines. Therefore, to achieve efficient and reliable combustion organization in a wide-range ramjet engine and explore fuel injection and mixing enhancement measures under supersonic high-enthalpy incoming flow conditions has become one of the important tasks.

[0003] During the large-range transonic flight process, the transonic Mach number flight makes the combustion chamber in different combustion modes, and there are significant differences in aerodynamics, injection and combustion states between different modes, which brings challenges to the operation of wide-speed-range aircrafts. To ensure the performance of the combustion chamber under different flight conditions, the ram combustion chamber needs to have an adjustment ability matching the flight conditions. Currently, a large number of scholars study the use of variable-geometry combustion chambers to adjust the area of the combustion chamber to achieve matching with the flight conditions. In addition, the wide-speed-range fixed-geometry combustion chamber has a fixed flow channel structure, which reduces the difficulty of adapting to different flight conditions. However, the single injection and combustion organization method can only be used for a relatively narrow flight condition. The wide-speed-range fixed-geometry combustion chamber needs to adjust the injection strategy and stable combustion scheme under different flight states to meet the performance requirements. The combustion chamber mode conversion requires an adjustable injector and injection / stable combustion scheme, especially considering the geometric structure of the engine combustion chamber. Therefore, it is necessary to propose an adjustable injection structure to be applicable to the fuel injection and combustion organization of a large-scale wide-range ram combustion chamber. Summary of the Invention

[0004] The purpose of the present invention is to provide a multi-stage telescopic strut structure applicable to a large-scale wide-range ram combustion chamber, so as to solve the above-mentioned problems existing in the prior art, provide a solution for the fuel supply of a large-scale wide-speed-range ram combustion chamber, and lay a foundation for the realization of wide-speed-range flight of a large-thrust hypersonic aircraft.

[0005] To achieve the above purpose, the present invention provides the following solutions:

[0006] The present invention provides a multi-stage telescopic strut structure applicable to a large-scale wide-field ram combustion chamber, including an injector housing, an injection strut, and an elastic element. The injector housing is connected to the combustion chamber wall, and an injector inner cavity is formed between the injector housing and the combustion chamber wall. The injector housing is provided with a fuel inlet and outlet, and the combustion chamber wall is provided with a wall through-hole communicating with the injector inner cavity. The injection strut is disposed in the injector inner cavity and can extend into the combustion chamber through the wall through-hole.

[0007] The injection strut includes n stages of struts sleeved and connected in sequence from outside to inside, where n≥2. Each stage of the strut includes a strut wall surface. The upper ends of the strut wall surfaces of each stage of the strut are all connected with upper limit baffles, the lower ends of the strut wall surfaces of the 1st to the (n - 1)th stages of the strut are all connected with lower limit baffles, the lower end of the strut wall surface of the nth stage of the strut is sealed by a bottom sealing plate. A plurality of injection holes are provided on each strut wall surface, and through-holes are provided in each upper limit baffle, and the through-holes are sequentially communicated.

[0008] The outermost strut is hermetically slid in the injector housing through the upper limit baffle at its upper end and divides the injector inner cavity into an upper oil storage cavity and a lower assembly cavity. The fuel inlet and outlet communicate with the oil storage cavity, and the combustion chamber wall around the wall through-hole forms a limit for the upper limit baffle of the outermost strut.

[0009] Among two adjacent stages of struts, the inner strut is hermetically slid on the inner wall surface of the outer strut wall through the upper limit baffle at its upper end. The inner strut can slide downward and extend out of the outer strut, and the upper limit baffle and the lower limit baffle of the outer strut form a limit for the upper limit baffle of the inner strut.

[0010] The elastic element is disposed in the injector inner cavity. One end of the elastic element is connected to the upper inner wall of the injector inner cavity, and the other end passes through each through-hole and extends into the inner cavity of the innermost strut wall surface and is connected to the bottom sealing plate at its lower end. Under the action of fuel drive, each stage of the strut can extend into the combustion chamber through the wall through-hole, and the inner strut can extend downward out of the outer strut. After stopping fuel supply, under the action of the elastic element, the inner strut retracts into the outer strut, and each stage of the strut resets into the assembly cavity.

[0011] Preferably, the outer wall surface of each strut wall surface is inclined inward from the upper end to the lower end, and the inner wall surface of each strut wall surface is vertically arranged.

[0012] Preferably, a plurality of the injection holes arranged vertically are provided on both sides of the wall surface of each support plate, and the diameter of the injection holes is 0.5-1 mm.

[0013] Preferably, the upper limit baffle of the outermost support plate is in sealed sliding connection with the inner wall of the injector housing through a sealing ring; among two adjacent levels of support plates, the upper limit baffle of the inner support plate is in sealed sliding connection with the inner wall surface of the wall surface of the outer support plate through a sealing ring.

[0014] Preferably, the center lines of each level of support plates are collinear and collinear with the center line of the injector housing.

[0015] Preferably, the center line of the elastic element is collinear with the center line of the injector housing, one end of the elastic element is connected to the center position of the upper inner wall of the inner cavity of the injector, and the other end is connected to the center position of the bottom sealing plate.

[0016] Preferably, the injection support plate includes three levels of support plates sleeved and connected in sequence from outside to inside.

[0017] Preferably, the arrangement direction of the injection support plate forms an angle of 45°-60° with the normal direction of the combustion chamber wall surface, and the angle is determined by the incoming flow Mach number.

[0018] The present invention has achieved the following technical effects compared with the prior art:

[0019] The present invention provides a multi-stage telescopic support plate structure applicable to a large-scale wide-range ram combustion chamber. Based on a large-scale fixed-geometry combustion chamber of a ramjet engine, during use, the fuel inlet and outlet are opened, fuel enters the fuel storage chamber, and high-pressure fuel drives the injection support plate into the combustion chamber. The inner support plates in the injection support plate extend out in sequence, and each level of support plate is sequentially limited at a fixed position. At the same time, the fuel enters the internal flow channel of the injection support plate and is injected in the combustion chamber through the injection holes; when not in use, the fuel drains out from the fuel inlet and outlet, and the injection support plate sequentially contracts into the assembly chamber under the action of the elastic element; it provides a solution for fuel supply and combustion organization in a large-scale wide-range ram combustion chamber and lays a foundation for realizing wide-speed-range flight of hypersonic aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required in the embodiments. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0021] Figure 1Schematic cross-sectional structure diagram of the multi-stage telescopic strut structure applicable to large-scale wide-field ram combustion chambers provided by the present invention;

[0022] Figure 2 Schematic cross-sectional structure diagram when the injection strut extends into the combustion chamber in the present invention;

[0023] Figure 3 Schematic side view showing that the arrangement direction of the injection strut in the present invention forms a certain angle with the normal direction of the combustion chamber wall;

[0024] In the figure: 1 - injector housing, 2 - injection strut, 3 - elastic element, 4 - combustion chamber wall, 5 - injector inner cavity, 6 - fuel inlet and outlet, 7 - wall through-hole, 8 - injection hole, 9 - oil storage chamber, 10 - assembly chamber, 11 - first-stage strut, 12 - second-stage strut, 13 - third-stage strut, 14 - first-stage strut wall, 15 - first-stage upper limit baffle, 16 - first-stage lower limit baffle, 17 - second-stage strut wall, 18 - second-stage upper limit baffle, 19 - second-stage lower limit baffle, 20 - third-stage strut wall, 21 - third-stage upper limit baffle, 22 - bottom sealing plate, A - engine outer contour. Detailed implementation manners

[0025] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts belong to the scope of protection of the present invention.

[0026] The purpose of the present invention is to provide a multi-stage telescopic strut structure applicable to large-scale wide-field ram combustion chambers to solve the problems existing in the prior art, provide a solution for fuel supply of large-scale wide-speed ram combustion chambers, and lay a foundation for the realization of wide-speed flight of large-thrust hypersonic aircraft.

[0027] To make the above objects, features, and advantages of the present invention more obvious and understandable, the present invention will be further described in detail below in conjunction with the drawings and specific implementation manners.

[0028] As Figures 1-3As shown in the figure, this embodiment provides a multi-stage telescopic strut structure applicable to a large-scale wide-field stamping combustion chamber, including an injector housing 1, an injection strut 2, and an elastic element 3. The injector housing 1 is connected to the combustion chamber wall 4, and an injector inner cavity 5 is formed between the injector housing 1 and the combustion chamber wall 4. A fuel inlet / outlet 6 is provided on the injector housing 1, and a wall through-hole 7 communicating with the injector inner cavity 5 is provided on the combustion chamber wall 4. The injection strut 2 is disposed in the injector inner cavity 5 and can extend into the combustion chamber through the wall through-hole 7.

[0029] The injection strut 2 includes n stages of struts sleeved and connected in sequence from outside to inside, where n≥2. Each stage of strut includes a strut wall surface. Upper limit baffles are connected to the upper ends of the strut wall surfaces of each stage of strut. Lower limit baffles are connected to the lower ends of the strut wall surfaces of the 1st to the (n - 1)th stages of struts. The lower end of the strut wall surface of the nth stage of strut is sealed by a bottom sealing plate 22. A plurality of injection holes 8 are provided on each strut wall surface, and through-holes are provided in each upper limit baffle, and the through-holes communicate in sequence.

[0030] The outermost strut is hermetically slidable in the injector housing 1 through its upper limit baffle at the upper end and divides the injector inner cavity 5 into an upper oil storage chamber 9 and a lower assembly chamber 10. The fuel inlet / outlet 6 communicates with the oil storage chamber 9, and the combustion chamber wall 4 around the wall through-hole 7 forms a limit for the upper limit baffle of the outermost strut.

[0031] Among two adjacent stages of struts, the inner strut is hermetically slidable on the inner wall surface of the outer strut wall through its upper limit baffle at the upper end. The inner strut can slide downward and extend out of the outer strut. The upper limit baffle and the lower limit baffle of the outer strut form a limit for the upper limit baffle of the inner strut.

[0032] The elastic element 3 is disposed in the injector inner cavity 5. One end of the elastic element 3 is connected to the upper inner wall of the injector inner cavity 5, and the other end passes through each through-hole and extends into the inner cavity of the innermost strut wall and is connected to its bottom sealing plate 22 at the lower end. Under the action of fuel drive, each stage of strut can extend into the combustion chamber through the wall through-hole 7, and the inner strut can extend downward out of the outer strut. After the fuel supply stops, under the action of the elastic element 3, the inner strut retracts into the outer strut, and each stage of strut resets into the injector inner cavity 5.

[0033] Based on a large-scale constant-geometry wide-field ram combustion chamber, the supersonic incoming flow velocity is Ma = 2 to 6+. Under the condition of high Mach number incoming flow, the combustion chamber has strong anti-backpressure ability. Fuel is injected through the central strut arranged at the end of the isolator, and the ignition process and combustion organization are carried out downstream of the central strut. Under the condition of low Mach number incoming flow, the combustion chamber has weak anti-backpressure ability. Fuel injection and fuel supply at the above positions are likely to cause the combustion chamber not to start. Therefore, fuel supply and combustion organization under low Mach number incoming flow conditions need to be arranged in the expansion section of the downstream combustion chamber; to achieve stable and reliable combustion organization, a "V"-shaped flame stabilizer with a relatively large blockage ratio is usually used. This flame stabilizer will cause a large total pressure loss, which is disadvantageous for working under high Mach number incoming flow conditions. In the present invention, a telescopic injection strut is provided in the expansion section of the downstream combustion chamber, which extends into the combustion chamber to work under low Mach number conditions and retracts and does not work under high Mach number conditions, taking into account the working range of the wide-speed combustion chamber. When the incoming flow Mach number is 2 to 4, the injection strut 2 extends into the combustion chamber. When the incoming flow Mach number is 4 to 6, the injection strut 2 retracts into the injector inner cavity 5; at the same time, in order to take into account the uniformity of fuel distribution in the flow passage of the large-scale combustion chamber and the limitation of the overall outline size of the ramjet on the size of the injector housing, the present invention adopts a multi-stage telescopic strut scheme. Fuel is distributed through the relatively long injection strut structure formed by the extension of each stage of the strut, so that the fuel distribution in the flow passage of the combustion chamber is uniform. After the telescopic injection strut is retracted, it can meet the limitation of the overall outline size of the ramjet.

[0034] In this embodiment, the outer wall surfaces of the walls of each strut are inclined inward from the upper end to the lower end, and the inner wall surfaces of the walls of each strut are vertically arranged.

[0035] In this embodiment, a plurality of injection holes 8 arranged vertically are provided on both sides of the walls of each strut. The diameter of the injection holes 8 is 0.5 to 1 mm, preferably 0.5 mm.

[0036] In this embodiment, the upper limit baffle of the outermost strut is hermetically and slidably connected to the inner wall of the injector housing 1 through a sealing ring; among adjacent two-stage struts, the upper limit baffle of the inner strut is hermetically and slidably connected to the inner wall surface of the outer strut wall through a sealing ring.

[0037] In this embodiment, the center lines of each stage of the strut are collinearly arranged and collinearly arranged with the center line of the injector housing 1.

[0038] In this embodiment, the center line of the elastic element 3 is collinearly arranged with the center line of the injector housing 1. One end of the elastic element 3 is connected to the center position of the upper end inner wall of the injector inner cavity 5, and the other end is connected to the center position of the bottom sealing plate 22.

[0039] In this embodiment, the injection strut 2 includes three levels of struts sleeved and connected in sequence from outside to inside, namely the first-level strut 11, the second-level strut 12, and the third-level strut 13. The first-level strut 11 includes a first-level strut wall surface 14, and a first-level upper limit baffle 15 and a first-level lower limit baffle 16 respectively connected to the upper and lower ends of the first-level strut wall surface 14. The second-level strut 12 includes a second-level strut wall surface 17, and a second-level upper limit baffle 18 and a second-level lower limit baffle 19 respectively connected to the upper and lower ends of the second-level strut wall surface 17. The third-level strut 13 includes a third-level strut wall surface 20, and a third-level upper limit baffle 21 and a bottom sealing plate 22 respectively connected to the upper and lower ends of the third-level strut wall surface 20. One end of the elastic element 3 is connected to the central position of the bottom sealing plate 22.

[0040] In this embodiment, the arrangement direction of the injection strut 2 forms an angle of 45° to 60° with the normal direction of the combustion chamber wall surface 4, and the angle is determined by the incoming flow Mach number, and the angle satisfies the drag reduction requirement of the injection strut 2.

[0041] In the present invention, specific examples are used to elaborate on the principle and implementation manner of the present invention. The description of the above embodiments is only used to help understand the method and its core idea of the present invention. At the same time, for those of ordinary skill in the art, according to the idea of the present invention, there will be changes in the specific implementation manner and application scope. In summary, the content of this specification should not be construed as a limitation on the present invention.

Claims

1. A multi-stage telescopic strut structure applicable to a large-scale wide-field ram combustion chamber, characterized in that: It includes an injector housing, an injection support plate and an elastic element. The injector housing is connected to the combustion chamber wall surface. An injector inner cavity is formed between the injector housing and the combustion chamber wall surface. A fuel inlet and outlet is provided on the injector housing. A wall through hole communicating with the injector inner cavity is provided on the combustion chamber wall surface. The injection support plate is arranged in the injector inner cavity and can extend into the combustion chamber through the wall through hole. The injection support plate includes n-level support plates sleeved and connected in sequence from outside to inside, where n≥2. Each level of the support plates includes a support plate wall surface. Upper limit baffles are connected to the upper ends of the support plate wall surfaces of each level of the support plates. Lower limit baffles are connected to the lower ends of the support plate wall surfaces of the 1st to the n-1st levels of the support plates. The lower end of the support plate wall surface of the nth level of the support plate is sealed by a bottom sealing plate. A plurality of injection holes are provided on each support plate wall surface. Through holes are provided in each of the upper limit baffles, and the through holes communicate with each other in sequence. The outermost support plate is hermetically slidable in the injector housing through the upper limit baffle at its upper end and divides the injector inner cavity into an upper oil storage cavity and a lower assembly cavity. The fuel inlet and outlet communicates with the oil storage cavity. The combustion chamber wall surface around the wall through hole forms a limit on the upper limit baffle of the outermost support plate. Among two adjacent levels of the support plates, the inner support plate is hermetically slidable on the inner wall surface of the outer support plate wall through the upper limit baffle at its upper end. The inner support plate can slide downward and extend out of the outer support plate. The upper limit baffle and the lower limit baffle of the outer support plate form a limit on the upper limit baffle of the inner support plate. The elastic element is arranged in the injector inner cavity. One end of the elastic element is connected to the upper inner wall of the injector inner cavity, and the other end passes through each through hole and extends into the inner cavity of the innermost support plate wall surface and is connected to the bottom sealing plate at its lower end. Under the action of fuel drive, each level of the support plates can extend into the combustion chamber through the wall through hole, and the inner support plate can extend downward out of the outer support plate. After stopping fuel supply, under the action of the elastic element, the inner support plate retracts into the outer support plate, and each level of the support plates resets into the assembly cavity.

2. The multi-stage telescopic strut structure applicable to a large-scale wide-field stamping combustion chamber according to claim 1, wherein: The outer wall surfaces of each support plate wall surface are inclined inward from the upper end to the lower end, and the inner wall surfaces of each support plate wall surface are vertically arranged.

3. The multi-stage telescopic strut structure applicable to a large-scale wide-field stamping combustor according to claim 1, wherein: A plurality of the injection holes arranged vertically are provided on both sides of each support plate wall surface, and the diameter of the injection holes is 0.5-1 mm.

4. The multi-stage telescopic strut structure applicable to a large-scale wide-field stamping combustor according to claim 1, wherein: The upper limit baffle of the outermost support plate is hermetically slidably connected to the inner wall of the injector housing through a sealing ring. Among two adjacent levels of the support plates, the upper limit baffle of the inner support plate is hermetically slidably connected to the inner wall surface of the outer support plate wall through a sealing ring.

5. The multi-stage telescopic strut structure applicable to a large-scale wide-field stamping combustor according to claim 1, characterized in that: The center lines of each level of the support plates are collinear and collinear with the center line of the injector housing.

6. The multi-stage telescopic strut structure applicable to a large-scale wide-range stamping combustion chamber according to claim 5, characterized in that: The center line of the elastic element is collinear with the center line of the injector housing. One end of the elastic element is connected to the center position of the upper inner wall of the inner cavity of the injector, and the other end is connected to the center position of the bottom sealing plate.

7. The multi-stage telescopic strut structure applicable to a large-scale wide-field ram combustion chamber according to claim 1, characterized in that: The injection support plate includes three levels of support plates sleeved and connected in sequence from outside to inside.

8. The multi-stage telescopic strut structure applicable to a large-scale wide-field stamping combustion chamber according to claim 1, characterized in that: The arrangement direction of the injection support plate forms an angle of 45° to 60° with the normal direction of the combustion chamber wall surface, and the angle is determined by the incoming flow Mach number.

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