Interlayer device and engine

Abstract

The utility model belongs to the technical field of solid rocket engines, and particularly relates to an interlayer device and an engine. The interlayer device comprises a composite interlayer, the composite interlayer comprises a heat insulation layer and an inner reinforcing layer, and the inner reinforcing layer is located in the heat insulation layer and divides the heat insulation layer into a first heat insulation layer and a second heat insulation layer in the axial direction; a first open cavity and a second open cavity which are back to each other are correspondingly formed in the axial side of the first heat insulation layer and the axial side of the second heat insulation layer; the composite interlayer is provided with a weakening structure, and when the composite interlayer bears pressure from the second open cavity to the first open cavity, the weakening structure can crack to form an opening communicating the second open cavity with the first open cavity. In the application, the inner reinforcing layer is additionally arranged in the heat insulation layer and is an internal reinforcing material of the heat insulation layer, so that the structural damage caused by large deformation of the interlayer is avoided, and the structural integrity when the weakening structure is opened is also ensured. The interlayer device is convenient to assemble and light in weight, and the mass ratio of the engine is increased.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of solid rocket engines, and particularly relates to a partition device and an engine. BACKGROUND

[0002] The solid double-pulse engine is actually a solid engine combustion chamber divided into two parts by a partition device, and can be shut down and started twice. The aircraft using the solid double-pulse engine as a power device can reasonably distribute the interval time of two-stage pulse thrust through the on-board control program, realize the optimal control of the flight trajectory and the optimal management of the engine energy, and thus meet the needs of different flight performances.

[0003] For the double-pulse engine with end-face combustion propellant of the second-stage pulse, the existing scheme is to bond a rubber partition on the side of the starting combustion end face of the end-face combustion propellant solid grain. The rubber partition plays a sealing and heat-insulating role when the first-stage pulse works, so as to avoid igniting the solid grain of the second-stage pulse. When the second-stage pulse works, the rubber partition can be smoothly opened under the action of the combustion gas in the combustion chamber of the second-stage pulse.

[0004] However, the existing rubber partition has insufficient structural strength, and the bonding mode increases the risk of sealing failure due to insufficient structural strength. Moreover, when the second-stage pulse starts to work and breaks through the rubber partition, part of the rubber partition forms large rubber fragments in the combustion chamber. Some large fragments may enter the nozzle, and even cause the risk of blocking the nozzle. CONTENT OF THE INVENTION

[0005] The application provides a partition device and an engine to solve the technical problem that the existing rubber partition has insufficient structural strength, increases the risk of sealing failure, and easily forms large rubber fragments.

[0006] According to one aspect of the application, a partition device is provided, which comprises a composite partition, the composite partition comprising a heat-insulating layer and an inner reinforcing layer, the inner reinforcing layer being located in the heat-insulating layer and dividing the heat-insulating layer into a first heat-insulating layer and a second heat-insulating layer in the axial direction; the axial side of the first heat-insulating layer and the axial side of the second heat-insulating layer correspondingly form a first open cavity and a second open cavity facing away from each other; the composite partition is provided with a weakened structure and is arranged to be capable of cracking to form an opening connecting the second open cavity and the first open cavity when bearing pressure from the second open cavity to the first open cavity.

[0007] In a further optional embodiment, the middle part of the composite partition is convexly arranged in the axial direction towards the first open cavity and forms a deepened ring cavity located on the side of the first open cavity, and the deepened ring cavity and the second open cavity partially overlap in the circumferential direction.

[0008] In a further optional embodiment, the composite partition further comprises an outer reinforcing layer, the outer reinforcing layer being located on at least part of the surface of the first heat insulation layer at the location of the deepened annular cavity.

[0009] In a further optional embodiment, the second open cavity is arranged to taper in the direction from the opening side of the second open cavity towards the first open cavity.

[0010] In a further optional embodiment, the part of the deepened annular cavity that overlaps the circumferentially projected part of the second open cavity is arranged to taper in the direction from the opening side of the first open cavity towards the second open cavity.

[0011] In a further optional embodiment, the weakened structure is located in the middle part of the composite partition and is formed between the first heat insulation layer and the inner reinforcing layer.

[0012] In a further optional embodiment, the weakened structure comprises a plurality of straight grooves that meet at a point.

[0013] In a further optional embodiment, the cross section of the straight grooves is arranged to taper in the direction from the opening side of the straight grooves towards the inside.

[0014] In a further optional embodiment, a fixing ring is further included, the fixing ring being connected to the outer circumferential side of the composite partition.

[0015] According to another aspect of the present application, an engine is provided, the engine comprising the partition device described above, the partition device being located between a first pulse combustion chamber and a second pulse combustion chamber of the engine to isolate the first pulse combustion chamber and the second pulse combustion chamber.

[0016] In summary, the partition device and the engine provided by the present application have at least the following beneficial effects:

[0017] The partition device is suitable for solid double-pulse engines or other forms of multi-pulse engines. In the case of application to a solid double-pulse engine, the composite partition in the partition device can seal and insulate during the first pulse operation, preventing the second solid propellant from being ignited. Under the impact of high-temperature gas in the second pulse combustion chamber during the second pulse operation, the weakened structure is opened to form an opening, thereby realizing the intermittent operation function between the two sides of the engine.

[0018] Due to the additional inner reinforcing layer in the heat insulation layer, the inner reinforcing layer is an internal reinforcing material for the heat insulation layer, which improves the deformation resistance of the heat insulation layer to the first pulse and ensures the structural integrity when the weakened structure is opened, thereby reducing the risk of large debris blocking the nozzle.

[0019] Further, the non-protruding part surface without the arranged weakening structure is arranged with an outer reinforcing layer, which can further improve the deformation capacity of the composite partition layer under a first level pulse.

[0020] Further, the partition device adopts a metal and non-metal composite structure, belongs to a material manufacturing fixed ring, and the composite partition layer adopts a multi-material hierarchical structure, which improves the structural strength under the action of the reinforcing layer, ensures that the partition layer will not be damaged due to large deformation, and ensures the heat insulation and deformation capacity. The partition device is simple to assemble, reduces the mass of the partition device, and improves the mass ratio of the engine. BRIEF DESCRIPTION OF DRAWINGS

[0021] In order to more clearly illustrate the technical solutions in the specific embodiments or prior art of the present application, the drawings needed to be used in the description of the specific embodiments or prior art will be briefly introduced. Obviously, the drawings in the following description are some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor on the basis of these drawings.

[0022] Figure 1 A partial cross-sectional view of an engine according to one of the embodiments of the present application is provided;

[0023] Figure 2a A schematic view of a partition device according to one of the embodiments of the present application is provided from one perspective;

[0024] Figure 2b A cross-sectional view of the partition device in Figure 2a at B-B;

[0025] Figure 2c A cross-sectional view of the partition device in Figure 2a at E-E;

[0026] Figure 3 An enlarged schematic view of the fixed ring in Figure 2b ;

[0027] Figure 4a A schematic view of the inner reinforcing layer in Figure 2a ;

[0028] Figure 4b A cross-sectional view of F-F in Figure 4a .

[0029] The reference signs are as follows:

[0030] 100, partition device; C1, first open cavity; C11, deepened ring cavity; C2, second open cavity;

[0031] 10, composite interlayer; 11, thermal barrier layer; 111, first thermal barrier layer; 112, second thermal barrier layer; 12, inner reinforcing layer; 13, flat section; 14, outer reinforcing layer; 15, weakened structure; A, groove;

[0032] 20, fixed ring; D, sealing ring groove; 30, sealing ring; 40, two-stage solid propellant grain;

[0033] R1, primary pulse combustion chamber; R2, secondary pulse combustion chamber. DETAILED DESCRIPTION

[0034] In the description of the present application, if the features limited with "first", "second", "primary", "secondary" are used for the purpose of description only, it should not be understood as indicating or implying relative importance or implying the number of the indicated technical features. The features limited with "first", "second", "primary", "secondary" can explicitly or implicitly include at least one of the limited features. If the description of "plurality" appears, it generally means at least two, for example, two, three, etc., unless otherwise explicitly specified.

[0035] In the present application, unless otherwise explicitly specified and limited, if the terms such as "mounting", "connecting", "connecting", "fixing" and the like appear, they should be understood in a broad sense. For example, it can be fixedly connected, or it can be detachably connected, or it can be integrated; it can be mechanically connected, or it can be electrically connected, it can be directly connected, or it can be indirectly connected through an intermediate medium, it can be the internal communication of two elements or the interaction relationship between two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0036] In the description of the present application, if the terms such as "one embodiment", "some embodiments", "example", "specific example", or "some examples" appear, it means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In the present description, the illustrative description of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any appropriate manner in any one or more embodiments or examples. In addition, those skilled in the art can combine and combine the different embodiments or examples described in the present description and the features of the different embodiments or examples without contradiction.

[0037] In the description of the present application, "axial" can refer to the length direction of the solid double-pulse engine, and "circumferential" can refer to the circumferential direction of the solid double-pulse engine.

[0038] Figure 1Figure 1 is a partial sectional view of an engine according to an embodiment of the present application. Referring to Figure 1, Figure 1 The engine comprises a partition device 100 located between a first pulse combustion chamber R1 and a second pulse combustion chamber R2 of the engine to separate the first pulse combustion chamber R1 from the second pulse combustion chamber R2.

[0039] The engine according to the embodiment is a solid double-pulse engine. The first pulse combustion chamber R1 contains a first solid propellant grain (not shown in the figure), and the second pulse combustion chamber R2 contains a second solid propellant grain 40. In the embodiment, the first solid propellant grain is a bore-type grain, and the bore portion thereof serves as a combustion surface. When the first solid propellant grain burns, the combustion surface starts from the surface of the bore and gradually expands outward, forming a gradually increasing combustion area. The second solid propellant grain 40 is an end-face-type grain, and the combustion starts from one axial end of the grain and gradually moves along the axial direction of the grain to the other end.

[0040] The partition device 100 is located between the first pulse combustion chamber R1 and the second pulse combustion chamber R2 to separate the first solid propellant grain in the first pulse combustion chamber R1 from the second solid propellant grain 40 in the second pulse combustion chamber R2. Thus, when the first solid propellant grain burns, the partition device 100 can prevent the second solid propellant grain 40 from being ignited.

[0041] Figure 2a Figure 2 is a schematic view of the partition device 100 according to an embodiment of the present application from one perspective. Figure 2b Figure 3 is a sectional view of the partition device 100 in Figure 1 at A-A. Figure 2a Figure 4 is a sectional view of the partition device 100 in Figure 1 at B-B. Figure 2c Figure 5 is a sectional view of the partition device 100 in Figure 1 at C-C. Figure 2a Figure 6 is a sectional view of the partition device 100 in Figure 1 at E-E.

[0042] Figure 7 is a sectional view of the partition device 100 according to an embodiment of the present application. Figures 2a to 2c The partition device 100 comprises a composite partition 10, which comprises a heat-insulating layer 11 and an inner reinforcing layer 12 located in the heat-insulating layer 11 and separating the heat-insulating layer 11 into a first heat-insulating layer 111 and a second heat-insulating layer 112 in the axial direction.

[0043] The axial side of the first heat-insulating layer 111 and the axial side of the second heat-insulating layer 112 correspondingly form first and second open cavities C1 and C2 facing away from each other.

[0044] The composite partition 10 is provided with a weakening structure 15 and is arranged to bear pressure from the second open cavity C2 toward the first open cavity C1. The weakening structure 15 can crack to form an opening that connects the second open cavity C2 and the first open cavity C1.

[0045] In the embodiment, the composite partition 10 is a multi-layer structure combined by multiple materials, and specifically, the inner reinforcing layer 12 is arranged in the heat insulation layer 11, the inner reinforcing layer 12 separates the heat insulation layer 11 in the axial direction, and forms the layout of the first heat insulation layer 111, the inner reinforcing layer 12 and the second heat insulation layer 112 arranged in the axial direction in sequence.

[0046] Further, the axial two sides of the composite partition 10 correspondingly form the first open cavity C1 and the second open cavity C2, and it should be noted that the open cavity herein refers to a cavity arranged in an open manner in the axial direction. The first open cavity C1 is located at the axial side of the first heat insulation layer 111, and the second open cavity C2 is located at the axial side of the second heat insulation layer 112.

[0047] Specifically, the first open cavity C1 is arranged towards the first-stage pulse combustion chamber R1, and the second open cavity C2 is arranged towards the second-stage pulse combustion chamber R2 and accommodates the axial one end of the second-stage solid propellant 40. The second-stage solid propellant 40 herein is an end face type propellant, and the axial one end of the second-stage solid propellant 40 accommodated by the second open cavity C2 is the initial combustion end.

[0048] Further, the composite partition 10 is provided with a weakened structure 15, and it should be noted that the structural strength of the weakened structure 15 is lower than that of other positions of the composite partition 10. Therefore, when the composite partition 10 bears the pressure from the second open cavity C2 towards the first open cavity C1 (also from the second-stage pulse combustion chamber R2 towards the first-stage pulse combustion chamber R1, hereinafter referred to as the forward direction), the weakened structure 15 cracks and forms an opening to connect the second open cavity C2 and the first open cavity C1, and further connect the second-stage pulse combustion chamber R2 and the first-stage pulse combustion chamber R1.

[0049] It should be noted that the forward pressure can be formed when the second-stage solid propellant 40 is ignited. In addition, when the first-stage solid propellant burns, although the pressure from the first open cavity C1 towards the second open cavity C2 (also from the first-stage pulse combustion chamber R1 towards the second-stage pulse combustion chamber R2, hereinafter referred to as the reverse direction) is formed on the composite partition 10, the axial side end of the composite partition 10 is attached to the second-stage solid propellant 40, so that the composite partition 10 cannot form a large deformation when bearing the reverse pressure, thereby avoiding the weakened structure 15 from cracking and forming an opening when bearing the reverse pressure. In other words, the assembly position of the composite partition 10 ensures that the weakened structure 15 can only open in the forward direction to form an opening.

[0050] Therefore, the composite partition 10 can play a sealing and heat insulation role when the first-stage pulse works, and prevents the second-stage solid propellant 40 from being ignited. When the second-stage pulse works, the weakened structure 15 is opened to form an opening under the impact of the high-temperature gas in the second-stage pulse combustion chamber R2, thereby realizing the function of intermittent work between the two sides of the engine.

[0051] Further, due to the additional inner reinforcing layer 12 in the thermal insulation layer 11, the composite insulation layer 10 has good structural strength, and can ensure good sealing even when a large reverse pressure is formed during primary pulse operation. Moreover, the second open cavity C2 covers the axial starting combustion end of the secondary solid propellant column 40, and has better sealing performance.

[0052] Due to the increased structural strength of the composite insulation layer 10, large fragments are not generated during the opening process, and after the opening, the composite insulation layer 10 is gradually ablated outward from the opening, reducing the risk of clogging of the nozzle. In other words, the inner reinforcing layer 12 is an internal reinforcing material of the thermal insulation layer 11, which improves the deformation resistance of the thermal insulation layer 11 to the primary pulse (reverse pressure) and ensures the structural integrity when the weakening structure 15 is opened.

[0053] Moreover, due to the increased structural strength of the composite insulation layer 10, a simpler structural design can be used, so that the weight of the insulation device 100 is lighter, thereby not affecting the mass ratio of the engine.

[0054] In a further optional embodiment, the insulation device 100 further comprises a fixing ring 20 connected to the outer circumferential side of the composite insulation layer 10.

[0055] In this embodiment, the composite insulation layer 10 is fixed by the fixing ring 20, which is used to cooperate with the inner circumferential wall of the combustion chamber of the engine. Figure 3 For Figure 2b is an enlarged view of the fixing ring 20. Please refer to Figure 3 , the outer circumferential side of the fixing ring 20 is provided with a sealing ring groove D for installing a sealing ring 30.

[0056] Please refer to Figure 1 In specific applications, the fixing ring 20 is a metal ring which cooperates with the sealing ring 30 to connect to the inner circumferential wall of the secondary pulse combustion chamber R2 to achieve fixed installation of the insulation device 100. The fixing ring 20 is made of aluminum alloy, titanium alloy material, etc., such as hard aluminum LY20, which ensures sufficient strength while being relatively light in weight, facilitating assembly.

[0057] Further, the inner circumferential side of the fixing ring 20 is irregularly shaped with grooves and protrusions, and the axial ends are also designed with grooves. The above design increases the pressure bonding area between the fixing ring 20 and the composite insulation layer 10, and improves the interface failure stress threshold by changing the shape of the bonding surface.

[0058] In some optional embodiments, the middle part of the composite insulation layer 10 is convexly arranged along the axial direction towards the first open cavity C1 and forms a deepened ring cavity C11 located on the circumferential side of the first open cavity C1. The deepened ring cavity C11 overlaps with the projection of the second open cavity C2 in the circumferential direction.

[0059] In the embodiment, the middle part of the composite partition layer 10 is arranged protruding in the positive direction, the peripheral part of the first open cavity C1 corresponds to form a deepened ring cavity C11, and the deepened ring cavity C11 surrounds the outer periphery of the second open cavity C2, that is, the deepened ring cavity C11 and the second open cavity C2 partially overlap in the circumferential direction.

[0060] In this way, the middle part of the composite partition layer 10 is arranged protruding towards the first pulse combustion chamber R1, so that the composite partition layer 10 also has the deformation ability under the action of the reverse pressure.

[0061] In a further optional embodiment, the composite partition layer 10 further comprises an outer reinforcing layer 14, which is located on at least part of the surface of the first heat insulation layer 111 at the position of the deepened ring cavity C11.

[0062] In the embodiment, the surface of the first heat insulation layer 111 at the position of the deepened ring cavity C11 is provided with the outer reinforcing layer 14, which can further improve the deformation ability of the composite partition layer 10 to withstand the first pulse.

[0063] In specific applications, the heat insulation layer 11 is a rubber layer, which can be a nitrile rubber material. The material has a density of less than 1.20x10 3 kg / m3, which can reduce the mass of the partition device 100 and improve the engine mass ratio; the material has an elongation at break of more than 300%, which can well adapt to the need for deformation; at the same time, under the action of high-temperature and high-pressure gas of the engine, the material has low linear ablation rate and thermal conductivity, the linear ablation rate is less than 0.06mm / s, which well meets the needs of ablation and heat insulation.

[0064] The inner reinforcing layer 12 and the outer reinforcing layer 14 are reinforcing cloth, which can be nylon cloth, and has good compatibility with the nitrile rubber material. The nylon cloth material has a density of more than 1.1g / m3, a tensile strength of more than 100MPa, an elongation of more than 100%, and a melting point of more than 100℃.

[0065] In addition, the partition device 100 is integrally formed by a mold pressing and bonding process, and the heat insulation layer 11, the inner reinforcing layer 12 and the outer reinforcing layer 14 are molded together and directly bonded to the fixing ring 20. Moreover, the nitrile rubber material and the aluminum alloy material have good interface bonding performance, so that they will not easily separate.

[0066] In some optional embodiments, the second open cavity C2 is arranged to be tapered in the direction from the opening side of the second open cavity C2 towards the first open cavity C1.

[0067] In the embodiment, the opening side of the second open cavity C2 is larger than the inner side, which is convenient for assembling and covering the composite barrier 10 on the axial starting combustion end of the secondary solid propellant grain 40.

[0068] In some alternative embodiments, the overlapping part of the deepened ring cavity C11 and the second open cavity C2 in the circumferential direction is arranged to be tapered from the opening side of the first open cavity C1 to the direction of the second open cavity C2.

[0069] In the embodiment, the deeper the deepened ring cavity C11 is, the narrower the size is. The inner side of the deepened ring cavity C11 can be a smooth transition pointed shape. Please refer to Figure 2b In this case, the cross-sectional shape of the composite barrier 10 is similar to a W shape, which has a certain deformation capacity under the action of the primary pulse (reverse pressure) to adapt to the partial axial deformation of the grain caused by the primary pulse working pressure, avoid the structure damage of the composite barrier 10 under the large axial deformation, and ensure that the two combustion chambers are completely isolated in the axial direction. Of course, the shape also meets the structure shape requirement of the molding process.

[0070] In some alternative embodiments, the weakening structure 15 is located in the middle part of the composite barrier 10 and is formed in the first heat insulation layer 111 and the inner reinforcing layer 12.

[0071] In the embodiment, the middle part of the composite barrier 10 has a weakening structure 15, and the middle part of the composite barrier 10 protrudes towards the primary pulse combustion chamber R1, that is, the weakening structure 15 is located in the first heat insulation layer 111 and the inner reinforcing layer 12 at the protruding position of the middle part of the composite barrier 10.

[0072] It should be noted that the first heat insulation layer 111 at the middle part of the composite barrier 10 corresponds to the convex side layer, and correspondingly, the second heat insulation layer 112 corresponds to the concave side layer. Obviously, the weakening structure 15 is located on the convex side, and the protruding position of the middle part of the composite barrier 10 is not provided with the outer reinforcing layer 14, which is more conducive to breaking the weakening structure 15 under the positive pressure (when the secondary pulse is ignited) to form an opening.

[0073] In the illustrated embodiment, the middle part of the composite barrier 10 is a flat layer section 13, the surface of the flat layer section 13 is a plane and is not provided with the outer reinforcing layer 14, and the weakening structure 15 is located in the flat layer section 13. It should be noted that the shape of the flat layer section 13 is not limited to the illustrated embodiment, and can be adjusted according to the shape of the axial starting combustion end of the secondary solid propellant grain 40.

[0074] In further alternative embodiments, the weakening structure 15 includes a plurality of straight grooves A, and the plurality of straight grooves A converge at a point.

[0075] In this embodiment, the weakening structure 15 is composed of multiple straight grooves A, which intersect at a point, thus forming a radial arrangement of multiple straight groove structures with the intersection point as the radiation center. Preferably, the intersection point of the multiple straight grooves A is located on the axis of the partition device 100.

[0076] It should be noted that the partition device 100 is generally coaxially assembled with the secondary solid propellant column 40, that is, the intersection point of multiple straight grooves A is arranged close to the axis of the secondary solid propellant column 40.

[0077] It should be understood that the thickness at the straight groove A is the smallest, and therefore the strength at the straight groove A is the lowest. When the secondary pulse is ignited, a gas flow is formed towards the primary pulse combustion chamber R1. The gas flow is the largest and the temperature is the highest near the axis. Thus, cracking can start from the intersection point and crack along the straight groove A. In this way, even under the lower positive pressure formed when the secondary pulse is working, it can open smoothly in a petal shape without producing fragments.

[0078] exist Figure 2a In the illustrated embodiment, there are eight straight grooves A, and one end of these straight grooves A converges at a point, forming a radial shape structure with the convergence point as the radiation center. The number of straight grooves A can be adjusted appropriately, preferably six to eight.

[0079] Figure 4a for Figure 2a Schematic diagram of the inner reinforcing layer 12. Figure 4b for Figure 4a Sectional view at FF. See also Figure 4a and Figure 4b The inner reinforcing layer 12 also has grooves. The number and position of the grooves on the inner reinforcing layer 12 are the same as those on the first heat insulation layer 111. The two work together to form the straight groove in the weakening structure 15. That is, the weakening structure 15 is formed on the first heat insulation layer 111 and the inner reinforcing layer 12.

[0080] Please see Figure 2c In a further optional embodiment, the cross-section of the straight groove A is gradually tapered inward on the opening side of the straight groove A.

[0081] In this embodiment, the opening side of the straight groove A is the widest, and it becomes narrower towards the inside. Figure 2c In the embodiment shown, the cross-section of the straight groove A is V-shaped, but it is not limited to this; for example, it can also be semi-circular, teardrop-shaped, etc.

[0082] It should be understood that the thickness of the interlayer at the location of the straight groove A is an important factor affecting the strength of the weakened structure 15, and it is set according to the material and the working duration of the first-stage pulse.

[0083] In summary, the interlayer device 100 adopts a metal and non-metal composite structure, which plays a role of axial heat insulation and sealing in the solid double-pulse engine and has a positive opening function, meeting the dual requirements of structure and function.

[0084] In the formula, the non-metal material is used to manufacture the composite interlayer 10, and the metal material is used to manufacture the fixing ring 20. The composite interlayer 10 adopts a multi-material hierarchical structure, which improves the structural strength under the action of the reinforcing layer, ensures that the interlayer will not be damaged due to large deformation, and ensures the heat insulation and deformation capacity. The interlayer device 100 is easy to assemble, reduces the mass of the interlayer device 100, and improves the mass ratio of the engine. It should be noted that the interlayer device 100 is not limited to be applied to the solid double-pulse engine, but can also be applied to other multi-pulse engines.

[0085] Although the embodiments of the present application have been shown and described above, it should be understood that the above-described embodiments are exemplary and should not be construed as limiting the present application, and those skilled in the art can make changes, modifications, replacements and variations to the above-described embodiments within the scope of the present application.

Claims

1. A spacer device, characterized in that The composite partition (10) comprises a heat insulation layer (11) and an inner reinforcing layer (12) located in the heat insulation layer (11) and separating the heat insulation layer (11) into a first heat insulation layer (111) and a second heat insulation layer (112) in the axial direction; The axial side of the first heat insulation layer (111) and the axial side of the second heat insulation layer (112) correspondingly form a first open cavity (C1) and a second open cavity (C2) facing away from each other; The composite partition (10) is provided with a weakening structure (15) and is arranged to be cracked to form an opening communicating the second open cavity (C2) and the first open cavity (C1) when subjected to pressure from the second open cavity (C2) towards the first open cavity (C1).

2. The spacer device of claim 1, wherein, The middle part of the composite partition (10) is convexly arranged in the axial direction towards the first open cavity (C1) and forms a deepened ring cavity (C11) located at the side of the first open cavity (C1), and the deepened ring cavity (C11) and the second open cavity (C2) partially overlap in the circumferential direction.

3. The spacer device of claim 2, wherein, The composite partition (10) further comprises an outer reinforcing layer (14) located on at least part of the surface of the first heat insulation layer (111) at the position of the deepened ring cavity (C11).

4. The spacer device of claim 2, wherein, The second open cavity (C2) is arranged to be tapered in the direction from the opening side of the second open cavity (C2) towards the first open cavity (C1).

5. The spacer device of claim 2, wherein, The part of the deepened ring cavity (C11) overlapping the second open cavity (C2) in the circumferential direction is arranged to be tapered in the direction from the opening side of the first open cavity (C1) towards the second open cavity (C2).

6. The spacer device of claim 1, wherein, The weakening structure (15) is located in the middle part of the composite partition (10) and is formed in the first heat insulation layer (111) and the inner reinforcing layer (12).

7. The spacer device of claim 6, wherein, The weakening structure (15) comprises a plurality of straight grooves (A) intersecting at a point.

8. The spacer device of claim 7, wherein, The cross section of the straight groove (A) is tapered in the inward direction of the opening side of the straight groove (A).

9. The partition device according to any one of claims 1 to 8, characterized in that Further comprising a fixing ring (20) connected to the outer circumferential side of the composite partition (10).

10. An engine characterized by, The engine comprises the partition device (100) according to any one of claims 1 to 9, which is located between a first pulse combustion chamber (R1) and a second pulse combustion chamber (R2) of the engine to isolate the first pulse combustion chamber (R1) and the second pulse combustion chamber (R2).

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