Split type supporting structure suitable for annular runner of detonation ramjet engine

Abstract

The utility model provides a split type supporting structure suitable for an annular runner of a detonation ramjet engine, and belongs to the technical field of detonation ramjet engines, the split type supporting structure specifically comprises at least three supporting seats and a limiting assembly, the three supporting seats are distributed in the circumferential direction of an outer cylinder, and the supporting seats are fixedly connected with the outer side of the outer cylinder; grooves are formed in the positions, corresponding to the mounting holes, of the side wall of the outer ring of the inner cylinder, the ends, facing the inner cylinder, of the supporting seats are located in the grooves, the bottoms of the grooves and the end faces, facing the inner cylinder, of the supporting seats are arranged at intervals, and gaps are formed between the side walls, corresponding to the two axial ends of the inner cylinder, in the grooves and the side walls, facing the end of the inner cylinder, of the supporting seats. The limiting assembly limits the relative displacement of the inner cylinder and the supporting base in the circumferential direction of the inner cylinder. The requirement for relative displacement compensation of the inner cylinder and the outer cylinder when the engine works at high temperature can be met, and meanwhile vibration energy transmitted outwards by engine knocking combustion is greatly reduced.

Description

Technical Field

[0001] This application relates to the field of detonation ramjet engines, and more particularly to a split support structure suitable for the annular flow channel of a detonation ramjet engine. Background Technology

[0002] Detonation combustion technology, as an upgrade to traditional slow-burning combustion technology, can fundamentally replace existing propulsion devices that utilize combustion energy. Detonation combustion-based propulsion technology can significantly reduce fuel consumption and substantially improve the specific impulse characteristics of the propulsion system, which is of great significance for broadening the operational envelope of aircraft and enhancing the economy and performance of existing equipment.

[0003] However, compared to slow-burn combustion, detonation combustion is more difficult to trigger and less controllable. The understanding and mastery of its mechanism remain insufficient, hindering its application in propulsion systems. Researchers have experimented with standing-wave detonation engines and pulse detonation engines, conducting extensive research on pulse detonation engines and achieving a series of results. However, breakthroughs in highly efficient and reliable valves and stable and reliable re-ignition technologies have yet to be achieved, making it difficult for pulse detonation rocket engine technology to meet engineering application requirements.

[0004] To reduce the difficulty of engineering applications, continuous rotary detonation technology has emerged. Rotary detonation combustion releases heat rapidly and has a high thermal density; only a single successful ignition is needed for the detonation wave to propagate continuously along the circumference of the combustion chamber. Due to the unique continuous rotary detonation combustion method of the detonation ramjet engine, an annular flow channel structure is required to ensure the self-sustainability and stability of the detonation combustion. However, traditional annular flow channels employ an integral structure to ensure the sealing of the high-speed airflow passage. Under the high temperature, high pressure, and strong vibration environment generated during the operation of the continuous rotary detonation ramjet engine, this structure will generate thermal stress exceeding the material strength limit, which may lead to structural deformation and failure. Utility Model Content

[0005] In view of this, this application provides a split support structure suitable for the annular flow channel of a detonation ramjet engine, which solves the problems in the prior art, can meet the relative displacement compensation requirements of the inner and outer cylinders when the engine is operating at high temperature, and at the same time significantly reduces the vibration energy transmitted outward by the engine's detonation combustion.

[0006] The split support structure for the annular flow channel of a detonation ramjet engine provided in this application adopts the following technical solution:

[0007] A split-type support structure for the annular flow channel of a detonation ramjet engine is disclosed. The detonation ramjet engine includes an inner cylinder and an outer cylinder surrounding the outer circumference of the inner cylinder. The inner wall of the outer cylinder and the outer wall of the inner cylinder have circular cross-sections. The split-type support structure includes at least three support seats and a limiting component. The three support seats are distributed circumferentially around the outer cylinder. The outer cylinder has a mounting hole through which one end of the support seat passes. One end of the support seat passes through the mounting hole, and the other end of the support seat is fixedly connected to the outer side of the outer cylinder. The outer sidewall of the inner cylinder has a groove corresponding to the mounting hole. The end of the support seat facing the inner cylinder is located in the groove, and the bottom of the groove and the end face of the support seat facing the inner cylinder are spaced apart. A gap is provided between the sidewalls of the groove corresponding to the axial ends of the inner cylinder and the sidewall of the support seat facing the inner cylinder. The limiting component is used to limit the relative displacement of the inner cylinder and the end of the support seat facing the inner cylinder in the circumferential direction of the inner cylinder.

[0008] Optionally, the groove bottom is provided with a positioning pin protruding in the radial direction of the inner cylinder, and the end face of the support seat facing the inner cylinder is provided with an elongated hole. The length direction of the elongated hole is set along the axial direction of the inner cylinder, and the positioning pin is allowed to slide in the elongated hole. The elongated hole and the positioning pin meet the clearance fit assembly requirements of IT6-IT11 in the width direction of the elongated hole. The end face of the elongated hole facing away from the inner cylinder and the end of the positioning pin facing away from the inner cylinder are spaced apart. The positioning pin and the elongated hole constitute the limiting component.

[0009] Optionally, the inner wall of the groove and the outer peripheral wall of the end of the support facing the inner cylinder are both spaced apart.

[0010] Optionally, the locating pin is a cylindrical pin.

[0011] Optionally, the edge of the locating pin opposite to the inner cylinder is rounded.

[0012] Optionally, the support includes a flange mounting plate and a mating rod. The flange mounting plate is a flat plate structure. The length direction of the mating rod is perpendicular to the flange mounting plate. The flange mounting plate is fixed to the outer periphery of the outer cylinder by bolts. One end of the mating rod is connected to the flange mounting plate, and the other end of the mating rod mates with the groove.

[0013] Optionally, the outer peripheral sidewall of the outer cylinder is provided with a mating boss around the mounting hole. The side of the mating boss facing away from the inner cylinder is a planar structure, and a sealing groove is provided on the planar side of the mating boss facing away from the inner cylinder. A sealing ring is embedded in the sealing groove, and the sealing ring abuts against the end face of the outer cylinder facing away from the flange mounting plate.

[0014] Optionally, the support base has four evenly distributed along the circumference of the outer cylinder.

[0015] In summary, this application includes the following beneficial technical effects:

[0016] This application constrains the circumferential relative rotation of the inner and outer cylinders and their axial centers through the design of the support base, thus meeting the accuracy requirements for the relative position of the inner and outer cylinders. It also provides space for the relative displacement of the inner and outer cylinders in the axial and radial directions, thereby meeting the requirements for relative displacement compensation of the inner and outer cylinders when the engine is operating at high temperatures. At the same time, it also significantly reduces the vibration energy transmitted outward by the engine's knock combustion. Attached Figure Description

[0017] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1 This is a schematic diagram of the overall structure of the split support structure of this application;

[0019] Figure 2 This is a schematic diagram of the cross-sectional structure of the support base, inner cylinder, and outer cylinder in this application.

[0020] Explanation of reference numerals in the attached drawings: 1. Inner cylinder; 11. Groove; 12. Locating pin; 2. Outer cylinder; 21. Mounting hole; 22. Mating boss; 23. Bolt; 24. Sealing groove; 3. Support base; 31. Oblong hole; 32. Flange mounting plate; 33. Mating rod. Detailed Implementation

[0021] The embodiments of this application will now be described in detail with reference to the accompanying drawings.

[0022] The following specific examples illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. This application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this application. It should be noted that, in the absence of conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0023] It should be noted that various aspects of embodiments within the scope of the appended claims are described below. It will be apparent that the aspects described herein can be embodied in a wide variety of forms, and any particular structure and / or function described herein is merely illustrative. Based on this application, those skilled in the art will understand that one aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number of aspects set forth herein can be used to implement the device and / or practice the method. Additionally, this device and / or method can be implemented using structures and / or functionalities other than one or more of the aspects set forth herein.

[0024] It should also be noted that the illustrations provided in the following embodiments are only schematic representations of the basic concept of this application. The illustrations only show the components related to this application and are not drawn according to the number, shape and size of the components in actual implementation. In actual implementation, the form, quantity and proportion of each component can be arbitrarily changed, and the layout of the components may also be more complex.

[0025] Furthermore, specific details are provided in the following description to facilitate a thorough understanding of the examples. However, those skilled in the art will understand that the described aspects can be practiced without these specific details.

[0026] This application provides a split support structure suitable for the annular flow channel of a detonation ramjet engine.

[0027] like Figure 1 and him Figure 2 As shown, a split support structure suitable for the annular flow channel of a detonation ramjet engine is disclosed. The detonation ramjet engine includes an inner cylinder 1 and an outer cylinder 2 surrounding the outer periphery of the inner cylinder 1. The inner cylinder 1 and the outer cylinder 2 are coaxially arranged. The inner wall of the outer cylinder 2 and the outer wall of the inner cylinder 1 have circular cross-sections, forming an annular flow channel between the outer cylinder 2 and the inner cylinder 1. The split support structure includes at least three support seats 3 and a limiting component. The multiple support seats 3 are distributed circumferentially around the outer cylinder 2. The outer cylinder 2 is provided with a mounting hole 21 for one end of the support seat 3 to pass through. One end of the support seat 3 passes through the mounting hole 21, and the other end of the support seat 3 is fixedly connected to the outer side of the outer cylinder 2. The outer ring sidewall of the inner cylinder 1 has a groove 11 at the position corresponding to the mounting hole 21. The end of the support seat 3 facing the inner cylinder 1 is located in the groove 11, and the bottom of the groove 11 and the end face of the support seat 3 facing the inner cylinder 1 are spaced apart. There is a gap between the sidewalls of the groove 11 corresponding to the two axial ends of the inner cylinder 1 and the end sidewall of the support seat 3 facing the inner cylinder 1. The limiting component is used to limit the relative displacement of the inner cylinder 1 and the end of the support seat 3 facing the inner cylinder 1 in the circumferential direction of the inner cylinder 1.

[0028] In this application, the inner cylinder 1 and the outer cylinder 2 are connected by at least three support seats 3. The fixed connection between the support seats 3 and the outer cylinder 2, as well as the design of the limiting components, limit the position of the inner cylinder 1's axis relative to the outer cylinder 2 and its circumferential rotation. The axial gap between the support seats 3 and the grooves 11 of the inner cylinder 1 provides space for the axial relative displacement of the inner cylinder 1 and the outer cylinder 2. The bottom of the grooves 11 and the end face of the support seats 3 facing the inner cylinder 1 are spaced apart, providing space for the radial deformation of the inner cylinder 1 and the outer cylinder 2. Through the design of the support seats 3, this application constrains the circumferential relative rotation and the axial relative position of the inner cylinder 1 and the outer cylinder 2, meeting the accuracy requirements for the relative position of the inner cylinder 1 and the outer cylinder 2. It also provides space for the relative displacement of the inner cylinder 1 and the outer cylinder 2 in the axial and radial directions, thereby meeting the requirements for relative displacement compensation of the inner and outer cylinders when the engine is operating at high temperatures, and also significantly reducing the vibration energy transmitted outward by engine knock combustion.

[0029] In this embodiment, the support base 3 has four holes evenly distributed around the outer cylinder 2, and the axial direction of the mounting holes 21 is arranged along the radial direction of the outer cylinder 2.

[0030] The groove 11 has a positioning pin 12 protruding radially along the inner cylinder 1 on its bottom. The support base 3 has an elongated hole 31 on its end face facing the inner cylinder 1. The length of the elongated hole 31 is along the axial direction of the inner cylinder 1, and the positioning pin 12 is allowed to slide in the elongated hole 31 along its length. The elongated hole 31 and the positioning pin 12 meet the clearance fit requirements of IT6 to IT11 in the width direction of the elongated hole 31. The end face of the elongated hole 31 facing away from the inner cylinder 1 and the end of the positioning pin 12 facing away from the inner cylinder 1 are spaced apart. The positioning pin 12 and the elongated hole 31 constitute the limiting component.

[0031] The positioning pin 12 is a cylindrical pin, and the positioning pin 12 and the inner cylinder 1 are an integral structure. The positioning pin 12 and the two side walls in the corresponding width direction of the elongated hole 31 are assembled with a small clearance of H7 / f6, that is, the length of the elongated hole 31 is 2-4 times the diameter of the positioning pin 12, and the width distance of the elongated hole 31 and the diameter of the positioning pin 12 meet the assembly requirements of H7 / f6 clearance fit.

[0032] The inner wall of the groove 11 and the outer peripheral wall of the end of the support 3 facing the inner cylinder 1 are spaced apart to prevent over-constraint in the radial direction of the engine.

[0033] The end face of the positioning pin 12 facing away from the inner cylinder 1 is rounded to facilitate the quick entry of the positioning pin 12 into the elongated hole 31.

[0034] The support base 3 includes a flange mounting plate 32 and a mating rod 33. The flange mounting plate 32 is a flat plate structure. The length direction of the mating rod 33 is perpendicular to the flange mounting plate 32. The flange mounting plate 32 is fixed to the outer periphery of the outer cylinder 2 by bolts 23. One end of the mating rod 33 is integrally connected to the flange mounting plate 32, and the other end of the mating rod 33 mates with the groove 11. A gap is provided between the outer wall of the mating rod 33 and the inner wall of the mounting hole 21 to facilitate the quick assembly of the support base 3. The length of the mating rod 331 is set along the radial direction of the outer cylinder 2.

[0035] The outer peripheral sidewall of the outer cylinder 2 is provided with a mating boss 22 around the mounting hole 21. The side of the mating boss 22 facing away from the inner cylinder 1 is a planar structure, and a sealing groove 24 is provided on the plane of the mating boss 22 facing away from the inner cylinder 1. A sealing ring is embedded in the sealing groove 24. The sealing ring abuts against the end face of the outer cylinder 2 and the flange mounting plate 32, and the sealing ring seals the mating surface of the support base 3 and the outer cylinder 2.

[0036] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A split-type support structure for the annular flow channel of a detonation ramjet engine, the detonation ramjet engine comprising an inner cylinder (1) and an outer cylinder (2) surrounding the outer periphery of the inner cylinder (1), wherein the inner wall of the outer cylinder (2) and the outer wall of the inner cylinder (1) have circular cross-sections, characterized in that, The split support structure includes at least three support seats (3) and a limiting component. The multiple support seats (3) are circumferentially distributed around the outer cylinder (2). The outer cylinder (2) has mounting holes (21) through which one end of the support seat (3) passes. One end of the support seat (3) passes through the mounting hole (21), and the other end of the support seat (3) is fixedly connected to the outer side of the outer cylinder (2). The outer ring sidewall of the inner cylinder (1) has a groove (11) corresponding to the mounting hole (21). The support seats (3)... The end of the inner cylinder (1) facing the inner cylinder (1) is located in the groove (11), and the bottom of the groove (11) and the end face of the support (3) facing the inner cylinder (1) are spaced apart. There is a gap between the side wall of the groove (11) corresponding to both ends of the inner cylinder (1) and the side wall of the end of the support (3) facing the inner cylinder (1). The limiting component is used to limit the relative displacement of the end of the inner cylinder (1) and the end of the support (3) facing the inner cylinder (1) in the circumferential direction of the inner cylinder (1).

2. The split support structure for the annular flow channel of a detonation ramjet engine according to claim 1, characterized in that, The groove (11) has a positioning pin (12) protruding in the radial direction of the inner cylinder (1) on the bottom of the groove. The support base (3) has an elongated hole (31) on the end face facing the inner cylinder (1). The length direction of the elongated hole (31) is set along the axial direction of the inner cylinder (1), and the positioning pin (12) is allowed to slide in the elongated hole (31). The elongated hole (31) and the positioning pin (12) meet the clearance fit assembly requirements of IT6-IT11 in the width direction of the elongated hole (31). The end face of the elongated hole (31) facing away from the inner cylinder (1) and the end of the positioning pin (12) facing away from the inner cylinder (1) are spaced apart. The positioning pin (12) and the elongated hole (31) constitute the limiting component.

3. The split support structure for the annular flow channel of a detonation ramjet engine according to claim 2, characterized in that, The inner wall of the groove (11) and the outer peripheral wall of the end of the support (3) facing the inner cylinder (1) are both spaced apart.

4. The split support structure for the annular flow channel of a detonation ramjet engine according to claim 2, characterized in that, The positioning pin (12) is a cylindrical pin.

5. The split support structure for the annular flow channel of a detonation ramjet engine according to claim 4, characterized in that, The end face of the positioning pin (12) facing away from the inner cylinder (1) is rounded.

6. The split support structure for the annular flow channel of a detonation ramjet engine according to claim 1, characterized in that, The support base (3) includes a flange mounting plate (32) and a mating rod (33). The flange mounting plate (32) is a flat plate structure. The length direction of the mating rod (33) is perpendicular to the flange mounting plate (32). The flange mounting plate (32) is fixed to the outer periphery of the outer cylinder (2) by bolts (23). One end of the mating rod (33) is connected to the flange mounting plate (32), and the other end of the mating rod (33) is mated with the groove (11).

7. The split support structure for the annular flow channel of a detonation ramjet engine according to claim 6, characterized in that, The outer peripheral sidewall of the outer cylinder (2) is provided with a mating boss (22) around the mounting hole (21). The side of the mating boss (22) facing away from the inner cylinder (1) is a planar structure, and a sealing groove (24) is provided on the plane of the mating boss (22) facing away from the inner cylinder (1). A sealing ring is embedded in the sealing groove (24), and the end face of the sealing ring facing away from the outer cylinder (2) abuts against the flange mounting plate (32).

8. The split support structure for the annular flow channel of a detonation ramjet engine according to claim 1, characterized in that, The support base (3) has four supports evenly distributed around the outer cylinder (2).

Images