A combined rotary detonation engine combustion chamber structure

Abstract

The application discloses a combined rotary detonation engine combustion chamber structure, which mainly comprises a high-temperature alloy cylinder, bolts, nuts and a CMC cylinder, wherein the high-temperature alloy cylinder mainly comprises bolt holes, a main body cooling groove, a high-temperature alloy front flange, a high-temperature alloy front flange cooling groove, a high-temperature alloy rear flange, a high-temperature alloy rear flange cooling groove, cooling pipes, cooling pipe inlets, cooling pipe outlets and an igniter. The application can effectively improve the temperature resistance of the rotary detonation engine combustion chamber. The main body cooling groove is processed on the outer side of the high-temperature alloy cylinder, and the cooling pipes are installed on the cooling groove, so that the temperature of the high-temperature alloy cylinder can be reduced during the working of the rotary detonation engine combustion chamber. The temperature resistance of the ceramic matrix composite material adopted by the CMC cylinder reaches 1923K, and no additional cooling device is needed. The combined combustion chamber structure can increase the working durability of the rotary detonation engine combustion chamber, reduce the mass of the combustion chamber, improve the working efficiency and improve the thrust-to-weight ratio of the detonation engine.

Description

Technical Field

[0001] This invention relates to the technical field of rotary detonation engines, and more particularly to a combined rotary detonation engine combustion chamber structure. Background Technology

[0002] The rotating detonation engine is a novel type of engine that utilizes detonation waves to generate thrust, differing significantly from traditional gas turbine engines. Rotating detonation engines offer advantages such as high thermal cycle efficiency, simple structure, light weight, and a high thrust-to-weight ratio. However, the thermal environment of the combustion chamber in a detonation engine is extremely complex and harsh, especially the high-temperature environment, which places higher demands on the combustion chamber's temperature resistance. Traditional ordinary combustion chambers can no longer meet the high-temperature load requirements. To meet the high-temperature environmental requirements of rotating detonation engine combustion chambers, various active and passive cooling systems and composite material combustion chamber structures have been proposed. However, each structure faces certain structural defects and challenges, such as poor temperature resistance or excessive ablation rates leading to damage over time. Currently, few combustion chamber structures can meet the long-term use requirements of rotating detonation engine combustion chambers, and those that can achieve the required temperature increase weight and structural complexity. Therefore, there is an urgent need to design a rotating detonation engine combustion chamber structure to solve the aforementioned problems. Summary of the Invention

[0003] The technical problem to be solved by this invention is to address the shortcomings of the prior art by providing a combined rotary detonation engine combustion chamber structure. This invention uses a ceramic matrix composite (CMC) and high-temperature alloy to form a combined combustion chamber structure. Furthermore, a cooling device is provided on the high-temperature alloy, simplifying the rotary detonation engine combustion chamber structure, effectively improving the combustion chamber's temperature resistance, and thus improving the efficiency and thrust-to-weight ratio of the rotary detonation engine.

[0004] To achieve the above-mentioned technical objectives, the technical solution adopted by the present invention is as follows: A combined rotary detonation engine combustion chamber structure is characterized by comprising a high-temperature alloy cylinder, a CMC cylinder, and an igniter. The front end of the high-temperature alloy cylinder is connected to the combustion chamber inlet, and the rear end is connected to the front end of the CMC cylinder. The rear end of the CMC cylinder is connected to the combustion chamber outlet. The igniter is connected to the high-temperature alloy cylinder and is used to ignite the inner cavity of the high-temperature alloy cylinder. A main cooling groove is machined on the high-temperature alloy cylinder, and cooling pipes are installed on the main cooling grooves. Coolant flows in the cooling pipes and is used to cool the high-temperature alloy cylinder.

[0005] The aforementioned high-temperature alloy cylinder includes a high-temperature alloy front flange, an alloy cylinder body, a high-temperature alloy front flange cooling groove, a high-temperature alloy rear flange, and a high-temperature alloy rear flange cooling groove. The high-temperature alloy front flange is fixed to the front end of the alloy cylinder body, and the high-temperature alloy rear flange is fixed to the rear end of the alloy cylinder body. The high-temperature alloy front flange cooling groove is formed on the high-temperature alloy front flange, the high-temperature alloy rear flange cooling groove is formed on the high-temperature alloy rear flange, and the main cooling groove is formed on the alloy cylinder body. The high-temperature alloy front flange cooling groove, the main cooling groove, and the high-temperature alloy rear flange cooling groove are connected in sequence, and the cooling pipe is placed in the high-temperature alloy front flange cooling groove, the main cooling groove, and the high-temperature alloy rear flange cooling groove.

[0006] The aforementioned high-temperature alloy front flange cooling groove is spirally arranged around the outer surface of the high-temperature alloy front flange, the high-temperature alloy rear flange cooling groove is spirally arranged around the high-temperature alloy rear flange, the main cooling groove is spirally arranged around the main body of the alloy cylinder, the lower end of the cooling pipe is the cooling pipe inlet, the upper end of the cooling pipe is the cooling pipe outlet, the coolant enters the cooling pipe from the cooling pipe inlet and flows out of the cooling pipe from the cooling pipe outlet.

[0007] The aforementioned igniter is made of high-temperature alloy material. The igniter is connected to the alloy cylinder body at an angle to the normal direction of the alloy cylinder body wall. The cooling pipe is close to or in contact with the igniter to cool it down.

[0008] The CMC cylinder is fixed with a CMC front flange at the front end and a CMC rear flange at the rear end. The CMC front flange, CMC rear flange, high-temperature alloy front flange, and high-temperature alloy rear flange are all provided with multiple bolt holes that run through the front and rear. After the bolts pass through the bolt holes, they cooperate with the nuts to seal and fix the high-temperature alloy front flange to the combustion chamber inlet, the CMC front flange to the high-temperature alloy rear flange, and the CMC rear flange to the combustion chamber outlet.

[0009] The connection between the CMC cylinder and the CMC front flange, as well as the connection between the CMC cylinder and the CMC rear flange, are provided with CMC chamfers, and the CMC chamfers are greater than or equal to R5.

[0010] Both the front surface of the CMC front flange and the rear surface of the CMC rear flange are provided with CMC sealing grooves, and flexible graphite for sealing is provided in the CMC sealing grooves.

[0011] The bolts mentioned above are also fitted with washers, which are placed between the nut and the corresponding flange.

[0012] The aforementioned high-temperature alloy cylinder is made of high-temperature alloy material, the CMC cylinder is made of ceramic matrix composite material, the bolts and nuts are made of ceramic matrix composite material, and the gaskets are made of aluminum alloy or rubber.

[0013] The aforementioned CMC tube is made of 2.5D woven C / SiC material.

[0014] The present invention has the following advantages: This invention can improve the durability of the combustion chamber of a rotating detonation engine. The combined structure of the CMC cylinder and the high-temperature alloy cylinder effectively improves the temperature resistance of the combustion chamber. The design of the cooling groove improves the temperature resistance of the high-temperature alloy cylinder and reduces the thermal stress caused by the different coefficients of thermal expansion of the flange connection at high temperatures. The design of the sealing groove improves the sealing performance of the combined combustion chamber and improves the overall performance of the rotating detonation engine. The selection of CMC material can reduce the weight of the engine and has a very good beneficial effect on improving the various performances of the rotating detonation engine. It has extremely high application value for the application of rotating detonation engines in various aerospace aircraft. Attached Figure Description

[0015] Figure 1 This is the combustion chamber structure of a rotary detonation engine; Figure 2 Drawings of combustion chamber components; Figure 3 This is a structural diagram of the high-temperature alloy cylinder for the combustion chamber. Figure 4 This is a structural diagram of the combustion chamber CMC cylinder.

[0016] The attached figures are labeled as follows: 1 for high-temperature alloy cylinder, 101 for bolt hole, 102 for main cooling tank, 103 for high-temperature alloy front flange, 104 for high-temperature alloy front flange cooling tank, 105 for high-temperature alloy rear flange, 106 for high-temperature alloy rear flange cooling tank, 107 for cooling pipe, 108 for cooling pipe inlet, 109 for cooling pipe outlet, 110 for igniter, 2 for bolt, 3 for nut, 301 for gasket, 4 for CMC cylinder, 401 for CMC front flange, 402 for CMC chamfer, 403 for CMC sealing groove, and 404 for CMC rear flange. Detailed Implementation

[0017] To make the objectives, technical solutions, and advantages of this application clearer, the application is described and illustrated below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the scope of this application. All other embodiments obtained by those skilled in the art based on the embodiments provided in this application without inventive effort are within the scope of protection of this application.

[0018] Obviously, the accompanying drawings described below are merely some examples or embodiments of this application. Those skilled in the art can apply this application to other similar scenarios based on these drawings without any inventive effort. Furthermore, it is understood that although the efforts made in this development process may be complex and lengthy, for those skilled in the art related to the content disclosed in this application, any changes to design, manufacturing, or production based on the technical content disclosed in this application are merely conventional technical means and should not be construed as insufficient disclosure of the content of this application.

[0019] In this application, the reference to "embodiment" means that a specific feature, structure, or characteristic described in connection with an embodiment may be included in at least one embodiment of this application. The appearance of this phrase in various places in the specification does not necessarily refer to the same embodiment, nor is it a separate or alternative embodiment that is mutually exclusive with other embodiments. It will be explicitly and implicitly understood by those skilled in the art that the embodiments described in this application may be combined with other embodiments without conflict.

[0020] Unless otherwise defined, the technical or scientific terms used in this application shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms “a,” “an,” “an,” “the,” and similar words used in this application do not indicate quantity limitation and may indicate singular or plural. The terms “comprising,” “including,” “having,” and any variations thereof used in this application are intended to cover non-exclusive inclusion; for example, a process, method, system, product, or apparatus that includes a series of steps or units (elements) is not limited to the listed steps or units, but may also include steps or units not listed, or may include other steps or units inherent to these processes, methods, products, or apparatus. The terms “connected,” “linked,” “coupled,” and similar words used in this application are not limited to physical or mechanical connections, but may include electrical connections, whether direct or indirect. The terms “multiple” / “several” used in this application refer to two or more. “And / or” describes the relationship between related objects, indicating that three relationships may exist; for example, “A and / or B” can indicate: A alone, A and B simultaneously, or B alone. The character " / " generally indicates that the preceding and following objects are in an "or" relationship. The terms "first," "second," and "third" used in this application are merely to distinguish similar objects and do not represent a specific ordering of the objects.

[0021] Please see Figure 1 , Figure 2 , Figure 3 and Figure 4 The embodiments of the present invention include: A combined rotary detonation engine combustion chamber structure includes a high-temperature alloy cylinder 1, bolts 2, nuts 3, and a CMC cylinder 4. The high-temperature alloy cylinder 1 is mainly composed of bolt holes 101, a main cooling groove 102, a high-temperature alloy front flange 103, a high-temperature alloy front flange cooling groove 104, a high-temperature alloy rear flange 105, a high-temperature alloy rear flange cooling groove 106, a cooling pipe 107, a cooling pipe inlet 108, a cooling pipe outlet 109, and an igniter 110. The CMC cylinder 4 is mainly composed of a CMC front flange 401, a CMC chamfer 402, a CMC sealing groove 403, and a CMC rear flange 404.

[0022] The high-temperature alloy front flange 103 is connected to the combustion chamber inlet device, and the CMC rear flange 404 is connected to the combustion chamber tail nozzle. The high-temperature alloy cylinder 1 and the CMC cylinder 4 are connected by flanges to form the rotary detonation engine combustion chamber, which has a very high temperature resistance.

[0023] The high-temperature alloy cylinder 1 is made of high-temperature alloy material, such as GH3536, which has excellent high-temperature mechanical stability. The high-temperature alloy front flange 103 and high-temperature alloy rear flange 105 on the high-temperature alloy cylinder 1 are respectively machined with high-temperature alloy front flange cooling groove 104 and high-temperature alloy rear flange cooling groove 106. A main cooling groove 102 is machined on the high-temperature alloy cylinder 1. The high-temperature alloy rear flange cooling groove 106, the main cooling groove 102, and the high-temperature alloy front flange cooling groove 104 are connected in sequence. A cooling pipe 107 is inserted. The coolant enters the cooling pipe inlet 108 of the high-temperature alloy rear flange cooling groove 106, passes through the main cooling groove 102, and flows out from the cooling pipe outlet on the high-temperature alloy front flange cooling groove 104. The coolant is the liquid fuel of the combustion chamber. Because the temperature at the rear end of the high-temperature alloy cylinder 1 is higher than the temperature at the inlet end, this coolant flow method can effectively reduce the overall temperature of the high-temperature alloy cylinder 1, increase the temperature resistance of the rotary detonation engine, and increase the working time of the rotary detonation engine combustion chamber. The length of the high-temperature alloy cylinder 1 is generally set to one-third of the total length of the combustion chamber. It is located in the inlet area of ​​the rotating detonation combustion chamber, where the temperature is the lowest. The design can be adjusted according to the actual working conditions. The high-temperature alloy cylinder 1 used here can be connected to the combustion chamber inlet using the high-temperature alloy front flange.

[0024] The cooling pipes of the high-temperature alloy front flange cooling tank 104 and the high-temperature alloy rear flange cooling tank 106 are circulated with coolant, which can effectively reduce the temperature of the high-temperature alloy front flange 103 and the high-temperature alloy rear flange 105. This can reduce the temperature of the flange connection area, effectively reduce the thermal stress of the bolt 2 and nut 3 connection caused by the difference in high-temperature thermal expansion properties, effectively improve the stability and sealing of the flange connection of the combined combustion chamber of the rotary detonation engine, and improve the structural strength of the flange connection.

[0025] The igniter 110 is made of high-temperature alloy material, such as GH3536, which has excellent high-temperature mechanical stability. The cooling pipe 107 flows around the igniter, which can effectively reduce the temperature of the igniter and increase the durability of the igniter and combustion chamber.

[0026] Bolt 2 and nut 3 are made of ceramic matrix composite material with a 2D needle-punched braiding structure, which has high temperature thermal stability and low coefficient of thermal expansion. Gasket 301 is made of aluminum alloy or rubber material.

[0027] The CMC cylinder 4 mainly consists of a CMC front flange 401, a CMC chamfer 402, a CMC sealing groove 403, and a CMC rear flange 404. The CMC cylinder 4 is made of ceramic matrix composite material, with a 2.5D or 3D weaving method. The warp direction of the weave structure is the same as the axial direction of the combustion chamber, and the weft direction is the same as the circumferential direction of the combustion chamber. This material has good high-temperature resistance and mechanical properties. The thickness of the CMC cylinder is between 5-10mm, exhibiting excellent ablation resistance. Its application in the combustion chamber of a rotary detonation engine can significantly increase the combustion chamber's temperature resistance, reduce cooling air volume, lower the weight of the detonation engine, and improve its efficiency and thrust-to-weight ratio. The CMC cylinder is made of ceramic matrix composite material. There are many types of ceramic matrix composite materials; here, a 2.5D woven C / SiC material is selected. It exhibits good mechanical properties in ultra-high temperature environments, can operate for short periods at 2500K, and can operate for long periods below 1932K. This reduces the cooling air volume of the rotary detonation engine, lowers its weight, and improves its efficiency and thrust-to-weight ratio.

[0028] The CMC front flange 401 of the CMC cylinder 4 has a CMC sealing groove 403 of a certain width on its outer side. Flexible graphite is placed in the groove, and then the flange is connected and fixed by bolts 2 and nuts 3. The flexible graphite placed in the CMC sealing groove 403 has good high temperature stability, so the flange connection part of the combustion chamber has good temperature resistance and sealing performance.

[0029] The CMC cylinder 4 features a CMC chamfer 402 in the abrupt structural change area. The CMC chamfer 402 is defined as a chamfer greater than or equal to R5. This allows for a more reasonable arrangement of the woven structure of the CMC cylinder 4, ensuring that the overall structural strength of the CMC cylinder 4 is not reduced due to excessive rotation angles. This effectively improves the overall structural strength of the rotating detonation combustion chamber.

[0030] When the rotating detonation combustor is in operation, fuel and air or a specific amount of oxygen are injected into the inlet at a certain ratio. The inlet is the inlet of the high-temperature alloy cylinder 1. After ignition by the igniter, the fuel and air combust violently, forming a shock wave. The shock wave rotates in the combustor, forming a continuously rotating detonation wave. This detonation wave passes through the combustor and is ejected at high speed from the outlet, generating a huge thrust on the tail nozzle. The high-temperature gas in the combustor will cause a strong thermal shock and ablation to the combustor wall. The average temperature of the gas can reach about 2000K. Ordinary alloy combustors cannot resist the impact of such high-temperature gas. The average temperature of the high-temperature gas in the combustor is different. The temperature is lowest at the inlet and higher closer to the outlet. Therefore, this invention adopts a combined combustor structure, placing the high-temperature alloy cylinder in the inlet area and the CMC cylinder in the combustor outlet area. This can effectively resist the high-temperature impact and ablation of the gas in the combustor.

[0031] To ensure a tight seal in the flange connection area of ​​the detonation combustion chamber, a sealing groove is machined on the flange of the CMC cylinder, and flexible graphite is added into the sealing groove. When the combustion chamber starts operating, coolant is introduced through the cooling pipe inlet. The coolant is the liquid fuel required by the rotary detonation engine combustion chamber, such as kerosene or gasoline, eliminating the need for additional coolant and reducing the weight of the rotary detonation engine. The coolant flows in from the cooling pipe inlet, passes through the high-temperature alloy rear flange, the outer wall of the high-temperature alloy cylinder, and the high-temperature alloy front flange, and then flows out from the cooling pipe outlet. The outflowing coolant is injected into the fuel inlet of the rotary detonation engine into the combustion chamber. This method has three benefits: first, it effectively reduces the temperature of the high-temperature alloy cylinder; second, it improves the fuel utilization efficiency of the rotary detonation engine combustion chamber, eliminating the need for additional coolant and reducing the weight of the rotary detonation engine during operation; and third, the coolant introduced into the flange reduces the temperature of the flange connection area, effectively reducing thermal stress caused by high temperatures and improving the structural strength of the flange connection.

[0032] This invention can improve the durability and temperature resistance of the combustion chamber of a rotating detonation engine. It has a simple overall structure, good sealing performance and high-temperature stability, and can effectively increase the operating temperature of the detonation engine and reduce its weight. It has a very good effect on improving the various performance characteristics of the rotating detonation engine and has a promising application prospect in various aerospace aircraft.

[0033] This invention enables ultra-high temperature ablation tests of ceramic matrix composites in various complex and variable environments, which helps to study the ablation performance and structural damage of ceramic matrix composites under various high-temperature environments. It can effectively avoid the failure of ceramic matrix composites under high-temperature service environments and has good application prospects in various aero-engines and high-speed aircraft that use ceramic matrix composites as hot-end components. It has a very good beneficial effect on improving the service life of various aero-engines and high-speed aircraft.

[0034] The above are merely preferred embodiments of the present invention. The scope of protection of the present invention is not limited to the above embodiments. All technical solutions falling within the scope of the present invention's concept are within the scope of protection of the present invention. It should be noted that for those skilled in the art, any improvements and modifications made without departing from the principles of the present invention should be considered within the scope of protection of the present invention.

Claims

1. A combined rotary detonation engine combustion chamber structure, characterized in that: Including high temperature The high-temperature alloy cylinder (1), CMC cylinder (4), and igniter (110) are provided. The front end of the high-temperature alloy cylinder (1) is connected to the combustion chamber inlet, and the rear end is connected to the front end of the CMC cylinder (4). The rear end of the CMC cylinder (4) is connected to the combustion chamber outlet. The igniter (110) is connected to the high-temperature alloy cylinder (1) and is used to ignite the inner cavity of the high-temperature alloy cylinder (1). The high-temperature alloy cylinder (1) is provided with a main cooling groove (102), and a cooling pipe (107) is installed on the main cooling groove (102). Cooling liquid flows in the cooling pipe (107) and is used to cool the high-temperature alloy cylinder (1). The high-temperature alloy cylinder (1) includes a high-temperature alloy front flange (103), an alloy cylinder body, and a high-temperature alloy front flange (103). The high-temperature alloy front flange cooling groove (104), high-temperature alloy rear flange (105), and high-temperature alloy rear flange cooling groove (106) are provided. The high-temperature alloy front flange (103) is fixed to the front end of the alloy cylinder body, and the high-temperature alloy rear flange (105) is fixed to the rear end of the alloy cylinder body. The high-temperature alloy front flange cooling groove (104) is formed on the high-temperature alloy front flange (103), and the high-temperature alloy rear flange cooling groove (106) is formed on the high-temperature alloy rear flange (105). The main cooling groove (102) is formed on the alloy cylinder body. The high-temperature alloy front flange cooling groove (104), main cooling groove (102), and high-temperature alloy rear flange cooling groove (106) are provided. 6) The cooling pipe (107) is connected in sequence and placed in the high-temperature alloy front flange cooling tank (104), the main cooling tank (102), and the high-temperature alloy rear flange cooling tank (106); the high-temperature alloy front flange cooling tank (104) is spirally arranged around the outer surface of the high-temperature alloy front flange (103), the high-temperature alloy rear flange cooling tank (106) is spirally arranged around the high-temperature alloy rear flange (105), and the main cooling tank (102) is spirally arranged around the main body of the alloy cylinder. The lower end of the cooling pipe (107) is the cooling pipe inlet (108), and the upper end of the cooling pipe (107) is the cooling pipe outlet (109). The coolant enters the cooling pipe (107) from the cooling pipe inlet (108) and exits from the cooling pipe outlet (109). The cooling pipe (107) flows out of the outlet (109); the front end of the CMC cylinder (4) is fixed with a CMC front flange (401) and the rear end is fixed with a CMC rear flange (404). The CMC front flange (401), CMC rear flange (404), high temperature alloy front flange (103) and high temperature alloy rear flange (105) are all provided with multiple bolt holes (101) that run through the front and rear. After the bolt (2) can pass through the bolt hole (101), it cooperates with the nut (3) to seal and fix the high temperature alloy front flange (103) to the combustion chamber inlet, the CMC front flange (401) to the high temperature alloy rear flange (105), and the CMC rear flange (404) to the combustion chamber outlet.

2. The combined rotary detonation engine combustion chamber structure according to claim 1, characterized in that: The igniter (110) is made of high-temperature alloy material. The igniter (110) is connected to the alloy cylinder body in such a way that it has an angle with the normal direction of the alloy cylinder body wall. The cooling pipe (107) is close to or in contact with the igniter (110) to cool down the igniter (110).

3. The combined rotary detonation engine combustion chamber structure according to claim 2, characterized in that: The connection between the CMC cylinder (4) and the CMC front flange (401) and the connection between the CMC cylinder (4) and the CMC rear flange (404) are provided with CMC chamfers (402), and the CMC chamfers (402) are greater than or equal to R5.

4. The combined rotary detonation engine combustion chamber structure according to claim 3, characterized in that: The front surface of the CMC front flange (401) and the rear surface of the CMC rear flange (404) are both provided with CMC sealing grooves (403), and flexible graphite for sealing is provided in the CMC sealing grooves (403).

5. The combined rotary detonation engine combustion chamber structure according to claim 4, characterized in that: The bolt (2) is also fitted with a washer (301), which is placed between the nut (3) and the corresponding flange.

6. The combined rotary detonation engine combustion chamber structure according to claim 5, characterized in that: The high-temperature alloy cylinder (1) is made of high-temperature alloy material, the CMC cylinder (4) is made of ceramic matrix composite material, the bolt (2) and nut (3) are made of ceramic matrix composite material, and the gasket (301) is made of aluminum alloy or rubber.

7. The combined rotary detonation engine combustion chamber structure according to claim 6, characterized in that: The CMC tube (4) is made of 2.5-dimensional woven C / SiC material.

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