Gaseous bipropellant thrust chamber structure

Abstract

The present invention provides a gaseous bipropellant thrust chamber structure, comprising an integrally formed head and nozzle. The head comprises a head body and a combustion chamber wall. The head body, the combustion chamber wall, and the nozzle are coaxially arranged in sequence, with the bottom of the head body and the inner side of the combustion chamber wall forming a combustion chamber. A first component flow channel serving as a cooling channel is disposed within the head body and the combustion chamber wall, and a second component flow channel is disposed within the head body. Both the first component flow channel and the second component flow channel are connected to the combustion chamber, which is then connected to the nozzle. The first gaseous component enters the combustion chamber through the first component flow channel, and the second gaseous component enters the combustion chamber through the second component flow channel. The first and second gaseous components are mixed and ignited within the combustion chamber, thereby generating thrust. By utilizing an integrally formed head and nozzle, the present invention reduces the number of thrust chamber parts to one, shortening the product processing cycle, reducing processing costs, and improving the product's structural strength.

Description

Technical Field

[0001] The present invention relates to the field of rocket drive equipment, and in particular to a gaseous bipropellant thrust chamber structure. Background Art

[0002] In the field of aerospace propulsion systems, low cost, long life and reusability of engines have always been the goals pursued, but the harsh working environment of the engine has seriously restricted the realization of the above goals.

[0003] The high combustion temperature of the engine exceeds the melting point of many metals, so the engine combustion chamber needs to adopt special materials with high melting points such as niobium tungsten alloy to meet the high temperature resistance requirements, while limiting the engine's working time.

[0004] Patent publication number CN212985397U discloses a rocket engine thrust chamber comprising a thrust chamber body and a nozzle section. The thrust chamber body comprises a head and a throat, the throat section being recessed relative to the head section in the axial direction of the throat section. The nozzle section is interconnected at both ends and has an internal passage for the circulation of liquid / gas media. The thrust chamber body and nozzle section are coaxially arranged, and the adjacent end surfaces of the thrust chamber body and nozzle section are connected by a welded joint. The overall structure is rationally designed, ensuring structural stability and secure fixation in high-pressure and low-temperature environments, ensuring safe use of the rocket engine thrust chamber. However, the thrust chamber sidewalls lack cooling channels, which significantly limits the materials used in the combustion chamber. Summary of the Invention

[0005] In view of the defects in the prior art, the purpose of the present invention is to provide a gaseous bipropellant thrust chamber structure.

[0006] The gaseous bipropellant thrust chamber structure provided by the present invention includes a head and a nozzle, the head and the nozzle being integrally formed, the head including a head body and a combustion chamber wall, the head body, the combustion chamber wall, and the nozzle being coaxially arranged in sequence, and the bottom of the head body and the inner side of the combustion chamber wall forming a combustion chamber;

[0007] A first component flow channel as a cooling flow channel is provided inside the head body and the combustion chamber wall, and a second component flow channel is provided inside the head body. The first component flow channel and the second component flow channel are both connected to the combustion chamber, and the combustion chamber is connected to the nozzle;

[0008] The first gaseous component enters the combustion chamber through the first component flow channel, and the second gaseous component enters the combustion chamber through the second component flow channel. The first gaseous component and the second gaseous component are mixed and ignited in the combustion chamber, thereby generating thrust.

[0009] Preferably, the first component flow channel comprises a first component inlet, a guide groove and an injection hole which are connected in sequence;

[0010] The first component inlet is provided on the head body, the guide groove is provided inside the combustion chamber wall, and the injection hole is provided at the bottom inside the combustion chamber wall and communicates with the combustion chamber;

[0011] The first gaseous component passes through the first component inlet, the guide groove and the injection hole in sequence, and enters the combustion chamber from the bottom of the combustion chamber.

[0012] Preferably, the hole wall of the injection hole is arranged horizontally along the tangential direction of the combustion chamber wall and serves as an inner cooling channel;

[0013] After being ejected from the injection hole, the second gaseous component is rotated out horizontally along the tangential direction.

[0014] Preferably, the guide groove is a spiral groove structure, which is arranged inside the combustion chamber wall and serves as an outer cooling channel.

[0015] Preferably, there are multiple injection holes, and the multiple injection holes are circumferentially arranged at the inner bottom of the combustion chamber wall.

[0016] Preferably, the first component inlet and the guide groove are both arranged in a one-to-one correspondence with the injection holes.

[0017] Preferably, the second component flow channel comprises a second component inlet, a first gas collecting ring, a second gas collecting ring and a direct current injection hole which are connected in sequence;

[0018] The second component inlet, the first gas collecting ring, the second gas collecting ring and the direct current injection hole are all arranged inside the head body;

[0019] The second gaseous component passes through the second component inlet, the first gas collecting ring, the second gas collecting ring and the direct current injection hole in sequence, and enters the combustion chamber from the top of the combustion chamber.

[0020] Preferably, the first gas collecting ring, the second gas collecting ring and the DC injection holes form an n-type flow channel;

[0021] The bottom end of the first gas collecting ring is connected to the second component inlet, the top end of the first gas collecting ring is connected to one end of the second gas collecting ring, the other end of the second gas collecting ring is connected to the top end of the direct current injection hole, and the bottom end of the direct current injection hole is connected to the combustion chamber;

[0022] The flow direction of the second gaseous component in the first gas collecting ring is opposite to the flow direction in the direct current injection hole.

[0023] Preferably, the head and the nozzle are formed by additive manufacturing.

[0024] Preferably, a nozzle mounting seat is provided on the top of the head.

[0025] Compared with the prior art, the present invention has the following beneficial effects:

[0026] 1. The present invention has a simple structure and is easy to operate. It adopts an integrally formed head and nozzle, reducing the number of thrust chamber parts to one, shortening the product processing cycle, reducing processing costs, and improving the product structural strength.

[0027] 2. The present invention adopts the technical means of forming an n-type flow channel by a first gas collecting ring, a second gas collecting ring and a DC injection hole, and ensures the stability of the flow field of the second gaseous component by setting a multi-ring structure.

[0028] 3. The present invention adopts the technical means of tangentially setting the injection hole wall and uniformly distributing the guide grooves of the spiral groove structure on the wall of the combustion chamber, forming a two-layer cooling flow channel, which has significant cooling and heat insulation effects, effectively reduces the temperature of the combustion chamber wall, reduces the restrictions of the combustion chamber on materials, and breaks through the restrictions of the combustion chamber on material use. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Other features, objects and advantages of the present invention will become more apparent upon reading the detailed description of non-limiting embodiments with reference to the following drawings:

[0030] Figure 1 It is a structural schematic diagram of the present invention;

[0031] The figure shows:

[0032] Head 1 First air collecting ring 122

[0033] First component flow channel 11 Second gas collecting ring 123

[0034] First component inlet 111 DC injection hole 124

[0035] Guide groove 112 Nozzle mounting seat 13

[0036] Injection hole 113 Combustion chamber 2

[0037] Second component flow channel 12 nozzle 3

[0038] Second component entry 121 DETAILED DESCRIPTION

[0039] The present invention will be described in detail below with reference to specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those skilled in the art, several changes and improvements can be made without departing from the scope of the present invention. These all fall within the scope of protection of the present invention.

[0040] The present invention discloses a gaseous bipropellant thrust chamber structure, which creatively adopts an integrated thrust chamber structure, an n-type flow channel, and double-layer cooling flow channels inside and outside the combustion chamber. It has the advantages of simple structure, low combustion chamber wall temperature, and long working life, and can meet the use requirements of a long-life thrust chamber.

[0041] According to the gaseous bipropellant thrust chamber structure disclosed in the present invention, Figure 1 As shown, the head 1 includes an integrally formed head 1 and a nozzle 3. The head 1 includes a head body and a combustion chamber wall. The head body, the combustion chamber wall, and the nozzle 3 are coaxially arranged in sequence. The bottom of the head body and the inner side of the combustion chamber wall form a combustion chamber 2. A first component flow channel 11 serving as a cooling flow channel is provided within the head body and the combustion chamber wall. A second component flow channel 12 is provided within the head body. Both the first component flow channel 11 and the second component flow channel 12 are connected to the combustion chamber 2, which is connected to the nozzle 3. A first gaseous component enters the combustion chamber 2 through the first component flow channel 11, and a second gaseous component enters the combustion chamber 2 through the second component flow channel 12. The first and second gaseous components are mixed and ignited in the combustion chamber 2, thereby generating thrust. A nozzle mounting seat 13 is provided on the top of the head 1. After the first and second gaseous components are mixed in the combustion chamber 2, the nozzle ignites to generate thrust. Preferably, a through hole is axially arranged in the middle of the head body, a nozzle mounting seat 13 is arranged at one end of the through hole, and the other end of the through hole is connected to the combustion chamber 2.

[0042] Preferably, the head 1 and the nozzle 3 are formed by additive manufacturing, which has advantages of simple structure and low cost. Preferably, the first component flow channel 11 and the second component flow channel 12 are multiple and are uniformly arranged inside the head 1 along the circumferential direction.

[0043] The first component flow channel 11 includes a first component inlet 111, a guide groove 112, and an injection hole 113, which are connected in sequence. The first component inlet 111 is set on the head body, the guide groove 112 is set inside the combustion chamber wall, and the injection hole 113 is set at the bottom of the inner side of the combustion chamber wall and connected to the combustion chamber 2. The first gaseous component passes through the first component inlet 111, the guide groove 112, and the injection hole 113 in sequence and enters the combustion chamber 2 from the bottom of the combustion chamber 2. The hole wall of the injection hole 113 is arranged horizontally along the tangential direction of the combustion chamber wall and serves as the inner cooling flow channel. After the second gaseous component is ejected from the injection hole 113, it spirals out horizontally along the tangential direction. The guide groove 112 is a spiral groove structure, which is evenly distributed inside the combustion chamber wall and serves as the outer cooling flow channel. The guide groove (112) and the injection hole (113) form a double-layer cooling flow channel inside and outside the combustion chamber, which has a significant cooling and heat insulation effect, effectively reduces the temperature of the combustion chamber wall surface, and reduces the restriction of the combustion chamber on the material. Preferably, there are multiple injection holes 113, and the multiple injection holes 113 are arranged circumferentially at the bottom of the inner side of the combustion chamber wall surface, and the first component inlet 111 and the guide groove 112 are arranged in a one-to-one correspondence with the injection holes 113.

[0044] The second component flow channel 12 includes a second component inlet 121, a first gas collecting ring 122, a second gas collecting ring 123 and a DC injection hole 124 which are connected in sequence; the second component inlet 121, the first gas collecting ring 122, the second gas collecting ring 123 and the DC injection hole 124 are all arranged inside the head body; the second gaseous component passes through the second component inlet 121, the first gas collecting ring 122, the second gas collecting ring 123 and the DC injection hole 124 in sequence and enters the combustion chamber 2 from the top of the combustion chamber 2. The first gas collecting ring 122, the second gas collecting ring 123 and the DC injection hole 124 form an n-type flow channel; the bottom end of the first gas collecting ring 122 is connected to the second component inlet 121, the top end of the first gas collecting ring 122 is connected to one end of the second gas collecting ring 123, the other end of the second gas collecting ring 123 is connected to the top end of the DC injection hole 124, and the bottom end of the DC injection hole 124 is connected to the combustion chamber 2; the flow direction of the second gas component in the first gas collecting ring 122 is opposite to the flow direction in the DC injection hole 124, and the stability of the flow field is ensured through the multi-ring structure.

[0045] Example 1:

[0046] This embodiment provides a thrust chamber structure with two components of gas, hydrogen and oxygen. Gas hydrogen enters the head 1 from the first component inlet 111, and enters the combustion chamber 2 in sequence through the guide groove 112 and the injection hole 113. Gas oxygen enters the head 1 from the second component inlet 121, and enters the combustion chamber 2 in sequence through the first gas collecting ring 122, the second gas collecting ring 123 and the direct current injection hole 124. After the gas hydrogen and gas oxygen enter the combustion chamber, they are mixed in the combustion chamber and ignited under the action of the ignition source to generate thrust.

[0047] The hydrogen gas flows at a high speed in the spiral guide groove 112 and takes away part of the structural heat of the thrust chamber. After being ejected from the tangentially arranged injection hole 113, it rotates out horizontally tangentially to form an air film that adheres to the wall and rotates toward the top of the combustion chamber 2, isolating the high-temperature combustion gas from the combustion chamber wall. The double-layer cooling flow channel keeps the temperature of the combustion chamber wall at a low level, greatly reducing the thrust chamber's stringent requirements on materials and increasing the service life of the thrust chamber.

[0048] Specifically, the first gas collecting ring 122, the second gas collecting ring 123 and the DC injection hole 124 form an n-type oxidant flow channel, and the stability of the gas-oxygen path flow field is ensured through the multi-ring structure.

[0049] In the description of this application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on this application.

[0050] The above describes specific embodiments of the present invention. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art may make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. The embodiments of this application and the features in the embodiments may be combined with each other in any manner unless there is a conflict.

Claims

1. A gaseous bipropellant thrust chamber structure, characterized in that: The invention comprises a head (1) and a nozzle (3), wherein the head (1) and the nozzle (3) are integrally formed, the head (1) comprising a head body and a combustion chamber wall, the head body, the combustion chamber wall and the nozzle (3) being coaxially arranged in sequence, and the bottom of the head body and the inner side of the combustion chamber wall forming a combustion chamber (2); A first component flow channel (11) serving as a cooling flow channel is provided inside the head body and the combustion chamber wall, a second component flow channel (12) is provided inside the head body, the first component flow channel (11) and the second component flow channel (12) are both connected to the combustion chamber (2), and the combustion chamber (2) is connected to the nozzle (3); A first gaseous component enters the combustion chamber (2) through a first component flow channel (11), and a second gaseous component enters the combustion chamber (2) through a second component flow channel (12). The first gaseous component and the second gaseous component are mixed and ignited in the combustion chamber (2), thereby generating thrust.

2. The gaseous bipropellant thrust chamber structure according to claim 1, characterized in that: The first component flow channel (11) comprises a first component inlet (111), a guide groove (112) and an injection hole (113) which are connected in sequence; The first component inlet (111) is provided on the head body, the guide groove (112) is provided inside the combustion chamber wall, and the injection hole (113) is provided at the bottom inside the combustion chamber wall and is connected to the combustion chamber (2); The first gaseous component passes through the first component inlet (111), the guide groove (112) and the injection hole (113) in sequence, and enters the combustion chamber (2) from the bottom of the combustion chamber (2).

3. The gaseous bipropellant thrust chamber structure according to claim 2, characterized in that: The hole wall of the injection hole (113) is arranged horizontally along the tangential direction of the combustion chamber wall and serves as an inner cooling channel; After being ejected from the injection hole (113), the second gaseous component is rotated horizontally in a tangential direction.

4. The gaseous bipropellant thrust chamber structure according to claim 2, characterized in that: The guide groove (112) is a spiral groove structure, which is arranged inside the combustion chamber wall and serves as an outer cooling channel.

5. The gaseous bipropellant thrust chamber structure according to claim 2, characterized in that: There are multiple injection holes (113), and the multiple injection holes (113) are arranged on the inner bottom of the combustion chamber wall along the circumferential direction.

6. The gaseous bipropellant thrust chamber structure according to claim 5, characterized in that: The first component inlet (111) and the guide groove (112) are both arranged in one-to-one correspondence with the injection holes (113).

7. The gaseous bipropellant thrust chamber structure according to claim 1, characterized in that: The second component flow channel (12) comprises a second component inlet (121), a first gas collecting ring (122), a second gas collecting ring (123) and a direct current injection hole (124) which are connected in sequence; The second component inlet (121), the first gas collecting ring (122), the second gas collecting ring (123) and the direct current injection hole (124) are all arranged inside the head body; The second gaseous component passes through the second component inlet (121), the first gas collecting ring (122), the second gas collecting ring (123) and the direct current injection hole (124) in sequence, and enters the combustion chamber (2) from the top of the combustion chamber (2).

8. The gaseous bipropellant thrust chamber structure according to claim 7, characterized in that: The first gas collecting ring (122), the second gas collecting ring (123) and the direct current injection hole (124) form an n-type flow channel; The bottom end of the first gas collecting ring (122) is connected to the second component inlet (121), the top end of the first gas collecting ring (122) is connected to one end of the second gas collecting ring (123), the other end of the second gas collecting ring (123) is connected to the top end of the direct current injection hole (124), and the bottom end of the direct current injection hole (124) is connected to the combustion chamber (2); The flow direction of the second gaseous component in the first gas collecting ring (122) is opposite to the flow direction in the direct current injection hole (124).

9. The gaseous bipropellant thrust chamber structure according to claim 1, characterized in that: The head (1) and the nozzle (3) are formed by additive manufacturing.

10. The gaseous bipropellant thrust chamber structure according to claim 1, characterized in that: A nozzle mounting seat (13) is provided on the top of the head (1).

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