A visual combustion chamber with body cooling and its rocket engine

Abstract

The present invention belongs to the field of combustion chambers, and specifically relates to a visual combustion chamber with body cooling and a rocket engine thereof, comprising a combustion chamber body, an observation window, and a window temperature control structure. The combustion chamber body comprises an injection assembly mounting wall, a cylindrical side wall, and a nozzle assembly mounting wall arranged in sequence, the injection assembly mounting wall, the cylindrical side wall, and the nozzle assembly mounting wall enclosing a combustion chamber. The observation window is disposed on the side wall of the cylindrical side wall. The window temperature control structure comprises a cooling air film outlet channel for ejecting a cooling air film from the upstream end of the observation window to control the temperature of the inner wall of the observation window, and a propellant air film outlet channel for ejecting a propellant air film to assist flame combustion in the combustion chamber, forming a double-layer air film with the cooling air film to assist the cooling air film in controlling the temperature of the inner wall of the observation window. The present invention can significantly reduce the temperature of the observation window while improving the flame combustion effect in the combustion chamber.

Description

Technical Field

[0001] The invention belongs to the field of combustion chambers, and in particular relates to a visual combustion chamber with body cooling and a rocket engine thereof. Background Art

[0002] With the continued development of liquid rocket engines and the demand for high-performance, high-reliability, lightweight, and reusable engines, it is imperative to more comprehensively understand the combustion flow field parameters of liquid rocket engines. Key physical parameters include the structural characteristics of the combustion flow field, combustion chamber temperature, and pressure. Analyzing the pressure oscillations and flow characteristics within key components such as the combustion chamber, piping, and injectors can better guide engine design.

[0003] During ground testing, conventional liquid rocket engine combustion chambers are often fully enclosed, making it impossible to observe the combustion flow field structure. Understanding combustion phenomena relies primarily on indirect measurements and computational simulations, lacking intuitive and robust data. This limits in-depth understanding of combustion mechanisms and hinders the analysis and control of combustion stability. High-frequency combustion instabilities can induce large pressure oscillations, seriously threatening engine reliability. Furthermore, this makes it impossible to diagnose and prevent potential faults, increasing the difficulty of engine design optimization and limiting improvements in combustion chamber performance. Therefore, liquid rocket engine combustion chambers with visual observation windows have been developed. This allows cameras to observe the combustion flow field structure through the observation window. However, long-term use has revealed that the service life of the observation window is far shorter than that of the combustion chamber itself. This is primarily due to the high temperature of the flame affecting the observation window, significantly reducing its service life. Therefore, there is an urgent need for a rocket engine combustion chamber with enhanced overall performance. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to provide a visual combustion chamber with body cooling and a rocket engine thereof, which can improve the combustion effect and ensure the temperature control of the observation window.

[0005] The present invention provides a visual combustion chamber with body cooling, comprising a combustion chamber body, an observation window and a window temperature control structure;

[0006] The combustion chamber body comprises an injection assembly mounting wall, a cylindrical side wall and a nozzle assembly mounting wall which are arranged in sequence, wherein the injection assembly mounting wall, the cylindrical side wall and the nozzle assembly mounting wall enclose a combustion chamber;

[0007] The observation window is provided on the side wall of the cylindrical side wall for observing the combustion condition of the flame in the combustion chamber;

[0008] The window temperature control structure includes a cooling air component and a propellant component. The cooling air component includes a cooling air film outlet channel. The cooling air film outlet channel is arranged toward the observation window close to one end of the injection component installation wall, and is used to spray a cooling air film from the upstream end of the observation window to the inner wall of the observation window for temperature control. The propellant component includes a propellant air film outlet channel arranged on the inner side of the cooling air film outlet channel. The propellant air film outlet channel is used to spray a propellant air film to assist the flame combustion in the combustion chamber, and form a double-layer air film with the cooling air film to assist the cooling air film in temperature control of the inner wall of the observation window.

[0009] Furthermore, the injection assembly installation wall is provided with an injection assembly installation slot, and the injection assembly installation slot is provided with an injection panel;

[0010] The cooling air component further includes a cooling air cavity provided on the inner wall of the injection component mounting groove and a cooling air inlet provided on the outer wall of the combustion chamber body and connected to the cooling air cavity, wherein the cooling air cavity is connected to the cooling air film outlet channel;

[0011] The injection panel includes an embedding portion embedded in the injection assembly installation groove, and an outer wall end of the embedding portion is spaced apart from the upstream end surface of the observation window, and the space forms the cooling air film outlet channel.

[0012] Furthermore, the cooling air cavity includes a circular channel arranged in the injection panel and a flare connected to the side wall of the circular channel. One side of the flare abuts against the outer wall of the mosaic part, and the other side abuts against the upstream end face of the observation window. The circular channel, the flare, the outer wall of the mosaic part and the upstream end face of the observation window enclose to form the cooling air cavity.

[0013] Furthermore, the propellant assembly further includes a propellant gas cavity provided in the injection panel and a propellant gas inlet provided on the outer wall of the injection panel and communicating with the propellant gas cavity, and the propellant gas film outlet channel is communicated with the propellant gas cavity.

[0014] Furthermore, a fuel nozzle is provided in the middle of the injection panel, and the propulsion gas cavity is arranged around the outer wall of the fuel nozzle.

[0015] Furthermore, the cooling gas film outlet channel and the propellant film outlet channel are strip-shaped slit channels, and the length of the strip-shaped slit channels corresponds to the end surface of the observation window.

[0016] Furthermore, the cylindrical side wall is a rectangular cylinder, the three side walls of the rectangular cylinder are provided with the observation windows, and the other side wall of the cylindrical side wall is provided with a temperature measuring hole.

[0017] Furthermore, the visual combustion chamber with body cooling further comprises a water cooling structure provided on the combustion chamber body;

[0018] The water cooling structure includes a water cooling liquid inlet and a water cooling liquid outlet arranged on the outer wall of the combustion chamber body, and also includes a water cooling channel arranged inside the combustion chamber body to communicate with the water cooling liquid inlet and the water cooling liquid outlet.

[0019] Furthermore, the visualized combustion chamber with body cooling further comprises a nozzle assembly arranged on the nozzle assembly mounting wall.

[0020] The present invention also provides a rocket engine, comprising the above-mentioned visualized combustion chamber with body cooling.

[0021] The beneficial effect of the present invention is that the visual combustion chamber with body cooling provided by the present invention can significantly reduce the temperature of the observation window on the basis of improving the flame combustion effect in the combustion chamber through the structural design of the cooling gas film outlet channel and the propellant film outlet channel. On the one hand, it solves the problem that the current observation window is not resistant to high temperature and is easily damaged by the high temperature in the combustion chamber, affecting the overall performance of the combustion chamber. On the other hand, it also solves the problem that the current cooling gas generally uses inert gas that does not participate in the combustion reaction, which causes the inert gas to enter the combustion chamber and affect the flame combustion. Specifically, the cooling air film ejected from the cooling air film outlet channel is used to directly dissipate heat to the inner wall of the observation window on the one hand, and can isolate the high-temperature flame in the combustion chamber from the observation window on the other hand, thereby ensuring the temperature of the observation window, achieving effective thermal protection for the observation window, and further improving the overall structural performance of the combustion chamber; the propellant air film ejected from the propellant air film outlet channel can, on the one hand, promote further combustion of the flame and improve combustion efficiency, and on the other hand, form a double-layer air film with the cooling air film, that is, it is used to increase the flow distance of the cooling air film along the inner wall of the observation window, ensure the temperature control effect of the observation window at various locations in the direction from the injection assembly mounting wall to the nozzle assembly mounting wall, and can isolate the high-temperature flame in the combustion chamber from the cooling air film, and further isolate the high-temperature flame in the combustion chamber from the observation window. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Attachment Figure 1 This is a schematic diagram of the first angle structure of the combustion chamber body in the present invention;

[0023] Attachment Figure 2 For attachment Figure 1 Exploded cross-section view from a medium perspective;

[0024] Attachment Figure 3 This is a second angle structural diagram of the combustion chamber body in the present invention;

[0025] Attachment Figure 4 For attachment Figure 3 Exploded cross-section view from a medium perspective;

[0026] Attachment Figure 5 A 3 / 4 cross-sectional view of a visualized combustion chamber with body cooling according to the present invention;

[0027] Attachment Figure 6 For attachment Figure 5 A partial enlarged view of point A in the middle.

[0028] In the figure, 1-combustion chamber body; 11-injection assembly mounting wall; 111-injection assembly mounting groove; 12-cylindrical side wall; 121-window mounting groove; 122-temperature measuring hole; 13-nozzle assembly mounting wall; 131-nozzle mounting groove; 14-combustion chamber; 15-window cover; 2-observation window; 3-cooling gas assembly; 31-cooling gas inlet; 32-cooling gas cavity; 321-circular channel; 322-expansion; 33-cooling gas film outlet channel; 4-injection panel; 41-fuel nozzle; 42-propellant assembly; 421-propellant gas inlet; 422-propellant gas cavity; 423-propellant gas film outlet channel; 43-fitting part; 44-limiting part; 5-nozzle assembly; 6-water cooling structure; 61-water cooling liquid inlet; 62-water cooling channel; 63-water cooling liquid outlet; 7-asbestos gasket; 8-sealing ring. DETAILED DESCRIPTION

[0029] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention without making any creative efforts shall fall within the scope of protection of the present invention.

[0030] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relative position relationship, movement status, etc. between the various components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0031] In addition, the terms "first," "second," and so on, used in this disclosure are for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referenced. Thus, a feature specified as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of this disclosure, "plurality" means at least two, such as two or three, unless otherwise specifically defined.

[0032] In the present invention, unless otherwise specified or limited, the terms "connection" and "fixation" should be understood in a broad sense. For example, "fixation" can mean fixed connection, detachable connection, or integration; it can mean mechanical connection, electrical connection, physical connection, or wireless communication connection; it can mean direct connection or indirect connection through an intermediate medium; it can mean internal communication between two elements or interaction between two elements, unless otherwise specified. For those skilled in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0033] In addition, the technical solutions between the various embodiments of the present invention can be combined with each other, but it must be based on the fact that ordinary technicians in this field can implement it. When the combination of technical solutions is mutually contradictory or cannot be implemented, it should be deemed that such a combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0034] As attached Figure 1 -Attached Figure 6 As shown, the present invention provides a visual combustion chamber with body cooling, comprising a combustion chamber body 1, an observation window 2 and a window temperature control structure;

[0035] The combustion chamber body 1 includes an injection assembly mounting wall 11, a cylindrical side wall 12, and a nozzle assembly mounting wall 13, which are arranged in sequence. The injection assembly mounting wall 11, the cylindrical side wall 12, and the nozzle assembly mounting wall 13 enclose a combustion chamber 14. The injection assembly mounting wall 11, the cylindrical side wall 12, and the nozzle assembly mounting wall 13 can be integrally formed and can be fixedly connected to each other using an assembled structure.

[0036] The observation window 2 is provided on the side wall of the cylindrical side wall 12 and is used to observe the flame combustion condition in the combustion chamber 14. Specifically, a camera can be used to continuously observe the flame combustion condition in the combustion chamber 14, which can be used to obtain data for combustion tests and to monitor the combustion condition of the combustion chamber in actual use.

[0037] The window temperature control structure includes a cooling air component 3 and a propellant component 42. The cooling air component 3 includes a cooling air film outlet channel 33. The cooling air film outlet channel 33 is arranged toward the observation window 2 close to the injection component mounting wall 11. The end of the observation window 2 close to the injection component mounting wall 11 is the upstream end, and the end close to the nozzle assembly mounting wall 13 is the upstream end. The cooling air film outlet channel 33 is used to spray a cooling air film from the upstream end of the observation window 2 to the inner wall of the observation window 2 for temperature control. Specifically, the cooling air film is used to directly dissipate heat to the inner wall of the observation window 2 on the one hand, and on the other hand, it can isolate the high-temperature flame in the combustion chamber 14 from the observation window 2, so as to ensure the temperature of the observation window 2, realize effective thermal protection of the observation window 2, and thereby improve the overall structural performance of the combustion chamber. The propellant component 42 includes a cooling air film outlet channel 33 arranged at the cooling air film outlet channel 33. Inside the nozzle channel 33, the propellant film outlet channel 423, along with the cooling air film outlet channel 33 and the observation window 2, is arranged sequentially from the inside out. The propellant film outlet channel 423 is used to eject a propellant film to assist the flame combustion within the combustion chamber 14. It also forms a double-layered film with the cooling air film, assisting the cooling air film in temperature control of the inner wall of the observation window 2. This propellant film not only promotes further flame combustion and improves combustion efficiency, but also forms a double-layered film with the cooling air film, increasing the distance the cooling air film flows along the inner wall of the observation window 2, ensuring effective temperature control of the observation window 2 from the injection assembly mounting wall 11 to the nozzle assembly mounting wall 13. It also isolates the high-temperature flame within the combustion chamber 14 from the cooling air film, further isolating the high-temperature flame within the combustion chamber 14 from the observation window 2. As the propellant film develops downstream, the propellant diffuses toward the center of the combustion chamber 14, promoting flame combustion.

[0038] That is, the visual combustion chamber with body cooling provided by the present invention can significantly reduce the temperature of the observation window 2 on the basis of improving the flame combustion effect in the combustion chamber 14 through the structural design of the cooling gas film outlet channel 33 and the propellant gas film outlet channel 423. On the one hand, it solves the problem that the current observation window 2 is not resistant to high temperatures and is easily damaged by the high temperature in the combustion chamber 14, affecting the overall performance of the combustion chamber. On the other hand, it also solves the problem that the current cooling gas generally uses inert gas that does not participate in the combustion reaction, which causes the inert gas to enter the combustion chamber 14 and affect the flame combustion. Specifically, the cooling air film ejected from the cooling air film outlet channel 33 is used to directly dissipate heat to the inner wall of the observation window 2 on the one hand, and can isolate the high-temperature flame in the combustion chamber 14 from the observation window 2 on the other hand, thereby ensuring the temperature of the observation window 2, achieving effective thermal protection for the observation window 2, and thereby improving the overall structural performance of the combustion chamber body 1; the propellant air film ejected from the propellant air film outlet channel 423 can, on the one hand, promote further combustion of the flame and improve combustion efficiency, and on the other hand, can form a double-layer air film with the cooling air film, that is, it is used to increase the flow distance of the cooling air film along the inner wall surface of the observation window 2, ensure the temperature control effect of the observation window 2 at various locations in the direction from the injection assembly mounting wall 11 to the nozzle assembly mounting wall 13, and can isolate the high-temperature flame in the combustion chamber 14 from the cooling air film, and further isolate the high-temperature flame in the combustion chamber 14 from the observation window 2.

[0039] In one embodiment, an injection assembly mounting groove 111 is provided on the injection assembly mounting wall 11, and an injection panel 4 is provided on the injection assembly mounting groove 111. The injection panel 4 includes a limiting portion 44 and a fitting portion 43 connected to each other, wherein the limiting portion 44 abuts against the end surface of the injection assembly mounting wall 11, and the fitting portion 43 is fitted into the injection assembly mounting groove 111. In addition, the injection panel 4 also includes a fuel nozzle 41 that passes through both ends of the fitting portion 43 and the limiting portion 44. The fuel nozzle 41 communicates with the combustion chamber 14 and the outer wall of the injection panel 4. In addition, a propellant assembly 42 is also provided on the injection panel 4.

[0040] The cooling air component 3 also includes a cooling air cavity 32 provided on the inner wall of the injection component mounting groove 111 and a cooling air inlet 31 provided on the outer wall of the combustion chamber body 1 and communicating with the cooling air cavity 32. The cooling air film outlet channel 33 is communicated with the cooling air cavity 32, wherein the cooling air inlet 31 is used to connect to the cooling air input pipeline to supply air to the cooling air cavity 32, and the cooling air cavity 32 is used to accommodate cooling air and to evenly transport cooling air to the cooling air film outlet channel 33;

[0041] There is a gap between the outer wall end of the interlocking portion 43 and the upstream end face of the observation window 2, and the gap forms the cooling air film outlet channel 33. At this time, the cooling air film outlet channel 33 starts to spray directly from the end face of the observation window 2, so that the cooling air film can flow downstream close to the inner wall face of the observation window 2.

[0042] In this embodiment, the cooling gas film outlet channel 33 does not need to be processed separately, but is formed by the cooperation of the injection panel 4 and the injection component mounting groove 111. This can simplify the processing difficulty and is directly formed after the injection panel 4 is installed in the injection component mounting groove 111. In addition, it can also improve the temperature control effect of the cooling gas film on the injection panel 4.

[0043] In one embodiment, the cooling air cavity 32 includes a circular channel 321 provided in the injection panel 4 and a flare 322 connected to the side wall of the circular channel 321. One side of the flare 322 abuts against the outer wall of the fitting portion 43, and the other side abuts against the upstream end face of the observation window 2. The circular channel 321, the flare 322, the outer wall of the fitting portion 43 and the upstream end face of the observation window 2 are combined to form the cooling air cavity 32. In this embodiment, there is no need to provide a closed cooling air channel in the injection panel 4. An open structure is used for easy processing. The cooling air cavity 32 is directly formed after the observation window 2 and the injection panel 4 are installed. In addition, in this embodiment, the cooling air can also be cooled when it contacts the upstream end face of the observation window 2, further ensuring the temperature control effect of the observation window 2.

[0044] In one embodiment, the propellant assembly 42 further includes a propellant gas cavity 422 disposed within the injection panel 4 and a propellant gas inlet 421 disposed on the outer wall of the injection panel 4 and connected to the propellant gas cavity 422. The propellant gas film outlet channel 423 is connected to the propellant gas cavity 422. The propellant gas inlet 421 is used to connect to a propellant gas input pipeline. After passing through the propellant gas cavity 422, the propellant gas is evenly ejected from the propellant gas film outlet channel 423 to form a uniform gas film.

[0045] In one embodiment, a fuel nozzle 41 is provided in the middle of the injection panel 4, and the propellant gas cavity 422 is arranged around the outer wall of the fuel nozzle 41, so that when there are multiple observation windows 2, one propellant gas cavity 422 can be used to supply gas to multiple propellant gas film outlet channels 423.

[0046] In one embodiment, the cooling gas film outlet channel 33 and the propellant film outlet channel 423 are strip slit channels, and the length of the strip slit channels corresponds to the end surface of the observation window 2, that is, the cooling gas film and the propellant film are both planar films with the same width as the observation window 2, further ensuring the temperature control effect on the observation window 2.

[0047] In one embodiment, the cylindrical side wall 12 is a rectangular cylinder, and the observation windows 2 are provided on the three side walls of the rectangular cylinder, and a temperature measuring hole 122 is provided on the side wall of another cylindrical side wall 12. In this embodiment, the three observation windows 2 enable observation of the flame combustion condition in the combustion chamber 14 from multiple directions, and the other side wall without the observation window 2 is provided with the temperature measuring hole 122 for installing a temperature sensor, which can avoid the double-layer air film affecting the temperature measurement accuracy of the temperature sensor and ensure the accuracy of the temperature measurement. Preferably, a plurality of temperature measuring holes 122 are arranged at equal intervals along the direction from the injection assembly mounting wall 11 to the nozzle assembly mounting wall 13, so as to monitor the temperature of different positions of the flame.

[0048] In one embodiment, the visual combustion chamber with body cooling further includes a water cooling structure 6 provided on the combustion chamber body 1;

[0049] The water-cooling structure 6 includes a water-cooling liquid inlet 61 and a water-cooling liquid outlet 63 arranged on the outer wall of the combustion chamber body 1, and also includes a water-cooling channel 62 arranged inside the combustion chamber body 1 to connect the water-cooling liquid inlet 61 and the water-cooling liquid outlet 63. The water-cooling liquid inlet 61 and the water-cooling liquid outlet 63 are respectively connected to the coolant input pipe and the coolant output pipe, and the water-cooling channel 62 is used to dissipate heat to the injection assembly mounting wall 11, the cylindrical side wall 12 and the nozzle assembly mounting wall 13 to ensure the overall structural stability of the combustion chamber body 1. Preferably, the water-cooling channel 52 is provided on the injection assembly mounting wall 11, the cylindrical side wall 12 and the nozzle assembly mounting wall 13, and multiple water-cooling liquid outlets 63 can also be provided.

[0050] In one embodiment, the visual combustion chamber with body cooling further includes a nozzle assembly 5 arranged on the nozzle assembly mounting wall 13, and the nozzle assembly 5 is used to spray flames. Preferably, a nozzle mounting groove 131 is provided on the nozzle assembly mounting wall 13, and the nozzle assembly 5 is arranged on the nozzle mounting groove 131.

[0051] In one embodiment, a window mounting groove 121 for mounting the observation window 2 is provided on the cylindrical side wall 12, and a window cover 15 is removably provided on the outer wall of the cylindrical side wall 12. Preferably, the window mounting groove 121 is a stepped groove, and the observation window 2 is stepped corresponding to the stepped groove, and the window cover 15 is used to lock the observation window 2 in the window mounting groove 121. Preferably, asbestos gaskets 7 are provided between the step of the window mounting groove 121 and the observation window 2, and between the window cover 15 and the observation window 2, and a sealing ring 8 is also provided between the window cover 15 and the observation window 2, thereby achieving sealing between the window mounting groove 121 and the observation window 2.

[0052] The present invention also provides a rocket engine, comprising the above-mentioned visualized combustion chamber with body cooling.

[0053] The above description is merely an embodiment and does not limit the present invention in any way. Any person skilled in the art can, without departing from the scope of the technical solution of the present invention, make many possible changes, modifications, or modifications to the technical solution of the present invention into equivalent embodiments with equivalent changes using the technical content disclosed above. Therefore, any simple modifications, equivalent changes, and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the scope of protection of the technical solution of the present invention.

Claims

1. A visual combustion chamber with body cooling, characterized in that: It includes a combustion chamber body (1), an observation window (2) and a window temperature control structure; The combustion chamber body (1) comprises an injection assembly mounting wall (11), a cylindrical side wall (12) and a nozzle assembly mounting wall (13) which are arranged in sequence, wherein the injection assembly mounting wall (11), the cylindrical side wall (12) and the nozzle assembly mounting wall (13) enclose a combustion chamber (14); The observation window (2) is provided on the side wall of the cylindrical side wall (12) and is used for observing the combustion condition of the flame in the combustion chamber (14); The window temperature control structure includes a cooling air component (3) and a propellant component (42), the cooling air component (3) includes a cooling air film outlet channel (33), the cooling air film outlet channel (33) is arranged toward the observation window (2) near one end of the injection component installation wall (11), and is used to spray a cooling air film from the upstream end of the observation window (2) to control the temperature of the inner wall of the observation window (2), the propellant component (42) includes a propellant air film outlet channel (423) arranged on the inner side of the cooling air film outlet channel (33), the propellant air film outlet channel (423) is used to spray a propellant air film to assist the flame combustion in the combustion chamber (14), and form a double-layer air film with the cooling air film to assist the cooling air film in controlling the temperature of the inner wall of the observation window (2); The injection assembly installation wall (11) is provided with an injection assembly installation groove (111), and the injection assembly installation groove (111) is provided with an injection panel (4); The cooling air component (3) further comprises a cooling air cavity (32) provided on the inner wall of the injection component mounting groove (111) and a cooling air inlet (31) provided on the outer wall of the combustion chamber body (1) and communicating with the cooling air cavity (32); the cooling air cavity (32) is communicated with the cooling air film outlet channel (33); The injection panel (4) includes an inserting portion (43) inserted into the injection assembly mounting groove (111), and an outer wall end portion of the inserting portion (43) is spaced from an upstream end surface of the observation window (2), the space forming the cooling air film outlet channel (33); The cooling air cavity (32) includes a circular channel (321) provided in the injection panel (4) and a flared opening (322) communicating with the side wall of the circular channel (321); one side of the flared opening (322) abuts against the outer wall of the fitting portion (43), and the other side abuts against the upstream end face of the observation window (2); the circular channel (321), the flared opening (322), the outer wall of the fitting portion (43), and the upstream end face of the observation window (2) enclose and form the cooling air cavity (32); The propellant assembly (42) further includes a propellant gas cavity (422) disposed within the injection panel (4) and a propellant gas inlet (421) disposed on the outer wall of the injection panel (4) and communicating with the propellant gas cavity (422); the propellant gas film outlet channel (423) is communicated with the propellant gas cavity (422).

2. The visualized combustion chamber with body cooling according to claim 1, characterized in that: A fuel nozzle (41) is provided in the middle of the injection panel (4), and the propulsion gas cavity (422) is arranged around the outer wall of the fuel nozzle (41).

3. The visualized combustion chamber with body cooling according to claim 1 or 2, characterized in that: The cooling air film outlet channel (33) and the propellant air film outlet channel (423) are strip-shaped slit channels, and the length of the strip-shaped slit channels corresponds to the end surface of the observation window (2).

4. The visualized combustion chamber with body cooling according to claim 1 or 2, characterized in that: The cylindrical side wall (12) is a rectangular cylinder, and the observation windows (2) are provided on three side walls of the rectangular cylinder, and a temperature measuring hole (122) is provided on another side wall of the cylindrical side wall (12).

5. The visualized combustion chamber with body cooling according to claim 1 or 2, characterized in that: It also includes a water cooling structure (6) provided on the combustion chamber body (1); The water cooling structure (6) includes a water cooling liquid inlet (61) and a water cooling liquid outlet (63) arranged on the outer wall of the combustion chamber body (1), and also includes a water cooling channel (62) arranged inside the combustion chamber body (1) and communicating with the water cooling liquid inlet (61) and the water cooling liquid outlet (63).

6. The visualized combustion chamber with body cooling according to claim 1 or 2, characterized in that: It also includes a nozzle assembly (5) arranged on the nozzle assembly mounting wall (13).

7. A rocket engine, characterized in that: The utility model comprises a visualized combustion chamber with body cooling as described in any one of claims 1 to 6.

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