Thrust chamber, power system and aircraft

Abstract

The invention provides a thrust chamber, a power system and an aircraft. The thrust chamber comprises a combustion body which is cylindrical and is provided with a throat part, and a combustion chamber is defined by a first part, located on the upstream of the throat part, of the combustion body; the first annular side wall is connected with the combustion body and located at the end, away from the throat part, of the combustion chamber. Wherein the combustion body is provided with a first cooling channel, and the first cooling channel extends from the lower end of the combustion body to the upper end of the combustion body; the first annular side wall is provided with a plurality of first cooling holes communicating with the first cooling channel, the multiple first cooling holes are distributed in the circumferential direction of the combustion body and extend in the axial direction of the combustion body, and the first cooling holes communicate with the combustion chamber and are close to the inner wall of the combustion chamber. Coolant enters the combustion chamber from the upstream through the first cooling channel and the first cooling hole in sequence, the coolant is dispersed along the inner wall of the combustion chamber, the temperature near the inner wall of the combustion chamber can be reduced, and the wall face of the combustion chamber is protected.

Description

Technical Field

[0001] The present application relates to the field of aerospace technology, and in particular, to a thrust chamber, a power system and an aircraft. Background Art

[0002] In liquid rocket engines, there are many factors that affect the thrust chamber of liquid rocket propellant, and the type of injector is one of the important factors. The most common types of injectors can be divided into pintle injectors, centrifugal injectors and direct current injectors.

[0003] For the liquid oxygen-kerosene pintle thrust chamber, the spray mixing pattern of the pintle injector forms an annular recirculation zone. The annular flow field makes the combustion stability and combustion performance of the pintle thrust chamber significantly better than traditional direct current injectors and centrifugal injectors.

[0004] During the operation of the pintle thrust chamber, if the thermal protection design is unreasonable, the annular flow field may cause the high-temperature gas to flow back and burn the pintle, and at the same time burn the bottom of the kerosene chamber; if the wall cooling structure is not designed properly, it may cause wall ablation; at the same time, the heat flux density near the throat is the largest, and ablation is prone to occur during the test run. Therefore, the technical difficulty and key point of the pintle thrust chamber is how to protect the thrust chamber and prevent it from ablation. Summary of the invention

[0005] In view of the shortcomings of the existing methods, the present application proposes a thrust chamber, a power system and an aircraft to solve the technical problems of insufficient thrust chamber cooling and easy ablation in the related technology.

[0006] In a first aspect, an embodiment of the present application provides a thrust chamber, comprising: The combustion body is cylindrical and has a throat, and a first portion of the combustion body located upstream of the throat forms a combustion chamber; A first annular side wall connected to the combustion body and located at an end of the combustion chamber away from the throat; Wherein: a first cooling channel is provided on the combustion body, and the first cooling channel extends from the lower end of the combustion body to the upper end of the combustion body; The first annular side wall is provided with a plurality of first cooling holes connected with the first cooling channel. The plurality of first cooling holes are distributed along the circumference of the combustion body and each extends along the axial direction of the combustion body. The first cooling holes are connected with the combustion chamber and are arranged close to the inner wall of the combustion chamber.

[0007] Optionally, a second cooling hole connected to the first cooling channel is provided on the combustion body, the second cooling hole is connected to the combustion chamber, and is located at one end of the combustion chamber close to the throat.

[0008] Optionally, the number of the first cooling channel and the number of the second cooling holes are respectively plural; The thrust chamber includes at least one of the following: A plurality of second cooling holes are distributed along the circumference of the combustion body; Each first cooling channel is arranged corresponding to at least one second cooling hole.

[0009] Optionally, the number of the first cooling passages is plural, and the second portion of the combustion body located downstream of the throat serves as a nozzle; The thrust chamber includes at least one of the following: A plurality of first cooling channels are distributed along the circumference of the combustion body; A first liquid collecting ring is arranged outside the nozzle, and the first liquid collecting ring has a first annular cavity extending along the circumference of the nozzle and a first inlet communicating with the first annular cavity, and the lower ends of the plurality of first cooling channels are respectively communicated with the first annular cavity.

[0010] Optionally, the thrust chamber further comprises an injector, the injector comprising a second liquid collecting ring connected to the combustion body and the first annular side wall; The second liquid collecting ring has a liquid collecting cavity communicated with the first cooling channel; The combustion body, the first annular side wall and the second liquid collecting ring form a second cooling channel communicating with the liquid collecting cavity; The second cooling channel is in communication with the first cooling hole.

[0011] Optionally, a plurality of third cooling holes are further provided on the first annular side wall; The third cooling hole is located on a side of the first cooling hole away from the throat, and is communicated with the second cooling channel and the combustion chamber respectively; The plurality of third cooling holes are distributed along the circumference of the combustion body, and each of the third cooling holes extends along a direction perpendicular to the axis of the combustion body.

[0012] Optionally, a plurality of fourth cooling holes are further provided on the first annular side wall; The fourth cooling hole is located between the first cooling hole and the third cooling hole, and is communicated with the second cooling channel and the combustion chamber respectively; A plurality of fourth cooling holes are distributed along the circumference of the combustion body, and each of the fourth cooling holes extends along a direction intersecting with the axis of the combustion body and not perpendicular thereto.

[0013] Optionally, there are multiple second cooling channels, which are distributed along the circumference of the combustion body and are connected to the multiple first cooling holes in a one-to-one correspondence; or, The second cooling channel is an annular channel extending along the circumference of the combustion body, and the second cooling channel is communicated with the plurality of first cooling holes.

[0014] In a second aspect, an embodiment of the present application provides a power system, comprising: a thrust chamber as described above.

[0015] In a third aspect, an embodiment of the present application provides an aircraft, comprising: a power system as described above.

[0016] The beneficial technical effects brought about by the technical solution provided by the embodiment of the present application include: In the embodiment of the present application, the combustion body of the thrust chamber is cylindrical and has a throat. The first part of the combustion body located upstream of the throat forms a combustion chamber, and the propellant is atomized, mixed and burned in the combustion chamber. The first annular side wall of the thrust chamber is connected to the combustion body and is located at one end of the combustion chamber away from the throat, that is, located upstream of the combustion chamber.

[0017] The combustion body is provided with a first cooling channel extending from the lower end of the combustion body to the upper end of the combustion body. The coolant flows in the first cooling channel to cool the wall surface of the combustion body. The first annular side wall is provided with a plurality of first cooling holes connected to the first cooling channel, and the plurality of first cooling holes are connected to the combustion chamber. The coolant in the first cooling channel can enter the combustion chamber from upstream through the first cooling holes.

[0018] Since the plurality of first cooling holes are distributed along the circumference of the combustion body and are arranged near the inner wall of the combustion chamber, when the coolant enters the combustion chamber through the plurality of first cooling holes, the coolant is distributed around the combustion chamber and dispersed along the inner wall of the combustion chamber, thereby reducing the temperature near the circumferential inner wall of the combustion chamber, fully cooling the inner wall of the combustion chamber, and placing the inner wall of the combustion chamber in a low mixing ratio and low residual oxygen coefficient atmosphere, thereby protecting the inner wall of the combustion chamber and preventing it from being ablated. By providing the first cooling channel and the plurality of first cooling holes, the wall surface of the thrust chamber can be protected and ablation of the wall surface of the thrust chamber can be prevented.

[0019] Additional aspects and advantages of the present application will be partially given in the following description, which will become apparent from the following description, or will be understood through the practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The above and / or additional aspects and advantages of the present application will become apparent and easily understood from the following description of the embodiments in conjunction with the accompanying drawings, in which: Figure 1 A schematic diagram of a top view of a thrust chamber provided in an embodiment of the present application; Figure 2 for Figure 1 Schematic diagram of the cross-sectional structure of the middle thrust chamber along the AA direction; Figure 3 for Figure 2 A partial enlarged structural diagram of the middle thrust chamber; Figure 4 for Figure 2 Another partial enlarged structural diagram of the middle thrust chamber; Figure 5 for Figure 2 Another partial enlarged structural diagram of the middle thrust chamber.

[0021] Reference numerals: 100 - thrust chamber; 10- Combustion body; 11-throat; 12-combustion chamber; 13-first cooling channel; 14-second cooling hole; 15-nozzle; 16-combustion outer wall; 17-combustion inner wall; 20-a first annular side wall; 21-first cooling hole; 22-third cooling hole; 23-fourth cooling hole; 30-first liquid collecting ring; 31-first annular cavity; 32-first inlet; 40-injector; 41-second liquid collecting ring; 42-liquid collecting cavity; 43-pin plug head; 44-injection part; 45-avoidance hole; 46-second inlet; 47-oxidant channel; 48-injection hole; 50- second cooling channel; 51-first sub-channel; 52-second sub-channel; 60- second annular side wall; 70-Annular seam. DETAILED DESCRIPTION

[0022] The embodiments of the present application are described below in conjunction with the drawings in the present application. It should be understood that the implementation methods described below in conjunction with the drawings are exemplary descriptions for explaining the technical solutions of the embodiments of the present application and do not constitute a limitation on the technical solutions of the embodiments of the present application.

[0023] Those skilled in the art will appreciate that, unless specifically stated, the "said" and "the" used herein may also include plural forms. It should be further understood that the term "including" used in the specification of the present application refers to the presence of the features, integers and / or components, but does not exclude the implementation of other features, information, data, steps, operations, elements, components and / or combinations thereof supported by the technical field. The term "and / or" used herein refers to at least one of the items defined by the term, for example, "A and / or B" can be implemented as "A", or as "B", or as "A and B".

[0024] In order to make the objectives, technical solutions and advantages of the present application clearer, the implementation methods of the present application will be further described in detail below with reference to the accompanying drawings.

[0025] The thrust chamber, power system and aircraft provided in the present application are intended to solve the technical problem in the related art that the needle bolt, the bottom of the kerosene chamber, the wall surface, the throat and the like of the thrust chamber are prone to ablation, so as to reliably cool the thrust chamber and thus protect the thrust chamber and prevent it from ablation.

[0026] The following is a detailed description of the technical solution of the present application and how the technical solution of the present application solves the above technical problems with specific embodiments. It should be noted that the following implementations can refer to, draw on or combine with each other, and the same terms, similar features and similar implementation steps in different implementations will not be described repeatedly.

[0027] The present application embodiment provides a thrust chamber 100, and the structural schematic diagram of the thrust chamber 100 is as follows Figures 1 to 3 As shown, it includes: a combustion body 10 and a first annular side wall 20.

[0028] The combustion body 10 is cylindrical and has a throat 11 . The first part of the combustion body 10 located upstream of the throat 11 forms a combustion chamber 12 . The first annular side wall 20 is connected to the combustion body 10 and is located at one end of the combustion chamber 12 away from the throat 11 .

[0029] The combustion body 10 is provided with a first cooling channel 13, and the first cooling channel 13 extends from the lower end of the combustion body 10 to the upper end of the combustion body 10. The first annular side wall 20 is provided with a plurality of first cooling holes 21 connected to the first cooling channel 13, and the plurality of first cooling holes 21 are distributed along the circumference of the combustion body 10, and each of the first cooling holes 21 extends along the axial direction of the combustion body 10, and the first cooling holes 21 are connected to the combustion chamber 12 and are arranged close to the inner wall of the combustion chamber 12.

[0030] In the embodiment of the present application, the combustion body 10 of the thrust chamber 100 is cylindrical, and the combustion body 10 has a throat 11. Along the flow direction of the propellant in the thrust chamber 100, the combustion body 10 includes a first part located upstream of the throat 11 and a second part located downstream of the throat 11. The first part of the combustion body 10 located upstream of the throat 11 encloses the combustion chamber 12, and the propellant is atomized, mixed and burned in the combustion chamber 12. The first annular side wall 20 of the thrust chamber 100 is connected to the combustion body 10 and is located at one end of the combustion chamber 12 away from the throat 11, that is, located upstream of the combustion chamber 12.

[0031] The combustion body 10 is provided with a first cooling channel 13 extending from the lower end of the combustion body 10 to the upper end of the combustion body 10. The coolant flows in the first cooling channel 13 to cool the wall surface of the combustion body 10. The first annular side wall 20 is provided with a plurality of first cooling holes 21 connected to the first cooling channel 13, and the plurality of first cooling holes 21 are connected to the combustion chamber 12. The coolant in the first cooling channel 13 can enter the combustion chamber 12 from upstream through the first cooling holes 21.

[0032] Since the plurality of first cooling holes 21 are distributed along the circumference of the combustion body 10 and are arranged near the inner wall of the combustion chamber 12, when the coolant enters the combustion chamber 12 through the plurality of first cooling holes 21, the coolant is distributed around the combustion chamber 12 and dispersed along the inner wall of the combustion chamber 12, thereby reducing the temperature near the circumferential inner wall of the combustion chamber 12, fully cooling the inner wall of the combustion chamber 12, and making the inner wall of the combustion chamber 12 near the inner wall of the combustion chamber 12 in a low mixing ratio and low residual oxygen coefficient atmosphere, thereby protecting the inner wall of the combustion chamber 12 from ablation. By providing the first cooling channel 13 and the plurality of first cooling holes 21, the wall surface of the thrust chamber 100 can be protected to prevent ablation of the wall surface of the thrust chamber 100.

[0033] Optionally, in the embodiment of the present application, a plurality of first cooling holes 21 are evenly spaced and distributed along the circumference of the combustion body 10. Such an arrangement can improve the uniformity of the coolant cooling the inner wall of the combustion chamber 12, and ensure the uniformity and consistency of the temperature distribution on the circumferential wall of the combustion chamber 12. The axis of the first cooling hole 21 is parallel to the axis L of the combustion body 10, and the first cooling hole 21 serves as an axial edge cooling hole.

[0034] Optionally, in the embodiment of the present application, there are multiple first cooling channels 13 ; the multiple first cooling channels 13 are distributed along the circumference of the combustion body 10 .

[0035] In the embodiment of the present application, the plurality of first cooling channels 13 are independent of each other and do not interfere with each other. The coolant flows in the plurality of first cooling channels 13 to cool the wall surface of the thrust chamber 100 , thereby improving the cooling effect and preventing the wall surface of the thrust chamber 100 from being ablated.

[0036] Optionally, in the embodiment of the present application, a plurality of first cooling channels 13 are evenly spaced and distributed along the circumference of the combustion body 10. Such an arrangement can improve the uniformity and consistency of the coolant cooling the wall surface of the thrust chamber 100.

[0037] Alternatively, if Figure 2 and Figure 4 As shown, in the embodiment of the present application, a second cooling hole 14 connected to the first cooling channel 13 is provided on the combustion body 10. The second cooling hole 14 is connected to the combustion chamber 12 and is located at one end of the combustion chamber 12 close to the throat 11.

[0038] In the embodiment of the present application, the second cooling hole 14 is communicated with the first cooling channel 13 and the combustion chamber 12 respectively, and the second cooling hole 14 is located at one end of the combustion chamber 12 close to the throat 11, that is, located upstream of the throat 11. In this way, the coolant can enter the combustion chamber 12 through the first cooling channel 13 and the second cooling hole 14 in sequence, and spray near the throat 11, protecting the upstream and downstream of the throat 11, and preventing the throat 11 of the thrust chamber 100 from being ablated.

[0039] Alternatively, if Figure 2 and Figure 4 As shown, in the embodiment of the present application, there are multiple second cooling holes 14; the multiple second cooling holes 14 are distributed along the circumference of the combustion body 10.

[0040] In the embodiment of the present application, a plurality of second cooling holes 14 are distributed along the circumference of the combustion body 10 and are located upstream of the throat 11. In this way, the coolant in the first cooling channel 13 can be sprayed into the combustion chamber 12 from the circumference upstream of the throat 11 through the plurality of second cooling holes 14, forming a liquid film at the throat 11 or its vicinity (including the upstream and downstream near the throat 11), which can better cool the throat 11 and its upstream and downstream, reduce the temperature of the throat 11 and its upstream and downstream walls, and protect the throat 11 and its upstream and downstream walls from being ablated. The second cooling hole 14 is located at one end of the combustion chamber 12 close to the throat 11 and upstream of the throat 11, and the second cooling hole 14 serves as a throat liquid film cooling hole.

[0041] Optionally, in the embodiment of the present application, the plurality of first cooling channels 13 are connected to the plurality of second cooling holes 14 in a one-to-one correspondence. That is, each first cooling channel 13 is provided with a corresponding second cooling hole 14. The coolant in the plurality of first cooling channels 13 is ejected through a second cooling hole 14 correspondingly connected to each first cooling channel 13, so as to cool the throat 11 and the wall surface near it.

[0042] Of course, in other optional embodiments of the present application, at least one first cooling channel 13 among the plurality of first cooling channels 13 can be connected to two or more second cooling holes 14 according to actual needs. Optionally, the two or more second cooling holes 14 correspondingly connected to one first cooling channel 13 can be reasonably arranged according to actual needs, such as distributed along the extension direction of the first cooling channel 13, or distributed perpendicular to the extension direction of the first cooling channel 13, or distributed in other regular or irregular distribution modes.

[0043] Alternatively, if Figure 2 and Figure 5As shown, in the embodiment of the present application, the second part of the combustion body 10 located downstream of the throat 11 serves as the nozzle 15; a first liquid collecting ring 30 is provided on the outer side of the nozzle 15, and the first liquid collecting ring 30 has a first annular cavity 31 extending along the circumference of the nozzle 15 and a first inlet 32 ​​connected to the first annular cavity 31, and the lower ends of the plurality of first cooling channels 13 are respectively connected to the first annular cavity 31.

[0044] In the embodiment of the present application, the radial dimension of the nozzle 15 gradually increases along the direction from the throat 11 to the lower end of the combustion body 10. The nozzle 15 is used to convert the thermal energy of the combustion products into kinetic energy to generate a high-speed jet. The first liquid collecting ring 30 is arranged on the outside of the nozzle 15 and has a first annular cavity 31 and a first inlet 32 ​​that are connected. The first annular cavity 31 extends along the circumference of the nozzle 15 and is connected to the lower ends of the plurality of first cooling channels 13. In this way, the coolant can enter and converge in the first annular cavity 31 through the first inlet 32, and then enter the plurality of first cooling channels 13 and the plurality of second cooling holes 14 and the plurality of first cooling holes 21 that are connected to the plurality of first cooling channels 13, so as to realize the cooling and protection of the wall surface of the thrust chamber 100 and prevent it from being ablated.

[0045] Alternatively, if Figures 2 to 5 As shown, in the embodiment of the present application, the combustion body 10 includes a combustion outer wall 16 and a combustion inner wall 17, and the combustion outer wall 16 is sleeved on the outer side of the combustion inner wall 17, that is, it is sleeved on the side of the combustion inner wall 17 away from the axis of the combustion body 10. The combustion outer wall 16 and the combustion inner wall 17 are connected and enclose a plurality of first cooling channels 13. The first liquid collecting ring 30 is connected to the combustion outer wall 16 and encloses a first annular cavity 31. A plurality of second cooling holes 14 are spaced apart on the combustion inner wall 17 around the axis L of the combustion body 10. The first annular side wall 20 is connected to the combustion inner wall 17 and is located at the upper end of the combustion inner wall 17.

[0046] Alternatively, if Figure 2 and Figure 3 As shown, the thrust chamber 100 further includes an injector 40, which includes a second liquid collecting ring 41 connected to the combustion body 10 and the first annular side wall 20; the second liquid collecting ring 41 has a liquid collecting cavity 42 connected to the first cooling channel 13. The combustion body 10, the first annular side wall 20 and the second liquid collecting ring 41 enclose a second cooling channel 50 connected to the liquid collecting cavity 42; the second cooling channel 50 is connected to the first cooling hole 21.

[0047] In the embodiment of the present application, the coolant can enter the combustion chamber 12 through the first cooling channel 13, the liquid collecting cavity 42, the second cooling channel 50, and the first cooling hole 21 which are connected in sequence to cool and protect the inner wall of the combustion chamber 12 to prevent it from being ablated.

[0048] Optionally, in the embodiment of the present application, the injector 40 includes but is not limited to a pintle injector.

[0049] Alternatively, if Figures 2 to 5 As shown, in the embodiment of the present application, the combustion outer wall 16 and the combustion inner wall 17 enclose the first cooling channel 13, and the combustion outer wall 16 and the combustion inner wall 17 are respectively connected to the bottom wall of the second liquid collecting ring 41, so that the first cooling channel 13 is connected to the liquid collecting cavity 42. The combustion inner wall 17, the bottom wall of the second liquid collecting ring 41, and the first annular side wall 20 enclose the second cooling channel 50 connected to the liquid collecting cavity 42. The first cooling hole 21 on the first annular side wall 20 is connected to the second cooling channel 50.

[0050] In some optional embodiments of the present application, such as Figure 3 As shown, the second cooling channel 50 includes a first sub-channel 51 and a second sub-channel 52 , the liquid collecting cavity 42 is connected with the second sub-channel 52 through the first sub-channel 51 , and the second sub-channel 52 is connected with the first cooling hole 21 .

[0051] Optionally, in the embodiment of the present application, there are multiple first sub-channels 51 , and the multiple first sub-channels 51 are distributed in sequence along the circumference of the combustion body 10 , and the liquid collecting cavity 42 is connected to the multiple first sub-channels 51 .

[0052] Alternatively, if Figure 3 As shown, in the embodiment of the present application, the first sub-channel 51 extends in a direction parallel to the axis of the combustion body 10 .

[0053] Optionally, in the embodiment of the present application, the second sub-channel 52 is an annular channel extending along the circumference of the combustion body 10. The plurality of first sub-channels 51 are each connected to the second sub-channel 52. The second sub-channel 52 is connected to the plurality of first cooling holes 21.

[0054] In some other optional embodiments of the present application, it can also be arranged according to actual needs: the number of second cooling channels 50 is multiple, the multiple second cooling channels 50 are distributed along the circumference of the combustion body 10, the multiple second cooling channels 50 are connected to the liquid collecting cavity 42, and are connected to the multiple first cooling holes 21 one by one; or, the second cooling channel 50 is an annular channel extending along the circumference of the combustion body 10, the second cooling channel 50 is connected to the liquid collecting cavity 42, and is connected to the multiple first cooling holes 21.

[0055] Alternatively, if Figure 3 As shown, in the embodiment of the present application, a plurality of third cooling holes 22 are further provided on the first annular side wall 20; the third cooling holes 22 are located on the side of the first cooling hole 21 away from the throat 11 (i.e., arranged close to the second liquid collecting ring 41), and are respectively connected to the second cooling channel 50 and the combustion chamber 12. The coolant in the second cooling channel 50 can be sprayed into the combustion chamber 12 through the third cooling holes 22.

[0056] Alternatively, if Figure 3 As shown, in the embodiment of the present application, a plurality of third cooling holes 22 are distributed along the circumference of the combustion body 10 , and each of the third cooling holes 22 extends in a direction perpendicular to the axis L of the combustion body 10 .

[0057] In the embodiment of the present application, a plurality of third cooling holes 22 are distributed at intervals along the circumference of the combustion body 10, and each extends radially along the combustion body 10. The coolant can be sprayed radially toward the center from the periphery of the combustion body 10 through the plurality of third cooling holes 22 to cool and protect the bottom of the second liquid collecting ring 41 to prevent it from being ablated. The axis of the third cooling hole 22 is perpendicular to the axis L of the combustion body 10, and the third cooling hole 22 serves as a radial edge cooling hole.

[0058] Alternatively, if Figure 2 and Figure 3 As shown, in the embodiment of the present application, the thrust chamber 100 further includes a second annular side wall 60, which is connected to the bottom wall of the second liquid collecting ring 41, and the first annular side wall 20 is sleeved on the outside of the second annular side wall 60, and a recirculation zone is formed between the first annular side wall 20 and the second annular side wall 60. The third cooling hole 22 is arranged on the side of the first annular side wall 20 close to the bottom wall of the second liquid collecting ring 41, and extends radially along the combustion body 10. The coolant is sprayed to the bottom of the second liquid collecting ring 41 and the recirculation zone through the third cooling hole 22. The mist fan sprayed from the third cooling hole 22 can reduce the mixing ratio near the inner bottom of the liquid collecting cavity 42, reduce the combustion temperature of the inner bottom of the liquid collecting cavity 42, and reduce the mixing ratio of the recirculation zone, reduce the temperature of the recirculation zone, effectively reduce the gas reflow temperature, and protect the inner bottom of the liquid collecting cavity 42 from being ablated.

[0059] Alternatively, if Figure 3 As shown, in the embodiment of the present application, a plurality of fourth cooling holes 23 are further provided on the first annular side wall 20; the fourth cooling holes 23 are located between the first cooling holes 21 and the third cooling holes 22, and are respectively connected to the second cooling channel 50 and the combustion chamber 12. The coolant in the second cooling channel 50 can be sprayed into the combustion chamber 12 through the fourth cooling holes 23.

[0060] Alternatively, if Figure 3 As shown, in the embodiment of the present application, a plurality of fourth cooling holes 23 are distributed along the circumference of the combustion body 10 , and each of the fourth cooling holes 23 extends in a direction that intersects with the axis L of the combustion body 10 and is not perpendicular to the axis L of the combustion body 10 .

[0061] In the embodiment of the present application, a plurality of fourth cooling holes 23 are distributed at intervals along the circumference of the combustion body 10, and each extends in an oblique direction that intersects but is not perpendicular to the axis L of the combustion body 10. The coolant can be sprayed obliquely from the periphery of the combustion body 10 toward the center through the plurality of fourth cooling holes 23, which is used to reduce the mixing ratio near the needle plug head 43 of the injector 40, and can effectively reduce the temperature near the needle plug head 43, protecting the needle plug head 43 from being ablated. The axis of the fourth cooling hole 23 is inclined relative to the axis L of the combustion body 10, and the coolant sprayed from the fourth cooling hole 23 is used to cool the needle plug head 43. Therefore, the fourth cooling hole 23 serves as an oblique cooling needle plug hole.

[0062] Alternatively, if Figure 2 and Figure 3 As shown, in the embodiment of the present application, the axis of the fourth cooling hole 23 is inclined at an angle relative to the axis L of the combustion body 10 to ensure that the coolant sprayed from the fourth cooling hole 23 is sprayed on the needle bolt head 43, near the needle bolt head 43, and below the needle bolt head 43 and close to the needle bolt head 43, so as to cool and protect the needle bolt head 43 and prevent it from being burned.

[0063] Alternatively, if Figure 3 As shown, in the embodiment of the present application, the plurality of third cooling holes 22 are in communication with the second sub-channel 52 of the second cooling channel 50. The plurality of fourth cooling holes 23 are in communication with the second sub-channel 52. Of course, in other optional embodiments of the present application, if the number of the second cooling channels 50 is a plurality distributed along the circumference of the combustion body 10, the plurality of third cooling holes 22 can be arranged to be in communication with the plurality of second cooling channels 50 in a one-to-one correspondence, and the plurality of fourth cooling holes 23 can be arranged to be in communication with the plurality of second cooling channels 50 in a one-to-one correspondence, according to actual conditions.

[0064] Alternatively, if Figure 3 As shown, in the embodiment of the present application, the injector 40 includes an injection portion 44, which is connected to the inner side of the top wall of the second liquid collecting ring 41, and a avoidance hole 45 communicating with the liquid collecting cavity 42 is provided on the bottom wall of the second liquid collecting ring 41, and a second annular side wall 60 is provided at the avoidance hole 45 on the bottom wall of the second liquid collecting ring 41, and the second annular side wall 60 has a receiving cavity communicating with the avoidance hole 45. The injection portion 44 extends into the combustion chamber 12 after passing through the liquid collecting cavity 42, the avoidance hole 45 and the receiving cavity of the second annular side wall 60 in sequence from the inner side of the top wall of the second liquid collecting ring 41.

[0065] Alternatively, if Figure 2 and Figure 3 As shown, in the embodiment of the present application, an annular gap 70 is formed between the injection portion 44 and the bottom wall of the second liquid collecting ring 41 and the inner wall of the second annular side wall 60 . One end of the annular gap 70 is connected to the liquid collecting cavity 42 , and the other end is connected to the combustion chamber 12 .

[0066] Optionally, in the embodiment of the present application, the propellant includes an oxidizer and a fuel. The oxidizer includes but is not limited to liquid oxygen. The fuel includes but is not limited to kerosene.

[0067] Optionally, in the embodiment of the present application, kerosene can be used as both a fuel and a coolant for the thrust chamber 100. Specifically, Figures 2 to 5 As shown, kerosene can enter the first annular cavity 31 (the first annular cavity 31 serves as a kerosene annular cavity) from the first inlet 32 ​​(the first inlet 32 ​​serves as a kerosene inlet), and then enter the plurality of first cooling channels 13 (the first cooling channels 13 serve as regeneration cooling channels). Then, a small portion of the kerosene flowing through the plurality of first cooling channels 13 (for example, an amount accounting for 8% of the total kerosene flow) is ejected through the plurality of second cooling holes 14 (i.e., throat liquid film cooling holes) to cool and protect the upstream and downstream of the throat 11 of the thrust chamber 100, and prevent the wall surface near the throat 11 from being ablated.

[0068] Next, the remaining kerosene in the plurality of first cooling channels 13 (for example, 92% of the total kerosene flow) flows into the liquid collecting chamber 42. A portion of the kerosene in the liquid collecting chamber 42 (for example, 15% of the total kerosene flow) flows into the second cooling channel 50, and the remaining portion of the kerosene in the liquid collecting chamber 42 enters the combustion chamber 12 through the annular slit 70.

[0069] A portion of the kerosene in the second cooling channel 50 (for example, 5% of the total kerosene flow) is sprayed into the combustion chamber 12 through a plurality of first cooling holes 21 (i.e., axial edge cooling holes) to cool and protect the inner wall of the combustion chamber 12 and prevent the inner wall of the combustion chamber 12 from being burned; another portion (for example, 5% of the total kerosene flow) is sprayed into the combustion chamber 12 through a plurality of third cooling holes 22 (i.e., radial edge cooling holes) to cool the bottom wall and the recirculation zone of the second liquid collecting ring 41, effectively reducing the temperature of the recirculation zone and protecting the bottom of the second liquid collecting ring 41 from being burned; and another portion (for example, 5% of the total kerosene flow) is sprayed into the combustion chamber 12 through a plurality of fourth cooling holes 23 (i.e., oblique cooling pintle holes) to cool and protect the pintle head and prevent the pintle head from being burned.

[0070] The thrust chamber 100 of the embodiment of the present application has four types of cooling holes for protecting the thrust chamber from being ablated. Specifically, the radial edge cooling holes (i.e., the third cooling holes 22) mainly function to reduce the mixing ratio in the recirculation zone, reduce the combustion temperature at the bottom of the liquid collecting cavity, and protect the bottom of the second liquid collecting ring from being ablated; the axial edge cooling holes (i.e., the first cooling holes 21) mainly function to protect the combustion chamber wall surface at a low mixing ratio and low residual oxygen coefficient, reduce the temperature near the wall surface, and protect the combustion chamber wall surface from being ablated; the oblique cooling pintle hole (i.e., the fourth cooling hole 23) mainly functions to reduce the mixing ratio near the pintle head, reduce the combustion temperature around the pintle head, and protect the pintle head from being ablated; the liquid film cooling holes upstream of the throat (i.e., the second cooling holes 14) mainly function to form a liquid film, reduce the wall temperature, protect the upstream and downstream of the throat, and protect the wall surface from being ablated.

[0071] In the embodiment of the present application, kerosene injected into the combustion chamber 12 through the first cooling hole 21, the second cooling hole 14, the third cooling hole 22 and the fourth cooling hole 23 is used as a coolant to protect the thrust chamber from being ablated. The kerosene entering the combustion chamber 12 through the annular gap 70 is used as a fuel for the propellant.

[0072] Alternatively, if Figure 1 and Figure 3 As shown, in the embodiment of the present application, the injection portion 44 has a second inlet 46, an oxidant channel 47 connected to the second inlet 46, and an injection hole 48 connected to the oxidant channel 47. The oxidant can enter the oxidant channel 47 through the second inlet 46, and then be injected into the combustion chamber 12 through the injection hole 48, and mix and burn with the fuel (such as kerosene) that enters the combustion chamber 12 through the annular gap 70. The pintle head 43 is arranged at the lower end of the injection portion 44 and is located in the combustion chamber 12.

[0073] Alternatively, if Figure 2 and Figure 3 As shown, in the embodiment of the present application, the axis of the oxidant channel 47 is parallel to the axis L of the combustion body 10. The axis of the injection hole 48 intersects with the axis L of the combustion body 10 (for example, perpendicular to it).

[0074] Alternatively, if Figure 3 As shown, in the embodiment of the present application, the injection holes 48 are provided in two layers, the upper layer injection holes 48 have a smaller aperture than the lower layer injection holes 48. Of course, in other optional embodiments of the present application, the aperture of the upper layer injection holes 48 can also be set to be greater than or equal to the aperture of the lower layer injection holes 48 according to actual needs.

[0075] The embodiment of the present application provides a thrust chamber with multiple cooling methods, which can be applied to the field of rocket engine technology, and further to the field of liquid rocket engine technology.

[0076] The thrust chamber 100 provided in the embodiment of the present application can protect the thrust chamber from being ablated through a plurality of cooling holes (including the first cooling hole 21, the second cooling hole 14, the third cooling hole 22 and the fourth cooling hole 23). The following is an example of a liquid oxygen-kerosene pintle thrust chamber with multi-hole cooling: like Figures 1 to 5 As shown, an embodiment of the present application provides a porous cooled liquid oxygen-kerosene pintle thrust chamber, including a pintle injector 40, a combustion chamber 12, a regeneration cooling channel (i.e., a first cooling channel 13), liquid film cooling holes (i.e., second cooling holes 14), edge cooling holes (including first cooling holes 21, third cooling holes 22, and fourth cooling holes 23), and a liquid collecting cavity 42.

[0077] According to the following parameters and formula 1, it is calculated Thrust chamber mixture ratio , area ratio , ground thrust F, chamber pressure According to thermodynamic calculation CEA (Chemical Equilibrium with Applications) and formula 1, the throat diameter is , the theoretical rated flow is , is the nozzle exit velocity, combustion chamber diameter , is the nozzle exit area, is the combustion chamber throat area, is the nozzle outlet pressure, The pressure of the surrounding environment.

[0078] Formula 1 Assume the combustion chamber efficiency is , nozzle efficiency , according to formula 2, calculate the actual flow .

[0079] Formula 2 Pin diameter ; The overtravel ratio is set to = .

[0080] The blocking ratio is equal to 1, ensuring sufficient mixing and contact of the two propellants.

[0081] The rated injection pressure drop of liquid oxygen is set to , the rated pressure drop of kerosene injection is set to , and Ensure that the injection pressure drop meets the 60% working condition, the atomized particle size is small and stable combustion is maintained.

[0082] Kerosene annular gap flow coefficient , liquid oxygen injection hole flow coefficient .

[0083] The calculated width of the annular gap is б.

[0084] The injection holes 48 are designed as two rows of circular holes, with the number of each row being no less than 30, and the calculated diameters are D1 and D2.

[0085] The gas residence time τ is set to 2ms~8ms to ensure that the propellant is fully burned in the combustion chamber and improve the combustion efficiency.

[0086] The number of cooling channels of the regenerative cooling channel (i.e., the first cooling channel 13) can be set according to heat transfer calculation. In the embodiment of the present application, the number of regenerative cooling channels of the thrust chamber 100 is set to 300, and the regenerative cooling flow accounts for 92% of the total kerosene flow.

[0087] The liquid film cooling holes (i.e., the second cooling holes 14) are arranged upstream of the throat. The number of the liquid film cooling holes is consistent with the number of the regeneration cooling channels to ensure that the cooling liquid film covers the entire wall surface. The cooling flow of the liquid film cooling holes accounts for 8% of the total kerosene flow.

[0088] The edge zone cooling holes are arranged in the axial direction (i.e., the first cooling hole 21), radial direction (i.e., the third cooling hole 22) and oblique direction (i.e., the fourth cooling hole 23), and the injection hole diameter is the same. The number of radial edge zone cooling holes and oblique edge zone cooling holes is not less than 80 each. The axial edge zone cooling holes are 3 mm away from the inner wall of the combustion chamber 12, and the number is not less than 100. The cooling flow of the edge zone cooling holes (including the first cooling hole 21, the third cooling hole 22 and the fourth cooling hole 23) accounts for 15% of the total flow.

[0089] Based on the same inventive concept, an embodiment of the present application provides a power system, which includes: a thrust chamber 100 as described above.

[0090] Optionally, in the embodiment of the present application, the power system may further include a turbo pump, a gas generator, etc. It should be noted that the structure of the turbo pump and the gas generator in the embodiment of the present application and the arrangement between the turbo pump and the gas generator and the thrust chamber may be the same or similar to the structure of the turbo pump and the gas generator in the prior art and the arrangement between the turbo pump and the gas generator and the thrust chamber, and will not be described in detail here.

[0091] It should be noted that, since the power system in the embodiment of the present application includes the thrust chamber in the above-mentioned embodiment of the present application, the power system in the embodiment of the present application also has the above-mentioned beneficial effects of the thrust chamber in the above-mentioned embodiment of the present application, which will not be repeated here.

[0092] Optionally, the power system in the embodiment of the present application can be applied to a rocket engine, and further can be applied to a liquid rocket engine.

[0093] Based on the same inventive concept, an embodiment of the present application provides an aircraft, which includes: a power system as described above.

[0094] It should be noted that, since the aircraft in the embodiment of the present application includes a power system as in the above-mentioned embodiment of the present application, the aircraft in the embodiment of the present application also has the above-mentioned beneficial effects of the power system in the above-mentioned embodiment of the present application, which will not be repeated here.

[0095] Optionally, the aircraft in the embodiments of the present application includes but is not limited to aircraft, spacecraft, rockets and missiles.

[0096] By applying the embodiments of the present application, at least the following beneficial effects can be achieved: In the embodiment of the present application, the combustion body of the thrust chamber is cylindrical and has a throat. The first part of the combustion body located upstream of the throat forms a combustion chamber, and the propellant is atomized, mixed and burned in the combustion chamber. The first annular side wall of the thrust chamber is connected to the combustion body and is located at one end of the combustion chamber away from the throat, that is, located upstream of the combustion chamber.

[0097] The combustion body is provided with a first cooling channel extending from the lower end of the combustion body to the upper end of the combustion body. The coolant flows in the first cooling channel to cool the wall surface of the combustion body. The first annular side wall is provided with a plurality of first cooling holes connected to the first cooling channel, and the plurality of first cooling holes are connected to the combustion chamber. The coolant in the first cooling channel can enter the combustion chamber from upstream through the first cooling holes.

[0098] Since the plurality of first cooling holes are distributed along the circumference of the combustion body and are arranged near the inner wall of the combustion chamber, when the coolant enters the combustion chamber through the plurality of first cooling holes, the coolant is distributed around the combustion chamber and dispersed along the inner wall of the combustion chamber, thereby reducing the temperature near the circumferential inner wall of the combustion chamber, fully cooling the inner wall of the combustion chamber, and placing the inner wall of the combustion chamber in a low mixing ratio and low residual oxygen coefficient atmosphere, thereby protecting the inner wall of the combustion chamber and preventing it from being ablated. By providing the first cooling channel and the plurality of first cooling holes, the wall surface of the thrust chamber can be protected and ablation of the wall surface of the thrust chamber can be prevented.

[0099] In the description of the present application, the directions or positional relationships indicated by words such as "center", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" are based on the exemplary directions or positional relationships shown in the accompanying drawings. They are for the convenience of describing or simplifying the description of the embodiments of the present application, and do not indicate or imply that the referred device or component must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be understood as limitations on the present application.

[0100] The terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of this application, unless otherwise specified, "plurality" means two or more.

[0101] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0102] In the description of this specification, specific features, structures, materials or characteristics may be combined in an appropriate manner in any one or more embodiments or examples.

[0103] The above is only a partial implementation method of the present application. It should be pointed out that for ordinary technicians in this technical field, without departing from the technical concept of the scheme of the present application, other similar implementation methods based on the technical ideas of the present application are also within the protection scope of the embodiments of the present application.

Claims

1. A thrust chamber, characterized in that: include: A combustion body, which is cylindrical and has a throat, wherein a first portion of the combustion body located upstream of the throat forms a combustion chamber; A first annular side wall connected to the combustion body and located at an end of the combustion chamber away from the throat; Wherein: the combustion body is provided with a first cooling channel, and the first cooling channel extends from the lower end of the combustion body to the upper end of the combustion body; The first annular side wall is provided with a plurality of first cooling holes connected with the first cooling channel, the plurality of first cooling holes are distributed along the circumference of the combustion body, and each of the first cooling holes extends along the axial direction of the combustion body, and the first cooling holes are connected with the combustion chamber and are arranged close to the inner wall of the combustion chamber.

2. The thrust chamber according to claim 1, characterized in that: The combustion body is provided with a second cooling hole communicated with the first cooling channel. The second cooling hole is communicated with the combustion chamber and is located at one end of the combustion chamber close to the throat.

3. The thrust chamber according to claim 2, characterized in that: The number of the first cooling channel and the number of the second cooling holes are respectively multiple; The thrust chamber includes at least one of the following: A plurality of the second cooling holes are distributed along the circumference of the combustion body; Each of the first cooling channels is arranged corresponding to at least one of the second cooling holes.

4. The thrust chamber according to claim 1, characterized in that: The number of the first cooling passages is plural, and the second portion of the combustion body located downstream of the throat serves as a nozzle; The thrust chamber includes at least one of the following: A plurality of the first cooling channels are distributed along the circumference of the combustion body; A first liquid collecting ring is disposed on the outer side of the nozzle, and the first liquid collecting ring has a first annular cavity extending along the circumference of the nozzle and a first inlet communicating with the first annular cavity, and the lower ends of the plurality of first cooling channels are respectively communicated with the first annular cavity.

5. The thrust chamber according to any one of claims 1 to 4, characterized in that: Also included is an injector, the injector comprising a second liquid collecting ring connected to the combustion body and the first annular side wall; The second liquid collecting ring has a liquid collecting cavity communicated with the first cooling channel; The combustion body, the first annular side wall and the second liquid collecting ring form a second cooling channel communicating with the liquid collecting cavity; The second cooling channel is in communication with the first cooling hole.

6. The thrust chamber according to claim 5, characterized in that: The first annular side wall is also provided with a plurality of third cooling holes; The third cooling hole is located on a side of the first cooling hole away from the throat, and is communicated with the second cooling channel and the combustion chamber respectively; The plurality of third cooling holes are distributed along the circumference of the combustion body, and each of the third cooling holes extends along a direction perpendicular to the axis of the combustion body.

7. The thrust chamber according to claim 6, characterized in that: The first annular side wall is also provided with a plurality of fourth cooling holes; The fourth cooling hole is located between the first cooling hole and the third cooling hole, and is communicated with the second cooling channel and the combustion chamber respectively; The plurality of fourth cooling holes are distributed along the circumference of the combustion body, and each of the fourth cooling holes extends along a direction intersecting with and not perpendicular to the axis of the combustion body.

8. The thrust chamber according to claim 5, characterized in that: There are multiple second cooling channels, and the multiple second cooling channels are distributed along the circumference of the combustion body and are connected to the multiple first cooling holes in a one-to-one correspondence; or, The second cooling channel is an annular channel extending along the circumference of the combustion body, and the second cooling channel is communicated with the plurality of first cooling holes.

9. A power system, characterized in that: include: A thrust chamber as claimed in any one of claims 1 to 8.

10. An aircraft, characterized in that: include: The power system as claimed in claim 9.

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