CN114838385B - Self-diverting composite cooling combustion chamber - Google Patents
Self-diverting composite cooling combustion chamber Download PDFInfo
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- CN114838385B CN114838385B CN202210281759.6A CN202210281759A CN114838385B CN 114838385 B CN114838385 B CN 114838385B CN 202210281759 A CN202210281759 A CN 202210281759A CN 114838385 B CN114838385 B CN 114838385B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03043—Convection cooled combustion chamber walls with means for guiding the cooling air flow
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E20/00—Combustion technologies with mitigation potential
- Y02E20/34—Indirect CO2mitigation, i.e. by acting on non CO2directly related matters of the process, e.g. pre-heating or heat recovery
Abstract
The invention discloses a self-flow-dividing composite cooling combustion chamber, which relates to the technical field of liquid rocket engines and improves the cooling performance of the combustion chamber. The combustion chamber comprises an outer shell and an inner shell, wherein a first end of the outer shell is provided with a coolant inlet, and a second end of the outer shell is provided with a coolant outlet; the inner shell is coaxially sleeved with the outer shell, and a plurality of regeneration cooling channels are formed between the outer shell and the inner shell; the regeneration cooling channel is communicated with the coolant inlet and the coolant outlet; the outer wall of the inner shell is provided with an annular segmented area, the annular segmented area is arranged between the first end and the second end and used for dividing the regenerative cooling channel into two parts which are communicated, and a flow dividing hole which is communicated with the regenerative cooling channel and the inner part of the inner shell is circumferentially arranged in the annular segmented area and used for leading part of coolant in the regenerative cooling channel into the inner shell to form a cooling liquid film to cool the inner wall of the inner shell.
Description
Technical Field
The invention belongs to the technical field of liquid rocket engines, and particularly relates to a self-flow-dividing composite cooling combustion chamber.
Background
During rocket engine thrust chamber design testing, the thrust chamber is divided into a combustion chamber and a head containing the injector, so that different injectors can be replaced for testing.
The high-thrust liquid rocket engine thrust chamber adopts high chamber pressure to work, the pressure of the combustion chamber exceeds 20MPa, when the pressure of the combustion chamber is increased, the heat flux density is also greatly increased, the combustion chamber is difficult to cool, and the service life and the reusability are affected. The traditional combustion chamber is provided with an independent cooling annular cavity, and the system is required to independently supply cooling liquid for inner wall cooling after ignition, so that the problem of complex timing matching of the ignition of a cooling circuit and a main circuit is caused.
Disclosure of Invention
The invention aims to provide a self-flow-dividing composite cooling combustion chamber so as to improve the reliability of the cooling performance of the combustion chamber.
In order to achieve the above object, the present invention provides the following technical solutions:
a self-diverting composite cooling combustor comprising:
the cooling device comprises an outer shell, a cooling device and a cooling device, wherein a first end of the outer shell is provided with a coolant inlet, and a second end of the outer shell is provided with a coolant outlet;
the inner shell is coaxially sleeved with the outer shell, and a plurality of regeneration cooling channels are formed between the outer shell and the inner shell; the regenerative cooling channel communicates with the coolant inlet chamber and the coolant outlet chamber; the outer wall of the inner shell is provided with an annular segmented area, the annular segmented area is arranged between the first end and the second end and is used for dividing the regenerative cooling channel into two parts which are communicated, and a diversion hole which is communicated with the regenerative cooling channel and the inner part of the inner shell is circumferentially arranged in the annular segmented area and is used for guiding part of coolant in the regenerative cooling channel into the inner shell to form a cooling liquid film to cool the inner wall of the inner shell.
Compared with the prior art, the coolant flows to the annular segmented region for diversion after entering the regenerative cooling channel from the coolant inlet, most of the coolant flows to the second end of the regenerative cooling channel, enters the head fuel cavity from the coolant outlet, is sprayed out by the nozzle for atomization combustion, and forms a rotational flow for cooling the inner surface of the head of the combustion chamber; the small part of coolant is led into the inner shell through the flow dividing holes at the annular segmented region and is sprayed out in a high-speed rotational flow mode to form a cooling liquid film which is adhered to and flows in a rotating mode, the inner wall of the inner shell is cooled reliably before the fuel is ignited, the utilization rate of the coolant is improved, and the defects that the timing sequence matching of the liquid film cooling path, the cooling path and the main path which are required to be independently arranged is complex and the gas anti-channeling cavity is overcome.
In one implementation mode, a plurality of ribs which are uniformly distributed in a spiral mode are arranged on the outer wall of the inner shell, and two adjacent ribs, the outer wall of the inner shell and the inner wall of the outer shell form the regenerative cooling channel with a spiral structure.
By adopting the scheme, the regeneration cooling channel with the spiral structure can increase the flow velocity of the coolant and enhance the cooling effect under the condition of certain coolant flow.
In one implementation, the inner shell and the plurality of ribs are an integrally formed structure.
By adopting the scheme, the device has the advantages that the reliability is improved while the processing cost is reduced, the reusability is good, the maintenance and the treatment are simple, and the flow distribution holes and the annular segmented area structure of the processing are better than those of the traditional assembly formed circular seam scheme in flow equalization effect, the deformation is small, and the uniformity of the liquid film is obviously improved.
In one implementation, the diversion holes are uniformly arranged in the annular segmented region along the circumferential direction and are obliquely arranged in a circular section where the annular segmented region is located.
In one implementation, the inner housing includes a converging-diverging section and a cylindrical section coaxially connected in a direction from a first end to a second end; the annular segmented area is arranged at the joint of the convergent-divergent section and the cylindrical section.
By adopting the effect of the scheme, the coolant can be sprayed out through the diversion holes 5 in a high-speed rotational flow mode to form a cooling liquid film which is adhered to the inner wall of the inner shell and rotationally flows, so that the protection of the inner wall of the inner shell is improved, and the throat area of the contraction-expansion section with a severe thermal environment is protected.
In one implementation, an annular protrusion is arranged in the annular segmented region, the height of the annular protrusion is smaller than that of the rib, a plurality of step surfaces are uniformly arranged on the annular protrusion along the circumferential direction, and the inlets of the diversion holes are positioned on the step surfaces.
By adopting the above scheme, under the condition, the annular bulge can play a role in resisting flow of the coolant flowing out of the regeneration cooling channel, and the arrangement of the step-shaped inlet improves the flow coefficient of the slender flow dividing hole, ensures that the pressure drop of the annular sectional area meets the requirement, ensures that the flow dividing proportion is reasonable, and keeps the outlet speed of the flow dividing hole to be large so as to form a coolant film to realize good cooling on the inner wall.
In one implementation mode, the inner wall of the inner shell is provided with a ring groove corresponding to the annular bulge, the outlet of the flow dividing hole is communicated with the ring groove, the edge of the ring groove close to one side of the cylindrical section is higher than the edge of the ring groove close to one side of the convergent-divergent section, and the height difference is 0.5mm-2mm.
By adopting the effect of the scheme, the edges on two sides of the annular groove 22 form a height difference, so that the entrainment effect of the central main flow gas G is reduced, the premature chemical reaction of the gas and the liquid film is reduced, the gas is prevented from destroying the liquid, and the throat cooling effect is enhanced.
In one implementation mode, a conical surface transition section is arranged on the inner wall of the inner shell, which is close to one side of the expansion section, of the annular groove, and the length of the conical surface transition section is 18-25 mm.
By adopting the scheme, the liquid film momentum loss is low when the coolant comes out from the outlet of the flow dividing hole, and the wall attaching effect on the inner wall of the inner shell is good.
In one implementation, the conical surface transition section and the axis of the inner shell form an included angle θ of 4 ° to 6 °.
By adopting the scheme, the momentum loss of the liquid film is low during the outlet, and the wall attaching effect is good.
In one implementation, the ratio of the length to the diameter of the diverter aperture is less than 8.
By adopting the scheme, the loss of the inlet and the edge is reduced, the loss of the edge momentum is large because the ratio of the length to the diameter of the existing diversion hole is larger than 15, if the outlet flow velocity of the diversion hole is high, the loss of the inlet and the edge is properly small, the loss of the liquid film momentum is low during the outlet is ensured, and the wall attaching effect of the liquid film is good.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention and do not constitute a limitation on the invention.
FIG. 1 is a cross-sectional view of a combustion chamber provided by the present invention;
FIG. 2 is a cross-sectional view of an annular segmented region of an inner housing of the present invention;
FIG. 3 is an enlarged partial view of a cross-sectional view of an annular segmented region of an inner housing of the present invention;
fig. 4 is a cross-sectional view of fig. 3 taken along the X-X direction.
Wherein:
1-an outer shell; 2-an inner housing; 3-annular segmented region; 4-a regenerative cooling channel; 5-a diversion hole; 6-collecting and expanding sections; 7-a cylindrical section; 11-a coolant inlet; 12-a coolant outlet; 21-ribs; 22-ring grooves; 31-annular protrusions; 32-step surface.
Detailed Description
Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to like or similar elements or elements having like or similar functions throughout. The embodiments described below by referring to the drawings are illustrative and intended to explain the present invention and should not be construed as limiting the invention.
In the description of the present invention, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the drawings, are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature. In the description of the present invention, the meaning of "a plurality" is two or more, unless explicitly defined otherwise.
In the present invention, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
In the present invention, unless expressly stated or limited otherwise, a first feature "above" or "below" a second feature may include both the first and second features being in direct contact, as well as the first and second features not being in direct contact but being in contact with each other through additional features therebetween. Moreover, a first feature being "above," "over" and "on" a second feature includes the first feature being directly above and obliquely above the second feature, or simply indicating that the first feature is higher in level than the second feature. The first feature being "under", "below" and "beneath" the second feature includes the first feature being directly under and obliquely below the second feature, or simply means that the first feature is less level than the second feature.
As shown in fig. 1-2, a self-flow-dividing composite cooling combustion chamber is disclosed for an embodiment of the present invention, and comprises an outer casing 1 and an inner casing 2, wherein a first end of the outer casing 1 is provided with a coolant inlet 11, and a second end of the outer casing 1 is provided with a coolant outlet 12; the inner shell 2 is coaxially sleeved with the outer shell 1, and a plurality of regeneration cooling channels 4 are formed between the outer shell 1 and the inner shell 2; the regenerative cooling channel 4 communicates with the coolant inlet 11 and the coolant outlet 12; the outer wall of the inner shell 2 is provided with an annular segmented area 3, the annular segmented area 3 is arranged between a first end and a second end and used for dividing the regenerative cooling channel 4 into two communicated parts, a flow dividing hole 5 which is used for communicating the regenerative cooling channel 4 with the inner part of the inner shell 2 is circumferentially arranged in the annular segmented area 3 and used for guiding part of coolant in the regenerative cooling channel 4 into the inner shell 2 to form a cooling liquid film to cool the inner wall of the inner shell 2.
In operation, as shown by the arrow in fig. 1, coolant flows to the annular segment area 3 for diversion after entering the regeneration cooling channel 4 from the coolant inlet 11, most of the coolant flows to the regeneration cooling channel 4 and enters the head fuel cavity from the coolant outlet 12, and is sprayed and atomized to burn through the nozzle, and a swirl liquid film is formed to cool the inner surface of the combustion chamber; a small part of the coolant is introduced into the inner shell 2 at the annular segmented region 3 through the flow dividing holes 5 and is sprayed out in a high-speed rotational flow mode to form a cooling liquid film which is adhered to the rotating flow, and the inner wall of the inner shell 2 is reliably cooled before the fuel is ignited.
According to the scheme and the process, the coolant is simple to supply, the defect that the timing sequence matching of the liquid film cooling path, the cooling path and the main path ignition is complex to set independently is overcome, the reliable cooling of the coolant liquid film on the inner wall of the inner shell before the ignition of fuel is effectively ensured, the coolant flow distribution at the head part of the combustion chamber and the sectional area is realized through the sectional flow resistance design of the sectional area, and the cooling flow distribution proportion is determined.
Illustratively, the outer shell 1 is made of steel materials, the inner shell 2 is made of copper materials, the inner shell and the copper materials are connected through brazing to form a combustion chamber structure, a combustion agent-unsymmetrical dimethylhydrazine (also called 1, 1-dimethylhydrazine, molecular formula (CH 3) 2NNH2 or C2H8N 2)) with good cooling performance is adopted as a regenerated coolant, the regenerated coolant enters from the coolant inlet 11, is split through the segmentation area 3, enters the inner shell 2 through the split hole 5 in a small part, and flows out from the coolant outlet 12 through the regenerated cooling channel 4 in a large part.
In one embodiment, as shown in fig. 2, a plurality of ribs 21 are spirally and uniformly arranged on the outer wall of the inner shell 2, and two adjacent ribs 21, the outer wall of the inner shell 2 and the inner wall of the outer shell 1 form a regeneration cooling channel 4 with a spiral structure. In this case, the spiral-structured regenerative cooling passage 4 can increase the coolant flow rate and enhance the cooling effect in the case where the coolant flow rate is constant.
Preferably, the inner housing 2 and the plurality of ribs 21 in the present embodiment are an integrally molded structure. Under the condition, the processing is convenient, the reusability is good, the maintenance and treatment are simple, the structure of the processed flow dividing holes 5 and the annular segmented region 3 is better than that of a circular seam scheme formed by traditional assembly, the deformation is small, and the uniformity of a liquid film is obviously improved.
In the present embodiment, the flow dividing holes 5 are uniformly provided in the annular segment region 3 in the circumferential direction, and are provided obliquely in the circular cross section where the annular segment region 3 is located. When the combustion agent used as the liquid film is sprayed toward the inner wall surface, the impact angle with the inner wall surface inevitably causes the rebound of the liquid droplets, resulting in a decrease in the amount of the actual cooling liquid film. Preferably, the axial direction of the diversion holes 5 is tangential to the circular inner surface of the inner casing 2 as much as possible, so as to reduce the loss.
Specifically, the inner housing 2 includes a convergent-divergent section 6 and a cylindrical section 7 coaxially connected in a direction from the first end to the second end, and the annular segmented section 3 is disposed at a junction between the convergent-divergent section 6 and the cylindrical section 7 and is communicated with the regenerative cooling channels 4 on both sides. The coolant is sprayed out through the diversion holes 5 in a high-speed rotational flow mode to form a cooling liquid film which is adhered to and rotationally flows, so that the protection of the inner wall of the inner shell 2 in the collecting and expanding section 6 is improved, and the throat area of the collecting and expanding section 6 with a severe thermal environment is protected.
In some embodiments, as shown in fig. 2, an annular protrusion 31 is provided in the annular segmented region 3, the height of the annular protrusion 31 is smaller than the height of the rib 21, a plurality of step surfaces 32 are provided on the annular protrusion 31 in the circumferential direction, and the inlets of the diversion holes 5 are located on the step surfaces 32. In this case, the annular protrusion 31 can perform a flow blocking effect on the coolant flowing out of the regenerative cooling channel 4, and the arrangement of the stepped inlet improves the flow coefficient of the diversion hole 5, ensures that the pressure drop of the annular segmented region 3 meets the requirement, ensures that the diversion ratio is reasonable, and keeps the outlet speed of the diversion hole 5 to be high so as to form a coolant film to realize good cooling on the inner wall.
In this embodiment, the ratio of the length to the diameter of the diverting holes 5 is less than 8. In this case, since the ratio of the length to the diameter of the existing diversion hole 5 is greater than 15, the loss of the along-the-path momentum is large, if the outlet flow velocity of the diversion hole 5 is high, the loss of the inlet and along-the-path is properly small, the loss of the momentum of the liquid film is low during the outlet, and the adhesion effect of the liquid film is good.
In this embodiment, the flow rate of the coolant at the outlet of the split hole 5 may be 80m/s, and the ratio of the speed of the fuel gas to the flow rate of the coolant is 4.5 to 4.7. In this case, the greater the outlet speed of the split holes 5, the better the adherence of the liquid film, the better the cooling effect of the combustion chamber with respect to the maintenance of the liquid film morphology and the enhancement of the resistance to the disturbance of the air flow.
As shown in fig. 3, in the present embodiment, the height of the annular projection 31 is at most 3mm smaller than the height of the rib 21, i.e., the height difference H is not more than 3mm. The thickness of the annular bulge 31 is ensured to ensure structural strength, the annular bulge 31 does not obstruct the circulation of the coolant from the coolant inlet to the coolant outlet along the regeneration cooling channel, because the height of the rib 21 is larger than that of the annular bulge 31, when the outer surface of the inner shell 2 is connected with the inner surface of the outer shell 1, an annular cavity is formed at the position of the annular bulge 31, the shunted coolant circulates in the annular cavity, the flow direction of the coolant is thickened in the direction shown by an arrow in fig. 2, the two sides of the annular cavity are thickened to improve the flow speed and structural strength, the coolant forms anticlockwise circulation after entering the annular cavity from the regeneration cooling channel 4, the coolant enters the shunt hole 5 after circulating here, and the coolant forms clockwise rotational flow on the inner wall of the inner shell through the shunt hole 5, so the arrangement is provided for uniformly distributing the circulation in the annular cavity into the shunt hole 5, and the phenomenon that the circulation direction in the annular cavity is consistent with the circulation direction of the circulation in the annular cavity, and the flow of the part of the shunt hole 5 is excessively small due to the section opposite to the rib 21, the flow of the coolant causes the flow of the here to excessively small flow speed of the shunt hole 5 at the outlet of the inner wall, and the uneven liquid film is formed.
In the embodiment shown in fig. 3 to 4, the inner wall of the inner housing 2 is provided with a ring groove 22 corresponding to the annular protrusion 31, the outlet of the split flow hole 5 is communicated with the ring groove 22, the edge of the ring groove 22 near the cylindrical section 7 is higher than the edge of the ring groove 22 near the expanding section 6, and the height difference L is 0.5-2mm. At this time, the edges on two sides of the ring groove 22 form a height difference, which reduces the entrainment of the central main flow gas, and reduces the premature chemical reaction of the gas and the liquid film, so as to prevent the gas from destroying the liquid, and enhance the cooling effect on the expansion section 6. The height difference L is equal to or slightly larger than the thickness of the liquid film, and is generally 1-2 mm in the large-thrust combustion chamber, and 0.5-1 mm in the medium-small-thrust combustion chamber.
In this embodiment, the inner wall of the inner casing 2 on the side of the ring groove 22 close to the expansion section 6 is provided with a conical surface transition section, and the length of the conical surface transition section is 18mm-25mm. At this time, it is ensured that the loss of momentum of the liquid film is low when the coolant comes out from the outlet of the split hole 5, and the wall sticking effect on the inner wall of the inner casing 2 is good.
In this embodiment, as shown in fig. 3, the conical surface transition section forms an included angle θ with the axis of the inner housing 2, and the included angle θ is 4 ° to 6 °. Under the condition, the momentum loss of the liquid film at the outlet is low, and the wall attaching effect is good.
Compared with the prior art, the invention has the advantages that:
(1) The present invention adopts the integral structure that a regeneration cooling channel and an inlet and an outlet of an annular segmented area are processed on one part of an inner shell, and the integral self-flow structure has the advantages of simple system supply, obviously improved liquid film uniformity and good reusability, and is suitable for a combustion chamber with a composite cooling structure.
(2) The invention improves the service life and uniformity of the liquid film of the high-pressure combustion chamber, improves the outlet speed of the split holes through the structural design of the annular sectional area and the split holes, ensures low momentum loss of the liquid film during outlet, has good adherence effect, reduces the premature chemical reaction of fuel gas and the liquid film, and enhances the throat cooling effect.
In the description of the present specification, a description referring to terms "one embodiment," "some embodiments," "examples," "specific examples," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present invention. In this specification, schematic representations of the above terms are not necessarily directed to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Further, one skilled in the art can engage and combine the different embodiments or examples described in this specification.
While embodiments of the present invention have been shown and described above, it will be understood that the above embodiments are illustrative and not to be construed as limiting the invention, and that variations, modifications, alternatives and variations may be made to the above embodiments by one of ordinary skill in the art within the scope of the invention.
Claims (5)
1. A self-diverting composite cooling combustion chamber, comprising:
the cooling device comprises an outer shell, a cooling device and a cooling device, wherein a first end of the outer shell is provided with a coolant inlet, and a second end of the outer shell is provided with a coolant outlet;
the inner shell is coaxially sleeved with the outer shell, and a plurality of regeneration cooling channels are formed between the outer shell and the inner shell; the regenerative cooling channel is in communication with the coolant inlet and the coolant outlet; the outer wall of the inner shell is provided with an annular segmented area, the annular segmented area is arranged between the first end and the second end and is used for dividing the regenerative cooling channel into two communicated parts, and a diversion hole which is communicated with the regenerative cooling channel and the inner part of the inner shell is circumferentially arranged in the annular segmented area and is used for guiding part of coolant in the regenerative cooling channel into the inner shell to form a cooling liquid film to cool the inner wall of the inner shell;
a plurality of ribs which are uniformly distributed in a spiral manner are arranged on the outer wall of the inner shell, and two adjacent ribs, the outer wall of the inner shell and the inner wall of the outer shell form a regenerative cooling channel with a spiral structure;
the inner shell comprises a convergent-divergent section and a cylindrical section which are coaxially connected along the direction from the first end to the second end; the annular segmented area is arranged at the joint of the convergent-divergent section and the cylindrical section;
the annular segmented region is internally provided with an annular bulge, the height of the annular bulge is smaller than that of the rib, a plurality of step surfaces are uniformly arranged on the annular bulge along the circumferential direction, and the inlets of the diversion holes are positioned on the step surfaces;
the inner wall of the inner shell is provided with a ring groove corresponding to the annular bulge, the outlet of the diversion hole is communicated with the ring groove, the edge of one side of the ring groove, which is close to the cylindrical section, is higher than the edge of one side of the ring groove, which is close to the expanding section, and the height difference is 0.5mm-2mm;
the annular groove is provided with a conical surface transition section on the inner wall of the inner shell close to one side of the collecting and expanding section, and the length of the conical surface transition section is 18mm-25mm.
2. The self-diverting composite cooled combustion chamber of claim 1, wherein said inner shell and a plurality of said ribs are of unitary construction.
3. The self-diverting composite cooling combustion chamber according to claim 1, wherein the diverting holes are uniformly arranged in the annular sectional area along the circumferential direction and are obliquely arranged in the circular section where the annular sectional area is located.
4. The self-diverting composite cooling combustor according to claim 1, wherein the conical surface transition section forms an angle θ of 4 ° to 6 ° with the axis of the inner housing.
5. The self-diverting composite cooled combustion chamber of claim 1, wherein the ratio of the length to the diameter of the diverting holes is less than 8.
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