CN115217670B - Design method of three-duct supersonic jet pipe configuration - Google Patents
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- 238000000034 method Methods 0.000 title claims abstract description 66
- 239000007921 spray Substances 0.000 claims description 55
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/40—Nozzles having means for dividing the jet into a plurality of partial jets or having an elongated cross-section outlet
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- G—PHYSICS
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Abstract
The invention discloses a three-duct supersonic jet pipe configuration and a design method thereof, relates to the field of aeroengine jet pipes for supersonic aircraft, and solves the problems that typical structural characteristics of the existing three-duct supersonic jet pipe and the design method thereof are not obvious, and high-performance design of the three-duct jet pipe cannot be directly realized. The jet pipe structure has the characteristics of compact and smooth jet pipe structure, high performance of each duct jet pipe, suitability for military and civil supersonic aircraft and high design efficiency.
Description
Technical Field
The invention relates to the field of aero-engine spray pipes for supersonic aircraft, in particular to a design method of a three-duct supersonic spray pipe configuration.
Background
The third flow of the three-duct spray pipe can reduce the overflow resistance of the engine; reducing the temperature of the hot end wall surface and the exhaust temperature of the engine, and inhibiting infrared radiation characteristic signals; the three-duct spray pipe has the advantages of low radiation, low noise and low resistance, and is a key component of a military and civil supersonic aircraft.
The three-duct spray pipe for supersonic speed fighter and the three-duct spray pipe for supersonic speed airliner proposed in the existing research have different configurations, typical structural characteristics are not obvious, a design method is not clear, and the high-performance design of the three-duct spray pipe cannot be directly realized. Therefore, a design method of the three-duct supersonic jet pipe configuration is provided.
Disclosure of Invention
The invention aims to provide a design method of a three-duct supersonic jet pipe configuration, which solves the problems that typical structural characteristics of the existing three-duct supersonic jet pipe and the design method thereof are not obvious, and high-performance design of the three-duct jet pipe cannot be directly realized.
In order to achieve the above purpose, the present invention provides the following technical solutions: the design method of the three-duct supersonic jet pipe configuration is characterized by comprising the following steps of:
S1: s-bend unilateral expansion spray pipe design of main flow duct is carried out:
1. the method comprises the following steps:
(1) S-bend convergent section design is carried out by adopting an S-bend spray pipe design method based on multi-parameter coupling;
the S-bend convergence section design process comprises the following steps: a. calculating a central line of the main flow jet pipe according to the LEE curve equation; b. giving a change rule of the cross-sectional area, and obtaining the cross-sectional area at each position along the way according to the areas of the inlet and the throat; c. performing rotary transformation on each section based on the central line; d. fitting to obtain inner and outer wall surface lines, and obtaining an S-bend convergence section.
(2) Obtaining a supersonic initial line of a throat region by adopting a conventional Soxhlet method, and designing a unilateral expansion section by adopting a characteristic line method on the basis of the supersonic initial line;
(3) Connecting the S-shaped convergent section with the unilateral expansion section to obtain a two-dimensional S-shaped unilateral expansion spray pipe, repeating the steps (1) - (3) to obtain a certain number of S-shaped unilateral expansion spray pipes with different configurations, and performing numerical simulation on the S-shaped unilateral expansion spray pipes with different configurations to obtain supersonic velocity initial line distribution data;
(4) Building a convolutional neural network model according to the supersonic initial line distribution data, inputting geometric appearance features, namely an S-bend convergence section profile and the supersonic initial line distribution features, into the convolutional neural network, building a mapping relation between the supersonic initial line distribution and the geometric appearance features through convolution and pooling processes, and reconstructing a supersonic initial line of the S-bend convergence section;
2. And (3) pre-estimating:
(1) For the S-bend convergence section which is input again, an accurate supersonic velocity initial line is directly and rapidly predicted through the established convolutional neural network model;
(2) On the basis of a reconstructed supersonic initial line, adopting a characteristic line method based on maximum thrust constraint to develop a unilateral expansion section design, completing the design of a core area and a spray pipe molded surface through progressive calculation of inner points and wall points under the given length and the maximum thrust constraint, and then combining the core area and the spray pipe molded surface with an S-bend convergence section;
S2: s-bend unilateral expansion spray pipe design of secondary flow culvert is carried out: s1, a mapping relation between an S-shaped convergence section and geometric shape features is obtained, and in the process, the pre-estimation design can be directly carried out;
(1) Designing an S-bend convergence section of the secondary flow culvert, and directly and rapidly predicting an accurate supersonic velocity initial line through an established convolutional neural network model;
(2) On the basis of a reconstructed supersonic initial line, adopting a characteristic line method based on maximum thrust constraint to develop a unilateral expansion section design, giving a length and maximum thrust constraint, and restricting the expansion section outlet of the secondary flow duct nozzle to be tangent with the outer wall surface outlet of the main flow duct nozzle, finishing the core area and nozzle profile design through progressive calculation of inner points and wall surface points, and then combining the core area and nozzle profile design with an S-bend convergence section;
s3: s-bend single-side expansion spray pipe design of a third flow duct is carried out:
(1) Designing an S-bend convergence section of a third flow duct, and directly and rapidly predicting an accurate supersonic velocity initial line through an established convolutional neural network model;
(2) On the basis of a reconstructed supersonic initial line, a characteristic line method based on maximum thrust constraint is adopted to develop a unilateral expansion section design, the length and the maximum thrust constraint are given, the expansion section outlet of the third flow culvert pipe is constrained to be tangent with the outer wall surface outlet of the secondary flow culvert pipe, the core area and the spray pipe molded surface design are still completed through progressive calculation of inner points and wall surface points, and then the core area and the spray pipe molded surface are combined with an S-bend convergence section.
The three-duct supersonic jet pipe structure is formed through the design of the steps S1-S3, and comprises a main flow duct, a secondary flow duct and a third flow duct, wherein the main flow duct is composed of an outer wall surface I and a tail cone, the secondary flow duct is composed of an outer wall surface II and an inner wall surface II, and the third flow duct is composed of an outer wall surface III and an inner wall surface III.
Preferably, the main flow duct, the secondary flow duct and the third flow duct are all S-bend unilateral expansion spray pipes consisting of S-bend convergent sections, throats and unilateral expansion sections.
Preferably, the main flow duct comprises an S-bend converging channel I, a throat I and a unilateral expansion expanding channel I.
Preferably, the secondary flow duct comprises a second S-bend convergence channel, a second throat (24) and a second unilateral expansion channel.
Preferably, the third flow duct comprises an S-bend convergence channel III, a throat III and a unilateral expansion channel III.
Preferably, the designing process of the unilateral expansion section in the step S1 includes: a. calculating the flow parameters of the area determined by the initial line through the supersonic initial line until the boundary characteristic line of the area is calculated; b. calculating the area determined by the boundary characteristic line and the throat expansion section line; c. and calculating the supersonic section molded lines of the rest areas to obtain the unilateral expansion section.
Compared with the related art, the design method of the three-duct supersonic jet pipe configuration has the following beneficial effects:
The design method of the three-duct supersonic jet pipe configuration can be used for directly designing the three-duct supersonic jet pipe, is applicable to military and civil supersonic aircrafts, and has the advantages of high design efficiency, compact and smooth jet pipe structure and high performance of each duct jet pipe.
Drawings
Fig. 1 is a schematic structural view of a three-duct supersonic nozzle configuration of the present invention.
Fig. 2 is a schematic plan view of a three-duct supersonic nozzle configuration of the present invention.
FIG. 3 is a flow chart of a design method of a three-duct supersonic jet pipe configuration.
In the figure: 10. a third flow bypass; 11. an outer wall surface III; 12. an inner wall surface III; 13. s-bend convergence channel III; 14. a third throat; 15. a unilateral expansion channel III; 20. a secondary flow duct; 21. an outer wall surface II; 22. an inner wall surface II; 23. s-bend convergence channel II; 24. a second throat; 25. a unilateral expansion channel II; 30. a main flow duct; 31. an outer wall surface I; 32. a tail cone; 33. s-bend convergence channel I; 34. a first throat; 35. the unilateral inflation expands the first passageway.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all embodiments of the invention; all other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Embodiment one:
referring to fig. 1-3, the present invention provides a technical solution: the three-duct supersonic jet pipe structure comprises a main flow duct 30, a secondary flow duct 20 and a third flow duct 10, wherein the main flow duct 30 is composed of an outer wall surface I31 and a tail cone 32, the secondary flow duct 20 is composed of an outer wall surface II 21 and an inner wall surface II 22, and the third flow duct 10 is composed of an outer wall surface III 11 and an inner wall surface III 12.
The main flow duct 30, the secondary flow duct 20 and the third flow duct 10 are all S-shaped unilateral expansion spray pipes consisting of S-shaped convergent sections, throats and unilateral expansion sections.
The main flow duct 30 includes an S-bend converging channel one 33, a throat one 34, and a single-sided expanding channel one 35.
The secondary flow duct 20 comprises a second S-bend converging channel 23, a second throat 24 and a second unilateral expansion expanding channel 25.
The third flow duct 10 includes an S-bend converging channel three 13, a throat three 14, and a unilateral expanding channel three 15.
In the embodiment, the design of the three-duct spray pipe can be directly carried out, and the design method is applicable to both military and civil supersonic aircraft, and has the advantages of high design efficiency, compact and smooth spray pipe structure and high performance of each duct spray pipe.
Embodiment two:
Referring to fig. 1-3, on the basis of the first embodiment, the present invention provides a technical solution:
The S-MOC method provided by the invention is adopted to design the S-bend unilateral expansion spray pipe of each duct. S of the S-MOC method refers to an S-bend spray pipe design method based on multi-parameter coupling, and is used for designing S-bend convergence; MOC refers to a feature line method (Method of Characteristics, MOC) that considers maximum thrust constraints for the design of an expansion segment, which may be considered during the design process. The S-MOC method provided by the invention does not directly connect the S-bend convergence section designed by adopting the S-bend spray pipe design method based on multi-parameter coupling and the unilateral expansion section designed by adopting the MOC method, but considers the transition problem between the two, namely the design of the throat region. When the characteristic line method is adopted for designing the expansion section, the initial line distribution of the supersonic speed needs to be known, and the initial line distribution of the supersonic speed is asymmetric and complex in shape due to the S-bend convergence section and cannot be obtained through theoretical deduction adopted by the conventional method. The invention provides a method for reconstructing a supersonic velocity initial line of a throat region after an S-bend convergence section based on a convolutional neural network. The combination of the S-bend spray pipe design method based on multi-parameter coupling, the supersonic initial line reconstruction method based on a convolutional neural network and the expansion section design method based on a characteristic line method is called as an S-MOC method.
A design method of a three-duct supersonic jet pipe configuration comprises the following steps:
S1: s-bend unilateral expansion spray pipe design of main flow duct is carried out:
1. the method comprises the following steps:
(1) The S-bend convergent section design is carried out by adopting an S-bend spray pipe design method based on multi-parameter coupling, and the design process comprises the following steps: a. calculating a central line of the main flow jet pipe according to the LEE curve equation; b. giving a change rule of the cross-sectional area, and obtaining the cross-sectional area at each position along the way according to the areas of the inlet and the throat; c. performing rotary transformation on each section based on the central line; d. fitting to obtain inner and outer wall surface lines and obtaining an S-shaped convergence section;
(2) The method comprises the steps of obtaining a supersonic initial line of a throat region by adopting a conventional Soxhlet method, designing a unilateral expansion section by adopting a characteristic line method on the basis of the supersonic initial line, wherein the design process comprises the following steps: a. calculating the flow parameters of the area determined by the initial line through the supersonic initial line until the boundary characteristic line of the area is calculated; b. calculating the area determined by the boundary characteristic line and the throat expansion section line; c. calculating the supersonic section molded lines of the rest areas to obtain a unilateral expansion section;
(3) Connecting the S-shaped convergent section with the unilateral expansion section to obtain a two-dimensional S-shaped unilateral expansion spray pipe, repeating the steps 1) -3) to obtain a certain number of S-shaped unilateral expansion spray pipes with different configurations, and performing numerical simulation on the S-shaped unilateral expansion spray pipes with different configurations to obtain supersonic velocity initial line distribution data;
(4) Building a convolutional neural network model according to the supersonic initial line distribution data, inputting geometric appearance characteristics (namely, S-bend convergence section profiles) and the supersonic initial line distribution characteristics into the convolutional neural network, building a mapping relation between the supersonic initial line distribution and the geometric appearance characteristics through convolution, pooling and other processes, and reconstructing a supersonic initial line of the S-bend convergence section;
2. And (3) pre-estimating:
(1) For the S-bend convergence section which is input again, an accurate supersonic velocity initial line is directly and rapidly predicted through the established convolutional neural network model;
(2) On the basis of a reconstructed supersonic initial line, adopting a characteristic line method based on maximum thrust constraint to develop a unilateral expansion section design, completing core area and spray pipe molded surface design through progressive calculation of inner points and wall surface points under given length and maximum thrust constraint, combining the core area and the S-bend convergence section to realize the inverse design of the high-performance S-bend unilateral expansion spray pipe, wherein the inner wall surface of the S-bend convergence section and the expansion section form a tail cone (32) molded line, and the outer wall surface of the S-bend convergence section is a first (31) molded line of the outer wall surface of the main flow spray pipe, so that the S-bend unilateral expansion spray pipe design of the main flow culvert is completed;
S2: s-bend unilateral expansion spray pipe design of secondary flow culvert is carried out: s1, a mapping relation between an S-shaped convergence section and geometric shape features is obtained, and in the process, the pre-estimation design can be directly carried out;
(1) Designing an S-bend convergence section of the secondary flow culvert, and directly and rapidly predicting an accurate supersonic velocity initial line through an established convolutional neural network model;
(2) On the basis of a reconstructed supersonic initial line, adopting a characteristic line method based on maximum thrust constraint to develop a unilateral expansion section design, giving length and maximum thrust constraint, and restricting the expansion section outlet of the secondary flow culvert pipe to be tangent with the outer wall surface outlet of the main flow culvert pipe, finishing the core area and the spray pipe profile design through progressive calculation of inner points and wall surface points, combining the core area and the spray pipe profile design with an S-bend convergence section to realize the inverse design of the high-performance S-bend unilateral expansion spray pipe of the secondary flow culvert, wherein the inner wall surface of the S-bend convergence section and the expansion section form a second (22) profile of the inner wall surface of the secondary flow culvert pipe, and the outer wall surface of the S-bend convergence section is a second (21) profile of the outer wall surface of the secondary flow culvert pipe;
s3: s-bend single-side expansion spray pipe design of a third flow duct is carried out:
(1) Designing an S-bend convergence section of a third flow duct, and directly and rapidly predicting an accurate supersonic velocity initial line through an established convolutional neural network model;
(2) On the basis of a reconstructed supersonic initial line, a characteristic line method based on maximum thrust constraint is adopted to develop a unilateral expansion section design, the length and the maximum thrust constraint are given, an expansion section outlet of a third flow culvert pipe is constrained to be tangent to an outer wall surface outlet of a secondary flow culvert pipe, a core area and a spray pipe molded surface design are completed through progressive calculation of inner points and wall surface points, the core area and the spray pipe molded surface design are combined with an S-bend convergence section, the reverse design of the high-performance S-bend unilateral expansion spray pipe of the third flow culvert is realized, the inner wall surface of the S-bend convergence section and the expansion section form an inner wall surface three (12) molded line of the third flow culvert pipe, and the outer wall surface of the S-bend convergence section is an outer wall surface three (11) molded line of the secondary flow culvert pipe.
Claims (6)
1. The design method of the three-duct supersonic jet pipe configuration is characterized by comprising the following steps of:
S1: s-bend unilateral expansion spray pipe design of main flow duct is carried out:
1. the method comprises the following steps:
(1) S-bend convergent section design is carried out by adopting an S-bend spray pipe design method based on multi-parameter coupling;
The S-bend convergence section design process comprises the following steps: a. calculating a central line of the main flow jet pipe according to the LEE curve equation; b. giving a change rule of the cross-sectional area, and obtaining the cross-sectional area at each position along the way according to the areas of the inlet and the throat; c. performing rotary transformation on each section based on the central line; d. fitting to obtain inner and outer wall surface lines and obtaining an S-shaped convergence section;
(2) Obtaining a supersonic initial line of a throat region by adopting a conventional Soxhlet method, and designing a unilateral expansion section by adopting a characteristic line method on the basis of the supersonic initial line;
(3) Connecting the S-shaped convergent section with the unilateral expansion section to obtain a two-dimensional S-shaped unilateral expansion spray pipe, repeating the steps (1) - (3) to obtain a certain number of S-shaped unilateral expansion spray pipes with different configurations, and performing numerical simulation on the S-shaped unilateral expansion spray pipes with different configurations to obtain supersonic velocity initial line distribution data;
(4) Building a convolutional neural network model according to the supersonic initial line distribution data, inputting geometric appearance features, namely an S-bend convergence section profile and the supersonic initial line distribution features, into the convolutional neural network, building a mapping relation between the supersonic initial line distribution and the geometric appearance features through convolution and pooling processes, and reconstructing a supersonic initial line of the S-bend convergence section;
2. And (3) pre-estimating:
(1) For the S-bend convergence section which is input again, an accurate supersonic velocity initial line is directly and rapidly predicted through the established convolutional neural network model;
(2) On the basis of a reconstructed supersonic initial line, adopting a characteristic line method based on maximum thrust constraint to develop a unilateral expansion section design, completing the design of a core area and a spray pipe molded surface through progressive calculation of inner points and wall points under the given length and the maximum thrust constraint, and then combining the core area and the spray pipe molded surface with an S-bend convergence section;
S2: s-bend unilateral expansion spray pipe design of secondary flow culvert is carried out: s1, a mapping relation between an S-shaped convergence section and geometric shape features is obtained, and in the process, the pre-estimation design can be directly carried out;
(1) Designing an S-bend convergence section of the secondary flow culvert, and directly and rapidly predicting an accurate supersonic velocity initial line through an established convolutional neural network model;
(2) On the basis of a reconstructed supersonic initial line, adopting a characteristic line method based on maximum thrust constraint to develop a unilateral expansion section design, giving a length and maximum thrust constraint, and restricting the expansion section outlet of the secondary flow duct nozzle to be tangent with the outer wall surface outlet of the main flow duct nozzle, finishing the core area and nozzle profile design through progressive calculation of inner points and wall surface points, and then combining the core area and nozzle profile design with an S-bend convergence section;
s3: s-bend single-side expansion spray pipe design of a third flow duct is carried out:
(1) Designing an S-bend convergence section of a third flow duct, and directly and rapidly predicting an accurate supersonic velocity initial line through an established convolutional neural network model;
(2) On the basis of a reconstructed supersonic initial line, adopting a characteristic line method based on maximum thrust constraint to develop a unilateral expansion section design, giving a length and maximum thrust constraint, and constraining the expansion section outlet of the third flow culvert pipe to be tangent with the outer wall surface outlet of the secondary flow culvert pipe, finishing the core area and the spray pipe profile design through progressive calculation of inner points and wall surface points, and then combining the core area and the spray pipe profile design with an S-bend convergence section;
The three-duct supersonic jet pipe configuration is formed through the design of the steps S1-S3, and comprises a main flow duct (30), a secondary flow duct (20) and a third flow duct (10), wherein the main flow duct (30) is composed of an outer wall surface I (31) and a tail cone (32), the secondary flow duct (20) is composed of an outer wall surface II (21) and an inner wall surface II (22), and the third flow duct (10) is composed of an outer wall surface III (11) and an inner wall surface III (12).
2. The design method of the three-duct supersonic nozzle configuration according to claim 1, wherein the main duct (30), the secondary duct (20) and the third flow duct (10) are all S-bend single-side expansion nozzles consisting of S-bend convergent sections, throats and single-side expansion sections.
3. The method for designing a three-duct supersonic nozzle configuration according to claim 2, wherein the main duct (30) comprises an S-bend converging channel one (33), a throat one (34) and a single-side expanding channel one (35).
4. The method for designing a three-duct supersonic nozzle configuration according to claim 2, wherein the secondary flow duct (20) comprises a second S-bend converging channel (23), a second throat (24) and a second unilateral expanding channel (25).
5. The method for designing a three-duct supersonic nozzle configuration according to claim 2, wherein the third flow duct (10) comprises an S-bend converging channel three (13), a throat three (14) and a single-side expanding channel three (15).
6. The method for designing a three-duct supersonic nozzle configuration according to claim 1, wherein the designing process of the single-side expansion section of (1) in S1 comprises: a. calculating the flow parameters of the area determined by the initial line through the supersonic initial line until the boundary characteristic line of the area is calculated; b. calculating the area determined by the boundary characteristic line and the throat expansion section line; c. and calculating the supersonic section molded lines of the rest areas to obtain the unilateral expansion section.
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