A quick design method for flow path size of full annular cooling structure of convergent-divergent nozzle

Abstract

The application belongs to the field of aero-engine design, and particularly relates to a convergent-divergent nozzle full-ring cooling structure flow path size rapid design method. The method comprises the following steps: step one, determining a basic configuration of the convergent-divergent nozzle full-ring cooling structure; step two, obtaining design parameters of a ground full-afterburner state; step three, determining a convergent section cooling channel length according to the design parameters; step four, calculating a cooling channel outlet size; and step five, calculating a cooling channel inlet size. The convergent-divergent nozzle full-ring cooling structure flow path size rapid design method can quickly obtain all key sizes of a cooling flow path of a full-ring cooling scheme according to given design input through calculation, and overcomes the shortcomings of a long design period and a large workload of a traditional cooling scheme design method.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of aero-engine design, and particularly relates to a convergent-divergent nozzle full-ring cooling structure flow path size rapid design method. BACKGROUND

[0002] With the gradual increase of the exhaust temperature of an aero-engine, the temperature load on the flow passage components in the nozzle is higher and higher. In order to improve the cooling efficiency of the nozzle, the full-ring cooling scheme is gradually applied. The full-ring cooling scheme can form a circumferentially continuous cooling channel in the convergent section of the nozzle, so that the gas film is more uniform and covers the entire nozzle inner flow passage surface, greatly improving the cooling efficiency of the nozzle and the reliability of the nozzle.

[0003] The existing full-ring cooling scheme design method is to iteratively optimize the geometric model according to the results of three-dimensional CFD simulation, so that the cooling air flow and the cooling effect meet the design requirements. This method needs to repeatedly carry out the iterative process of geometric modeling, three-dimensional CFD simulation, result analysis and model optimization, which will make the design process too long and tedious. A rapid full-ring cooling scheme key structure size design method is urgently needed to quickly obtain the structure size parameters that meet the design requirements in the early design stage.

[0004] Therefore, it is desirable to have a technical solution to overcome or at least alleviate at least one of the aforementioned deficiencies of the prior art. SUMMARY

[0005] The purpose of the present application is to provide a convergent-divergent nozzle full-ring cooling structure flow path size rapid design method to solve at least one problem existing in the prior art.

[0006] The technical solution of the present application is:

[0007] A convergent-divergent nozzle full-ring cooling structure flow path size rapid design method, comprising:

[0008] Step one, obtaining the convergent-divergent nozzle full-ring cooling structure, determining the flow path size parameters of the convergent-divergent nozzle full-ring cooling structure, the flow path size parameters including the convergent section cooling channel length, the cooling channel outlet size and the cooling channel inlet size;

[0009] Step two, obtaining the design parameters of the ground full afterburner state;

[0010] Step three, determining the convergent section cooling channel length according to the design parameters;

[0011] Step four, calculating the cooling channel outlet size, comprising:

[0012] S41, calculating the cooling channel outlet width according to the design parameters;

[0013] S42, calculating the cooling passage cooling gas flow according to the cooling passage outlet width;

[0014] S43, obtaining the convergent section wall static pressure distribution through 2D CFD numerical simulation calculation;

[0015] S44, establishing a cooling passage outlet size and cooling gas flow relationship calculation model, and calculating the cooling passage outlet height according to the relationship calculation model and the convergent section cooling passage length;

[0016] Step five, calculating the cooling passage inlet size, comprising:

[0017] S51, calculating the cooling passage inlet height according to the design parameters;

[0018] S52, calculating the cooling passage inlet width according to the design parameters and the cooling passage cooling gas flow.

[0019] In at least one embodiment of the present application, the convergent-divergent nozzle full-ring cooling structure comprises a booster cylinder, a convergent section and a divergent section connected in sequence, the convergent section comprises a convergent adjusting fin assembly and a box-type convergent sealing fin, the convergent adjusting fin assembly and the box-type convergent sealing fin are arranged in a whole ring structure in a circumferential direction, the convergent adjusting fin assembly comprises a convergent adjusting fin bottom plate and a convergent adjusting fin heat shield located radially inside the convergent adjusting fin bottom plate, a adjusting fin cooling passage is formed between the convergent adjusting fin bottom plate and the convergent adjusting fin heat shield, and a sealing fin cooling passage is formed inside the box-type convergent sealing fin.

[0020] In at least one embodiment of the present application, in step two, the design parameters include aerodynamic design parameters and geometric design parameters, wherein,

[0021] The aerodynamic design parameters include: nozzle inlet core total temperature T t7 , nozzle inlet bypass total temperature T t17 , nozzle inlet core total pressure P t7 , nozzle inlet bypass total pressure P t17 , and maximum bypass cooling gas total flow

[0022] The geometric design parameters include: booster heat shield outlet height H jl , nozzle inlet radius R7, nozzle throat radius R8 and convergent section length Lc.

[0023] In at least one embodiment of the present application, in step three, the convergent section cooling passage length determined according to the design parameters comprises:

[0024] The convergent section cooling passage length L is:

[0025] L = a*L c

[0026] Wherein, Lc is the length of convergent section, a is 0.7-0.95.

[0027] In at least one embodiment of the present application, in S41, the calculation of the cooling passage outlet width according to the design parameters comprises:

[0028] Determining the cooling passage outlet width W of the sealing sheet according to the width of the box convergent sealing sheet m2 ;

[0029] Adjusting the cooling passage outlet width W of the sealing sheet t2 to:

[0030]

[0031] Wherein, R8 is the throat radius of the nozzle, n is the number of circumferential units, each circumferential unit includes a convergent adjustment sheet assembly and a box convergent sealing sheet.

[0032] In at least one embodiment of the present application, in S42, the calculation of the cooling gas flow rate of the cooling passage according to the cooling passage outlet width comprises:

[0033] Calculating the cooling gas flow rate allocated to each circumferential unit

[0034]

[0035] Wherein, is the maximum total flow rate of the outer bypass cooling gas;

[0036] The cooling gas flow rate of the adjustment sheet cooling passage outlet is:

[0037]

[0038] The cooling gas flow rate of the sealing sheet cooling passage outlet is:

[0039]

[0040] Wherein, c is the cooling gas flow rate ratio allocated to the unit circumferential length of the convergent adjustment sheet assembly and the box convergent sealing sheet.

[0041] In at least one embodiment of the present application, in S43, the convergent section wall surface static pressure distribution calculated by 2D CFD numerical simulation comprises:

[0042] Establishing a full-ring cooling structure model of the convergent-divergent nozzle to perform 2D CFD numerical simulation calculation to obtain the convergent section wall surface static pressure distribution:

[0043] P s = f(L)

[0044] Wherein, L is the length of the convergent section cooling passage.

[0045] In at least one embodiment of the present application, in S44, the calculation model of the relationship between the cooling passage outlet size and the cooling gas flow rate is established, and the cooling passage outlet height is calculated according to the calculation model and the length of the convergent section cooling passage, comprising:

[0046] The calculation model of the relationship between the cooling passage outlet size and the cooling gas flow rate is established:

[0047]

[0048]

[0049]

[0050]

[0051] According to the relationship calculation model, the relationship between the regulating vane cooling passage outlet height H t2 and the length of the convergent section cooling passage L is obtained:

[0052] H t2 = g1(L)

[0053] The length of the convergent section cooling passage L is substituted into the above formula to obtain the regulating vane cooling passage outlet height H t2 .

[0054] According to the relationship calculation model, the relationship between the sealing vane cooling passage outlet height H m2 and the length of the convergent section cooling passage L is obtained:

[0055] H m2 = g2(L)

[0056] The length of the convergent section cooling passage L is substituted into the above formula to obtain the sealing vane cooling passage outlet height H m2 .

[0057] Wherein, K is equal to 0.04042, P t17 is the total pressure of the outer duct at the inlet of the nozzle, T t7 is the total temperature of the inner duct at the inlet of the nozzle, k is the gas constant, and M a is the local Mach number.

[0058] In at least one embodiment of the present application, in S51, the cooling passage inlet height is calculated according to the design parameters, comprising:

[0059] The regulating vane cooling passage inlet height Ht1 is:

[0060] H t1 = H jl

[0061] Seal piece cooling channel entrance height H m1 is:

[0062] H m1 = H t1 -t t -t m

[0063] Wherein, H jl is the force shield outlet height, t t is the converging adjustment piece heat shield thickness, t m is the box converging seal piece thickness.

[0064] In at least one embodiment of the present application, in S52, the cooling channel entrance width is calculated according to the design parameters and the cooling channel cooling gas flow, comprising:

[0065] Seal piece cooling channel entrance width W m1 is:

[0066]

[0067] Adjustment piece cooling channel entrance width W t1 is:

[0068]

[0069] Wherein, R7 is the nozzle inlet radius.

[0070] The present application has at least the following beneficial technical effects:

[0071] The converging-diverging nozzle full-ring cooling structure flow path size rapid design method of the present application can quickly obtain all key sizes of the cooling flow path of the full-ring cooling scheme according to given design input through calculation, overcoming the shortcomings of long design period and large workload of traditional cooling scheme design methods. BRIEF DESCRIPTION OF DRAWINGS

[0072] Figure 1 is a converging-diverging nozzle full-ring cooling structure schematic diagram of one embodiment of the present application;

[0073] Figure 2 is a converging-diverging nozzle full-ring cooling structure cross-sectional view of one embodiment of the present application;

[0074] Figure 3 is the G-G view of Figure 2 ; and

[0075] Figure 4 is Figure 2 M-M view of

[0076] Figure 5 is a simplified model of the full annular cooling structure of the convergent-divergent nozzle according to an embodiment of the present application.

[0077] wherein:

[0078] 1 - convergent adjustment sheet bottom plate; 2 - convergent adjustment sheet heat shield; 3 - box type convergent sealing sheet. DETAILED DESCRIPTION

[0079] In order to make the purpose, technical scheme and advantages of the present application clearer, the technical scheme of the embodiments of the present application will be described in more detail below in combination with the drawings of the embodiments of the present application. In the drawings, the same or similar notations represent the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some of the embodiments of the present application, not all of the embodiments. The embodiments described below by reference to the drawings are exemplary and are intended to explain the present application, and cannot be understood as a limitation of the present application. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative labor fall within the scope of protection of the present application. The embodiments of the present application will be described in detail below in combination with the drawings.

[0080] In the description of the present application, it should be understood that the terms "center", "longitudinal", "transverse", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the purpose of facilitating the description of the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the scope of protection of the present application.

[0081] The embodiments of the present application will be described in detail below in combination with the drawings. Figures 1 to 5 The present application will be described in further detail.

[0082] The present application provides a rapid design method for flow path size of a full annular cooling structure of a convergent-divergent nozzle, comprising the following steps:

[0083] Step one, determine the flow path size parameters of the full annular cooling structure of the convergent-divergent nozzle, determine the flow path size parameters of the full annular cooling structure of the convergent-divergent nozzle that need to be designed, the flow path size parameters include the cooling channel length of the convergent section, the cooling channel outlet size and the cooling channel inlet size;

[0084] As Figures 1-4As shown, the convergent-divergent nozzle full-ring cooling structure includes a booster cylinder, a convergent section and a divergent section connected in sequence, the convergent section includes a convergent adjusting sheet assembly and a box-type convergent sealing sheet 3, the convergent adjusting sheet assembly and the box-type convergent sealing sheet 3 are arranged in a circumferential interval to form a whole ring structure, the convergent adjusting sheet assembly includes a convergent adjusting sheet bottom plate 1 and a convergent adjusting sheet heat shield 2 located radially inside the convergent adjusting sheet bottom plate 1, and a adjusting sheet cooling channel is formed between the convergent adjusting sheet bottom plate 1 and the convergent adjusting sheet heat shield 2, and a sealing sheet cooling channel is formed inside the box-type convergent sealing sheet 3.

[0085] The adjusting sheet cooling channel and the sealing sheet cooling channel are independent of each other, and the two kinds of cooling channels are distributed in a circumferential interval to form a circumferentially continuous full-ring cooling channel, and the outer annular cooling gas flowing between the booster cylinder A and the booster heat shield B is introduced into the divergent section, and a cooling gas film is formed in the divergent section to avoid the wall temperature of the divergent sealing sheet C and the divergent adjusting sheet D being too high.

[0086] In this application, the key sizes in the flow path of the convergent-divergent nozzle full-ring cooling structure need to be quickly designed, including the adjusting sheet cooling channel inlet height H t1 , the adjusting sheet cooling channel outlet height H t2 , the adjusting sheet cooling channel inlet width W t1 , the adjusting sheet cooling channel outlet width W t2 , the sealing sheet cooling channel inlet height H m1 , the sealing sheet cooling channel outlet height H m2 , the sealing sheet cooling channel inlet width W m1 , the sealing sheet cooling channel outlet width W m2 , the convergent section cooling channel length L, which is the length of the convergent adjusting sheet heat shield 2, and except for the adjusting sheet cooling channel outlet width W t2 which will change with the change of the nozzle throat radius R8, the other parameters will not change with the change of the engine state.

[0087] Step two, obtain the design parameters of the ground full-afterburner state;

[0088] Step three, determine the convergent section cooling channel length according to the design parameters;

[0089] Step four, calculate the cooling channel outlet size, including:

[0090] S41, calculate the cooling channel outlet width according to the design parameters;

[0091] S42, calculate the cooling channel cooling gas flow according to the cooling channel outlet width;

[0092] S43, obtain the convergent section wall static pressure distribution through 2D CFD numerical simulation calculation;

[0093] S44, a calculation model of the relationship between the cooling passage outlet size and the cooling gas flow rate is established, and the cooling passage outlet height is calculated according to the calculation model and the convergent section cooling passage length;

[0094] Step five, the cooling passage inlet size is calculated, including:

[0095] S51, the cooling passage inlet height is calculated according to the design parameters;

[0096] S52, the cooling passage inlet width is calculated according to the design parameters and the cooling gas flow rate of the cooling passage.

[0097] In the preferred embodiment of the present application, the ground full afterburner state is taken as the design point, and the design parameters include: the aerodynamic design parameters and the geometric design parameters, wherein the aerodynamic design parameters include: the nozzle inlet core total temperature T t7 , the nozzle inlet bypass total temperature T t17 , the nozzle inlet core total pressure P t7 , the nozzle inlet bypass total pressure P t17 , and the maximum bypass cooling gas total flow rate The geometric design parameters include: the afterburner screen outlet height H jl , the nozzle inlet radius R7, the nozzle throat radius R8, and the convergent section length Lc.

[0098] In the step three, the convergent section cooling passage length is determined according to the design parameters, including:

[0099] The convergent section cooling passage length L is:

[0100] L = α·L c

[0101] Wherein, Lc is the convergent section length, and α is generally 0.7-0.95.

[0102] The calculation process of the cooling passage outlet size of the full-ring cooling structure flow path size rapid design method of the convergent-divergent nozzle of the present application includes:

[0103] The size of the sealing piece cooling passage outlet width is determined by the width of the box convergent sealing piece, and the size of the adjusting piece cooling passage outlet width is determined by the nozzle throat radius and the sealing piece cooling passage outlet width.

[0104] S41, the cooling passage outlet width is calculated according to the design parameters, including:

[0105] The sealing piece cooling passage outlet width W m2 is determined according to the width of the box convergent sealing piece;

[0106] The adjusting piece cooling passage outlet width W t2 is:

[0107]

[0108] where R8 is the throat radius of the nozzle, n is the number of circumferential units, each circumferential unit includes one convergent adjustment sheet assembly and one box convergent seal sheet.

[0109] S42, calculating the cooling gas flow rate of the cooling channel according to the cooling channel outlet width includes:

[0110] Calculating the cooling gas flow rate allocated to each circumferential unit

[0111]

[0112] where, is the maximum total bypass cooling gas flow rate;

[0113] The cooling gas flow rate of each adjustment sheet cooling channel outlet is:

[0114]

[0115] The cooling gas flow rate of each seal sheet cooling channel outlet is:

[0116]

[0117] where c is the cooling gas flow rate ratio allocated to the unit circumferential length of the convergent adjustment sheet assembly and the box convergent seal sheet. The size of c is determined according to the strength and life requirements of the divergent adjustment sheet D and the divergent seal sheet C, and is generally taken as 1.0-1.3:

[0118] S43, obtaining the convergent section wall static pressure distribution by 2D CFD numerical simulation calculation includes:

[0119] Establishing a full-ring cooling structure model of the convergent-divergent nozzle to perform 2D CFD numerical simulation calculation to obtain the convergent section wall static pressure distribution:

[0120] P s = f(L)

[0121] where L is the length of the convergent section cooling channel.

[0122] In this embodiment, a simplified convergent-divergent nozzle model as shown in Figure 5 is used for 2D CFD numerical simulation calculation. The nozzle inlet parameters are consistent with the inner core parameters in the design input, and the outlet is set to 1 atmosphere. The nozzle sizes R7, R8 and Lc are consistent with the given design input. The convergent section wall static pressure distribution of the nozzle is obtained by calculation simulation.

[0123] Further, S44, a relationship calculation model of the cooling passage outlet size and the cooling gas flow rate is established, and the cooling passage outlet height is calculated according to the relationship calculation model and the convergent section cooling passage length, including:

[0124] The relationship calculation model of the cooling passage outlet size and the cooling gas flow rate is established:

[0125]

[0126]

[0127]

[0128]

[0129] According to the relationship calculation model, the relationship of the adjusting sheet cooling passage outlet height H t2 and the convergent section cooling passage length L is obtained:

[0130] H t2 = g1(L)

[0131] The convergent section cooling passage length L is substituted into the above formula, and the adjusting sheet cooling passage outlet height H t2 is obtained.

[0132] According to the relationship calculation model, the relationship of the sealing sheet cooling passage outlet height H m2 and the convergent section cooling passage length L is obtained:

[0133] H m2 = g2(L)

[0134] The convergent section cooling passage length L is substituted into the above formula, and the sealing sheet cooling passage outlet height H m2 is obtained.

[0135] Wherein, K is equal to 0.04042, P t17 is the total pressure of the outer duct at the nozzle inlet, T t7 is the total temperature of the inner duct at the nozzle inlet, k is the gas constant, taken as 1.4, M a is the local Mach number.

[0136] By solving the four equations in the relationship calculation model, the relationship formulas of the adjusting sheet cooling passage outlet height H t2 , the sealing sheet cooling passage outlet height H m2 and the convergent section cooling passage length L are obtained, and the numerical value of L is substituted into the corresponding relationship formula, so that the adjusting sheet cooling passage outlet height H t2 and the sealing sheet cooling passage outlet height H m2 satisfying the flow distribution requirement are obtained.

[0137] Finally, the cooling passage inlet size is calculated, the process is as follows:

[0138] S51, the cooling passage inlet height is calculated according to the design parameters, including:

[0139] The regulating fin cooling passage inlet height H t1 is:

[0140] H t1 = H jl

[0141] The sealing fin cooling passage inlet height H m1 is:

[0142] H m1 = H t1 -t t -t m

[0143] Wherein, H jl is the exit height of the heat shield, t t is the thickness of the converging regulating fin heat shield, t m is the thickness of the box converging sealing fin.

[0144] The design principle of the cooling passage inlet width is: it is necessary to ensure that the flow per unit circumferential length of the regulating fin cooling passage and the sealing fin cooling passage is consistent, so as to ensure that the circumferential distribution of the exit cooling gas flow of the heat shield is uniform; At the same time, the cooling passage inlet width needs to meet the geometric constraint condition. The cooling passage inlet width meeting the above requirements is as follows:

[0145] S52, the cooling passage inlet width is calculated according to the design parameters and the cooling gas flow of the cooling passage, including:

[0146] The sealing fin cooling passage inlet width W m1 is:

[0147]

[0148] The regulating fin cooling passage inlet width W t1 is:

[0149]

[0150] Wherein, R7 is the entrance radius of the nozzle.

[0151] The full-ring cooling structure flow path size rapid design method of the convergent-divergent nozzle of the application determines the unit circumferential length flow ratio of the regulating vane cooling channel and the seal vane cooling channel outlet according to the different cooling requirements of the regulating vane and the seal vane, and further determines the cooling gas flow of the regulating vane cooling channel and the seal vane cooling channel; according to the cooling gas flow size of the cooling channel and the convergent section wall surface static pressure distribution, the cooling channel outlet height meeting the flow requirement is quickly calculated; and the cooling channel inlet width is quickly calculated according to the principle of ensuring the circumferential uniform distribution of the afterburner heat shield outlet cooling gas flow. The application can quickly obtain the full-ring cooling flow path size parameters meeting the requirements according to the design input, and compared with the traditional three-dimensional simulation iterative optimization method, the design cycle is greatly shortened and the design efficiency is improved.

[0152] The above is only a specific embodiment of the application, but the protection scope of the application is not limited thereto, any person skilled in the art can easily think of changes or replacements within the technical range disclosed by the application, which should be covered within the protection scope of the application. Therefore, the protection scope of the application should be subject to the protection scope of the claims.

Claims

1. A method for rapid design of flow path dimensions for a full-ring cooling structure of a converging-expanding nozzle, characterized in that, include: Step 1: Obtain the full-ring cooling structure of the converging and expanding nozzle, and determine the flow path size parameters of the full-ring cooling structure of the converging and expanding nozzle. The flow path size parameters include the length of the converging section cooling channel, the outlet size of the cooling channel, and the inlet size of the cooling channel. Step 2: Obtain the design parameters for the ground under full applied force. Step 3: Determine the length of the convergence section cooling channel based on the design parameters; Step 4: Calculate the cooling channel outlet dimensions, including: S41. Calculate the cooling channel outlet width based on the design parameters; S42. Calculate the cooling air flow rate of the cooling channel based on the width of the cooling channel outlet; S43. The static pressure distribution on the wall of the convergence section is obtained by 2D CFD numerical simulation. S44. Establish a calculation model for the relationship between the cooling channel outlet size and the cooling air flow rate, and calculate the cooling channel outlet height based on the calculation model and the length of the convergent cooling channel. Step 5: Calculate the inlet dimensions of the cooling channel, including: S51. Calculate the cooling channel inlet height based on the design parameters; S52. Calculate the inlet width of the cooling channel based on the design parameters and the cooling air flow rate of the cooling channel.

2. The rapid design method for flow path dimensions of the full-ring cooling structure of the converging and expanding nozzle according to claim 1, characterized in that, The full-ring cooling structure of the converging and expanding nozzle includes a booster cylinder, a converging section, and an expanding section connected in sequence. The converging section includes a converging adjustment plate assembly and a box-type converging sealing plate (3). The converging adjustment plate assembly and the box-type converging sealing plate (3) are arranged circumferentially to form a complete ring structure. The converging adjustment plate assembly includes a converging adjustment plate base plate (1) and a converging adjustment plate heat insulation screen (2) located radially inside the converging adjustment plate base plate (1). A cooling channel for the adjustment plate is formed between the converging adjustment plate base plate (1) and the converging adjustment plate heat insulation screen (2). A cooling channel for the sealing plate is formed inside the box-type converging sealing plate (3).

3. The rapid design method for flow path dimensions of the full-ring cooling structure of the converging and expanding nozzle according to claim 2, characterized in that, In step two, the design parameters include: aerodynamic design parameters and geometric design parameters, wherein, The aerodynamic design parameters include: total internal temperature T at the nozzle inlet. t7 Total temperature T of nozzle inlet bypass t17 Total pressure P at the nozzle inlet t7 Total pressure P of nozzle inlet outer bypass t17 and the maximum total flow rate of the bypass cooling air The geometric design parameters include: the outlet height H of the heat insulation screen. jl The nozzle inlet radius R7, the nozzle throat radius R8, and the convergence section length Lc are all specified.

4. The rapid design method for flow path dimensions of the full-ring cooling structure of the converging and expanding nozzle according to claim 3, characterized in that, Step three, determining the length of the convergence section cooling channel based on the design parameters, includes: The length L of the cooling channel in the convergence section is: L=α·L c Where Lc is the length of the convergence segment, and α is 0.7 to 0.

95.

5. The rapid design method for flow path dimensions of the full-ring cooling structure of the converging and expanding nozzle according to claim 4, characterized in that, In S41, calculating the cooling channel outlet width based on the design parameters includes: The width W of the cooling channel outlet of the sealing sheet is determined based on the width of the box-type convergent sealing sheet. m2 ; Adjusting the width of the cooling channel outlet W t2 for: Where R8 is the nozzle throat radius, n is the number of circumferential units, and each circumferential unit includes a convergence adjustment plate assembly and a box-type convergence sealing plate.

6. The rapid design method for flow path dimensions of the full-ring cooling structure of the converging and expanding nozzle according to claim 5, characterized in that, In S42, calculating the cooling air flow rate of the cooling channel based on the width of the cooling channel outlet includes: Calculate the cooling air flow rate allocated to each circumferential unit. in, This represents the maximum total flow rate of the outer bypass cooling air. Adjust the flow rate of cooling air flowing out of the cooling channel outlet. for: The cooling gas flow rate exiting the cooling channel of the sealing plate is: Where c is the ratio of cooling air flow rate distributed per unit circumferential length between the convergence regulating plate assembly and the box-type convergence sealing plate.

7. The rapid design method for flow path dimensions of the full-ring cooling structure of the converging and expanding nozzle according to claim 6, characterized in that, In S43, the static pressure distribution on the convergence segment wall obtained through 2D CFD numerical simulation includes: A full-ring cooling structure model of the converging-diverging nozzle was established and 2D CFD numerical simulation was performed to obtain the static pressure distribution on the wall of the convergence section. P s =f(L) Where L is the length of the cooling channel in the convergence section.

8. The rapid design method for flow path dimensions of the full-ring cooling structure of the converging and expanding nozzle according to claim 7, characterized in that, In S44, establishing a calculation model for the relationship between the cooling channel outlet size and the cooling air flow rate, and calculating the cooling channel outlet height based on the calculation model and the length of the convergent cooling channel section, includes: Establish a calculation model for the relationship between cooling channel outlet size and cooling air flow rate: Based on the aforementioned relationship calculation model, the outlet height H of the regulating plate cooling channel is obtained. t2 Relationship with the length L of the convergent cooling channel: H t2 =g1(L) Substituting the length L of the convergent cooling channel into the above formula, we obtain the outlet height H of the regulating plate cooling channel. t2 ; Based on the aforementioned relationship calculation model, the outlet height H of the sealing plate cooling channel is obtained. m2 Relationship with the length L of the convergent cooling channel: H m2 =g2(L) Substituting the length L of the converging cooling channel into the above formula, we obtain the outlet height H of the sealing plate cooling channel. m2 ; Where K equals 0.04042, P t17 T is the total pressure of the nozzle inlet bypass. t7 The total internal temperature of the nozzle inlet is given by k, where k is the gas constant and M is the total internal temperature. a This is the local Mach number.

9. The rapid design method for flow path dimensions of the full-ring cooling structure of the converging and expanding nozzle according to claim 8, characterized in that, In S51, calculating the cooling channel inlet height based on the design parameters includes: Adjusting the inlet height H of the cooling channel t1 for: H t1 =H jl Sealing plate cooling channel inlet height H m1 for: H m1 =H t1 -t t -t m Among them, H jl To increase the outlet height of the heat insulation screen, t t To converge the thickness of the heat insulation screen, t m The thickness of the box-type convergent sealing sheet.

10. The rapid design method for flow path dimensions of the full-ring cooling structure of the converging and expanding nozzle according to claim 9, characterized in that, In S52, calculating the cooling channel inlet width based on the design parameters and the cooling channel cooling air flow rate includes: Sealing plate cooling channel inlet width W m1 for: Adjusting the inlet width W of the cooling channel t1 for: Where R7 is the nozzle inlet radius.

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