Aero-engine center cone wall surface heat exchanger structure and design method thereof

Abstract

The present application relates to the field of gas turbine engine design, and discloses an aero-engine center cone wall heat exchanger structure and a design method thereof, the heat exchanger structure comprising an air inlet manifold, an air outlet manifold and a plurality of annular flow channels, the plurality of annular flow channels being arranged inside the center cone wall, each annular flow channel being provided with an inlet end and an outlet end, the inlet end of the first-stage annular flow channel close to the center cone taper portion being in communication with the air inlet manifold, the outlet end of each annular flow channel being in communication with the inlet end of the next-stage annular flow channel, and the outlet end of the last-stage annular flow channel downstream of the center cone wall being in communication with the air outlet manifold. The present application utilizes the cooling airflow to fully exchange heat in the plurality of annular flow channels of the center cone, so as to greatly reduce the wall temperature of the center cone, thereby greatly reducing the infrared radiation intensity of the engine. In addition, the structure is compact, effectively utilizes the wall space of the center cone of the aero-engine, reduces the volume and weight of the heat exchanger, and is beneficial to the overall performance improvement of the aero-engine.

Description

Technical Field

[0001] This invention relates to the field of gas turbine engine design, and discloses a structure and design method for a central cone wall heat exchanger for an aero-engine. Background Technology

[0002] As aero-engine performance continues to improve, turbine inlet temperatures are also rising, leading to difficulties in cooling hot-end components and placing higher demands on cooling systems. Traditional aero-engine cooling systems primarily rely on air, fuel, and lubricating oil cooling, but these methods often fall short of meeting the demands for efficient cooling under extreme operating conditions. Given that the rate of increase in material temperature resistance lags behind the rate of increase in turbine inlet temperature, exploring new and more promising efficient cooling technologies is essential.

[0003] The temperature of the afterburner center cone is relatively high, and the air system flow path is generally designed for convection or film cooling. However, because the afterburner center cone is located after the turbine outlet, the airflow pressure is relatively high, and the cooling air must simultaneously meet high pressure and low temperature conditions. Therefore, the temperature reduction of the center cone wall using air convection or film cooling is limited. For example, if the air from the fan component outlet is drawn into the center cone for cooling, the temperature of the fan component outlet air is still high, and the cooled center cone wall temperature reaches over 600°C, which is still a high temperature, and the infrared radiation intensity is also high. The afterburner center cone accounts for a large proportion of the infrared radiation source at the engine exhaust. Using efficient cooling technology to reduce the surface temperature of the center cone can effectively reduce the infrared radiation intensity of the center cone surface. For example, reducing the center cone wall temperature by 300°C can reduce its radiation intensity by more than 70%, but air cooling cannot achieve this temperature reduction. Summary of the Invention

[0004] The purpose of this invention is to provide a heat exchanger structure and design method for the central cone wall of an aero-engine, which can achieve a significant reduction in the central cone wall temperature, thereby greatly reducing the intensity of the engine's rearward infrared radiation.

[0005] To achieve the above-mentioned technical effects, the technical solution adopted by the present invention is as follows:

[0006] A heat exchanger structure for the central cone wall of an aero-engine, wherein the central cone is a hollow cone-shaped structure, comprising:

[0007] The intake manifold has one end connected to an air source, which is used to introduce the cooling airflow from the air source to the central cone section.

[0008] The exhaust manifold is used to discharge the cooling airflow introduced into the cone position to the outside of the central cone;

[0009] The annular flow channels are arranged inside the wall of the central cone and are equidistantly distributed along the wall of the central cone. Each annular flow channel is provided with an inlet end and an outlet end, and the inlet end and the outlet end of the same annular flow channel are symmetrically distributed on both sides of the corresponding annular flow channel. The inlet end of the first-stage annular flow channel near the cone part of the central cone is connected to the intake manifold, the outlet end of each annular flow channel is connected to the inlet end of the next-stage annular flow channel, and the outlet end of the last-stage annular flow channel downstream of the central cone wall is connected to the exhaust manifold.

[0010] Furthermore, an air collection chamber is provided between the inlet end of the main air intake pipe and the inlet end of the first-stage annular flow channel, and between the two interconnected inlet ends and outlet ends.

[0011] Furthermore, each annular flow channel includes multiple annular airflow channels that communicate with the corresponding air collection chamber.

[0012] Furthermore, the cross-sectional area of ​​the main intake pipe is greater than or equal to the cross-sectional area of ​​each of the air collecting chambers, and the cross-sectional area of ​​each of the air collecting chambers is greater than or equal to the sum of the cross-sectional areas of all annular flow channels; the cross-section of the air collecting chamber is a cross-section perpendicular to the flow direction of the airflow within the air collecting chamber.

[0013] Furthermore, the cooling gas flow in the gas source is air, hydrogen, or supercritical carbon dioxide.

[0014] To achieve the above-mentioned technical effects, the present invention also provides a design method for a heat exchanger structure on the central cone wall of an aero-engine, used to obtain the aforementioned heat exchanger structure on the central cone wall of an aero-engine, comprising:

[0015] Based on the performance parameters of the incoming air and the size of the working channel of the central cone under the working conditions of the central cone, the first heat transfer coefficient between the outer wall of the central cone and the incoming air at the corresponding circumferential position of each annular channel is obtained by analysis, and the first analytical model of the heat transfer between the incoming air and the outer wall of the central cone at the corresponding circumferential position of each annular channel is constructed.

[0016] Given the initial values ​​of the annular flow channel size parameters, the second heat transfer coefficient between the cooling airflow and the annular flow channel wall is obtained by analyzing the cooling airflow performance parameters under the initial values ​​of the annular flow channel size parameters; and a second analytical model of the heat transfer of cooling airflow in a single annular flow channel is constructed based on the inlet temperature, outlet temperature, and wall temperature of the annular flow channel.

[0017] Based on the thermal conductivity of the central cone material and the distance between the outer wall of the central cone and the annular flow channel, a third analytical model for heat exchange between the outer wall of the central cone and the wall of the annular flow channel is constructed.

[0018] Make the output values ​​of the first analysis model, the second analysis model and the third analysis model equal at the same position of the annular flow channel, and perform a simultaneous analysis of the first analysis model, the second analysis model and the third analysis model to obtain the temperature of the outer wall of the central cone corresponding to each circumferential position of the annular flow channel;

[0019] Using the temperature of the outer wall of the central cone corresponding to each annular flow channel position as input, the temperature distribution of the entire outer wall of the central cone is obtained through simulation analysis. If the average temperature of the entire outer wall of the central cone is within the design target temperature range, the given initial value meets the design requirements; otherwise, the annular flow channel size parameters are adjusted until the average temperature of the entire outer wall of the central cone is within the design target temperature range.

[0020] Furthermore, the first heat transfer coefficient between the outer wall of the central cone at the corresponding circumferential position of each annular flow channel and the incoming air is... ,in For the first The first heat transfer coefficient between the outer wall of the central cone corresponding to the circumferential position of the annular flow channel and the incoming air. For the first The radial height of the working channel section on the outer wall of the central cone corresponding to the circumferential position of each annular flow channel. The thermal conductivity of the incoming air. For the first The incoming air velocity at the working channel section of the outer wall of the central cone corresponding to the circumferential position of the annular flow channel. The Prandtl number of the incoming airflow;

[0021] The first analytical model for the heat exchange between the incoming air and the outer wall of the central cone at each circumferential position of the annular flow channel is as follows: ,in, For the first The incoming air at each circumferential position of the annular flow channel exchanges heat with the outer wall of the central cone. For the first Each annular flow channel corresponds to the heat exchange area between the incoming airflow at the circumferential position and the outer wall of the central cone. The total temperature of the incoming air intake. For the first Temperature of the outer wall surface of the central cone corresponding to the circumferential position of each annular flow channel The emissivity of the material on the outer wall of the central cone. is the Stefan Boltzmann constant.

[0022] Furthermore, given the initial values ​​of the annular flow channel size parameters, the second heat transfer coefficient between the cooling airflow and the annular flow channel wall is... ,in, For the first The second heat transfer coefficient between the cooling airflow and the annular channel wall within the annular channel. For the first The diameter of the annular flow channel, The thermal conductivity of the cooling airflow. For the first The flow rate of the cooling airflow within the annular flow channel, The Prandtl number is the number of the cooling airflow.

[0023] The second analytical model for heat transfer of cooling airflow in a single annular channel, based on the inlet temperature, outlet temperature, and wall temperature of the annular channel, is as follows: In the formula, For the first The cooling airflow in the annular flow channel exchanges heat. For the first The inner wall area of ​​the annular flow channel For the first Temperature of the inner wall surface of the annular flow channel For cooling airflow in the first The intake temperature of the annular flow channel For cooling airflow in the first The outlet temperature of each annular flow channel, where 'a' is the axial distance between adjacent annular flow channels. Let be the thermal conductivity of the central cone material, and tanh be the hyperbolic tangent function. , Let be the independent variable of the hyperbolic tangent function.

[0024] Furthermore, the third analytical model for heat exchange between the outer wall of the central cone and the wall of the annular flow channel is constructed as follows: In the formula, For the first The heat exchange between the outer wall of the central cone at each circumferential position of the annular flow channel and the wall of the annular flow channel is as follows: The thermal conductivity of the central cone material is... For the first The temperature of the outer wall surface of the central cone at the circumferential position of each annular flow channel. For the first Temperature of the inner wall surface of the annular flow channel For the first The wall thickness between the outer wall of the central cone and the wall of the annular flow channel at the circumferential position of each annular flow channel.

[0025] Furthermore, the method for obtaining the average temperature of the entire outer wall surface of the central cone is as follows: integrate the temperature of the central cone along the airflow path of the air source, and calculate the average temperature of the entire outer surface of the central cone.

[0026] Compared with the prior art, the beneficial effects of this invention are:

[0027] 1. This invention utilizes the cooling airflow to fully exchange heat in multiple annular channels of the central cone, achieving a significant reduction in the central cone wall temperature, thereby substantially reducing the intensity of the engine's rearward infrared radiation. Furthermore, this compact structure effectively utilizes the wall space of the aero-engine's central cone, reducing the volume and weight of the heat exchanger, which is beneficial for improving the overall performance of the aero-engine.

[0028] 2. This invention comprehensively considers multiple factors such as mainstream temperature, channel size, and airflow performance, and constructs a first analytical model that can accurately reflect the cooling effect of incoming air on the outer wall of the central cone, a second analytical model that reflects the heat transfer of airflow from a single annular channel, and a third analytical model that considers factors such as the thermal conductivity of the central cone material and the distance between the outer wall of the central cone and the annular channel. These models are used to accurately predict the temperature of the outer wall of the central cone corresponding to each annular channel position. The temperature distribution of the entire outer wall of the central cone is then used as the criterion for determining whether the size of the annular channel meets the design requirements. This not only improves the accuracy of the design but also greatly shortens the design cycle, providing strong support for the optimized design of the heat exchanger on the central cone wall of an aero-engine. Attached Figure Description

[0029] Figure 1 This is a schematic diagram of the heat exchanger structure on the central cone wall of the aero-engine in the embodiment;

[0030] Figure 2 This is a schematic diagram showing the flow direction of airflow in each annular channel in the embodiment.

[0031] Among them, 1. intake manifold; 2. center cone; 3. exhaust manifold; 4. annular flow channel; 5. air collection chamber. Detailed Implementation

[0032] The present invention will now be described in further detail with reference to the embodiments and accompanying drawings. However, this should not be construed as limiting the scope of the above-described subject matter of the present invention to the following embodiments; all technologies implemented based on the content of the present invention fall within the scope of the present invention.

[0033] Example

[0034] See Figure 1 and Figure 2 A heat exchanger structure for the central cone wall of an aero-engine, wherein the central cone is a hollow cone structure, comprising:

[0035] The main intake pipe 1 is connected to an air source at one end, and is used to introduce the airflow from the air source to the conical part of the central cone 2.

[0036] The exhaust manifold 3 is used to discharge the airflow introduced into the cone position to the outside of the central cone 2;

[0037] Annular flow channels 4 are provided inside the wall of the central cone 2 and are equidistantly distributed along the wall of the central cone 2. Each annular flow channel 4 is provided with an inlet end and an outlet end, and the inlet end and the outlet end of the same annular flow channel 4 are symmetrically distributed on both sides of the corresponding annular flow channel 4. The inlet end of the first-stage annular flow channel 4 near the cone part of the central cone 2 is connected to the intake manifold 1, the outlet end of each annular flow channel 4 is connected to the inlet end of the next-stage annular flow channel 4, and the outlet end of the last-stage annular flow channel 4 downstream of the wall of the central cone 2 is connected to the exhaust manifold 3.

[0038] This embodiment uses supercritical carbon dioxide as the gas source to illustrate the working principle of the heat exchanger structure on the wall of the aero-engine center cone 2 of the present invention. See also... Figure 2 The arrows in the diagram indicate the airflow direction. The flow path of supercritical carbon dioxide in the heat exchanger on the wall of the central cone 2 is as follows: supercritical carbon dioxide enters the conical part of the central cone 2 from the intake manifold 1, then enters the first annular flow channel 4 near the conical part of the central cone 2, and then enters the next-stage annular flow channel 4 from the outlet end of the first annular flow channel 4; subsequently, it passes through the outlet end of the previous-stage annular flow channel 4 and enters the next-stage annular flow channel 4 in sequence. The airflow converges at the outlet end of the last-stage annular flow channel 4 and flows out from the exhaust manifold 3. This embodiment utilizes cooling airflow (such as supercritical carbon dioxide) to fully exchange heat in multiple annular flow channels 4 of the central cone 2, improving heat exchange efficiency and achieving a significant reduction in the wall temperature of the central cone 2, thereby significantly reducing the intensity of the engine's rearward infrared radiation. In addition, this structure is compact, effectively utilizes the wall space of the aero-engine's central cone 2, reduces the volume and weight of the heat exchanger, and is beneficial to the overall performance improvement of the aero-engine.

[0039] In this embodiment, gas collecting chambers 5 are provided between the inlet end of the main inlet pipe 1 and the inlet end of the first-stage annular flow channel 4, and between the two interconnected inlet ends and outlet ends. Supercritical carbon dioxide in the main inlet pipe 1 first enters the gas collecting chamber 5, and through the buffering and distribution function of the gas collecting chamber 5, it can smoothly flow into the inlet end of the first-stage annular flow channel 4. Similarly, between the two interconnected annular flow channels 4, the gas collecting chamber 5 also serves to transition and distribute the airflow, ensuring that supercritical carbon dioxide can smoothly enter the next-stage annular flow channel 4 from the outlet end of the previous-stage annular flow channel 4. This contributes to the uniform distribution and flow of supercritical carbon dioxide in the heat exchanger structure, not only improving the stability of the airflow but also further enhancing the heat exchange efficiency.

[0040] In this embodiment, each annular flow channel 4 includes multiple annular airflow channels connected to the corresponding gas collection chamber 5. These annular airflow channels are evenly distributed on the wall of the central cone 2, which increases the heat exchange area and heat transfer coefficient, while ensuring the structural strength under supercritical carbon dioxide high pressure conditions. Thus, with the outer shape and wall thickness of the central cone 2 remaining almost unchanged, supercritical carbon dioxide can fully exchange heat with the wall of the central cone 2, thereby maximizing the heat exchange efficiency.

[0041] In this embodiment, the cross-sectional area of ​​the main intake pipe 1 is greater than or equal to the cross-sectional area of ​​each of the gas collecting chambers 5, and the cross-sectional area of ​​each of the gas collecting chambers 5 is greater than or equal to the sum of the cross-sectional areas of all the annular flow channels 4; the cross-section of the gas collecting chamber 5 is a cross-section perpendicular to the flow direction of the airflow within the gas collecting chamber 5. While achieving cooling of the entire surface of the central cone 2, the design of the flow area ratio between the gas collecting chambers 5 and the microchannels (annular airflow channels) achieves a uniform supercritical carbon dioxide flow distribution and a low carbon dioxide pressure loss, resulting in uniform cooling of the central cone 2 wall surface.

[0042] Based on the same inventive concept, this embodiment also provides a design method for a heat exchanger structure on the central cone wall of an aero-engine, including:

[0043] Step 1: Based on the performance parameters of the incoming air under the working conditions of the central cone 2 and the working channel size of the central cone 2, analyze and obtain the first heat transfer coefficient between the outer wall of the central cone 2 and the incoming air at the corresponding circumferential position of each annular channel 4, and construct the first analytical model of the heat transfer between the incoming air and the outer wall of the central cone 2 at the corresponding circumferential position of each annular channel 4.

[0044] In this embodiment, the first heat transfer coefficient between the outer wall of the central cone 2 at the corresponding circumferential position of each annular flow channel 4 and the incoming air is... ,in For the first The first heat transfer coefficient between the outer wall of the central cone 2 corresponding to the circumferential position of the four annular flow channels and the incoming air. For the first The radial height of the working channel section on the outer wall of the central cone 2 at the 4 circumferential positions of the annular flow channel. The thermal conductivity of the incoming air. For the first The air velocity at the working channel section of the outer wall of the central cone 2 corresponding to the 4 circumferential positions of the annular flow channel is as follows: The Prandtl number of the incoming airflow;

[0045] The first analytical model for the heat exchange between the incoming air and the outer wall of the central cone 2 at the four circumferential positions of each annular flow channel is as follows: ,in, For the first The incoming air at the four circumferential positions of the annular flow channel exchanges heat with the outer wall of the central cone 2. For the first The heat exchange area between the incoming airflow at the circumferential position of each annular flow channel 4 and the outer wall of the central cone 2. The total temperature of the incoming air intake. For the first Temperature of the outer wall surface of the central cone 2 corresponding to the 4 circumferential positions of the annular flow channel The emissivity of the outer wall material of the central cone 2, is the Stefan Boltzmann constant.

[0046] Step 2: Under the given initial values ​​of the size parameters of the annular flow channel 4, the second heat transfer coefficient between the cooling airflow and the wall of the annular flow channel 4 is obtained by analyzing the performance parameters of the cooling airflow under the initial values ​​of the size parameters of the annular flow channel 4; and a second analytical model of the heat transfer of the cooling airflow in a single annular flow channel 4 is constructed based on the inlet temperature, outlet temperature, and wall temperature of the annular flow channel 4.

[0047] In this embodiment, under the given initial values ​​of the annular flow channel 4 size parameters, the second heat transfer coefficient between the cooling airflow and the wall of the annular flow channel 4 is... ,in, For the first The second heat transfer coefficient between the cooling airflow inside the annular flow channel 4 and the wall of the annular flow channel 4. For the first The diameter of the annular flow channel 4, The thermal conductivity of the cooling airflow. For the first The flow rate of the cooling airflow within the annular flow channel 4 The Prandtl number is the number of the cooling airflow.

[0048] The second analytical model for heat transfer of cooling airflow in a single annular flow channel 4, based on the inlet temperature, outlet temperature, and wall temperature of the annular flow channel 4, is as follows: In the formula, For the first The cooling airflow in the four annular channels exchanges heat. For the first The inner wall area of ​​each annular flow channel 4 For the first Temperature of the inner wall surface of the four annular flow channels For cooling airflow in the first The intake temperature of the annular flow channel 4 For cooling airflow in the first The outlet temperature of each annular flow channel 4, where 'a' is the axial distance between adjacent annular flow channels 4. Let be the thermal conductivity of the material in the central cone 2, and tanh be the hyperbolic tangent function. , Let be the independent variable of the hyperbolic tangent function.

[0049] Step 3: Based on the thermal conductivity of the material of the central cone 2 and the distance between the outer wall of the central cone 2 and the annular flow channel 4, construct a third analytical model for the heat exchange between the outer wall of the central cone 2 and the wall of the annular flow channel 4.

[0050] In this embodiment, the third analytical model for heat exchange between the outer wall of the central cone 2 and the wall of the annular flow channel 4 is as follows: In the formula, For the first The outer wall of the central cone 2 at the circumferential position of each annular flow channel 4 exchanges heat with the wall of the annular flow channel 4. The thermal conductivity of the material of the central cone 2 is... For the first The outer wall surface temperature of the central cone 2 at the circumferential position of each annular flow channel 4 For the first Temperature of the inner wall surface of the four annular flow channels For the first The wall thickness between the outer wall of the central cone 2 and the wall of the annular flow channel 4 at the circumferential position of the annular flow channel 4.

[0051] Step 4: Make the output values ​​of the first analysis model, the second analysis model, and the third analysis model at the same position of the annular flow channel 4 equal, and perform a simultaneous analysis of the first analysis model, the second analysis model, and the third analysis model to obtain the outer wall temperature of the central cone 2 corresponding to each circumferential position of the annular flow channel 4.

[0052] In this embodiment, let The first, second, and third analytical models are combined for analysis to obtain the outer wall temperature of the central cone 2 corresponding to the circumferential position of each annular flow channel.

[0053] Step 5: Using the temperature of the outer wall of the central cone 2 corresponding to each position of the annular flow channel 4 as input, obtain the temperature distribution of the entire outer wall of the central cone 2 through simulation analysis. If the average temperature of the entire outer wall of the central cone 2 is within the design target temperature range, the given initial value meets the design requirements. Otherwise, adjust the size parameters of the annular flow channel 4 until the average temperature of the entire outer wall of the central cone 2 is within the design target temperature range.

[0054] In this embodiment, the method for obtaining the average temperature of the outer wall of the entire central cone 2 is as follows: the temperature of the central cone 2 along the airflow path of the air source is integrated to calculate the average temperature of the outer surface of the entire central cone 2.

[0055] In this embodiment, the structural design of the heat exchanger on the wall of the aero-engine center cone 2 comprehensively considers multiple factors such as mainstream temperature, channel size, and airflow performance. A first analytical model accurately reflects the cooling effect of the incoming airflow on the outer wall of the center cone 2; a second analytical model reflects the heat transfer of the airflow from a single annular channel 4; and a third analytical model considers the thermal conductivity of the center cone 2 material and the distance between the outer wall of the center cone 2 and the annular channel 4. These models are used to evaluate the relationship between the outer wall temperature of the center cone 2, the wall temperature of the annular channel 4, and the heat transfer. By simultaneously analyzing these three models, the outer wall temperature of the center cone 2 at each location of the annular channel 4 can be accurately predicted. The temperature distribution of the entire outer wall of the center cone 2 is then used as the criterion for determining whether the dimensions of the annular channel 4 meet the design requirements. This not only improves the accuracy of the design but also significantly shortens the design cycle, providing strong support for the optimized design of the heat exchanger on the wall of the aero-engine center cone 2.

[0056] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A heat exchanger structure for the central cone wall of an aero-engine, wherein the central cone is a hollow cone-shaped structure, characterized in that, include: The intake manifold has one end connected to an air source, which is used to introduce the cooling airflow from the air source to the central cone section. The exhaust manifold is used to discharge the cooling airflow introduced into the cone position to the outside of the central cone; An annular flow channel is provided, with multiple annular flow channels disposed inside the wall of the central cone and equidistantly distributed along the wall of the central cone; each annular flow channel is provided with an inlet end and an outlet end, and the inlet end and the outlet end of the same annular flow channel are symmetrically distributed on both sides of the corresponding annular flow channel; the inlet end of the first-stage annular flow channel near the cone part of the central cone is connected to the intake manifold, the outlet end of each annular flow channel is connected to the inlet end of the next-stage annular flow channel, and the outlet end of the last-stage annular flow channel downstream of the wall of the central cone is connected to the exhaust manifold.

2. The heat exchanger structure of the central cone wall of an aero-engine according to claim 1, characterized in that, An air collection chamber is provided between the inlet end of the main air intake pipe and the inlet end of the first-stage annular flow channel, and between the two interconnected inlet ends and outlet ends.

3. The heat exchanger structure of the central cone wall of an aero-engine according to claim 2, characterized in that, Each level of the annular flow channel includes multiple annular airflow channels that are connected to the corresponding air collection chamber.

4. The heat exchanger structure of the center cone wall of an aero-engine according to claim 2, characterized in that, The cross-sectional area of ​​the main intake pipe is greater than or equal to the cross-sectional area of ​​each of the air collecting chambers, and the cross-sectional area of ​​each of the air collecting chambers is greater than or equal to the sum of the cross-sectional areas of all the annular flow channels; the cross-section of the air collecting chamber is a cross-section perpendicular to the flow direction of the airflow within the air collecting chamber.

5. The heat exchanger structure of the central cone wall of an aero-engine according to claim 1, characterized in that, The cooling gas flow in the gas source is air, hydrogen, or supercritical carbon dioxide.

6. A design method for a heat exchanger structure on the central cone wall of an aero-engine, used to obtain the heat exchanger structure on the central cone wall of an aero-engine as described in any one of claims 1-5, characterized in that, include: Based on the performance parameters of the incoming air and the size of the working channel of the central cone under the working conditions of the central cone, the first heat transfer coefficient between the outer wall of the central cone and the incoming air at the corresponding circumferential position of each annular channel is obtained by analysis, and the first analytical model of the heat transfer between the incoming air and the outer wall of the central cone at the corresponding circumferential position of each annular channel is constructed. Given the initial values ​​of the annular flow channel size parameters, the second heat transfer coefficient between the cooling airflow and the annular flow channel wall is obtained by analyzing the cooling airflow performance parameters under the initial values ​​of the annular flow channel size parameters; and a second analytical model of the heat transfer of cooling airflow in a single annular flow channel is constructed based on the inlet temperature, outlet temperature, and wall temperature of the annular flow channel. Based on the thermal conductivity of the central cone material and the distance between the outer wall of the central cone and the annular flow channel, a third analytical model for heat exchange between the outer wall of the central cone and the wall of the annular flow channel is constructed. Make the output values ​​of the first analysis model, the second analysis model and the third analysis model equal at the same position of the annular flow channel, and perform a simultaneous analysis of the first analysis model, the second analysis model and the third analysis model to obtain the temperature of the outer wall of the central cone corresponding to each circumferential position of the annular flow channel; Using the temperature of the outer wall of the central cone corresponding to each annular flow channel position as input, the temperature distribution of the entire outer wall of the central cone is obtained through simulation analysis. If the average temperature of the entire outer wall of the central cone is within the design target temperature range, the given initial value meets the design requirements; otherwise, the annular flow channel size parameters are adjusted until the average temperature of the entire outer wall of the central cone is within the design target temperature range.

7. The design method according to claim 6, characterized in that, The first heat transfer coefficient between the outer wall of the central cone at the corresponding circumferential position of each annular flow channel and the incoming air. ,in For the first The first heat transfer coefficient between the outer wall of the central cone corresponding to the circumferential position of the annular flow channel and the incoming air. For the first The radial height of the working channel section on the outer wall of the central cone corresponding to the circumferential position of each annular flow channel. The thermal conductivity of the incoming air. For the first The incoming air velocity at the working channel section of the outer wall of the central cone corresponding to the circumferential position of the annular flow channel. The Prandtl number of the incoming airflow; The first analytical model for the heat exchange between the incoming air and the outer wall of the central cone at each circumferential position of the annular flow channel is as follows: ,in, For the first The incoming air at each circumferential position of the annular flow channel exchanges heat with the outer wall of the central cone. For the first Each annular flow channel corresponds to the heat exchange area between the incoming airflow at the circumferential position and the outer wall of the central cone. The total intake temperature of the incoming air. For the first Temperature of the outer wall surface of the central cone corresponding to the circumferential position of each annular flow channel The emissivity of the material on the outer wall of the central cone. is the Stefan Boltzmann constant.

8. The design method according to claim 7, characterized in that, Given the initial values ​​of the annular flow channel dimensions, the second heat transfer coefficient between the cooling airflow and the annular flow channel wall is... ,in, For the first The second heat transfer coefficient between the cooling airflow and the annular channel wall within the annular channel. For the first The diameter of the annular flow channel, The thermal conductivity of the cooling airflow. For the first The flow rate of the cooling airflow within the annular flow channel, The Prandtl number is the number of the cooling airflow. The second analytical model for heat transfer of cooling airflow in a single annular channel, based on the inlet temperature, outlet temperature, and wall temperature of the annular channel, is as follows: In the formula, For the first The cooling airflow in the annular flow channel exchanges heat. For the first The inner wall area of ​​the annular flow channel For the first Temperature of the inner wall surface of the annular flow channel For cooling airflow in the first The intake temperature of the annular flow channel For cooling airflow in the first The outlet temperature of each annular flow channel, where 'a' is the axial distance between adjacent annular flow channels. Let be the thermal conductivity of the central cone material, and tanh be the hyperbolic tangent function. , Let be the independent variable of the hyperbolic tangent function.

9. The design method according to claim 8, characterized in that, The third analytical model for heat exchange between the outer wall of the central cone and the wall of the annular flow channel is as follows: In the formula, For the first The heat exchange between the outer wall of the central cone at each circumferential position of the annular flow channel and the wall of the annular flow channel is as follows: The thermal conductivity of the central cone material is... For the first The temperature of the outer wall surface of the central cone at the circumferential position of each annular flow channel. For the first Temperature of the inner wall surface of the annular flow channel For the first The wall thickness between the outer wall of the central cone and the wall of the annular flow channel at the circumferential position of each annular flow channel.

10. The design method according to any one of claims 6-9, characterized in that, The method to obtain the average temperature of the entire outer wall of the central cone is as follows: integrate the temperature of the central cone along the airflow path of the air source, and calculate the average temperature of the entire outer surface of the central cone.

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