Total temperature probe with high-efficiency particulate matter taking-out structure and flow channel optimization method of total temperature probe

Abstract

The invention discloses a total temperature probe with an efficient particulate matter taking-out structure and a flow channel optimization method of the total temperature probe, belongs to the technical field of total temperature probes, and solves the problem that the measurement precision is affected due to the fact that an existing total temperature probe cannot discharge particulate matter in time. The device comprises a support shell, a socket and a head shell, wherein a throat, a concave surface channel and a sweepback sensitive channel are arranged in the head shell, the throat and the concave surface channel are communicated with each other, and the sweepback sensitive channel is located at the bottom between the throat and the concave surface channel. Through the arrangement of the throat channel, the concave channel and the sweepback sensitive channel, water drops, ice, ice crystals, dust and other particles contained in air enter the flow channel and then are guided out of the straight outlet through airflow inertia, the situation that the total temperature measurement precision and reliability are reduced due to channel blockage caused by particle deposition is prevented, and the flight safety of an aircraft is improved.

Description

Technical Field

[0001] The invention relates to the technical field of total temperature probes, and in particular to a total temperature probe with a particle efficient carrying-out structure and a flow channel optimization method thereof. Background Art

[0002] As a device for measuring the total temperature of the atmosphere on an aircraft, the total temperature probe is of great significance to the flight control system for its accurate and efficient measurement. Most existing total temperature probes are retardation total temperature sensors, which work by reducing the velocity of the airflow entering the flow channel inside the probe, causing it to stagnate, and then measuring the temperature of the stagnant air. However, due to the complex environment in which the probe is located, the air entering the flow channel contains particles such as water droplets, ice, ice crystals or sand and dust. If these particles cannot be discharged from the flow channel in time, the total temperature measurement will be inaccurate or fail, thus affecting flight safety. Summary of the invention

[0003] In view of the above problems in the prior art, the present invention provides a total temperature probe with an efficient particle removal structure and a flow channel optimization method thereof, which solves the problem that the existing total temperature probe affects the measurement accuracy due to the inability to discharge particles in time.

[0004] In order to achieve the above object, the technical solution adopted by the present invention is as follows:

[0005] On the one hand, a total temperature probe with a particle efficient removal structure is provided, comprising: a bracket shell, a total temperature sensitive element for measuring the total temperature is fixed inside the bracket shell; a socket, the socket is fixed to the bottom of the bracket shell through a flange and is connected to the bottom of the total temperature sensitive element; a head shell, the head shell is fixed to the top of the bracket shell, and the head shell is provided with a throat, a concave channel and a swept angle sensitive channel located at the bottom between the throat and the concave channel, the larger opening end of the throat is a circular air inlet, the smaller opening end of the throat is connected to one end of the swept angle sensitive channel and the concave channel respectively, and the bottom end of the swept angle sensitive channel is connected to the total temperature sensitive element; the concave channel is in a truncated cone structure and the inner wall is a curved surface, the large diameter end of the concave channel has a diameter larger than the small opening end of the throat, and a straight outlet is provided on the small diameter end of the concave channel.

[0006] The working principle of this scheme is that the air enters the throat from the circular air inlet. The setting of the throat allows the air entering the total temperature probe to achieve a process of first compression and then expansion, ensuring that the airflow has a high speed after passing through the separation bend on the swept angle sensitive channel, so that the particles have a strong airflow inertia. After passing through the throat, the air collides with the upper and lower concave surfaces of the concave channel and contracts. The setting of the concave channel first expanding and contracting makes the particles in the incoming flow direction ejected in the direction of the straight outlet after collision, and guided out from the straight outlet by the inertia of the airflow, so that the particles do not have the conditions to enter the swept angle sensitive channel, so that the air entering the swept angle sensitive channel basically does not contain particles, which improves the measurement accuracy of the total temperature sensitive element.

[0007] Furthermore, the curved inner wall of the concave channel includes an upper concave surface and a lower concave surface, both of which are curved surfaces. The upper concave surface is tangent to the connection between the throat and the upper curvature of the upper concave surface is greater than the lower curvature of the lower concave surface. The concave channel is optimized based on the technology of vortex control inertial force to eject particles. The curve of the upper concave surface transitions to the tangent of the throat main channel. The setting of the upper curvature being greater than the lower curvature makes it more difficult for particles such as sand and ice to enter the swept angle sensitive channel, and effectively weakens the vortex intensity of the upper concave surface, thereby improving the particle ejection efficiency.

[0008] Furthermore, the horizontal angles at the large diameter end and the small diameter end of the upper concave surface are 9° and 19° respectively, and the horizontal angles at the large diameter end and the small diameter end of the lower concave surface are 26° and 34° respectively.

[0009] Furthermore, the included angle between the throat entrance slope and the horizontal incoming flow is 28.7°.

[0010] Furthermore, a separation bend connected to the throat and the concave channel is provided at the top of the swept angle sensitive channel, and multiple adsorption holes are provided on the entrance slope of the throat, on both sides of the separation bend, and on the rear wall of the swept angle sensitive channel. The provision of the adsorption holes reduces the influence of the boundary layer of the airflow, weakens the vortex intensity in the separation bend and the swept angle sensitive channel, makes the airflow in the flow channel smoother, eliminates the formation of the lower concave vortex, and enhances the total temperature recovery coefficient.

[0011] Furthermore, a circular exhaust channel connected to the multiple adsorption holes is provided through the head shell at the entrance of the separation bend. The circular exhaust channel facilitates the air in the multiple adsorption holes to be collected and discharged, provides the flowability of the adsorption holes, and enables the adsorption holes to better reduce the influence of the boundary layer of the airflow.

[0012] Furthermore, the center lines of the straight outlet and the circular air inlet are both coincident horizontal lines, and the area ratios of the inlet surface of the circular air inlet, the throat surface of the throat, the concave curved surface at the large diameter end of the concave channel, and the outlet surface of the straight outlet are 9.5:3:7.3:1. By setting the flow channel to expand first, shrink, expand again, and finally shrink, the particles first have a strong airflow inertia, and then collide and shrink, which is convenient for reducing the impact of the particles.

[0013] Furthermore, the total temperature sensitive element comprises an inner insulation tube with a temperature sensor arranged inside, an outer insulation tube is arranged outside the inner insulation tube, and a rectifying crown for gas rectification is arranged at the upper end of the outer insulation tube.

[0014] Furthermore, the bracket shell is tilted at 85 degrees, a plurality of air outlet holes are arranged on the back of the bracket shell at the top of the total temperature sensitive element, and a plurality of exhaust holes are arranged on the side of the bracket shell at the bottom of the total temperature sensitive element.

[0015] On the other hand, a flow channel optimization method of a total temperature probe having a particle efficient removal structure is provided, comprising the following steps:

[0016] S1, taking x1, x2, x3, x4 and x5 as optimization target independent variables, where x1, x2, x3, x4 and x5 are the circular inlet area, the climbing ratio of the throat, the area of ​​the straight outlet, the sweep angle of the sweep angle sensitive channel and the concave curve curvature of the concave channel respectively;

[0017] S2, determine the evaluation indicators F1, F2 and F3 of the objective function;

[0018]

[0019] Wherein, ΔT is the difference between the total temperature in the swept angle sensitive channel and the theoretical total temperature, r is the total temperature recovery coefficient, C is the ratio of the water content entering the swept angle sensitive channel to the water content of the circular air inlet, and A is the area of ​​the swept angle sensitive channel, in m 2 ; T i represents the temperature of the grid point of the sweep angle sensitive channel, in K; T represents the average temperature of the sweep angle sensitive channel area, T s represents the static temperature of the boundary condition input, T m Indicates the theoretical total temperature; m out represents the mass of liquid water entering the sweep angle sensitive channel, m in Represents the mass of liquid water entering the flow channel from the circular air inlet.

[0020] S3, establishing a flow channel design model in the total temperature probe according to the optimization target independent variables and environmental boundary conditions;

[0021] S4, setting the solver of the CFD two-phase flow module through initial boundary conditions;

[0022] S5, continuously change the value of the optimization target independent variable through the neural network model until F1 = lim Ti ΔT≈0, F2=lim T r≈1, and F3=lim m C≈0, and the final optimization target independent variable value is used as the design parameter of the internal flow channel of the total temperature probe.

[0023] When the three evaluation indicators F1, F2 and F3 meet the conditions at the same time, it means that the total temperature probe is in the most ideal measurement state. F1 = 0 means that there is no loss in total temperature, and the measured temperature is the total temperature. Since this is impossible to achieve from an engineering point of view, the measured value and the theoretical value are close to 0. F2 is the total temperature recovery coefficient, that is, F2 should be above 0.9999. Different Mach numbers and angles of attack will affect F2. F3 = 0 means that it is ideal that ice crystals and water droplets will not enter the swept angle sensitive channel, that is, the swept angle sensitive channel will not freeze, and the total temperature measurement accuracy will not be affected by particulate matter. The specific difference between F1, F2, F3 and the target value can be adjusted according to actual conditions.

[0024] The present invention discloses a total temperature probe with a particle efficient removal structure and a flow channel optimization method thereof, and the beneficial effects thereof are:

[0025] 1. The present invention arranges the throat, concave channel and swept angle sensitive channel, so that particles such as water droplets, ice, ice crystals and dust contained in the air enter the flow channel and are discharged from the straight outlet by airflow inertia, thereby preventing the channel from being blocked due to the accumulation of particles and reducing the total temperature measurement accuracy and reliability, thereby improving the flight safety of the aircraft.

[0026] 2. The adsorption holes on the entrance slope of the throat, on both sides of the separation bend, and in the swept angle sensitive channel of the present invention improve the generation of vortices in the swept angle sensitive channel, increase the blocking effect of the airflow, and improve the temperature recovery coefficient of the total temperature probe. The present invention has a total temperature recovery coefficient of 0.999 under the condition of an air pressure of less than 1Ma and an attack angle range of ±15°.

[0027] 3. The concave channel of the present invention is optimized based on the technology of vortex controlling inertial force to eject particles. The upper concave curve transitions with the tangent of the throat main channel, and the upper curvature is greater than the lower curvature. This angle makes it more difficult for particles such as sand and ice to enter the swept angle sensitive channel, and effectively weakens the vortex intensity of the upper concave surface, thereby improving the particle ejection efficiency. The vortex generation area at the lower concave surface is set as a swept angle sensitive channel, and a hole is opened on the side to reduce the formation of the lower concave surface vortex and enhance the total temperature recovery coefficient.

[0028] 4. The circular air inlet of the present invention maximizes the inlet area to increase the airflow entering the probe; the middle section adopts a throat design that first contracts and then expands, so that the airflow has a higher flow rate and increases inertia; the rear section adopts a concave channel to form a small vortex at the place where the curvature of the upper concave surface is reduced, which increases the incident angle of the particles ejected backwards and reduces the impact on the diversion of the swept angle sensitive channel. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 It is a structural schematic diagram of the appearance of the total temperature probe;

[0030] Figure 2 This is the internal cross-sectional view of the total temperature probe;

[0031] Figure 3 is a cross-sectional view of the head shell;

[0032] Figure 4 It is a structural schematic diagram of the curvature of the upper concave surface and the lower concave surface;

[0033] Figure 5 It is the schematic diagram of the flow channel cross section of the total temperature probe; Figure 6 It is a flow chart of the flow channel optimization method of the total temperature probe;

[0034] Among them: 1. head shell; 2. bracket shell; 3. flange; 4. socket; 5. fairing crown; 6. outer insulation tube; 7. inner insulation tube; 8. temperature sensor; 101. circular air inlet; 102. throat; 103. adsorption hole; 104. swept angle sensitive channel; 104a. rear wall; 105. concave channel; 106. straight outlet; 201. exhaust hole; 202. air outlet; 102a. entrance groove; 102b. circular exhaust channel; 105a. upper concave surface; 105b. lower concave surface. DETAILED DESCRIPTION

[0035] The specific implementation modes of the present invention are described below so that those skilled in the art can understand the present invention. However, it should be clear that the present invention is not limited to the scope of the specific implementation modes. For those of ordinary skill in the art, as long as various changes are within the spirit and scope of the present invention as defined and determined by the attached claims, these changes are obvious, and all inventions and creations utilizing the concept of the present invention are protected.

[0036] Example 1

[0037] refer to Figure 1 This embodiment provides a total temperature probe with a particle efficient removal structure, including a head shell 1, a bracket shell 2 and a socket 4.

[0038] refer to Figure 2A total temperature sensitive element for measuring the total temperature is fixed inside the bracket shell. The bracket shell 2 is inclined at 85°. A plurality of air outlet holes 202 are arranged on the back side of the bracket shell 2 at the top of the total temperature sensitive element. A plurality of air outlet holes 201 are arranged on the side of the bracket shell 2 at the bottom of the total temperature sensitive element.

[0039] The socket 4 is fixed to the bottom of the bracket housing 2 through the flange 3 and is connected to the bottom of the total temperature sensitive element. The total temperature sensitive element includes an inner insulation tube 7 with a temperature sensor 8 disposed inside, an outer insulation tube 6 is disposed outside the inner insulation tube 7, and a rectifying crown 5 for gas rectification is disposed at the upper end of the outer insulation tube 6.

[0040] The head shell 1 is fixed on the top of the bracket shell 2. The interior of the head shell 1 is provided with a throat 102 and a concave channel 105 which are interconnected, and a swept angle sensitive channel 104 located at the bottom between the throat 102 and the concave channel 105. The larger opening end of the throat 102 is a circular air inlet 101, and the smaller opening end of the throat 102 is respectively connected to the swept angle sensitive channel 104 and one end of the concave channel 105. The bottom end of the swept angle sensitive channel 104 is connected to the total temperature sensitive element; the concave channel 105 is in a truncated cone structure and the inner wall is a curved surface. The large diameter end of the concave channel 105 is larger than the smaller opening end of the throat 102, and a straight outlet 106 is provided on the small diameter end of the concave channel 105.

[0041] The circular air inlet 101 maximizes the inlet area to increase the airflow entering the probe; the middle section adopts a throat 102 design that first contracts and then expands, so that the airflow has a higher flow rate and increases inertia; the rear section adopts a concave channel 105 to form a small vortex at the place where the curvature of the upper concave surface 105a decreases, thereby increasing the incident angle of the particles ejected backwards and reducing the impact on the diversion of the swept angle sensitive channel 104.

[0042] Specifically, the center lines of the straight outlet 106 and the circular air inlet 101 are both coincident horizontal lines. Figure 5 The area ratio of the inlet surface of the circular air inlet 101, the throat surface of the throat 102, the concave curve surface of the large diameter end of the concave channel 105 and the outlet surface of the straight outlet 106 is 9.5:3:7.3:1. By setting the flow channel to expand first, then shrink, then expand again, and finally shrink, the particles first have a strong airflow inertia, and then collide and shrink, which is convenient for reducing the impact of the particles. Among them, Figure 5 The shapes of A, B, C, and D in the figure are respectively the shapes of the inlet surface of the circular air inlet 101, the throat surface of the throat 102, the concave curved surface of the large diameter end of the concave channel 105, and the outlet surface of the straight outlet 106.

[0043] Specifically, as the specific structure of the concave channel 105, refer to Figure 2 and Figure 4 The curved inner wall of the concave channel 105 includes an upper concave surface 105a and a lower concave surface 105b, both of which are curved surfaces. The upper concave surface 105a is tangent to the connection between the throat 102, and the upper curvature of the upper concave surface 105a is greater than the lower curvature of the lower concave surface 105b. The concave channel 105 is optimized based on the technology of ejecting particles by controlling the inertial force of the vortex. The curve of the upper concave surface 105a transitions with the tangent of the main channel of the throat 102. The setting of the upper curvature being greater than the lower curvature makes it more difficult for particles such as sand and ice to enter the swept angle sensitive channel 104, and effectively weakens the vortex intensity of the upper concave surface 105a, thereby improving the particle ejection efficiency.

[0044] Preferably, in this embodiment, reference Figure 4 The horizontal angles of the large diameter end and the small diameter end of the upper concave surface 105a are 9° and 19° respectively, and the horizontal angles of the large diameter end and the small diameter end of the lower concave surface 105b are 26° and 34° respectively. The angle between the inlet 102a of the throat 102 and the horizontal incoming flow is 28.7°.

[0045] As a further solution of this embodiment, refer to Figure 3 The top of the swept angle sensitive channel 104 is provided with a separation bend which is connected to the throat 102 and the concave channel 105 respectively. A plurality of adsorption holes 103 are provided on the entrance slope of the throat 102, on both sides of the separation bend, and on the rear wall 104a of the swept angle sensitive channel 104. The provision of the adsorption holes 103 reduces the influence of the boundary layer of the airflow, weakens the vortex intensity in the separation bend and the swept angle sensitive channel 104, makes the airflow in the flow channel smoother, eliminates the formation of vortex on the lower concave surface 105b, and enhances the total temperature recovery coefficient. Figure 2 A circular exhaust passage 102b connected to the plurality of adsorption holes 103 is provided at the entrance of the separation bend on the head shell 1. The circular exhaust passage 102b facilitates the air in the plurality of adsorption holes 103 to be collected and discharged, provides the flowability of the adsorption holes 103, and enables the adsorption holes 103 to better reduce the influence of the boundary layer of the airflow.

[0046] Example 2

[0047] This embodiment is further limited on the basis of the embodiment 1. The specific improvement is that the internal flow channel of the total temperature probe is optimized to have the characteristic of efficiently carrying out particles. For other parts not mentioned, refer to the embodiment 1 or the prior art.

[0048] refer to Figure 6 This embodiment provides a flow channel optimization method of a total temperature probe with a particle efficient removal structure, comprising the following steps:

[0049] S1. Take x1, x2, x3, x4 and x5 as optimization target independent variables, where x1, x2, x3, x4 and x5 are respectively the area of ​​the circular air inlet 101, the climbing ratio of the throat 102, the area of ​​the straight outlet 106, the sweep angle of the sweep angle sensitive channel 104 and the concave curve curvature of the concave channel 105.

[0050] S2. Determine the evaluation indicators F1, F2 and F3 of the objective function.

[0051]

[0052] Wherein, ΔT is the difference between the total temperature in the swept angle sensitive channel 104 and the theoretical total temperature, r is the total temperature recovery coefficient, C is the ratio of the water content entering the swept angle sensitive channel 104 to the water content of the circular air inlet, and A represents the area of ​​the swept angle sensitive channel 104, in m 2 ; T i represents the temperature of the grid point of the sweep angle sensitive channel 104, in K; T represents the average temperature of the sweep angle sensitive channel 104 area, T s represents the static temperature of the boundary condition input, T m Indicates the theoretical total temperature; m out represents the mass of liquid water entering the sweep angle sensitive channel 104, m in Represents the mass of liquid water entering the flow channel from the circular air inlet.

[0053] S3. Establish a flow channel design model in the total temperature probe based on the optimization target independent variables and environmental boundary conditions.

[0054] S4. Set up the solver of the CFD two-phase flow module through initial boundary conditions.

[0055] S5, continuously change the value of the optimization target independent variable through the neural network model until F2=lim T r≈1, and F3=lim m C≈0, and the final optimization target independent variable value is used as the design parameter of the internal flow channel of the total temperature probe.

[0056] When the three evaluation indicators F1, F2 and F3 meet the conditions at the same time, it means that the total temperature probe is in the most ideal measurement state. F1 = 0 means that there is no loss in total temperature, and the measured temperature is the total temperature. Since this is impossible to achieve from an engineering point of view, the measured value and the theoretical value are close to 0. F2 is the total temperature recovery coefficient, that is, F2 should be above 0.9999. Different Mach numbers and angles of attack will affect F2. F3 = 0 means that ideally, ice crystals and water droplets will not enter the swept angle sensitive channel 104, that is, the swept angle sensitive channel 104 will not freeze, and the total temperature measurement accuracy will not be affected by particulate matter. The specific difference between F1, F2, F3 and the target value can be adjusted according to actual conditions.

[0057] In this embodiment, the Mach number is 0.5 and the sea level is used as the boundary conditions, and the optimization target independent variable x1=266.8 mm 2 , x2=0.58,x3=22.9mm 2 , x4 = 85°, x5 is the tangent transition between the upper concave surface 105a curve and the throat 102, the horizontal angle is 9°:19°, the horizontal angle of the lower concave surface 105b curve is 26°:34°. F1 = ΔT = 0.26K, F2 = r = 0.9993, F3 = C = 0.05%.

[0058] Although the specific implementation of the invention is described in detail in conjunction with the drawings, it should not be understood as limiting the scope of protection of this patent. Within the scope described in the claims, various modifications and variations that can be made by those skilled in the art without creative work still fall within the scope of protection of this patent.

Claims

1. A total temperature probe with a particle efficient removal structure, characterized in that: include: A bracket shell (2), wherein a total temperature sensitive element for measuring total temperature is fixed inside the bracket shell (2); A socket (4), wherein the socket (4) is fixed to the bottom of the bracket housing (2) through a flange (3) and is in electrical communication with the bottom of the total temperature sensitive element; A head shell (1), wherein the head shell (1) is fixed on the top of the bracket shell (2), and the head shell (1) is provided with a throat (102) and a concave channel (105) which are interconnected, and a swept angle sensitive channel (104) located at the bottom between the throat (102) and the concave channel (105), wherein the larger opening end of the throat (102) is a circular air inlet (101), and the smaller opening end of the throat (102) is respectively connected to one end of the swept angle sensitive channel (104) and the concave channel (105), and the bottom end of the swept angle sensitive channel (104) is connected to a total temperature sensitive element, and the rear wall surface (104a) of the swept angle sensitive channel (104) is arranged obliquely; The concave channel (105) is in a truncated cone structure and has a curved inner wall. The diameter of the large diameter end of the concave channel (105) is larger than the diameter of the smaller opening end of the throat (102), and a straight outlet (106) is provided on the small diameter end of the concave channel (105).

2. The total temperature probe according to claim 1, characterized in that: The curved inner wall of the concave channel (105) comprises an upper concave surface (105a) and a lower concave surface (105b), both of which are curved surfaces; the upper concave surface (105a) is tangent to the connection with the throat (102), and the curvature of the upper concave surface (105a) is greater than the curvature of the lower concave surface (105b).

3. The total temperature probe according to claim 2, characterized in that: The horizontal angles at the large diameter end and the small diameter end of the upper concave surface (105a) are 9° and 19° respectively, and the horizontal angles at the large diameter end and the small diameter end of the lower concave surface (105b) are 26° and 34° respectively.

4. The total temperature probe according to claim 1, characterized in that: The included angle between the inlet slope (102a) of the throat (102) and the horizontal incoming flow is 28.7°.

5. The total temperature probe according to claim 1, characterized in that: A separation bend is provided at the top of the swept angle sensitive channel (104) and is respectively connected to the throat (102) and the concave channel (105); a plurality of adsorption holes (103) are provided on the entrance slope of the throat (102), on both sides of the separation bend, and on the rear wall surface (104a) of the swept angle sensitive channel (104).

6. The total temperature probe according to claim 5, characterized in that: A circular exhaust passage (102b) communicating with the plurality of adsorption holes (103) is provided through the head shell (1) at the entrance of the separation bend.

7. The total temperature probe according to claim 5, characterized in that: The center lines of the straight outlet (106) and the circular air inlet (101) are both overlapping horizontal lines, and the area ratio of the inlet surface of the circular air inlet (101), the throat surface of the throat (102), the concave curved surface of the large diameter end of the concave channel (105), and the outlet surface of the straight outlet (106) is 9.5:3:7.3:

1.

8. The total temperature probe according to claim 1, characterized in that: The total temperature sensitive element comprises an inner heat-insulating tube (7) with a temperature sensor (8) arranged inside, an outer heat-insulating tube (6) arranged outside the inner heat-insulating tube (7), and a rectifying crown (5) for gas rectification arranged at the upper end of the outer heat-insulating tube (6).

9. The total temperature probe according to claim 1, characterized in that: The support shell (2) is arranged at an angle of 85 degrees, a plurality of air outlet holes (202) are arranged on the back side of the support shell (2) at the top of the total temperature sensitive element, and a plurality of air exhaust holes (201) are arranged on the side of the support shell (2) at the bottom of the total temperature sensitive element.

10. The flow channel optimization method of the total temperature probe according to any one of claims 1 to 9, characterized in that: The following steps are involved: S1, taking x1, x2, x3, x4 and x5 as optimization target independent variables, wherein x1, x2, x3, x4 and x5 are respectively the area of ​​the circular air inlet (101), the slope ratio of the throat (102), the area of ​​the straight outlet (106), the sweep angle of the sweep angle sensitive channel (104) and the concave curve curvature of the concave channel (105); S2, determine the evaluation indicators F1, F2 and F3 of the objective function; Wherein, ΔT is the difference between the total temperature in the swept angle sensitive channel (104) and the theoretical total temperature, r is the total temperature recovery coefficient, C is the ratio of the water content entering the swept angle sensitive channel (104) to the water content of the circular air inlet, and A represents the area of ​​the swept angle sensitive channel (104), in m 2 ; T i represents the temperature of the grid point of the sweep angle sensitive channel (104), in K; T represents the average temperature of the sweep angle sensitive channel (104) area, T s represents the static temperature of the boundary condition input, T m Indicates the theoretical total temperature; m out represents the mass of liquid water entering the sweep angle sensitive channel (104), m in It represents the mass of liquid water entering the flow channel from the circular air inlet; S3, establishing a flow channel design model in the total temperature probe according to the optimization target independent variables and environmental boundary conditions; S4, setting the solver of the CFD two-phase flow module through initial boundary conditions; S5, through the neural network model in the solver, continuously change the value of the optimization target independent variable until F1 = lim Ti ΔT≈0, F2=lim T r≈1, and F3=lim m C≈0, and the final optimization target independent variable value is used as the design parameter of the internal flow channel of the total temperature probe.

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