Total temperature sensor and manufacturing method thereof

Abstract

The invention relates to the technical field of sensors, in particular to a total temperature sensor and a manufacturing method thereof. The invention provides a total temperature sensor. The total temperature sensor comprises a sensor main body structure and a temperature sensing element, wherein the sensor main body structure at least comprises a mounting seat and a sensor shell; the sensor shell is mounted on the mounting seat; a sensing cavity is formed in the sensor shell, and the sensing cavity is filled with the three-period minimum curved surface unit cell filling structure; and the temperature sensing element is arranged in the sensing cavity. According to the total temperature sensor and the manufacturing method thereof provided by the invention, the sensing cavity is filled with the three-period minimum curved surface unit cell filling structure, so that the total temperature sensor has the characteristics of light weight, high strength, good connectivity and controllable topological structure, and the impact resistance of the sensing cavity can be remarkably improved.

Description

Technical Field

[0001] The present invention relates to the field of sensor technology, and more particularly to a total temperature sensor and a manufacturing method thereof. Background Art

[0002] For the total temperature sensor at the inlet of an aircraft engine, as the front part of the engine that may be hit by birds, special attention should be paid to its bird strike resistance requirements. At present, the temperature measurement function is given priority in the design of the total temperature sensor, but the impact resistance performance needs to be improved.

[0003] In order to obtain the total temperature of the gas, existing sensor designs usually set up a sensing cavity to block the airflow in the cavity so that the flow rate is reduced to zero, and the kinetic energy of the gas is converted into heat energy. However, the sensing cavity is generally a cavity with a temperature sensing element installed inside. This part often becomes a weak point when impacted and is prone to damage. Therefore, the structural design of the T12 sensor (used to measure the total temperature of a specific cross section of the fan inlet in real time) needs to further consider the impact strength and design weight requirements such as bird strike resistance.

[0004] In addition, when the sensor is exposed to rain, snow, and freezing weather conditions, ice may form, which will not only lead to inaccurate temperature measurements, but also the falling ice may damage other key components.

[0005] Therefore, measures need to be taken to prevent or slow down the occurrence of icing to a certain extent, or to minimize the volume of ice accumulation. Existing sensor anti-icing generally adopts active methods such as electric heating or bleed air heating, but these methods make sensor design complicated, traditional manufacturing methods more difficult, and the control method is complicated.

[0006] Figure 1 The schematic diagram of the location of the total temperature sensor of the aircraft engine in the engine is revealed, such as Figure 1 As shown, the aircraft engine total temperature sensor 11 is installed on the inner wall plate 12 of the air inlet duct and extends out to be exposed to the air flowing into the fan, so as to measure the total temperature of the fan inlet in real time.

[0007] The total temperature sensor 11 may freeze when exposed to rain, snow or freezing weather conditions, and as a front component of the engine, it may be hit by foreign objects.

[0008] Figure 2a and Figure 2b The structure diagram and cross-sectional diagram of the total temperature sensor in the prior art are disclosed respectively. Figure 3a and Figure 3b The AA section and BB section schematic diagrams of the total temperature sensor in the prior art are disclosed respectively, as shown in FIG. Figures 2a to 3b As shown, the total temperature sensor in the prior art includes a cover 14, a mounting base 15 and a sensor housing 16:

[0009] The sensor housing 16 has air inlet holes 13 on both sides;

[0010] The sensor housing 16 has a sensing cavity 18 formed therein.

[0011] The temperature sensing element 17 extends out and probes into the sensing cavity 18, the sensing cavity 18 is exposed to the air flowing into the fan, and the portion above the sensing cavity 18 is inside the inner wall plate 12 of the air inlet duct;

[0012] The air flow enters the sensing cavity 18 through the air inlet 13 and the bottom opening.

[0013] The sensor housing 16 needs to withstand the impact of foreign objects, and the windward surface of the sensor housing 16 is prone to ice.

[0014] Since the sensing cavity 18 of the conventional total temperature sensor is a hollow cavity and air inlet holes 13 are opened on both sides, the sensor housing 16 is easily damaged in the hollow cavity area when impacted by foreign objects.

[0015] The existing sensor design and processing method requires welding and assembling the temperature sensing element 17 in the sensing cavity 18 and the sensor housing 16, which makes the manufacturing process complicated and has low reliability. Summary of the invention

[0016] The object of the present invention is to provide a total temperature sensor to solve the problem that the total temperature sensor in the prior art has poor bird strike resistance.

[0017] Another object of the present invention is to provide a total temperature sensor to solve the problems of complex manufacturing process and low reliability of the total temperature sensor in the prior art.

[0018] Another object of the present invention is to provide a total temperature sensor to solve the problem of complex anti-icing design structure of the total temperature sensor in the prior art.

[0019] In order to achieve the above object, the present invention provides a total temperature sensor, including a sensor main structure and a temperature sensing element:

[0020] The sensor main body structure at least includes a mounting seat and a sensor housing;

[0021] The sensor housing is mounted on a mounting base;

[0022] The sensor housing has a sensing cavity formed inside, and the sensing cavity is filled with a three-periodic minimal surface unit cell filling structure;

[0023] The temperature sensing element is arranged in the sensing cavity.

[0024] In one embodiment, the temperature sensing element is a stick-on thermal resistor;

[0025] A sealing cover is arranged in the upper area of ​​the sensing cavity, and an adhesive thermal resistor is arranged on the upper surface of the sealing cover.

[0026] In one embodiment, a protective layer is provided on the windward side of the sensor housing:

[0027] A three-periodic minimal surface unit cell filling structure is filled between the protective layer and the sensor housing.

[0028] In one embodiment, the protective layer is a memory alloy protective layer.

[0029] In one embodiment, the protective layer is provided with a plurality of prefabricated grooves:

[0030] The plurality of prefabricated grooves divide the surface of the protective layer into a plurality of tiny fragment structures.

[0031] In one embodiment, the plurality of tiny fragment structures are triangular structures, prismatic structures, or honeycomb structures.

[0032] In one embodiment, the three-periodic minimal surface unit cell filling structure filled in the sensing cavity is a Gyroid unit cell.

[0033] In one embodiment, the three-periodic minimal surface unit cell filling structure filled between the protective layer and the sensor housing is an IWP unit cell.

[0034] In one embodiment, the adhesive thermal resistor is a flexible thermal resistor.

[0035] In one embodiment, the memory alloy protective layer is a nickel-titanium shape memory alloy.

[0036] In one embodiment, the temperature measured by the adhesive thermal resistor is converted into the total air temperature through the dynamic temperature recovery coefficient.

[0037] In one embodiment, the dynamic temperature recovery coefficient is calculated by a wind tunnel test according to the following expression:

[0038]

[0039] Among them, γ is the dynamic temperature recovery coefficient, T0 is the total airflow temperature, T g is the temperature measured by the sensor, κ is the adiabatic index, and Ma is the airflow Mach number.

[0040] In order to achieve the above object, the present invention provides an aircraft engine, comprising a total temperature sensor as described in any one of the above items.

[0041] In one embodiment, the total temperature sensor is installed in the air intake duct of the aircraft engine.

[0042] In order to achieve the above object, the present invention provides a method for manufacturing a total temperature sensor, which is used to manufacture the total temperature sensor as described in any one of the above items, wherein a protective layer is provided on the windward surface of the sensor housing of the total temperature sensor, comprising the following steps:

[0043] The main structure of the sensor is formed in one go using additive manufacturing technology;

[0044] Based on the completed sensor main structure, the protective layer is additively manufactured;

[0045] The sensor main structure and the protective layer are integrated.

[0046] In one embodiment, the sensor main body structure is stainless steel, and the protective layer is nickel-titanium memory alloy.

[0047] The present invention provides a total temperature sensor and a manufacturing method thereof. The sensing cavity is filled with a three-periodic minimal surface unit cell filling structure, which can significantly improve the impact resistance of the sensing cavity. The windward surface of the sensor adopts a fragment-type memory alloy protective layer, which has the functions of active anti-icing and impact energy absorption. BRIEF DESCRIPTION OF THE DRAWINGS

[0048] The above and other features, properties and advantages of the present invention will become more apparent through the following description in conjunction with the accompanying drawings and embodiments, in which the same reference numerals always represent the same features, wherein:

[0049] Figure 1 The schematic diagram of the location of the aircraft engine total temperature sensor in the engine is revealed;

[0050] Figure 2a The structural schematic diagram of the total temperature sensor in the prior art is disclosed;

[0051] Figure 2b A cross-sectional schematic diagram of a total temperature sensor in the prior art is disclosed;

[0052] Figure 3a The AA cross-sectional schematic diagram of the total temperature sensor in the prior art is disclosed;

[0053] Figure 3b The BB cross-sectional schematic diagram of the total temperature sensor in the prior art is disclosed;

[0054] Figure 4a A schematic structural diagram of a total temperature sensor according to an embodiment of the present invention is disclosed;

[0055] Figure 4b A cross-sectional schematic diagram of a total temperature sensor according to an embodiment of the present invention is disclosed;

[0056] Figure 5aThe AA cross-sectional schematic diagram of the total temperature sensor according to an embodiment of the present invention is disclosed;

[0057] Figure 5b A BB cross-sectional schematic diagram of a total temperature sensor according to an embodiment of the present invention is disclosed;

[0058] Figure 6a A first schematic diagram of a windward surface protection layer of a sensor according to an embodiment of the present invention is disclosed;

[0059] Figure 6b A second schematic diagram of a windward surface protection layer of a sensor according to an embodiment of the present invention is disclosed;

[0060] Figure 7a A schematic diagram of filling the Gyroid unit cell in the upper area of ​​the sensing cavity according to an embodiment of the present invention is disclosed;

[0061] Figure 7b A partial schematic diagram of a cross section of a filling area according to an embodiment of the present invention is disclosed;

[0062] Figure 8a A first schematic diagram of an IWP unit cell of a windward surface protection layer according to an embodiment of the present invention is disclosed;

[0063] Figure 8b A second schematic diagram of an IWP unit cell of a windward surface protection layer according to an embodiment of the present invention is disclosed.

[0064] The meanings of the reference numerals in the figures are as follows:

[0065] 11 total temperature sensor;

[0066] 12 air intake duct inner wall panel;

[0067] 13 air inlet;

[0068] 14 cover;

[0069] 15 mounting seat;

[0070] 16 sensor housing;

[0071] 17 Temperature sensing element;

[0072] 18 sensing cavity;

[0073] 23 air inlet;

[0074] 24 covers;

[0075] 25 mounting seat;

[0076] 26 sensor housing;

[0077] 28 sensing cavity;

[0078] 29 protective layers;

[0079] 210 Three-periodic minimal surface unit cell packing structure;

[0080] 211 adhesive thermal resistor;

[0081] 212 sealing cover;

[0082] 213 prefabricated trough. DETAILED DESCRIPTION

[0083] In order to make the purpose, technical solution and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the invention and are not used to limit the invention.

[0084] Figure 4a and Figure 4b The structure diagram and cross-sectional diagram of the total temperature sensor according to an embodiment of the present invention are disclosed respectively. Figure 5a and Figure 5b The AA cross-sectional schematic diagram and the BB cross-sectional schematic diagram of the total temperature sensor of an embodiment of the present invention are respectively disclosed, as shown in FIG. Figures 4a to 5b As shown, a total temperature sensor proposed by the present invention includes a sensor main body structure and a temperature sensing element:

[0085] The sensor main body structure at least includes a mounting seat 25 and a sensor housing 26;

[0086] The sensor housing 26 is mounted on the mounting base 25;

[0087] The sensor housing 26 has a sensing cavity 28 formed therein;

[0088] The sensing cavity 28 is filled with a three-periodic minimal surface unit cell filling structure 10;

[0089] The temperature sensing element is disposed in the sensing cavity 28 .

[0090] In this embodiment, the temperature sensing element is a stick-on thermal resistor 211;

[0091] A sealing cover 212 is disposed in the upper area of ​​the sensing cavity 28 , and an adhesive thermal resistor 211 is disposed on the upper surface of the sealing cover 212 .

[0092] It should be noted that the temperature measured by the adhesive thermal resistor 211 is not completely equal to the total air temperature. In order to obtain an accurate total air temperature, a conversion can be performed using a dynamic temperature recovery coefficient.

[0093] As a key parameter, the dynamic temperature recovery coefficient can be measured through wind tunnel tests. The dynamic temperature conversion coefficient is closely related to factors such as sensor structure, size, sensing cavity unit cell topology, airflow viscosity and flow velocity.

[0094] When conducting wind tunnel tests, the dynamic temperature recovery coefficient can be calculated according to the following formula:

[0095]

[0096] Among them, γ is the dynamic temperature recovery coefficient, T0 is the total airflow temperature, T g is the temperature measured by the sensor, κ is the adiabatic index, and Ma is the airflow Mach number.

[0097] Preferably, the adhesive thermal resistor 211 can be a flexible thermal resistor, which can deform along with the adhesive position when the sensor is impacted, and is therefore less likely to fail.

[0098] Air inlet holes 23 are formed on both sides of the sensor housing 26 .

[0099] A total temperature sensor proposed in the present invention, based on the existing sensor structure, changes the sensing cavity 28 from a simple cavity to a structure filled with a three-periodic minimal surface unit cell filling structure 210, fully utilizing the advantages of the three-periodic minimal surface unit cell filling structure 210, such as light weight and high strength, good connectivity, and controllable topological structure, effectively realizes airflow blocking, and significantly improves the impact resistance of the sensor sensing cavity 28.

[0100] The novel sensing cavity constructed by the three-periodic minimal surface unit cell filling structure 210 uses its porous connectivity to allow gas to enter the connected holes to achieve airflow blocking. At the same time, the three-periodic minimal surface unit cell structure is lightweight and high-strength to improve the impact resistance of the sensing cavity.

[0101] The sensing cavity 28 filled with the three-periodic minimal surface unit cell filling structure 210 blocks the gas, triggering the transformation of the gas kinetic energy into heat energy, causing the structural temperature of the sensing cavity 28 to rise. This temperature change can be accurately measured by the adhesive thermal resistor 211 arranged at the upper position of the sensing cavity 28.

[0102] like Figure 4a , Figure 4b and Figure 5b As shown, a protective layer 29 is provided on the windward side of the sensor housing 26:

[0103] A three-periodic minimal surface unit cell filling structure is filled between the protective layer 29 and the sensor housing 26 .

[0104] In this embodiment, the protective layer 29 is a memory alloy protective layer, which will deform when the air temperature drops to the transition temperature.

[0105] The memory alloy protective layer designed on the windward side of the sensor is also filled with a three-period minimal surface unit cell filling structure. Its function is to block the gas flow, so that when the temperature changes, the shape of the protective layer changes, and the outermost layer of ice attached to the windward side of the sensor is squeezed and broken, and the entire ice layer falls off, thereby realizing the automatic ice crushing and de-icing process on the outer surface of the sensor.

[0106] Optionally, the memory alloy is a nickel-titanium shape memory alloy.

[0107] Except for the protective layer 29 which is made of memory alloy, other parts of the sensor main structure are made of stainless steel.

[0108] like Figure 4a and Figure 5b As shown, the protective layer 29 has a plurality of prefabricated grooves 213 on its surface, which facilitates the deformation of the shape memory alloy, squeezes the ice layer, and causes the ice layer to fall off.

[0109] The several prefabricated grooves 213 on the surface of the protective layer divide the surface of the protective layer into several small fragment structures, which are easily locally damaged and fall off when impacted by foreign objects, absorbing the impact energy and reducing the impact energy on the main structure. The fallen small fragments will not cause damage to the engine.

[0110] In this embodiment, the depth of the prefabricated groove is 1 / 2 of the thickness of the protective layer, and the width is 1 mm.

[0111] In this embodiment, the protective layer prefabricated grooves 213 divide the surface into many tiny triangular structures.

[0112] The form of the prefabricated grooves is not particularly limited. In other embodiments, the prefabricated grooves can divide the surface of the protective layer into other shapes that can equally achieve the same effect.

[0113] Figure 6a A first schematic diagram of a windward surface protection layer of a sensor according to an embodiment of the present invention is disclosed. Figure 6a In the illustrated embodiment, the prefabricated grooves divide the surface of the protective layer into prismatic structures.

[0114] Figure 6b A second schematic diagram of a windward surface protection layer of a sensor according to an embodiment of the present invention is disclosed. Figure 6b In the illustrated embodiment, the prefabricated grooves divide the surface of the protective layer into a honeycomb structure.

[0115] Figure 7a A schematic diagram of filling the Gyroid unit cell in the inner area of ​​the sensing cavity according to an embodiment of the present invention is disclosed. Figure 7b A partial schematic diagram of a cross section of a filling area according to an embodiment of the present invention is disclosed, such as Figure 7a and Figure 7bAs shown, the three-periodic minimal surface unit cell filling structure 210 filled in the sensing cavity is a Gyroid unit cell. The Gyroid unit cell has a relatively high specific surface area, which can improve the airflow blocking efficiency, thereby improving the sensor response speed.

[0116] like Figure 4b and Figure 7a As shown, the three-periodic minimal surface unit cell filling structure 210 filled in the upper area of ​​the sensing cavity 28 is connected to the sealing cover 212 , and the adhesive thermal resistor 211 is adhered to the upper surface of the sealing cover 212 .

[0117] The main function of the sealing cover 212 is to prevent airflow from entering the interior of the engine, while the adhesive thermal resistor 211 provides a smooth adhesive surface.

[0118] Figure 8a A first schematic diagram of an IWP unit cell of a windward surface protection layer according to an embodiment of the present invention is disclosed. Figure 8b A second schematic diagram of an IWP unit cell of a windward surface protection layer according to an embodiment of the present invention is disclosed, Figure 8a and Figure 8b As shown, the three-periodic minimal surface unit cell structure filled between the protective layer and the sensor housing is an IWP unit cell structure. This unit cell structure exhibits excellent performance when under pressure and can absorb a large amount of impact energy when impacted, thereby achieving effective protection.

[0119] The total temperature sensor described in the above embodiment is particularly suitable for installation in the air intake of an aircraft engine. However, it can be understood that the total temperature sensor described above is not limited to installation in the air intake, but can also be a total temperature sensor set at other locations. It is not even limited to use in aircraft engines, but can also be a total temperature sensor set in an aircraft, such as installed at the wing tip, the top of the tail vertices, the side of the nose, or other places where the airflow is not easily disturbed.

[0120] The present invention further provides a method for manufacturing the above-mentioned total temperature sensor, wherein a protective layer is provided on the windward surface of the sensor housing of the total temperature sensor, and the method for manufacturing the total temperature sensor comprises the following steps:

[0121] The main structure of the sensor except the protective layer is formed in one go using additive manufacturing technology;

[0122] Based on the completed sensor main structure, the protective layer is additively manufactured;

[0123] The completed sensor main structure and protective layer are integrated.

[0124] In this embodiment, the sensor main body structure except the protective layer is made in one piece by additive manufacturing.

[0125] Since the materials of the protective layer and the sensor main structure are different, after the additive manufacturing of the sensor main structure is completed, the additive manufacturing of the protective layer is performed based on the manufactured sensor main structure.

[0126] Furthermore, the sensor main body structure except the protective layer is made of stainless steel, and the protective layer is made of nickel-titanium memory alloy.

[0127] The melting point of stainless steel is around 1400°C, and the melting point of nickel-titanium memory alloy is around 2000°C. Printing in order from low to high melting points allows the interfaces between the materials to fuse together, ensuring interface strength.

[0128] Although the above methods are illustrated and described as a series of actions for simplicity of explanation, it should be understood and appreciated that these methods are not limited by the order of the actions, because according to one or more embodiments, some actions may occur in a different order and / or concurrently with other actions from those illustrated and described herein or not illustrated and described herein but understandable to those skilled in the art.

[0129] The present invention provides a total temperature sensor and a manufacturing method thereof, which specifically have the following beneficial effects:

[0130] 1) The sensing cavity is filled with a three-periodic minimal surface unit cell filling structure. This structure has the characteristics of light weight, high strength, good connectivity, and controllable topology. While achieving airflow blocking, it can significantly improve the impact resistance of the sensing cavity. The gradient design of the unit cell structure is highly flexible and can effectively improve mechanical and vibration performance;

[0131] 2) The windward side of the sensor adopts a fragment-type memory alloy protective layer, which not only has an active anti-icing function, but also can absorb impact energy, effectively protecting the main structure of the sensor. Even if the protective layer falls off tiny fragments, it will not cause harm to the engine;

[0132] 3) Through additive manufacturing technology, integrated printing processing is performed to integrate the outer shell and inner core into a single component, greatly reducing the connection between parts, which not only improves the performance of the component, but also reduces the overall processing cost.

[0133] As shown in this application and claims, unless the context clearly indicates an exception, the words "a", "an", "an" and / or "the" do not refer to the singular and may also include the plural. Generally speaking, the terms "include" and "comprise" only indicate the inclusion of the steps and elements that have been clearly identified, and these steps and elements do not constitute an exclusive list. The method or device may also include other steps or elements.

[0134] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0135] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0136] The above embodiments are provided for persons familiar with the art to implement or use the present invention. Personnel familiar with the art can make various modifications or changes to the above embodiments without departing from the inventive concept of the present invention. Therefore, the protection scope of the present invention is not limited to the above embodiments, but should be the maximum scope of the innovative features mentioned in the claims.

Claims

1. A total temperature sensor, characterized in that: Including sensor main structure and temperature sensing element: The sensor main body structure at least includes a mounting seat and a sensor housing; The sensor housing is mounted on the mounting base; The sensor housing has a sensing cavity formed inside, and the sensing cavity is filled with a three-periodic minimal surface unit cell filling structure; The temperature sensing element is arranged in the sensing cavity.

2. The total temperature sensor according to claim 1, characterized in that: The temperature sensing element is a stick-on thermal resistor; A sealing cover is arranged in the upper area of ​​the sensing cavity, and an adhesive thermal resistor is arranged on the upper surface of the sealing cover.

3. The total temperature sensor according to claim 1, characterized in that: A protective layer is provided on the windward side of the sensor housing: A three-periodic minimal surface unit cell filling structure is filled between the protective layer and the sensor housing.

4. The total temperature sensor according to claim 3, characterized in that: The protective layer is a memory alloy protective layer.

5. The total temperature sensor according to claim 3, characterized in that: The protective layer is provided with a plurality of prefabricated grooves: The plurality of prefabricated grooves divide the surface of the protective layer into a plurality of tiny fragment structures.

6. The total temperature sensor according to claim 5, characterized in that: The plurality of tiny fragment structures are triangular structures, prismatic structures or honeycomb structures.

7. The total temperature sensor according to claim 1, characterized in that: The three-periodic minimal surface unit cell filling structure filled in the sensing cavity is a Gyroid unit cell.

8. The total temperature sensor according to claim 3, characterized in that: The three-periodic minimal surface unit cell filling structure filled between the protective layer and the sensor housing is an IWP unit cell.

9. The total temperature sensor according to claim 2, characterized in that: The adhesive thermal resistor is a flexible thermal resistor.

10. The total temperature sensor according to claim 4, characterized in that: The memory alloy protective layer is a nickel-titanium shape memory alloy.

11. The total temperature sensor according to claim 2, characterized in that: The temperature measured by the adhesive thermal resistor is converted into the total air temperature through the dynamic temperature recovery coefficient.

12. The total temperature sensor according to claim 11, characterized in that: The dynamic temperature recovery coefficient is calculated through wind tunnel test according to the following expression: Among them, γ is the dynamic temperature recovery coefficient, T0 is the total airflow temperature, T g is the temperature measured by the sensor, κ is the adiabatic index, and Ma is the airflow Mach number.

13. An aircraft engine, characterized in that: The method comprises the total temperature sensor according to any one of claims 1 to 12.

14. The aircraft engine according to claim 13, characterized in that: The total temperature sensor is installed in the air intake duct of the aircraft engine.

15. A method for manufacturing a total temperature sensor, for manufacturing the total temperature sensor according to any one of claims 1 to 12, wherein a protective layer is provided on the windward surface of a sensor housing of the total temperature sensor, wherein: The following steps are involved: The main structure of the sensor except the protective layer is formed in one go using additive manufacturing technology; Based on the completed sensor main structure, the protective layer is additively manufactured; The completed sensor main structure and protective layer are integrated.

16. The method for manufacturing a total temperature sensor according to claim 15, characterized in that: The sensor main body structure except the protective layer is made of stainless steel, and the protective layer is made of nickel-titanium memory alloy.

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