A total temperature sensor, an aero-engine, an aircraft and a method for measuring total temperature

Abstract

The application provides a total temperature sensor, an aero-engine, an airplane and a total temperature measuring method. The total temperature sensor comprises a base, a probe receiving part installed on the base, a windward surface with a first plane and a second plane intersecting on the windward side to form a wedge-shaped structure, a leeward surface extending from the windward surface, the leeward surface having an air outlet, a bottom end surface having an air inlet, wherein the windward surface, the leeward surface and the bottom end surface form an outer shell structure surrounding the probe receiving part in the circumferential direction and on the bottom side of the probe receiving part, the probe receiving part is located in a cavity defined by the probe outer shell structure, and the probe receiving part is fluidly connected with the outside through the air inlet and the air outlet. The total temperature sensor has simple structure, good anti-icing effect, strong bird impact resistance and good measuring performance.

Description

Technical Field

[0001] This invention relates to the field of sensors, and more particularly to a total temperature sensor, an aero-engine, an aircraft, and a method for measuring total temperature. Background Technology

[0002] In rainy, snowy, or icy weather conditions, the total temperature sensor is very likely to freeze. Generally speaking, there are two hazards associated with icing: first, the ice may block the sensor's air intake or exhaust port, thus affecting real-time temperature measurement; second, if the ice buildup on the sensor is too large, it may fall off and damage other engine components.

[0003] Meanwhile, the total temperature sensor, which is located in front of the engine intake fan, is also highly susceptible to bird strikes. Therefore, the total temperature sensor is required to have a certain degree of bird strike resistance to ensure that the sensor is not damaged in the event of a large bird strike, so as to avoid safety accidents.

[0004] Currently, most existing total temperature sensors use heating to prevent icing, which makes the sensor structure complex and difficult to manufacture.

[0005] For example, Chinese invention patent application with publication number "CN112556728A", titled "An anti-icing sensor and engine having the same", and publication date March 26, 2021, in which... Figure 1 A cross-sectional schematic diagram of the anti-icing sensor is shown. The anti-icing sensor has a sensing end 200 and an air intake assembly 11. The sensing end 200 has a windward side 220 located upstream of the direction in which the measured airflow is blown, and a leeward side 230 located downstream of the direction in which the measured airflow is blown. The air intake assembly 11 includes a pipe connector 111 and an air intake channel 112. The anti-icing sensor also includes a sensing probe 206, a housing 10, and a sensing cavity 210, a spacer 12, and a hot air cavity 110 disposed within the housing. The spacer 12 divides the interior of the housing 10 into the sensing cavity 210 and the hot air cavity 110. The air intake assembly 11 connects the hot air cavity 110 with the hot air region outside the housing 10. The sensing probe 206 is located inside the sensing cavity 210. The sensing cavity 210 also has an air inlet 201 facing the windward side 220. The air inlet 201 has a structure in which the diameter gradually decreases from the outside to the inside, as shown in the figure. The air inlet 201 is used to allow the gas to be measured to flow into the sensing cavity 210 from the outside for detection. A guide ring 204 is provided on the housing 10 at the air inlet 201. Summary of the Invention

[0006] The purpose of this invention is to provide a total temperature sensor.

[0007] The purpose of this invention is to provide an aircraft engine.

[0008] The purpose of this invention is to provide an aircraft.

[0009] The purpose of this invention is to provide a method for measuring total temperature.

[0010] According to one aspect of the present invention, a total temperature sensor includes: a base; a probe sensing portion mounted on the base; a windward surface having a first plane and a second plane, the first plane and the second plane intersecting on the windward side to form a wedge-shaped structure; a leeward surface extending from the windward surface, the leeward surface having an air outlet; and a bottom surface having an air inlet; wherein the windward surface, the leeward surface, and the bottom surface constitute a shell structure surrounding the probe sensing portion circumferentially and on its bottom side; the probe sensing portion is located within a cavity defined by the probe shell structure, and the probe sensing portion is fluidly connected to the outside environment through the air inlet and the air outlet.

[0011] In one or more specific embodiments of the total temperature sensor, the vent is located in a region on the leeward side near the intersection line of the leeward side and the windward side.

[0012] In one or more embodiments of the total temperature sensor, the leeward side extends smoothly from the windward side.

[0013] In one or more specific embodiments of the total temperature sensor, the cross-section of the chamber is elliptical.

[0014] In one or more specific embodiments of the total temperature sensor, the sensing portion of the probe includes a platinum resistance thermometer.

[0015] In one or more embodiments of the total temperature sensor, the angle between the first plane and the second plane is greater than 30° and less than 75°.

[0016] In one or more embodiments of the total temperature sensor, the cross-sectional profile of the housing is a rhomboid profile.

[0017] In one or more specific embodiments of the total temperature sensor, the base includes a cable socket, a flange, and a mounting section. The cable socket is used to connect to an external cable, the flange is used to fix the total temperature sensor to a mounting wall by bolts, and the mounting section is used to be placed inside the mounting wall.

[0018] According to one aspect of the present invention, an aircraft engine includes a total temperature sensor as described above.

[0019] In one or more specific embodiments of the aircraft engine, the total temperature sensor is installed in the air intake of the aircraft engine.

[0020] An aircraft according to one aspect of the present invention includes a total temperature sensor as described above.

[0021] According to one aspect of the present invention, a method for measuring total temperature includes: a total temperature sensor probe sensing part being surrounded by a housing and located within a cavity defined by the housing; an air outlet being provided on the leeward side of the housing and an air inlet being provided on the bottom surface of the housing; the total temperature sensor probe sensing part being fluidly connected to the outside through the air outlet and the air inlet, a portion of the outside airflow passing through the surface of the air outlet causing a negative pressure to be formed in the cavity, and the negative pressure driving a portion of the outside airflow to be directly drawn into the cavity from the bottom through the air inlet.

[0022] The beneficial effects of the present invention include, but are not limited to:

[0023] The overall structure of the total temperature sensor achieves good anti-icing performance. The wedge-shaped structure itself prevents ice buildup on the windward side, preventing the formation of large ice blocks. Simultaneously, the outer shell structure consisting of the windward side, leeward side, and bottom surface, along with the connection of the probe sensing part to the external fluid via air inlet and outlet ports, all protect the probe sensing part, preventing it from being directly affected by liquid water droplets or ice crystals contained in the incoming flow. Because the air inlet and outlet ports are not located on the windward side, they avoid direct impact from the airflow, making it difficult for liquid water droplets in the airflow to accumulate at the air inlet and freeze, blocking the air outlet. Furthermore, the wedge-shaped structure formed by the first and second planes is part of the outer shell structure. The windward side of the outer shell structure forms a wedge-shaped structure as a whole, which diverts the incoming flow and creates a large airflow velocity at the intersection of the windward and leeward sides. The high-speed airflow reduces the pressure near the air outlet, and the gas in the chamber continuously flows out through the air outlet to form an internal negative pressure. The external gas enters the chamber through the air inlet, thereby achieving airflow and ensuring the measurement performance of the total temperature sensor. Attached Figure Description

[0024] The above-described and other features, properties, and advantages of the present invention will become more apparent from the following description taken in conjunction with the accompanying drawings and embodiments, in which the same reference numerals always denote the same features. It should be noted that these drawings are merely illustrative and are not drawn to scale, and should not be construed as limiting the scope of protection actually claimed by the present invention, wherein:

[0025] Figure 1 This is a cross-sectional schematic diagram of a prior art sensor;

[0026] Figure 2 This is a front view schematic diagram of a total temperature sensor according to one embodiment;

[0027] Figure 3 This is a longitudinal cross-sectional schematic diagram of a total temperature sensor according to one embodiment;

[0028] Figure 4 A bottom view of one embodiment of the total temperature sensor;

[0029] Figure 5 This is a right-side schematic diagram of a total temperature sensor according to one embodiment;

[0030] Figure 6 Based on Figure 2 A cross-sectional view of section AA, the front view of the total temperature sensor;

[0031] Figure 7 A longitudinal cross-sectional schematic diagram of a total temperature sensor according to another embodiment;

[0032] Figure 8 A three-dimensional schematic diagram of a total temperature sensor according to one embodiment;

[0033] Figure 9 A bottom view schematic diagram of the total temperature sensor according to another embodiment;

[0034] Figure 10 A schematic diagram of the total temperature sensor according to one embodiment;

[0035] Figure 11 This is a flowchart illustrating one embodiment of a total temperature measurement method.

[0036] Figure label:

[0037] 200 - Sensing end, 220 - Windward side, 230 - Leeward side, 201 - Air inlet, 204 - Air guide ring;

[0038] 206 - Sensing probe;

[0039] 10-House, 12-Spacer, 110-Hot air chamber, 210-Sensing chamber;

[0040] 11-Air eliminator assembly, 111-Pipe connector, 112-Air eliminator channel;

[0041] 1-Base, 101-Cable socket, 102-Flange, 103-Mounting section;

[0042] 2-Windward side, 20-Windward side, 201-First plane, 202-Second plane;

[0043] 3-Leaf side, 30-Leaf side;

[0044] 23 - The line of intersection between the windward and leeward sides;

[0045] 4- Bottom end face;

[0046] 5 - Sensing part of the probe; 51, 52 - Platinum resistance thermometers;

[0047] 6-Air intake port;

[0048] 7 - Vent hole; 701, 702, 703 - Small holes; 704 - Long holes;

[0049] 8-Cavity, 9-Outer shell structure. Detailed Implementation

[0050] Reference will now be made in detail to various embodiments of the invention, examples of which are shown in the accompanying drawings and described below. Although the invention will be described in conjunction with exemplary embodiments, it should be understood that this specification is not intended to limit the invention to those exemplary embodiments. Rather, the invention is intended to cover not only these exemplary embodiments, but also various alternatives, modifications, equivalents, and other embodiments that may be included within the spirit and scope of the invention as defined by the appended claims.

[0051] In the following description, the orientation or positional relationship indicated by terms such as "circumferential," "bottom," "top," or other directional terms is based on the orientation or positional relationship shown in the accompanying drawings and is only for the convenience of describing the invention and simplifying the description, and is not intended to indicate or imply that the device or component referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. Furthermore, this application uses specific terms to describe embodiments of the invention. For example, "an embodiment" and / or "an embodiment" refers to a feature, structure, or characteristic associated with at least one embodiment of the invention. Therefore, it should be emphasized and noted that "an embodiment," "an embodiment," or "an alternative embodiment" mentioned twice or more in different locations in this specification do not necessarily refer to the same embodiment. In addition, certain features, structures, or characteristics in one or more embodiments of the invention can be appropriately combined.

[0052] This application also uses flowcharts to illustrate the operations performed by the system according to embodiments of this application. It should be understood that the preceding or following operations are not necessarily performed in exact order. Other operations may be added to these processes, or one or more operations may be removed from these processes.

[0053] refer to Figure 2 Combination Figure 3 , Figure 4 As shown, in one embodiment, an example of the specific structure of the total temperature sensor may include a base 1, a probe sensing part 5, a windward surface 2, a leeward surface 3, and a bottom surface 4. For example... Figure 3 As shown, the sensing part 5 of the probe is mounted on the base 1. Figure 4As shown, the windward side 2 has a first plane 201 and a second plane 202, which intersect at the windward side 20 to form a wedge-shaped structure. The leeward side 3 extends from the windward side 2, specifically from the first plane 201 and the second plane 202, and the angle α between the leeward side 3 and the windward side 2 is no greater than 180°. The leeward side 3 has an air outlet 7, and the bottom end face 4 has an air inlet 6. The windward side 2, the leeward side 3, and the bottom end face 4 constitute a housing structure 9 that surrounds the probe sensing part 5 circumferentially and on its bottom side. The top of the housing structure 9 is sealed by the base 1. The probe sensing part 5 is located within the chamber 8 defined by the housing structure 9, and the probe sensing part 5 is fluidly connected to the outside environment through the air inlet 6 and the air outlet 7. The overall structure of the total temperature sensor achieves a good anti-icing effect. The wedge-shaped structure itself prevents ice buildup on the windward side, preventing the formation of large ice blocks. Simultaneously, the outer shell structure, consisting of the windward, leeward, and bottom surfaces, along with the connection of the probe's sensing element to the external fluid via the air inlet and outlet, all protect the probe's sensing element from direct impact by liquid water droplets or ice crystals in the incoming flow. Since the air inlet and outlet are not located on the windward side, they avoid direct airflow impact, making it difficult for liquid water droplets to accumulate and freeze at the air inlets, thus preventing blockage. Furthermore, the wedge-shaped structure formed by the first and second planes is part of the outer shell structure. The windward side of the outer shell structure forms a wedge shape, causing the incoming flow to be diverted at the intersection of the windward and leeward sides, creating a higher airflow velocity. This high-speed airflow reduces the pressure near the outlet, causing gas to continuously flow out of the chamber through the outlet, creating an internal negative pressure. External gas then enters the chamber through the air inlet, thus achieving airflow and ensuring the measurement performance of the total temperature sensor.

[0054] Furthermore, using negative pressure to drive the air intake eliminates the need for a guide structure, as described in the background section, to guide the air inlet, thus preventing icing and blockage. This is because the inventors discovered through long-term practice that, without a heating element to heat the sensor, a guide structure at the air intake is prone to icing due to airflow impact, blocking the air intake channel. Additionally, since the wedge-shaped structure formed by the first and second planes is part of the outer shell structure, it offers stronger bird strike resistance compared to adding a small wedge structure to the sensor itself.

[0055] The total temperature sensor described in the above embodiments is particularly suitable for installation in the air intake of an aircraft engine. This is because a total temperature sensor installed in front of the engine intake fan would find it difficult to draw hot air from the compressor for anti-icing purposes and would also need a certain level of bird strike resistance. As mentioned above, the total temperature sensor described in the above embodiments has good anti-icing performance and bird strike resistance. However, it should be understood that the total temperature sensor described above is not limited to installation in the air intake; it can also be installed in other locations. Furthermore, it is not limited to aircraft engines; it can also be installed on the aircraft itself, such as at the wingtip, top of the tailpipe, side of the nose, or other locations where airflow is not easily disturbed. In all these cases, the advantages of the total temperature sensor described in the above embodiments—effective anti-icing and / or bird strike resistance without the need for heating components—can be utilized.

[0056] refer to Figure 2 Combination Figure 5 As shown, in one embodiment, an example of the specific structure of the total temperature sensor is that the vent 7 is located in the region of the leeward side 3, close to the intersection line 23 of the leeward side 3 and the windward side 2. Specifically, the distance of the vent 7 from the intersection line 23 of the leeward and windward sides is less than the distance of the vent 7 from the leeward side 30. This allows the airflow velocity near the vent to be as fast as possible, creating a sufficiently strong negative pressure in the chamber and reducing the time constant, thus ensuring measurement performance. However, the time constant cannot be too small. To obtain a more accurate total temperature measurement, it is necessary to ensure that the airflow has a certain residence time in the chamber. The specific distance between the vent and the intersection line of the leeward and windward sides can be precisely adjusted through simulation or experimentation according to actual needs.

[0057] refer to Figure 2 Combination Figure 4 As shown, in one embodiment, an example of the specific structure of the total temperature sensor can be that the leeward side 3 extends smoothly from the windward side 2. This can reduce the airflow deceleration from the windward side 2 to the leeward side 3, and make the airflow speed near the outlet as fast as possible, so that a sufficiently strong negative pressure is formed in the chamber, allowing new gas to continuously enter the chamber, which is conducive to the flow of air and gives the total temperature sensor good measurement capability.

[0058] refer to Figure 6 Combination Figure 3 As shown, in one embodiment, an example of the specific structure of the total temperature sensor is that the cross-section of the chamber 8 is elliptical. Compared with cylindrical or cubic chambers, the elliptical cylindrical chamber ensures that the chamber has a larger space, which is conducive to the formation of total temperature, while also ensuring that the windward side has a thicker shell wall, which has better structural strength and can greatly improve the ability to resist bird strikes.

[0059] refer to Figure 3 Combination Figure 7As shown, the sensing part 5 of the probe includes platinum resistance thermometers. The sensing part 5 can include multiple platinum resistance thermometers, and their lengths can be determined through simulation or experimentation as needed. The farther the platinum resistance is from the air inlet 6 (i.e., the shorter its length), the larger the total temperature measurement time constant; conversely, the closer it is to the air inlet 6 (i.e., the longer its length), the smaller the total temperature measurement time constant. Figure 3 In the illustrated embodiment, the sensing part 5 of the probe includes two Pt200 type platinum resistance thermometers 51, and the air outlet 7 includes three small holes 701, 702, and 703. The bottom end of the platinum resistance thermometer 51 is located at the middle air outlet 702. Figure 7 In the embodiment shown, the sensing part 5 of the probe includes two Pt200 type platinum resistance thermometers 52, and the air outlet includes three small holes 701, 702, and 703. The bottom end of the platinum resistance thermometer 52 is located at the lowest air outlet 703.

[0060] In one implementation, such as Figure 7 As shown, the vent 7 includes multiple small holes 701, 702, and 703. In another embodiment, as... Figure 8 As shown, the vent 7 is an elongated 704 hole. Both small-hole and elongated hole structures have their advantages and disadvantages. Small-hole structures are stronger and easier to adapt to different design modifications, accommodating platinum resistance thermometers of varying lengths, thus offering wider applicability. Elongated holes are larger and less prone to clogging, with faster airflow and a smaller time constant. In practice, the choice can be made based on specific needs.

[0061] refer to Figure 2 As shown, in one embodiment, an example of the specific structure of the total temperature sensor can also be that the angle β between the first plane 201 and the second plane 202 is greater than 30° and less than 75°. The angle β between the first plane 201 and the second plane 202 is obtained by simulation calculation. A larger wedge-shaped surface greatly enhances the airflow velocity outside the air outlet on the leeward side, which is conducive to forming a pressure drop between the inside and outside of the cavity and facilitates airflow. The better the airflow, the smaller the time constant. However, the time constant cannot be too small. To ensure the accuracy of the measurement, it is necessary to ensure that the airflow has a certain residence time in the cavity. The influence of different angles on the airflow velocity outside the air outlet on the leeward side of the sensor can be confirmed by simulation calculation or experiment according to actual needs, and the appropriate angle can be selected.

[0062] refer to Figure 4 As shown, in one embodiment, another example of the specific structure of the total temperature bed dryer is that the cross-sectional profile of the probe housing is a rhombus shape. This ensures a high airflow velocity outside the air outlet while reducing the weight of the total temperature sensor. This embodiment is a preferred choice. It should be understood that the rhombus shape described here is not strictly rhomboid; for example… Figure 4 The windward and leeward sides shown are connected by a smooth, fluid extension, rather than the sharp angles of a strict rhombus.

[0063] refer to Figure 9 As shown, in one optional embodiment, the two leeward surfaces 3 extending from the first plane 201 and the second plane 202 are parallel to each other. In another optional embodiment, the angle α between the windward surface 2 and the leeward surface 3 is 180 degrees. The larger the angle α between the windward surface 2 and the leeward surface 3, the smaller the decrease in airflow velocity outside the leeward surface. However, to maintain the sealing of the probe housing, the weight of the sensor will also increase accordingly. In practice, a suitable selection can be made through simulation calculations or experiments as needed.

[0064] refer to Figure 10 As shown, in one embodiment, the base 1 includes a cable socket 101, a flange 102, and a mounting section 103. The cable socket 101 is used to connect to an external cable, the flange 102 is used to fix the total temperature sensor to the mounting wall via bolts, and the mounting section 103 is placed inside the mounting wall. When the total temperature sensor is fixed to the mounting location via bolts and flange 102, a gasket can be used to ensure sufficient sealing at the mounting location. The diameter and length of the mounting section 103 are adjusted according to the actual installation position and the structure of the mounting location. The length of the sensor mounting section 103 should be close to the thickness of the mounting wall. The remaining sensor probe extends into the engine flow channel for measurement.

[0065] refer to Figure 11 As shown, in one embodiment, an example of the specific steps of the total temperature measurement method may include:

[0066] The sensing part of the total temperature sensor probe is configured to be surrounded by a housing and located within the cavity defined by the housing; an air outlet is provided on the leeward side of the housing, and an air inlet is provided on the bottom side of the housing.

[0067] The sensing part of the total temperature sensor probe is fluidly connected to the outside through the air outlet and the air inlet. A portion of the external airflow passes through the surface of the air outlet, creating a negative pressure in the chamber. This negative pressure drives a portion of the external airflow to be directly drawn into the chamber from the bottom through the air inlet.

[0068] The gas flowing over the outer surface of the vent has a high velocity and low pressure. Gas continuously flows out of the vent, creating a negative pressure within the chamber. New gas enters through the inlet, achieving airflow. This eliminates the need for a guide structure as described in the background section; instead, gas is directly drawn in under negative pressure. The advantages, as mentioned above, are that no guide structure is needed, preventing the guide structure from freezing and blocking the intake channel due to airflow carrying droplets or ice crystals impacting it. For example, in the structure of the total temperature sensor described above, the windward side 2 has a first plane 201 and a second plane 202. The first plane 201 and the second plane 202 intersect at the windward side 20 to form a wedge-shaped structure. The leeward side 3 extends from the first plane 201 and the second plane 202. The larger wedge-shaped structure diverts the incoming flow and accelerates the diverted airflow, creating a higher airflow velocity at the intersection of the windward and leeward sides. The sensing part of the total temperature sensor probe is surrounded by a shell structure 9 consisting of a first plane 201, a second plane 202, a leeward surface 3, and a bottom surface 4. It is located in a chamber 8 defined by the shell structure 9. An air outlet 7 is opened on the leeward surface 3, and an air inlet 6 is opened on the bottom surface 4. The high-speed airflow outside the air outlet 7 reduces the pressure near the air outlet 7. The gas in the chamber 8 flows out continuously through the air outlet 7, forming an internal negative pressure. The external gas enters the chamber through the air inlet 6, thereby achieving airflow and ensuring the measurement performance of the total temperature sensor.

[0069] In summary, the beneficial effects of the total temperature sensor, aero-engine, aircraft, and method for measuring total temperature described in the above embodiments include, but are not limited to, one or a combination of the following:

[0070] 1. Excellent anti-icing effect: The sharp wedge structure of the total temperature sensor and the design of the air inlet and outlet holes can prevent the air inlet and outlet holes from being blocked by ice. The protective shell structure prevents the sensing part of the probe from being directly impacted by the incoming flow containing droplets or ice crystals, and the windward side of the sensor will not accumulate ice to form large ice blocks under various operating conditions.

[0071] 2. Strong bird strike resistance: The overall wedge-shaped structure can effectively improve bird strike resistance; at the same time, the elliptical cylindrical cavity helps to improve bird strike resistance compared to cylindrical or cubic inner cavities, thus possessing good bird strike resistance.

[0072] 3. Excellent temperature measurement performance: The total temperature sensor described in this embodiment has a large wedge-shaped surface, which greatly enhances the airflow velocity outside the air outlet on the leeward side, which is conducive to the formation of pressure drop inside and outside the outlet and facilitates airflow, allowing new gas to continuously enter the sensor chamber; in addition, the elliptical cylindrical chamber is conducive to the formation of total temperature, giving the total temperature sensor a good ability to measure total temperature.

[0073] 4. Simple structure: The total temperature sensor described in this embodiment has a simple structure and can be manufactured using various existing mature processes (such as casting).

[0074] While the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the invention. Any variations and modifications can be made by those skilled in the art without departing from the spirit and scope of the invention. Therefore, any modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of the present invention, without departing from the scope of the invention, fall within the protection scope defined by the claims of the present invention.

Claims

1. A total temperature sensor, characterized in that, include: Base; The sensing part of the probe is mounted on the base; The windward side has a first plane and a second plane, and the first plane and the second plane intersect on the windward side to form a wedge-shaped structure; The leeward side extends from the windward side and has air vents. The bottom surface has an air inlet. The windward side, the leeward side, and the bottom side form a shell structure that surrounds the probe sensing part around the periphery and the bottom side of the probe sensing part; the probe sensing part is located in the cavity defined by the probe shell structure, the air inlet and the air outlet are not located on the windward side, and the probe sensing part is fluidly connected to the outside through the air inlet and the air outlet. The wedge-shaped structure formed by the first plane and the second plane is part of the outer shell structure. The windward side of the outer shell structure forms a wedge-shaped structure as a whole. The airflow formed at the intersection of the windward and leeward sides caused by the wedge-shaped structure reduces the pressure near the air outlet. The gas in the chamber flows out through the air outlet to form an internal negative pressure, and the external gas enters the chamber through the air inlet, thereby achieving airflow.

2. The total temperature sensor according to claim 1, characterized in that, The air outlet is located in the region of the leeward side, close to the intersection line of the leeward side and the windward side.

3. The total temperature sensor according to claim 1, characterized in that, The leeward side extends smoothly from the windward side.

4. The total temperature sensor according to claim 1, characterized in that, The cross-section of the chamber is elliptical.

5. The total temperature sensor according to claim 1, characterized in that, The sensing part of the probe includes a platinum resistance thermometer.

6. The total temperature sensor according to claim 1, characterized in that, The angle between the first plane and the second plane is greater than 30° and less than 75°.

7. The total temperature sensor according to claim 5, characterized in that, The cross-sectional profile of the outer shell is a rhombus shape.

8. The total temperature sensor according to claim 1, characterized in that, The base includes a cable socket, a flange, and a mounting section. The cable socket is used to connect to an external cable, the flange is used to fix the total temperature sensor to the mounting wall by bolts, and the mounting section is used to be placed inside the mounting wall.

9. An aircraft engine, characterized in that, Including the total temperature sensor as described in any one of claims 1-8.

10. The aero-engine according to claim 9, characterized in that, The total temperature sensor is installed in the air intake of the aircraft engine.

11. An aircraft, characterized in that, Including the total temperature sensor as described in any one of claims 1-8.

12. A method for measuring total temperature, characterized in that, The total temperature sensor as described in any one of claims 1-8 includes: The sensing part of the total temperature sensor probe is configured to be surrounded by a housing and located within the cavity defined by the housing; an air outlet is provided on the leeward side of the housing, and an air inlet is provided on the bottom side of the housing. The sensing part of the total temperature sensor probe is fluidly connected to the outside through the air outlet and the air inlet. A portion of the external airflow passes through the surface of the air outlet, creating a negative pressure in the chamber. This negative pressure drives a portion of the external airflow to be directly drawn into the chamber from the bottom through the air inlet.

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