Anti-icing total temperature sensor and aero-engine

Abstract

The invention provides an anti-icing total temperature sensor and an aero-engine, the anti-icing total temperature sensor comprises a shell, the top of the shell is fixedly installed at the installation position of an air inlet channel of the aero-engine, the shell is provided with a windward side and a leeward side, and a hot air cavity, a heat insulation cavity and a temperature measurement cavity are sequentially arranged in the shell at intervals in the direction from the windward side to the leeward side; an air inlet communicated with the temperature measuring cavity is formed in the bottom of the shell, and a sensor for measuring temperature is arranged in the temperature measuring cavity; an impact cavity is further formed in the side, away from the heat insulation cavity, of the hot air cavity, at least one communication hole is formed between the impact cavity and the hot air cavity, and at least one exhaust hole communicated with the impact cavity is further formed in the windward side of the shell and formed in the position, close to the top of the impact cavity, of the shell. According to the anti-icing total temperature sensor, the windward side of the sensor is heated by adopting a mode of combining impact heating and gas film heating, so that the sensor cannot accumulate ice to form large ice blocks under various different working conditions, and the operation safety of an aero-engine is improved.

Description

Technical Field

[0001] This invention relates to the field of aircraft engine control system technology, specifically to an anti-icing total temperature sensor and an aircraft engine. Background Technology

[0002] Modern aircraft flight control requires the accurate measurement of the total atmospheric temperature of the environment in which the aircraft operates during flight. In the aviation field, the stagnation temperature is called the total temperature, and it is measured by total temperature sensors installed on the surface of the aircraft.

[0003] For some aircraft engine total temperature sensors, icing may occur when exposed to rain, snow, or freezing weather conditions. Icing of the total temperature sensor not only leads to inaccurate temperature measurements, but the detached ice can also damage other critical components, causing significant damage.

[0004] For example, the patent with publication number "CN101042072B" describes a sensor assembly, in which... Figure 5 The system includes a pipe 14, an air outlet 32, an inner wall portion 22, and a compressor exhaust flow 30. The compressor exhaust flow is used to increase the temperature of the inner wall portion 22, thereby preventing icing.

[0005] In this method, the inner wall is not heated evenly, and ice will still form in some areas. Moreover, the gas discharged from the exhaust port is closer to the detection position, which can easily affect the detection results.

[0006] Based on this, the inventors of this application propose an anti-icing total temperature sensor and an aero-engine in order to solve the above-mentioned technical problems. Summary of the Invention

[0007] The technical problem to be solved by the present invention is to overcome the defect of poor anti-icing effect of existing anti-icing sensors, and to provide an anti-icing total temperature sensor and an aero-engine.

[0008] The present invention solves the above-mentioned technical problems through the following technical solution:

[0009] This invention provides an anti-icing total temperature sensor, characterized in that it includes:

[0010] The housing is fixedly installed at the top to the air intake of the aircraft engine. The housing has a windward side and a leeward side. A hot air chamber, a heat insulation chamber, and a temperature measuring chamber are arranged sequentially and spaced apart along the direction from the windward side to the leeward side inside the housing. An air inlet communicating with the temperature measuring chamber is opened at the bottom of the housing. A temperature sensor is located inside the temperature measuring chamber.

[0011] The hot air chamber is also provided with an impact chamber on the side away from the heat insulation chamber. At least one communication hole is provided between the impact chamber and the hot air chamber. The shell is also provided with at least one exhaust hole communicating with the impact chamber on the windward side. The exhaust hole is located on the shell near the top of the impact chamber.

[0012] According to one embodiment of the present invention, the hot gas chamber is provided with multiple rows of connecting holes at intervals along the direction of the impact chamber perpendicular to the incoming flow, so as to impact the inner wall of the impact chamber.

[0013] According to one embodiment of the present invention, the impact chamber and the hot gas chamber are arranged at the same height and correspondingly arranged in a direction perpendicular to the incoming flow;

[0014] The housing has a plurality of exhaust holes spaced apart on the windward side near the top of the impact chamber. The hot airflow discharged through the exhaust holes is used to form an air film on the windward surface for heat insulation.

[0015] According to one embodiment of the present invention, the cross-sectional dimension of the windward surface of the housing increases along the direction of the incoming flow;

[0016] The cross-sectional shape of the impact chamber and the hot gas chamber along the incoming flow direction is consistent with the shape of the windward surface.

[0017] According to one embodiment of the present invention, the cross-sectional dimension of the heat insulation cavity increases along the direction of the incoming flow on the side of the heat insulation cavity near the windward side, and the housing is provided with a vent communicating with the heat insulation cavity.

[0018] According to one embodiment of the present invention, the number of vents is at least two and they are respectively located on opposite sides of the housing;

[0019] The ventilation opening is elongated and extends in a direction perpendicular to the incoming flow.

[0020] According to one embodiment of the present invention, the height of the heat insulation cavity perpendicular to the incoming flow direction is the same as that of the hot gas cavity.

[0021] According to one embodiment of the present invention, the housing is provided with two air outlets communicating with the temperature measuring cavity, and the two air outlets are located on opposite sides of the housing along the incoming flow direction.

[0022] According to one embodiment of the present invention,

[0023] The temperature measuring cavity has an elliptical cross-sectional shape perpendicular to the direction of the incoming flow;

[0024] The temperature sensor is located on the side of the temperature measuring cavity closest to the leeward side.

[0025] According to one embodiment of the present invention, the air outlet is elongated and extends perpendicular to the direction of incoming flow.

[0026] According to one embodiment of the present invention, the top of the housing is provided with a mounting flange, and the mounting flange is installed to the mounting position of the aircraft engine via a threaded connector;

[0027] The mounting flange is also equipped with a cable socket for connecting an external cable, one end of which is connected to a temperature sensor.

[0028] The present invention also provides an aircraft engine, comprising: a body and an anti-icing total temperature sensor as described above, wherein the anti-icing total temperature sensor is disposed in the air intake passage of the body, and the hot air chamber is connected to the engine operating area.

[0029] The positive and progressive effects of this invention are as follows:

[0030] The present invention relates to an anti-icing total temperature sensor, which includes an impact chamber on one side of the hot gas chamber. Gas from the hot gas chamber impacts the inner wall of the impact chamber near the windward side of the housing through a connecting hole, thereby improving heat exchange efficiency. Furthermore, the exhaust vents on the windward side of the housing form an air film on the windward surface of the housing, which helps to insulate the outer wall of the windward side of the housing. Thus, the dual effects of impact heating and air film insulation prevent the housing from icing on the windward side, improving the anti-icing effect of the sensor. Attached Figure Description

[0031] The above 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, wherein:

[0032] Figure 1 This is an isometric view of the anti-icing total temperature sensor of the present invention;

[0033] Figure 2 for Figure 1 Front view of the anti-icing total temperature sensor;

[0034] Figure 3 for Figure 1 Side view of the anti-icing total temperature sensor;

[0035] Figure 4 for Figure 2 Sectional view of AA;

[0036] Figure 5 for Figure 3 Sectional view of BB;

[0037] Figure 6 This is a streamline diagram of the incoming flow around the anti-icing total temperature sensor of the present invention.

[0038] 1. Housing; 11. Windward side; 111. Exhaust port; 12. Leeward side; 13. Hot air chamber; 14. Insulation chamber; 141. Vent; 15. Temperature measuring chamber; 151. Air outlet; 16. Air inlet; 17. Impact chamber; 171. Connecting hole; 18. Mounting flange; 181. Cable socket;

[0039] 2. Temperature sensor. Detailed Implementation

[0040] The present invention will be further described below with reference to specific embodiments and accompanying drawings. More details are set forth in the following description in order to provide a full understanding of the present invention. However, the present invention can obviously be implemented in many other ways different from those described herein. Those skilled in the art can make similar extensions and derivations based on actual application situations without departing from the spirit of the present invention. Therefore, the scope of protection of the present invention should not be limited by the content of this specific embodiment.

[0041] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application pertains; the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the application; the terms “comprising” and “having”, and any variations thereof, in the specification, claims, and foregoing description of the drawings are intended to cover non-exclusive inclusion.

[0042] Please refer to Figures 1 to 6 This invention proposes an anti-icing total temperature sensor, which includes a housing 1. The top of the housing 1 is fixedly installed at the installation position of the air intake of the aircraft engine. The housing 1 has a windward side 11 and a leeward side 12. A hot air chamber 13, a heat insulation chamber 14, and a temperature measuring chamber 15 are sequentially spaced along the direction from the windward side 11 to the leeward side 12 inside the housing 1. An air inlet 16 communicating with the temperature measuring chamber 15 is opened at the bottom of the housing 1. The sensor for measuring temperature is located inside the temperature measuring chamber 15.

[0043] The hot air chamber 13 is also provided with an impact chamber 17 on the side away from the heat insulation chamber 14. At least one connecting hole 171 is provided between the impact chamber 17 and the hot air chamber 13. The shell 1 is also provided with at least one exhaust hole 111 on the windward side 11 that communicates with the impact chamber 17. The exhaust hole 111 is located on the shell 1 near the top of the impact chamber 17.

[0044] Please refer to Figures 1 to 3 The top of the housing 1 is provided with a mounting flange 18, which is installed to the mounting position of the aircraft engine through a threaded connector and is used with a sealing ring to provide sufficient sealing.

[0045] The mounting flange 18 is also equipped with a cable socket 181 for connecting an external cable, one end of which is connected to the temperature sensor 2.

[0046] Mounting flange 18 is used to fix the total temperature sensor. Cable socket 181 is connected to temperature sensor 2 through one end of mounting flange 18 so that the data detected by temperature sensor 2 can be transmitted to the electronic controller of the aircraft engine.

[0047] The housing 1 extends below the mounting flange 18 into the engine's intake air passage, exposed to the air for total temperature detection.

[0048] The windward surface 11 of the housing 1 is in direct contact with the cold air flow K. Therefore, the windward surface 11 is prone to icing in rainy, snowy, and freezing weather conditions. The ice formed can damage other important components after it falls. Moreover, the temperature sensor 2 needs to receive external gas for temperature measurement. Low temperature environment can also cause ice to form and block the temperature measuring cavity 15, thereby preventing the flow from entering and affecting the measurement results.

[0049] Based on this, the housing 1 of the present invention is along the incoming flow direction ( Figure 1 A hot air chamber 13, a heat insulation chamber 14, and a temperature measuring chamber 15 are sequentially arranged in the middle (K). An impact chamber 17 is arranged on the side of the hot air chamber 13 away from the heat insulation chamber 14. The impact chamber 17 is connected to the hot air chamber 13 through a connecting hole 171. Therefore, the hot air in the hot air chamber 13 can enter the impact chamber 17 through the connecting hole 171. The hot air in the impact chamber 17 will continuously impact the inner wall surface of the impact chamber 17 near the windward side 11, so as to efficiently heat the part of the shell 1 near the windward side 11.

[0050] Please continue to refer to Figures 4 to 6 The casing 1 has an exhaust port 111 located on the windward side 11 near the top of the hot air chamber 13. The exhaust port 111 continuously discharges hot gas, and the hot air forms a hot air film layer on the surface of the windward side 11. The combination of impact heating by the impact chamber 17 and the hot air film layer can prevent the windward side 11 from icing, thereby avoiding damage to other important components in the aero engine from large ice blocks falling off the windward side 11.

[0051] The air inlet 16 on the existing total temperature sensor is located on the side of the housing 1 instead of the bottom. The air inlet 16 located on the side is affected by the exhaust hot airflow, which affects the detection accuracy of the temperature sensor 2. Moreover, once there is some ice on the side of the housing 1, the ice will block the air inlet 16 and affect the accuracy of the detection data. In addition, water droplets dripping from the ice will also cause the air inlet 16 to freeze and block it, preventing the external flow from smoothly entering the temperature measuring chamber 15.

[0052] Based on this, the present invention places the air inlet 16 of the temperature sensor 2 at the bottom of the housing 1, and the exhaust port 111 at the top of the housing 1 near the impact chamber 17, so that the flow directions of the air inlet 16 and the exhaust port 111 are perpendicular. In this way, the hot air flow discharged through the exhaust port 111 is dispersed by the cold air flow on the windward side 11, and the gas received by the air inlet 16 will not be affected by the hot air discharged through the exhaust port 111, thereby improving the detection accuracy of the temperature sensor 2.

[0053] Furthermore, the air inlet 16 is located at the bottom of the housing 1, preventing water droplets from impacting and freezing, thus preventing the air inlet from freezing and becoming blocked. The incoming flow can smoothly enter the temperature measuring chamber 15, improving the effectiveness and accuracy of total temperature detection.

[0054] Please refer to Figure 5 The hot air chamber 13 is provided with multiple rows of connecting holes 171 at intervals along the direction perpendicular to the incoming flow of the impact chamber 17, so as to impact the inner wall of the impact chamber 17.

[0055] The housing 1 includes a transverse direction along the incoming flow direction and a vertical direction perpendicular to the incoming flow. The hot air chamber 13 is provided with multiple connecting holes 171 along both the transverse and vertical directions of the housing 1. The multiple connecting holes 171 are arranged in a matrix, so that the hot air flow can be transferred to the impact chamber 17 more evenly, and the hot air flow received by the inner wall of the impact chamber 17 is also more uniform.

[0056] That is, the inner wall of the impact chamber 17 near the windward side 11 will be impacted by the continuous high-temperature hot airflow from the hot air chamber 13. The high-temperature hot airflow heats the windward side 11 of the shell 1, thus reducing the probability of the shell 1 freezing on the windward side 11.

[0057] Furthermore, the impact chamber 17 and the hot air chamber 13 are arranged at the same height and correspondingly in the direction perpendicular to the incoming flow; the housing 1 has a plurality of exhaust holes 111 at intervals on the windward side 11 near the top of the impact chamber 17, and the hot air flow discharged through the exhaust holes 111 is used to form an air film on the surface of the windward side 11 for heat insulation.

[0058] After the hot airflow is discharged through the exhaust port 111, it forms a countercurrent with the incoming cold airflow. Under the action of the incoming flow, the hot airflow turns downstream and forms a hot air film on the outer wall of the windward side 11 of the casing 1. The high temperature hot air film can prevent the windward side 11 of the casing 1 from icing, so as to avoid ice block falling off and damaging other important components of the aero engine.

[0059] Please refer to Figure 1 and Figure 4 The cross-sectional dimensions of the windward surface 11 of the shell 1 increase along the direction of the incoming flow; the cross-sectional shapes of the impact chamber 17 and the hot air chamber 13 along the direction of the incoming flow are consistent with the shape of the windward surface 11.

[0060] Specifically, the windward surface 11 of the shell 1 has a conical shape, which can reduce the stagnation effect of the incoming flow on the windward surface 11 of the shell 1, thereby allowing the incoming flow to maintain a high flow velocity over the windward surface 11 of the shell 1, further reducing the possibility of icing.

[0061] The impact chamber 17 and the hot gas chamber 13 are arranged in a transverse V-shape. The impact chamber 17 and the hot gas chamber 13 are stacked and the thickness between the impact chamber 17 and the hot gas chamber 13 is uniform. In this way, the gas in the hot gas chamber 13 can enter the impact chamber 17 evenly, so that the impact flow received by the impact chamber 17 is more uniform and the heat exchange efficiency of the shell 1 is improved.

[0062] Furthermore, setting the impact chamber 17 and the hot air chamber 13 as a V-shape can reduce the average distance between the hot air chamber 13 and the outer wall of the windward side 11. On the one hand, this allows the side of the shell 1 closest to the windward side 11 to be at a relatively higher temperature due to the influence of the hot air chamber 13 and the impact chamber 17, thus better preventing icing. On the other hand, it can increase the relative distance between the hot air chamber 13 and the temperature measuring chamber 15, thereby reducing the influence of the hot air chamber 13 on temperature measurement and improving the accuracy of temperature measurement.

[0063] Furthermore, the cross-sectional dimensions of the heat insulation cavity 14 increase along the direction of the incoming flow on the side of the windward side 11, and a vent 141 communicating with the heat insulation cavity 14 is provided on the shell 1. The vent 141 is located on the side of the heat insulation cavity 14 near the temperature measuring cavity 15.

[0064] That is, the heat insulation cavity 14 is conical, which on the one hand increases the volume of the heat insulation cavity 14, making it easier for the heat insulation cavity 14 to collect more heat insulation gas and improve the heat insulation effect; on the other hand, it can reduce the temperature of the hot gas cavity 13 on the side close to the heat insulation cavity 14, further improving the heat insulation effect.

[0065] Because the hot air in the hot air chamber 13 will enter the impact chamber 17 through the connecting hole 171, the temperature of the side of the hot air chamber 13 near the heat insulation chamber 14 will also be very high due to the influence of the hot air. In order to avoid the high temperature from affecting the measurement accuracy of the temperature sensor 2, the heat insulation chamber 14 is set up for heat insulation. At the same time, the ventilation port 141 opened on the side of the heat insulation chamber 14 near the temperature measuring chamber 15 can continuously exchange heat, reduce the temperature inside the heat insulation chamber 14, and thus eliminate the impact on the temperature measurement accuracy of the temperature measuring chamber 15.

[0066] It should be noted that the height of the heat insulation cavity 14 perpendicular to the incoming flow direction is the same as that of the hot air cavity 13. This can better prevent the heat in the hot air cavity 13 from being transferred to the temperature measuring cavity 15 and affecting the actual temperature measurement effect, thereby improving the accuracy of the total temperature measurement.

[0067] Furthermore, the number of vents 141 is at least two and they are located on opposite sides of the housing 1; the vents 141 are elongated and extend in a direction perpendicular to the incoming flow.

[0068] The shape and size of the vent 141 can be adjusted according to actual needs and are not limited here. Setting the vent 141 as an elongated shape helps to increase the flow rate of gas entering the insulation chamber 14, thereby improving the heat exchange efficiency of the insulation chamber 14.

[0069] In one embodiment, the housing 1 is provided with two air outlets 151 that communicate with the temperature measuring chamber 15, and the two air outlets 151 are located on opposite sides of the housing 1 along the incoming flow direction.

[0070] The temperature measuring chamber 15 has an air inlet 16 located at the bottom of the housing 1 for introducing the gas to be measured, and two air outlets 151 for discharging the gas after detection.

[0071] The air inlet 16 is set perpendicular to the direction of the incoming flow, so that water droplets will not hit and freeze at the air inlet 16, preventing the air inlet 16 from freezing and blocking it. The airflow to be measured can smoothly enter the temperature measuring chamber 15 from the bottom of the housing 1, thus improving the accuracy of the total temperature detection.

[0072] Meanwhile, the vent 151 is located in the low-pressure area of ​​the leeward side 12, so that the air pressure at the vent 151 of the temperature measuring chamber 15 is lower than the gas pressure inside the temperature measuring chamber 15, which is conducive to the smooth discharge of the incoming flow from the vent 151 of the temperature measuring chamber 15.

[0073] Furthermore, the vent 151 is located on the side of the temperature measuring cavity 15 away from the leeward side 12; the vent 151 is elongated and extends perpendicular to the direction of the incoming flow.

[0074] That is, the vent 151 is located upstream of the temperature measuring cavity 15 along the direction of the incoming flow. The elongated vent 151 can increase the outlet area of ​​the incoming flow, so that the incoming flow entering the temperature measuring cavity 15 can be discharged quickly, thereby allowing new incoming flow to enter the temperature measuring cavity 15 quickly and ensuring real-time and rapid temperature measurement.

[0075] In some alternative embodiments, the vent 151 may also be circular, square or other shapes, and the number of vents 151 may be two or more, etc., which is not limited here.

[0076] The temperature measuring cavity 15 is elliptical, and the air inlet is circular. The radius of the air inlet is equal to the minimum radius of the elliptical cross-section of the temperature measuring cavity 15. On the one hand, this avoids the situation where a small-sized air inlet is easily blocked, preventing external flow from entering the temperature measuring cavity 15; on the other hand, it allows more gas to enter the temperature measuring cavity 15 quickly, thereby reducing the response time constant of the temperature sensor 2.

[0077] Optionally, the radius of the air inlet of the temperature measuring cavity 15 can also be smaller than the minimum cross-sectional radius of the temperature measuring cavity 15. To ensure the air intake, two, three or more air inlets can be provided.

[0078] In summary, the anti-icing total temperature sensor of the present invention has an impact chamber 17 provided on one side of the hot gas chamber 13. The gas in the hot gas chamber 13 impacts the inner wall surface of the impact chamber 17 near the windward side 11 of the housing 1 through the connecting hole 171, thereby improving the heat exchange efficiency. Moreover, the exhaust hole 111 opened on the windward side 11 of the housing 1 forms an opposition with the incoming flow, which is conducive to the formation of a hot gas film on the outer wall surface of the windward side 11 of the housing 1. In this way, the housing 1 is prevented from icing on the windward side through the dual effects of impact heating and gas film insulation, thus improving the anti-icing effect of the sensor.

[0079] The present invention also proposes an aero-engine, comprising: a main body and an anti-icing total temperature sensor as described above, wherein the anti-icing total temperature sensor is disposed in the air intake duct of the main body, and the hot air chamber 13 is connected to the engine working area.

[0080] Specifically, the anti-icing total temperature sensor is installed in the air intake of the aircraft engine, generally at the 11 o'clock position (in the same direction as the aircraft engine). The specific installation position can be adjusted according to actual needs and is not limited here.

[0081] The anti-icing total temperature sensor installed on the aero-engine of this invention uses a combination of impact heating and gas film heating to heat the windward side 11 of the sensor, so that the sensor will not accumulate ice and form large ice blocks under various operating conditions, thereby improving the operational safety of the aero-engine.

[0082] Furthermore, a heat insulation cavity 14 is provided between the hot air cavity 13 and the temperature measuring cavity 15, which can avoid the influence of hot air in the hot air cavity 13 on the measuring structure and ensure the detection accuracy of the temperature sensor 2.

[0083] The air inlet 16 of the temperature measuring chamber 15 is set perpendicular to the airflow being measured, so that the air inlet 16 is protected from the frontal impact of the incoming flow. This avoids the problem of the air inlet 16 freezing and becoming blocked, thus ensuring the normal operation of the test.

[0084] In the description of the embodiments of this application, unless otherwise expressly specified and limited, the technical terms such as "installation", "connection", "joining", and "fixing" should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integral connections; they can also refer to mechanical connections. For those skilled in the art, the specific meaning of the above terms in the embodiments of this application can be understood according to the specific circumstances.

[0085] This application uses specific terms to describe embodiments of the application. Terms such as "an embodiment," "one embodiment," and / or "some embodiments" refer to a particular feature, structure, or characteristic associated with at least one embodiment of the application. Therefore, it should be emphasized and noted that references to "an embodiment," "one embodiment," or "an alternative embodiment" in different locations throughout this specification do not necessarily refer to the same embodiment. Furthermore, certain features, structures, or characteristics in one or more embodiments of the application can be appropriately combined.

[0086] 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. An anti-icing total temperature sensor, characterized in that, include: The housing is fixedly installed at the top to the air intake of the aircraft engine. The housing has a windward side and a leeward side. A hot air chamber, a heat insulation chamber, and a temperature measuring chamber are arranged sequentially and spaced apart along the direction from the windward side to the leeward side inside the housing. An air inlet communicating with the temperature measuring chamber is opened at the bottom of the housing. A temperature sensor is located inside the temperature measuring chamber. The hot air chamber is also provided with an impact chamber on the side away from the heat insulation chamber. At least one communication hole is provided between the impact chamber and the hot air chamber. The shell is also provided with at least one exhaust hole communicating with the impact chamber on the windward side. The exhaust hole is located on the shell near the top of the impact chamber.

2. The anti-icing total temperature sensor according to claim 1, characterized in that, The hot gas chamber is provided with multiple rows of connecting holes at intervals along the direction perpendicular to the incoming flow of the impact chamber, so as to impact the inner wall of the impact chamber.

3. The anti-icing total temperature sensor according to claim 1, characterized in that, The impact chamber and the hot gas chamber are arranged at the same height and correspondingly in a direction perpendicular to the incoming flow. The housing has a plurality of exhaust holes spaced apart on the windward side near the top of the impact chamber. The hot airflow discharged through the exhaust holes is used to form an air film on the windward surface for heat insulation.

4. The anti-icing total temperature sensor according to claim 1, characterized in that, The cross-sectional dimension of the windward surface of the housing increases along the direction of the incoming flow; The cross-sectional shape of the impact chamber and the hot gas chamber along the incoming flow direction is consistent with the shape of the windward surface.

5. The anti-icing total temperature sensor according to claim 4, characterized in that, The cross-sectional dimensions of the heat insulation cavity increase along the direction of the incoming flow on the side of the windward side, and the shell is provided with a vent that communicates with the heat insulation cavity.

6. The anti-icing total temperature sensor according to claim 5, characterized in that, The number of ventilation openings is at least two, and they are located on opposite sides of the housing; The ventilation opening is elongated and extends in a direction perpendicular to the incoming flow.

7. The anti-icing total temperature sensor according to claim 4, characterized in that, The height of the heat insulation cavity perpendicular to the incoming flow direction is the same as that of the hot air cavity.

8. The anti-icing total temperature sensor according to claim 1, characterized in that, The housing is provided with two air outlets that communicate with the temperature measuring cavity, and the two air outlets are located on opposite sides of the housing along the incoming flow direction.

9. The anti-icing total temperature sensor according to claim 8, characterized in that, The temperature measuring cavity has an elliptical cross-sectional shape perpendicular to the direction of the incoming flow; The temperature sensor is located on the side of the temperature measuring cavity closest to the leeward side.

10. The anti-icing total temperature sensor according to claim 9, characterized in that, The air outlet is elongated and extends perpendicular to the direction of the incoming flow.

11. The anti-icing total temperature sensor according to claim 1, characterized in that, The top of the housing is provided with a mounting flange, which is installed to the mounting position of the aircraft engine via a threaded connector; The mounting flange is also equipped with a cable socket for connecting an external cable, one end of which is connected to a temperature sensor.

12. An aircraft engine, characterized in that, include: The body and the anti-icing total temperature sensor as described in any one of claims 1 to 11, wherein the anti-icing total temperature sensor is disposed in the air intake passage of the body, and the hot air chamber is connected to the engine operating area.

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