Aircraft total temperature sensor shell and total temperature sensor assembly

Abstract

An aircraft total temperature sensor shell comprises a sensor protection cover, two exhaust end heating pipes and two flow guide blocks. Wherein the semi-closed sensor protection cover provides shielding for the total temperature sensor on the upstream of the flow channel, the exhaust end heating pipes and the flow guide blocks form opposite air inlet flow channels on the opening side of the sensor protection cover, an exhaust flow channel is formed between the two exhaust end heating pipes, and an exhaust channel is formed between the two flow guide blocks. Air flow enters the sensor protection cover through the air inlet channel and is exhausted through the exhaust channel and the exhaust channel. And a boundary layer flow channel is formed between the flow guide block and the exhaust end heating pipe, so that the heated airflow is directly exhausted. The aircraft total temperature sensor shell can avoid icing and prevent the heating pipe from interfering with a temperature measurement result. The invention further provides an aircraft total temperature sensor assembly.

Description

Technical Field

[0001] The invention belongs to the field of aviation engines, and in particular relates to an aircraft total temperature sensor housing and a total temperature sensor assembly. Background Art

[0002] The normal flight altitude of civil airliners is several thousand meters. The air temperature is low in high-altitude environments and contains a certain amount of water vapor. The surfaces of some parts in the aircraft's air intake structure may be frozen due to condensation of water vapor. Once the ice falls off, it will affect flight safety. Therefore, anti-icing designs are performed on structures such as the aircraft's wings and engines. In addition to the special design of the air intake structure to reduce the risk of icing, the structure with anti-icing design also introduces a heat source to avoid icing. However, during the flight of the aircraft, the total temperature sensor needs to measure the external temperature in real time. The total temperature sensor needs to be able to respond to the temperature quickly and also needs to have a high total temperature recovery efficiency. The additional anti-icing heat source will interfere with the operation of the total temperature sensor. Therefore, providing a total temperature sensor housing for an aircraft engine, which has high practical value while preventing the sensor from being interfered with while preventing icing. Summary of the invention

[0003] The object of the present invention is to provide an aircraft total temperature sensor housing to improve the measurement accuracy of the sensor. The present invention also provides an aircraft total temperature sensor assembly.

[0004] According to an embodiment of one aspect of the present invention, there is provided an aircraft total temperature sensor housing, the housing comprising a sensor protection cover, an exhaust end heating pipe and a guide block. Wherein: the sensor protection cover is configured as a semi-enclosed shell, the sensor protection cover is closed on the upstream side of the airflow direction, and has an opening on the downstream side; the exhaust end heating pipe is arranged downstream of the sensor protection cover, and two exhaust end heating pipes are arranged, and an exhaust flow channel is formed between the two exhaust end heating pipes; the guide block is arranged between the sensor protection cover and the exhaust end heating pipe and partially extends into the semi-enclosed shell, and two guide blocks are arranged, and an exhaust channel connected to the exhaust flow channel in a straight line is formed between the two guide blocks; the sensor protection cover, the guide block and the exhaust end heating pipe jointly define the intake flow channel of the total temperature sensor, so as to allow the airflow to flow into the opening from the opening along the intake flow channel, and flow out through the exhaust channel and the exhaust flow channel after contacting the total temperature sensor housing; a boundary layer flow channel is arranged between the guide block and the exhaust end heating pipe, so as to allow the airflow heated by the exhaust end heating pipe to flow out from the exhaust flow channel through the boundary layer flow channel.

[0005] The aircraft total temperature sensor housing shields the airflow directly blowing toward the temperature sensor through the sensor protection cover, and transports the airflow from the open sensor protection cover to the temperature sensor through the intake air duct arranged in the downstream direction, thereby preventing solid impurities such as dust and ice crystals mixed in the airflow from damaging the temperature sensor; the exhaust end heating pipe can heat the airflow to prevent water accumulation or ice from blocking the intake air duct; the boundary layer flow channel arranged between the exhaust end heating pipe and the guide block can directly guide the heated boundary layer hot air formed on the surface of the exhaust end heating pipe through the exhaust flow channel, thereby preventing the anti-icing heating from interfering with the temperature measurement result.

[0006] Furthermore, in some embodiments, the aircraft total temperature sensor housing further includes an air intake end heating pipe, which is arranged upstream of the sensor protection cover to shield the airflow in the flow channel that directly blows toward the sensor protection cover. The air intake end heating pipe can prevent the airflow from directly impacting the sensor protection cover and prevent ice from forming on the surface of the sensor protection cover.

[0007] Furthermore, in some embodiments, a gap is provided between the air intake end heating tube and the sensor protection cover. The gap between the air intake end heating tube and the sensor protection cover can prevent the sensor protection cover from being heated and prevent the temperature measurement result from being disturbed by the air intake end heating tube.

[0008] Furthermore, in some embodiments, the semi-enclosed shell of the sensor protection cover includes a semi-arc-shaped wall body. The semi-arc-shaped wall body can improve the aerodynamic performance of the aircraft total temperature sensor shell and reduce the airflow impact load.

[0009] Furthermore, in some embodiments, the distance between the ends of the two exhaust end heating pipes that are away from each other is greater than the width of the sensor protection cover. The distance between the ends of the two exhaust end heating pipes is greater than the width of the sensor protection cover, which can reduce the impact of the inlet air duct being shielded by the sensor protection cover and guide more airflow into the sensor protection cover.

[0010] Furthermore, in some embodiments, the cross-sectional shape of the aircraft total temperature sensor housing is axially symmetrical with respect to the straight line where the exhaust passage and the exhaust flow passage are located. The exhaust passage and the exhaust flow passage have symmetrical structures on both sides and have the same aerodynamic performance, which can improve the aerodynamic performance in the aircraft total temperature sensor housing and reduce the resistance of gas flow.

[0011] Furthermore, in some embodiments, a first guide surface extending toward the sensor protection cover is formed at the outer end of the exhaust end heating pipe, and a second arc-shaped guide surface is formed on the side of the guide block close to the exhaust end heating pipe. The first guide surface and the second guide surface can improve aerodynamic performance and reduce wind resistance between the airflow and the intake air duct.

[0012] Furthermore, in some embodiments, the width of the boundary layer flow channel is 1mm-5mm. The thickness of the boundary layer airflow heated on the surface of the exhaust end heating tube is roughly in the range of 1mm-5mm, and the boundary layer airflow can be led out through the boundary layer flow channel to reduce its interference with the temperature measurement result and improve the measurement accuracy.

[0013] According to an embodiment of another aspect of the present invention, there is provided an aircraft total temperature sensor assembly, comprising a total temperature sensor and a housing, wherein the housing is the aircraft total temperature sensor housing provided in any of the aforementioned embodiments.

[0014] Further, in some embodiments, the total temperature sensor includes two temperature sensors, an exhaust interval is formed between the two temperature sensors, and the exhaust interval is aligned with the exhaust channel. The exhaust interval is aligned with the exhaust channel, which is conducive to quickly guiding the airflow out of the sensor protection cover and reducing wind resistance. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 This is a schematic diagram of the structure of an aircraft total temperature sensor assembly in one embodiment;

[0016] Figure 2 This is a schematic diagram of an enlarged structure of an aircraft total temperature sensor assembly in one embodiment;

[0017] Figure 3 Schematic diagram of airflow direction in an aircraft total temperature sensor assembly in one embodiment.

[0018] The purpose of the above drawings is to explain the present invention in detail so that those skilled in the art can understand the technical concept of the present invention. For the sake of simplicity, the above drawings only schematically illustrate the structures related to the technical features of the present invention, and do not strictly draw the complete device and all details according to the actual proportion. DETAILED DESCRIPTION

[0019] The present invention is further described in detail below through specific embodiments in conjunction with the accompanying drawings.

[0020] Reference to "embodiments" herein means that a particular feature, structure, or characteristic described in conjunction with the embodiments may be included in at least one embodiment of the present invention. The phrase appearing in various locations in the specification does not necessarily refer to the same embodiment, nor is it limited to mutually exclusive independent or alternative embodiments. Those skilled in the art should be able to understand that the embodiments herein may be combined with other embodiments without causing structural conflicts.

[0021] In the description of this article, unless otherwise clearly specified and limited, the technical terms "installed", "connected", "connected" and the like should be understood in a broad sense, which can be a movable connection, a fixed connection or an integral connection. For ordinary technicians in this field, the specific meanings of the above terms in the embodiments of this application can be understood according to specific circumstances.

[0022] In the description of this document, terms indicating orientation or positional relationships, such as "up", "down", "left", "right", "horizontal", "vertical", "height", "length", and "width", are intended to accurately describe the embodiments and simplify the description, but are not intended to limit the parts or structures involved to have a specific orientation, be installed or operate in a specific orientation, and should not be construed as a limitation on the embodiments in this document.

[0023] In the description of this article, the terms "first", "second" and the like are only used to distinguish different objects, and cannot be understood as indicating relative importance or limiting the quantity, specific order or primary and secondary relationship of the described technical features. In the description of this article, the meaning of "plurality" is at least two.

[0024] One embodiment of the present invention provides an aircraft total temperature sensor assembly, the local structure of which is as follows: Figure 1 and Figure 2 As shown, the total temperature sensor assembly includes a shell and a total temperature sensor 4. The shell includes a sensor protective cover 1, an exhaust end heating pipe 3 and a guide block 2. With reference to the external airflow direction, the sensor protective cover 1 is a semi-enclosed shell structure, which accommodates the total temperature sensor 4 inside. The closed end of the semi-enclosed shell structure is located upstream in the airflow direction to shield the airflow blowing from the upstream, avoid the airflow directly impacting the total temperature sensor 4, and prevent the dust, ice crystals and other solid impurities mixed in the airflow from damaging the total temperature sensor 4. In a preferred embodiment, the windward side of the sensor protective cover 1 is configured as a semi-arc wall to further reduce wind resistance. The sensor protective cover 1 has an opening 9 facing downstream in the airflow direction, two exhaust end heating pipes 3 are arranged in the downstream direction of the opening 9, and two guide blocks 2 are arranged between the exhaust end heating pipe 3 and the sensor protective cover 1, and part of the guide block 2 extends from the opening 9 into the sensor protective cover 1. The gap between the two guide blocks 2 forms an exhaust channel 11, and the gap between the two exhaust end heating tubes 3 forms an exhaust flow channel 12. The exhaust channel 11 is connected to the exhaust flow channel 12 in a straight line. There is a gap between the guide block 2 and the exhaust end heating tube 3, and the gap forms a boundary layer flow channel 10. The sensor protection cover 1, the guide block 2 and the exhaust end heating tube 3 together define the intake flow channel of the aircraft total temperature sensor.

[0025] In a preferred embodiment, an air inlet heating tube 5 is also provided upstream of the sensor protective cover 1, and the air inlet heating tube 5 can shield the sensor protective cover 1, prevent the airflow from directly impacting the sensor protective cover 1, and prevent ice from forming on the surface of the sensor protective cover 1. The cross-sectional shape of the air inlet heating tube 5 can be set to a triangle or a cone to reduce wind resistance. In a further preferred embodiment, a gap is provided between the air inlet heating tube 5 and the sensor protective cover 1, so that the air inlet heating tube 5 does not contact the sensor protective cover 1, and the heat of the air inlet heating tube 5 is prevented from being transferred to the sensor protective cover 1 to interfere with it.

[0026] In a preferred embodiment, the distance between the two ends 6a and 6b of the exhaust end heating tube 3 that are far away from each other is greater than the width of the sensor protection cover 1, so that the airflow bypassing the sensor protection cover 1 can be more guided by the exhaust end heating tube 3.

[0027] In a preferred embodiment, the outer ends 6a and 6b of the exhaust end heating pipe 3 extend toward the sensor protection cover 1 to form a first guide surface with a certain curvature on its surface; the outer surface of the guide block 2 is formed with an arc-shaped second guide surface 7 at one end close to the exhaust end heating pipe 3. The first guide surface and the second guide surface 7 can guide the airflow to flow into the sensor protection cover 1 through the opening 9 more stably, thereby reducing wind resistance and vibration.

[0028] In a preferred embodiment, two total temperature sensors 4 are provided, an exhaust interval 8 is formed between the two total temperature sensors 4 , and the exhaust interval 8 is aligned with the exhaust passage 11 .

[0029] In a preferred embodiment, during the flight of the aircraft, the airflow state is as follows: Figure 3 As shown: the upstream airflow 13 is blocked by the intake end heating tube 5 and the sensor protection cover 1 in turn, and will not directly impact the total temperature sensor 4. The upstream airflow 13 bypasses the sensor protection cover 1 and impacts the surface of the exhaust end heating tube 3, and flows inward under the action of the first guide surface formed by the extension of the end 6a, 6b. The boundary layer airflow 14 close to the exhaust end heating tube 3 is heated by the exhaust end heating tube 3, so that ice or water will not accumulate on the windward surface of the exhaust end heating tube 13. The thickness of the boundary layer airflow 14 is usually about 1mm, so in the preferred embodiment, the width of the boundary layer flow channel 10 can be set to 1mm-5mm. The airflow far from the exhaust end heating tube 3 is limited by the temperature gradient of the high-speed airflow and the temperature remains unchanged. Under the guidance of the second guide surface 7 on the surface of the guide block 2, the flow direction of this part of the airflow changes to form a backflow airflow 15, and flows into the sensor protection cover 1 through the opening 9, and contacts with the total temperature sensor 4, so that the total temperature sensor 4 can measure the airflow temperature.

[0030] In a preferred embodiment, the cross-sectional structure of the engine total temperature sensor housing is axially symmetrical with respect to the straight line where the exhaust passage 11 and the exhaust flow passage 12 are located, and the aerodynamic structures on both sides of the symmetry axis are the same, so that the momentum of the reverse flow 15 flowing in from both sides of the opening 9 cancels each other, and finally enters the exhaust passage 11 through the exhaust interval 8 between the two sensors 4 to form an exhaust airflow 16. The flow rate of the exhaust airflow 16 is significantly higher than the boundary layer airflow 14, so the exhaust airflow 16 and the boundary layer airflow 14 are mixed downstream of the guide block 2, and drive the boundary layer airflow 14 to flow out from the exhaust flow passage 12 together to form an exhaust airflow 17.

[0031] In this process, the air intake end heating pipe 5 and the exhaust end heating pipe 3 of the windward side parts can be heated to prevent water accumulation or ice formation. In some embodiments, the air intake end heating pipe 5 and the exhaust end heating pipe 3 can be heated by the high temperature gas drawn from the engine, such as Figure 1 As shown, the hot air flow 18 flows into the heating pipe 5 at the air inlet end and flows out of the heating pipe 3 at the exhaust end to form a cycle. In other embodiments, the heating pipe 5 at the air inlet end and the heating pipe 2 at the exhaust end can be connected in series or in parallel on the hot air path; in other embodiments, heating can also be achieved by electric heating or other methods. The heated thin layer of airflow is guided out through the boundary layer flow channel 10 and will not come into contact with the total temperature sensor 4. The gas that the total temperature sensor 4 contacts is the backflow airflow 15. If the gas is mixed with solid particles such as dust and ice crystals, the backflow airflow 15 will be separated from the impurity particles due to inertia during the airflow turning process, so it can also better protect the total temperature sensor 4.

[0032] The purpose of the above embodiments is to further explain the present invention in detail in conjunction with the accompanying drawings so that those skilled in the art can understand the technical concept of the present invention. Based on the embodiments of the present invention, the optimization or equivalent replacement of the part structures involved, as well as the combination of implementation methods in different embodiments without conflict of structure and principle, all fall within the protection scope of the present invention.

Claims

1. An aircraft total temperature sensor housing, characterized in that: It includes a sensor protection cover, an exhaust end heating pipe and a guide block, wherein: The sensor protection cover is configured as a semi-enclosed shell, a receiving cavity is formed in the sensor protection cover to receive the total temperature sensor, the sensor protection cover is closed on the upstream side in the airflow direction, and is open on the downstream side; The exhaust end heating pipe is arranged downstream of the sensor protection cover, and two exhaust end heating pipes are provided, and an exhaust flow channel is formed between the two exhaust end heating pipes; The guide block is arranged between the sensor protection cover and the exhaust end heating pipe and partially extends into the semi-enclosed shell, and two guide blocks are arranged, and an exhaust passage connected to the exhaust flow channel in a straight line is formed between the two guide blocks; The sensor protection cover, the guide block and the exhaust end heating pipe together define an inlet airflow passage of the aircraft total temperature sensor, so as to allow airflow to flow into the sensor protection cover from the opening along the inlet airflow passage, and to flow out through the exhaust passage and the exhaust airflow passage after contacting the total temperature sensor; A boundary layer flow channel is provided between the guide block and the exhaust end heating tube to allow the airflow heated by the exhaust end heating tube to flow out of the exhaust flow channel through the boundary layer flow channel.

2. The aircraft total temperature sensor housing according to claim 1, characterized in that: It also includes an air intake end heating pipe, which is arranged upstream of the sensor protection cover to shield the airflow in the flow channel that directly blows toward the sensor protection cover.

3. The aircraft total temperature sensor housing according to claim 2, characterized in that: A gap is arranged between the air intake end heating pipe and the sensor protection cover.

4. The aircraft total temperature sensor housing according to claim 1, 2 or 3, characterized in that: The semi-enclosed shell of the sensor protection cover includes a semi-arc-shaped wall.

5. The aircraft total temperature sensor housing according to claim 1, 2 or 3, characterized in that: The distance between the ends of the two exhaust end heating pipes that are away from each other is greater than the width of the sensor protection cover.

6. The aircraft total temperature sensor housing according to claim 1, 2 or 3, characterized in that: The cross-sectional shape of the aircraft total temperature sensor housing is axially symmetrical with respect to the straight line where the exhaust passage and the exhaust flow channel are located.

7. The aircraft total temperature sensor housing according to claim 1, 2 or 3, characterized in that: A first guide surface extending toward the sensor protection cover is formed at the outer end of the exhaust end heating pipe, and an arc-shaped second guide surface is formed on one side of the guide block close to the exhaust end heating pipe.

8. The aircraft total temperature sensor housing according to claim 1, 2 or 3, characterized in that: The width of the boundary layer flow channel is 1mm-5mm.

9. An aircraft total temperature sensor assembly, comprising a total temperature sensor and a housing, characterized in that: The housing is an aircraft total temperature sensor housing as claimed in any one of claims 1 to 8.

10. The aircraft total temperature sensor assembly according to claim 9, characterized in that: The total temperature sensor includes two temperature sensors, an exhaust interval is formed between the two temperature sensors, and the exhaust interval is aligned with the exhaust passage.

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