Temperature sensor of aero-engine and aero-engine

Abstract

The invention discloses a temperature sensor of an aero-engine and the aero-engine, and the temperature sensor of the aero-engine comprises a temperature sensing part (1) which is configured to sense the temperature; the wing-shaped flow guide component (2) is provided with an installation cavity (21) for containing the temperature sensing component (1), the installation cavity (21) is located between a front edge (22) and a tail edge (23) in the length direction of a wing chord of the flow guide component (2), and at least one end, in the thickness direction of the flow guide component (2), of the installation cavity (21) is an open end.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, and more specifically, to a temperature sensor for an aircraft engine and an aircraft engine. Background Technology

[0002] Because clouds may contain metastable supercooled liquid water with temperatures below freezing, icing can easily occur on the surfaces of aircraft's windward components when they pass through these clouds. For aircraft engine components, such as hoods, fan blades, intake manifolds, and engine sensors, the probability of icing is even higher due to the acceleration and cooling of airflow caused by the engine's suction.

[0003] Engine temperature sensors are used to measure the temperature at the location of corresponding engine components, and include both total temperature and static temperature sensors. After obtaining the temperature signal, the temperature sensor feeds it back to the engine and aircraft control systems for their respective control functions. Icing on the temperature sensor's sensing surface will cause the sensor to malfunction, transmitting incorrect signals to the control system and rendering it inoperable.

[0004] like Figure 1 As shown, in existing conventional sensor configurations, a cover plate 3 is directly placed at the air inlet 2 of the temperature measurement chamber of sensor 1, allowing water droplets to directly impact the cover plate 3, thus preventing water droplets from entering the temperature measurement chamber of sensor 1 and causing icing. This configuration has a large overall frontal area, resulting in a significant change in the velocity and direction of the airflow, leading to substantial airflow losses. Sensor 1 and cover plate 3 have a significant impact on the entire flow field, reducing the intake uniformity of the main airflow path of the aero-engine and affecting engine performance. Simultaneously, the sensor's overall size and weight are large, increasing engine weight. Traditional sensor anti-icing methods and airflow directions are as follows... Figure 1 As shown. Summary of the Invention

[0005] The present invention aims to provide a temperature sensor for an aircraft engine and an aircraft engine, so as to improve the problem of inaccurate detection results caused by icing in the temperature sensor in the prior art.

[0006] According to one aspect of the present invention, a temperature sensor for an aircraft engine is provided, the temperature sensor comprising:

[0007] A temperature sensing element is configured to sense temperature; and

[0008] The airfoil-shaped airflow guide has a mounting cavity for accommodating a temperature sensing component. The mounting cavity is located between the leading edge and the trailing edge along the length of the airflow guide's chord. At least one end of the mounting cavity in the thickness direction of the airflow guide is an open end.

[0009] In some embodiments, both ends of the mounting cavity along the thickness direction of the flow guide are open ends, so that the mounting cavity forms a flow channel extending from one end of the flow guide along the thickness direction to the other end.

[0010] In some embodiments, the flow channel is arranged at an angle relative to the thickness direction.

[0011] In some embodiments, the first end of the flow channel along the thickness direction is closer to the leading edge of the flow guide than the second end.

[0012] In some embodiments, the area of ​​the flow channel cross-section gradually increases along the direction closer to the second end.

[0013] In some embodiments, the first end of the flow channel is disposed on the pressure surface of the flow guide component to form an air inlet, and the second end of the flow channel is disposed on the suction surface of the flow guide component to form an exhaust outlet.

[0014] In some embodiments, the thickness of the flow guide increases and then decreases from the leading edge to the trailing edge, and the second end of the flow channel is the side near the trailing edge where the thickness of the flow guide is at its maximum.

[0015] In some embodiments, in a cross-section perpendicular to the length direction of the flow guide member, the leading edge is arc-shaped and the trailing edge is pointed.

[0016] In some embodiments, the flow guide includes a first portion having a leading edge and a second portion having a trailing edge, the first portion and the second portion being spaced apart to form a mounting cavity.

[0017] In some embodiments, the temperature sensor further includes a first end cap and a second end cap respectively disposed at both ends of the first part and the second part along the length direction of the flow guide member, one end of the first part and the second part along the length direction of the flow guide member being connected to the first end cap, and the other end being connected to the second end cap.

[0018] In some embodiments, at least one of the first part and the second part is a hollow structure.

[0019] According to another aspect of the invention, an aircraft engine is also disclosed, which includes the temperature sensor described above.

[0020] By applying the technical solution of this application, the leading edge of the airfoil-shaped guide component is the windward end. The optimized shape of the sensor can effectively reduce the interference of the sensor on the main flow field of the aero-engine. At the same time, since the temperature sensing component is placed in the mounting cavity of the guide component and does not protrude from the pressure surface and suction surface of the guide component, it is beneficial to prevent water droplets from directly hitting the temperature sensing component to achieve an anti-icing effect.

[0021] Other features and advantages of the invention will become clear from the following detailed description of exemplary embodiments of the invention with reference to the accompanying drawings. Attached Figure Description

[0022] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0023] Figure 1 A schematic diagram of the structure of a temperature sensor assembly for a prior art aircraft engine is shown.

[0024] Figure 2 A schematic diagram showing the parameters of the wing according to an embodiment of the present invention is provided.

[0025] Figure 3 A three-dimensional structural schematic diagram of a temperature sensor for an aircraft engine according to an embodiment of the present invention is shown;

[0026] Figure 4 A three-dimensional structural schematic diagram of the temperature sensor for an aircraft engine, according to an embodiment of the present invention, is shown from another angle.

[0027] Figure 5 A front view schematic diagram of the temperature sensor for an aero-engine according to an embodiment of the present invention is shown;

[0028] Figure 6 It shows Figure 4 A schematic diagram of the cross-sectional structure of AA; and

[0029] Figure 7 A schematic diagram of the airflow direction of a temperature sensor for an aircraft engine according to an embodiment of the present invention is shown.

[0030] In the picture:

[0031] 1. Temperature sensing component; 2. Flow guiding component; 21. Mounting cavity; 211. First end; 212. Second end; 22. Leading edge; 23. Trailing edge; 24. First part; 25. Second part; 3. First end cap; 4. Second end cap. Detailed Implementation

[0032] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit the present invention or its application or use. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0033] 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.

[0034] In this document, the term "embodiment" means that a particular feature, structure, or characteristic described in connection with an embodiment may be included in at least one embodiment of this application. The appearance of this phrase in various places throughout the specification does not necessarily refer to the same embodiment, nor is it a separate or alternative embodiment mutually exclusive with other embodiments. It will be explicitly and implicitly understood by those skilled in the art that the embodiments described herein can be combined with other embodiments.

[0035] In the description of this application, it should be noted that, unless otherwise stated, "a plurality of" means two or more; the terms "upper," "lower," "left," "right," "inner," and "outer," etc., indicating orientation or positional relationships, are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element 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 on this application. Furthermore, the terms "first," "second," and "third," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance. "Vertical" is not vertical in the strict sense, but within the allowable tolerance range. "Parallel" is not parallel in the strict sense, but within the allowable tolerance range.

[0036] The directional terms used in the following description refer to the directions shown in the figures and are not intended to limit the specific structure of this application. It should also be noted in the description of this application that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0037] Unless otherwise specified, the terms "comprising" and "including" as used in this application can be open-ended or closed-ended. For example, "comprising" and "including" can mean that other components not listed may also be included, or that only the listed components may be included.

[0038] Unless otherwise specified, the term "or" is inclusive in this application. For example, the phrase "A or B" means "A, B, or both A and B". More specifically, the condition "A or B" is satisfied by any of the following conditions: A is true or exists and B is false or does not exist; A is false or does not exist and B is true or exists; or both A and B are true or exist.

[0039] See Figure 2 The main parameters of the wing include the leading edge Le, trailing edge Te, mid-curve Mcl, chord Ac, chord length Cl, and thickness T.

[0040] in,

[0041] Leading edge (Le) refers to the edge of the leading edge of the wing, and leading edge refers to the windward end of the wing.

[0042] Trailing edge (Te) refers to the edge at the rear end of the wing;

[0043] The mid-curve Mcl refers to the line connecting the midpoints of the pressure and suction surfaces of an airfoil.

[0044] The chord Ac is the line connecting the leading edge and trailing edge of the wing.

[0045] Chord length Cl refers to the length of the wing chord;

[0046] Thickness T refers to the dimension of the wing in the direction of the vertical chord Ac or the mid-curve Mcl.

[0047] See Figure 3 As shown in Figure 6, the temperature sensor for the aircraft engine in this embodiment includes a temperature sensing component 1 and an airfoil-shaped airflow guiding component 2.

[0048] Temperature sensing component 1 is configured to sense temperature. Airfoil-shaped airflow guide 2 is provided with mounting cavity 21 for accommodating temperature sensing component 1. Mounting cavity 21 is located between leading edge 22 and trailing edge 23 along the length direction of airflow guide 2's chord. At least one end of mounting cavity 21 in the thickness direction of airflow guide 2 is open.

[0049] In the technical solution of this embodiment, the leading edge of the airfoil-shaped guide component 2 is the windward end. The optimized shape of the sensor can effectively reduce the interference of the sensor on the main flow field of the aero-engine. At the same time, since the temperature sensing component 1 is placed in the mounting cavity 21 of the guide component 2 and does not protrude from the pressure surface and suction surface of the guide component 2, it is beneficial to prevent water droplets from directly hitting the temperature sensing component 1 so that the sensor has an anti-icing effect.

[0050] In some embodiments, the temperature sensing component 1 includes a temperature probe, which can be a thermocouple or a resistance temperature detector (RTD) and is encased in a metal cylinder to achieve the sensor's temperature measurement function.

[0051] Both ends of the mounting cavity 21 along the thickness direction of the flow guide 2 are open, so that the mounting cavity 21 forms a flow channel extending from one end of the flow guide 2 along the thickness direction to the other end. See also Figure 6 and Figure 7 One end of the flow guide component 2 along the thickness direction is a pressure surface and the other end is a suction surface. Under the action of the pressure difference between the pressure surface and the suction surface of the flow guide component 2, part of the air on the pressure surface side of the flow guide component 2 flows to the suction surface side through the flow channel formed by the mounting cavity 21. The first end 211 of the flow channel is located on the pressure surface of the flow guide component 2 to form an air inlet, and the second end of the flow channel is located on the suction surface of the flow guide component 2 to form an exhaust port.

[0052] Air flowing through the flow channel formed by the mounting cavity 21 is blown toward the temperature sensing component 1 installed inside the mounting cavity 21, so that the temperature sensing component 1 can sense the temperature of the air. Furthermore, most of the air flows from the leading edge 22 to the trailing edge 23 through the pressure surface or suction surface of the guide component 2, and the proportion of air flowing through the flow channel formed by the mounting cavity 21 is relatively small. Therefore, the amount of water droplets impacting the temperature sensing component 1 is also less, and the icing problem of the temperature sensing component 1 is effectively improved.

[0053] In some embodiments, the flow channel is arranged obliquely relative to the thickness direction, and the first end 211 of the flow channel along the thickness direction is closer to the leading edge 22 of the flow guide member 2 than the second end 212. Figure 7 As shown, the angle between the air flowing through the flow channel formed by the mounting cavity 21 and the airflow flowing through the suction surface of the guide component 2 is small, which helps to reduce the impact between airflows and reduce the interference of the air flowing through the flow channel formed by the mounting cavity 21 on the main flow field.

[0054] In some embodiments, the cross-sectional area of ​​the flow channel gradually increases along the direction near the second end 212 of the flow channel. The cross-section of the flow channel is a section perpendicular to the airflow direction. The area of ​​the cross-sectional area of ​​the flow channel gradually decreases along the direction near the second end 212 of the flow channel, which can effectively reduce the air velocity in the flow channel. While ensuring that the air flows through the temperature sensing component 1 to ensure the detection effect of the temperature sensing component 1, it reduces the impact of the air in the flow channel on the temperature sensing component 1, thereby reducing the probability of icing on the surface of the temperature sensing component 1. Furthermore, it also helps to reduce the impact of the airflow flowing out of the flow channel on the airflow of the suction surface, and reduces the interference of the air flowing through the flow channel formed by the mounting cavity 21 on the main flow field.

[0055] The thickness of the flow guide component 2 increases and then decreases from the leading edge 22 to the trailing edge 23. The second end 212 of the flow channel is located on the side near the trailing edge 23 where the thickness of the flow guide component 2 is the greatest. The cross-section of the flow guide component 2 is generally flat.

[0056] In some embodiments, in the cross-section of the flow guide 2, the pressure surface of the flow guide 2 is one of a concave arc shape, a convex arc shape, and a straight line shape. The suction surface of the flow guide 2 is a convex arc shape.

[0057] In some embodiments, in the cross-section of the guide member 2 perpendicular to the length direction, the leading edge 22 is arc-shaped and the trailing edge 23 is pointed.

[0058] The flow guide 2 includes a first portion 24 having a leading edge 22 and a second portion 25 having a trailing edge 23, the first portion 24 and the second portion 25 being spaced apart to form a mounting cavity 21.

[0059] The temperature sensor also includes a first end cap 3 and a second end cap 4 respectively disposed at both ends of the first part 24 and the second part 25 along the length direction of the flow guide member 2. One end of the first part 24 and the second part 25 along the length direction of the flow guide member 2 is connected to the first end cap 3, and the other end is connected to the second end cap 4.

[0060] In some embodiments, the first part 24, the second part 25, the first end cap 3, and the second end cap 4 are respectively separately provided and processed. After the temperature sensing component 1 is installed on the first end cap 3, the first part 24 and the second part 25 are welded to the first end cap 3, and then the second end cap 4 is bolted to the first part 24 and the second part 25.

[0061] In some embodiments, at least one of the first portion 24 and the second portion 25 is a hollow structure. See also Figure 6 In this embodiment, the first part 24 of the flow guiding component 2 is a hollow structure, thereby reducing the overall weight of the sensor. At the same time, the front end of the first part 24 is thicker to prevent incoming ice from impacting.

[0062] In this embodiment, under the same engine operating conditions, the sensor's structural shape design prevents water droplets from entering the sensor's interior, thus preventing icing of the temperature sensing component 1 inside the sensor's mounting cavity 21 and its impact on temperature measurement. Unobstructed airflow is ensured inside the sensor, allowing the temperature probe to obtain accurate temperatures for the corresponding engine structures. The airfoil design of the sensor reduces interference from the external flow field at the sensor's mounting location, minimizing its impact on engine performance. The sensor omits the anti-icing cover, reducing its weight.

[0063] According to another aspect of the invention, an aircraft engine is also provided, which includes the aforementioned temperature sensor.

[0064] The above are merely exemplary embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A temperature sensor for an aircraft engine, characterized in that, include: The temperature sensing element (1) is configured to sense temperature; as well as The airfoil-shaped airflow guide (2) is provided with a mounting cavity (21) for accommodating a temperature sensing component (1). The mounting cavity (21) is located between the leading edge (22) and the trailing edge (23) along the length direction of the chord of the airflow guide (2). At least one end of the mounting cavity (21) in the thickness direction of the airflow guide (2) is an open end.

2. The temperature sensor according to claim 1, characterized in that, Both ends of the mounting cavity (21) along the thickness direction of the flow guide (2) are open ends, so that the mounting cavity (21) forms a flow channel extending from one end of the flow guide (2) along the thickness direction to the other end.

3. The temperature sensor according to claim 2, characterized in that, The flow channel is arranged at an angle relative to the thickness direction.

4. The temperature sensor according to claim 3, characterized in that, The first end (211) of the flow channel along the thickness direction is closer to the leading edge (22) of the flow guide (2) than the second end (212).

5. The temperature sensor according to claim 4, characterized in that, The area of ​​the cross-section of the flow channel gradually increases in the direction close to the second end (212).

6. The temperature sensor according to claim 4, characterized in that, The first end (211) of the flow channel is located on the pressure surface of the flow guide (2) to form an air inlet, and the second end of the flow channel (212) is located on the suction surface of the flow guide (2) to form an exhaust outlet.

7. The temperature sensor according to claim 6, characterized in that, The thickness of the flow guide (2) increases and then decreases from the leading edge (22) to the trailing edge (23), and the second end (212) of the flow channel is the side near the trailing edge (23) where the thickness of the flow guide (2) is the largest.

8. The temperature sensor according to claim 1, characterized in that, In the cross-section of the guide member (2) perpendicular to the length direction, the leading edge (22) is arc-shaped and the trailing edge (23) is pointed.

9. The temperature sensor according to claim 1, characterized in that, The flow guide (2) includes a first portion (24) having the leading edge (22) and a second portion (25) having the trailing edge (23), the first portion (24) and the second portion (25) being spaced apart to form the mounting cavity (21).

10. The temperature sensor according to claim 9, characterized in that, It also includes a first end cap (3) and a second end cap (4) respectively disposed at both ends of the first part (24) and the second part (25) along the length direction of the flow guide (2). One end of the first part (24) and the second part (25) along the length direction of the flow guide (2) is connected to the first end cap (3) respectively, and the other end is connected to the second end cap (4) respectively.

11. The temperature sensor according to claim 9, characterized in that, At least one of the first part (24) and the second part (25) is a hollow structure.

12. An aircraft engine, characterized in that, The temperature sensor includes any one of claims 1 to 11.

Images