CN215952796U - Sensor and aircraft engine comprising same - Google Patents
Sensor and aircraft engine comprising same Download PDFInfo
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- CN215952796U CN215952796U CN202122294006.2U CN202122294006U CN215952796U CN 215952796 U CN215952796 U CN 215952796U CN 202122294006 U CN202122294006 U CN 202122294006U CN 215952796 U CN215952796 U CN 215952796U
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Abstract
The sensor comprises a probe shell, wherein a plurality of air holes are formed in the probe shell, the air holes are formed in the probe shell along the circumferential direction of the probe shell, and the projection of each air hole on the inner wall of the probe shell is not overlapped with other air holes. According to the sensor, the air holes are formed in the circumferential direction of the probe shell, so that air flow in any incoming flow direction on the periphery can quickly enter the probe shell through the air holes and is detected by the sensing elements in the probe shell, the time constant of the sensor is greatly reduced, and signals can be quickly responded and fed back. The projection of each air hole on the inner wall of the opposite probe shell is not overlapped with other air holes, so that the air flow entering the probe shell can impact the opposite inner wall of the shell firstly, the air flow forms vortex in the inner cavity of the shell and then leaves through other air holes, and the measuring effect of the sensor is effectively ensured.
Description
Technical Field
The utility model relates to a sensor and an aircraft engine comprising the same.
Background
Heat flow gas is introduced into a pipeline of a nacelle anti-icing system or a starter pipeline in a fan cabin of the aircraft engine, leakage or pipeline burst breakage occurs under extreme conditions, and a fan cabin temperature sensor can be arranged in the fan cabin for monitoring the leakage or burst. The temperature sensor is a total temperature sensor, needs to respond within a short time after pipe explosion occurs, feeds measured values back to the electronic controller through a cable, and cuts off the air pipe after logic judgment so as to prevent the temperature in the cabin from further continuously rising to prevent accessories from being injured and protect the engine.
If pipelines such as an anti-icing pipe and the like in the fan cabin burst, the sensor is required to have an equivalent time constant for the temperature change of peripheral airflow, but the specific position, the burst direction, the burst flow, the heat flow speed and the like of the burst pipe are difficult to determine, the local temperature part around the sensor is difficult to obtain, the optimal time constant is required to be reached, and the ideal state is that the airflow directly impacts an air inlet hole to the inner cavity of the sensor, so that the bypass is avoided. The existing total temperature sensor cannot ensure that the air flow impact from any direction around has a short time constant due to the structural design problem.
SUMMERY OF THE UTILITY MODEL
The utility model aims to solve the technical problem that the defects that the specific position, the burst direction, the burst flow, the heat flow speed and the like of a burst pipe of a nacelle anti-icing system pipeline or a starter pipeline in a fan cabin of an aircraft engine are difficult to determine and the rapid response of a sensor to cut off the pipeline cannot be guaranteed in the prior art are overcome, and the sensor and the aircraft engine comprising the sensor are provided.
The utility model solves the technical problems through the following technical scheme:
the utility model provides a sensor which comprises a probe shell, wherein a plurality of air holes are formed in the probe shell, the air holes are formed in the circumferential direction of the probe shell, and the projection of each air hole on the inner wall of the probe shell is not overlapped with other air holes.
In this scheme, adopt above-mentioned structural style, set up the gas pocket through the circumference at the probe casing of sensor, can make the air current of arbitrary incoming flow direction all around all can get into the probe casing through the gas pocket fast and detect by the sensing element in the probe casing, greatly reduced the time constant of sensor to can quick response and feedback signal. The projection of each air hole on the inner wall of the opposite probe shell is not overlapped with other air holes, so that the air flow entering the probe shell can impact the opposite inner wall of the shell firstly, the air flow forms vortex in the inner cavity of the shell and then leaves through other air holes, and the measuring effect of the sensor is effectively ensured.
Preferably, a plurality of the air holes are arranged at intervals along the axial direction of the probe shell;
and/or a plurality of air holes are arranged at the same axial position of the probe shell.
In this scheme, adopt above-mentioned structural style, set up crisscross gas pocket in the circumference and the circumference of probe casing for the air current of arbitrary direction can both get into fast in the probe casing and be detected by the sensing element.
Preferably, the air holes located at the adjacent axial positions of the probe shell are staggered.
In this scheme, adopt above-mentioned structural style, can strengthen the gas pocket in the density that circumference is respectively, further make the air current of arbitrary direction get into the probe casing fast.
Preferably, the number of the air holes is at least three, and at least three air holes are located at the same axial position of the probe shell.
In this scheme, set up at least three gas pocket and can satisfy this sensor quick response's lower requirement.
Preferably, the air holes are in a strip-shaped structure.
In this scheme, the gas pocket that adopts rectangular shape structure can increase the probability that the air current got into in the probe casing, further makes the air current of arbitrary incoming flow direction all around get into in the probe casing through the gas pocket fast and is detected by the sensing element in the probe casing to reduce the time constant of sensor.
Preferably, the sensor further comprises an installation part and a cable connection part, the probe shell is fixed on one side of the installation part, and the cable connection part is fixed on the other side of the probe shell deviating from the installation part.
In this scheme, set up the installation department and be convenient for the sensor installation, set up cable junction portion and be convenient for be connected the sensor through the cable with external control ware electricity to carry out corresponding operation through cable feedback to the controller with the measured value of sensor.
Preferably, the sensor further comprises a sensing element disposed within the probe housing.
In this scheme, will be felt the component and set up in the inner chamber, can avoid felt the component by direct impact of air current or because of the unexpected condition emergence that leads to felt the unable use of component.
Preferably, the sensing element is a thermal resistor or a thermocouple.
In this embodiment, the sensing element is a thermal resistor or a thermocouple so that the sensor is a temperature sensor to detect temperature changes.
Preferably, the sensor further comprises an electrical connection portion, the electrical connection portion is electrically connected with the sensing element, and the electrical connection portion is used for transmitting the signal acquired by the sensing element to an external cable.
The utility model also provides an aircraft engine, which comprises the sensor, wherein the sensor is arranged in a fan cabin of the aircraft engine.
The positive progress effects of the utility model are as follows: according to the sensor, the air holes are formed in the circumferential direction of the probe shell, so that air flow in any incoming flow direction on the periphery can quickly enter the probe shell through the air holes and is detected by the sensing elements in the probe shell, the time constant of the sensor is greatly reduced, and signals can be quickly responded and fed back. The projection of each air hole on the inner wall of the opposite probe shell is not overlapped with other air holes, so that the air flow entering the probe shell can impact the opposite inner wall of the shell firstly, the air flow forms vortex in the inner cavity of the shell and then leaves through other air holes, and the measuring effect of the sensor is effectively ensured.
Drawings
Fig. 1 is a schematic structural diagram of a sensor in embodiment 1 of the present invention.
Fig. 2 is a front view of fig. 1.
Fig. 3 is a rear view of fig. 1.
Fig. 4 is a bottom view in lateral cross section of a sensor in embodiment 1 of the present invention.
Fig. 5 is a schematic view of the probe housing of fig. 1 in an expanded state.
Fig. 6 is an expanded schematic view of a probe housing of a sensor in embodiment 2 of the present invention.
Fig. 7 is an expanded schematic view of a probe housing of a sensor in embodiment 3 of the present invention.
Description of reference numerals:
Cable socket mounting section 400
Sensitive element mount 600
Detailed Description
The utility model will be more clearly and completely described below by way of examples and with reference to the accompanying drawings, without thereby limiting the scope of the utility model to these examples.
Example 1
As shown in fig. 1 to 5, the sensor disclosed in this embodiment includes a probe portion, a mounting portion, and a cable connecting portion, the probe portion is fixed on one side of the mounting portion, and the cable connecting portion is fixed on the other side of the mounting portion away from the probe housing 100. The sensor is provided with the mounting part, so that the sensor can be conveniently mounted and fixed at a detection position. The cable connecting part is arranged to facilitate the sensor to be electrically connected with an external controller through a cable, so that the measured value of the sensor is fed back to the controller through the cable to perform corresponding operation.
The probe part comprises a probe shell 100 and a sensing element 700 positioned in the probe shell 100, wherein the sensing element 700 is used for detecting external fluid and generating corresponding signal change. By disposing the sensing element 700 in the inner cavity, the sensing element 700 is prevented from being directly impacted by the airflow or the sensing element 700 is prevented from being disabled by accident. The probe casing 100 has a sensing element mounting seat 600 fixed to the mounting portion, and the sensing element 700 is mounted on the sensing element mounting seat 600 and extends in the axial direction of the probe casing 100.
In this embodiment, the mounting portion includes a mounting flange 300, and the mounting flange 300 is used for fixing the sensor to a corresponding mounting portion near the detected position by bolts and has a sufficient sealing function by matching with a sealing ring.
In this embodiment, the cable connection portion includes a cable socket mounting section 400, a cable socket 500 is provided on the cable socket mounting section 400, and the cable socket 500 is used to connect an external cable, so that measurement data of the sensor is transmitted to an external controller or the like. The cable socket mounting section 400 has an electrical connection portion therein, one end of which is electrically connected to the sensing element 700, and the electrical connection portion is used for transmitting the signal collected by the sensing element 700 to an external controller. The other end of the electrical connection part is electrically connected with the cable socket 500, and the cable is installed on the cable socket 500 and then electrically connected with the sensing element 700 through the electrical connection part, so that the signal transmission of the sensing element 700 is realized.
The probe shell 100 is provided with a plurality of air holes 200, the plurality of air holes 200 are arranged along the circumferential direction of the probe shell 100, and the projection of each air hole 200 on the inner wall of the opposite probe shell 100 is not overlapped with other air holes 200. The air holes 200 are formed in the circumferential direction of the probe shell 100 of the sensor, so that air flow in any incoming flow direction around can quickly enter the probe shell 100 through the air holes 200 and is detected by the sensing elements 700 in the probe shell 100, the time constant of the sensor is greatly reduced, and signals can be quickly responded and fed back. The projection of each air hole 200 on the inner wall of the opposite probe shell 100 is not overlapped with other air holes 200, so that the air flow entering the probe shell 100 can impact the opposite shell inner wall firstly, the air flow forms vortex in the shell inner cavity and then leaves through other air holes 200, and the measuring effect of the sensor is effectively ensured.
In the present embodiment, a plurality of air holes 200 are provided at the same axial position of the probe case 100 along the circumferential direction of the probe case 100, and a plurality of air holes 200 are also provided at different axial positions of the probe case 100 along the circumferential direction of the probe case 100. As shown in fig. 1 to 3 and 5, the probe casing 100 of the present embodiment has six air holes 200, which are a first air hole 201, a second air hole 202, a third air hole 203, a fourth air hole 204, a fifth air hole 205 and a sixth air hole 206. The first air hole 201, the second air hole 202 and the third air hole 203 are in a group, are arranged at the same axial position of the probe shell 100 and are arranged along the circumferential direction of the probe shell 100; the fourth air hole 204, the fifth air hole 205, and the sixth air hole 206 are also provided in one set at the same axial position of the probe case 100 and in the circumferential direction of the probe case 100, but the two sets of air holes 200 are respectively located at different axial positions of the probe case 100.
In some embodiments, a plurality of air holes 200 are spaced along the axial direction of the probe housing 100. That is, each of the air holes 200 is located at a different axial position of the probe case 100, respectively, but the air holes 200 are distributed along the circumferential direction of the probe case 100. The air holes 200 in adjacent axial positions may have partially staggered sections in the axial positions, but it is still necessary to ensure that the projection of the air holes 200 does not overlap with the staggered sections.
Alternatively, in some embodiments, multiple air holes 200 are provided at the same axial location of the probe housing 100. That is, the plurality of air holes 200 are distributed along the circumferential direction of the probe case 100 at the same axial position of the probe case 100.
In the above embodiment, the staggered air holes 200 are arranged in the axial direction and the circumferential direction of the probe casing 100, so that air flow in any direction can quickly enter the probe casing 100 and be detected by the sensing element 700.
When the air holes 200 are circumferentially distributed at different axial positions of the probe shell 100, the air holes 200 at adjacent axial positions of the probe shell 100 are arranged in a staggered manner. By adopting the structure, the respective density of the air holes 200 in the circumferential direction can be enhanced, and further, air flow in any direction can rapidly enter the probe shell 100.
In the present embodiment, as shown in fig. 5, there are two sets of air holes 200 located at two axial positions of the probe housing 100, and any one air hole 200 in each set of air holes 200 is located between two air holes 200 in the other set.
In some embodiments, to meet the lower requirements of the sensor for fast response, there are at least three air holes 200 in the probe housing 100, and at least three air holes 200 are located at the same axial position of the probe housing 100.
As shown in fig. 1-3 and 5, in the present embodiment, the air holes 200 have a long strip-shaped structure. The air hole 200 with the strip-shaped structure can increase the probability of air flow entering the probe shell 100, and further, air flow in any incoming flow direction around can rapidly enter the probe shell 100 through the air hole 200 and is detected by the sensing element 700 in the probe shell 100, so that the time constant of the sensor is reduced.
In other embodiments, the air holes 200 may have other shapes, such as circular holes.
The sensor in this embodiment is a temperature sensor, the sensing element 700 may be installed with a thermal resistor or a thermocouple according to actual needs, and the redundancy may be designed according to actual needs. The sensing element 700 is a thermal resistor or a thermocouple so that the sensor is a temperature sensor that can detect temperature changes.
In other embodiments, a sensor having the same structure as that of the present embodiment but having a different function is obtained by changing the type of the sensing element 700.
The sensor of the above-described structure of the present embodiment will be described below by taking it as an example for use in an aircraft engine. The embodiment also discloses an aeroengine, and the aeroengine contains foretell sensor, and the sensor is located aeroengine's fan cabin.
When pipelines such as anti-icing pipes in the fan compartment burst, assuming that the burst airflow direction is opposite to the first air hole 201, namely, the burst airflow firstly reaches the first air hole 201, the burst airflow enters the inner cavity of the probe casing 100 through the first air hole 201, and because the first air hole 201 is opposite to the casing wall along the radial direction of the cylinder where the probe casing 100 is located, the airflow forms vortex in the inner cavity, slightly stagnates and then rapidly exits through the second air hole 202 and the third air hole 203, and the measurement of the total temperature in the fan compartment is effectively ensured.
The sensor of the embodiment has approximately opposite holes for any incoming flow direction on the periphery, so that the response in a short time after the pipe explosion is ensured on the structural design of the sensor. According to the simulation result, if the incoming flow direction of the burst air flow is opposite to the air inlet 200 of the sensor, the time constant is far smaller than that of the air inlet 200 which is not opposite to the sensor.
The sensor transmits the measured temperature signal to a cable socket 500 of the sensor through a signal wire (an electric connection part) arranged on the sensor, then transmits the temperature signal to an electronic controller of the aircraft engine through an external cable, and cuts off an air pipe after logic judgment so as to prevent the temperature in the fan cabin from further continuously rising, prevent accessories from being damaged and protect the aircraft engine.
As the highest bleed air temperature of an anti-icing system pipeline or a starter pipeline in the fan cabin is about 500 ℃, the sensor, the cable plug and the cable are required to have the capacity of resisting the temperature of 500 ℃ within a time constant.
The sensor can be adapted to a thermal resistor or a thermocouple which meets the requirements, including temperature resistance, the time constant performance of the element, and the like. And can be adapted to meet the requirements of cable plugs and cables. When the cable plug does not meet the high-temperature requirement, the cable plug can be switched to the low-temperature region through a high-temperature-resistant cable, so that the cable plug of the sensor is prevented from losing efficacy.
Example 2
As shown in fig. 6, the sensor in the present embodiment has substantially the same structure as that of embodiment 1, except that: in the present embodiment, the number of the air holes 200 is 8, and the air holes are divided into two groups and distributed at two axial positions of the probe casing 100, and each group of the air holes 200 has 4 air holes. Any one air hole 200 in each set of air holes 200 is located between two air holes 200 in the other set.
Example 3
As shown in fig. 7, the sensor in the present embodiment has substantially the same structure as that of embodiment 1, except that: in the present embodiment, the number of the air holes 200 is 9, which are divided into three groups and distributed at three axial positions of the probe housing 100, and each group of the air holes 200 has 3 air holes. Any one air hole 200 in each set of air holes 200 is located between two air holes 200 in an adjacent set.
While specific embodiments of the utility model have been described above, it will be appreciated by those skilled in the art that this is by way of example only, and that the scope of the utility model is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and scope of the utility model, and these changes and modifications are within the scope of the utility model.
Claims (10)
1. A sensor comprises a probe shell, wherein a plurality of air holes are formed in the probe shell, and the sensor is characterized in that the air holes are formed in the circumferential direction of the probe shell, and the projection of each air hole on the inner wall of the probe shell is not overlapped with other air holes.
2. The sensor of claim 1, wherein a plurality of said air holes are spaced axially along said probe housing;
and/or a plurality of air holes are arranged at the same axial position of the probe shell.
3. The sensor of claim 2, wherein said air holes located adjacent an axial position of said probe housing are staggered.
4. The sensor of claim 1, wherein there are at least three of said air holes, at least three of said air holes being located at a same axial position of said probe housing.
5. The sensor of claim 1, wherein the air holes have an elongated configuration.
6. The sensor of claim 1, further comprising a mounting portion and a cable connection portion, the probe housing being secured to one side of the mounting portion, the cable connection portion being secured to the other side of the mounting portion that faces away from the probe housing.
7. The sensor of claim 1, further comprising a sensing element disposed within the probe housing.
8. The sensor of claim 7, wherein the sensing element is a thermal resistor or a thermocouple.
9. The sensor of claim 7, further comprising an electrical connection electrically connected to the sensing element for transferring signals collected by the sensing element to an external cable.
10. An aircraft engine, characterized in that it comprises a sensor according to any one of claims 1 to 9, which is arranged in a fan compartment of the aircraft engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122294006.2U CN215952796U (en) | 2021-09-22 | 2021-09-22 | Sensor and aircraft engine comprising same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122294006.2U CN215952796U (en) | 2021-09-22 | 2021-09-22 | Sensor and aircraft engine comprising same |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215952796U true CN215952796U (en) | 2022-03-04 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122294006.2U Active CN215952796U (en) | 2021-09-22 | 2021-09-22 | Sensor and aircraft engine comprising same |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215952796U (en) |
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2021
- 2021-09-22 CN CN202122294006.2U patent/CN215952796U/en active Active
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