CN115524009A - Gas temperature detection device inside the pipeline of aircraft air source - Google Patents

Abstract

The invention provides a gas temperature detection device inside a pipeline of an aircraft air source, comprising: a heat conduction grid arranged in the pipeline along the cross section of the pipeline, and the heat conduction grid has a plurality of A plurality of hollow spaces through which the airflow can flow; and an infrared temperature measuring device, which is arranged in the pipeline at a distance from the heat conduction grid; wherein the infrared temperature measuring device is arranged in pairs Measure the temperature at multiple locations on the thermal grid. The gas temperature detection device inside the pipeline according to the present invention can provide the average temperature on the pipeline cross-section, and can accurately feedback the temperature of the fluid in the pipeline when the temperature difference of the pipeline cross-section is large, so as to avoid the situation of over-temperature or insufficient temperature of the bleed air.

Description

Gas temperature detection device inside the pipeline of aircraft air source

technical field

The invention relates to the field of aircraft air source system design, in particular, the invention and a gas temperature detection device in an aircraft air source pipeline.

Background technique

In the current aircraft air source system, the air source drawn from the engine is high-temperature and high-pressure gas. It is usually required to cool the gas drawn from the engine to meet the temperature required by the downstream air system. Usually, this cooling is achieved through a precooler. In order to improve its heat exchange efficiency, the precoolers commonly used in the industry at present adopt a cross-flow design.

The temperature control function of the air source system needs to be adjusted by measuring the average temperature in the downstream pipeline, so the measurement of the downstream temperature is particularly important. In the air source system of an existing aircraft, a thermal resistance temperature sensor is usually installed in the temperature measurement area, located downstream of the precooler, to measure the temperature of the airflow downstream of the precooler, and the obtained temperature value will be used as the realization of the temperature of the air source system. Input signal for the conditioning function.

However, especially for the pre-cooler using the cross-flow heat exchanger, due to the structure of the cross-flow heat exchanger itself, the temperature distribution of the outlet section is extremely uneven. The maximum temperature difference at the outlet of the device can reach 98°C, which brings great difficulties to the measurement of the average temperature of the gas. Conventional temperature sensors only measure the temperature at one point in the outlet section. Although the installation position of conventional temperature sensors can be set based on engineering experience, bench tests and simulation calculation results, which can basically reflect the average temperature of the gas to a certain extent, the measured temperature in some configurations is still higher than the average temperature. If it is too low, this will cause the actual bleed air to overheat.

Several techniques have been proposed to accurately measure the average temperature of the gas flow inside the pipeline. For example, CN200972433Y provides a temperature and humidity sampling device with a honeycomb element, wherein the honeycomb element is arranged in the front section of the pipeline to evenly mix the pipeline airflow, and then the uniform temperature in the pipeline is measured by a temperature and humidity sensor. However, setting the honeycomb in the pipeline will have a significant impact on the flow field in the pipeline, significantly increasing the flow resistance, thereby reducing the air-introduction efficiency.

Therefore, there is insufficient temperature monitoring of the airflow in the pipeline in the current aircraft air source system, and it is necessary to provide a temperature detection device capable of more accurately feeding back the temperature of the airflow.

Contents of the invention

In order to overcome the deficiencies of the prior art, the present invention provides a gas temperature detection device for the pipeline of an aircraft air source, comprising: a heat conduction grid, the heat conduction grid is arranged in the pipeline along the cross section of the pipeline, the The heat conduction grid has a plurality of hollow spaces through which multiple airflows can flow and forms a plurality of temperature measurement points on the heat conduction grid; and an infrared temperature measuring device, the infrared temperature measurement device is adjacent to the heat conduction grid Arranged in the pipeline; wherein the infrared temperature measuring device is arranged to measure a plurality of the temperature measuring points of the heat conduction grid.

According to one aspect of the present invention, the heat conduction grid is composed of wires with a diameter between 0.6 mm and 1 mm, and the hollow space of the heat conduction grid is between 300 mm ² and 500 mm ² .

According to still another aspect of the present invention, the heat conduction grid is made of metal wires arranged in a staggered manner.

According to still another aspect of the present invention, the metal material includes copper-zinc alloy.

According to another aspect of the present invention, the device includes a signal processor, the signal processor is in signal communication with the infrared measuring device, and the signal processor is arranged outside the pipeline, and the signal processor is configured After processing and calculating a plurality of temperature signals from the infrared measuring device signal, an average temperature value is output.

According to still another aspect of the present invention, the signal processor can be connected to an integrated controller of the gas source system to send the average temperature value to the condensation controller.

According to still another aspect of the present invention, the infrared temperature measuring device is arranged downstream of the heat conducting grid along the flow direction of the airflow inside the pipeline.

According to still another aspect of the present invention, the heat conduction grid is configured such that the flow resistance generated in the pipe is less than 1% of the total flow resistance in the pipe.

According to still another aspect of the present invention, the infrared temperature measuring device includes a microbolometer type uncooled infrared focal plane detector.

According to still another aspect of the present invention, the temperature detection device is installed on the outlet pipeline downstream of the precooler of the aircraft air source system.

The temperature detection device according to the present invention can accurately detect and calculate the average temperature of the section inside the pipe, and improve the temperature control accuracy of the air source system of the aircraft.

According to the temperature detection device of the present invention, the installation is convenient, the cost is low, and the influence on the flow field in the pipe is small.

Description of drawings

For a more complete understanding of the present invention, the following description of exemplary embodiments may be considered by reference to the accompanying drawings, in which:

Fig. 1 shows a schematic diagram of an aircraft air source equipped with a pipeline internal gas temperature detection device of an aircraft air source according to a preferred embodiment of the present invention.

List of reference signs

10 temperature detection device

11 thermal grid

12 Infrared temperature measuring device

15 signal processor

20 precooler

21 Manager

30 controllers

detailed description

The present invention will be further described below in conjunction with specific embodiments and accompanying drawings. In the following description, more details are set forth in order to fully understand the present invention, but the present invention can obviously be implemented in many other ways different from this description.

When an aircraft is in the air, it uses bleed air through the engine, for example to supply air to the air conditioning system. The engine bleed air system usually uses a high-pressure compressor to guide the air flow through the pressure regulating shut-off valve (PRSOV), and then flows through the precooler 20 to the air source main pipe. The temperature of the air flow in the main pipe will be monitored by the temperature detection device 10 .

FIG. 1 schematically shows a part of a pipeline 21 including a precooler 20 and an air source main pipe for leading out airflow in the bleed air system, and the temperature detection device 10 is included in the pipeline 21 . The high-temperature airflow drawn from the engine enters the precooler 20 from the left side of FIG. 1 , and is drawn out from the airflow pipeline 21 on the right side after being cooled in the precooler 20 . The interior of the precooler 20 usually includes a fork-type flow heat exchanger, and there is a large temperature difference in the cross-section of the gas source manifold downstream of this kind of precooler.

As shown in FIG. 1 , in particular, the temperature detection device 10 of the present invention includes a heat conduction grid 11 and an infrared temperature measurement device 12 arranged in a pipe 21 . Preferably, the infrared temperature measurement device 12 is arranged downstream of the heat conduction grid 11 along the flow direction of the airflow in the airflow outlet duct 21 , and the infrared temperature measurement device 12 is separated from the heat conduction grid 11 by a certain distance.

The heat conduction grid 11 has a plurality of hollow spaces through which air can flow, and the heat conduction grid 11 itself constitutes a target temperature measurement object of the infrared temperature measurement device 12 . The distance between the infrared temperature measurement device 12 and the heat conduction grid 11 can be determined according to the selected model of the infrared temperature measurement device 12 , so that the infrared temperature measurement device 12 is arranged to be able to measure every part of the heat conduction grid 11 .

The heat conduction grid 11 has a shape corresponding to the cross section inside the pipe 21 , and when the heat conduction grid 11 is arranged inside the pipe along the cross section of the pipe, the heat conduction grid 11 covers the entire cross section inside the pipe. For example the duct 21 generally has a circular cross-section, the adapted grid 11 substantially forming a corresponding circle. Most of the airflow in the pipeline can flow downstream through the hollow part of the heat conduction grid 11 .

It is important that the flow resistance generated by the heat conduction grid 11 in the pipe 21 should be as small as possible, preferably less than 1% of the total flow resistance in the pipe. In order to control the influence of the flow resistance generated by the heat conduction grid 11, preferably, the heat conduction grid 11 is composed of grid lines whose diameter or section width is between 0.6 mm and 1 mm, more preferably, the heat conduction grid 11 The diameter or cross-sectional width of the grid lines is 0.8mm. The size of the hollow space of the heat conduction grid 11 is preferably between 300mm ² and 500mm ² , more preferably, the hollow space is formed as a 20x20mm square. The width of the grid lines and the size of the hollow spaces set in this way can ensure that the flow resistance generated by the heat conduction grid 11 in the pipe is kept below 1% of the total flow resistance in the pipe.

The material of the heat conduction grid 11 can be selected from a material capable of rapid and sufficient heat conduction with the airflow in the pipe 21 , usually metal, that is, a metal grid is arranged inside the pipe. More preferably, copper-zinc alloy is selected as the metal material. Copper-zinc alloy has good thermal conductivity and it is easier to form the grid 11. The heat flow in the pipeline 21 can quickly convect heat with the copper-zinc alloy grid 11, so that the grid 21 Able to rapidly acquire a temperature comparable to the air flow passing through it.

The infrared temperature measuring device 12 arranged inside the pipeline 21 can detect the temperature of each part of the heat conduction grid 11 body at the same time, so as to obtain the fluid temperature at multiple positions on the heat conduction grid 11, when the average temperature of these positions is Accurately reflects the average temperature of the fluid at the location of the thermal mesh.

It should be understood that the greater the number of temperature measurement points, the closer the average value obtained is to the true condition of the fluid temperature at the section. Preferably, multiple temperatures on a section can be selected from the measured temperatures of various parts of the heat conduction grid 11 body to take an average value, so as to reflect the average temperature on a specific section in the pipe 21 .

In the gas temperature detection device 10 inside the pipeline according to the present invention, the infrared temperature measuring device 12 includes a microbolometer type uncooled infrared focal plane detector for detecting the infrared radiation emitted by the heat conduction grid 11 and generating a representative temperature electrical signal. Infrared focal plane detector is a device on the focal plane of the infrared optical system based on the thermal effect of infrared radiation and sensitive elements to detect the target. It includes multiple infrared light sensor units to form a two-dimensional infrared focal plane array, which can Make one-to-one correspondence between each pixel in the observation field of view grid and the sensitive element. The volume of the uncooled infrared focal plane detector is relatively small, and choosing this kind of detector to be installed in the pipe 21 can minimize the influence of the infrared temperature measuring device 12 on the flow field in the pipe.

In the present invention, the heat conduction grid 11 is arranged on the focal plane of the uncooled infrared focal plane detector, so that the uncooled infrared focal plane detector can detect the infrared radiation generated by the heat conduction grid 11 and obtain the corresponding temperature signal .

As shown in FIG. 1 , the gas temperature detection device 10 inside the pipeline also includes a signal processor 15 in signal communication with the infrared measuring device. Usually, the signal processor 15 is arranged outside the pipeline 21 .

The signal processor 15 is configured to process and calculate multiple temperature signals from the infrared measuring device and output an average temperature value. The signal processor 15 is further communicated with the integrated controller 30 of the air source system, and the average temperature value in the pipe output after processing and calculation will be sent to the integrated controller 30 of the air source system for controlling the downstream bleed air temperature.

It should be understood that the signal processor 15 shown in FIG. 1 for receiving and receiving the electrical signal representing the temperature is provided separately. However, in other alternative embodiments, the signal processor for generating the temperature average value can also be integrated with the integrated controller 30 .

The installation of the gas temperature detection device 10 inside the pipeline according to the present invention is very convenient. The heat conduction grid 11 is pre-prepared according to the cross-sectional shape and size of the pipe segment. The air induction pipeline 21 downstream of the precooler 20 is usually spliced by multiple independent pipe sections. Before the pipe sections are spliced, the heat conduction grid 11 is attached to the end of one of the pipe sections to cover the entire section of the end. However, the The pipe sections are spliced to form the bleed air pipe.

The infrared temperature measuring device 12 is usually in the shape of a probe. The probe-shaped infrared temperature measuring device 12 is inserted into a through hole in the pipe wall downstream of the heat conduction grid 11, and then the infrared temperature measuring device 12 is fixed relative to the pipe wall and connected to transmit the signal. The installation of the temperature detection device 10 can be completed.

Preferably, the infrared temperature measuring device 12 protruding into the pipeline 21 can be as close as possible to the inner wall of the pipeline, so as to reduce the resistance to the airflow inside the pipeline 1 .

Adopting the gas temperature detection device 10 inside the pipeline according to the present invention can provide the average temperature on the pipeline cross-section, and can accurately feedback the temperature of the fluid in the pipeline when the temperature difference of the pipeline cross-section is large, so as to avoid the situation of over-temperature or insufficient temperature of the bleed air .

In addition, the temperature detection device according to the present invention is easy to install, low in cost, and has little influence on the flow field in the pipe.

Although the present invention is disclosed above with preferred embodiments, it is not intended to limit the present invention, and any person skilled in the art can make possible changes and modifications without departing from the spirit and scope of the present invention. Therefore, any modifications, equivalent changes and modifications made to the above embodiments according to the technical essence of the present invention, all fall within the scope of protection defined by the claims of the present invention.

Claims (10)

1. A pipe interior gas temperature sensing device for an aircraft gas supply system, comprising:

a heat conductive mesh disposed within the duct along a cross-section of the duct, the heat conductive mesh having a plurality of hollow spaces through which a plurality of gas streams can flow; and

the infrared temperature measuring device is arranged in the pipeline at a distance from the heat conducting grid;

wherein the infrared temperature measuring device is arranged to measure the temperature of a plurality of locations of the thermally conductive grid.

2. The duct interior gas temperature sensing device of claim 1, wherein the thermally conductive mesh is configured to produce a flow resistance within the duct that is less than 1% of a total flow resistance within the duct.

3. The apparatus according to claim 2, wherein the heat conductive mesh is formed of wires having a diameter of 0.6mm to 1mm, and the heat conductive mesh has a hollow cell size of 300mm ² To 500mm ² In between.

4. The apparatus according to any one of claims 1 to 3, wherein the heat conductive mesh is made of a metal material arranged in a staggered manner.

5. The apparatus for detecting a gas temperature inside a pipe according to claim 4, wherein the metal material includes a copper-zinc alloy.

6. The apparatus according to claim 1, wherein said apparatus includes a signal processor in signal communication with said infrared detection device and disposed outside of said duct,

the signal processor is configured to process and calculate a plurality of temperature signals from the infrared measuring device signal and output an average temperature value.

7. The apparatus according to claim 6, wherein the signal processor is connectable to a comprehensive controller to the gas source system, and the average temperature value obtained by the signal processor is transmitted to the comprehensive controller.

8. The apparatus according to claim 1, wherein the infrared temperature measuring device is disposed downstream of the heat conductive mesh in a flow direction of the gas flow inside the pipe.

9. The apparatus for detecting the temperature of a gas inside a pipe according to claim 1 or 8, wherein said infrared temperature measuring means comprises a microbolometer type uncooled infrared focal plane detector.

10. The duct internal gas temperature detection device according to claim 1, wherein the temperature detection device is mounted on an outlet duct downstream of a precooler of an aircraft air supply system.

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