Adjustable contrast type thermocouple temperature sensor, electronic equipment and regulation and control method

Abstract

The invention provides an adjustable comparison type thermocouple temperature sensor, electronic equipment and a regulation and control method. The adjustable comparison type thermocouple temperature sensor comprises a junction box; the plug is connected with one end of the compensation cable, and the other end of the compensation cable is connected with the junction box; and the first thermocouple and the second thermocouple are both connected with the junction box. The invention provides a comparison type thermocouple temperature sensor which can output a fuel gas standard temperature value and an actual temperature value at the typical rotating speed of an aircraft engine at the same time after being debugged, and can be matched between different engines and cockpit instruments.

Description

Technical Field

[0001] The present application relates to an adjustable contrast thermocouple temperature sensor, electronic equipment and a control method. Background Art

[0002] The temperature of high-temperature gas in aircraft engines is mainly measured by thermocouple temperature sensors. Traditional thermocouple temperature sensors convert gas temperature into voltage signals and output them to cockpit instruments to indicate gas temperature. However, due to the actual manufacturing differences in the structural performance of each engine, the actual gas temperature at the same speed varies. The client cannot determine the difference between the actual gas temperature and the standard temperature at the speed through traditional thermocouples, and it will cost a huge amount of money to adjust the cockpit instrument line according to the actual working conditions of each engine. Summary of the invention

[0003] In view of this, the present application provides an adjustable comparative thermocouple temperature sensor, an electronic device and a control method, which can simultaneously output the standard temperature value and the actual temperature value of the fuel gas at a typical speed of the aircraft engine after debugging.

[0004] The present application provides the following technical solution: an adjustable contrast thermocouple temperature sensor, comprising: a junction box; a plug and a compensation cable, the plug is connected to one end of the compensation cable, and the other end of the compensation cable is connected to the junction box; a first thermocouple and a second thermocouple, both connected to the junction box.

[0005] Furthermore, the junction box includes: an insulating seat; a wiring board fixedly arranged on the insulating seat; and an adjustable resistor wound on the wiring board and connected to the compensation cable and the second thermocouple.

[0006] Furthermore, the compensation cable includes a first positive wire, a first negative wire, a second positive wire and a second negative wire; the first positive wire is connected to the terminal block and the insulating seat, and the two ends of the adjustable resistor are respectively connected to the first positive wire and the positive pole of the second thermocouple; the first negative wire is connected to the insulating seat and the negative pole of the second thermocouple; the second positive wire is connected to the insulating seat and the positive pole of the first thermocouple; the second negative wire is connected to the insulating seat and the negative pole of the first thermocouple.

[0007] Furthermore, the junction box comprises a shell and a cover, wherein the cover is fixed on the shell and forms a receiving space, and the insulating seat, the wiring board and the adjustable resistor are all arranged in the receiving space.

[0008] Furthermore, the first thermocouple, the second thermocouple and the compensating cable are all connected to the housing.

[0009] The present application also provides a control method, which is performed using the above-mentioned adjustable contrast thermocouple temperature sensor.

[0010] Furthermore, the control method includes the following steps: installing an adjustable comparative thermocouple temperature sensor on the engine and performing an ignition test; judging whether the output signal of the second positive wire and the second negative wire is consistent with the standard temperature at the speed; when the output signal of the second positive wire and the second negative wire is consistent with the standard temperature at the speed, removing the adjustable resistor and short-circuiting the positive pole of the second thermocouple with the first positive wire; the first positive wire, the first negative wire, the second positive wire and the second negative wire all output signals consistent with the standard temperature at the speed.

[0011] Furthermore, the control method includes the following steps: when the output signal of the second positive wire and the second negative wire is inconsistent with the standard temperature at the speed, the end of the adjustable resistor connected to the first positive wire is unsoldered, the adjustable resistor is trimmed according to the standard temperature value at the speed, and one end of the adjustable resistor is welded and fixed to the first positive wire after trimming; the second positive wire and the second negative wire output the actual gas temperature, the first positive wire and the first negative wire output the standard temperature at the speed, and the difference between the actual gas temperature and the standard temperature at the speed can be obtained.

[0012] The present application also provides an electronic device, comprising the above-mentioned adjustable contrast thermocouple temperature sensor.

[0013] Compared with the prior art, the beneficial effects that can be achieved by at least one of the above-mentioned technical solutions adopted in the present application include at least the following: the present application provides a comparative thermocouple temperature sensor which can simultaneously output the standard temperature value of the fuel gas at a typical speed of the aircraft engine and the actual temperature value after debugging, and can be matched between different engines and cockpit instruments. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0015] Attached Figure 1 It is a front cross-sectional view of the thermocouple temperature sensor of the present application;

[0016] Attached Figure 2 It is a left side view of the thermocouple temperature sensor of the present application;

[0017] Attached Figure 3 is the wiring diagram of the thermocouple temperature sensor of the present application;

[0018] Attached Figure 4 This is a flow chart of the thermocouple temperature sensor of this application before use during engine test run;

[0019] The reference numerals in the figure are: 1. plug; 2. compensation cable; 3. terminal block; 4. first screw; 5. insulating seat; 6. adjustable resistor; 7. second screw; 8. first thermocouple; 9. second thermocouple; 10. housing; 11. cover; 12. bolt. DETAILED DESCRIPTION

[0020] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0021] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0022] like Figures 1 to 3 As shown, the embodiment of the present application provides an adjustable contrast thermocouple temperature sensor, including a junction box, a plug 1, a compensation cable 2, a first thermocouple 8, and a second thermocouple 9. The plug 1 is connected to one end of the compensation cable 2, and the other end of the compensation cable 2 is connected to the junction box. The first thermocouple 8 and the second thermocouple 9 are both connected to the junction box.

[0023] The present application provides a comparative thermocouple temperature sensor which can simultaneously output the standard temperature value and the actual temperature value of the fuel gas at a typical speed of the aircraft engine after debugging, and can be matched between different engines and cockpit instruments.

[0024] The junction box includes: an insulating seat 5, a terminal block 3 and an adjustable resistor 6. The terminal block 3 is fixedly arranged on the insulating seat 5; the adjustable resistor 6 is wound on the terminal block 3 and connected to the compensation cable 2 and the second thermocouple 9.

[0025] like Figure 2 As shown, the junction box also includes a housing 10 and a cover 11, the cover 11 is fixed on the housing 10 and forms a receiving space, and the insulating seat 5, the terminal block 3 and the adjustable resistor 6 are all arranged in the receiving space. The housing 10 and the cover 11 are connected by bolts 12, and the insulating seat 5 is connected to the housing 10 by a second screw 7. The first thermocouple 8, the second thermocouple 9 and the compensation cable 2 are all connected to the housing 10 by threads.

[0026] Furthermore, the compensation cable 2 includes a first positive conductor, a first negative conductor, a second positive conductor and a second negative conductor; wherein,

[0027] The first positive wire is connected to the terminal block 3 and the insulating seat 5, and the two ends of the adjustable resistor 6 are respectively connected to the first positive wire and the positive electrode of the second thermocouple 9;

[0028] The first negative electrode wire is connected to the insulating seat 5 and the negative electrode of the second thermocouple 9;

[0029] The second positive lead is connected to the insulating seat 5 and the positive electrode of the first thermocouple 8;

[0030] The second negative electrode wire is connected to the insulating base 5 and the negative electrode of the first thermocouple 8 .

[0031] The above-mentioned wire connection can be connected by using the first screw 4, see Figure 1 As shown, it will not be described in detail here.

[0032] Among them, the first thermocouple 8 and the second thermocouple 9 are K-graded thermocouples, and the adjustable resistor 6 uses manganese copper wire with a small temperature resistance coefficient to prevent resistance changes caused by changes in ambient temperature. After connecting the compensation cable 2, the first thermocouple 8 directly outputs the actual engine gas temperature through the plug 1; the second thermocouple 9 is connected to the adjustable resistor 6 and then connected to the compensation cable 2 and then outputs the adjusted signal through the plug 1: the adjustable resistor 6 is trimmed according to the standard temperature value at the engine speed, and the current value is changed by adjusting the resistance value in the entire test circuit, so as to adjust the temperature display of the cockpit instrument to be consistent with the standard temperature at the speed. If the actual engine gas temperature output by the first thermocouple 8 is consistent with the standard temperature at the engine speed, the adjustable resistor 6 is cancelled. At this time, both thermocouples output signals consistent with the standard temperature at the speed.

[0033] like Figure 3 and Figure 4 As shown, the present application also provides a control method, which is performed using the above-mentioned adjustable contrast thermocouple temperature sensor.

[0034] The control method comprises the following steps:

[0035] The adjustable contrast thermocouple temperature sensor is installed on the engine and an ignition test is carried out; the output signal of the first thermocouple 8 is the actual gas temperature, i.e. Figure 3 middle.

[0036] Determine whether the output signal of the second positive wire and the second negative wire is consistent with the standard temperature at the speed;

[0037] When the output signals of the second positive wire and the second negative wire (output signals of B+ and B-) are consistent with the standard temperature at the speed, the adjustable resistor 6 is removed, and the positive electrode of the second thermocouple 9 is short-circuited with the first positive wire;

[0038] The first positive wire, the first negative wire, the second positive wire and the second negative wire all output signals consistent with the standard temperature at the speed, that is, Figure 3 A+, A- and B+, B- all output signals consistent with the standard temperature at that speed.

[0039] The above method ensures that sensors can be accurately matched between different engines and cockpit instruments, and can adapt to changes in engine performance over time, thereby improving the accuracy and reliability of aircraft engine temperature monitoring.

[0040] The control method comprises the following steps:

[0041] When the output signals of the second positive wire and the second negative wire (output signals of B+ and B-) are inconsistent with the standard temperature at the speed, the end of the adjustable resistor 6 connected to the first positive wire is unsoldered, and the adjustable resistor is trimmed according to the standard temperature value at the speed (the current value is changed by adjusting the resistance value in the entire test circuit, so as to adjust the temperature display of the cockpit instrument to be consistent with the standard temperature at the speed) and after the trimming is completed, one end of the adjustable resistor 6 is welded and fixed to the first positive wire;

[0042] The second positive wire and the second negative wire output the actual gas temperature, the first positive wire and the first negative wire output the standard temperature at the speed, and can obtain the difference between the actual gas temperature (output signals of B+, B-) and the standard temperature at the speed (output signals of A+, A-).

[0043] As the engine is used for more hours, its performance will change. Therefore, during the engine regular inspection and matching test, it is necessary to readjust according to the above steps so that the thermocouple outputs the correct standard temperature.

[0044] This adjustment method not only improves the accuracy of temperature monitoring, but also greatly reduces maintenance costs because it can match different engines with cockpit instruments and adapt to changes in engine performance over time. In this way, it can ensure that the temperature monitoring of aircraft engines under various operating conditions is accurate and reliable, which is crucial to ensuring flight safety and engine performance.

[0045] The present application also provides an electronic device, comprising the above-mentioned adjustable contrast thermocouple temperature sensor.

[0046] The electronic device provided by the present application integrates an adjustable contrast thermocouple temperature sensor, which can accurately monitor the temperature of the aircraft engine gas. This sensor design allows dynamic adjustment of the temperature reading under different working conditions, ensures the output of the standard temperature value corresponding to the engine speed, and provides a comparison of the actual temperature value. Such a design not only improves the accuracy of temperature measurement, but also enhances flight safety, because pilots can rely on these accurate data to make better operational decisions.

[0047] In addition, the sensor design reduces the need for cockpit instrument line adjustments, reduces maintenance costs, and simplifies the matching process between different engines. As the engine age grows and performance changes, the sensor can adapt to these changes through simple adjustments, maintaining the reliability of temperature monitoring, which is critical to extending engine life and improving overall performance.

[0048] The beneficial effects of this application are:

[0049] The present application solves the problem that the pilot cannot determine the difference between the actual gas temperature and the standard temperature at the engine speed by using the traditional thermocouple.

[0050] The present application solders an adjustable resistor in the thermocouple sensor circuit, which can be matched between different engines and cockpit instruments. When the engine performance changes with the increase of usage hours, the thermocouple can output the correct standard temperature by adjusting the adjustable resistor at any time.

[0051] If the cockpit instrument lines are adjusted according to the actual working conditions of each engine, it will cost a huge amount of money. This application greatly reduces the cost.

[0052] The above is only a specific embodiment of the present application, and cannot be used to limit the scope of the application. Therefore, the replacement of equivalent components, or equivalent changes and modifications made according to the protection scope of the patent of this application, should still fall within the scope of this patent. In addition, the technical features in this application can be freely combined with each other, with each other, and with each other.

Claims

1. An adjustable contrast thermocouple temperature sensor, characterized in that: include: Junction box; A plug (1) and a compensating cable (2), wherein the plug (1) is connected to one end of the compensating cable (2), and the other end of the compensating cable (2) is connected to the junction box; The first thermocouple (8) and the second thermocouple (9) are both connected to the junction box.

2. The adjustable contrast thermocouple temperature sensor according to claim 1, characterized in that: The junction box comprises: Insulation seat (5); A wiring board (3) is fixedly mounted on an insulating seat (5); The adjustable resistor (6) is wound on the wiring board (3) and connected to the compensation cable (2) and the second thermocouple (9).

3. The adjustable contrast thermocouple temperature sensor according to claim 2, characterized in that: The compensating cable (2) comprises a first positive conductor, a first negative conductor, a second positive conductor and a second negative conductor; The first positive wire is connected to the wiring board (3) and the insulating seat (5), and the two ends of the adjustable resistor (6) are respectively connected to the first positive wire and the positive electrode of the second thermocouple (9); The first negative electrode wire is connected to the insulating seat (5) and the negative electrode of the second thermocouple (9); The second positive electrode wire is connected to the insulating seat (5) and the positive electrode of the first thermocouple (8); The second negative electrode wire is connected to the insulating seat (5) and the negative electrode of the first thermocouple (8).

4. The adjustable contrast thermocouple temperature sensor according to claim 2, characterized in that: The junction box comprises a shell (10) and a cover (11), wherein the cover (11) is fixed on the shell (10) and forms a receiving space, and the insulating seat (5), the wiring board (3) and the adjustable resistor (6) are all arranged in the receiving space.

5. The adjustable contrast thermocouple temperature sensor according to claim 4, characterized in that: The first thermocouple (8), the second thermocouple (9) and the compensation cable (2) are all connected to the housing (10).

6. A control method, using an adjustable contrast thermocouple temperature sensor, characterized in that: The adjustable contrast type thermocouple temperature sensor is the adjustable contrast type thermocouple temperature sensor according to any one of claims 1 to 5.

7. The control method according to claim 6, characterized in that: The control method comprises the following steps: Install the adjustable contrast thermocouple temperature sensor on the engine and conduct an ignition test run; Determine whether the output signal of the second positive wire and the second negative wire is consistent with the standard temperature at the speed; When the output signals of the second positive wire and the second negative wire are consistent with the standard temperature at the speed, the adjustable resistor (6) is removed, and the positive electrode of the second thermocouple (9) is short-circuited with the first positive wire; The first positive wire, the first negative wire, the second positive wire, and the second negative wire all output signals consistent with the standard temperature at the rotation speed.

8. The control method according to claim 7, characterized in that: The control method comprises the following steps: When the output signals of the second positive wire and the second negative wire are inconsistent with the standard temperature at the speed, the end of the adjustable resistor (6) connected to the first positive wire is unsoldered, the adjustable resistor is trimmed according to the standard temperature value at the speed, and after the trimming is completed, one end of the adjustable resistor (6) is welded and fixed to the first positive wire; The second positive wire and the second negative wire output the actual gas temperature, the first positive wire and the first negative wire output the standard temperature at the speed, and the difference between the actual gas temperature and the standard temperature at the speed can be obtained.

9. An electronic device comprising an adjustable contrast thermocouple temperature sensor, characterized in that: The adjustable contrast type thermocouple temperature sensor is the adjustable contrast type thermocouple temperature sensor according to any one of claims 1 to 5.

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