Hypersonic speed temperature sensor measuring device

Abstract

The invention relates to a hypersonic speed temperature sensor measuring device, which relates to the technical field of temperature measurement, and comprises an outer tube, a stagnation cover and an exposed end type sheathed thermocouple, one end of the outer pipe is closed and the other end is open; a plurality of stagnation covers communicated with the outer pipe are formed on the outer side wall of the outer pipe in the length direction of the outer pipe, air inlets are formed in the ends, away from the outer pipe, of the stagnation covers, and at least one air outlet is formed in the side wall of each stagnation cover; an exposed end type sheathed thermocouple is arranged in each stagnation cover, and a metal shell of the exposed end type sheathed thermocouple is hermetically welded with the stagnation cover; and all the air outlets are positioned between the detection ends of the corresponding exposed end type sheathed thermocouples and the metal shell. The hypersonic speed temperature sensor measuring device is reliable in overall structure, the temperature collecting duration of the hypersonic speed temperature sensor measuring device under high-temperature hypersonic speed airflow impact can be prolonged, and the credibility of a measuring result is improved.

Description

Technical Field

[0001] This invention relates to the field of temperature measurement technology, and in particular to a hypersonic temperature sensor measurement device. Background Technology

[0002] In aero engines, performance tests of structures such as compressors, turbines, and fans require the use of temperature measurement devices to collect temperatures at multiple points.

[0003] Chinese patent CN106918410A discloses a total temperature blade-type probe, including a temperature sensor, lead wire, stagnation cover, heat insulation ring, and blades. Each blade has at least five measuring points. The stagnation cover and temperature sensor are fixed near the leading edge of the blade, with the axis of the stagnation cover facing the expected incoming flow direction. The head of the temperature sensor is fitted with a heat insulation ring. Two symmetrical outflow holes are opened on the left and right sides of the stagnation cover. The lead wire is fixed on the blade surface or inside the blade and extends from the blade root. This probe can simultaneously measure the total temperature at multiple points between blade rows in a short measurement time.

[0004] In high-performance aero engines, the gas entering the turbine can reach temperatures exceeding 1400°C and speeds reaching hypersonic speeds. These high-temperature, hypersonic conditions easily cause the aforementioned probe to crack and break, resulting in extremely short measurement times under these conditions. The measurement results are also susceptible to environmental interference, leading to low reliability. Summary of the Invention

[0005] To address the shortcomings of related technologies, this invention provides a hypersonic temperature sensor measuring device. It utilizes an exposed-end armored thermocouple with a high response frequency. The outer tube and stagnation shield are made of metal, and the stagnation shield and exposed-end armored thermocouple are sealed and welded together. The metal shell of the exposed-end armored thermocouple is filled with inorganic insulating particles, which reliably fix the thermocouple wire within the metal shell. The overall structure of the hypersonic temperature sensor measuring device is reliable, extending the temperature acquisition time under high-temperature hypersonic airflow impact and improving the reliability of the measurement results.

[0006] This invention provides a hypersonic temperature sensor measuring device, comprising an outer tube, a stagnation hood, and an exposed-end armored thermocouple; one end of the outer tube is closed, and the other end is open; multiple stagnation hoods connected to the outer tube are formed along the length of the outer tube on its outer side wall, with the end of the stagnation hood furthest from the outer tube serving as an air inlet, and at least one air outlet provided on the side wall of the stagnation hood; an exposed-end armored thermocouple is disposed inside each stagnation hood, and the metal shell of the exposed-end armored thermocouple is sealed and welded to the stagnation hood; all air outlets are located between the detection end of their corresponding exposed-end armored thermocouple and the metal shell; The hypersonic temperature sensor measurement device also includes a temperature calculation module connected to an exposed-end armored thermocouple. This module corrects the measured temperature of the exposed-end armored thermocouple using a temperature correction and compensation formula, outputting the static temperature. The temperature correction and compensation formula is as follows:

[0007]

[0008] In the formula, The measured temperature value is for an exposed-end armored thermocouple. For static temperature, The gas flow velocity in the area to be measured. For isobaric specific heat capacity, To restore the positive coefficient, As a reference for restoring positive coefficients, For reference pressure, Here is the reference temperature, and p is the real-time pressure. To calculate the coefficients; The data was obtained through actual measurement using a measuring device whose detection end is located near the hypersonic temperature sensor measuring device. For setting value, for Pressure values ​​near the hypersonic temperature sensor measuring device under certain conditions. Obtained through measurement; The specific heat capacity at constant pressure is obtained through experiments or by consulting known common gases; p is obtained in real time through a measuring device near the hypersonic temperature sensor measuring device. The diameter of the thermocouple wire, the type of gas being measured, and the gas flow rate based on the exposed-end armored thermocouple are obtained through experiments or by consulting known tables. : Obtained through experiments; Exposed-end armored thermocouples were placed in test airflows at different known temperatures for measurement, and the temperature sensor's measurement results were as follows: The temperature of the test airflow is T, and the corresponding Substituting T into the temperature correction and compensation formula above, n can be calculated by reverse calculation.

[0009] In some embodiments, the sidewall of the stagnation shield is provided with multiple air outlets, all of which are evenly distributed around the axis of the stagnation shield.

[0010] In some embodiments, along the length of the stagnation shroud, the distance between the end of the stagnation shroud furthest from the outer tube and the detection end of the exposed-end armored thermocouple is 3 to 5 mm, and the distance between the detection end of the exposed-end armored thermocouple and the outlet is 3 to 5 mm.

[0011] In some embodiments, the distance from the sensing end of the exposed-end armored thermocouple to the metal housing is 8 to 10 mm along the length of the stagnation shield.

[0012] In some embodiments, the outer tube is composed of two parts, the interface between the two parts of the outer tube is parallel to the length direction of the outer tube, and the stagnation cover is formed on one part of the outer tube.

[0013] In some embodiments, the weld between the metal shell and the stagnation shield of the exposed-end armored thermocouple is located inside the outer tube.

[0014] In some embodiments, the weld between the metal shell and the stagnation shield of the exposed-end armored thermocouple is an electron beam weld.

[0015] In some embodiments, the hypersonic temperature sensor measuring device further includes a cooling structure encased in an outer tube, the cooling structure having a cooling channel for introducing a fluid medium, the input and output ends of the cooling channel being located at the open end of the outer tube.

[0016] In some embodiments, magnesium oxide particles are filled between the metal shell and the thermocouple wire of the exposed-end armored thermocouple.

[0017] In some embodiments, the hypersonic temperature sensor measuring device also includes a cap mounted on the open end of the outer tube, through which the wires of all exposed-end armored thermocouples pass.

[0018] Compared with the prior art, the beneficial effects of the present invention are as follows: This invention utilizes an exposed-end armored thermocouple with a high response frequency. The outer tube and stagnation shield are made of metal, and the stagnation shield and exposed-end armored thermocouple are sealed and welded together. The metal shell of the exposed-end armored thermocouple is filled with inorganic insulating particles, which can reliably fix the thermocouple wire inside the metal shell. The overall structure of the hypersonic temperature sensor measuring device is reliable, which can extend the temperature acquisition time of the hypersonic temperature sensor measuring device under the impact of high temperature and hypersonic airflow, and improve the reliability of the measurement results. Attached Figure Description

[0019] The accompanying drawings, which are included to provide a further understanding of the invention and form part of this application, illustrate exemplary embodiments of the invention and, together with their description, serve to explain the invention and do not constitute an undue limitation thereof. In the drawings: Figure 1 This is a schematic diagram of the hypersonic temperature sensor measuring device without a water-cooling structure in a specific embodiment of the present invention; Figure 2 This is a schematic diagram of the internal structure of the stagnation cover in a specific embodiment of the present invention.

[0020] In the diagram: 1. Outer tube; 2. Silencing cover; 21. Air inlet; 22. Air outlet; 3. Exposed-end armored thermocouple; 31. Metal shell; 32. Thermocouple wire; 33. Inorganic insulating particles; 34. Detection end; 4. End cap; 5. Weld. Detailed Implementation

[0021] The technical solutions in 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 a part of the embodiments of the present invention, and not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0022] In the description of this invention, it should be understood that the terms "center", "lateral", "longitudinal", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention 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. Therefore, they should not be construed as limitations on this invention.

[0023] The terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined as "first," "second," or "third" may explicitly or implicitly include one or more of that feature.

[0024] In the description of this invention, it should be noted 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; and they can refer to the internal communication between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0025] like Figure 1-2As shown in the schematic embodiment of the hypersonic temperature sensor measuring device of the present invention, the hypersonic temperature sensor measuring device includes an outer tube 1, a stagnation cover 2, and an exposed-end armored thermocouple 3; one end of the outer tube 1 is closed, and the other end of the outer tube 1 is open; a plurality of stagnation covers 2 connected to the outer tube 1 are formed on the outer side wall of the outer tube 1 along the length direction of the outer tube 1, the end of the stagnation cover 2 away from the outer tube 1 is an air inlet 21, and at least one air outlet 22 is provided on the side wall of the stagnation cover 2; an exposed-end armored thermocouple 3 is provided in each stagnation cover 2, and the metal shell 31 of the exposed-end armored thermocouple 3 is sealed and welded to the stagnation cover 2; all air outlets 22 are located between the detection end 34 of their corresponding exposed-end armored thermocouple 3 and the metal shell 31.

[0026] In this embodiment, the exposed-end armored thermocouple 3 has a high response frequency. The outer tube 1 and the stagnation cover 2 are made of metal. The stagnation cover 2 and the exposed-end armored thermocouple 3 are sealed and welded. The metal shell 31 of the exposed-end armored thermocouple 3 is filled with inorganic insulating particles 33, which can reliably fix the thermocouple wire 32 inside the metal shell 31. The overall structure of the hypersonic temperature sensor measuring device is reliable, which can extend the temperature acquisition time of the hypersonic temperature sensor measuring device under the impact of high temperature and hypersonic airflow and improve the reliability of the measurement results. The hypersonic temperature sensor measurement device also includes a temperature calculation module connected to an exposed-end armored thermocouple. This module corrects the measured temperature of the exposed-end armored thermocouple using a temperature correction and compensation formula, outputting the static temperature. The temperature correction and compensation formula is as follows:

[0027]

[0028] In the formula, The measured temperature value is for an exposed-end armored thermocouple. For static temperature, The gas flow velocity in the area to be measured. For isobaric specific heat capacity, To restore the positive coefficient, As a reference for restoring positive coefficients, For reference pressure, Here is the reference temperature, and p is the real-time pressure. To calculate the coefficients; The data was obtained through actual measurement using a measuring device whose detection end is located near the hypersonic temperature sensor measuring device. For setting value, for Pressure values ​​near the hypersonic temperature sensor measuring device under certain conditions. Obtained through measurement; The specific heat capacity at constant pressure is obtained through experiments or by consulting known common gases; p is obtained in real time through a measuring device near the hypersonic temperature sensor measuring device. The wire diameter, gas type, and gas flow rate of the exposed-end armored thermocouple were obtained experimentally or by consulting known tables, which are recorded in NACA TN3455 (1955). For example, when the wire diameter was 0.32 mm, the gas was air, and the flow rates were 0.2, 0.4, 0.6, 0.8, 1.2, 1.6, and 2 (in Ma), the values ​​of Δa were 0.0010, 0.0015, 0.0030, 0.0045, 0.0050, 0.0060, and 0.0075, respectively.

[0029] : Obtained through experiments; Exposed-end armored thermocouples were placed in test airflows at different known temperatures for measurement, and the temperature sensor's measurement results were as follows: The temperature of the test airflow is T, and the corresponding Substituting T into the temperature correction and compensation formula above, n can be calculated by reverse calculation.

[0030] In some embodiments, the sidewall of the stagnation cover 2 is provided with multiple air outlets 22, and all air outlets 22 are evenly distributed around the axis of the stagnation cover 2 to improve the circumferential temperature uniformity of the detection end 34 of the exposed end armored thermocouple 3.

[0031] In some embodiments, along the length of the stagnation hood 2, the distance between the end of the stagnation hood 2 away from the outer tube 1 and the detection end 34 of the exposed-end armored thermocouple 3 is 3 to 5 mm, and the distance between the detection end 34 of the exposed-end armored thermocouple 3 and the air outlet 22 is 3 to 5 mm, so as to ensure the airflow stagnation effect inside the stagnation hood 2 and improve the detection effect.

[0032] In some embodiments, the distance from the detection end 34 of the exposed-end armored thermocouple 3 to the metal housing 31 in the length direction of the stagnation cover 2 is 8 to 10 mm. By increasing the length of the detection end 34 of the exposed-end armored thermocouple 3, the time constant of the exposed-end armored thermocouple 3 is reduced, thereby improving the measurement efficiency of the exposed-end armored thermocouple 3.

[0033] In some embodiments, the outer tube 1 is composed of two parts, the interface between the two parts of the outer tube 1 is parallel to the length direction of the outer tube 1, and the stagnation cover 2 is formed on one part of the outer tube 1 to facilitate the assembly of the metal shell 31 and the stagnation cover 2.

[0034] Furthermore, the outer tube 1 is a stainless steel outer tube 1, the stagnation cover 2 is a stainless steel stagnation cover 2, and the metal shell 31 of the exposed end armored thermocouple 3 is a stainless steel shell.

[0035] In some embodiments, the weld 5 between the metal shell 31 and the stagnation cover 2 of the exposed-end armored thermocouple 3 is located inside the outer tube 1, which reduces the possibility of the weld 5 being damaged by airflow impact and extends the service life of the hypersonic temperature sensor measuring device.

[0036] In some embodiments, the weld 5 between the metal housing 31 and the stagnation shield 2 of the exposed armored thermocouple 3 is an electron beam weld. The weld 5 has a high depth-to-width ratio, is not easily oxidized at the weld, has good process repeatability, and has a small amount of thermal deformation, which helps to further improve the connection reliability between the metal housing 31 and the stagnation shield 2 and extend the service life of the hypersonic temperature sensor measuring device.

[0037] In some embodiments, the hypersonic temperature sensor measuring device further includes a cooling structure covering the outer tube 1. The cooling structure has a cooling channel for introducing a fluid medium. The input and output ends of the cooling channel are both located at the open end of the outer tube 1, to further extend the residence time of the hypersonic temperature sensor measuring device under the impact of high-temperature hypersonic airflow. The cooling structure is a stainless steel cooling structure.

[0038] In some embodiments, magnesium oxide particles are filled between the metal shell 31 and the thermocouple wire 32 of the exposed-end armored thermocouple 3, which helps to extend the service life of the exposed-end armored thermocouple 3 under high-temperature and hypersonic airflow impact conditions.

[0039] In some embodiments, the hypersonic temperature sensor measuring device also includes a cap installed at the open end of the outer tube 1, through which the wires of all exposed-end armored thermocouples 3 pass.

[0040] Through the description of several embodiments of the hypersonic temperature sensor measuring device of the present invention, it can be seen that the embodiments of the hypersonic temperature sensor measuring device of the present invention have at least the following advantages: This invention utilizes an exposed-end armored thermocouple with a high response frequency. The outer tube and stagnation shield are made of metal, and the stagnation shield and exposed-end armored thermocouple are sealed and welded together. The metal shell of the exposed-end armored thermocouple is filled with inorganic insulating particles, which can reliably fix the thermocouple wire inside the metal shell. The overall structure of the hypersonic temperature sensor measuring device is reliable, which can extend the temperature acquisition time of the hypersonic temperature sensor measuring device under the impact of high temperature and hypersonic airflow, and improve the reliability of the measurement results.

[0041] Finally, it should be noted that the various embodiments in this specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0042] The above embodiments are only used to illustrate the technical solutions of the present invention and not to limit them; although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications can still be made to the specific implementation of the present invention or equivalent substitutions can be made to some technical features without departing from the spirit of the technical solutions of the present invention, and all such modifications and substitutions should be covered within the scope of the technical solutions claimed in the present invention.

Claims

1. A hypersonic temperature sensor measurement device, characterized by, The temperature sensor measuring device comprises an outer tube, a stagnation cover and a exposed-type armored thermocouple; one end of the outer tube is closed, and the other end of the outer tube is open; a plurality of stagnation covers are formed on the outer tube along the length direction of the outer tube, and the stagnation covers are communicated with the outer tube; the end of the stagnation cover away from the outer tube is an air inlet, and at least one air outlet is arranged on the side wall of the stagnation cover; one exposed-type armored thermocouple is arranged in each stagnation cover, and the metal shell of the exposed-type armored thermocouple is sealingly welded with the stagnation cover; all the air outlets are located between the detection end of the corresponding exposed-type armored thermocouple and the metal shell. The high supersonic temperature sensor measuring device further comprises a temperature operation module connected with the exposed-type armored thermocouple, and the temperature operation module is used for correcting the measured temperature of the exposed-type armored thermocouple through a temperature correction compensation formula and outputting the static temperature. The temperature correction compensation formula is as follows: wherein, is the measured temperature value of the exposed end armored thermocouple, is the static temperature, is the gas flow rate of the region to be measured, is the specific heat capacity at constant pressure, is the recovery positive coefficient, is the reference recovery positive coefficient, is the reference pressure, is the reference temperature, p is the real-time pressure, is the calculation coefficient; Obtained by detecting the measuring device located near the hypersonic temperature sensor measuring device is set to a value, is the pressure value in the vicinity of the hypersonic temperature sensor measuring device under the condition, obtained by measuring; obtained by experiment or by consulting the average constant-pressure specific heat capacity of commonly known gases; p is obtained in real time by measuring with a measuring device in the vicinity of the hypersonic temperature sensor measuring device; The thermocouple wire diameter is obtained by experiment or by consulting a known table based on the exposed type armored thermocouple, the type of gas measured, and the gas flow rate. : Obtained by experiment; the exposed end armored thermocouple is placed in different test gas streams with known temperature, the measured result of the temperature sensor is , the temperature of the test gas stream is T, and the corresponding and T are brought into the above temperature correction compensation formula to calculate n inversely.

2. A high-hypersonic temperature sensor measuring device according to claim 1, characterized in that The side wall of the stagnation cover is provided with a plurality of air outlets, and all the air outlets are uniformly distributed around the axis of the stagnation cover.

3. A hypersonic temperature sensor measuring device according to claim 2, wherein, In the length direction of the stagnation cover, the distance between the end of the stagnation cover away from the outer tube and the detection end of the exposed-type armored thermocouple is 3 to 5 mm, and the distance between the detection end of the exposed-type armored thermocouple and the air outlet is 3 to 5 mm.

4. A hypersonic temperature sensor measuring device according to claim 3, wherein In the length direction of the stagnation cover, the distance between the detection end of the exposed-type armored thermocouple and the metal shell is 8 to 10 mm.

5. A hypersonic temperature sensor measuring device according to claim 1, wherein, The outer tube is composed of two parts, the interface between the two parts of the outer tube is parallel to the length direction of the outer tube, and the stagnation cover is formed on one part of the outer tube.

6. A hypersonic temperature sensor measuring device according to claim 5, wherein, The welding seam between the metal shell of the exposed-type armored thermocouple and the stagnation cover is located inside the outer tube.

7. A hypersonic temperature sensor measuring device according to claim 6, wherein, The welding seam between the metal shell of the exposed-type armored thermocouple and the stagnation cover is an electron beam welding seam.

8. A high-temperature supersonic sensor measuring device according to any one of claims 1-7, characterized in that, The temperature sensor measuring device further comprises a cooling structure wrapped around the outer tube, and the cooling structure has a cooling channel for passing fluid medium inside; the input end and the output end of the cooling channel are located at the open end of the outer tube.

9. A high-temperature supersonic sensor measuring device according to any one of claims 1-7, characterized in that, Magnesium oxide particles are filled between the metal shell of the exposed-type armored thermocouple and the thermocouple wire.

10. A high-temperature supersonic sensor measuring device according to any one of claims 1-7, characterized in that, The temperature sensor measuring device further comprises a cover installed at the open end of the outer tube, and the wires of all the exposed-type armored thermocouples pass through the end cover.

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