Total temperature and total pressure sampling composite probe

Abstract

The invention provides a total temperature and total pressure sampling composite probe, and belongs to the technical field of aero-engines, the total temperature and total pressure sampling composite probe comprises a fairing, a double-hole porcelain tube fixed in the fairing, a sampling tube arranged outside the fairing, a gas collection cavity arranged at the tail end of the fairing and the tail end of the sampling tube and a sampling adapter tube, and the tail end of the sampling adapter tube is connected with sampling equipment. Positive and negative electrodes of the thermocouple are respectively fixed in holes of the double-hole porcelain tube, a gap is formed between the fairing and the sampling tube, a windward end of the fairing is provided with a plurality of high-temperature gas collecting holes and a mounting hole, a gas discharge tube is mounted on the mounting hole, and a high-temperature gas discharge hole is formed in the gas discharge tube; high-temperature fuel gas flows into the inner side of the fairing through a windward end gas inlet hole of the fairing, one part of the high-temperature fuel gas flows out of the high-temperature fuel gas drainage hole, and the other part of the high-temperature fuel gas flows into a gap between the fairing and the sampling pipe, the gas collecting cavity, the sampling adapter pipe and sampling equipment in sequence from the high-temperature fuel gas collecting hole. According to the invention, high integration of measuring points of ultra-high temperature measurement is realized, and the reliability of probe measurement is improved.

Description

TECHNICAL FIELD

[0001] The application relates to the technical field of an aero-engine, and particularly relates to a total temperature and total pressure sampling composite probe. BACKGROUND

[0002] For an aero-engine, the gas temperature directly determines the working performance of the engine. Therefore, the most direct method to improve the thrust-to-weight ratio of the engine is to increase the turbine inlet and outlet temperature of the engine. The development of aero-engines is towards higher gas working temperature, higher heat capacity and higher inlet and outlet average temperature, so that the working temperature of the aero-engine is continuously pushed to a new height. Aero-engine testing is a basic method and approach to obtain qualitative or quantitative information of an aero-engine, which is to obtain various state parameter data of the engine by a sensitive device, and to process and evaluate the data to analyze and evaluate the performance, function and reliability of the aero-engine. Therefore, for the current and future advanced aero-engine, the design, testing and health management of the engine all need the support of ultra-high temperature gas measurement technology. The outlet temperature distribution of the combustion chamber is an important design index of the combustion chamber. Due to the increase of the outlet temperature of the combustion chamber, the requirement for the distribution of the outlet temperature of the combustion chamber is becoming more and more stringent.

[0003] The outlet temperature measurement of the combustion chamber component test at home and abroad mainly adopts traditional contact type measurement means such as thermocouple and gas sampling analysis, and non-contact type measurement means based on laser spectrum diagnosis technology (TDLAS, CARS, PLIF, etc.) as a supplementary way of gas testing. The non-contact TDLAS technology is the most commonly used method in the world at present, and is also the research hotspot in the world. The non-contact TDLAS technology has the advantages of small disturbance to the flow field and fast response rate. TDLAS measurement needs to design a detailed optical window on the combustion chamber test piece, and also needs to avoid the interference of oil stains to shield the surface of the optical window. However, the engine combustion environment often has the characteristics of strong vibration, strong turbulence and many scattered particles, so there are serious interference factors to the measurement signal, and therefore the measurement accuracy of the temperature field based on the current technology cannot meet the performance evaluation requirements of the combustion chamber, and the method is also not mature enough in the data processing method and signal detection technology.

[0004] Therefore, the acquisition of the outlet radial temperature distribution, the outlet circumferential temperature distribution and the temperature of the hot junction of the combustion chamber mainly relies on the contact type measurement results. At present, the outlet temperature distribution of the aero-engine combustion chamber is measured by a thermocouple total temperature probe, a total pressure probe and a gas sampling probe, and the measurement data may not belong to the same gas flow and not at the same time, resulting in low accuracy of the measurement results. SUMMARY

[0005] Therefore, the total temperature and total pressure sampling composite probe provided by the embodiments of the present application at least partially solves the problem of low result accuracy caused by multiple probes for separate measurement in the prior art.

[0006] The total temperature and total pressure sampling composite probe provided by the embodiments of the present application comprises a fairing, a double-hole porcelain tube fixed on the inner side of the fairing, a sampling tube arranged on the outer side of the fairing, a gas collection cavity arranged at the tail end of the fairing and the sampling tube, and a sampling adapter pipe fixed on the gas collection cavity, the tail end of the sampling adapter pipe being connected to a sampling device, the positive and negative electrodes of a thermocouple being fixed in the holes of the double-hole porcelain tube, a gap being arranged between the fairing and the sampling tube, a plurality of high-temperature gas collection holes and a plurality of mounting holes being arranged on the windward end of the fairing, a gas discharge pipe being mounted on the mounting holes, the gas discharge pipe penetrating through the sampling tube and the fairing, and a high-temperature gas discharge hole being arranged on the gas discharge pipe; high-temperature gas flows into the inner side of the fairing through the air inlet holes on the windward end of the fairing, part of the high-temperature gas flows out from the high-temperature gas discharge hole, and the other part of the high-temperature gas flows into the gap between the fairing and the sampling tube, the gas collection cavity, the sampling adapter pipe and the sampling device in sequence through the high-temperature gas collection holes.

[0007] According to a specific implementation manner of the embodiments of the present application, the fairing is a hollow columnar structure, the windward end of the fairing is provided with a boss extending in the circumferential direction, the fairing and the sampling tube are butted against each other at the windward end to form a closed structure, and the fairing is internally provided with a stepped hole for mounting the double-hole porcelain tube.

[0008] According to a specific implementation manner of the embodiments of the present application, the thermocouple is arranged as an iridium-rhodium 40-iridium thermocouple.

[0009] According to a specific implementation manner of the embodiments of the present application, the surface of the thermocouple in contact with the high-temperature gas is provided with an alumina coating.

[0010] According to a specific implementation manner of the embodiments of the present application, the gas collection cavity is arranged as a hollow columnar structure, the side surface of the gas collection cavity is provided with through holes for fixed mounting of the fairing, the sampling tube and the sampling adapter pipe, and the two ends of the gas collection cavity are sealed by plugs.

[0011] According to a specific implementation manner of the embodiments of the present application, the tail end of the sampling adapter pipe is provided with a tee pipe and a solenoid valve for switching of the sampling function and the total pressure test function.

[0012] According to a specific implementation manner of the embodiments of the present application, the distance from the center of the high-temperature gas collection hole or the mounting hole to the windward end surface of the fairing is 2.5-3 times the diameter of the air inlet hole.

[0013] According to a specific implementation manner of the embodiments of the present application, the ratio of the area of the air inlet hole to the total area of the plurality of high-temperature gas collection holes is 3-3.5, and the ratio of the area of the air inlet hole to the total area of the high-temperature gas discharge holes is 3-3.5.

[0014] According to a specific implementation manner of the embodiment of the present application, the distance between the mounting surface of the double-hole porcelain tube and the center of the high-temperature gas collection hole is 1-1.5 times the diameter of the high-temperature gas collection hole, and / or the distance between the mounting surface of the double-hole porcelain tube and the center of the mounting hole is 1-1.5 times the diameter of the mounting hole.

[0015] The total temperature and total pressure sampling composite probe according to claim 1, wherein the length of the positive and negative poles of the thermocouple extending out of the double-hole porcelain tube satisfies that the length-diameter ratio is not less than 9.

[0016] Beneficial effects: The total temperature and total pressure sampling composite probe in the embodiment of the present application integrates the thermocouple temperature measurement, total pressure and gas sampling together, forms a probe with multiple functions, can improve the probe measurement reliability, and obtains more test data. The data of the combustion chamber outlet temperature distribution obtained by test can obtain various data of the combustion chamber aerodynamic performance, and relying on the test data can further guide the improvement of the combustion chamber design and finally improve the performance of the designed combustion chamber. BRIEF DESCRIPTION OF DRAWINGS

[0017] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed in the embodiments will be briefly introduced as follows. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can also be obtained by those skilled in the art without creative labor.

[0018] Figure 1 FIG. 1 is a structural diagram of the total temperature and total pressure sampling composite probe according to an embodiment of the present application; Figure 2 FIG. 2 is an A-A sectional view of FIG. 1; Figure 1 FIG. 3 is a structural diagram of the fairing according to an embodiment of the present application; Figure 3 FIG. 4 is a B-B sectional view of FIG. 3. Figure 4 Figure 3 FIG. 5 is a structural diagram of the fairing according to an embodiment of the present application.

[0019] In the figure: 1, thermocouple; 2, fairing; 3, gas vent pipe; 4, double-hole porcelain tube; 5, sampling pipe; 6, gas collection cavity; 7, plug cover; 8, sampling adapter pipe; 9, high-temperature gas flow hole; 10, high-temperature gas collection hole; 11, stepped hole; 12, boss; 13, mounting hole. DETAILED DESCRIPTION

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

[0021] ​Following, the embodiments of the present application are described through specific examples, and other advantages and effects of the present application can be easily understood by those skilled in the art from the disclosure. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The present application can also be implemented or applied through other different specific embodiments, and various modifications or changes can be made to the details in the specification based on different views and applications without departing from the spirit of the present application. It should be noted that the following embodiments and features in the embodiments can be combined with each other without conflict. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor are within the scope of protection of the present application.

[0022] It should be noted that the various aspects of the embodiments described below are within the scope of the appended claims. It should be apparent that the aspects described herein can be embodied in a wide variety of forms and that any specific structure and / or function described herein is merely illustrative. Based on the teachings herein one skilled in the art should appreciate that an aspect described herein can be implemented independently of any other aspects and that an aspect can be implemented both as any number of software, firmware, and / or hardware structures.

[0023] It should also be noted that the figures provided in the following embodiments are only to illustrate the basic concepts of the present application in a schematic manner, and only the components related to the present application are shown in the figures, not drawn according to the number, shape and size of the components in actual implementation, and the actual implementation of each component can be a random change in shape, number and proportion, and the layout of the components can also be more complex.

[0024] In addition, in the following description, specific details are provided to facilitate a thorough understanding of examples. However, one skilled in the art will understand that the described aspects can be practiced without these specific details.

[0025] The embodiments of the present application provide a total temperature and total pressure sampling composite probe, which is described below with reference to Figures 1 to 4 in detail.

[0026] In one embodiment, with reference to Figures 1 to 4The total temperature and total pressure sampling composite probe comprises a fairing 2, a double-hole porcelain tube 4 fixed inside the fairing 2, a sampling tube 5 arranged outside the fairing 2, a gas collection cavity 6 arranged at the tail end of the fairing 2 and the sampling tube 5, and a sampling adapter pipe 8 fixed on the gas collection cavity 6, the tail end of the sampling adapter pipe 8 being connected to a sampling device, the positive and negative electrodes of a thermocouple 1 being fixed in the holes of the double-hole porcelain tube 4, a gap being arranged between the fairing 2 and the sampling tube 5, a plurality of high-temperature gas collection holes 10 and a plurality of mounting holes 13 being arranged at the windward end of the fairing 2, a gas discharge pipe 3 being mounted on the mounting hole 13, the gas discharge pipe 3 penetrating through the sampling tube 5 and the fairing 2, and a high-temperature gas discharge hole 9 being arranged on the gas discharge pipe 3; high-temperature gas flows into the inside of the fairing 2 through the gas inlet hole at the windward end of the fairing 2, part of the high-temperature gas flows out from the high-temperature gas discharge hole 9, and the other part of the high-temperature gas flows into the gap between the fairing 2 and the sampling tube 5, the gas collection cavity 6, the sampling adapter pipe 8 and the sampling device in sequence through the high-temperature gas collection holes 10.

[0027] In the embodiment, the functions of the probe are integrated by structural and functional integration design on the basis of the size of a single functional probe, high-temperature gas measurement ≤2250K is realized, and the size of the total temperature and total pressure sampling composite probe ≤6mm.

[0028] Further, referring to Figure 3 The fairing 2 is a hollow columnar structure, the windward end of the fairing 2 is provided with a flange 12 extending in the circumferential direction, the fairing 2 and the sampling tube 5 are butted at the windward end to form a closed structure through the flange 12, and the inside of the fairing 2 is provided with a stepped hole 11 for mounting the double-hole porcelain tube 4.

[0029] Specifically, the fairing 2 is a hollow columnar structure with a flange 12 outside, the inside is provided with a stepped hole 11 for mounting the double-hole porcelain tube 4, N high-temperature gas collection holes 10 are opened on the side surface for the sampling tube 5 to collect high-temperature gas, and M mounting holes 13 are opened for high-temperature gas discharge; the side wall of the fairing 2 is designed to have both small holes for collecting high-temperature gas and high-temperature gas discharge holes 9, so as to reduce the total temperature speed error and the radiation error, improve the insensitive angle range of the total pressure, ensure that the total temperature measurement accuracy is ≤1% at ≤2250K, and the total pressure measurement accuracy reaches ≤0.3% within a range of ±20°.

[0030] In one embodiment, the thermocouple 1 is arranged as an iridium-rhodium 40-iridium thermocouple 1.

[0031] Preferably, the surface of the thermocouple 1 in contact with the high-temperature gas is provided with an alumina coating.

[0032] Specifically, the positive and negative electrodes of the iridium-rhodium 40-iridium thermocouple 1 are fixed in the double-hole porcelain tube 4 with insulation function, and the exposed surface in contact with high-temperature gas is sprayed with an alumina coating after positioning and sizing. The average thickness of the surface alumina coating is about 40 μm, which avoids the oxidation and volatilization of iridium elements, causing performance degradation and failure of the iridium-rhodium thermocouple. The iridium-rhodium thermocouple 1 and the double-hole porcelain tube 4 are embedded in the rectifier cover 2 made of platinum-iridium alloy material. The high-temperature gas flows into the rectifier cover 2 through the windward end and flows out from the gas discharge pipe 3. The high-temperature gas exchanges heat with the iridium-rhodium 40-iridium thermocouple 1, achieving total temperature measurement function.

[0033] In one embodiment, the gas collection cavity 6 is provided as a hollow columnar structure, and the side surface of the gas collection cavity 6 is provided with through holes for fixed installation of the rectifier cover 2, the sampling pipe 5 and the sampling adapter pipe 8. The two ends of the gas collection cavity 6 are sealed by the plug 7.

[0034] Further, the tail end of the sampling adapter pipe 8 is provided with a three-way pipe and an electromagnetic valve for switching between the sampling function and the total pressure test function.

[0035] In specific implementation, the side surface of the gas collection cavity 6 is provided with openings for fixed installation of the rectifier cover 2, the sampling pipe 5 and the sampling adapter pipe 8, and the two end openings of the gas collection cavity 6 are sealed by the plug 7. The gas collection cavity 6 collects the >2250K high-temperature gas flowing through the cavity formed by the high-temperature gas collection hole 10 of the side wall of the rectifier cover 2 and the sampling pipe 5, and the high-temperature gas is introduced to a gas analysis instrument through the sampling adapter pipe 8, achieving the sampling function. The tail end of the sampling adapter pipe 8 is directly connected to a pressure sensor or other collection equipment, achieving the total pressure measurement function. The three-way pipe and the electromagnetic valve installed at the tail end of the sampling adapter pipe 8 can switch between the sampling function and the total pressure function of the probe.

[0036] In one embodiment, the distance between the center of the high-temperature gas collection hole 10 or the mounting hole 13 and the windward end surface of the rectifier cover 2 is 2.5-3 times the diameter of the inlet hole, which ensures that the measurement point position of the iridium-rhodium 40-iridium thermocouple 1 has a relatively stable aerodynamic environment, reducing data fluctuations.

[0037] In one embodiment, the ratio of the area of the inlet hole to the total area of the plurality of high-temperature gas collection holes 10 is 3-3.5, and the ratio of the annular area between the inner diameter of the sampling pipe 5 and the outer diameter of the rectifier cover 2 to the total area of the N high-temperature gas collection holes 10 is 1, which ensures that sufficient high-temperature gas can be collected through the annular cavity between the inner diameter of the sampling pipe 5 and the outer diameter of the rectifier cover 2. When the throat speed condition is established by air pumping, the areas of the two sections are equal, and the flow channel size of the high-temperature gas flow is unified.

[0038] The ratio of the area of the air inlet hole to the total area of the high-temperature gas discharge hole 9 is 3-3.5. The ratio of the area of the air inlet hole of the fairing 2 to the total area of the M mounting holes 13 is 1.5-2. The gas discharge pipe 3 is matched with the M mounting holes 13, and finally the ratio of the area of the air inlet hole of the fairing 2 to the total area of the inner diameter of the gas discharge pipe 3 is 3-3.5. The high-temperature gas flowing into the fairing 2 flows out through the gas discharge pipe 3, and the high-temperature gas flowing into the fairing 2 is ensured to be in a high flow state.

[0039] In an embodiment, the distance between the mounting surface of the double-hole porcelain tube 4 and the center of the high-temperature gas collection hole 10 is 1-1.5 times the diameter of the high-temperature gas collection hole 10, and / or the distance between the mounting surface of the double-hole porcelain tube 4 and the center of the mounting hole 13 is 1-1.5 times the diameter of the mounting hole 13. The position of the iridium-rhodium 40-iridium thermocouple 1 is ensured to have a relatively stable aerodynamic environment, and the data fluctuation is reduced.

[0040] In an embodiment, the length of the positive and negative electrodes of the thermocouple 1 extending out of the double-hole porcelain tube 4 satisfies that the length-diameter ratio is not less than 9. The length of the iridium-rhodium 40-iridium thermocouple 1 extending out is ensured to have sufficient supporting strength in a high-temperature environment, while reducing the heat conduction error and improving the measurement accuracy of the thermocouple 1.

[0041] In an embodiment, the ratio of the area of the inner hole of the sampling adapter pipe 8 to the total area of the N high-temperature gas collection holes 10 is 1-1.5. The high-temperature gas flowing into the fairing 2 flows out through the gas discharge pipe 3, and the area ratio is ensured to be sufficient for the high-temperature gas to be collected through the annular cavity between the inner diameter of the sampling pipe 5 and the outer diameter of the fairing 2.

[0042] In an embodiment, the structural members of the probe are thin-walled members with a thickness of 0.5-1 mm, and laser welding is used for welding the structural members, platinum-rhodium welding wire is added, and after welding, there is no crack and no deformation, and the weld is subjected to flaw detection inspection and pressure confirmation to ensure the sealing property.

[0043] The embodiment provided by the application has the functions of temperature measurement and sampling analysis, and ensures that the high-temperature gas contacted and sampled by the thermocouple 1 is the same gas flow. In the performance test of the aero-engine combustion chamber, the thermocouple 1 and the sampling analysis simultaneously measure the total temperature at the same position, which can not only increase the measurement margin and ensure the acquisition of test data, but also be used for comparative analysis of two temperature measurement technologies. At the same time, when the gas is not sampled, the back end can switch to measure the total pressure through the electronic valve, and has the functions of total temperature and total pressure or total temperature and sampling at the same time. The application not only realizes the high integration of the measurement point of the ultra-high temperature measurement, but also improves the reliability of the temperature measurement.

[0044] The above merely provides the specific implementation of the present application, but the protection scope of the present application is not limited to this. Any changes or replacements within the technical scope disclosed by the present application can be easily conceived by the person skilled in the art, and should be covered within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A total temperature and total pressure sampling composite probe, characterized in that, The probe includes a shroud (2), a double-hole ceramic tube (4) fixed inside the shroud (2), a sampling tube (5) set outside the shroud (2), a gas collection chamber (6) set at the tail end of the shroud (2) and the sampling tube (5), and a sampling adapter (8) fixed on the gas collection chamber (6). The tail end of the sampling adapter (8) is connected to a sampling device. The positive and negative poles of the thermocouple (1) are fixed in the holes of the double-hole ceramic tube (4), respectively. There is a gap between the shroud (2) and the sampling tube (5). The shroud (2) has multiple high-temperature gas collection holes (10) and multiple safety gates at the windward end. Install hole (13), install vent pipe (3) on the installation hole (13), vent pipe (3) passes through sampling pipe (5) and hood (2), vent pipe (3) is provided with high temperature gas vent hole (9); high temperature gas flows into the inside of hood (2) through the air inlet at the windward end of hood (2), part of the high temperature gas flows out from the high temperature gas vent hole (9), and the other part of the high temperature gas flows into the gap between hood (2) and sampling pipe (5), gas collection chamber (6), sampling adapter pipe (8) and sampling equipment through the high temperature gas collection hole (10).

2. The total temperature and total pressure sampling composite probe according to claim 1, characterized in that, The fairing (2) is a hollow columnar structure. The windward end of the fairing (2) is provided with a boss (12) extending in the circumferential direction. The boss (12) and the sampling tube (5) are connected to form a closed structure at the windward end. The interior of the fairing (2) is provided with a stepped hole (11) for installing a double-hole ceramic tube (4).

3. The total temperature and total pressure sampling composite probe according to claim 1, characterized in that, The thermocouple (1) is configured as an iridium-rhodium 40-iridium thermocouple (1).

4. The total temperature and total pressure sampling composite probe according to claim 3, characterized in that, The surface of the thermocouple (1) that comes into contact with the high-temperature gas is coated with an aluminum oxide coating.

5. The total temperature and total pressure sampling composite probe according to claim 1, characterized in that, The gas collection chamber (6) is configured as a hollow columnar structure. The side of the gas collection chamber (6) is provided with through holes for fixing the fairing (2), sampling tube (5) and sampling adapter tube (8). The two ends of the gas collection chamber (6) are sealed by plugs (7).

6. The total temperature and total pressure sampling composite probe according to claim 1, characterized in that, The tail end of the sampling adapter (8) is equipped with a three-way pipe and a solenoid valve for switching between sampling function and total pressure test function.

7. The total temperature and total pressure sampling composite probe according to claim 1, characterized in that, The distance between the center of the high-temperature gas collection hole (10) or the mounting hole (13) and the windward end face of the shroud (2) is 2.5-3 times the diameter of the air inlet.

8. The total temperature and total pressure sampling composite probe according to claim 1, characterized in that, The ratio of the area of ​​the air inlet to the total area of ​​the multiple high-temperature gas collection holes (10) is 3-3.5, and the ratio of the area of ​​the air inlet to the total area of ​​the high-temperature gas vent hole (9) is 3-3.

5.

9. The total temperature and total pressure sampling composite probe according to claim 1, characterized in that, The distance between the mounting surface of the double-hole ceramic tube (4) and the center of the high-temperature gas collection hole (10) is 1-1.5 times the diameter of the high-temperature gas collection hole (10), and / or the distance between the mounting surface of the double-hole ceramic tube (4) and the center of the mounting hole (13) is 1-1.5 times the diameter of the mounting hole (13).

10. The total temperature and total pressure sampling composite probe according to claim 1, characterized in that, The positive and negative poles of the thermocouple (1) extend out of the double-hole ceramic tube (4) to a length ratio of not less than 9.

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