CN111982457A - Mach number measuring device under high temperature supersonic flow field environment - Google Patents
Mach number measuring device under high temperature supersonic flow field environment Download PDFInfo
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Abstract
The invention provides a Mach number measuring device in a high-temperature supersonic flow field environment, which solves the problems that the existing Mach number measuring device is difficult to realize miniaturization and has low measuring accuracy. The device comprises a measuring rake body, a water inlet pipe, a water outlet pipe, a first pressure sensor, a second pressure sensor, a temperature sensor and probe components, wherein each probe component comprises a total pressure probe, a static pressure probe and a total temperature probe; the windward side of the measuring rake body is of a wedge-shaped structure; a plurality of cooling channels are arranged in the measuring rake body; the water inlet pipe and the water outlet pipe are arranged in the measuring rake body; a plurality of Mach number measuring points are arranged on the windward side of the measuring rake body, and each Mach number measuring point comprises a first air hole and a second air hole which penetrate through the wedge-shaped structure; the total temperature probe is arranged in the first air hole, and a temperature sensor is arranged in the total temperature probe; the total pressure probe is arranged in the second air hole and is connected with the first pressure sensor; the static pressure probe is arranged in the total pressure probe and is connected with the second pressure sensor.
Description
Technical Field
The invention belongs to the field of ground tests of supersonic and hypersonic liquid power systems, and mainly relates to measurement of Mach number of simulated incoming flow of a ground test system of a supersonic and hypersonic liquid power system, in particular to a Mach number measuring device under a high-temperature supersonic flow field environment, which can be applied to a ground test system of a supersonic and hypersonic liquid power system.
Background
In the process of developing the supersonic and hypersonic liquid power system, a large number of ground simulation tests need to be developed, and the premise of the validity of the simulation tests is that the incoming flow at the inlet of the power system is consistent with the incoming flow of real flight. The simulated incoming flow of the (high) supersonic velocity dynamic ground simulation test system or the wind tunnel has the characteristics of high temperature, high pressure, supersonic velocity and oxygen enrichment, and the most important parameter for simulating the incoming flow is Mach number. Because the simulated incoming flow has the characteristics of high temperature, high pressure and supersonic velocity, and the Mach number needs to measure three parameters of total temperature, total pressure and static pressure at the same time, the contact Mach number measuring device is still the most main and most common way for evaluating the incoming flow. However, when the mach number measuring device is placed in an ultrasonic flow field, shock waves can be generated, parameters of total temperature and total pressure after shock waves and shock waves are inconsistent, actually measured parameters are parameters after shock waves, an improper probe structure causes a disordered shock wave system, and the parameters of the total temperature, the total pressure and the like of the current place cannot be truly reflected, so that the mach number measuring result deviates from the actual flow field parameters.
Therefore, the key technical and bottleneck difficulties faced by the mach number measuring device under the high-temperature and supersonic flow field environment at present are as follows: the Mach number measuring device is difficult to work for a long time under the working environment of high temperature, high pressure and high oxygen enrichment, is difficult to realize miniaturization, and is difficult to weaken the shock wave intensity of an ultrasonic flow field, so that the measuring accuracy of the Mach number measuring device is low.
Disclosure of Invention
The invention aims to solve the problems that the existing Mach number measuring device under the high-temperature supersonic flow field environment is difficult to realize miniaturization and has lower measuring accuracy, and provides the Mach number measuring device under the high-temperature supersonic flow field environment. The device realizes the miniaturization of the whole structure by the heat protection technology combining the cooling channel water cooling structure and the high-temperature oxidation-resistant alloy material; the wedge-shaped windward side conforming to the supersonic velocity flow line is adopted, and reasonable intervals among different probes are designed, so that the mutual interference between a shock wave system of a supersonic velocity flow field and adjacent probes is weakened, and the accuracy of the Mach number measuring device is improved.
In order to achieve the above purpose, the technical scheme of the invention is as follows:
a Mach number measuring device in a high-temperature supersonic flow field environment comprises a measuring rake body, a water inlet pipe, a water outlet pipe, a first pressure sensor, a second pressure sensor, a temperature sensor and a plurality of probe assemblies, wherein each probe assembly comprises a total pressure probe, a static pressure probe and a total temperature probe which are all of tubular structures; the measuring rake body is made of high-temperature alloy with high oxidation resistance and high-temperature mechanical property, the windward side of the measuring rake body is of a wedge-shaped structure, and the inclination angle of the wedge-shaped structure is 11-25 degrees; a plurality of cooling channels are arranged in the measuring rake body, one end of each cooling channel is communicated with a shunting ring groove arranged at the bottom end of the measuring rake body, and the other end of each cooling channel is communicated with a backflow ring groove arranged in the middle of the measuring rake body; the water inlet pipe is arranged in the measuring rake body, the inlet of the water inlet pipe is communicated with external cooling water, and the outlet of the water inlet pipe is communicated with a shunting ring groove arranged at the bottom end of the measuring rake body; the water outlet pipe is arranged in the measuring rake body, the inlet of the water outlet pipe is communicated with the backflow ring groove arranged in the middle of the measuring rake body, and the outlet of the water outlet pipe is positioned outside the measuring rake body; a plurality of Mach number measuring points which are arranged in an equal area are arranged on the windward side of the measuring rake body, the distance between every two adjacent Mach number measuring points is more than or equal to 4 times the diameter of the total pressure probe, and each Mach number measuring point comprises a first air hole and a second air hole which penetrate through the wedge-shaped structure; the total temperature probe is arranged in the second air hole, and a temperature sensor is arranged in the total temperature probe; the total pressure probe is arranged in the first air hole, one end of the total pressure probe extends out of the wedge-shaped structure, the other end of the total pressure probe is connected with the first pressure sensor, and a static pressure hole is formed in the pipe wall of the total pressure probe; the static pressure probe is arranged in the total pressure probe, one end of the static pressure probe penetrates through the static pressure hole, and the other end of the static pressure probe is connected with the second pressure sensor.
Further, the inlet of the total pressure probe is a conical horn mouth or a hemisphere shape.
Furthermore, the inlet of the total temperature probe is a conical horn mouth, and the area ratio of the inlet to the outlet is 1.5-3.
Further, the total pressure probe, the static pressure probe and the total temperature probe are integrated with the measuring rake body.
Furthermore, the temperature sensor is PT100, and the lateral wall of total temperature probe is provided with two symmetrical through-holes, and the through-hole constitutes the export after the incoming flow gas stagnates.
Furthermore, GH202 with high temperature resistance and strong oxidation resistance is selected as the material of the measuring rake body.
Furthermore, the measuring rake body is connected with the wind tunnel installation seat through a connecting flange arranged on the outer side of the measuring rake body.
Further, the side of the measuring rake body is provided with a reinforcing pin for improving the strength of the measuring rake body.
Furthermore, the total pressure probe, the static pressure probe and the total temperature probe are made of high-temperature alloy materials.
Further, a high-mesh filter is arranged at the inlet of the water inlet pipe.
Compared with the prior art, the technical scheme of the invention has the beneficial effects that:
1. the Mach number measuring device in the high-temperature supersonic flow field environment adopts the thermal protection technology combining the cooling channel water-cooling structure and the high-temperature oxidation-resistant alloy material, thereby effectively solving the outstanding contradiction between the structural strength and the miniaturization of the Mach number in the wide-range simulated incoming flow environment, realizing the miniaturization of the whole structure, simultaneously ensuring that the working temperature of the device has wide application range and can cover the high-temperature oxygen-enriched fuel gas from normal temperature to above 2000K.
2. The Mach number measuring device in the high-temperature supersonic flow field environment adopts the wedge-shaped windward side which accords with the supersonic flow line, and simultaneously, the space between the probes is reasonably arranged, so that the problems of mutual overlapping and interference of complex shock wave systems of the supersonic flow field are effectively solved, the shock wave system of the supersonic flow field is weakened as much as possible, and the accuracy of the Mach number measuring device is improved.
3. The Mach number measuring device under the high-temperature supersonic flow field environment can be suitable for measuring the Mach number from the subsonic speed to the supersonic speed Ma6, can cover the high-temperature fuel gas from the normal temperature to more than 2000K in the temperature range, and meets the long-time working requirement.
4. The Mach number measuring device and the size range of the wind tunnel in the high-temperature supersonic flow field environment of the invention are
Has a high total pressure recovery coefficient, wherein
When the diameter of the wind tunnel and the Mach number of 5 groups are measured, the maximum total pressure recovery coefficient reaches 97.6 percent.
Drawings
FIG. 1 is a schematic structural diagram of a Mach number measuring device in a high-temperature supersonic flow field environment according to the present invention;
FIG. 2 is a partial cross-sectional view of a Mach number measuring device in a high-temperature supersonic flow field environment according to the present invention;
FIG. 3 is a schematic view of the structure of a cooling channel of the present invention;
FIG. 4 is a schematic view of the installation of the probe assembly of the present invention;
FIG. 5 is a schematic view of the installation of the temperature sensor of the present invention;
FIG. 6 is a schematic view of the installation of the hydrostatic probe of the present invention;
FIG. 7 is a schematic diagram of the present invention with Mach number measurement points arranged in equal areas.
Reference numerals: 1-measuring rake body, 2-water inlet pipe, 3-water outlet pipe, 4-first pressure sensor, 5-second pressure sensor, 6-temperature sensor, 7-total pressure probe, 8-static pressure probe, 9-total temperature probe, 10-connecting flange, 11-wedge structure, 12-cooling channel, 13-shunting ring groove, 14-backflow ring groove, 15-first air hole, 16-second air hole, 17-static pressure hole, 18-reinforcing pin and 19-through hole.
Detailed Description
The invention is described in further detail below with reference to the figures and the detailed description.
The invention provides a Mach number measuring device in a high-temperature supersonic flow field environment, which solves the problem that the existing contact type Mach number measuring device is easy to form a complex shock wave system to further influence the Mach number measuring accuracy in the high-temperature, high-pressure, oxygen-enriched and supersonic flow field environments. The device adopts a thermal protection technology combining a cooling channel water cooling structure and a high-temperature oxidation-resistant alloy material, solves the strength problem in a high-temperature environment, and realizes the miniaturization of the measuring device; meanwhile, a wedge-shaped windward side which accords with the characteristics of the supersonic flow line is adopted, so that the shock wave of the supersonic flow field is weakened as much as possible; in addition, according to the characteristics of the shock wave system, the measuring point intervals are reasonably set, and the flow field interference between the total temperature probe and the total pressure probe and between the characteristic points is reduced, so that the accuracy of Mach number measurement in a high-temperature supersonic gas flow field environment is remarkably improved, and the use requirements of high-temperature supersonic flow field Mach number measurement are met.
The Mach number measuring device can simultaneously measure the total temperature, the total pressure and the static pressure of a plurality of radial sections of the wind tunnel, and determine the Mach number of a certain point of the high-temperature supersonic velocity simulation incoming flow and the Mach number distribution of the same circumferential section and different radial positions, thereby evaluating the simulation incoming flow Mach number of the certain point of the wind tunnel and the radial flow field uniformity of the simulation incoming flow of the wind tunnel.
As shown in fig. 1 and 2, the mach number measuring device in the high-temperature supersonic flow field environment of the present invention includes a measuring rake body 1, a water inlet pipe 2, a water outlet pipe 3, a first pressure sensor 4, a second pressure sensor 5, a temperature sensor 6, a fixed connection flange 10, and a plurality of probe assemblies, where each probe assembly includes a total pressure probe 7, a static pressure probe 8, and a total temperature probe 9, which are all tubular structures. The measuring rake body 1 is the main body part of the Mach number measuring device, and the material of the measuring rake body is high-temperature alloy with high oxidation resistance and high-temperature mechanical property, such as GH202, so that the strength requirement of miniaturization under the working environment of high temperature, high pressure and oxygen enrichment is met. The measuring rake body 1 adopts an upper lobe structure and a lower lobe structure, one lobe is L-shaped with a windward side, the other lobe is a flat plate type cover plate, the two lobes are buckled and then welded by brazing, argon arc welding is carried out on the leeward side, on one hand, welding seams on the windward side are avoided, and on the other hand, welding connection strength and reliability are enhanced on the back side; to further increase the welding strength, reinforcement pins 18 are arranged on the sides as required. Meanwhile, the windward side of the measuring rake body 1 is set to be the wedge-shaped structure 11 conforming to the supersonic velocity streamline, and the inclination angle beta of the wedge-shaped structure 11 is selected to be 11-25 degrees according to the Mach number range.
As shown in fig. 2 and fig. 3, the measuring rake body 1 is provided with a thermal protection structure, that is, the measuring rake body is provided with a plurality of cooling channels 12, one end of each cooling channel 12 is communicated with a shunt ring groove 13 arranged at the bottom end of the measuring rake body 1, and the other end is communicated with a return ring groove 14 arranged in the middle of the measuring rake body 1; the water inlet pipe 2 is arranged in the measuring rake body 1, the inlet of the water inlet pipe is communicated with external cooling water, and the outlet of the water inlet pipe is communicated with a shunting ring groove 13 arranged at the bottom end of the measuring rake body 1; the water outlet pipe 3 is arranged in the measuring rake body 1, the inlet of the water outlet pipe is communicated with the backflow ring groove 14 arranged in the middle of the measuring rake body 1, and the outlet of the water outlet pipe is positioned outside the measuring rake body 1. The water inlet pipe 2 is inserted into the lee side of the measuring rake body 1, pressurized cooling water is supplied to the bottom end of the measuring rake body 1, the pressurized cooling water turns back through the shunt ring groove 13 to enter each cooling channel 12, and after the measuring rake body 1 is cooled, the pressurized cooling water is gathered to the backflow ring groove 14 and finally discharged through the water outlet pipe 3. The cooling channel 12 can be formed by milling the rake body by a special milling cutter, the pressure and the flow of the introduced cooling water are determined by thermal calculation according to the temperature of the wind tunnel used by the measuring device, and the inlet and the outlet of the cooling water can be arranged on the same end surface outside the mounting flange of the measuring rake body 1. As the measuring rake body 1 is provided with the straight-groove type cooling channel 12 water cooling structure, the measuring rake body has wide temperature application range, can cover high-temperature fuel gas from normal temperature to above 2000K, and meets the long-time working requirement. When the temperature range of the simulated incoming flow is from normal temperature to 650K, cooling water is not allowed to be introduced, the strength requirement is met through the mechanical property of the high-temperature alloy, the cooling water is introduced at the temperature higher than 650K, the inlet and outlet temperatures of the cooling water are automatically recorded, and the pressure of the cooling water is 1.0 MPa-1.5 MPa.
The device adopts the special water-cooling channel 12, selects high-temperature oxidation-resistant materials and other thermal protection technologies, so that the device realizes miniaturization design, the minimum thickness of the windward side of the device is 8-10 mm, the thickness of the rake body is 11-14 mm, and the width of the measuring rake body 1 is designed according to the number of probes, the diameter of a pressure guide pipe and the like and is of an equal-width structure.
As shown in fig. 4, 5 and 6, a plurality of mach number measuring points are arranged on the windward side of the measuring rake body 1 at different radial positions according to the equal area, and each mach number measuring point comprises a first wind hole 15 and a second wind hole 16 which penetrate through the wedge-shaped structure 11; a Mach number measuring point comprises a total temperature probe 9, a total pressure probe 7 and a static pressure probe 8, the total temperature probe 9 is arranged in a second air hole 16, a temperature sensor 6 is arranged in the total temperature probe, the temperature sensor 6 can adopt PT100, at the moment, two symmetrical through holes 19 are arranged on the side wall of the total temperature probe, and the through holes form an outlet for stagnant incoming air; the total pressure probe 7 is arranged in the first air hole 15, one end of the total pressure probe extends out of the wedge-shaped structure 11, the other end of the total pressure probe is connected with the first pressure sensor 4, and a static pressure hole 17 is formed in the pipe wall of the total pressure probe; the static pressure probe 8 is arranged in the total pressure probe 7, one end of the static pressure probe penetrates through the static pressure hole 17, and the other end of the static pressure probe is connected with the second pressure sensor 5. At this moment, static pressure probe 8 and total pressure probe 7 are 90 settings, can set up total pressure probe 7, static pressure probe 8 and total temperature probe 9 and measurement harrow body 1 integration, avoid appearing the welding, and then guaranteed the intensity of measuring the harrow body. According to flow field simulation and test verification, each Mach number measuring point is arranged in principle according to the equal equivalent area, the distance between the total pressure probes 7 of two adjacent Mach number measuring points needs to be not less than 4 times of the diameter d of the total pressure probe 7, and at the moment, shock waves which do not appear or are light are not overlapped and interfered with each other between the total pressure probes 7 under the condition of different Mach numbers (not more than Ma 6). The total pressure probe 7 and the total temperature probe 9 are made of high-temperature alloy material pipes, such as GH202, and the diameter d is generally taken
The distance L2 extending out of the windward side is (0-3) dmm.
As shown in fig. 7, on the windward side of the measurement rake body 1, mach number measurement points are arranged in the radial position in an equal area, at this time, the areas of a1, a2, A3 and a4 are the same, and the heat received by the temperature sensor is the same under the same area.
As shown in fig. 5, the inlet of the total temperature probe 9 is preferably in the shape of a conical bell, and different thermocouples are used for measuring the total temperature in a high temperature environment according to the temperature range to be measured. The area ratio of the inlet to the outlet of the total temperature probe 9 is selected to be 1.5-3, wherein when the area ratio is 2.5, the total temperature recovery coefficient of the total temperature probe 9 under the supersonic (Ma is less than or equal to 6) flow field environment is the highest, and the total temperature recovery can reach more than 98%.
As shown in FIG. 6, the inlet form of the total pressure probe 7 is preferably selected to be a conical bell mouth and a hemisphere, and for the hemisphere-shaped total pressure probe 7, when the flow deflection angle is selected to be alpha less than or equal to 3 degrees, the flow deflection angle is not sensitive to the total pressure value of the total pressure probe 7; for the conical inlet total pressure probe 7, when Ma is less than or equal to 2.5, the conical inlet total pressure probe 7 is insensitive to the flow deflection angle, and when Ma is greater than 2.5, the flow deflection angle has a larger influence on the conical total pressure probe 7.
Based on the structural characteristics, the Mach number measuring device has the following characteristics: firstly, a special milling groove type cooling channel structure and a circular groove flow equalizing structure are adopted, the cooling effect is good, the temperature application range is wide, and the temperature can cover the temperature from normal temperature to more than 2000K; secondly, combining supersonic flow field simulation, and utilizing a streamline wedge-shaped windward side, the range of the covered Mach number is large, and the Mach number is up to more than Ma6 from subsonic velocity to supersonic velocity; thirdly, based on a supersonic flow field simulation model, a measuring point distance selection criterion is established, the interaction of shock wave systems among measuring points in a supersonic flow field environment is weakened or eliminated, and the measuring accuracy is improved; fourthly, through technical approaches such as cooling structure design, select anti-oxidation high temperature alloy material, satisfy intensity requirement under the high temperature environment, realized measuring device's miniaturization, anti-oxidation and long-time the use, windward side thickness is not more than 10mm, and unilateral surplus wall thickness is less than 1.5mm, satisfies intensity requirement under high temperature, high pressure, oxygen boosting environment. The Mach number measuring device of the invention and the size range of the wind tunnel are
It can have a high total pressure recovery coefficient, wherein,
when the diameter of the wind tunnel and the Mach number of 5 groups are measured, the maximum total pressure recovery coefficient reaches 97.6 percent.
Before the measuring device is checked and accepted and used every time, the structural integrity of the measuring device is detected by adopting an airtight and hydraulic test, and a high-mesh filter is arranged in front of the water inlet pipe 2, so that the phenomenon that the inner channel of the measuring device is blocked by impurities in water is avoided. During installation, the connecting flange 11 is connected and fixed with the wind tunnel installation seat, the windward side is opposite to the high-temperature supersonic airflow, and the total temperature, the total pressure and the static pressure of the current place need to be measured at the same time for each Mach number. Wherein the total pressure obtained by the actual measurement of the supersonic flow field is the total pressure p after shock waveten1The total pressure P of the shock wave front is iteratively calculated through the standard wind tunnel calibration of an ultrasonic flow field or through a pneumatic calculation formula of the shock wave front and the shock wave rear0The total pressure P of the shock wave front is calculated by calibration or iteration0And calculating the Mach number. The iterative formula is as follows. Meanwhile, the windward side of the invention adopts the thin wedge-shaped structure 11, so that the shock waves among the measuring points are not overlapped and interfered secondarily, and the interaction of a complex shock wave system is avoided. Therefore, the total pressure P in the shock wave front can be obtained with high accuracy0。
Wherein: p is a radical often1Is total pressure after shock wave, p0Is the total pressure in the shock front and k is the adiabatic index.
The Mach number measuring device under the high-temperature supersonic flow field environment has the following testing process:
1) placing a Mach number measuring device in a high-temperature supersonic flow field environment through a connecting flange, wherein the windward side of the measuring device is opposite to an incoming flow;
2) measuring the total temperature, total pressure and static pressure of the simulated incoming flow of the same section, and calculating to obtain the Mach number of the current place, or measuring and obtaining the Mach numbers of different sections; the local Mach number of the supersonic flow field in a certain airflow environment is obtained through the following calculation formula:
in the formula, P0、PsRespectively representing the total pressure of the local air flow (the total pressure of the shock wave, obtained by the formula (1)) and the static pressure; kappa is the specific heat ratio of the actual gas at the point, and is obtained by iteration according to the local total temperature and the mass fraction of the gas components, and the specific gas is the total temperature T0A function of (a);
3) the Mach number measuring device is connected with the data acquisition system, and is used for measuring, acquiring and recording numerical values of all points simultaneously, so that the change of simulated incoming flow along with time can be obtained, and meanwhile, the uniformity or the unevenness of airflow fields at different radial positions of the same section can be evaluated by comparing the size and the relative error of the Mach number numerical values obtained by different Mach number measuring points.
Claims (10)
1. The utility model provides a mach number measuring device under high temperature supersonic flow field environment which characterized in that: the device comprises a measuring rake body (1), a water inlet pipe (2), a water outlet pipe (3), a first pressure sensor (4), a second pressure sensor (5), a temperature sensor (6) and a plurality of probe components, wherein each probe component comprises a total pressure probe (7), a static pressure probe (8) and a total temperature probe (9) which are all of tubular structures;
the measuring rake body (1) is made of high-temperature alloy with high oxidation resistance and high-temperature mechanical property, the windward side of the measuring rake body is set to be a wedge-shaped structure (11), and the inclination angle of the wedge-shaped structure (11) is 11-25 degrees;
a plurality of cooling channels (12) are arranged in the measuring rake body (11), one end of each cooling channel (12) is communicated with a shunting ring groove (13) arranged at the bottom end of the measuring rake body (1), and the other end of each cooling channel is communicated with a backflow ring groove (14) arranged in the middle of the measuring rake body (1);
the water inlet pipe (2) is arranged in the measuring rake body (1), the inlet of the water inlet pipe is communicated with external cooling water, and the outlet of the water inlet pipe is communicated with a shunting ring groove (13) arranged at the bottom end of the measuring rake body (1);
the water outlet pipe (3) is arranged in the measuring rake body (1), the inlet of the water outlet pipe is communicated with a backflow ring groove (14) arranged in the middle of the measuring rake body (1), and the outlet of the water outlet pipe is positioned outside the measuring rake body (1);
a plurality of Mach number measuring points which are arranged in an equal area are arranged on the windward side of the measuring rake body (1), the distance between every two adjacent Mach number measuring points is more than or equal to 4 times the diameter of the total pressure probe (7), and each Mach number measuring point comprises a first air hole (15) and a second air hole (16) which penetrate through the wedge-shaped structure (11);
the total temperature probe (9) is arranged in the second air hole (16), and a temperature sensor (6) is arranged in the total temperature probe;
the total pressure probe (7) is arranged in the first air hole (15), one end of the total pressure probe extends out of the wedge-shaped structure (11), the other end of the total pressure probe is connected with the first pressure sensor (4), and a static pressure hole (17) is formed in the pipe wall of the total pressure probe;
the static pressure probe (8) is arranged in the total pressure probe (7), one end of the static pressure probe penetrates through the static pressure hole (17), and the other end of the static pressure probe is connected with the second pressure sensor (5).
2. The mach number measuring device in the high-temperature supersonic flow field environment according to claim 1, characterized in that: the inlet of the total pressure probe (7) is a conical horn mouth or a hemisphere shape.
3. A mach number measuring device in a high-temperature supersonic flow field environment according to claim 2, characterized in that: the inlet of the total temperature probe (9) is a conical horn mouth, and the area ratio of the inlet to the outlet is 1.5-3.
4. A Mach number measuring device in a hypersonic flow field environment according to claim 1, 2 or 3, characterized in that: the total pressure probe (7), the static pressure probe (8) and the total temperature probe (9) are integrated with the measuring rake body (1).
5. A Mach number measuring device in a high-temperature supersonic flow field environment according to claim 4, characterized in that: the temperature sensor (6) is PT100, and two symmetrical through holes (19) are formed in the side wall of the total temperature probe (9).
6. A Mach number measuring device in a high-temperature supersonic flow field environment according to claim 5, characterized in that: GH202 is selected as the material of the measuring rake body (1).
7. A Mach number measuring device in a high-temperature supersonic flow field environment according to claim 6, characterized in that: the measuring rake body (1) is connected with the wind tunnel mounting seat through a connecting flange (10) arranged on the outer side of the measuring rake body.
8. A Mach number measuring device in a high-temperature supersonic flow field environment according to claim 7, characterized in that: the side surface of the measuring rake body (1) is provided with a reinforcing pin (18) for improving the strength of the measuring rake body (1).
9. A Mach number measuring device in a high-temperature supersonic flow field environment according to claim 8, characterized in that: the total pressure probe (7), the static pressure probe (8) and the total temperature probe (9) are made of high-temperature alloy materials.
10. A mach number measuring apparatus in a pyrometric supersonic flow field environment according to claim 9, characterized in that: and a high-mesh filter is arranged at the inlet of the water inlet pipe (2).
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| CN115371999A (en) * | 2022-10-24 | 2022-11-22 | 中国航发四川燃气涡轮研究院 | Inlet flow field parameter measuring device in high-temperature and high-pressure test |
| CN115371999B (en) * | 2022-10-24 | 2023-03-24 | 中国航发四川燃气涡轮研究院 | Inlet flow field parameter measuring device in high-temperature and high-pressure test |
| CN116124414A (en) * | 2023-04-12 | 2023-05-16 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Probe for measuring static pressure fluctuation |
| CN116124414B (en) * | 2023-04-12 | 2023-06-09 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Probe for measuring static pressure fluctuation |
| CN116147882A (en) * | 2023-04-23 | 2023-05-23 | 中国航空工业集团公司哈尔滨空气动力研究所 | Low-speed wind tunnel flow field parameter measuring device and method |
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