CN114136647B - Supersonic high-temperature three-dimensional flow field measuring device - Google Patents
Supersonic high-temperature three-dimensional flow field measuring device Download PDFInfo
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- CN114136647B CN114136647B CN202111223559.7A CN202111223559A CN114136647B CN 114136647 B CN114136647 B CN 114136647B CN 202111223559 A CN202111223559 A CN 202111223559A CN 114136647 B CN114136647 B CN 114136647B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
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Abstract
The invention provides a supersonic high-temperature three-dimensional flow field measuring device, which comprises a sensing mechanism for measuring flow field characteristics and a displacement mechanism for adjusting the position of the sensing mechanism in a flow field, wherein the sensing mechanism is arranged on the flow field; the sensing mechanism comprises a rear supporting plate and a front flow guide plate for guiding a flow field, a cavity is formed between the rear supporting plate and the front flow guide plate, a plurality of probes are installed in the cavity, each probe comprises a temperature sensing probe, a pressure sensing probe and a three-dimensional flow field measuring probe, and the rear supporting plate and the front flow guide plate are connected with the displacement mechanism through a connecting plate. According to the invention, the sensing part adopts the design of the replacement positioning interface between the three-dimensional speed measuring probes and the front guide plate, so that each three-dimensional speed measuring probe can be used as an independent unit module to carry out a three-dimensional flow field aerodynamic characteristic test on a small-sized calibration wind tunnel, the cost of the calibration test is effectively reduced under the condition of ensuring the overall characteristic of the measuring device, and the calibration test is convenient and easy to operate.
Description
Technical Field
The invention belongs to the field of measurement, and in particular relates to a supersonic high-temperature three-dimensional flow field measurement device
Background
The high-temperature gas temperature field, the pressure field, the speed field and the static pressure field measurement data of the jet pipe outlet of the aero-engine can be used for analyzing and evaluating performance parameters such as a supersonic jet pipe, a vector jet pipe flow characteristic, a thrust characteristic, an effective vector angle and the like, can also be used for calculating the thrust of the engine, and can be compared with the thrust measured by a test bench to improve the reliability of the thrust measurement. Because the jet pipe outlet of the aeroengine is high-temperature high-speed fuel gas flow, the jet pipe outlet flow field measurement area is large, the requirements on the thermal shock resistance and vibration resistance of the measurement device are very high, and the disturbance influence of the measurement device on the flow field is required to be small. The measurement mode adopted at present for the whole aeroengine performance test research is that a plurality of fixed sensing parts are arranged at the inlet of a spray pipe, the sensing parts are not arranged at the outlet of the spray pipe or a small number of sensing parts are fixedly arranged at the outlet of the spray pipe, and the quantity of the measuring points at the inlet and the outlet of the spray pipe is limited; the nozzle inlet and outlet performance parameters obtained through the aero-engine test are limited. Aeroengine thrust testing is generally directly measured by adopting a test bench thrust measuring device, and the accuracy of the thrust direct testing is affected due to the fact that a small number of pipelines of the engine are associated with the test bench. The development of the three-dimensional flow field test of the nozzle outlet can provide test technical support for the performance analysis and the thrust auxiliary calculation of the whole nozzle of the aeroengine.
Disclosure of Invention
In order to solve the problems, the invention provides the measuring device which has reliable use strength, multiple measuring point types, wide measuring point distribution area, convenient installation and disassembly, small disturbance to the supersonic flow field, high measuring precision and good economic benefit under the gas environment with thermal shock and high aerodynamic load.
The invention aims to provide a supersonic high-temperature three-dimensional flow field measuring device, which comprises a sensing mechanism for measuring flow field characteristics and a displacement mechanism for adjusting the position of the sensing mechanism in a flow field; the sensing mechanism comprises a rear supporting plate and a front flow guide plate for guiding a flow field, a cavity is formed between the rear supporting plate and the front flow guide plate, a plurality of probes are installed in the cavity, each probe comprises a temperature sensing probe, a pressure sensing probe and a three-dimensional flow field measuring probe, and the rear supporting plate and the front flow guide plate are connected with the displacement mechanism through a connecting plate.
The supersonic high-temperature three-dimensional flow field measuring device provided by the invention has the characteristics that the rear supporting plate is of a U-shaped structure, and the grooves of the U-shaped structure are used for cooling water to pass through.
The supersonic high-temperature three-dimensional flow field measuring device provided by the invention is also characterized in that the front guide plate is of a wedge structure, and the ratio of the width of the windward side of the wedge structure to the axial length is 0.3-0.5.
The supersonic high-temperature three-dimensional flow field measuring device provided by the invention is characterized in that the temperature sensing probe comprises a shielding cover fixed on the front guide plate, a supporting pipe arranged in the shielding cover, a thermocouple and a filling agent, wherein the shielding cover stretches into the cavity, the thermocouple is arranged in the supporting pipe, and the filling agent is used for fixing the supporting pipe in the shielding cover.
The supersonic high-temperature three-dimensional flow field measuring device provided by the invention is further characterized in that an air inlet hole is formed in the end part of the shielding cover, air leakage holes are formed in the two sides of the head part of the shielding cover, the area ratio of the air inlet hole to the air leakage holes is 1.2-1.5, the diameter of the head part of the shielding cover is not more than 6mm, the diameter of the rear end of the shielding cover is not more than 12mm, a transition section is arranged between the head part of the shielding cover and the rear end of the shielding cover, the transition section is a conical surface of 30-45 degrees, and the rear end of the shielding cover is arranged in the cavity.
The supersonic high-temperature three-dimensional flow field measuring device provided by the invention has the characteristics that the thermocouple is Gao Wenou wire resistant, the diameter of the thermocouple is not smaller than 0.5mm, the length-diameter ratio of a temperature sensing section of the thermocouple extending out of the supporting tube is not smaller than 8, and the temperature sensing node of the thermocouple is spherical.
The supersonic high-temperature three-dimensional flow field measuring device provided by the invention also has the characteristics that the diameter of the pressure sensing probe is not more than 8mm; the three-dimensional flow field measuring probe comprises a sensed section with a conical structure and a positioning block used for positioning on the front guide plate, wherein a total pressure hole is formed in the axis position of the sensed section, four pressure sensing holes are uniformly distributed in the circumferential direction of the total pressure hole, and the total pressure hole is parallel to the opening direction of the pressure sensing holes.
The supersonic high-temperature three-dimensional flow field measuring device provided by the invention is further characterized in that the connecting plate comprises a first connecting plate in welded connection with the front guide plate and the supporting plate and a second connecting plate in clearance fit with the front guide plate and the supporting plate.
The supersonic high-temperature three-dimensional flow field measuring device provided by the invention is further characterized in that the first connecting plate and the second connecting plate are respectively connected with the displacement mechanism, the diameter of a first installation through hole connected with the displacement mechanism is larger than 1mm of the diameter of a first bolt matched with the first installation through hole, and the diameter of a second installation through hole connected with the displacement mechanism is larger than 4mm of the diameter of a second bolt matched with the second installation through hole.
The supersonic high-temperature three-dimensional flow field measuring device provided by the invention also has the characteristic that the displacement mechanism is a three-coordinate displacement mechanism.
Compared with the prior art, the invention has the following beneficial effects
According to the invention, the sensing part adopts the design of the replacement positioning interface between the three-dimensional speed measuring probes and the front guide plate, so that each three-dimensional speed measuring probe can be used as an independent unit module to carry out a three-dimensional flow field aerodynamic characteristic test on a small-sized calibration wind tunnel, the cost of the calibration test is effectively reduced under the condition of ensuring the overall characteristic of the measuring device, and the calibration test is convenient and easy to operate.
The sensing part is fixedly provided with the double-fulcrum mounting structure, the main body is provided with the water cooling structure, and the device is simple and convenient to mount and dismount, reliable in structural strength and high in economic benefit.
The invention has the advantages of multiple measuring point types, multiple measuring point numbers and wide measuring point distribution areas, can obtain test data of a large number of measuring points in supersonic speed high Wen Liuchang in a short time by matching with the auxiliary control device, greatly reduces the influence of the measuring device on a flow field, meets the requirements of test and test specifications on measuring precision, can obtain a three-dimensional total temperature field, a total pressure field, a speed field (containing vector angle) and a static pressure field of fuel gas at the outlet of the engine jet pipe, and lays a technical foundation for the performance evaluation and the accurate thrust evaluation of the jet pipe of the aeroengine.
Description of the drawings:
in order to more clearly illustrate the technical solutions of the present invention, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and that other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of a supersonic high-temperature three-dimensional flow field measurement device provided by the invention;
FIG. 2 is a schematic diagram of a sensing mechanism according to the present invention;
FIG. 3 is a partial cross-sectional view of a sensing mechanism according to the present invention,
wherein, 1: a temperature-sensitive section; 2: a pressure-sensitive section; 3: a direction-sensitive section; 4: a front baffle; 5: a rear support plate; 6: a connecting plate; 7: a pressure joint; 8: a cooling water joint; 9: a temperature tail end; 10: a first soft state pressure transmission tube; 11: a second soft state pressure transmission tube; 12: a thermocouple; 13: a support tube; 14: a filler; 15: reinforcing the supporting ribs; 16: a displacement mechanism; 17: and a shielding case.
Detailed Description
In order to make the technical means, the creation characteristics, the achievement of the purposes and the effects of the present invention easy to understand, the following embodiments specifically describe the measurement device provided by the present invention with reference to the accompanying drawings.
In the description of the embodiments of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the drawings, are merely for convenience in describing the present invention and simplify the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the invention.
Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first", "a second", etc. may explicitly or implicitly include one or more such feature. In the description of the invention, unless otherwise indicated, the meaning of "a plurality" is two or more. The terms "mounted," "connected," "coupled," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the creation of the present invention can be understood by those of ordinary skill in the art in a specific case.
As shown in fig. 1-3, a supersonic high temperature three-dimensional flow field measurement device is provided, the measurement device comprising a sensing mechanism for measuring flow field characteristics and a displacement mechanism 16 for adjusting the position of the sensing mechanism in the flow field; the sensing mechanism comprises a rear supporting plate 5 and a front guide plate 4 for guiding a flow field, a cavity is formed between the rear supporting plate 5 and the front guide plate 4, a plurality of probes are installed in the cavity, each probe comprises a temperature sensing probe, a pressure sensing probe and a three-dimensional flow field measuring probe, and the rear supporting plate 5 and the front guide plate 4 are connected with the displacement mechanism 16 through a connecting plate 6. Meanwhile, the supersonic total temperature, total pressure, static pressure, speed and direction test is concentrated on the same sensing part, so that the blocking area is reduced; the displacement mechanism drives the sensing part to measure in cooperation with the auxiliary control system, so that the density of the measuring points in the measured section can be adjusted in a short time.
In some embodiments, the rear support plate 5 has a U-shaped structure, and grooves of the U-shaped structure are used for the passage of cooling water. The sensing part adopts a water cooling mode, the main body material adopts a stainless steel material, the processing cost is low, and the processing technology is simple; the sensing part adopts a large-span double-fulcrum mounting structure, and the adapter plates at the two ends of the sensing part are in flange connection with the mounting interface of the displacement mechanism.
In some embodiments, the front baffle 4 is a wedge structure, and a ratio of a width of a windward side to an axial length of the wedge structure is 0.3-0.5. The front deflector 4 is provided with a positioning groove matched with the positioning block. This configuration effectively reduces drag effects in supersonic airflow.
In some embodiments, the temperature sensing probe comprises a shielding cover 17 fixed on the front guide plate, a supporting tube 13 arranged in the shielding cover 17, a thermocouple 12 and a filling agent 14, wherein the supporting tube 13 extends into the cavity, the thermocouple 12 is arranged in the supporting tube 13, and the filling agent 14 fixes the supporting tube 13 in the shielding cover 17. The supporting tube 13 is made of high temperature resistant insulating material, and the filler 14 is made of high temperature resistant material.
In some embodiments, an air inlet hole is formed at the end of the shielding cover 17, air leakage holes are formed at two sides of the head of the shielding cover 17, the area ratio of the air inlet hole to the air leakage holes is 1.2-1.5, the diameter of the head of the shielding cover 17 is not greater than 6mm, the diameter of the rear end of the shielding cover 17 is not greater than 12mm, a transition section is arranged between the head of the shielding cover 17 and the rear end, the transition section is a conical surface of 30-45 degrees, and the rear end of the shielding cover 17 is arranged in the cavity.
In some embodiments, the thermocouple is a Gao Wenou wire, the diameter of the thermocouple is not smaller than 0.5mm, the length-diameter ratio of a temperature sensing section of the thermocouple extending out of the supporting tube is not smaller than 8, and the temperature sensing node of the thermocouple is spherical. The rear end of the thermocouple is connected with the acquisition system after being led out of the cavity. The front end of the temperature-sensitive section 1 is provided with an air inlet hole, the side surface is provided with two air discharge holes, the air inlet and air discharge area ratio is 1.2-1.5, the influence caused by the air flow speed contacted by the thermocouple wire temperature-sensitive section is reduced, and the direct temperature measurement error is reduced; the external dimension of the head part of the temperature-sensitive section 1 is no more than 6mm, the external dimension of the rear end is no more than 12mm, the transition section adopts a conical surface of 30-45 degrees, and the disturbance to a flow field is reduced under the condition of ensuring the strength of the temperature-sensitive probe; the support tube 13 and the filler 14 insulate and fix the bare coupling wire; the outside of the shielding cover 17 is directly contacted with cooling water to reduce the temperature of the temperature sensing probe; the overall structural design of the temperature sensing probe enhances the vibration resistance of the temperature sensing probe in a high-temperature high-pneumatic load airflow environment.
In some embodiments, the pressure sensing probe has a diameter no greater than 8mm; the three-dimensional flow field measuring probe comprises a sensed section with a conical structure and a positioning block used for positioning on the front guide plate, wherein a total pressure hole is formed in the axis position of the sensed section, four pressure sensing holes are uniformly distributed in the circumferential direction of the total pressure hole, and the total pressure hole is parallel to the opening direction of the pressure sensing holes.
In some embodiments, the connection plate 6 includes a first connection plate welded to the front baffle 4 and the rear support plate 5, and a second connection plate in clearance fit with the front baffle 4 and the rear support plate 5.
In some embodiments, the first connection plate and the second connection plate are respectively connected with the displacement mechanism 16, a diameter of a first installation through hole of the first connection plate connected with the displacement mechanism 16 is larger than 1mm of a first bolt through diameter matched with the first installation through hole, and a diameter of a second installation through hole of the second connection plate connected with the displacement mechanism 16 is larger than 4mm of a second bolt through diameter matched with the second installation through hole. The structural design ensures that the strength of the measuring device in the high-temperature supersonic gas flow field at the outlet of the jet pipe of the aero-engine is reliable.
In some embodiments, the sizes of pressure transmission channels in the pressure sensing probe and the three-dimensional flow field measuring probe are not less than 1.5mm, and the large-aperture pressure transmission pipe prevents foreign matters from blocking the pressure transmission pipe; the appearance of the corresponding pressure sensing probe head is designed to be no more than 8mm, the appearance size of the three-dimensional flow field measuring probe head is 8 no more than mm, the head of the five-hole direction sensing section is a 60-degree cone, the middle is a total pressure sensing hole, 4 pressure sensing holes are uniformly distributed in the circumferential direction of the cone section, the opening direction of the pressure sensing hole is parallel to the total pressure hole, the head of the pressure sensing section 2 adopts a circular tube form, and the pneumatic characteristics of each measuring probe are effectively ensured. The three-dimensional flow field measuring probe is used as an independent unit module to assist in carrying out pneumatic characteristic test on a small wind tunnel independently by using a clamp, so as to obtain total pressure, static pressure and direction characteristic data of each three-dimensional flow field measuring probe, and then carrying out measurement deviation correction on the test data, so as to obtain total pressure, static pressure and direction characteristics after assembly, and the calibration test is simple and low in cost on the premise that the measurement precision meets the test requirement; the pressure sensing probe and the three-dimensional flow field measuring probe are designed to be in direct contact with cooling water to reduce the temperature; the overall structural design of the pressure sensing probe and the three-dimensional flow field measuring probe enhances the vibration resistance of the pressure sensing probe and the three-dimensional flow field measuring probe in a high-temperature high-aerodynamic load airflow environment.
In some embodiments, the displacement mechanism 16 is a three-coordinate displacement mechanism.
In some embodiments, the pressure sensing probe is connected with a first soft state pressure transmission tube 10, the three-dimensional flow field measurement probe is connected with a second soft state pressure transmission tube 11, and the first soft state pressure transmission tube 10 and the second soft state pressure transmission tube 11 are used for transmitting pressure; and a reinforcing support rib 15 for reinforcing structural strength is arranged between the front guide plate 4 and the rear support plate 5.
The present invention is not limited to the above-mentioned embodiments, and any changes or substitutions that can be easily understood by those skilled in the art within the technical scope of the present invention are intended to be included in the scope of the present invention. Therefore, the protection scope of the invention is subject to the protection scope of the claims.
Claims (8)
1. The supersonic high-temperature three-dimensional flow field measuring device is characterized by comprising a sensing mechanism for measuring flow field characteristics and a displacement mechanism for adjusting the position of the sensing mechanism in a flow field; the sensing mechanism comprises a rear supporting plate and a front flow guide plate for guiding a flow field, a cavity is formed between the rear supporting plate and the front flow guide plate, a plurality of probes are arranged in the cavity and comprise a temperature sensing probe, a pressure sensing probe and a three-dimensional flow field measuring probe, the rear supporting plate and the front flow guide plate are connected with the displacement mechanism through a connecting plate,
the diameter of the pressure sensing probe is not more than 8mm; the three-dimensional flow field measuring probe comprises a sensed section with a conical structure and a positioning block used for positioning on the front guide plate, wherein the axial center position of the sensed section is provided with a total pressure hole, four pressure sensing holes are uniformly distributed in the circumferential direction of the total pressure hole, the directions of the total pressure hole and the opening of the pressure sensing hole are parallel,
the connecting plate comprises a first connecting plate and a second connecting plate, wherein the first connecting plate is in welded connection with the front guide plate and the supporting plate, and the second connecting plate is in clearance fit with the front guide plate and the supporting plate.
2. The ultrasonic high temperature three-dimensional flow field measurement device according to claim 1, wherein the rear support plate is of a U-shaped structure, and grooves of the U-shaped structure are used for the passage of cooling water.
3. The ultrasonic high-temperature three-dimensional flow field measurement device according to claim 1, wherein the front flow guide plate is of a wedge structure, and the ratio of the width of a windward side of the wedge structure to the axial length is 0.3-0.5.
4. The ultrasonic high temperature three-dimensional flow field measurement device according to claim 1, wherein the temperature sensing probe comprises a shielding cover fixed on the front deflector, a supporting pipe arranged in the shielding cover, a thermocouple and a filler, the shielding cover extends into the cavity, the thermocouple is arranged in the supporting pipe, and the filler fixes the supporting pipe in the shielding cover.
5. The supersonic high-temperature three-dimensional flow field measurement device according to claim 4, wherein an air inlet hole is formed in the end portion of the shielding case, air leakage holes are formed in two sides of the head portion of the shielding case, the area ratio of the air inlet hole to the air leakage holes is 1.2-1.5, the diameter of the head portion of the shielding case is not more than 6mm, the diameter of the rear end of the shielding case is not more than 12mm, a transition section is arranged between the head portion of the shielding case and the rear end of the shielding case, the transition section is a conical surface of 30-45 degrees, and the rear end of the shielding case is arranged in the cavity.
6. The ultrasonic high-temperature three-dimensional flow field measurement device according to claim 4, wherein the thermocouple is Gao Wenou wire, the diameter of the thermocouple is not less than 0.5mm, the length-diameter ratio of a temperature sensing section of the thermocouple extending out of the supporting tube is not less than 8, and the temperature sensing node of the thermocouple is spherical.
7. The ultrasonic high-temperature three-dimensional flow field measurement device according to claim 1, wherein the first connecting plate and the second connecting plate are respectively connected with the displacement mechanism, the diameter of a first installation through hole of the first connecting plate connected with the displacement mechanism is larger than 1mm of a first bolt through diameter matched with the first installation through hole, and the diameter of a second installation through hole of the second connecting plate connected with the displacement mechanism is larger than 4mm of a second bolt through diameter matched with the second installation through hole.
8. The ultrasonic high temperature three-dimensional flow field measurement device of claim 1, wherein the displacement mechanism is a three-dimensional displacement mechanism.
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| CN114518212B (en) * | 2022-04-20 | 2022-06-28 | 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 | Simple device for realizing large-range flow field displacement measurement in limited space |
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