CN113551869A - Probe for measuring two-dimensional dynamic boundary layer of rotating-static end wall of multistage gas compressor - Google Patents
Probe for measuring two-dimensional dynamic boundary layer of rotating-static end wall of multistage gas compressor Download PDFInfo
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- CN113551869A CN113551869A CN202110829779.8A CN202110829779A CN113551869A CN 113551869 A CN113551869 A CN 113551869A CN 202110829779 A CN202110829779 A CN 202110829779A CN 113551869 A CN113551869 A CN 113551869A
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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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- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D21/00—Measuring or testing not otherwise provided for
- G01D21/02—Measuring two or more variables by means not covered by a single other subclass
Abstract
The invention belongs to the technical field of subsonic two-dimensional flow field parameter testing, and particularly relates to a probe for measuring a two-dimensional dynamic boundary layer of an end wall between rotating and static phases of a multistage compressor. The probe comprises a probe head, a supporting rod, a dynamic pressure sensor and a positioning block, wherein the probe head comprises a cylinder and a twisted pair body which share the bottom surface, the dynamic pressure sensor is packaged in the probe head, a pressure sensing hole is formed in the side surface of the cylinder at the probe head and is communicated with the dynamic pressure sensor packaged in the probe head, a sensor cable leads out the probe tail through a channel in the probe supporting rod, and the positioning block is sleeved at the probe tail. The method can measure the dynamic change of two-dimensional flow field parameters in the boundary layer of the end wall between the rotating and static phases of the multistage compressor through calibration of the wind tunnel, wherein the flow field parameters comprise an airflow deflection angle, total pressure, static pressure and Mach number, and actual measurement data basis is provided for improving the performance of the compressor. Compared with other probes with surface layers, the probe head adopts a twisted-pair wire rotating body structure, is I-shaped, has small vertical distance between the circle center of the pressure sensing hole and the lowest point of the probe head, has the advantages of self-contained positioning function, small size, high spatial resolution, capability of being inserted into a multi-stage compressor rotating and static chamber for measurement, small interference on a measured flow field, high measurement precision and multi-parameter dynamic measurement.
Description
Technical Field
The invention belongs to the technical field of subsonic two-dimensional flow field parameter testing, and particularly relates to a probe for measuring a two-dimensional dynamic boundary layer of an end wall between a rotor and a stator of a multistage gas compressor, which is suitable for measuring dynamic changes of two-dimensional flow field parameters in the boundary layer of the end wall between the rotor and the stator of the multistage gas compressor, wherein the flow field parameters comprise an airflow deflection angle, total pressure, static pressure and Mach number.
Background
The method has the advantages that the two-dimensional flow field parameters of the boundary layer of the end wall of the rotating and static space of the multistage gas compressor are obtained, and the method has an important effect on improving the performance of the gas compressor. The end wall boundary layer of the rotor-stator space of the multi-stage compressor comprises a casing boundary layer and a hub boundary layer, and for the test of two-dimensional flow field parameters inside the casing/hub boundary layer of the rotor-stator space of the compressor, the flow field has strong unsteady property and rotational property because the boundary layer flow field is influenced by the sweep of the wake of the movable blades, the leakage vortex, the angular vortex and other secondary flows; in addition, the rotating and static gaps of the multistage compressor are relatively small, and particularly the rotating and static gaps of the later stage are smaller; therefore, the test of the boundary layer flow field has the measurement difficulties of large airflow deflection angle, thin boundary layer thickness, narrow measurement space and the like.
At present, the measurement aiming at the parameters of the laminar flow field of the boundary surface can be divided into a contact measurement method and a non-contact measurement method.
The contact measurement mainly adopts the measurement methods of a boundary layer probe, a hot wire, a dynamic wall static pressure sensor and the like. In the conventional boundary layer probe, the head part of the probe is L-shaped, so that the probe cannot be inserted between a rotor and a stator of a gas compressor for measurement, and the boundary layer probe has a very large volume effect, so that only a steady state total pressure value of a measuring point can be obtained, and dynamic changes of an airflow deflection angle, static pressure and Mach number cannot be measured; according to the insensitivity of the boundary layer probe to the airflow direction, when the deflection angle of the flow field is large, the boundary layer probe cannot obtain an accurate total pressure value. When a hot wire probe is adopted to measure a boundary layer flow field, dynamic speed signals of a one-dimensional flow field can be usually measured, and dynamic parameter information of an airflow deflection angle, total pressure, static pressure and Mach number cannot be provided. The dynamic wall static pressure sensor can be arranged on the surface of a casing to measure the dynamic static pressure of a casing boundary layer, the installation of the sensor on the surface of the hub is limited due to the rotation of the hub, the measurement of the dynamic static pressure of the hub boundary layer is very difficult, and the dynamic wall static pressure sensor cannot measure the airflow deflection angle, the total pressure and the Mach number.
The non-contact measurement mainly comprises measurement methods such as a Particle Image Velocimetry (PIV) technology, a Laser Doppler Velocimetry (LDV) technology, a Phase Doppler Particle Analyzer (PDPA) and Pressure Sensitive Paint (PSP), wherein the PIV/LDV/PDPA can not interfere with a flow field and is commonly used for measuring the flow field speed, but the problems of wall surface reflection, low particle concentration and the like exist in the process of measuring the flow field speed of the boundary layer, accurate boundary layer speed field data cannot be obtained, and the measurement methods can not provide dynamic change information of total pressure and static pressure. Pressure Sensitive Paint (PSP) can obtain a distribution cloud chart of dynamic static pressure of a wall surface by utilizing the sensitivity of pressure sensitive paint to pressure, and can reflect the dynamic change of the static pressure in an end wall boundary layer, but the PSP is a macroscopic measurement method, cannot obtain an accurate static pressure value, and cannot obtain dynamic information of an airflow deflection angle, total pressure and Mach number at the same time.
For the measurement of two-dimensional flow field parameters of an end wall boundary layer in a compressor test, it is more desirable to obtain dynamic information of an airflow deflection angle, total pressure, static pressure and Mach number of a flow field in the end wall boundary layer during the test, and the dynamic information is used for verifying the compressor design and flow field diagnosis so as to improve the machine performance, but the measurement methods cannot meet the current test requirements.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the invention provides a probe for measuring the dynamic changes of an airflow deflection angle, total pressure, static pressure and Mach number in a two-dimensional flow field of an end wall boundary layer of a rotating and static chamber of a multi-stage compressor. The invention is suitable for measuring the dynamic changes of the airflow deflection angle, the total pressure, the static pressure and the Mach number in the two-dimensional flow field in the boundary layer of the end wall between the rotating and static phases of the multistage compressor.
The technical solution of the invention is as follows:
1. the utility model provides a measure multistage compressor and change quiet interior end wall two-dimentional developments boundary layer probe, by probe head (1), branch (2), dynamic pressure sensor (6), locating piece (8) constitute, its characterized in that: the probe head (1) is a cylinder (3) and a double-twisted-line rotating body (4) which share the same bottom surface, the joint of the cylinder (3) and the double-twisted-line rotating body (4) is in smooth curved surface transition, and a dynamic pressure sensor (6) is packaged in the probe head (1); a pressure sensing hole (5) is formed in the side face of a cylinder (3) of the probe head (1) and is a positive hole (5), and the positive hole (5) is communicated with a dynamic pressure sensor (6) packaged in the probe head (1); the central line of the positive hole (5) and the axis of the cylinder (3) of the probe head (1) are on the same plane, and the axis of the cylinder (3) of the probe head (1) and the axis of the probe supporting rod (2) are superposed.
2. Furthermore, the diameter of the cylinder (3) at the head part (1) of the probe is d, the range of d is more than or equal to 1.5 mm and less than or equal to 2.3 mm, and the length is 4d to 8 d.
3. Further, the rotating body (4) is formed by rotating an AB curve section on a lemniscate around a shaft L, a point A is an intersection point of the lemniscate, a tangent of a point B is perpendicular to a tangent of the point A, and the rotating shaft L passes through the point A and is perpendicular to the tangent of the point A.
4. Furthermore, the diameter of the positive hole (5) is 0.2 mm to 0.4 mm, the vertical distance between the center of the positive hole (5) and the lowest point of the surface of the rotating body (4) is h, and the value range of h is more than or equal to 0.29d and less than or equal to 0.6 d.
5. Furthermore, the probe supporting rod (2) is a cylinder, the diameter of the probe supporting rod is D, the value range of D is more than or equal to 4 mm and less than or equal to 10 mm, a circular pipeline is arranged in the probe supporting rod, a cable (7) of the dynamic pressure sensor packaged in the probe head part (1) is led out of the tail part of the probe through the pipeline in the probe supporting rod (2), and the tail part of the probe is sleeved with a positioning block (8);
6. furthermore, locating piece (8) structure as an organic whole contains cuboid base (9), cylinder boss (10), through-hole (11), screw hole (12), through-hole (11) suit in probe branch afterbody, passes boss (10) both sides screw hole (12) by countersunk screw (13) and fixes, and countersunk screw (13) are whole to be embedded in screw hole (12).
7. Further, cuboid base (9) contains four rectangle sides and two square bottom surfaces, two adjacent sides mutually perpendicular in four sides, four sides all can regard as the locating surface, a bottom surface is connected with cylinder boss (10) in base (9), the plumb line and boss (10) axis coincidence of bottom surface, boss (10) axis and through-hole (11) central line coincidence, the through-hole diameter is D +0.05 millimeter, the boss external diameter is M, the value range is D +2 millimeters and is less than or equal to M and is less than or equal to D +5 millimeters, base (9) bottom surface length of side is M to M +3 millimeters, base (9) thickness is H, the value range is 2 millimeters and is less than or equal to H and is less than or equal to 5 millimeters.
The invention has the beneficial effects that:
compared with other probes with boundary layers, the probe for measuring the two-dimensional dynamic boundary layer of the end wall between the rotating chamber and the static chamber of the multistage gas compressor has the following beneficial effects:
the beneficial effects are that: the head of the probe adopts a double-twisted-wire rotating body structure, and the dynamic pressure sensor can be installed closer to the pressure sensing hole, so that the volume of a cavity between the pressure sensing hole and the sensor is greatly reduced, the cavity effect is reduced, the frequency response of the probe is improved, and dynamic parameters of a flow field can be measured; the vertical distance between the circle center of the pressure sensing hole and the lowest point of the surface of the double-twisted-line rotating body is small, and the measurement of two-dimensional flow field parameters in the boundary layer of the end wall can be realized, wherein the parameters comprise an airflow deflection angle, total pressure, static pressure and Mach number; the probe head is I-shaped and small in size, on one hand, the probe can be inserted into a multi-stage compressor static transfer chamber for measurement, interference on a measured flow field is small, and on the other hand, the probe has high spatial resolution.
The beneficial effects are that: the double-twisted-line rotating body is in smooth curved surface transition with the cylinder at the head of the probe, when airflow flows through the surface of the double-twisted-line rotating body, the special structure of the double-twisted-line rotating body can inhibit the airflow separation of the airflow on the surface of the airflow, and the interference of the streaming around the head of the support rod on the flow field in the boundary layer is weakened; in addition, when the flow field parameters are measured close to the end wall, the invention can inhibit the scale of the horseshoe vortex at the front end of the probe head and improve the measurement precision.
The beneficial effects are three: the positioning block adopted by the invention has small size, the influence on the probe is small in the measuring process, and because four side surfaces of the positioning block can be used as positioning surfaces and can be replaced mutually, the positioning process is simple and convenient, and the positioning method is more suitable for practical engineering application.
Drawings
Fig. 1 is a schematic structural view of the present invention.
FIG. 2 is a lemniscate revolution generation process.
Fig. 3 is a right side view of fig. 1.
Fig. 4 is a partially enlarged view of fig. 3.
Fig. 5 is a top view of fig. 3.
FIG. 6 is a test layout of probes.
Wherein: 1-probe head, 2-probe support rod, 3-cylinder, 4-lemniscate spinning body, 5-positive hole, 6-dynamic pressure sensor, 7-cable of dynamic pressure sensor, 8-positioning block, 9-cuboid base, 10-cylinder boss, 11-through hole, 12-threaded hole, 13-countersunk screw, 14-casing, 15-rotor, 16-stator and 17-hub.
Detailed Description
The invention is described in detail below with reference to the figures and specific embodiments.
As shown in fig. 1, the embodiment introduces a probe for measuring a two-dimensional dynamic boundary layer of an end wall of a rotating chamber and a static chamber of a multi-stage compressor, which is composed of a probe head (1), a support rod (2), a dynamic pressure sensor (6) and a positioning block (8), and is characterized in that: the probe head (1) is a cylinder (3) and a double-twisted-line rotating body (4) which share the same bottom surface, the joint of the cylinder (3) and the double-twisted-line rotating body (4) is in smooth curved surface transition, and a dynamic pressure sensor (6) is packaged in the probe head (1); a pressure sensing hole (5) is formed in the side face of a cylinder (3) of the probe head (1) and is a positive hole (5), and the positive hole (5) is communicated with a dynamic pressure sensor (6) packaged in the probe head (1); the central line of the positive hole (5) and the axis of the cylinder (3) of the probe head (1) are on the same plane, and the axis of the cylinder (3) of the probe head (1) and the axis of the probe supporting rod (2) are superposed.
The diameter of the probe head (1) and the cylinder (3) is 2 mm, and the length is 10 mm.
The rotating body (4) is formed by rotating an AB curve section on a lemniscate around a shaft L, a point A is an intersection point of the lemniscate, a tangent line of a point B is perpendicular to a tangent line of the point A, and a rotating shaft L passes through the point A and is perpendicular to the tangent line of the point A.
The diameter of the positive hole (5) is 0.3 mm, and the vertical distance between the central line of the positive hole (5) and the lowest point of the surface of the twisted pair body (4) is 0.6 mm.
The probe supporting rod (2) is a cylinder, the diameter of the probe supporting rod is 6 mm, a circular pipeline is arranged in the probe supporting rod, a cable (7) of a dynamic pressure sensor packaged in the probe head (1) is led out of the probe tail part through the pipeline in the probe supporting rod (2), and a positioning block (8) is sleeved on the probe tail part.
Locating piece (8) structure as an organic whole contains cuboid base (9), cylinder boss (10), through-hole (11), screw hole (12), through-hole (11) suit in the probe afterbody, passes boss (10) both sides screw hole (12) by countersunk screw (13) and fixes, and countersunk screw (13) all imbeds in screw hole (12).
Cuboid base (9) contains four rectangle sides and two square bottom surfaces, two adjacent sides mutually perpendicular in four sides, the locating surface can all be regarded as to four sides, a bottom surface is connected with cylinder boss (10) in base (9), the perpendicular bisector and boss (10) axis coincidence of bottom surface, boss (10) axis and through-hole (11) central line coincidence, the through-hole diameter is 6.05 millimeters, the boss external diameter is 9 millimeters, base (9) bottom surface length of side is 11 millimeters, base (9) thickness is 3 millimeters.
The method comprises the steps of calibrating a probe in a subsonic calibration wind tunnel, selecting one side face of a base (9) of a positioning block (8) as a positioning face, determining the relative position of the positioning face of the positioning block (8) and a pressure sensing hole (5) through a level gauge, fixing the positioning block (8) through a countersunk head screw (13), and obtaining the pneumatic calibration coefficient of the probe under different incoming flow directions and different Mach numbers.
In actual measurement, a probe is installed and fixed on a displacement mechanism, the specific process is that a level gauge is utilized to adjust the level of a positioning surface of the displacement mechanism, the probe is installed on the displacement mechanism, the level gauge is placed on the positioning surface of a probe positioning block (8), the probe is rotated along the axis of a probe supporting rod (2), the level of the positioning surface is adjusted through the level gauge, the relative position of the central line of a front hole (5) and the positioning surface of the displacement mechanism is determined, and the probe is fixed on the displacement mechanism; the displacement mechanism for installing the probe is installed on a casing (14) of a tested air compressor through a positioning device, the probe is inserted into a certain radial position in a surface layer attached to a hub (17) between a rotor (15) and a stator (16) of the air compressor through the adjustment displacement mechanism, as shown in figure 6, according to the known average incoming flow direction, the probe is adjusted through the displacement mechanism, a positive hole (5) is aligned with the average incoming flow direction, the position is taken as a reference, the displacement mechanism is used for driving the probe to rotate around the axis of a probe supporting rod (2) by 1 angle in the anticlockwise and clockwise directions, the rotating angle is 40 degrees, 3 angular positions are measured in total, and under each angular position, the pneumatic calibration coefficients of the probe under different incoming flow directions and different Mach numbers obtained by combining with a subsonic calibration air tunnel are combined, and the airflow deflection angle, the total pressure, the static pressure and the Mach number of the tested flow field are calculated.
The invention has the positioning function, the adopted positioning block (8) has small size, the influence on the probe is small in the measuring process, the four side surfaces can be used as positioning surfaces and can be replaced mutually, the positioning process is simple and convenient, and the invention is more suitable for practical engineering application. The twisted pair spinning body (4) included in the probe head (1) can inhibit separation when airflow flows through the surface of the probe head, the interference of the streaming of the support rod head on a flow field in the boundary layer is weakened, when the probe head is close to an end wall to measure, the twisted pair spinning body (4) can also inhibit the scale of a horseshoe vortex at the front end of the probe head (1), and the structure improves the measurement accuracy of the flow field of the boundary layer of the end wall. The invention only comprises a pressure sensing hole (5), only one dynamic pressure sensor (6) is packaged in a cylinder (3) of the probe head part (1), the probe head part (1) is I-shaped, has small size, small interference on a measured flow field and high spatial resolution, and can be inserted into a multi-stage compressor rotor (15) and a stator (16) to measure dynamic changes of two-dimensional flow field airflow deflection angle, total pressure, static pressure and Mach number of an end wall boundary layer.
Claims (1)
1. The utility model provides a measure multistage compressor and change quiet interior end wall two-dimentional developments boundary layer probe, by probe head (1), branch (2), dynamic pressure sensor (6), locating piece (8) constitute, its characterized in that: the probe head (1) is composed of a cylinder (3) and a double-twisted-wire rotating body (4) which share the same bottom surface, the joint of the cylinder (3) and the double-twisted-wire rotating body (4) is in smooth curved surface transition, and a dynamic pressure sensor (6) is packaged in the probe head (1); a pressure sensing hole (5) is formed in the side face of a cylinder (3) of the probe head (1) and is a positive hole (5), and the positive hole (5) is communicated with a dynamic pressure sensor (6) packaged in the probe head (1); the central line of the positive hole (5) and the axis of the cylinder (3) of the probe head (1) are on the same plane, and the axis of the cylinder (3) of the probe head (1) is superposed with the axis of the probe supporting rod (2);
the diameter of the cylinder (3) of the probe head (1) is d, the range of d is more than or equal to 1.5 mm and less than or equal to 2.3 mm, and the length is 4d to 8 d;
the rotating body (4) is formed by rotating an AB curve section on a lemniscate around a shaft L, a point A is a lemniscate intersection point, a tangent of a point B is vertical to a tangent of the point A, and a rotating shaft L passes through the point A and is vertical to the tangent of the point A;
the diameter of the main hole (5) is 0.2 mm to 0.4 mm, the vertical distance between the circle center of the main hole (5) and the lowest point of the surface of the rotating body (4) is h, and the value range of h is more than or equal to 0.29d and less than or equal to 0.6 d;
the probe supporting rod (2) is a cylinder, the diameter of the probe supporting rod is D, the value range of D is more than or equal to 4 mm and less than or equal to 10 mm, a circular pipeline is arranged in the probe supporting rod, a cable (7) of a dynamic pressure sensor packaged in the head part (1) of the probe is led out of the tail part of the probe through the pipeline in the probe supporting rod (2), and a positioning block (8) is sleeved on the tail part of the probe;
the positioning block (8) is of an integrated structure and comprises a cuboid base (9), a cylindrical boss (10), a through hole (11) and threaded holes (12), the through hole (11) is sleeved at the tail of the probe, a countersunk screw (13) penetrates through the threaded holes (12) on the two sides of the boss (10) to be fixed, and the countersunk screw (13) is completely embedded into the threaded holes (12);
the rectangular base (9) comprises four rectangular side surfaces and two square bottom surfaces, two adjacent side surfaces in the four side surfaces are perpendicular to each other, the four side surfaces can be used as positioning surfaces, one bottom surface in the base (9) is connected with a cylindrical boss (10), a perpendicular bisector of the bottom surface is superposed with the axis of the boss (10), the axis of the boss (10) is superposed with the central line of a through hole (11), the diameter of the through hole is D +0.05 mm, the outer diameter of the boss is M, the value range is D +2 mm or more and less than or equal to D +5 mm, the side length of the bottom surface of the base (9) is M to M +3 mm, the thickness of the base (9) is H, and the value range is 2 mm or more and less than or equal to H and less than or equal to 5 mm;
calibrating the probe in a subsonic calibration wind tunnel, selecting one side surface of a base (9) of a positioning block (8) as a positioning surface, determining the relative position of the positioning surface of the positioning block (8) and a pressure sensing hole (5) through a level gauge, fixing the positioning block (8) through a countersunk head screw (13), and obtaining the pneumatic calibration coefficient of the probe in different incoming flow directions and different Mach numbers;
in actual measurement, a probe is installed and fixed on a displacement mechanism, the specific process is that a level gauge is utilized to adjust the level of a positioning surface of the displacement mechanism, the probe is installed on the displacement mechanism, the level gauge is placed on the positioning surface of a probe positioning block (8), the probe is rotated along the axis of a probe supporting rod (2), the level of the positioning surface is adjusted through the level gauge, the relative position of the central line of a front hole (5) and the positioning surface of the displacement mechanism is determined, and the probe is fixed on the displacement mechanism; the displacement mechanism for installing the probe is installed on a casing (14) of a tested compressor through a positioning device, the probe is inserted into a certain radial position in the boundary layer of the casing (14) or the boundary layer of a hub (17) between a rotor (15) and a stator (16) of the compressor by adjusting the displacement mechanism, according to the known average incoming flow direction, the probe is adjusted by the displacement mechanism to make the positive hole (5) aligned with the average incoming flow direction, taking the position as a reference, driving the probe to rotate around the axis of the probe supporting rod (2) by 1 angle in the anticlockwise direction and the clockwise direction by using a displacement mechanism, wherein the rotation angle is 30-45 degrees, measuring 3 angular positions in total, under each angle position, calculating an airflow deflection angle, total pressure, static pressure and Mach number of a measured flow field by combining the aerodynamic calibration coefficients of the probe under different incoming flow directions and different Mach numbers obtained by the subsonic calibration wind tunnel;
compared with other boundary layer probes, the probe has the beneficial effects that:
(1) the head of the probe adopts a double-twisted-wire rotating body structure, and the dynamic pressure sensor can be installed closer to the pressure sensing hole, so that the volume of a cavity between the pressure sensing hole and the sensor is greatly reduced, the cavity effect is reduced, the frequency response of the probe is improved, and dynamic parameters of a flow field can be measured; the vertical distance between the circle center of the pressure sensing hole and the lowest point of the surface of the double-twisted-line rotating body is small, and the measurement of two-dimensional flow field parameters in the boundary layer of the end wall can be realized, wherein the parameters comprise an airflow deflection angle, total pressure, static pressure and Mach number; the probe head is I-shaped and has smaller size, on one hand, the probe can be inserted into a multi-stage compressor static transfer chamber for measurement, the interference on a measured flow field is small, and on the other hand, the probe has higher spatial resolution;
(2) the double-twisted-line rotating body is in smooth curved surface transition with the cylinder at the head of the probe, when airflow flows through the surface of the double-twisted-line rotating body, the special structure of the double-twisted-line rotating body can inhibit the airflow separation of the airflow on the surface of the airflow, and the interference of the streaming around the head of the support rod on the flow field in the boundary layer is weakened; in addition, when the flow field parameters are measured close to the end wall, the invention can inhibit the scale of the horseshoe vortex at the front end of the probe head and improve the measurement precision;
(3) the positioning block adopted by the invention has small size, the influence on the probe is small in the measuring process, and because four side surfaces of the positioning block can be used as positioning surfaces and can be replaced mutually, the positioning process is simple and convenient, and the positioning method is more suitable for practical engineering application.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110829779.8A CN113551869A (en) | 2021-07-22 | 2021-07-22 | Probe for measuring two-dimensional dynamic boundary layer of rotating-static end wall of multistage gas compressor |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110829779.8A CN113551869A (en) | 2021-07-22 | 2021-07-22 | Probe for measuring two-dimensional dynamic boundary layer of rotating-static end wall of multistage gas compressor |
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| Publication Number | Publication Date |
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| CN113551869A true CN113551869A (en) | 2021-10-26 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115436656A (en) * | 2022-09-06 | 2022-12-06 | 北京航空航天大学 | Splayed hot wire probe for measuring interstage two-dimensional velocity field of gas compressor |
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2021
- 2021-07-22 CN CN202110829779.8A patent/CN113551869A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115436656A (en) * | 2022-09-06 | 2022-12-06 | 北京航空航天大学 | Splayed hot wire probe for measuring interstage two-dimensional velocity field of gas compressor |
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