CN216899542U - Probe for measuring three-dimensional dynamic boundary layer of hub between rotating and static of fan - Google Patents
Probe for measuring three-dimensional dynamic boundary layer of hub between rotating and static of fan Download PDFInfo
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- CN216899542U CN216899542U CN202121674541.4U CN202121674541U CN216899542U CN 216899542 U CN216899542 U CN 216899542U CN 202121674541 U CN202121674541 U CN 202121674541U CN 216899542 U CN216899542 U CN 216899542U
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Abstract
The invention belongs to the technical field of subsonic three-dimensional flow field parameter testing, and particularly relates to a probe for measuring a three-dimensional dynamic boundary layer of a hub between a rotating shaft and a static shaft of a fan. 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 double-twisted-line rotating 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 double-twisted-line rotating body at the probe head and communicated with the dynamic pressure sensor 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 probe head adopts a twisted pair wire rotating body structure, is I-shaped, has a small vertical distance between the circle center of a pressure sensing hole and the lowest point of the probe head, can measure the dynamic change of three-dimensional flow field parameters in a hub boundary layer between the rotating and the static of a fan through calibration wind tunnel calibration, and provides measurement data for improving the performance of the fan.
Description
Technical Field
The invention belongs to the technical field of subsonic three-dimensional flow field parameter testing, and particularly relates to a probe for measuring a three-dimensional dynamic boundary layer of a hub between a rotor and a stator of a fan.
Background
The method has the advantages that the pitch angle, the deflection angle, the total pressure, the static pressure and the Mach number of the airflow of the three-dimensional dynamic boundary layer of the hub between the rotation and the static of the fan are obtained, and the method has an important effect on improving the performance of the fan. Because the boundary layer flow field in the hub area is influenced by the sweep of the wake of the movable blade, the angular vortex and other secondary flows, the internal flow field has strong non-stationarity and rotation, the axial clearance between the rotating and static parts of the fan is very small, and particularly the axial clearance between the rotating and static parts of the fan is smaller in a small and medium-sized fan, so that the measurement difficulties of large positive airflow pitch angle, large airflow deflection angle, thin boundary layer thickness, narrow test space and the like exist for the test of the three-dimensional flow field parameters in the boundary layer of the hub between the rotating and static parts of the fan.
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 surface layer probe, because the head part of the probe is L-shaped, the probe cannot be inserted into a fan rotating and static space for measurement, and the surface layer probe also has a very large cavity effect, only a steady state total pressure value of a measuring point can be obtained, and dynamic changes of an airflow pitch angle, an airflow deflection angle, static pressure and a 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 air flow pitch angle, an air flow 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 pitch angle, the deflection angle, the total pressure and the Mach number of the airflow.
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 on a wall surface by utilizing the sensitivity of pressure sensitive paint to pressure, and can reflect the dynamic change of the static pressure in a hub 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 pitch angle, an airflow deflection angle, total pressure and a Mach number.
In a fan test, dynamic changes of an air flow pitch angle, an air flow deflection angle, total pressure, static pressure and a Mach number of a boundary layer flow field are preferably obtained by measuring three-dimensional flow field parameters of a hub boundary layer of a static interval, and the dynamic changes are used for verifying fan design and flow field diagnosis so as to improve machine performance, and the probe cannot meet test requirements.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: and measuring dynamic changes of an airflow pitch angle, an airflow deflection angle, total pressure, static pressure and Mach number in a three-dimensional flow field in a hub boundary layer between rotation and static of the fan. Therefore, compared with other boundary layer probes, the probe for measuring the three-dimensional dynamic boundary layer of the hub between the rotation and the static of the fan has the advantages of self-contained positioning function, small size, high spatial resolution, capability of being inserted into the rotation and static room for measurement, small interference on a measured flow field, high measurement precision and multi-parameter dynamic measurement. The invention is suitable for measuring the dynamic changes of the airflow pitch angle, the airflow deflection angle, the total pressure, the static pressure and the Mach number in the three-dimensional flow field in the hub boundary layer between the rotation and the static of the fan.
The technical solution of the invention is as follows:
1. the utility model provides a measure fan changes three-dimensional dynamic boundary layer probe of quiet room wheel hub, 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 twisted-pair body (4) which share the bottom surface, the smooth curved surface transition of the joint of the cylinder (3) and the twisted-pair body (4) is realized, a dynamic pressure sensor (6) is packaged in the probe head (1), a pressure sensing hole is formed in the surface of the twisted-pair body, the pressure sensing hole is an inclined hole (5), the inclined hole (5) is communicated with the dynamic pressure sensor (6) packaged in the probe head (1), the central line of the inclined hole (5) is positioned on the same plane with the axis of the cylinder (3) of the probe head (1), and the axis of the cylinder of the probe head (1) is coincided with the axis of the probe supporting rod (2).
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 inclined hole (5) is 0.2 mm to 0.4 mm, the included angle between the central line of the inclined hole (5) and the axial line of the cylinder (3) of the probe head (1) is theta, and the value range is that theta is more than or equal to 0 degrees and less than 90 degrees.
5. Furthermore, the vertical distance between the center of the inclined hole (5) and the lowest point of the surface of the twisted pair body (4) is h, and the value range of h is more than or equal to 0d and less than 0.29 d.
6. 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 probe tail part through the pipeline in the probe supporting rod (2), and the probe tail part is sleeved with a positioning block (8).
7. 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 the probe 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).
8. 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 boundary layer probes, the probe for measuring the three-dimensional dynamic boundary layer of the hub between the rotating and static parts of the fan has the following beneficial effects:
the beneficial effects are that: according to the invention, the head part of the probe adopts a twisted-pair wire rotating body structure, the dynamic pressure sensor can be installed closer to the pressure sensing hole, 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 three-dimensional flow field parameters in the hub boundary layer can be realized, wherein the parameters comprise an airflow pitch angle, 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 fan rotating 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 double-twisted-line rotating body and weaken the interference of the streaming around the head of the supporting rod on the flow field in the boundary layer, and on the other hand, when the double-twisted-line rotating body is close to a hub to measure flow field parameters, the double-twisted-line rotating body can inhibit the scale of a horseshoe vortex at the front end of the head of the probe 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 the four side surfaces can be used as positioning surfaces and can be replaced mutually, the positioning process is simple and convenient, and the positioning block is more suitable for 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-inclined 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-fan casing, 15-rotor, 16-stator and 17-fan 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 of the present invention provides a probe for measuring a three-dimensional dynamic boundary layer of a hub between a rotating chamber and a stationary chamber of a fan, which is composed of a probe head (1), a supporting 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-wire rotation body (4) which share the bottom surface, the smooth curved surface transition of the joint of the cylinder (3) and the double-twisted-wire rotation body (4) is realized, a dynamic pressure sensor (6) is packaged in the probe head (1), a pressure sensing hole is formed in the surface of the double-twisted-wire rotation body, the pressure sensing hole is an inclined hole (5), the inclined hole (5) is communicated with the dynamic pressure sensor (6) packaged in the probe head (1), the central line of the inclined hole (5) is positioned on the same plane with the axis of the cylinder (3) of the probe head (1), and the axis of the cylinder of the probe head (1) is coincided with the axis of the probe supporting rod (2).
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 inclined hole (5) is 0.3 mm, and the included angle between the central line of the inclined hole (5) and the axial line of the cylinder (3) of the probe head (1) is 50 degrees.
The vertical distance between the circle center of the inclined hole (5) and the lowest point of the surface of the double-twisted-line rotating body (4) is 0.06 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 probe is calibrated in a subsonic calibration wind tunnel, one side surface of a base (9) of a positioning block (8) is selected as a positioning surface, the relative position of the positioning surface of the positioning block (8) and an inclined hole (5) is determined through a level gauge, the positioning block (8) is fixed through a countersunk head screw (13), and the pneumatic calibration coefficient of the probe is obtained 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 an inclined 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 fan to be measured through a positioning device, the probe is inserted into a certain radial position in a hub (17) boundary layer between a fan rotor (15) and a stator (16) 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 pressure sensing hole is aligned to the average incoming flow direction, the probe is driven to rotate around the axis of a probe support rod (2) by 3 angles in the anticlockwise direction and the clockwise direction respectively by using the displacement mechanism as a reference, the angle interval is 15 degrees, 7 angular positions are measured in total, and under each angular position, the airflow pitch angle, the airflow deflection angle, the total pressure, the static pressure and the Mach number of the measured flow field are calculated by combining the aerodynamic calibration coefficients of the probe obtained by a subsonic calibration wind tunnel under different incoming flow directions and different Mach numbers.
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 engineering application. The probe head (1) comprises the twisted pair body (4), on one hand, the vertical distance between the circle center of the inclined hole (5) and the lowest point of the surface of the twisted pair body (4) is small, the three-dimensional flow field dynamic parameters in the boundary layer of the hub (17) can be measured, on the other hand, the twisted pair body (4) can inhibit separation when airflow flows through the surface of the twisted pair body, the interference of the circumfluence of the support rod head (1) on the flow field in the boundary layer is weakened, when the twisted pair body is close to the hub (17) to measure, the twisted pair body (4) can inhibit the scale of a horseshoe vortex at the front end of the probe head (1), the structure improves the measurement precision of the boundary layer flow field of the hub (17), and finally, on the other hand, because the twisted pair body (4) is flat, the dynamic sensor can be installed close to the inclined hole (5), the volume of a containing cavity between the inclined hole (5) and the sensor is greatly reduced, the cavity effect is reduced, and the frequency response of the probe is improved. The invention only comprises a pressure sensing hole, only one dynamic pressure sensor (6) is packaged in the cylinder (3) of the probe head (1), the diameter of the cylinder (3) of the probe head (1) is relatively small, the interference to a measured flow field is small, the spatial resolution is high, and the dynamic changes of the three-dimensional flow field airflow pitch angle, the airflow deflection angle, the total pressure, the static pressure and the Mach number of a hub (17) boundary layer can be measured by inserting the dynamic pressure sensor into a fan rotor (15) and a stator (16).
Claims (1)
1. The utility model provides a measure fan changes three-dimensional dynamic boundary layer probe of quiet room wheel hub, 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, a dynamic pressure sensor (6) is packaged in the probe head (1), a pressure sensing hole which is an inclined hole (5) is formed in the surface of the double-twisted-line rotating body, the inclined hole (5) is communicated with the dynamic pressure sensor (6) packaged in the probe head (1), the central line of the inclined 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 of the probe head (1) and the axis of the probe supporting rod (2) are overlapped;
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 inclined hole (5) is 0.2 mm to 0.4 mm, the included angle between the central line of the inclined hole (5) and the axial line of the cylinder (3) of the probe head (1) is theta, and the value range is that theta is more than or equal to 0 degree and less than 90 degrees;
the vertical distance between the circle center of the inclined hole (5) and the lowest point of the surface of the twisted pair body (4) is h, and the value range of h is more than or equal to 0d and less than 0.29 d;
the probe supporting rod (2) is a cylinder, the diameter of the probe supporting rod is D, the value range of D is not less than 4 mm and not more than 10 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 tail of the probe through the pipeline in the probe supporting rod (2), and a positioning block (8) is sleeved on the tail 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);
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 perpendicular bisector of bottom surface and boss (10) axis coincidence, 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 millimeter and is less than or equal to M +5 millimeter, base (9) bottom surface length of side is M to M +3 millimeter, base (9) thickness is H, the value range is 2 millimeter and is less than or equal to H and is less than or equal to 5 millimeters.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121674541.4U CN216899542U (en) | 2021-07-22 | 2021-07-22 | Probe for measuring three-dimensional dynamic boundary layer of hub between rotating and static of fan |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121674541.4U CN216899542U (en) | 2021-07-22 | 2021-07-22 | Probe for measuring three-dimensional dynamic boundary layer of hub between rotating and static of fan |
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| CN216899542U true CN216899542U (en) | 2022-07-05 |
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| CN202121674541.4U Active CN216899542U (en) | 2021-07-22 | 2021-07-22 | Probe for measuring three-dimensional dynamic boundary layer of hub between rotating and static of fan |
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- 2021-07-22 CN CN202121674541.4U patent/CN216899542U/en active Active
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