CN106885683B - Hemispherical head twelve-hole steady-state pressure probe for measuring three-dimensional complex flow field - Google Patents
Hemispherical head twelve-hole steady-state pressure probe for measuring three-dimensional complex flow field Download PDFInfo
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- CN106885683B CN106885683B CN201710132968.3A CN201710132968A CN106885683B CN 106885683 B CN106885683 B CN 106885683B CN 201710132968 A CN201710132968 A CN 201710132968A CN 106885683 B CN106885683 B CN 106885683B
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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
Abstract
The invention belongs to the technical field of pressure testing, and discloses a hemispherical head twelve-hole steady-state pressure probe for measuring a three-dimensional complex flow field, which comprises a probe head and a support rod, wherein the probe head consists of a cylinder and a hemisphere which share the bottom surface, 8 pressure sensing holes are formed in the cylindrical surface of the probe head, 4 pressure sensing holes are formed in the surface of the hemisphere, the 12 pressure sensing holes are respectively communicated with 12 pressure leading pipes in the probe head, and the 12 pressure leading pipes are led out of the tail part of the probe through an inner channel of the probe support rod. Compared with the existing pressure probe, the invention can simultaneously measure the total pressure, static pressure, Mach number, pitch angle and deflection angle parameters within the range of incoming flow deflection angle +/-180 DEG and pitch angle +/-30 DEG after calibration, and is suitable for measuring three-dimensional complex flow fields with backflow at the blade discharge inlet, outlet and interstage in the surge forcing process of aeroengines, gas compressors, fans and the like.
Description
Technical Field
The invention belongs to the technical field of pressure testing, relates to a dynamic pressure measuring device of a three-dimensional unsteady flow field, and particularly relates to a hemispherical head twelve-hole steady-state pressure probe for measuring a three-dimensional complex flow field, which is suitable for measuring the three-dimensional complex flow field with backflow at a blade inlet, a blade outlet and stages in the surge process of an aeroengine, a gas compressor, a fan and the like, and is also suitable for measuring the three-dimensional complex flow field with unclear incoming flow direction, large incoming flow direction change, no installation angle adjustment after the probe is installed and backflow.
Background
The pressure probe, such as a five-hole pressure probe, a seven-hole pressure probe and the like, is widely applied to the measurement of three-dimensional flow fields in aircraft engines, gas turbines, compressors, fans, pumps and the like due to the advantages of simple structure, firmness, durability, easiness in operation and the like. Due to the limitation of the structure and the aerodynamic characteristics, the range of the five-hole pressure probe for measuring the incoming flow direction is limited, the deflection angle is generally not more than +/-45 degrees, and the range of the seven-hole pressure probe for measuring the deflection angle of the incoming flow is not more than +/-70 degrees.
In the case of a flow field with an unknown incoming flow direction, if the probes are not roughly aligned with the incoming flow direction when being installed, and the angular measurement range of the probes is exceeded, although data are obtained from the pressure sensing hole measurement, flow parameters such as the air flow direction, the total pressure, the static pressure and the like cannot be calculated.
In the surge-inducing process of aero-engines, gas compressors, fans and the like, backflow exists in three-dimensional flow fields of inlets and outlets of blade rows or among blade rows, a five-hole pressure probe or a seven-hole pressure probe which is commonly used cannot accurately measure the airflow deflection angle, the pitch angle, the total pressure, the static pressure and the Mach number of the region, and a three-dimensional steady-state pressure probe technology which is practical in engineering and can measure the backflow is absent at present.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: aiming at the current three-dimensional steady state pressure probe technology which is lack of engineering practicality and can give consideration to the measurement of backflow, the invention provides a hemispherical head twelve-hole steady state pressure probe for measuring a three-dimensional complex flow field, which can measure steady state data such as deflection angle, pitch angle, total pressure, static pressure, Mach number and the like of airflow when backflow exists at inlets, outlets or blade rows of an aircraft engine, a gas compressor, a fan and the like.
The technical solution of the invention is as follows:
1. a twelve-hole hemispherical steady-state pressure probe for measuring a three-dimensional complex flow field is characterized in that: the probe comprises a probe head (1) and a supporting rod (2), wherein the probe head (1) comprises a cylinder (3) and a hemisphere (4) which share the bottom surface, the side surface of the cylinder (3) at the probe head is provided with 8 cylindrical surface pressure sensing holes (5) which are not communicated with each other, the side surface of the hemisphere (4) is provided with 4 spherical surface pressure sensing holes (6) which are not communicated with each other, and the 12 pressure sensing holes are respectively communicated with one end of 12 pressure leading pipes (7) packaged in the probe head (1).
2. Furthermore, the probe supporting rod (2) is a cylinder, a circular pipeline is arranged in the probe supporting rod, 12 pressure leading pipes (7) are packaged in the probe head (1), and the tail of the probe is led out through the pipeline in the probe supporting rod (2).
3. Furthermore, 8 cylindrical surface pressure sensing holes (5) formed in the side surface of the cylinder (3) of the probe head (1) are 0.5 mm to 1.5 mm in diameter, the included angle of the center lines of the adjacent 2 holes is 45 degrees, the center lines of the 8 holes are on the same plane, the plane is perpendicular to the axis of the cylinder (3) of the probe head (1), and the distance between the center line of the 8 holes and the bottom surface of the hemisphere (4) of the probe head (1) is 1 mm to 5 mm.
4. Furthermore, 4 spherical pressure sensing holes (6) are uniformly formed in the side face of the hemisphere (4) of the probe head (1) along the circumference, the diameter is 0.5 mm to 1.5 mm, the center line of each spherical pressure sensing hole (6) is positioned on the same plane with the center line of a positive pressure sensing hole (5) in the side face of the cylinder (3) corresponding to the right lower side and the axis of the cylinder (3) of the probe head (1), and the distance between the circle center of each spherical pressure sensing hole (6) and the arc of the bottom face of the hemisphere (4) is 2 mm to 6 mm.
5. Furthermore, the diameter of the cylinder (3) of the probe head (1) is 6 mm to 10 mm, the length of the cylinder is 10 mm to 40 mm, and the axis of the cylinder (3) of the probe head (1) is coincident with the axis of the probe support rod (2).
The invention has the beneficial effects that:
compared with the existing pressure probe, the invention can simultaneously measure the total pressure, static pressure, Mach number, pitch angle, deflection angle and other steady state data of the incoming flow within the range of a deflection angle +/-180 degrees and a pitch angle +/-30 degrees through calibration and calibration, is suitable for measuring the three-dimensional complex flow field with backflow at the inlet, the outlet and the interstage of the blade in the surge process of an aeroengine, a gas compressor, a fan and the like, and is also suitable for measuring the three-dimensional complex flow field with unclear incoming flow direction, large change of the incoming flow direction, no adjustment of the installation angle after the probe is installed and backflow.
Drawings
Fig. 1 is a schematic structural diagram of a twelve-hole pressure probe for measuring steady-state parameters of a three-dimensional complex flow field in a first embodiment of the present invention.
Fig. 2 is a schematic diagram of the definition of the incoming flow deflection angle and the pitch angle of the three-dimensional flow field.
Wherein: 1-probe head, 2-probe supporting rod, 3-cylinder, 4-hemisphere, 5-cylindrical surface pressure sensing hole, 6-spherical surface pressure sensing hole and 7-pressure guiding pipe.
Detailed Description
The invention is described in detail below with reference to the figures and specific embodiments.
As shown in fig. 1, in the first embodiment, a twelve-hole hemispherical head steady-state pressure probe for measuring a three-dimensional complex flow field is introduced, which includes a probe head (1) and a support rod (2), the probe head (1) includes a cylinder (3) and a hemisphere (4) which share a bottom surface, 8 cylindrical surface pressure sensing holes (5) which are not communicated with each other are formed in the side surface of the cylinder (3) at the probe head, 4 spherical surface pressure sensing holes (6) which are not communicated with each other are formed in the side surface of the hemisphere (4), and 12 pressure sensing holes are respectively communicated with one end of 12 pressure guiding pipes (7) which are packaged in the probe head (1).
The probe supporting rod (2) is a cylinder, the diameter of the probe supporting rod is 10 mm, a circular channel is formed in the probe supporting rod, the diameter of the circular channel is 8 mm, 12 pressure guiding pipes (7) are packaged in the probe head (1), and the tail of the probe is led out through a pipeline in the probe supporting rod (2).
The diameter of 8 cylindrical surface pressure sensing holes (5) formed in the side surface of a cylinder (3) of the probe head (1) is 0.5 mm, the included angle of the central lines of the adjacent 2 holes is 45 degrees, the central lines of the 8 holes are positioned on the same plane, the plane is perpendicular to the axis of the cylinder (3) of the probe head (1), and the distance between the plane and the bottom surface of a hemispheroid (4) of the probe head (1) is 1 mm.
The probe head (1) hemisphere (4) side, along the circumference evenly open have 4 sphere pressure sense hole (6), the diameter is 0.5 millimeter, the central line of every sphere pressure sense hole (6) and the central line of a positive pressure sense hole (5) on the cylinder (3) side that corresponds under with, the axis of probe head (1) cylinder (3) is on a plane, the distance of sphere pressure sense hole (6) centre of a circle and hemisphere (4) bottom surface circular arc is 2 millimeters.
The diameter of the cylinder (3) of the probe head (1) is 8 mm, the length of the cylinder is 30 mm, and the axis of the cylinder (3) of the probe head (1) is coincided with the axis of the probe supporting rod (2).
The hemispherical head twelve-hole steady-state pressure probe for measuring the three-dimensional complex flow field, disclosed by the embodiment of the invention, can obtain calibration data through calibration and calibration. When a three-dimensional complex flow field is actually measured, the 12 pressure sensing holes of the twelve-hole steady-state pressure probe with the hemispherical head measure pressure data sensed by the two pressure sensing holes, and the obtained calibration data are utilized to process the data, so that the steady-state data of the total pressure, the static pressure, the Mach number, the pitch angle and the deflection angle of three-dimensional incoming flow within the ranges of the deflection angle +/-180 degrees and the pitch angle +/-30 degrees can be measured, the three-dimensional complex flow field with the inlet, the outlet and the interstage of blades in the surge-forcing process of an aircraft engine, a gas compressor, a fan and the like can be measured, and the three-dimensional complex flow field with the unknown incoming flow direction, large change of the incoming flow direction, no adjustment of the installation angle.
Claims (1)
1. A twelve-hole hemispherical steady-state pressure probe for measuring a three-dimensional complex flow field is characterized in that: the probe comprises a probe head (1) and a supporting rod (2), wherein the probe head (1) comprises a cylinder (3) and a hemisphere (4) which share the same bottom surface, the side surface of the cylinder (3) at the probe head is provided with 8 cylindrical surface pressure sensing holes (5) which are not communicated with each other, the side surface of the hemisphere (4) is provided with 4 spherical surface pressure sensing holes (6) which are not communicated with each other, and the 12 pressure sensing holes are respectively communicated with one end of 12 pressure guiding pipes (7) which are packaged in the probe head (1);
the probe supporting rod (2) is a cylinder, a circular pipeline is arranged in the probe supporting rod, 12 pressure leading pipes (7) are packaged in the probe head (1), and the tail part of the probe is led out through the pipeline in the probe supporting rod (2);
the diameter of the cylinder (3) of the probe head (1) is 6 mm to 10 mm, the length of the cylinder (3) is 10 mm to 40 mm, and the axis of the cylinder (3) of the probe head (1) is coincided with the axis of the probe supporting rod (2);
the diameter of 8 cylindrical surface pressure sensing holes (5) formed in the side surface of a cylinder (3) of the probe head (1) is 0.5 mm to 1.5 mm, the included angle of the central lines of the adjacent 2 holes is 45 degrees, the central lines of the 8 holes are positioned on the same plane, the plane is vertical to the axis of the cylinder (3) of the probe head (1), and the distance between the plane and the bottom surface of a hemispheroid (4) of the probe head (1) is 1 mm to 5 mm;
the probe head (1) hemisphere (4) side, along the circumference evenly open have 4 sphere pressure sense hole (6), the diameter is 0.5 millimeter to 1.5 millimeters, the central line of every sphere pressure sense hole (6) and the central line of a positive pressure sense hole (5) on the cylinder (3) side that corresponds under with, the axis of probe head (1) cylinder (3) is on a plane, the distance of sphere pressure sense hole (6) centre of a circle and hemisphere (4) bottom surface circular arc is 2 millimeters to 6 millimeters.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710132968.3A CN106885683B (en) | 2017-03-08 | 2017-03-08 | Hemispherical head twelve-hole steady-state pressure probe for measuring three-dimensional complex flow field |
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| CN201710132968.3A CN106885683B (en) | 2017-03-08 | 2017-03-08 | Hemispherical head twelve-hole steady-state pressure probe for measuring three-dimensional complex flow field |
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| CN106885683A CN106885683A (en) | 2017-06-23 |
| CN106885683B true CN106885683B (en) | 2020-04-28 |
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| CN112098040B (en) * | 2020-11-18 | 2021-02-09 | 中国空气动力研究与发展中心低速空气动力研究所 | Measuring device and measuring method for mounting angle of directional dynamic pressure probe |
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| CN2108926U (en) * | 1991-12-12 | 1992-07-01 | 清华大学 | Omnibearing tow-dimensional speed measurer of air stream |
| JP2004104986A (en) * | 2002-07-16 | 2004-04-02 | Japan Servo Co Ltd | Permanent magnet type rotary electric machine |
| JP2006105859A (en) * | 2004-10-07 | 2006-04-20 | Tem-Tech Kenkyusho:Kk | Fluorine-containing resin thin film diaphragm pressure sensor and its manufacturing method |
| KR101184400B1 (en) * | 2010-05-13 | 2012-09-21 | 한양대학교 에리카산학협력단 | Anemovane |
| CN102636662A (en) * | 2012-04-20 | 2012-08-15 | 南京航空航天大学 | Full-flow direction flow velocity measurement probe and measurement method thereof |
| CN104155473A (en) * | 2014-08-12 | 2014-11-19 | 南京航空航天大学 | Wind speed and wind direction sensing device |
| CN204330280U (en) * | 2015-01-18 | 2015-05-13 | 中南大学 | Train parting flow field on-site testing device |
| CN204944736U (en) * | 2015-09-16 | 2016-01-06 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of total pressure measurement probe |
| CN105588703A (en) * | 2015-12-15 | 2016-05-18 | 中国燃气涡轮研究院 | 12-hole omni-directional probe for subsonic-speed and complex three-dimensional flow field measurement |
| CN106290968B (en) * | 2016-09-14 | 2018-11-23 | 华北电力科学研究院有限责任公司西安分公司 | A kind of large space pulsatile flow field three-dimension measuring system and measurement method |
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