CN106908191A - A kind of dynamic temperature force combination probe for measuring across sound Two Dimensional Unsteady flow field - Google Patents
A kind of dynamic temperature force combination probe for measuring across sound Two Dimensional Unsteady flow field Download PDFInfo
- Publication number
- CN106908191A CN106908191A CN201710136639.6A CN201710136639A CN106908191A CN 106908191 A CN106908191 A CN 106908191A CN 201710136639 A CN201710136639 A CN 201710136639A CN 106908191 A CN106908191 A CN 106908191A
- Authority
- CN
- China
- Prior art keywords
- probe
- sound
- dynamic temperature
- flow field
- dynamic
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L19/00—Details of, or accessories for, apparatus for measuring steady or quasi-steady pressure of a fluent medium insofar as such details or accessories are not special to particular types of pressure gauges
- G01L19/0092—Pressure sensor associated with other sensors, e.g. for measuring acceleration or temperature
Landscapes
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Measuring Temperature Or Quantity Of Heat (AREA)
- Measuring Fluid Pressure (AREA)
Abstract
The invention belongs to temperature, pressure test technical field, disclose a kind of dynamic temperature force combination probe for measuring across sound Two Dimensional Unsteady flow field, including end of probe, pole, end of probe is bicylindrical cambered surface prism structure, built with 3 dynamic pressure transducers, 1 dynamic temperature sensor.End of probe windward side includes just preceding cylinder cambered surface, left side plan and right side plan during measurement, and lee face is rear cylinder cambered surface.Respectively there is 1 pressure experience hole in 3 parts of windward side, connected with 3 dynamic pressure transducers in end of probe respectively, dynamic temperature sensor head exposes end of probe top surface, sensor wire draws probe tails by pole internal channel.Compared with existing pressure probe, the present invention is demarcated by calibration wind tunnel, across sound temperature of incoming flow, stagnation pressure, static pressure, deflection angle, Mach number and two-dimension speed can simultaneously be measured to change with time, for turbine experiment provides a kind of means for measuring across sound Two Dimensional Unsteady flow field parameter efficiently, accurately, comprehensively.
Description
Technical field
The invention belongs to flow field temperature, pressure test technical field, it is related to the dynamic temperature in transonic speed Two Dimensional Unsteady flow field
Degree, dynamic pressure measurement device, and in particular to a kind of dynamic temperature force combination probe in across the sound Two Dimensional Unsteady flow field of measurement,
Suitable for the test of transonic speed two dimension Dynamic Flow Field between nozzle ring and movable vane.
Background technology
Aero-engine, the turbine inlet of gas turbine carry out stream and there is hot spot that downstream thermo parameters method can be influenceed, or even sternly
Ghost image rings turbo blade thermic load and life-span.The mechanism of transmission of the research hot spot in nozzle ring is, it is necessary to measure turbine guiding
Device exports unsteady velocity field, pressure field and the temperature field of transonic speed two-dimensional flow field.
Three pore pressure force probes, stagnation temperature probe is typically respectively adopted at present, by the displacement mechanism on casing, drives
Probe goes to measured position, measures.Three pore pressure force probes can only provide to flow stagnation pressure, static pressure, deflection angle and Mach number, always
Warm probe can only provide stagnation temperature data.
Experimental study is carried out using existing probe measurement technique, be there are problems that following：1st, two kinds of probes are surveyed respectively
Amount, test period is long, and experimentation cost is high；2nd, two kinds of probes are measured respectively, need to change probe in process of the test to flow operating mode meeting
There is certain change, especially temperature field can be inconsistent；3rd, influenceed can by displacement mechanism positioning for the point position of different probe
Can it is variant, the flow parameter data that different probe is measured certainly not from same streamline, using these probe measurements
Data, when combination calculates the parameters such as speed, can bring about data error, and then can bring very important to total measurement result
Error；4th, due to the rotation of turbine rotor blade, nozzle ring outlet transonic speed two-dimensional flow field is unsteady, with movable vane leaf
The change of piece position and change, existing probe technique can only provide pressure, temperature and the speed data of stable state, it is impossible to reflection heat
The unsteady mechanism of transmission of the spot in turbine.
The content of the invention
The purpose of the present invention is directed to hot spot in turbine transonic speed two dimension Dynamic Flow Field propagation test, existing probe skill
Art can not simultaneously provide dynamic pressure, dynamic temperature and the dynamic speed data problem in tested flow field, and a kind of measurement of invention is across sound
The dynamic temperature force combination probe in Two Dimensional Unsteady flow field, can take into account measurement measurement high subsonic speed (0.75<Mach number<1.0)
With supersonic speed (1.0<Mach number<1.2) two-dimentional Dynamic Flow Field, while measuring the temperature that nozzle ring exports transonic speed two-dimensional flow field
Degree, stagnation pressure, static pressure, deflection angle, Mach number and speed change with time, it is adaptable to study hot spot in nozzle ring and go out
The unsteady mechanism of transmission of mouth.
Technical solution of the invention is：
1st, a kind of dynamic temperature force combination probe for measuring across sound Two Dimensional Unsteady flow field, it is characterised in that：Including visiting
Needle section (1), pole (2), the end of probe (1) are bicylindrical cambered surface prism structure, and it is internal equipped with 3 dynamic pressures biographies
Sensor, 1 dynamic temperature sensor, the top surface (3) of end of probe (1) are vertical with probe pole (2) rotation axis.Probe measurement
When end of probe (1) windward side include just preceding cylinder cambered surface (4), left side plan (5) and right side plan (6), after lee face is
Cylinder cambered surface (7)；Dynamic temperature sensor head (8) exposes top surface (3)；On the just preceding cylinder cambered surface (4) of end of probe (1), a left side
Side plane (5) and right side plan (6) are respectively provided with 1 pressure experience hole, respectively mesopore (9), left hole (10), right hole (11), and this 3
Individual not connected pressure experience hole, connects with 3 dynamic pressure transducers in end of probe (1) respectively.
2nd, further, probe pole (2) is cylinder, and round passage is provided with inside it, and circular channel is provided with inside it.
3rd, further, end of probe (1) mesopore (9) center line, temperature sensor head (8) center line and probe pole
(2) in approximately the same plane, left side plan (5) is with right side plan (6) along the plane symmetry, left hole (10) and right hole (11) for axis
It is distributed along the plane symmetry.
4th, further, left side plan (5) and right side plan (6) angle are 32 ° to 76 °, the just preceding cylinder of end of probe (1)
The arc length of cambered surface (4) is 1 millimeter to 2 millimeters.
5th, further, dynamic temperature sensor head (8) exposes (3) 1 millimeters to 3 millimeters of top surface.
6th, further, mesopore (9) center of circle and end of probe (1) top surface (3) distance are 1 millimeter to 5 millimeters.
7th, further, a diameter of 0.6 millimeter to 1.5 millimeters of mesopore (9), left hole (10) and right hole (11).
8th, further, the cable (12) of 3 dynamic pressure transducers in end of probe (1), 1 dynamic temperature sensor
Through probe pole (2) internal channel, drawn by probe tails.
The beneficial effects of the invention are as follows：
Compared with existing pressure probe, the present invention is demarcated by calibration wind tunnel, can simultaneously measure across sound temperature of incoming flow, total
Pressure, static pressure, deflection angle, Mach number and two-dimension speed change with time, for turbine experiment provide it is a kind of efficiently, accurately,
The means of across sound Two Dimensional Unsteady flow field parameter are measured comprehensively.
Brief description of the drawings
Fig. 1 is the dynamic temperature force combination probe in across the sound Two Dimensional Unsteady flow field of measurement in embodiments of the invention
Structural representation.
Fig. 2 is the left view of Fig. 1.
Fig. 3 is the top view of Fig. 1.
Wherein：1- end of probes, 2- probe poles, 3- top surfaces, the just preceding cylinder cambered surfaces of 4-, 5- left side plans, 6- right sides are flat
Face, cylinder cambered surface after 7-, 8- dynamic temperature sensor heads, 9- mesopores, 10- left hole, 11- right hole, 12- cables.
Specific embodiment
The present invention will be described in detail with specific embodiment below in conjunction with the accompanying drawings.
As shown in figure 1, describing a kind of dynamic temperature pressure group for measuring across sound Two Dimensional Unsteady flow field in the present embodiment
Probe, including end of probe (1), pole (2) are closed, end of probe (1) is bicylindrical cambered surface prism structure, and circumscribed circle diameter is 6
Millimeter, end of probe (1) is high 30 millimeters, and it is internal equipped with 3 dynamic pressure transducers, 1 dynamic temperature sensor, probe
The top surface (3) in portion (1) is vertical with probe pole (2) rotation axis.Before the windward side of end of probe (1) is included just during probe measurement
Cylinder cambered surface (4), left side plan (5) and right side plan (6), lee face are rear cylinder cambered surface (7)；Dynamic temperature sensor head
(8) top surface (3) is exposed；1 is respectively provided with the just preceding cylinder cambered surface (4) of end of probe (1), left side plan (5) and right side plan (6)
Pressure experience hole, respectively mesopore (9), left hole (10), right hole (11), this 3 not connected pressure experience holes, respectively with spy
3 dynamic pressure transducers connection in needle section (1).
Probe pole (2) is cylinder, and 8 millimeters of diameter is provided with round passage, 5 millimeters of diameter inside it.
End of probe (1) mesopore (9) center line, temperature sensor head (8) center line and probe pole (2) axis are same
In one plane, with right side plan (6) along the plane symmetry, left hole (10) and right hole (11) are along the plane pair for left side plan (5)
Claim distribution.The distance on left hole (10) center of circle and just preceding cylinder cambered surface (4) left side is 3 millimeters, right hole (11) center of circle and just preceding cylinder
Distance on the right of cambered surface (4) is 3 millimeters.
Left side plan (5) and right side plan (6) angle are 45 °, the arc length 1 of the just preceding cylinder cambered surface (4) of end of probe (1)
Millimeter.
Dynamic temperature sensor head (8) exposes (3) 2 millimeters of top surface.
Mesopore (9) center of circle is 2 millimeters with the distance of end of probe (1) top surface (3).
The center of circle of mesopore (9), left hole (10) and right hole (11) in approximately the same plane, a diameter of 0.6 millimeter.
3 dynamic pressure transducers in end of probe (1), the cable (12) of 1 dynamic temperature sensor are through probe branch
Bar (2) internal channel, is drawn by probe tails.
The dynamic temperature force combination probe in across the sound Two Dimensional Unsteady flow field of measurement introduced in the embodiment of the present invention, passes through
Transonic speed calibration wind tunnel is demarcated, and can obtain nominal data.During actual measurement transonic speed Two Dimensional Unsteady flow field, the dynamic temperature
3 dynamic pressure transducers of force combination probe, 1 dynamic temperature sensor measure the unsteady pressure each experienced simultaneously
Power, unsteady temperature data, using the transonic speed calibration wind tunnel nominal data for obtaining, carry out data processing, can obtain across sound
Temperature of incoming flow, stagnation pressure, static pressure, deflection angle, Mach number and two-dimension speed change with time.
Claims (8)
1. a kind of dynamic temperature force combination probe for measuring across sound Two Dimensional Unsteady flow field, it is characterised in that：Including probe
Portion (1), pole (2), the end of probe (1) are bicylindrical cambered surface prism structure, and it is internal equipped with 3 dynamic pressure sensings
Device, 1 dynamic temperature sensor, the top surface (3) of end of probe (1) are vertical with probe pole (2) rotation axis.During probe measurement
The windward side of end of probe (1) includes that just preceding cylinder cambered surface (4), left side plan (5) and right side plan (6), lee face are round after being
Post cambered surface (7)；Dynamic temperature sensor head (8) exposes top surface (3)；In the just preceding cylinder cambered surface (4) of end of probe (1), left side
Plane (5) and right side plan (6) are respectively provided with 1 pressure experience hole, respectively mesopore (9), left hole (10), right hole (11), this 3
Not connected pressure experience hole, connects with 3 dynamic pressure transducers in end of probe (1) respectively.
2. a kind of dynamic temperature force combination probe for measuring across sound Two Dimensional Unsteady flow field according to claim 1, its
It is characterised by：Probe pole (2) is cylinder, and circular channel is provided with inside it.
3. a kind of dynamic temperature force combination probe for measuring across sound Two Dimensional Unsteady flow field according to claim 1, its
It is characterised by：End of probe (1) mesopore (9) center line, temperature sensor head (8) center line and probe pole (2) axis exist
In approximately the same plane, with right side plan (6) along the plane symmetry, left hole (10) and right hole (11) are along the plane for left side plan (5)
It is symmetrical.
4. a kind of dynamic temperature force combination probe for measuring across sound Two Dimensional Unsteady flow field according to claim 1, its
It is characterised by：Left side plan (5) and right side plan (6) angle are 32 ° to 76 °, the just preceding cylinder cambered surface (4) of end of probe (1)
Arc length be 1 millimeter to 2 millimeters.
5. a kind of dynamic temperature force combination probe for measuring across sound Two Dimensional Unsteady flow field according to claim 1, its
It is characterised by：Dynamic temperature sensor head (8) exposes (3) 1 millimeters to 3 millimeters of top surface.
6. a kind of dynamic temperature force combination probe for measuring across sound Two Dimensional Unsteady flow field according to claim 1, its
It is characterised by：Mesopore (9) center of circle is 1 millimeter to 5 millimeters with end of probe (1) top surface (3) distance.
7. a kind of dynamic temperature force combination probe for measuring across sound Two Dimensional Unsteady flow field according to claim 1, its
It is characterised by：A diameter of 0.6 millimeter to 1.5 millimeters of mesopore (9), left hole (10) and right hole (11).
8. a kind of dynamic temperature force combination probe for measuring across sound Two Dimensional Unsteady flow field according to claim 1, its
It is characterised by：3 dynamic pressure transducers in end of probe (1), the cable (12) of 1 dynamic temperature sensor are through probe branch
Bar (2) internal channel, is drawn by probe tails.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710136639.6A CN106908191B (en) | 2017-03-09 | 2017-03-09 | Dynamic temperature and pressure combined probe for measuring transonic two-dimensional unsteady flow field |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710136639.6A CN106908191B (en) | 2017-03-09 | 2017-03-09 | Dynamic temperature and pressure combined probe for measuring transonic two-dimensional unsteady flow field |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106908191A true CN106908191A (en) | 2017-06-30 |
| CN106908191B CN106908191B (en) | 2020-11-13 |
Family
ID=59186281
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710136639.6A Active CN106908191B (en) | 2017-03-09 | 2017-03-09 | Dynamic temperature and pressure combined probe for measuring transonic two-dimensional unsteady flow field |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106908191B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108195510A (en) * | 2018-01-23 | 2018-06-22 | 中国航空工业集团公司北京长城计量测试技术研究所 | A kind of hot air wind tunnel calibration method of hot diaphragm type shear stress sensor |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201583369U (en) * | 2009-11-19 | 2010-09-15 | 东方电气集团东方汽轮机有限公司 | Multi-stage turbine test interstage measuring device |
| CN103267626A (en) * | 2013-06-03 | 2013-08-28 | 北京国电龙源环保工程有限公司 | Multifunctional detecting device for flow field measurement and detecting method applying same |
| CN104048808A (en) * | 2013-03-14 | 2014-09-17 | 中国科学院工程热物理研究所 | Dynamic entropy probe |
| CN104713693A (en) * | 2014-12-15 | 2015-06-17 | 中国燃气涡轮研究院 | Pressure-leading type supersonic velocity five-hole probe with orthogonal auxiliary holes |
| 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 |
| CN105716788A (en) * | 2015-11-02 | 2016-06-29 | 北京航空航天大学 | Three-hole transonic speed pressure probe |
| CN105716779A (en) * | 2015-11-02 | 2016-06-29 | 北京航空航天大学 | Dynamic pressure blade type probe |
| CN105890804A (en) * | 2016-04-08 | 2016-08-24 | 北京航空航天大学 | Method of improving airflow total temperature measurement precision of temperature sensor |
-
2017
- 2017-03-09 CN CN201710136639.6A patent/CN106908191B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201583369U (en) * | 2009-11-19 | 2010-09-15 | 东方电气集团东方汽轮机有限公司 | Multi-stage turbine test interstage measuring device |
| CN104048808A (en) * | 2013-03-14 | 2014-09-17 | 中国科学院工程热物理研究所 | Dynamic entropy probe |
| CN103267626A (en) * | 2013-06-03 | 2013-08-28 | 北京国电龙源环保工程有限公司 | Multifunctional detecting device for flow field measurement and detecting method applying same |
| CN104713693A (en) * | 2014-12-15 | 2015-06-17 | 中国燃气涡轮研究院 | Pressure-leading type supersonic velocity five-hole probe with orthogonal auxiliary holes |
| CN105716788A (en) * | 2015-11-02 | 2016-06-29 | 北京航空航天大学 | Three-hole transonic speed pressure probe |
| CN105716779A (en) * | 2015-11-02 | 2016-06-29 | 北京航空航天大学 | Dynamic pressure blade type 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 |
| CN105890804A (en) * | 2016-04-08 | 2016-08-24 | 北京航空航天大学 | Method of improving airflow total temperature measurement precision of temperature sensor |
Non-Patent Citations (1)
| Title |
|---|
| 向宏辉 等: "叶型探针对轴流压气机性能试验结果的影响", 《燃气涡轮试验与研究》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108195510A (en) * | 2018-01-23 | 2018-06-22 | 中国航空工业集团公司北京长城计量测试技术研究所 | A kind of hot air wind tunnel calibration method of hot diaphragm type shear stress sensor |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106908191B (en) | 2020-11-13 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US9429481B2 (en) | Apparatus and method for measuring total air temperature within an airflow | |
| CN106768824A (en) | A kind of three pore pressure force probes comb | |
| CN106768826A (en) | A kind of dynamic temperature force combination probe for measuring Supersonic Two Dimensional Unsteady flow field | |
| CN106989896A (en) | A kind of dynamic temperature force combination probe for measuring subsonics three-dimensional non-steady flow field | |
| CN212082825U (en) | Full-parameter probe for measuring high subsonic three-dimensional steady flow field | |
| CN106949989A (en) | A kind of hemispherical head steady temperature force combination probe for measuring low speed three-dimensional flow field | |
| CN106908191A (en) | A kind of dynamic temperature force combination probe for measuring across sound Two Dimensional Unsteady flow field | |
| CN107014434B (en) | Cone head steady-state temperature and pressure combined probe for measuring high subsonic three-dimensional flow field | |
| CN106871968A (en) | One kind measurement subsonic speed flow field multiple spot stagnation temperature stagnation pressure octal probe | |
| CN106918437A (en) | A kind of four hole probes for measuring subsonic speed two-dimensional flow field | |
| CN111089703A (en) | Full-parameter probe for measuring two-dimensional steady-state flow field of boundary layer of outer wall of hub | |
| CN107063340B (en) | Steady-state temperature and pressure combined probe for measuring supersonic three-dimensional flow field | |
| CN106840510A (en) | A kind of steady temperature force combination probe for measuring supersonic speed two-dimensional flow field | |
| CN106940241A (en) | A kind of steady temperature force combination probe for measuring transonic speed three-dimensional flow field | |
| CN106885681A (en) | A kind of monocline hole dynamic pressure probe for measuring rotor outlet subsonics three-dimensional flow field | |
| CN106768827A (en) | A kind of steady temperature force combination probe for measuring transonic speed two-dimensional flow field | |
| CN106840594B (en) | A kind of four hole dynamic pressure probes measuring transonic speed three-dimensional non-steady flow field | |
| CN212082771U (en) | Full-parameter probe for measuring two-dimensional steady-state flow field of boundary layer of outer wall of hub | |
| CN106840513A (en) | A kind of stagnation pressure blade profile probe | |
| CN111141522A (en) | Full-parameter probe for measuring high subsonic three-dimensional steady flow field | |
| CN106768825B (en) | Three-hole dynamic pressure probe for measuring supersonic two-dimensional unsteady flow field | |
| CN106679879A (en) | Multi-probe total pressure measuring device for measuring total pressure distribution in flow channel | |
| CN106950003A (en) | A kind of dynamic pressure probe of circular cone single hole for measuring rotor outlet across sound three-dimensional flow field | |
| CN106840272A (en) | A kind of dynamic temperature force combination probe for measuring across sound three-dimensional non-steady flow field | |
| CN106840511B (en) | Cone head four-hole dynamic pressure probe for measuring high subsonic three-dimensional unsteady flow |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |