CN106996848B - Pressure probe adopting single-row-hole air film cooling - Google Patents
Pressure probe adopting single-row-hole air film cooling Download PDFInfo
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- CN106996848B CN106996848B CN201710251001.7A CN201710251001A CN106996848B CN 106996848 B CN106996848 B CN 106996848B CN 201710251001 A CN201710251001 A CN 201710251001A CN 106996848 B CN106996848 B CN 106996848B
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- 239000000523 sample Substances 0.000 title claims abstract description 57
- 238000001816 cooling Methods 0.000 title claims abstract description 30
- 239000007789 gas Substances 0.000 claims abstract 8
- 239000000112 cooling gas Substances 0.000 claims abstract 4
- 230000001939 inductive effect Effects 0.000 claims abstract 4
- 239000004047 hole gas Substances 0.000 claims abstract 2
- 238000007664 blowing Methods 0.000 claims description 4
- 230000007704 transition Effects 0.000 claims 1
- 238000012360 testing method Methods 0.000 abstract description 6
- 238000000034 method Methods 0.000 abstract description 2
- 238000005259 measurement Methods 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000009776 industrial production Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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- 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
- G01L19/06—Means for preventing overload or deleterious influence of the measured medium on the measuring device or vice versa
- G01L19/0681—Protection against excessive heat
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Abstract
本发明公开了一种采用单排孔气膜冷却的压力探针，包括探针头部、支杆、引压管、气膜孔、进气管。所述探针头部与支杆焊接，引压管一端安装在探针头部上的测压孔处，从支杆内部穿出。支杆表面加工气膜孔。进气管根据主流流量与温度，调节送入支杆内部的冷却气体流量与温度，并将低温气体通过输气管送入支杆内部，低温气体从靠近探针头部处开始充满支杆的内部并从气膜孔吹出，形成低温气膜保护探针。通过上述方式，本发明能够在压力探针内部冷却的基础上在探针表面形成冷却气膜，避免高温气流直接与探针表面换热。同时根据来流的流量和温度，调节冷却气流的射流流量和温度，保证冷却效率，防止高温流场测试中高温导致探针损坏。
The invention discloses a pressure probe which adopts single-row-hole gas film cooling, which comprises a probe head, a support rod, a pressure-inducing pipe, a gas film hole and an air inlet pipe. The probe head is welded with the support rod, and one end of the pressure-inducing tube is installed at the pressure measuring hole on the probe head and passes through the interior of the support rod. Air film holes are processed on the surface of the strut. The air inlet pipe adjusts the flow rate and temperature of the cooling gas sent to the inside of the strut according to the mainstream flow rate and temperature, and sends the low-temperature gas into the inside of the strut through the gas delivery pipe. Blow out from the air film hole to form a low temperature air film to protect the probe. Through the above method, the present invention can form a cooling gas film on the surface of the probe on the basis of cooling the inside of the pressure probe, so as to prevent the high-temperature airflow from directly exchanging heat with the surface of the probe. At the same time, according to the flow rate and temperature of the incoming flow, the jet flow rate and temperature of the cooling airflow are adjusted to ensure the cooling efficiency and prevent the probe from being damaged due to high temperature in the high temperature flow field test.
Description
Technical Field
The invention relates to the technical field of high-temperature flow field testing, in particular to a pressure probe cooled by a single-row-hole air film, which can prevent the probe from being damaged by high-temperature incoming flow in the high-temperature flow field testing.
Background
In experiments or industrial production, pressure in a high-temperature flow field is often required to be measured, however, a common pressure probe has no cooling device, and if the high-temperature flow field is directly measured, the probe is often deformed or even broken due to too high temperature. In order to increase the temperature that the probe can withstand, cooling protection must be provided. Compared with various cooling methods developed at present, the research on the air cooling direction is more, and the research mainly comprises convection cooling, impingement cooling, column rib cooling and the like, and air film cooling and the like. The probe used for the high-temperature flow field test is reasonably cooled and designed, so that the probe can be prevented from being damaged by high temperature, and the test task is completed.
Disclosure of Invention
The invention mainly solves the technical problem of providing a pressure probe cooled by a single-row-hole air film, which can reduce the temperature of the probe through an air film cooling technology, and can effectively protect the probe through the air film when the incoming flow direction is more stable, thereby realizing the measurement in a high-temperature flow field.
In order to solve the technical problems, the invention adopts a technical scheme that:
there is provided a pressure probe cooled by a single row of holes film, comprising: probe head, branch, pressure tube, air film hole, changeover portion, intake pipe. The probe head is welded with the supporting rod, the number of the pressure guiding pipes corresponds to the number of the holes in the probe head, one end of each pressure guiding pipe is arranged at the pressure measuring hole in the probe head, and the other end of each pressure guiding pipe penetrates through the supporting rod and extends out of the hole in the switching section.
Further, a gas film hole is processed on the surface of the support rod, low-temperature gas is sent into the support rod through the gas inlet pipe, the low-temperature gas is blown out of the gas film hole and attached to the surface of the support rod under the action of incoming flow, and therefore the low-temperature gas film is formed and the probe is prevented from being damaged by high-temperature incoming flow.
Furthermore, the air inlet pipe needs to adjust the flow and the temperature of the cooling air sent into the support rod according to the main flow and the temperature, so that the proper air blowing ratio and temperature ratio are kept.
Further, the pressure probe head has an outer diameter of 4 to 8 mm and a length of 10 to 15 mm.
Furthermore, the included angle between the axis of the air film hole and the dead point on the probe supporting rod is +/-10 degrees to +/-45 degrees, and the hole is a circular hole with the diameter of 0.5 to 1 mm.
Furthermore, the included angle between the axis direction of the air film holes and the axis direction of the supporting rod is 30 degrees to 60 degrees, the distance between the air film holes and the two ends of the supporting rod are 1.5 millimeters to 5 millimeters, the air film holes are coordinated with the hole diameter, and the distance ratio is ensured to be 3 to 5.
Furthermore, the inner diameter of the supporting rod is 2-5 mm, the wall thickness is 1.5-4 mm, and the length-diameter ratio is ensured to be 3-5 according to the coordination of the aperture and the included angle between the axis direction of the air film hole and the axis direction of the supporting rod.
Furthermore, the air inlet pipe is adjusted according to the main flow, and the air blowing ratio of the air film hole is ensured to be 0.4-1.5.
Further, the air inlet pipe adjusts the temperature of the cooling air according to the temperature of the main flow, and the ratio of the temperature of the cooling air flow to the temperature of the main flow is guaranteed to be 0.4-1.
The invention has the beneficial effects that: the invention forms a cooling air film on the surface of the pressure probe on the basis of internal cooling of the pressure probe, and directly transfers heat between high-temperature airflow and the surface of the probe in an area covered by the air film to form a three-temperature heat transfer system of the high-temperature airflow, the cooling air film and the surface of the probe. Meanwhile, the jet flow and the temperature of cooling air flow are adjusted according to the flow and the temperature of incoming flow, the cooling efficiency is ensured, and the probe damage caused by high temperature in a high-temperature flow field test is prevented.
Drawings
FIG. 1 is a schematic diagram of a preferred embodiment of a pressure probe employing single row hole film cooling;
FIG. 2 is a cross-sectional view of a pressure probe film hole with single row hole film cooling;
the parts in the drawings are numbered as follows: 1. a probe head; 2. a strut; 3. a pressure guiding pipe; 4. a gas film hole; 5. a switching section; 6. an air inlet pipe.
Detailed Description
The following detailed description of the preferred embodiments of the present invention, taken in conjunction with the accompanying drawings, will make the advantages and features of the invention easier to understand by those skilled in the art, and thus will clearly and clearly define the scope of the invention.
As shown in fig. 1, a pressure probe employing single row hole film cooling, comprising: the probe comprises a probe head (1), a support rod (2), a pressure leading pipe (3), a gas film hole (4), a switching section (5) and an air inlet pipe (6). The probe head (1) is welded with the supporting rod (2), the number of the pressure guiding pipes (3) corresponds to the number of the holes on the probe head (1), one end of each pressure guiding pipe is arranged at the pressure measuring hole on the probe head (1), and the other end of each pressure guiding pipe penetrates through the supporting rod (2) and extends out of the hole on the switching section (5).
The probe head (1) has an outer diameter of 4 mm and a length of 12 mm. An air film hole (4) is formed at the position of +/-15 degrees between the probe supporting rod (2) and a stagnation point, and the hole is a circular hole with the diameter of 0.6 mm. The included angle between the axial direction of the air film holes (4) and the axial direction of the supporting rod (2) is 30 degrees, and the distance between the air film holes is 2.4 millimeters. The inner diameter of the support rod (2) is 5 mm, the wall thickness is 1.5 mm, and the length is 50 mm.
The pressure probe adopting single-row-hole air film cooling introduced by the embodiment has the advantages that the air film hole distance ratio is 4 by reasonably selecting the parameters of the air film holes, the length-diameter ratio is about 3.8, the cooling efficiency is better, when the flow field is actually measured, the jet flow and the temperature are adjusted according to the main flow parameters, the cooling efficiency of the low-temperature air film is ensured, the probe is prevented from being damaged by high-temperature incoming flow, the head of the probe is avoided by the air film, the interference of jet flow on measurement is avoided, and the probe can be stably and continuously measured in the high-temperature flow field.
The above description is only an embodiment of the present invention, and not intended to limit the scope of the present invention, and all modifications of equivalent structures and equivalent processes performed by the present specification and drawings, or directly or indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (1)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710251001.7A CN106996848B (en) | 2017-04-18 | 2017-04-18 | Pressure probe adopting single-row-hole air film cooling |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710251001.7A CN106996848B (en) | 2017-04-18 | 2017-04-18 | Pressure probe adopting single-row-hole air film cooling |
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| Publication Number | Publication Date |
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| CN106996848A CN106996848A (en) | 2017-08-01 |
| CN106996848B true CN106996848B (en) | 2020-05-22 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201710251001.7A Active CN106996848B (en) | 2017-04-18 | 2017-04-18 | Pressure probe adopting single-row-hole air film cooling |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109238511A (en) * | 2018-07-19 | 2019-01-18 | 中国航发沈阳发动机研究所 | A kind of temperature test detector probe |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS599531A (en) * | 1982-07-09 | 1984-01-18 | Hitachi Ltd | Pressure detecting device |
| CN201177544Y (en) * | 2008-03-14 | 2009-01-07 | 东南大学 | Anti-clogging pressure tube |
| CN103398815A (en) * | 2013-08-01 | 2013-11-20 | 哈尔滨东安发动机（集团）有限公司 | Pressure probe |
| CN103452595A (en) * | 2013-09-25 | 2013-12-18 | 青岛科技大学 | A Novel Air Film Hole for Improving Cooling Efficiency |
| CN105841917A (en) * | 2016-03-16 | 2016-08-10 | 北京航天长征飞行器研究所 | Supersonic flow field total pressure measurement device and measurement method thereof |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP6063240B2 (en) * | 2012-12-13 | 2017-01-18 | サーパス工業株式会社 | Amplifier built-in pressure sensor |
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2017
- 2017-04-18 CN CN201710251001.7A patent/CN106996848B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS599531A (en) * | 1982-07-09 | 1984-01-18 | Hitachi Ltd | Pressure detecting device |
| CN201177544Y (en) * | 2008-03-14 | 2009-01-07 | 东南大学 | Anti-clogging pressure tube |
| CN103398815A (en) * | 2013-08-01 | 2013-11-20 | 哈尔滨东安发动机（集团）有限公司 | Pressure probe |
| CN103452595A (en) * | 2013-09-25 | 2013-12-18 | 青岛科技大学 | A Novel Air Film Hole for Improving Cooling Efficiency |
| CN105841917A (en) * | 2016-03-16 | 2016-08-10 | 北京航天长征飞行器研究所 | Supersonic flow field total pressure measurement device and measurement method thereof |
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| CN106996848A (en) | 2017-08-01 |
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