CN108267295B - A kind of flow control jet pipe - Google Patents
A kind of flow control jet pipe Download PDFInfo
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- CN108267295B CN108267295B CN201711422731.5A CN201711422731A CN108267295B CN 108267295 B CN108267295 B CN 108267295B CN 201711422731 A CN201711422731 A CN 201711422731A CN 108267295 B CN108267295 B CN 108267295B
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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
- G01M10/00—Hydrodynamic testing; Arrangements in or on ship-testing tanks or water tunnels
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- General Physics & Mathematics (AREA)
- Jet Pumps And Other Pumps (AREA)
Abstract
The invention discloses a kind of flow control jet pipes, it includes pressure-stabilizing section, jet pipe assembled unit, plate unit and diffuser, the jet pipe assembled unit includes the two-dimensional nozzle of the three-dimensional nozzle and combination at center on the three-dimensional nozzle side wall, the plate unit is mounted on the inlet of the jet pipe assembled unit, it includes that can block single plate of two-dimensional nozzle entrance and can block the two-dimensional nozzle entrance again that double plates of the three-dimensional nozzle entrance can be blocked, the stable section is the cylinder with the entrance same shape of the jet pipe assembled unit, the diffuser is the cylinder that same shape is exported with the jet pipe assembled unit.The present invention solves the problems, such as that gas flowing span of control is difficult to control accurately greatly.Nozzle structure of the invention is compact, block design, and combination control is easy to overhaul and safeguard.
Description
Technical field
The present invention relates to a kind of supersonic nozzle, especially a kind of jet pipe adjusted for gas flow high-precision.
Background technique
Nuclear power generating equipment development at present needs to carry out gas entrained liquids test, and different tests operating condition gas flow span is big,
With going deep into for research, test accuracy demand is gradually increased, and due to there is biphase gas and liquid flow during the test, liquid is free and easy inverse
Stream, the reverse propagation phenomenon of gas sound wave, cause gas pressure and instability of flow state, so that the precision of gas entrainment test is not
Height need to provide a kind of high-precision gas flow regulating system to provide gas entrainment test precision.
It is to be adjusted response valve using flowmeter feedback signal to regulating valve and opened that gas flow, which adjusts first method,
Degree and position are adjusted, and then adjust flow, and this method advantage is that system is simple, easy to operate, the disadvantage is that flowing within the scope of large span
Meter precision is not high, and regulating valve voltage adjustment characteristic determines that it can not work normally in large span range of flow, and it is even more impossible to realize gas
Liquid two-phase high-precision control.Second is using flow controller, and basic principle is identical as first method, is by flow
Meter is integrated with regulating valve, by automatically controlled signal processing controller upstream and downstream flow, this method advantage and disadvantage and the first phase
Together.The third method is to realize that gas flow is adjusted in such a way that regulating valve is combined with throttling set, common throttling dress
It is set to orifice plate, velocity of sound flowing is formed using orifice plate tapping and throttles, prevent downstream pressure influence of fluctuations, then pass through regulating valve
The certain level that regulating gas pressure keeps gas flow stable, this method advantage are to stabilize orifice plate downstream flow to a certain extent
Influence to upstream provides relatively stable downstream flow field, the disadvantage is that orifice plate throat flow fluctuation, which limits flow, adjusts essence
Degree.
Therefore, to improve gas entrainment test gas flow degree of regulation, flow disturbance and large span flow tune need to be solved
Section problem.
Summary of the invention
The present invention overcomes the deficiencies of the prior art and provide a kind of novel ultrasonic speed jet pipe, which shields throat downstream stream
Dynamic disturbance guarantees that upstream flow dynamic height is stablized, and can work in large span range of flow, solves flow disturbance and large span flow
Regulation problem.
Flow control jet pipe of the invention includes pressure-stabilizing section, jet pipe assembled unit, plate unit and diffuser, the jet pipe
Assembled unit includes the two-dimensional nozzle of the three-dimensional nozzle and combination at center on the three-dimensional nozzle side wall, the plate unit peace
Mounted in the inlet of the jet pipe assembled unit comprising single plate of two-dimensional nozzle entrance can be blocked and institute can be blocked
Double plates of the three-dimensional nozzle entrance can be blocked by stating two-dimensional nozzle entrance again, and the stable section is and the jet pipe assembled unit
Entrance same shape cylinder, the diffuser be with the jet pipe assembled unit export same shape cylinder.
It is preferred that the three-dimensional nozzle at the center is Laval nozzle, the overall profile of lateral wall is cuboid, respectively with
Four side walls up and down of the Laval nozzle are that bottom wall is formed there are four two-dimensional nozzle, and upper and lower two two-dimensional nozzles are distinguished
Single plate is installed, can be inserted or pull out respectively by single plate and respective entire entrance is blocked or opened
It puts, two two-dimensional nozzles in left and right are separately installed with double plates, and left side binary spray can be blocked or be opened to double plates on the left side
The entrance of pipe, and the entrance of the left semicircle of the Laval nozzle can be blocked or open, double plates on the right can be blocked
Or the entrance of open right side two-dimensional nozzle, and can block or open the entrance of the right semi-circle of the Laval nozzle.
It is preferred that the throat position of four two-dimensional nozzles is identical as the throat position of the Laval nozzle.
It is preferred that two two-dimensional nozzles are symmetrical arranged up and down, the two-dimensional nozzle of left and right two is symmetrical arranged, upper and lower two
Throat's width of first jet pipe is less than throat's width of two two-dimensional nozzles in left and right.
Preferred center three-dimensional nozzle is 10%~50% for realizing centre portion, that is, the most frequently used operating condition of test flow
Control, top two-dimensional nozzle and control of the lower part two-dimensional nozzle for realizing the flow < 10% of small quantity operating condition of test, center
Three-dimensional nozzle is 50%~100% for realizing the flow of big flow operating condition of test with left part two-dimensional nozzle and right part two-dimensional nozzle
Control.
It is preferred that being provided with closed loss of weight chamber between the inner mold wall and lateral wall of the Laval nozzle.
The invention has the following advantages over the prior art:
(1) the reverse propagation interference problem of gas flow downstream flowing is solved；
(2) solve the problems, such as that gas flowing span of control is difficult to control accurately greatly；
(3) nozzle structure is compact, block design, and combination control is easy to overhaul and safeguard.
Detailed description of the invention
Fig. 1 is nozzle structure schematic diagram of the present invention；
Fig. 2 is jet pipe left view of the present invention；
Fig. 3 is jet pipe stable section profiled-cross-section figure of the present invention；
Fig. 4 is nozzle flow passage entrance section figure of the present invention；
Fig. 5 is nozzle throat sectional view of the present invention.
Specific embodiment
Invention is further described in detail with reference to the accompanying drawings and detailed description.
As shown in Figure 1, gas flow controls nozzle structure schematic diagram, which includes pressure-stabilizing section 1, upper gate valve 2, right inserts
Plate valve 3, underthrust plate valve 4, left gate valve 5, top two-dimensional nozzle 6, right part two-dimensional nozzle 7, lower part two-dimensional nozzle 8, left part binary
Jet pipe 9, nozzle structure block 10, center three-dimensional nozzle 11, diffuser 12；Wherein 1 main function of pressure-stabilizing section is to reduce gas spraying
The flowing velocity of tube inlet improves airflow stability, reduces turbulivity, and 1 front of stable section is circular configuration, rear portion and upper plate
Valve 2, right gate valve 3, underthrust plate valve 4, left gate valve 5 front end junction gradually transition be it is abnormally-structured, as shown in Figure 2.On
Gate valve 2, right gate valve 3, underthrust plate valve 4, left gate valve 5 along 1 rear portion of pressure-stabilizing section circumferentially, upper gate valve 2, right gate valve
3, underthrust plate valve 4, the respective plate seat of left gate valve 5 and stable section 1 guarantee gas without leakage, upper plate by being welded to connect
Valve 2, right gate valve 3, underthrust plate valve 4, the respective plate seat of left gate valve 5 respectively with top two-dimensional nozzle 6, right part two-dimensional nozzle
7, lower part two-dimensional nozzle 8, left part two-dimensional nozzle 9 and by being welded to connect, center three-dimensional nozzle 11 and circumferential top two-dimensional nozzle
6, right part two-dimensional nozzle 7, lower part two-dimensional nozzle 8,9 runner of left part two-dimensional nozzle share nozzle structure block 10, and are connected by welding
Connect, three-dimensional nozzle 11 inner mold face in center is made of 10 inner face of nozzle structure block, top two-dimensional nozzle 6, right part two-dimensional nozzle 7, under
Portion's two-dimensional nozzle 8,9 planar section of left part two-dimensional nozzle outside nozzle structure block 10 by constituting, the closed chamber of nozzle structure block 10
For loss of weight.Top two-dimensional nozzle 6, right part two-dimensional nozzle 7, lower part two-dimensional nozzle 8, left part two-dimensional nozzle 9 are respectively provided with independence
Outer mold surface, center three-dimensional nozzle 11 and circumferential top two-dimensional nozzle 6, right part two-dimensional nozzle 7, lower part two-dimensional nozzle 8, left part two
For first jet pipe 9 by being welded to connect, top two-dimensional nozzle 6, right part two-dimensional nozzle 7, lower part two-dimensional nozzle 8, left part two-dimensional nozzle 9 are logical
Welding is crossed to connect with diffuser 12.Top two-dimensional nozzle 6, right part two-dimensional nozzle 7, lower part two-dimensional nozzle 8, left part two-dimensional nozzle 9
And supersonic flows can be achieved in center three-dimensional nozzle 11, upper gate valve 2, right gate valve 3, underthrust plate valve 4, left gate valve 5 divide
Not Fu Ze top two-dimensional nozzle 6, right part two-dimensional nozzle 7, lower part two-dimensional nozzle 8, left part two-dimensional nozzle 9 state control, wherein
The valve plate of right gate valve 3 and left gate valve 5 can continue elongation to 11 entrance center of center three-dimensional nozzle, formed and sprayed to center ternary
The state of pipe 11 is managed.Center three-dimensional nozzle 11 is also the flow of the most frequently used operating condition of test for realizing intermediate flow section
(10%~50%) it controls, top two-dimensional nozzle 6 is with lower part two-dimensional nozzle 8 for realizing the flow (< of small quantity operating condition of test
10%) it controls, center three-dimensional nozzle 11 and right part two-dimensional nozzle 7 and left part two-dimensional nozzle 9 are for realizing big flow operating condition of test
Flow control (50%~100%).In small flow test operating condition, right gate valve 3 and left gate valve 5 are closed until by center
11 entrance of three-dimensional nozzle is closed, and gate valve 2 or underthrust plate valve 4 (according to actual flow needs, can open simultaneously) can be real in unlatching
Existing small-flow gas flow control, when carrying out conventional typical test conditions, gate valve 2 and underthrust plate valve 4 in closing make right insert
Plate valve 3 and left gate valve 5 is half-open fully opens to 11 entrance of center three-dimensional nozzle, and right part two-dimensional nozzle 7 and the spray of left part binary
9 entrance of pipe is in close state, and conventional type testing gas flow control can be realized using center three-dimensional nozzle 11.Work as needs
When carrying out the adjusting test of greater flow gas flow, make right gate valve 3 and 5 standard-sized sheet of left gate valve to center three-dimensional nozzle 11, the right side
Portion's two-dimensional nozzle 7 and 9 entrance of left part two-dimensional nozzle fully open, and runner is flowed out with supersonic flows at three, realize bigger stream
Measure Control experiment demand.Upper gate valve 2, right gate valve 3, underthrust plate valve 4, left gate valve 5 are all fully opened, can be realized
Runner is all flowed out with supersonic flows at five, realizes maximum stream flow Control experiment demand.
Supersonic nozzle throat can generate velocity of sound flowing, throat's downstream ultrasonic speed flowing, according to fluid mechanics principle, ultrasound
Fast Field Characteristics line only downstream extends, that is, disturbance can only streamwise propagate, and cannot inversely propagate, therefore, benefit
The interference that jet pipe front end is flowed with this characteristic maskable downstream disturbances of supersonic nozzle, in addition, supersonic nozzle flows
There is direct relation with jet pipe upstream and downstream pressure ratio, the supersonic nozzle design that the present invention designs fully considers and utilizes this spy
Property, enable the variation of the pressure ratio in entire flow adjustment range that jet pipe to be made to be in supersonic flows state, present invention design
Supersonic nozzle do not require upstream pressure to remain unchanged, be adapted to the changed operating condition of test of upstream pressure.
The gas of certain pressure flow parameter in jet pipe can change with the variation of nozzle section product, and of the invention is super
Velocity of sound jet pipe reference design point is that air-flow is made to form the velocity of sound in throat, and stabilizing gas flux is constant, that is, forms throttling, air-flow is along spray
Pipe downstream expansion, which accelerates to reach at throat's expansion, forms one of normal shock wave, and gas pressure adapts to back pressure environment after normal shock wave,
And it is normally flowed out with subsonic speed.With the raising of test gas pressure, gas flow is gradually increased, shock wave by downward downstream,
With the outer shifting of shock wave, wavefront gas flow rate will increase, and shock strength increases, and shock propagation speed increases, gas static pressure warp
Risen to after shock wave and continued in expansion segment with sub-critical flow pressurization and it is finally equal with back pressure, which adaptively matches ring
Border back pressure, and stablize upstream airflow, strength, which is provided, for flow adjusting supports.In addition, jet pipe of the invention is by center three-dimensional nozzle
And two-dimensional nozzle composite construction ensure that the inner mold face of each nozzle unit remains unchanged, no raised step and special-shaped sprue,
The larger problem of cavitation nargin caused by fundamentally avoiding single nozzle throat from adjusting, be also avoided that one by one to single spraying pipe more
Change problem.Jet pipe of the invention can keep entry condition such as pressure significantly to adjust without significantly adjusting and being able to achieve flow
Technical problem, so that control valve is in best effort section always, guarantee adjust high-precision.
The content that description in the present invention is not described in detail belongs to the well-known technique of those skilled in the art.
Claims (4)
1. a kind of flow control jet pipe, it is characterised in that: including stable section, jet pipe assembled unit, plate unit and diffuser, institute
State the three-dimensional nozzle and combine the two-dimensional nozzle on the three-dimensional nozzle side wall, the plate that jet pipe assembled unit includes center
Unit is mounted on the inlet of the jet pipe assembled unit, including that can block single plate of two-dimensional nozzle entrance and can either hide
Double plates of the three-dimensional nozzle entrance can be blocked by keeping off the two-dimensional nozzle entrance again, and the stable section is to combine with the jet pipe
The cylinder of the entrance same shape of unit, the diffuser are the cylinder that same shape is exported with the jet pipe assembled unit；
The three-dimensional nozzle at the center is Laval nozzle, and the overall profile of lateral wall is cuboid, respectively with the Lavalle
Four side walls up and down of jet pipe are that bottom wall is formed there are four two-dimensional nozzle, and upper and lower two two-dimensional nozzles are separately installed with described
Single plate is inserted or pull out by single plate respectively and respective entire entrance is blocked or opened, two binary in left and right
Jet pipe is separately installed with double plates, and the entrance of left side two-dimensional nozzle is blocked or opened to double plates on the left side, and block or
The entrance of right side two-dimensional nozzle is blocked or opened to the entrance of the left semicircle of the open Laval nozzle, double plates on the right, and
And block or open the entrance of the right semi-circle of the Laval nozzle；
The throat position of four two-dimensional nozzles is identical as the throat position of the Laval nozzle.
2. flow control jet pipe as described in claim 1, it is characterised in that: two two-dimensional nozzles up and down are symmetrically set
It sets, the two-dimensional nozzle of left and right two is symmetrical arranged, and throat's width of upper and lower two-dimensional nozzle is less than the two-dimensional nozzle of left and right two
Throat's width.
3. flow control jet pipe as claimed in claim 2, it is characterised in that: the center three-dimensional nozzle is for realizing middle area
Section is the control that the flow of the most frequently used operating condition of test is 10%~50%, top two-dimensional nozzle and lower part two-dimensional nozzle for realizing
The control of the flow < 10% of small quantity operating condition of test, center three-dimensional nozzle are used for left part two-dimensional nozzle and right part two-dimensional nozzle
The flow for realizing big flow operating condition of test is 50%~100% control.
4. flow control jet pipe as claimed in any one of claims 1-3, it is characterised in that: in the Laval nozzle
Closed loss of weight chamber is provided between type wall and lateral wall.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711422731.5A CN108267295B (en) | 2017-12-25 | 2017-12-25 | A kind of flow control jet pipe |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711422731.5A CN108267295B (en) | 2017-12-25 | 2017-12-25 | A kind of flow control jet pipe |
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| Publication Number | Publication Date |
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| CN108267295A CN108267295A (en) | 2018-07-10 |
| CN108267295B true CN108267295B (en) | 2019-10-18 |
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| CN201711422731.5A Active CN108267295B (en) | 2017-12-25 | 2017-12-25 | A kind of flow control jet pipe |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110767568B (en) * | 2018-07-26 | 2022-05-27 | 北京北方华创微电子装备有限公司 | Pressure regulating assembly, lower electrode device, process chamber and semiconductor processing equipment |
| CN115095449A (en) * | 2022-06-10 | 2022-09-23 | 西北工业大学 | Adjustable geometric throat with vector adjustment for axisymmetric rocket-ramjet combined engine |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1308506A (en) * | 1970-07-21 | 1973-02-21 | Secr Defence | Jet noise suppression means |
| US4930308A (en) * | 1986-08-11 | 1990-06-05 | The Dee Howard Co. | Double-flow turboshaft engine with variable confluent nozzle |
| CN102094704A (en) * | 2011-01-27 | 2011-06-15 | 康跃科技股份有限公司 | Multi-nozzle type variable flow rate supercharging device |
| CN102998085A (en) * | 2012-12-31 | 2013-03-27 | 中国人民解放军国防科学技术大学 | Mixing spray pipe runner wall face determination method, mixing spray pipe and supersonic speed mixing wind tunnel |
| CN103115027A (en) * | 2013-02-05 | 2013-05-22 | 中国人民解放军国防科学技术大学 | Supersonic velocity circular flow nozzle with injector |
| CN104535122A (en) * | 2014-12-31 | 2015-04-22 | 西安交通大学 | Critical flow venturi nozzle with throat inserting plate and with adjustable throat area |
| CN106121865A (en) * | 2016-03-14 | 2016-11-16 | 中国运载火箭技术研究院 | A kind of solid rocket ramjet gas flow self-checking device |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10371093B2 (en) * | 2013-03-08 | 2019-08-06 | Rolls-Royce North American Technologies Inc. | Aircraft nozzle with a variable nozzle area of a second flow path |
-
2017
- 2017-12-25 CN CN201711422731.5A patent/CN108267295B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1308506A (en) * | 1970-07-21 | 1973-02-21 | Secr Defence | Jet noise suppression means |
| US4930308A (en) * | 1986-08-11 | 1990-06-05 | The Dee Howard Co. | Double-flow turboshaft engine with variable confluent nozzle |
| CN102094704A (en) * | 2011-01-27 | 2011-06-15 | 康跃科技股份有限公司 | Multi-nozzle type variable flow rate supercharging device |
| CN102998085A (en) * | 2012-12-31 | 2013-03-27 | 中国人民解放军国防科学技术大学 | Mixing spray pipe runner wall face determination method, mixing spray pipe and supersonic speed mixing wind tunnel |
| CN103115027A (en) * | 2013-02-05 | 2013-05-22 | 中国人民解放军国防科学技术大学 | Supersonic velocity circular flow nozzle with injector |
| CN104535122A (en) * | 2014-12-31 | 2015-04-22 | 西安交通大学 | Critical flow venturi nozzle with throat inserting plate and with adjustable throat area |
| CN106121865A (en) * | 2016-03-14 | 2016-11-16 | 中国运载火箭技术研究院 | A kind of solid rocket ramjet gas flow self-checking device |
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| CN108267295A (en) | 2018-07-10 |
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