CN108267295A - A kind of flow control jet pipe - Google Patents
A kind of flow control jet pipe Download PDFInfo
- Publication number
- CN108267295A CN108267295A CN201711422731.5A CN201711422731A CN108267295A CN 108267295 A CN108267295 A CN 108267295A CN 201711422731 A CN201711422731 A CN 201711422731A CN 108267295 A CN108267295 A CN 108267295A
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- nozzle
- dimensional
- dimensional nozzle
- jet pipe
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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
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 can blocking single plate of two-dimensional nozzle entrance and can block the two-dimensional nozzle entrance can block double plates of the three-dimensional nozzle entrance again, 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 accurately control greatly.The nozzle structure of the present 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, particularly a kind of jet pipe adjusted for gas flow high-precision.
Background technology
Nuclear power generating equipment development at present needs to carry out gas entrained liquids experiment, and different tests operating mode gas flow span is big,
With going deep into for research, test accuracy demand is gradually increased, since there are biphase gas and liquid flow, liquid is free and easy inverse during experiment
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 to provide gas entrainment test precision, need to provide a kind of high-precision gas flow regulating system.
It is using flowmeter feedback signal to regulating valve that gas flow, which adjusts first method, adjusts response valve and is opened
Degree and position are adjusted, and then adjust flow, and this method advantage is simple system, easy to operate, and shortcoming is flowed in the range of large span
Gauge 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 with 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 a manner that throttling set is combined using regulating valve, common throttling dress
Orifice plate is set to, forming velocity of sound flowing using orifice plate tapping throttles, and prevents downstream pressure influence of fluctuations, then pass through regulating valve
The certain level that gas pressure stablizes gas flow is adjusted, this method advantage is to stabilize orifice plate downstream flow to a certain extent
Influence to upstream, provides relatively stable downstream flow field, and shortcoming is that orifice plate throat flow fluctuation limits flow-rate adjustment 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.
Invention content
The present invention overcomes the deficiencies of the prior art and provide a kind of novel ultrasonic speed jet pipe, jet pipe shielding throat downstream stream
Dynamic disturbance ensures 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.
The flow control jet pipe of the present 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, including that can block single plate of two-dimensional nozzle entrance and institute can be blocked
Double plates of the three-dimensional nozzle entrance can be blocked again by stating two-dimensional nozzle entrance, 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 formed for bottom wall 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 with the throat position of the Laval nozzle.
It is preferred that two two-dimensional nozzles are symmetrical arranged up and down, two two-dimensional nozzles in left and right are 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.
The flow that preferred center three-dimensional nozzle is used to implement i.e. the most frequently used operating condition of test of centre portion is 10%~50%
Control, top two-dimensional nozzle are used to implement the control of the flow ＜ 10% of small quantity operating condition of test, center with lower part two-dimensional nozzle
The flow that three-dimensional nozzle is used to implement big flow operating condition of test with left part two-dimensional nozzle and right part two-dimensional nozzle is 50%~100%
Control.
It is preferred that closed loss of weight chamber is provided between the inner mold wall and lateral wall of the Laval nozzle.
The present invention has the following advantages that compared with prior art：
(1) it solves gas flowing downstream flow and inversely propagates interference problem；
(2) solve the problems, such as that gas flowing span of control is difficult to accurately control greatly；
(3) nozzle structure is compact, block design, and combination control is easy to overhaul and safeguard.
Description of the drawings
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
The present invention is described in further detail with reference to the accompanying drawings and detailed description.
As shown in Figure 1, gas flow controls nozzle structure schematic diagram, which inserts including pressure-stabilizing section 1, upper gate valve 2, the right side
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 forepart of stable section is circular configuration, rear portion and upper plate
The gradual transition in front end junction of valve 2, right gate valve 3, underthrust plate valve 4, left gate valve 5 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
3rd, underthrust plate valve 4,5 respective plate seat of left gate valve and stable section 1 ensure gas without leakage, upper plate by being welded to connect
Valve 2, right gate valve 3, underthrust plate valve 4,5 respective plate seat of left gate valve respectively with top two-dimensional nozzle 6, right part two-dimensional nozzle
7th, 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
6th, 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 pass through welding and connect
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 are made of 10 outside of nozzle structure block, 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 management and 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 center ternary is sprayed
The state management and control of pipe 11.Center three-dimensional nozzle 11 is used to implement the flow that intermediate flow section is also the most frequently used operating condition of test
(10%~50%) it controls, top two-dimensional nozzle 6 is used to implement the flow (＜ of small quantity operating condition of test with lower part two-dimensional nozzle 8
10%) it controls, center three-dimensional nozzle 11 is used to implement big flow operating condition of test with right part two-dimensional nozzle 7 and left part two-dimensional nozzle 9
Flow control (50%~100%).In small flow test operating mode, 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 is opened completely 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 closed, you can realizes that conventional type testing gas flow controls using center three-dimensional nozzle 11.Work as needs
When carrying out the adjusting experiment 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 are opened completely, 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 opened completely, you can realize
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, profit
The interference flowed with the maskable downstream disturbances of this characteristic of supersonic nozzle to jet pipe front end, 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 jet pipe is made to be in supersonic flows state, present invention design
Supersonic nozzle upstream pressure is not required 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 that nozzle section accumulates, 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, the spray of air-flow edge
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 gradually increases, 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 supercharging and it is finally equal with back pressure, which adaptively matches ring
Border back pressure, and stablize upstream airflow, providing strength for flow-rate adjustment supports.In addition, the jet pipe of the present 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,
Fundamentally avoid the problem that single nozzle throat adjust caused by cavitation nargin it is larger, be also avoided that one by one to single spraying pipe more
Change problem.The jet pipe of the present invention can keep entry condition such as pressure without significantly adjusting and can realize that flow is significantly adjusted
Technical barrier, make control valve always in best effort section, ensure the high-precision adjusted.
The content not being described in detail in description of the invention belongs to the known technology of those skilled in the art.
Claims (6)
1. a kind of flow control jet pipe, it is characterised in that：Including pressure-stabilizing section, jet pipe assembled unit, plate unit and diffuser, institute
It states jet pipe assembled unit and 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, including that can block single plate of two-dimensional nozzle entrance and can hide
Double plates of the three-dimensional nozzle entrance can be blocked again by keeping off the two-dimensional nozzle entrance, and the stable section is combines 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.
2. flow control jet pipe as described in claim 1, it is characterised in that：The three-dimensional nozzle at the center is sprayed for Lavalle
Pipe, the overall profile of lateral wall is cuboid, is formed respectively using four side walls up and down of the Laval nozzle as bottom wall
There are four two-dimensional nozzle, upper and lower two two-dimensional nozzles are separately installed with single plate, be inserted into respectively by single plate or
It extracts and respective entire entrance is blocked or opened, two two-dimensional nozzles in left and right are separately installed with double plates, the left side
The entrance of left side two-dimensional nozzle is blocked or opened to double plates, and the left semicircle for blocking or opening the Laval nozzle enters
Mouthful, the entrance of right side two-dimensional nozzle is blocked or opened to double plates on the right, and blocks or open the right side of the Laval nozzle
The entrance of semicircle.
3. flow control jet pipe as claimed in claim 2, it is characterised in that：The throat position of four two-dimensional nozzles with
The throat position of the Laval nozzle is identical.
4. flow control jet pipe as claimed in claim 3, it is characterised in that：Two two-dimensional nozzles up and down are symmetrically set
It puts, two two-dimensional nozzles in left and right are 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.
5. flow control jet pipe as claimed in claim 4, it is characterised in that：The center three-dimensional nozzle is used to implement middle area
Section is that the flow of the most frequently used operating condition of test is 10%~50% control, and top two-dimensional nozzle is used to implement with lower part two-dimensional nozzle
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.
6. the flow control jet pipe as described in any one of claim 1-5, 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 |
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| 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 |
|---|---|
| CN108267295A true CN108267295A (en) | 2018-07-10 |
| CN108267295B CN108267295B (en) | 2019-10-18 |
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ID=62772451
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711422731.5A Active CN108267295B (en) | 2017-12-25 | 2017-12-25 | A kind of flow control jet pipe |
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| Country | Link |
|---|---|
| CN (1) | CN108267295B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110767568A (en) * | 2018-07-26 | 2020-02-07 | 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 |
Citations (8)
| 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 |
| US20150121889A1 (en) * | 2013-03-08 | 2015-05-07 | Rolls-Royce North American Technologies, Inc. | Aircraft nozzle |
| 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 |
-
2017
- 2017-12-25 CN CN201711422731.5A patent/CN108267295B/en active Active
Patent Citations (8)
| 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 |
| US20150121889A1 (en) * | 2013-03-08 | 2015-05-07 | Rolls-Royce North American Technologies, Inc. | Aircraft nozzle |
| 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 |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110767568A (en) * | 2018-07-26 | 2020-02-07 | 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108267295B (en) | 2019-10-18 |
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