CN104359646B - Suction method is used to control the hypersonic nozzle of boundary layer thickness - Google Patents
Suction method is used to control the hypersonic nozzle of boundary layer thickness Download PDFInfo
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- CN104359646B CN104359646B CN201410554947.7A CN201410554947A CN104359646B CN 104359646 B CN104359646 B CN 104359646B CN 201410554947 A CN201410554947 A CN 201410554947A CN 104359646 B CN104359646 B CN 104359646B
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- Prior art keywords
- jet pipe
- layer thickness
- pack
- suction
- screw rod
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Abstract
The invention provides a kind of hypersonic nozzle using suction method to control boundary layer thickness to include: jet pipe leading portion, front apron, screw rod, suction cylinder, pump orifice, jet pipe pack, pad and backboard；At the jet pipe back segment described screw rod of employing by described jet pipe pack Fine Boring together, and fix with described jet pipe leading portion and be connected；Having described pad between any two in described jet pipe pack, described pad is sleeved on described screw rod；Having described suction cylinder, one end of described suction cylinder to be connected with described front apron around described jet pipe back segment, the other end and described backboard connect, and form suction chamber；Described suction cylinder has described pump orifice.Take the fluid of a part of mental retardation in boundary-layer away by pump orifice, suppress boundary-layer to separate, thus reduce boundary layer thickness.Open the mode of multiple circumferential weld after using nozzle throat, boundary-layer is aspirated, it is achieved the control to jet pipe boundary layer thickness.
Description
Technical field
The present invention relates to a kind of hypersonic nozzle, use suction method to control boundary-layer particularly to one
The hypersonic nozzle of thickness.
Background technology
The ground experiment such as hypersonic wind tunnel and engine testsand is set by the development of hypersonic aircraft
For proposing the highest requirement.In these ground-testing plants, jet pipe is then to ensure that test section obtains
The vitals of the uniform air flow of Mach number must be designed.And nozzle exit attached of usual ground-testing plant
Surface layer is thicker, and the homogeneity range scope causing nozzle exit is less so that the size of test model is by greatly
Limit.Particularly when ground experiment equipment simulating high temperature, high dummy status, it may appear that attached of nozzle exit
Layer increases blocked up, even flow field district narrow scope or the problem without homogeneity range.
Existing ground-testing plant the most actively controls the thickness of boundary-layer, the spendable homogeneity range of jet pipe
It is limited in scope.When the large range of homogeneity range of needs, the general ground by building more heavy caliber jet pipe
The problem that the mode of testing equipment solves homogeneity range on a large scale.Owing to employing heavy caliber jet pipe not only can be anxious
Increase severely and add the construction cost of ground-testing plant, and the requirements at the higher level of relevant corollary equipment are often exceeded
Existing limit of power, is difficult in a short time.
Summary of the invention
The technical problem to be solved is: provide a kind of under conditions of not increasing jet pipe bore,
Use suction method control boundary layer thickness hypersonic nozzle, expanding test equipment homogeneity range scope and
Test capability.
The hypersonic nozzle using suction method to control boundary layer thickness of the present invention includes: before jet pipe
Section, front apron, screw rod, suction cylinder, pump orifice, jet pipe pack, pad and backboard；After jet pipe
Screw rod described in Duan Caiyong, and is fixed even with described jet pipe leading portion by described jet pipe pack Fine Boring together
Connect；Having described pad between any two in described jet pipe pack, described pad is sleeved on described screw rod；
Described suction cylinder, one end of described suction cylinder is had to be connected with described front apron, separately around described jet pipe back segment
One end and described backboard connect, and form suction chamber；Described suction cylinder has described pump orifice.
The most described jet pipe pack is ring segment, and the Internal periphery of described jet pipe pack is carried out according to jet pipe molded line
The circumferential weld that processing is preferably formed by described jet pipe pack and described pad at described jet pipe back segment has 60
Road.
The quantity of the most described screw rod is 6.
The most described pump orifice has multiple.
The present invention compared with prior art provides the benefit that:
(1) jet pipe back segment use screw rod by jet pipe pack Fine Boring together, and with jet pipe leading portion
Fixing connection, carries out polish to nozzle contour the most again, so processing is simple, profile degree of accuracy is high；
(2) between jet pipe pack, add pad, determined by the thickness of pad between the gap of jet pipe
Away from, form jet pipe open loop crack structure；
(3) having suction cylinder, one end to be connected with front apron around jet pipe back segment, the other end and backboard are even
Connect, form suction chamber；
(4) on suction cylinder, have pump orifice, by pump orifice, boundary-layer is aspirated, thus reduce
The thickness of jet pipe boundary-layer.
Accompanying drawing explanation
Fig. 1 is the hypersonic nozzle overall structure schematic diagram using suction method to control boundary layer thickness.
Fig. 2 is the partial structurtes schematic diagram of jet pipe.
Symbol description
1 is jet pipe leading portion, and 2 is front apron, and 3 is screw rod, and 4 is suction cylinder, and 5 is pump orifice, and 6 are
Jet pipe pack, 7 is pad, and 8 is backboard.
Detailed description of the invention
Below in conjunction with accompanying drawing, principle and the feature of the present invention are described in detail.
As it is shown in figure 1, the version of jet pipe uses open loop seam suction form, jet pipe is main
Including: jet pipe leading portion 1, front apron 2, screw rod 3, suction cylinder 4, pump orifice 5, jet pipe pack 6,
Pad 7, backboard 8 etc..
The version stitched for open loop after realizing nozzle throat, uses screw rod 3 by annular at jet pipe back segment
Jet pipe pack 6 Fine Boring together, and fixing with jet pipe leading portion 1 be connected, the most again to nozzle type
Face carries out polish, and jet pipe pack 6 has the installing hole installing screw rod 3, the Internal periphery of jet pipe pack 6
It is processed according to jet pipe molded line.Adding pad 7 between any two in jet pipe pack 6, pad 7 is annulus
Shape, it is sleeved on screw rod 3 across jet pipe pack 6, is determined the seam of jet pipe by the thickness of pad 7
Gap spacing, forms the open loop crack structure of jet pipe, is formed with 60 road circumferential welds in this example；Screw rod 3 is centered around
The peripheral uniformly configuration 6 of jet pipe back segment, by screw rod 3 and pad 7 by jet pipe pack 6 Fine Boring
Together, the most again nozzle contour is carried out polish.Jet pipe can be adjusted by the thickness of pad 7
Gap spacing.Jet pipe back segment is provided around suction cylinder 4, and one end is connected with front apron 2, the other end and
Backboard 8 connects, and forms suction chamber；Suction cylinder 4 is provided with pump orifice 5, right by pump orifice 5
The boundary-layer of jet pipe aspirates, thus reduces the thickness of jet pipe boundary-layer, to realize controlling attached of jet pipe
The effect of layer thickness.The quantity of pump orifice 5 determines as required.Jet pipe pack 6, screw rod 3 and pad
The quantity of 7 all can vary depending on.
Claims (5)
1. one kind uses the hypersonic nozzle that suction method controls boundary layer thickness, it is characterised in that bag
Include: jet pipe leading portion, front apron, screw rod, suction cylinder, pump orifice, jet pipe pack, pad and backboard；
Jet pipe back segment use described screw rod by described jet pipe pack Fine Boring together, and with described jet pipe before
Section is fixing to be connected；Having described pad between any two in described jet pipe pack, described pad is sleeved on described
On screw rod；Described suction cylinder, one end of described suction cylinder and described front apron is had around described jet pipe back segment
Connecting, the other end and described backboard connect, and form suction chamber；Take out described in described suction cylinder is provided with
Suction inlet.
Employing suction method the most according to claim 1 controls the hypersonic spray of boundary layer thickness
Pipe, it is characterised in that: described jet pipe pack is ring segment, and the Internal periphery of described jet pipe pack is according to jet pipe
Molded line is processed.
Employing suction method the most according to claim 1 controls the hypersonic spray of boundary layer thickness
Pipe, it is characterised in that: the circumferential weld formed by described jet pipe pack and described pad at described jet pipe back segment
There are 60 roads.
Employing suction method the most according to claim 1 controls the hypersonic spray of boundary layer thickness
Pipe, it is characterised in that: the quantity of described screw rod is 6.
Employing suction method the most according to claim 1 controls the hypersonic spray of boundary layer thickness
Pipe, it is characterised in that: described pump orifice has multiple.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410554947.7A CN104359646B (en) | 2014-10-17 | 2014-10-17 | Suction method is used to control the hypersonic nozzle of boundary layer thickness |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410554947.7A CN104359646B (en) | 2014-10-17 | 2014-10-17 | Suction method is used to control the hypersonic nozzle of boundary layer thickness |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104359646A CN104359646A (en) | 2015-02-18 |
| CN104359646B true CN104359646B (en) | 2016-09-14 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410554947.7A Expired - Fee Related CN104359646B (en) | 2014-10-17 | 2014-10-17 | Suction method is used to control the hypersonic nozzle of boundary layer thickness |
Country Status (1)
| Country | Link |
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| CN (1) | CN104359646B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104729825B (en) * | 2015-04-03 | 2017-06-16 | 中国航天空气动力技术研究院 | A kind of jet system for aiding in controlling high-speed wind tunnel Asia Transonic Flow |
| CN111396196A (en) * | 2019-01-02 | 2020-07-10 | 中国航发商用航空发动机有限责任公司 | S-shaped switching section of gas compressor and turbofan engine |
| CN111272377A (en) * | 2020-02-27 | 2020-06-12 | 北京航空航天大学 | Large-scale double-circulation back-cooling type low-temperature environment wind tunnel |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10163896B4 (en) * | 2001-12-22 | 2005-02-17 | Daimlerchrysler Ag | Wind tunnel short nozzle with boundary layer peeling |
| CN1808089A (en) * | 2006-02-16 | 2006-07-26 | 同济大学 | Horizontal pumping system and pumping control method for automobile wind tunnel |
| CN201572691U (en) * | 2009-12-15 | 2010-09-08 | 北京京诚瑞信长材工程技术有限公司 | Counterattack nozzle for turbulent water cooling device |
| CN102012307A (en) * | 2010-11-18 | 2011-04-13 | 中国人民解放军国防科学技术大学 | Supersonic speed boundary layer wind tunnel |
| CN102252818A (en) * | 2011-06-23 | 2011-11-23 | 中国人民解放军国防科学技术大学 | Supersonic wind tunnel with variable quality of flow field |
-
2014
- 2014-10-17 CN CN201410554947.7A patent/CN104359646B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10163896B4 (en) * | 2001-12-22 | 2005-02-17 | Daimlerchrysler Ag | Wind tunnel short nozzle with boundary layer peeling |
| CN1808089A (en) * | 2006-02-16 | 2006-07-26 | 同济大学 | Horizontal pumping system and pumping control method for automobile wind tunnel |
| CN201572691U (en) * | 2009-12-15 | 2010-09-08 | 北京京诚瑞信长材工程技术有限公司 | Counterattack nozzle for turbulent water cooling device |
| CN102012307A (en) * | 2010-11-18 | 2011-04-13 | 中国人民解放军国防科学技术大学 | Supersonic speed boundary layer wind tunnel |
| CN102252818A (en) * | 2011-06-23 | 2011-11-23 | 中国人民解放军国防科学技术大学 | Supersonic wind tunnel with variable quality of flow field |
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|---|---|
| CN104359646A (en) | 2015-02-18 |
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