CN106404405A - Apparatus for injecting tail gas and inflow hot air in vacuum cabin of ramjet - Google Patents
Apparatus for injecting tail gas and inflow hot air in vacuum cabin of ramjet Download PDFInfo
- Publication number
- CN106404405A CN106404405A CN201610814541.7A CN201610814541A CN106404405A CN 106404405 A CN106404405 A CN 106404405A CN 201610814541 A CN201610814541 A CN 201610814541A CN 106404405 A CN106404405 A CN 106404405A
- Authority
- CN
- China
- Prior art keywords
- vacuum
- nozzles
- injector
- receiving chamber
- entrance
- 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.)
- Pending
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
Abstract
The invention belongs to the technical field of ramjet test, and specifically relates to an apparatus for injecting the tail gas and inflow hot air in a vacuum cabin of a ramjet. The apparatus comprises a receiving chamber, a vacuum pipeline, a vacuum butterfly valve, an injection nozzle and a throttle pipeline, wherein the injection nozzle is of a De-Laval nozzle structure and is inserted in the receiving chamber, the inlet of the injection nozzle is exposed outside the receiving chamber for receiving external high-temperature steam, the outlet of the injection nozzle is positioned in the receiving chamber and communicates with the inlet of the throttle pipeline, and the vacuum pipeline is installed on the side surface of the receiving chamber and connected with the vacuum cabin of the ramjet through the vacuum butterfly valve. The apparatus can satisfy long-time test and stably retain pressure in the vacuum cabin.
Description
Technical field
The invention belongs to punching engine experimental technique field and in particular to a kind of punching engine vacuum chamber inner exhaust gas and
To flow hot-air induction apparatus.
Background technology
Punching engine is a kind of simple structure but can send very high thrust it is adaptable to the air of high speed flight at high altitude sprays
Gas engine.In the development test of punching engine, for true simulated altitude environment, need to produce vacuum chamber intrinsic motivation
The high temperature air injection that raw tail gas to flow with simulation, to out of my cabin, to maintain certain vacuum level requirements in cabin.
The method of more employing is the method for Vacuum Spherical Tank at present, using vavuum pump, spherical tank is extracted into certain vacuum degree, profit
With the vacuum of spherical tank, the gas in vacuum chamber is drawn in spherical tank.This method simulate incoming air amount larger when, no
Pressure in the long-time target tested and vacuum chamber can be met be difficult to keep stable.
Content of the invention
In order to solve the problems, such as in background technology, the invention provides one kind can meet long-time test and can stablize
Keep in vacuum chamber the punching engine vacuum chamber inner exhaust gas of pressure and flowing hot-air induction apparatus.
The concrete technical scheme of the present invention is：
The invention provides a kind of punching engine vacuum chamber inner exhaust gas and flowing hot-air induction apparatus, include acceptance
Room, vacuum pipe, vacuum butterfly valve, nozzles with injector and choke manifold；
Described nozzles with injector is Rafael nozzle structure, and nozzles with injector is inserted in receiving chamber, outside the entrance of nozzles with injector
It is exposed at the high-temperature steam outside entrance reception of receiving chamber outside and nozzles with injector, the outlet of nozzles with injector is located at and accepts interior
And connect with choke manifold entrance；
The side mounting vacuum tube road of receiving chamber；Vacuum pipe is connected with engine vacuum cabin by vacuum butterfly valve.
In order to adapt to actual experiment requirement, the nozzles with injector that would generally arrange at the trial is three and spaced
120 ° are inserted in receiving chamber；The quantity of described choke manifold is consistent with nozzles with injector.
Above-mentioned choke manifold includes mixing chamber, connecting pipe and the diffuser casing being sequentially communicated；The entrance of described mixing chamber
Outlet coaxial communication with nozzles with injector.
Above-mentioned mixing chamber is gradually reduced from entrance to outlet diameter；The constant diameter of described connecting pipe is constant；Described expansion
Scattered room is gradually increased from entrance to outlet diameter.
The general principle of the present invention is：
Nozzles with injector is a kind of structure of Rafael nozzle, after high-temperature steam flows through three nozzles with injectors, because high temperature steams
Vapour flow area local contraction, flow velocity increases, and static pressure declines, and produces negative pressure in nozzles with injector exit region, by vacuum tube
Road is by the tail gas in punching engine vacuum chamber and high temperature incoming air injection to receiving chamber.
The mixed gas of high-temperature steam, tail gas and high temperature air respectively enter the mixing chamber of three choke manifold, with mixed
Close the reduction further of gas flow area, negative pressure value increases further.The gas flowing out mixing chamber enters diffuser casing, and pressure is opened
Begin to raise, until pressure exceedes atmospheric pressure, mixed gas are entered air.High-temperature steam calorific value high acting ability is strong, generation true
Reciprocal of duty cycle is big, as long as steam exists can keep the stable vacuum long period in vacuum chamber, disclosure satisfy that the punching press to flow greatly is sent out
Motivation test requirements document.
It is an advantage of the current invention that：
1st, the induction apparatus of present invention design be capable of injection throughput big, produce that vacuum is high and vacuum remains steady
The fixed and time is long.
2nd, the induction apparatus compact conformation of the present invention, it is relatively small to take up an area space, saving test site that can be very high.
Brief description
Fig. 1 is the structure diagram of the present invention；
Fig. 2 is the A direction view of Fig. 1.
Specific embodiment
The invention provides a kind of punching engine vacuum chamber inner exhaust gas and flowing hot-air induction apparatus, include acceptance
Room, vacuum pipe, vacuum butterfly valve, nozzles with injector and choke manifold；
Wherein, nozzles with injector is Rafael nozzle structure, and nozzles with injector is inserted in receiving chamber, outside the entrance of nozzles with injector
It is exposed at the high-temperature steam outside entrance reception of receiving chamber outside and nozzles with injector, the outlet of nozzles with injector is located at and accepts interior
And connect with choke manifold entrance；
The side mounting vacuum tube road of receiving chamber；Vacuum pipe is connected with engine vacuum cabin by vacuum butterfly valve.
In order to adapt to actual experiment requirement, the nozzles with injector that would generally arrange at the trial is three and spaced
120 ° are inserted in receiving chamber；The quantity of described choke manifold is consistent with nozzles with injector.
Specifically, choke manifold includes mixing chamber, connecting pipe and the diffuser casing being sequentially communicated；Described mixing chamber
Entrance and the outlet coaxial communication of nozzles with injector.Mixing chamber is gradually reduced from entrance to outlet diameter；Described connecting pipe straight
Footpath is invariable；Described diffuser casing is gradually increased from entrance to outlet diameter.
The preferred forms of the present invention are as follows：
Referring to shown in Fig. 1 and Fig. 2, punching engine vacuum chamber inner exhaust gas and flowing in hot-air induction apparatus, three are drawn
Penetrate jet pipe 1 to be spaced in 120 ° of insertion receiving chamber 2, receiving chamber 2 side connects vacuum pipe 3, and vacuum pipe 3 is true with punching engine
Empty cabin 4 is connected, and centre has vacuum butterfly valve 5 to isolate, and three nozzles with injectors 1 are exported and connected (three sections respectively with three choke manifold 6
Flow tube road all includes mixing chamber 7, connecting pipe 8 and the diffuser casing 9 being sequentially connected)；Before engine ignition, steam is first passed through
Three nozzles with injectors 1, reduce because cross section of fluid channel amasss, export in nozzles with injector 1 and produce negative pressure.After stable, open vacuum pipe 3
On vacuum butterfly valve 5, vacuum pipe 3 and receiving chamber 2 insertion, the tail gas that engine ignition produces and air are entered by injection to flow
Receiving chamber 2, enters air with flow of steam at high temperature through choke manifold 6.As the middle part internal diameter D1=Φ 142mm of nozzles with injector 1, throttle
Pipeline 6 mixing chamber outlet internal diameter D2=Φ 550mm, in the case that nozzles with injector 1 is good with choke manifold 6 axiality, test card
Bright, this method can make the punching engine vacuum chamber vacuum long period stable in suitable scope, and fluctuation range is 5%
Within.
Claims (4)
1. a kind of punching engine vacuum chamber inner exhaust gas and flowing hot-air induction apparatus, including receiving chamber, vacuum pipe, vacuum
Butterfly valve, nozzles with injector and choke manifold；
Described nozzles with injector is Rafael nozzle structure, and nozzles with injector is inserted in receiving chamber, and the entrance of nozzles with injector is exposed at
It is used for receiving the high-temperature steam of outside outside receiving chamber, the outlet of nozzles with injector is located at and accepts indoor and connected with choke manifold entrance
Logical；
The side mounting vacuum tube road of receiving chamber；Vacuum pipe is connected with engine vacuum cabin by vacuum butterfly valve.
2. punching engine vacuum chamber inner exhaust gas according to claim 1 and flowing hot-air induction apparatus, its feature exists
In：Described nozzles with injector is inserted in receiving chamber for three and spaced 120 °；The quantity of described choke manifold and injection
Jet pipe is consistent.
3. punching engine vacuum chamber inner exhaust gas according to claim 2 and flowing hot-air induction apparatus, its feature exists
In：Described choke manifold includes mixing chamber, connecting pipe and the diffuser casing being sequentially communicated；The entrance of described mixing chamber and injection
The outlet coaxial communication of jet pipe.
4. punching engine vacuum chamber inner exhaust gas according to claim 3 and flowing hot-air induction apparatus, its feature exists
In：Described mixing chamber is gradually reduced from entrance to outlet diameter；The constant diameter of described connecting pipe is constant；Described diffuser casing from
Entrance is gradually increased to outlet diameter.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610814541.7A CN106404405A (en) | 2016-09-09 | 2016-09-09 | Apparatus for injecting tail gas and inflow hot air in vacuum cabin of ramjet |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610814541.7A CN106404405A (en) | 2016-09-09 | 2016-09-09 | Apparatus for injecting tail gas and inflow hot air in vacuum cabin of ramjet |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106404405A true CN106404405A (en) | 2017-02-15 |
Family
ID=57999167
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610814541.7A Pending CN106404405A (en) | 2016-09-09 | 2016-09-09 | Apparatus for injecting tail gas and inflow hot air in vacuum cabin of ramjet |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106404405A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109781427A (en) * | 2018-12-12 | 2019-05-21 | 西安航天动力试验技术研究所 | The high mould of liquid attitude control engine tests reverse thin incoming flow simulator |
| CN109540526B (en) * | 2018-12-09 | 2021-10-15 | 西安航天动力试验技术研究所 | Turbine injection system used in direct connection test of ramjet engine |
| CN114198511A (en) * | 2021-11-23 | 2022-03-18 | 内蒙航天动力机械测试所 | Double-pulse solid rocket engine high-altitude simulation test quick non-return device |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202451476U (en) * | 2012-01-18 | 2012-09-26 | 杭州隆达真空设备有限公司 | Multi-nozzle steam ejector |
| CN103611642A (en) * | 2013-12-04 | 2014-03-05 | 四川锦宇化机有限公司 | Steam pressure-rising ejector |
| CN204299978U (en) * | 2014-12-13 | 2015-04-29 | 杭州隆达真空设备有限公司 | Steam jet ejector |
| CN204299973U (en) * | 2014-12-13 | 2015-04-29 | 杭州隆达真空设备有限公司 | Vapor pump |
-
2016
- 2016-09-09 CN CN201610814541.7A patent/CN106404405A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202451476U (en) * | 2012-01-18 | 2012-09-26 | 杭州隆达真空设备有限公司 | Multi-nozzle steam ejector |
| CN103611642A (en) * | 2013-12-04 | 2014-03-05 | 四川锦宇化机有限公司 | Steam pressure-rising ejector |
| CN204299978U (en) * | 2014-12-13 | 2015-04-29 | 杭州隆达真空设备有限公司 | Steam jet ejector |
| CN204299973U (en) * | 2014-12-13 | 2015-04-29 | 杭州隆达真空设备有限公司 | Vapor pump |
Non-Patent Citations (3)
| Title |
|---|
| G.SOLFANELLI 等: "航天发动机高空模拟试验新设施", 《固体火箭技术》 * |
| 张奎好: "火箭发动机-超音速扩压器-蒸汽引引射泵组合式高空模拟试验系统的性能研究", 《推进技术》 * |
| 沈坚 等: "引射器及引射循环在工程中的应用", 《煤气与热力》 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109540526B (en) * | 2018-12-09 | 2021-10-15 | 西安航天动力试验技术研究所 | Turbine injection system used in direct connection test of ramjet engine |
| CN109781427A (en) * | 2018-12-12 | 2019-05-21 | 西安航天动力试验技术研究所 | The high mould of liquid attitude control engine tests reverse thin incoming flow simulator |
| CN109781427B (en) * | 2018-12-12 | 2020-08-04 | 西安航天动力试验技术研究所 | Reverse rarefied incoming flow simulation device for liquid attitude control engine high-mode test |
| CN114198511A (en) * | 2021-11-23 | 2022-03-18 | 内蒙航天动力机械测试所 | Double-pulse solid rocket engine high-altitude simulation test quick non-return device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN206192621U (en) | Experimental high -efficient jumbo size of intake duct is drawn and is penetrated piping installation | |
| CN113899516B (en) | Ground simulation device and method for rocket engine jet flow interference effect | |
| CN108168832B (en) | A kind of throat structure improving tube wind tunnel test Reynolds number | |
| CN204495535U (en) | 1.2 meters of magnitude wind-tunnel represent dynamically injectors | |
| CN105628331B (en) | The energy-conserving and environment-protective system of large-scale conventional hypersonic wind tunnel | |
| CN106404405A (en) | Apparatus for injecting tail gas and inflow hot air in vacuum cabin of ramjet | |
| CN102628385B (en) | For the crankcase ventilation of automobile | |
| CN104777002A (en) | Methane combustion heating experimental system for combustion chamber of scramjet engine | |
| CN104420998B (en) | Entrance system and relevant device and method for combustion gas turbine | |
| WO2014133996A1 (en) | Gas recirculation in turbocharged diesel engines | |
| CN106704039A (en) | Gaseous fuel, EGR and air mixing device and insert | |
| CN212819192U (en) | Natural gas hydrogen mixing system | |
| CN111929024B (en) | Icing wind tunnel air intake and height simulation system and method | |
| CN103149009A (en) | Supersonic isolating section wind tunnel test device | |
| CN105115720B (en) | Bi-turbo property test platform with gases at high pressure part flow arrangement | |
| CN207660707U (en) | The multipart anti-icing system of aero-engine | |
| CN104595058A (en) | Working method of ram rocket | |
| CN207715443U (en) | A kind of twin-stage low-pressure injection exhaust apparatus | |
| US6868830B1 (en) | Venturi induction for internal combustion engines | |
| CN106500950A (en) | A kind of efficient large scale injection piping installation of air intake test | |
| CN105806873B (en) | The cold effect experimental rigs of expansion ratios such as combustion engine turbine blade cooling | |
| CN202133528U (en) | Active flow control experimental device for high-speed wind tunnel air intake duct | |
| CN103967650A (en) | Turbofan engine | |
| CN106874536A (en) | A kind of multistage Multi Nozzle Ejector hierarchy optimization method | |
| CN104353376B (en) | A kind of oil gas mixing machine being applied in oil system experiment porch |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170215 |