CN203719871U - A high speed high enthalpy air-flow generating apparatus - Google Patents
A high speed high enthalpy air-flow generating apparatus Download PDFInfo
- Publication number
- CN203719871U CN203719871U CN201320868972.3U CN201320868972U CN203719871U CN 203719871 U CN203719871 U CN 203719871U CN 201320868972 U CN201320868972 U CN 201320868972U CN 203719871 U CN203719871 U CN 203719871U
- Authority
- CN
- China
- Prior art keywords
- generating apparatus
- high speed
- flow generating
- jet
- flow
- 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.)
- Expired - Lifetime
Links
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims abstract description 10
- 239000001301 oxygen Substances 0.000 claims abstract description 10
- 229910052760 oxygen Inorganic materials 0.000 claims abstract description 10
- 238000010304 firing Methods 0.000 claims description 14
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 claims description 11
- 239000007921 spray Substances 0.000 claims description 9
- 239000007789 gas Substances 0.000 claims description 3
- 238000012360 testing method Methods 0.000 abstract description 10
- 238000002485 combustion reaction Methods 0.000 abstract 5
- 238000001816 cooling Methods 0.000 description 5
- 238000013461 design Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000009530 blood pressure measurement Methods 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000012937 correction Methods 0.000 description 1
- 238000010891 electric arc Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
Landscapes
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The utility model belongs to the field of spaceflight and aviation, and relates to a high speed high enthalpy air-flow generating apparatus. The apparatus comprises medium inlet tubes, an igniting assembly, a combustion chamber and a jet-flow jet tube. A jet disc is arranged on the front section of the combustion chamber. The middle section of the combustion chamber is a combustion cavity. A flange connecting piece is arranged on the rear section of the combustion chamber. The medium inlet tube and the igniting assembly are installed on the jet disc. The flange connecting piece is in fixed connection with the jet-flow jet tube. The igniting assembly comprises a first-stage igniter and a secondary stage igniter arranged on an end portion of the first-stage igniter. Through the utilization of the apparatus, an air-flow Mach number, an oxygen mass content in the air in a real flight condition can be completely simulated, and a total temperature and a total pressure at a height point can also be simulated, so that requirements by engine wind tunnel tests are satisfied.
Description
Technical field
The utility model belongs to field of aerospace, relates to a kind of high speed high-enthalpy flow generating apparatus for the wind tunnel test of Aero-Space engine.
Background technology
Air-flow generating apparatus is as the use of Aero-Space engine wind tunnel test, for test provides the uniform simulated air incoming flow with certain Mach number.Conventional air generating apparatus restricted application, and be also merely able to simulate gasflow mach number or air-flow stagnation temperature, and also the data of the gasflow mach number drawing or air-flow stagnation temperature are not strict corresponding with simulated altitude point; Meanwhile, at aerospace flight vehicle, in practical flight process, in gasflow mach number, air, the stagnation temperature of oxygen quality content and simulated altitude point and stagnation pressure all have a certain impact to the range request of crossing of whole flight.
Utility model content
In order to solve the problem in background technology, the utility model proposes a kind of can simulate completely in practical flight condition oxygen quality content and the stagnation temperature of simulated altitude point and the high speed high-enthalpy flow generating apparatus of stagnation pressure in gasflow mach number, air.
Concrete technical scheme of the present utility model is:
A high speed high-enthalpy flow generating apparatus, is characterized in that: comprise medium inlet, ignition module, firing chamber and jet nozzle; Described firing chamber leading portion arranges spray dish, and stage casing is burning cavity, and back segment arranges flange connector; On described spray dish, medium inlet and ignition module are installed; Described flange connector is fixedly connected with jet nozzle;
The secondary points firearm that described ignition module comprises one-level lighter and is arranged on one-level lighter end.
Above-mentioned one-level lighter is gas oxygen/ethanol torch lighter; Described secondary points firearm is spark plug.
Above-mentioned jet nozzle comprises inlet flange, Entrance Convergence section, throat, the outlet diffuser connecting successively; Described inlet flange is connected with firing chamber.
Above-mentioned outlet diffuser maximum cross-section diameter is Φ 1.5m.
The beneficial effects of the utility model are:
1, oxygen quality content and the stagnation temperature of simulated altitude point and the requirement of total complete simulated engine wind tunnel test of pressure energy in the gasflow mach number that employing the utility model produces, air.
2, the utility model adopts the mode of two-stage igniting, and not only ignition effectiveness is high, and has guaranteed the security of igniting.
3, the utility model adopts bigbore jet nozzle outlet, and flow middle district is large, applied widely.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model.
1-medium inlet, 2-secondary points firearm, 3-one-level lighter, 4-firing chamber, 41-spray dish, 42-burning cavity, 43-flange connector, 5-jet nozzle, 51-inlet flange, 52-Entrance Convergence section, 52-throat, 53-export diffuser.
Embodiment
In order to simulate space flight and aviation aircraft stagnation temperature and stagnation pressure of oxygen quality content and simulated altitude point in gasflow mach number, air in practical flight condition completely, the utility model proposes and a kind ofly can meet simulation test completely and require high speed high-enthalpy flow generating apparatus.
Below in conjunction with accompanying drawing, this device is described in detail:
A high speed high-enthalpy flow generating apparatus, comprises medium inlet 1, ignition module, firing chamber 4 and jet nozzle 5; Wherein, firing chamber 4 leading portions arrange spray dish 41, and stage casing is burning cavity 42, and back segment arranges flange connector 43; Medium inlet 1 and ignition module are installed on spray dish 41; Flange connector 43 is fixedly connected with jet nozzle 5; In use, in order to control the temperature of whole firing chamber and the serviceable life of firing chamber, the leading portion spray dish 41 of firing chamber 4 adopts the metal material of good heat conductivity, and the type of cooling is that alcohol is cooling, 42 employings of stage casing burning cavity itself adopt stainless steel, and the type of cooling is water cooling;
Especially, in order to ensure efficiency and the reliability of igniting, the secondary points firearm 2 that the ignition module in this device comprises one-level lighter 3 and is arranged on one-level lighter 3 ends.
Due in order to meet in test air-flow total amount and to guarantee that air-flow enters firing chamber 4 uniformly, the medium inlet of the three kinds of actuating mediums of the front installation of spray dish 41 in this device, for by liquid oxygen/ethanol/air Injection firing chamber.
Furtherly, in this device, one-level lighter 3 is gas oxygen/ethanol torch lighter; Secondary points firearm 2 is spark plug; Spark plug effluve forms electric arc point combustion gas oxygen/ethanol torch lighter, realizes the ignition operation of ignition module.
Furtherly, jet nozzle 5 comprises and connects successively inlet flange 51, Entrance Convergence section 52, throat 53, outlet diffuser 54; Inlet flange 51 is connected with flange connector 43.The method that the design of this jet nozzle adopts characteristic curve to add boundary layer correction is calculated, and needs the Flow Field Performance of nozzle contour to carry out Fluid Mechanics Computation emulation check, to prove that the flow field of the pneumatic profile generation providing meets the demands after pipe design completes.When jet nozzle is used, in order to ensure guaranteeing that nozzle wall surface temperature is stable, there is not excessive thermal deformation, can utilize chilled water to carry out cooling to nozzle wall face.
Especially, in order to ensure flow middle, district is large, applied widely, and the outlet diffuser pipeline maximum cross-section diameter of the jet nozzle of this device is Φ 1.5m.
By test of many times, verify, the high speed high-enthalpy flow generating apparatus exit flow parameter that the utility model adopts can meet testing requirements.The exit flow Mach number Ma=8 of take is example, and the corresponding simulated altitude of jet nozzle outlet static pressure 122.8PaA(is 46.53km), oxygen volume fraction 23.8% in air-flow, air-flow stagnation temperature, total pressure measurement value can meet the requirement of test mission book completely.
Claims (4)
1. a high speed high-enthalpy flow generating apparatus, is characterized in that: comprise medium inlet, ignition module, firing chamber and jet nozzle; Described firing chamber leading portion arranges spray dish, and stage casing is burning cavity, and back segment arranges flange connector; On described spray dish, medium inlet and ignition module are installed; Described flange connector is fixedly connected with jet nozzle;
The secondary points firearm that described ignition module comprises one-level lighter and is arranged on one-level lighter end.
2. according to the high speed high-enthalpy flow generating apparatus described in claims 1, it is characterized in that: described one-level lighter is gas oxygen/ethanol torch lighter; Described secondary points firearm is spark plug.
3. according to the high speed high-enthalpy flow generating apparatus described in claims 2, it is characterized in that: described jet nozzle comprises inlet flange, Entrance Convergence section, throat, the outlet diffuser connecting successively; Described inlet flange is connected with firing chamber.
4. according to the high speed high-enthalpy flow generating apparatus described in claims 3, it is characterized in that: described outlet diffuser maximum cross-section diameter is Φ 1.5m.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320868972.3U CN203719871U (en) | 2013-12-23 | 2013-12-23 | A high speed high enthalpy air-flow generating apparatus |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320868972.3U CN203719871U (en) | 2013-12-23 | 2013-12-23 | A high speed high enthalpy air-flow generating apparatus |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203719871U true CN203719871U (en) | 2014-07-16 |
Family
ID=51159010
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320868972.3U Expired - Lifetime CN203719871U (en) | 2013-12-23 | 2013-12-23 | A high speed high enthalpy air-flow generating apparatus |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203719871U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107859484A (en) * | 2017-10-18 | 2018-03-30 | 中国石油大学(北京) | Simulate the experimental system and method for heating power jet broken rock |
| CN110595721A (en) * | 2019-09-10 | 2019-12-20 | 中国空气动力研究与发展中心超高速空气动力研究所 | Ignition device for ultra-high speed wind tunnel |
| CN110595792A (en) * | 2019-08-13 | 2019-12-20 | 西北工业大学 | Simulation device for hypersonic/subsonic combustion thermal environment of combined engine and use method |
| CN115014778A (en) * | 2022-05-17 | 2022-09-06 | 西安航天动力试验技术研究所 | Large-scale high-enthalpy wind tunnel incoming flow simulation combustion device |
| CN115307862A (en) * | 2022-10-11 | 2022-11-08 | 中国空气动力研究与发展中心超高速空气动力研究所 | Hypersonic wind tunnel mixed heating gas jet flow test device |
| CN118168753A (en) * | 2024-05-14 | 2024-06-11 | 中国空气动力研究与发展中心超高速空气动力研究所 | Ignition starting device and ignition starting method for high-temperature wind tunnel combustion heater |
-
2013
- 2013-12-23 CN CN201320868972.3U patent/CN203719871U/en not_active Expired - Lifetime
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107859484A (en) * | 2017-10-18 | 2018-03-30 | 中国石油大学(北京) | Simulate the experimental system and method for heating power jet broken rock |
| CN107859484B (en) * | 2017-10-18 | 2019-05-07 | 中国石油大学(北京) | Simulate the experimental system and method for heating power jet stream broken rock |
| CN110595792A (en) * | 2019-08-13 | 2019-12-20 | 西北工业大学 | Simulation device for hypersonic/subsonic combustion thermal environment of combined engine and use method |
| CN110595792B (en) * | 2019-08-13 | 2020-06-30 | 西北工业大学 | Simulation device for hypersonic/subsonic combustion thermal environment of combined engine |
| CN110595721A (en) * | 2019-09-10 | 2019-12-20 | 中国空气动力研究与发展中心超高速空气动力研究所 | Ignition device for ultra-high speed wind tunnel |
| CN115014778A (en) * | 2022-05-17 | 2022-09-06 | 西安航天动力试验技术研究所 | Large-scale high-enthalpy wind tunnel incoming flow simulation combustion device |
| CN115014778B (en) * | 2022-05-17 | 2024-05-03 | 西安航天动力试验技术研究所 | Large-scale high-enthalpy wind tunnel inflow simulated combustion device |
| CN115307862A (en) * | 2022-10-11 | 2022-11-08 | 中国空气动力研究与发展中心超高速空气动力研究所 | Hypersonic wind tunnel mixed heating gas jet flow test device |
| CN118168753A (en) * | 2024-05-14 | 2024-06-11 | 中国空气动力研究与发展中心超高速空气动力研究所 | Ignition starting device and ignition starting method for high-temperature wind tunnel combustion heater |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN203719871U (en) | A high speed high enthalpy air-flow generating apparatus | |
| CN109765031B (en) | Balance support rod for wind tunnel thermal jet interference test | |
| Frolov et al. | Wind tunnel tests of a hydrogen-fueled detonation ramjet model at approach air stream Mach numbers from 4 to 8 | |
| Golub et al. | Experimental and numerical investigation of hydrogen gas auto-ignition | |
| CN111963337B (en) | Direct connection hot test system and hot test method for oxygen-enriched afterburning engine thrust chamber | |
| CN111305974B (en) | Multifunctional integrated combustion assembly testing device | |
| CN102384834B (en) | Detonation-driving shock tunnel explosive discharge device | |
| CN110907123A (en) | High-enthalpy propulsion wind tunnel air heating method and device | |
| CN105424369A (en) | Pneumatic model tester for aircraft engine | |
| CN115875673A (en) | Pulse combustion wind tunnel hydrogen-oxygen combustion heater applied to high-temperature air incoming flow | |
| Smart et al. | Free-jet testing of a REST scramjet at off-design conditions | |
| CN105588702A (en) | Power system of flight test with power of low-speed wind tunnel model | |
| CN205138753U (en) | Direct current wind -tunnel device | |
| Ogorodnikov et al. | Russian research on experimental hydrogen-fueled dual-mode scramjet: conception and preflight tests | |
| Faget et al. | Free-jet Tests of a 6.5-inch-diameter Ram-jet Engine at Mach Numbers 1.81 and 2.00 | |
| CN112943484B (en) | Experimental device for researching heat transfer influence of roughness on wall surface of spray pipe | |
| CN203478234U (en) | Quick-start ground ultra-large three-component heater | |
| Dunsworth et al. | Ramjet engine testing and simulation techniques | |
| CN204575291U (en) | A kind of turbine engine jet flow experiment analogue means | |
| CN102493903A (en) | Method for manufacturing high-flow gas nozzle | |
| CN105387990A (en) | Direct-current wind tunnel device and working method thereof | |
| CN210802911U (en) | Supersonic engine test bed | |
| Gallis et al. | Development and Validation of a 0-D/1-D Model to Evaluate Pulsating Conditions from a Constant Volume Combustor | |
| CN114658566B (en) | Temperature distortion generator based on pulse detonation combustion and test method thereof | |
| CN208043384U (en) | A kind of high enthalpy impulse wind tunnel pipe structure of the wide Mach number of combined type |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20140716 |