CN105388007A - Combined removable nozzle test device - Google Patents
Combined removable nozzle test device Download PDFInfo
- Publication number
- CN105388007A CN105388007A CN201510849780.1A CN201510849780A CN105388007A CN 105388007 A CN105388007 A CN 105388007A CN 201510849780 A CN201510849780 A CN 201510849780A CN 105388007 A CN105388007 A CN 105388007A
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- Prior art keywords
- fuel
- nozzle
- inlet collector
- road
- oxygenant
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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
- G01M13/00—Testing of machine parts
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Engines (AREA)
Abstract
The invention provides a combined removable nozzle test device, which includes a fuel path inlet collector provided internally with a cavity. Two sides of the fuel path inlet collector are provided with fuel path inlets. A fuel nozzle is disposed at the upper portion of the fuel path inlet collector. The portion, which is located in the cavity of the fuel path inlet collector, of the fuel nozzle is provided with a fuel inlet. An oxidant nozzle is disposed at the upper portion of the fuel nozzle. The lower portion of the oxidant nozzle extends into the bottom in the fuel nozzle. An oxidant path inlet collector is disposed at the upper portion of the oxidant nozzle. An oxidant inlet is disposed above the oxidant path inlet collector. The fuel enters from the fuel path inlets at the two sides, and an oxidant enters from the oxidant inlet. The structure of the invention is easy to install and remove, reliable sealing of high pressure low temperature media can be achieved, the increase in test efficiency is facilitated. The invention is excellent in sealing and short in test cycle when used for an atomization test of high pressure low temperature liquid-propellant rocket engine materials and an oxidant nozzle.
Description
Technical field
The present invention relates to a kind of new type nozzle test unit being applicable to high pressure low temperature medium, can be used for the field that Aero-Space, petrochemical complex, automobile etc. relate to injection and atomization technique research.
Background technology
Nozzle tester is widely used in the field that Aero-Space, petrochemical complex, automobile etc. relate to injection and atomization technique research, such as, be used for the test unit of exploration rocket engine two bursts of propellant jet, mixing and spray rule.
In existing cryogenic liquid rocket motor injector test unit, fuel and mostly adopt braze-welded structure to be connected between oxidize nozzle with collector, due to welded restriction, fuel and oxidize nozzle cannot be changed, so often kind of test unit can only be studied for a kind of nozzle arrangements, thus add experimentation cost and time, be unfavorable for cost efficiency.
Summary of the invention
The technical problem to be solved in the present invention is: overcome the structural deficiency of existing apparatus, solve the problem that in high pressure low temperature medium nozzle test unit, fuel and oxidize nozzle cannot be changed, a kind of combined type replaceable nozzle tester is provided, makes fuel and the dismounting between oxidize nozzle and collector from structural design and exchange simpler.
Realize the technical scheme of the object of the invention: a kind of combined type replaceable nozzle tester, it comprises the fuel road inlet collector that inner band has cavity, in inlet collector both sides, fuel road, fuel road entrance is set respectively, fuel nozzle is arranged on inlet collector top, fuel road, and the position that fuel nozzle is positioned at the cavity of fuel road inlet collector is provided with fuel inlet; Oxidize nozzle is arranged on fuel nozzle top, and oxidize nozzle bottom extends into the bottom in fuel nozzle; Oxygenant road inlet collector is arranged on oxidize nozzle top, above the inlet collector of oxygenant road, arrange oxidant inlet; Fuel enters from the fuel road entrance of both sides, and fuel enters fuel nozzle through fuel road inlet collector again; Oxygenant enters from oxidant inlet, and oxygenant enters oxidize nozzle through oxygenant road inlet collector again.
A kind of combined type replaceable nozzle tester as above, the oxygenant road inlet collector described in it and oxidize nozzle contact position arrange first time axial sealing ring; Described oxidize nozzle and fuel nozzle contact position arrange the 3rd passage axial sealing ring; Described fuel nozzle and inlet collector upper contact place, fuel road arrange second time axial sealing ring, and lower contacts place arranges four-pass Axial and radial combined seal ring.
A kind of combined type replaceable nozzle tester as above, oxidize nozzle described in it, fuel nozzle are connected by multiple bolt and nuts that circumference is uniform with between oxygenant road inlet collector, fuel road inlet collector, and the oxidize nozzle and the fuel nozzle that realize different structure carry out dismounting and replacing.
A kind of combined type replaceable nozzle tester as above, the oxygenant road inlet collector described in it and fuel road inlet collector can realize sharing.
Effect of the present invention is: combined type replaceable nozzle tester of the present invention, solve the problem that in existing high pressure low temperature medium nozzle test unit, fuel and oxidize nozzle cannot be changed, make fuel and the dismounting between oxidize nozzle and collector from structural design and exchange more simple, what avoid common elements repeats operation simultaneously.Each test only needs refuelling nozzle and oxidize nozzle.This structure easy disassembly, can realize the positiver sealing of high pressure low temperature medium, is conducive to improving test efficiency, reduces costs.Test unit of the present invention sealing when carrying out spray test for high pressure low temperature liquid-propellant rocket engine fuel and oxidize nozzle is good, and the test period is short, and experimentation cost is low.
Accompanying drawing explanation
Fig. 1 is a kind of combined type replaceable nozzle tester structural representation of the present invention.
In figure: 1, oxidant inlet; 2, fuel road entrance; 3, oxygenant road inlet collector; 4, fuel road inlet collector; 5, oxidize nozzle; 6, fuel nozzle; 7, first time axial sealing ring; 8, second time axial sealing ring; 9, the 3rd passage axial sealing ring; 10, four-pass Axial and radial combined seal ring; 11, bolt and nut one; 12, bolt and nut two.
Embodiment
Below in conjunction with drawings and the specific embodiments, a kind of combined type replaceable nozzle tester of the present invention is described in further detail.
As shown in Figure 1, a kind of combined type replaceable nozzle tester of the present invention, it comprises the fuel road inlet collector 4 that inner band has cavity, in inlet collector 4 both sides, fuel road, fuel road entrance 2 is set respectively, fuel nozzle 6 is arranged on inlet collector 4 top, fuel road, and the position that fuel nozzle 6 is positioned at the cavity of fuel road inlet collector 4 is provided with fuel inlet;
Oxidize nozzle 5 is arranged on fuel nozzle 6 top, and oxidize nozzle 5 bottom extends into the bottom in fuel nozzle 6; Oxygenant road inlet collector 3 is arranged on oxidize nozzle 5 top, above oxygenant road inlet collector 3, arrange oxidant inlet 1;
Fuel enters from the fuel road entrance 2 of both sides, and fuel enters fuel nozzle 6 through fuel road inlet collector 4 again;
Oxygenant enters from oxidant inlet 1, and oxygenant enters oxidize nozzle 5 through oxygenant road inlet collector 3 again.
Described oxygenant road inlet collector 3 and oxidize nozzle 5 contact position arrange first time axial sealing ring 7; Described oxidize nozzle 5 arranges the 3rd passage axial sealing ring 9 with fuel nozzle 6 contact position; Described fuel nozzle 6 and inlet collector 4 upper contact place, fuel road arrange second time axial sealing ring 8, and lower contacts place arranges four-pass Axial and radial combined seal ring 10.
Described oxidize nozzle 5, fuel nozzle 6 are connected by multiple bolt and nuts that circumference is uniform with between oxygenant road inlet collector 3, fuel road inlet collector 4, and the oxidize nozzle 5 and the fuel nozzle 6 that realize different structure carry out dismounting and replacing.
Described oxygenant road inlet collector 3 and fuel road inlet collector 4 can realize sharing.
The present invention, according to the pressure distribution situation of different interface, adopts axial+radial multi-pass combined seal structure, achieves the sealing at diverse location place.Wherein oxygenant road inlet collector 3 and fuel road inlet collector 4 can realize sharing.Fuel of the present invention and adopt separate assembling to design between oxidize nozzle and collector, is bolted between each several part, achieves sharing of the conveniently replaced and hydrogen-oxygen collector of fuel and oxidize nozzle.
Claims (4)
1. a combined type replaceable nozzle tester, it is characterized in that: this device comprises fuel road inlet collector (4) that inner band has cavity, in inlet collector (4) both sides, fuel road, fuel road entrance (2) is set respectively, fuel nozzle (6) is arranged on inlet collector (4) top, fuel road, and the position that fuel nozzle (6) is positioned at the cavity on fuel road inlet collector (4) is provided with fuel inlet;
Oxidize nozzle (5) is arranged on fuel nozzle (6) top, and oxidize nozzle (5) bottom extends into the bottom in fuel nozzle (6); Oxygenant road inlet collector (3) is arranged on oxidize nozzle (5) top, arranges oxidant inlet (1) in top, oxygenant road inlet collector (3);
Fuel enters from fuel road entrance (2) of both sides, and fuel enters fuel nozzle (6) through fuel road inlet collector (4) again;
Oxygenant enters from oxidant inlet (1), and oxygenant enters oxidize nozzle (5) through oxygenant road inlet collector (3) again.
2. a kind of combined type replaceable nozzle tester according to claim 1, is characterized in that: described oxygenant road inlet collector (3) and oxidize nozzle (5) contact position arrange first time axial sealing ring (7); Described oxidize nozzle (5) and fuel nozzle (6) contact position arrange the 3rd passage axial sealing ring (9); Described fuel nozzle (6) and inlet collector (4) upper contact place, fuel road arrange second time axial sealing ring (8), and lower contacts place arranges four-pass Axial and radial combined seal ring (10).
3. a kind of combined type replaceable nozzle tester according to claim 1, it is characterized in that: described oxidize nozzle (5), fuel nozzle (6) are connected by multiple bolt and nuts that circumference is uniform with between oxygenant road inlet collector (3), fuel road inlet collector (4), and the oxidize nozzle (5) and the fuel nozzle (6) that realize different structure carry out dismounting and replacing.
4. a kind of combined type replaceable nozzle tester according to claim 1, is characterized in that: described oxygenant road inlet collector (3) and fuel road inlet collector (4) can realize sharing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510849780.1A CN105388007A (en) | 2015-11-27 | 2015-11-27 | Combined removable nozzle test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510849780.1A CN105388007A (en) | 2015-11-27 | 2015-11-27 | Combined removable nozzle test device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105388007A true CN105388007A (en) | 2016-03-09 |
Family
ID=55420549
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510849780.1A Pending CN105388007A (en) | 2015-11-27 | 2015-11-27 | Combined removable nozzle test device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105388007A (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106768946A (en) * | 2016-12-21 | 2017-05-31 | 成都航利航空科技有限责任公司 | A kind of fuel nozzle radial distribution comprehensive measurement device |
| CN107178437A (en) * | 2017-06-05 | 2017-09-19 | 上海空间推进研究所 | The burner of the miniature gentle bipropellant of gas |
| CN107588939A (en) * | 2017-09-11 | 2018-01-16 | 北京航空航天大学 | A kind of test tool of direct current centrifugation two-component injector element |
| CN110108446A (en) * | 2019-05-16 | 2019-08-09 | 中国科学院理化技术研究所 | A kind of single channel nozzle model testboard |
| CN110735732A (en) * | 2019-09-23 | 2020-01-31 | 北京航天动力研究所 | A multifunctional removable nozzle test device |
| CN111912614A (en) * | 2020-08-11 | 2020-11-10 | 江苏深蓝航天有限公司 | Centrifugal nozzle liquid flow test device of liquid rocket engine |
| CN112557044A (en) * | 2020-11-25 | 2021-03-26 | 西安航天动力研究所 | Double-component nozzle liquid flow performance testing device |
| CN115853670A (en) * | 2022-11-30 | 2023-03-28 | 上海空间推进研究所 | Reliable sealing structure for isolating bipropellant spontaneous combustion propellant |
| CN115853670B (en) * | 2022-11-30 | 2025-03-28 | 上海空间推进研究所 | Reliable sealing structure for isolating bipropellant hypergolic propellants |
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| WO1999039833A1 (en) * | 1998-02-05 | 1999-08-12 | L'air Liquide, Societe Anonyme Pour L'etude Et L'exploitation Des Procedes Georges Claude | Low firing rate oxy-fuel burner |
| US20060157108A1 (en) * | 2005-01-18 | 2006-07-20 | Mills Douglas W | Control valve for nitrous oxide injection system |
| CN101738326A (en) * | 2008-11-11 | 2010-06-16 | 北京航空航天大学 | Gas-gas single-nozzle experimental device |
| CN101782029A (en) * | 2009-01-15 | 2010-07-21 | 北京航空航天大学 | Device for testing flow characteristics of gas-gas nozzle |
| CN101956981A (en) * | 2010-07-08 | 2011-01-26 | 中国航天科技集团公司第六研究院第十一研究所 | Gas-liquid component high chamber-pressure large-range variable working condition combustor |
| CN102062020A (en) * | 2011-01-05 | 2011-05-18 | 北京航空航天大学 | Transparent combustion chamber with square interior passage |
| CN203570457U (en) * | 2013-10-28 | 2014-04-30 | 北京航天动力研究所 | Two-stage mixing type nozzle device |
| CN103867340A (en) * | 2012-12-12 | 2014-06-18 | 中国人民解放军国防科学技术大学 | Dual-rotational-flow inspirator |
-
2015
- 2015-11-27 CN CN201510849780.1A patent/CN105388007A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
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| WO1999039833A1 (en) * | 1998-02-05 | 1999-08-12 | L'air Liquide, Societe Anonyme Pour L'etude Et L'exploitation Des Procedes Georges Claude | Low firing rate oxy-fuel burner |
| US20060157108A1 (en) * | 2005-01-18 | 2006-07-20 | Mills Douglas W | Control valve for nitrous oxide injection system |
| CN101738326A (en) * | 2008-11-11 | 2010-06-16 | 北京航空航天大学 | Gas-gas single-nozzle experimental device |
| CN101782029A (en) * | 2009-01-15 | 2010-07-21 | 北京航空航天大学 | Device for testing flow characteristics of gas-gas nozzle |
| CN101956981A (en) * | 2010-07-08 | 2011-01-26 | 中国航天科技集团公司第六研究院第十一研究所 | Gas-liquid component high chamber-pressure large-range variable working condition combustor |
| CN102062020A (en) * | 2011-01-05 | 2011-05-18 | 北京航空航天大学 | Transparent combustion chamber with square interior passage |
| CN103867340A (en) * | 2012-12-12 | 2014-06-18 | 中国人民解放军国防科学技术大学 | Dual-rotational-flow inspirator |
| CN203570457U (en) * | 2013-10-28 | 2014-04-30 | 北京航天动力研究所 | Two-stage mixing type nozzle device |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106768946A (en) * | 2016-12-21 | 2017-05-31 | 成都航利航空科技有限责任公司 | A kind of fuel nozzle radial distribution comprehensive measurement device |
| CN106768946B (en) * | 2016-12-21 | 2023-06-23 | 成都航利航空科技有限责任公司 | Comprehensive measuring device for radial distribution of fuel nozzle |
| CN107178437A (en) * | 2017-06-05 | 2017-09-19 | 上海空间推进研究所 | The burner of the miniature gentle bipropellant of gas |
| CN107178437B (en) * | 2017-06-05 | 2019-01-08 | 上海空间推进研究所 | The burner of the miniature gentle bipropellant of gas |
| CN107588939A (en) * | 2017-09-11 | 2018-01-16 | 北京航空航天大学 | A kind of test tool of direct current centrifugation two-component injector element |
| CN110108446A (en) * | 2019-05-16 | 2019-08-09 | 中国科学院理化技术研究所 | A kind of single channel nozzle model testboard |
| CN110735732A (en) * | 2019-09-23 | 2020-01-31 | 北京航天动力研究所 | A multifunctional removable nozzle test device |
| CN111912614A (en) * | 2020-08-11 | 2020-11-10 | 江苏深蓝航天有限公司 | Centrifugal nozzle liquid flow test device of liquid rocket engine |
| CN112557044A (en) * | 2020-11-25 | 2021-03-26 | 西安航天动力研究所 | Double-component nozzle liquid flow performance testing device |
| CN112557044B (en) * | 2020-11-25 | 2021-11-02 | 西安航天动力研究所 | Double-component nozzle liquid flow performance testing device |
| CN115853670A (en) * | 2022-11-30 | 2023-03-28 | 上海空间推进研究所 | Reliable sealing structure for isolating bipropellant spontaneous combustion propellant |
| CN115853670B (en) * | 2022-11-30 | 2025-03-28 | 上海空间推进研究所 | Reliable sealing structure for isolating bipropellant hypergolic propellants |
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Application publication date: 20160309 |
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| RJ01 | Rejection of invention patent application after publication |