CN101832198A - Hydrogen-oxygen oxygen-rich preburner of full flow staged combustion cycle engine - Google Patents
Hydrogen-oxygen oxygen-rich preburner of full flow staged combustion cycle engine Download PDFInfo
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- CN101832198A CN101832198A CN200810225993A CN200810225993A CN101832198A CN 101832198 A CN101832198 A CN 101832198A CN 200810225993 A CN200810225993 A CN 200810225993A CN 200810225993 A CN200810225993 A CN 200810225993A CN 101832198 A CN101832198 A CN 101832198A
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- oxygen
- precombustion chamber
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- hydrogen
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Abstract
The invention relates to a hydrogen-oxygen oxygen-rich preburner used for a full flow staged combustion cycle engine system and belongs to the field of rocket engine structure design. The preburner comprises a gas dynamic resonance ignitor (1), a head part (2), a secondary injection segment (3), an adjustment segment (4), an exit segment (5), wherein the gas dynamic resonance ignitor (1) is arranged on the central axis of the head part (2) of the oxygen-rich preburner and is in threaded connection with the oxygen-rich preburner; the combustion gases of the ignitor are hydrogen and oxygen; as all the hydrogen is introduced into the oxygen-rich preburner through the ignitor, a hydrogen injector is removed from the structure of the head part of the oxygen-rich preburner; secondary injection is adopted in an oxygen-rich preburner body part, and a plurality of circles of radial oxygen injection holes are formed on the secondary injection segment (3); the adjustment segment (5) can adjust the length of the preburner and the axial position of the secondary injection; and the whole body of the oxygen-rich preburner is oxidation resistant due to nickel plating.
Description
[technical field]
The present invention relates to a kind of gas hydrogen-oxygen oxygen-rich precombustion chamber conceptual design that is used for full flow afterburning cycle engine system, belong to the rocket motor structure design field.
[background technique]
The full flow afterburning circulatory system is a kind of novel rocket motor circulatory system, is the grading combustion technology that has high burning performance at present, is one of important development developing direction of liquid propellant rocket engine technology.In full flow afterburning cycle engine system, because its all propellant agents all will enter the precombustion chamber burning, therefore, its oxygen enrichment precombustion chamber proportions of ingredients is very high, and the technical research of oxygen enrichment precombustion chamber is one of key technology of full flow afterburning cycle engine system.
In the gas hydrogen oxygen full flow afterburning cycle engine design of small flow, because hydrogen flowing quantity is little, the structural design difficulty of oxygen enrichment precombustion chamber is big.At first, hydrogen flowing quantity is very little, hydrogen flowing quantity control and hydrogen ejector filler design difficulty are big, igniting, flame is kept and is spread difficulty, as document S.Farhangi, K.hunt, L.Tuegel, D.matthews, and S.Fisher " Oxidizer-rich Preburner for Advanced Rocket Engine Application " AIAA 94-3260 is described, the propellant agent of the designed oxygen enrichment precombustion chamber of the document is liquid oxygen/gas hydrogen, compares gas hydrogen/gas oxygen oxygen-rich precombustion chamber, and proportions of ingredients is low under the uniform temp, hydrogen flowing quantity is big under the identical total discharge, and the design of hydrogen ejector filler is simple relatively.Secondly, oxygen proportion is big, and the uniformity coefficient of combustion gas blending is difficult to solve, in the lower oxygen enrichment circulatory system of proportions of ingredients, the general secondary spray modular construction that adopts, promptly in nozzle, carry out the secondary blending, as the precious unit of document Wu, Ge Lihu, Tan Yonghua, Liu Hongjun " experimental study of oxygen enrichment precombustion chamber high pressure reduced scale " is described, but this kind method is applied to have higher proportions of ingredients, and it is big that the hydrogen-oxygen ratio differs on the more greatly different full flow gas hydrogen-oxygen oxygen-rich precombustion chamber difficulty.The 3rd, high oxygen-enriched environment has high requirements to the oxidation resistance of oxygen enrichment precombustion chamber, usually adopt special oxidation resistant coating or oxidation-resistant material to make the oxygen enrichment precombustion chamber, the cost height, as document William M.Marshall, Sibtosh Pal, etc. " Benchmark Wall Heat Flux Data for a GO
2/ GH
2Single Element Combustor " .AIAA2005-3572 is described.
[summary of the invention]
The purpose of this invention is to provide a kind of simple in structure, igniting is reliable, blending evenly, the gas hydrogen-oxygen oxygen-rich precombustion chamber of good in oxidation resistance.
A kind of gas hydrogen-oxygen oxygen-rich precombustion chamber comprises Pneumatic resonance igniter 1, head 2, secondary spray section 3, adjustment section 4, outlet section 5 compositions.Pneumatic resonance igniter 1 is installed on oxygen enrichment precombustion chamber head 2, adopts scyewed joint with the oxygen enrichment precombustion chamber, and the igniter combustion gas are hydrogen and oxygen; All hydrogen enter the oxygen enrichment precombustion chamber by igniter, do not have the hydrogen ejector filler in the oxygen enrichment pre-combustion chamber, and circumferential weld oxygenating burning is adopted in the igniter outlet; Oxygen enrichment precombustion chamber body portion adopts the secondary spray, and secondary spray section 3 has radially oxygen spray orifice of multi-turn; Adjust the axial position of section 5 adjustable firing chamber length and secondary spray; The whole nickel plating of oxygen enrichment precombustion chamber is anti-oxidant.
Advantage and good effect that gas hydrogen-oxygen oxygen-rich precombustion chamber of the present invention has are: (1) has adopted technology maturation Pneumatic resonance igniter, but relight, independent debugging, ignition duration can be adjusted, and can split with the oxygen enrichment precombustion chamber, therefore the igniter working state can be transferred to the stable igniting that is used further to implement to the oxygen enrichment precombustion chamber, reduce the test difficulty, improved the reliability of igniting; (2) the igniter combustion gas are hydrogen and oxygen, can introduce from oxygen enrichment precombustion chamber supply air line, have simplified pilot system; (3) ignitor has the dual functions of igniting and supply of hydrogen, and ignition phase provides reliable igniting, provides concentrated hydrogen supply after igniting is finished.(4) hydrogen centralizedly supply is beneficial to burning and flame holding.(5) the igniter outlet is positioned at oxygen enrichment precombustion chamber spray face plate center, adopts circumferential weld oxygenating scheme, and the ablation spray panel of avoiding refluxing has also farthest reduced the probability that high-temperature oxygen-enriched combustion gas is ablated and avoided.(5) do not have the hydrogen ejector filler in the oxygen enrichment pre-combustion chamber, reduced design difficulty, do not have the consideration of hydrogen supply sequential in the sequential yet, reduced the test difficulty; (6) adopted radially secondary spray means, the oxygen disturbance flow field of spray helps improving the combustion gas uniformity; (7) adopted the adjustment segment structure, adjusting section can change, can adopt different adjustment segment length to change firing chamber length, be beneficial to carrying out of experimental study, simultaneously, adjust section both can be installed on also can be installed on secondary spray section before the secondary spray section after, can adjust the position of secondary spray, be beneficial to secondary spray The Characteristic Study; (8) whole nickel plating, the nickel plating technology maturation, technology is simple, and is with low cost, has good oxidation resistance again.
[description of drawings]
Fig. 1 is oxygen enrichment pre-combustion chamber figure
Fig. 2 is an oxygen enrichment precombustion-chamber ignition device export structure schematic representation
[embodiment]
Further specify the present invention below in conjunction with accompanying drawing.
Pneumatic resonance igniter 1 is connected with oxygen enrichment precombustion chamber head 2 by screw thread, and the igniter entry position is a head spray face plate center.The igniter combustion gas are hydrogen and oxygen, during test, enter the oxygen enrichment precombustion chamber after by air resonance heating resonatron hydrogen and oxygen being lighted and implement igniting.Hydrogen and oxygen is introduced from oxygen enrichment precombustion chamber supply line.
After the igniting process, close the igniter oxygen supply, keep on the hydrogen road, and igniter is converted to the hydrogen ejector filler.Because hydrogen all enters the oxygen enrichment precombustion chamber from the igniter outlet, has reduced the proportions of ingredients of center region, be beneficial to the stable and propagation of combustion flame.Adopt circumferential weld oxygenating combustion scheme in the igniter ingress of oxygen enrichment precombustion chamber, avoid fuel gas return-flow, as shown in Figure 2.
Secondary spray section 3 aerobic air cavitys and oxygen spray orifice, spray oxygen radially, the blending of combustion gas is promoted in the disturbance flow field, improves the combustion gas uniformity.
Adjusting section 4 can be installed between secondary spray section 3 and the outlet section 5, also can be installed between head 2 and the secondary spray section 3, or do not install or change the different secondary spray section of thickness, realize oxygen enrichment precombustion chamber experimental study different length, different secondary spray position.
All the structural entity nickel plating of oxygen enrichment precombustion chamber are anti-oxidant.
Claims (10)
1. gas hydrogen-oxygen oxygen-rich precombustion chamber, comprise igniter (1), head (2), secondary spray section (3), adjust section (4), outlet section (5), igniter is installed on the oxygen enrichment precombustion chamber head center axis, it is characterized in that: described igniter is the Pneumatic resonance igniter.
2. gas hydrogen-oxygen oxygen-rich precombustion chamber as claimed in claim 1 is characterized in that: the Pneumatic resonance igniter adopts hydrogen and oxygen as propellant agent, and hydrogen and oxygen provide by oxygen enrichment precombustion chamber air supply system.
3. gas hydrogen-oxygen oxygen-rich precombustion chamber according to claim 2 is characterized in that: all hydrogen enters from igniter.
4. gas hydrogen-oxygen oxygen-rich precombustion chamber according to claim 3 is characterized in that: the Pneumatic resonance igniter adopts with the oxygen enrichment precombustion chamber and is threaded, and the Pneumatic resonance igniter can be debugged separately.
5. according to the described gas hydrogen-oxygen oxygen-rich of claim 1～4 precombustion chamber, it is characterized in that: circumferential weld oxygenating burning is adopted in the igniter outlet.
6. according to the described gas hydrogen-oxygen oxygen-rich of claim 1～4 precombustion chamber, it is characterized in that: oxygen enrichment precombustion chamber body portion is provided with secondary spray oxygen structure.
7. according to the described gas hydrogen-oxygen oxygen-rich of claim 1～4 precombustion chamber, it is characterized in that: adjust section and can install and not install, can be installed between head and the secondary spray section or between secondary spray section and the outlet section, perhaps change different-thickness and adjust the section installation.
8. gas hydrogen-oxygen oxygen-rich precombustion chamber according to claim 1 is characterized in that: secondary spray position can be by adjusting section adjustment.
9. gas hydrogen-oxygen oxygen-rich precombustion chamber according to claim 1 is characterized in that: oxygen enrichment precombustion chamber length can be by adjusting section adjustment.
10. gas hydrogen-oxygen oxygen-rich precombustion chamber according to claim 1 is characterized in that: all structural member plating nickel on surface of oxygen enrichment precombustion chamber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200810225993A CN101832198A (en) | 2009-03-10 | 2009-03-10 | Hydrogen-oxygen oxygen-rich preburner of full flow staged combustion cycle engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200810225993A CN101832198A (en) | 2009-03-10 | 2009-03-10 | Hydrogen-oxygen oxygen-rich preburner of full flow staged combustion cycle engine |
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| CN101832198A true CN101832198A (en) | 2010-09-15 |
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| CN200810225993A Pending CN101832198A (en) | 2009-03-10 | 2009-03-10 | Hydrogen-oxygen oxygen-rich preburner of full flow staged combustion cycle engine |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102022225A (en) * | 2010-12-30 | 2011-04-20 | 北京航空航天大学 | Test unit for hydrogen-rich/ oxygen-rich gas multinozzle gas-gas injector |
| CN104712462A (en) * | 2015-01-14 | 2015-06-17 | 北京理工大学 | Secondary fluid jet thrust adjusting device with changeable jet pipe |
| CN108915899A (en) * | 2018-06-29 | 2018-11-30 | 北京航天动力研究所 | A kind of three chamber ejector filler of four bottom |
| CN109781422A (en) * | 2018-12-09 | 2019-05-21 | 西安航天动力试验技术研究所 | A kind of simulation incoming flow heating device of wide scope |
-
2009
- 2009-03-10 CN CN200810225993A patent/CN101832198A/en active Pending
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102022225A (en) * | 2010-12-30 | 2011-04-20 | 北京航空航天大学 | Test unit for hydrogen-rich/ oxygen-rich gas multinozzle gas-gas injector |
| CN102022225B (en) * | 2010-12-30 | 2013-03-27 | 北京航空航天大学 | Test device for hydrogen-rich/oxygen-rich gas multinozzle gas-gas injector |
| CN104712462A (en) * | 2015-01-14 | 2015-06-17 | 北京理工大学 | Secondary fluid jet thrust adjusting device with changeable jet pipe |
| CN108915899A (en) * | 2018-06-29 | 2018-11-30 | 北京航天动力研究所 | A kind of three chamber ejector filler of four bottom |
| CN108915899B (en) * | 2018-06-29 | 2020-02-14 | 北京航天动力研究所 | Four-bottom three-cavity injector |
| CN109781422A (en) * | 2018-12-09 | 2019-05-21 | 西安航天动力试验技术研究所 | A kind of simulation incoming flow heating device of wide scope |
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Application publication date: 20100915 |