CN102207043A - Gaseous hydrogen/gaseous oxygen eddy current cooling thrust chamber injector - Google Patents
Gaseous hydrogen/gaseous oxygen eddy current cooling thrust chamber injector Download PDFInfo
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- CN102207043A CN102207043A CN2011101076517A CN201110107651A CN102207043A CN 102207043 A CN102207043 A CN 102207043A CN 2011101076517 A CN2011101076517 A CN 2011101076517A CN 201110107651 A CN201110107651 A CN 201110107651A CN 102207043 A CN102207043 A CN 102207043A
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Abstract
The invention provides a gaseous hydrogen/gaseous oxygen eddy current cooling thrust chamber injector, which comprises an injector head, a turbulent flow disc, an injection panel, a combustion chamber, a gaseous oxygen injection ring and an injection pipe. The injector has a simple structure, and a gaseous oxygen nozzle inclines upwards along the inner wall surface of the combustion chamber, so that the stability of external eddy current and the cooling effect are improved; the problem that the cooling effect is unsatisfactory because the wall surface temperature of the combustion chamber is high is solved; and the gaseous hydrogen/gaseous oxygen eddy current cooling thrust chamber injector can be applied to a thrust chamber with the thrust of 3,000N and the pressure of the combustion chamber of 2MPa.
Description
Technical field
The invention belongs to liquid propellant rocket engine Push Technology field, be specifically related to a kind of gas hydrogen/gas oxygen eddy current Cooling Thrust Chamber ejector filler.
Background technique
Thrust chamber eddy current cooling technology is a kind of novel thrust chamber notion that U.S. ORBITEC company proposes, mix, burn in the inside that propellant agent is limited in the eddy region of two bursts of coaxial rotations, the perimeter of eddy current can stop high-temperature combustion product to contact with the firing chamber internal face.Adopt thrust chamber eddy current cooling technology, can solve the problem of the serious thermal force that combustor surface produces owing to propellant combustion.
Compare with traditional regeneration cooling means, eddy current Cooling Thrust Chamber technology mainly contains following characteristics: (1) reduces the pressure loss of the freezing mixture of the cooling that is used to regenerate; (2) because eddy current as effective combustion stabilizer, has improved the stability of burning; (3) can improve the cooling problem of some motors, for example, the motor that thrust is less, because coolant flow is little, the flowing coolant flow could satisfy and cools off requirement in needing to increase, this can increase specific impulse loss; (4) for the motor that acts as a fuel with kerosene, adopt the eddy current cooling technology, can avoid the problem of kerosene coking; (5) adopt the eddy current cooling technology, the firing chamber cylindrical section has been cancelled the sandwich structure of regeneration cooling, thereby has reduced the weight of firing chamber.
Eddy current cooled engine interior flow field is two-way vortex structure, and inside is the reaction stream whirlpool, and the outside is the cool stream whirlpool.From the characteristics of thrust chamber eddy current cooling technology as can be seen, the oxygenant ejector filler that is positioned at the bottom, firing chamber directly affects the cooling effect of wall, and the combustion efficiency of firing chamber is relevant with the propellant spray device at top, so the form of ejector filler is extremely important to the performance of eddy current cooled engine.
From the external various documents of delivering, the arrangement mode of fuel nozzle has two kinds: axially and radially, and the arrangement of oxidize nozzle has only circumferential formula.Though fuel nozzle radially spray has reasonable performance, can destroy outside vortex structure, reduced the cooling effect of wall.According to the characteristics of outer vortex, oxygenant is zero in the axial velocity of top of combustion chamber, and therefore, the axially-aligned of fuel nozzle makes the top of propellant combustion regional centralized in the firing chamber, causes the top of combustion chamber thermal force big, the temperature height.
Summary of the invention
At the problem that exists in the existing thrust chamber eddy current cooling technology, the present invention proposes a kind of gas hydrogen/gas oxygen eddy current Cooling Thrust Chamber ejector filler, has solved chamber wall surface temperature height, the unfavorable problem of cooling effect.Gas hydrogen/gas oxygen eddy current Cooling Thrust Chamber ejector filler that the present invention proposes has been applied to thrust 3000N, and chamber pressure is on the thrust chamber of 2MPa.
A kind of gas hydrogen/gas oxygen eddy current Cooling Thrust Chamber ejector filler is characterized in that: comprise ejector filler head, flow-disturbing dish, spray panel, firing chamber, gas oxygen spray ring and jet pipe;
Described ejector filler head is a slab construction, the bottom has groove A, the ejector filler head is evenly distributed with a plurality of through hole H at the outward edge of groove A, the central position of ejector filler head has through hole A, in the through hole A spark plug is installed, at the bilateral symmetry of through hole A distribute porose B and hole C, the below that is positioned at hole B and hole C is provided with the gas hydrogen liquid collecting cavity of annular, this gas hydrogen liquid collecting cavity is communicated with hole B, hole C, the neutral position of gas hydrogen liquid collecting cavity depth direction is fixed with the flow-disturbing dish, and gas hydrogen liquid collecting cavity is divided into two cavitys up and down;
Described firing chamber is a hollow structure, and the outer wall of top of combustion chamber circumferentially is fixed with flange plate A, and the through hole H on flange plate A and the ejector filler head is bolted to connection; Also be fixed with the spray panel between the groove A of ejector filler head and the top of combustion chamber;
Described spray panel is a disk construction, the spray panel has groove B on the upper surface of groove A, the spray face plate center has through hole E, by the fixing spark plug of through hole E and through hole A, be evenly distributed with a plurality of ladder hole F in the periphery of through hole E, be used for fixing gas hydrogen nozzle;
The bottom of described firing chamber is connected with gas oxygen spray ring, gas oxygen spray ring is the ring flake structure of hollow, be evenly distributed with a plurality of hole M on its wall, the outer rim of bottom, firing chamber and the outer wall of gas oxygen spray ring circumferentially are fixed with flange plate B, flange plate B circumferentially is evenly distributed with a plurality of through hole G, and also be symmetrically distributed with 2 shoulder hole K between the center of through hole G and flange plate B, through hole G fixes by bolt and jet pipe, and shoulder hole K is used to install gas oxygen connecting-tube nozzle; Flange plate B below shoulder hole K also has annular chamber B, the sidewall at the close flange plate B center of the outer wall looping chamber B of gas oxygen spray ring, gas oxygen flows among the annular chamber B through shoulder hole, and the hole M on gas oxygen spray ring arrives inside, firing chamber again, and hole M forms gas oxygen nozzle;
The bottom of gas oxygen spray ring connects jet pipe, and the outer wall at jet pipe top is fixed with flange plate C, fixes by flange plate C and flange plate B, realizes the fixing of jet pipe and firing chamber; The upper surface of flange plate C has annular chamber C, and this annular chamber C top is communicated with the bottom of annular chamber B, forms closed cavity.
The advantage that the present invention has is:
(1) the gas hydrogen/gas oxygen eddy current Cooling Thrust Chamber ejector filler of the present invention's proposition, gas oxygen nozzle is inclined upwardly along the firing chamber internal face, has improved the stability of outer vortex, has improved cooling effect.
(2) the gas hydrogen/gas oxygen eddy current Cooling Thrust Chamber ejector filler of the present invention's proposition, gas hydrogen nozzle stretches into the firing chamber, the combustion chambers burn center region is moved down, and the spray panel is formed effective protection.
(3) the gas hydrogen/gas oxygen eddy current Cooling Thrust Chamber ejector filler of the present invention's proposition, simple in structure, nozzle is the direct current well format.
Description of drawings
Fig. 1: the sectional drawing of gas hydrogen/gas oxygen eddy current Cooling Thrust Chamber ejector filler that the present invention proposes;
Fig. 2: the ejector filler head plan view of gas hydrogen/gas oxygen eddy current Cooling Thrust Chamber ejector filler that the present invention proposes;
Fig. 3: the ejector filler head sectional drawing of gas hydrogen/gas oxygen eddy current Cooling Thrust Chamber ejector filler that the present invention proposes;
Fig. 4: the flow-disturbing dish plan view of gas hydrogen/gas oxygen eddy current Cooling Thrust Chamber ejector filler that the present invention proposes;
Fig. 5: the firing chamber sectional drawing of gas hydrogen/gas oxygen eddy current Cooling Thrust Chamber ejector filler that the present invention proposes;
Fig. 6: the flange plate A plan view of gas hydrogen/gas oxygen eddy current Cooling Thrust Chamber ejector filler that the present invention proposes;
Fig. 7: the spray panel sectional drawing of gas hydrogen/gas oxygen eddy current Cooling Thrust Chamber ejector filler that the present invention proposes;
Fig. 8: the flange plate B plan view of gas hydrogen/gas oxygen eddy current Cooling Thrust Chamber ejector filler that the present invention proposes;
Fig. 9: the gas oxygen spray ring sectional drawing of gas hydrogen/gas oxygen eddy current Cooling Thrust Chamber ejector filler that the present invention proposes;
Figure 10: the jet pipe sectional drawing of gas hydrogen/gas oxygen eddy current Cooling Thrust Chamber ejector filler that the present invention proposes.
Among the figure:
1-ejector filler head 2-flow-disturbing dish 3-spray panel 4-firing chamber
5-gas oxygen spray ring 6-jet pipe 7-groove A 8-through hole A
B 10-hole, 9-hole C 11-through hole D 12-flange plate A
13-groove B 14-through hole E 15-ladder hole F 16-flange plate B
17-shoulder hole G 18-flange plate C 19-annular chamber C 20-through hole H
21-gas hydrogen nozzle 22-shoulder hole K 23-gas hydrogen liquid collecting cavity 24-annular chamber B
25-hole M
Embodiment
The present invention will be further described below in conjunction with accompanying drawing:
A kind of gas hydrogen/gas oxygen eddy current Cooling Thrust Chamber ejector filler that the present invention proposes as shown in Figure 1, comprises ejector filler head 1, flow-disturbing dish 2, spray panel 3, firing chamber 4, gas oxygen spray ring 5 and jet pipe 6.
As Fig. 2, shown in Figure 3, described ejector filler head 1 is a slab construction, and the bottom has groove A7, and ejector filler head 1 is evenly distributed with a plurality of through hole H20 at the outward edge of groove A7, and the number of through hole H20 is preferably more than 8; The central position of ejector filler head 1 has through hole A8, in the through hole A8 spark plug is installed, at the bilateral symmetry of through hole A8 distribute porose B9 and hole C10, the below that is positioned at hole B9 and hole C10 is provided with the gas hydrogen liquid collecting cavity 23 of annular, this gas hydrogen liquid collecting cavity 23 is communicated with hole B9 and hole C10, the neutral position of gas hydrogen liquid collecting cavity 23 depth directions is fixed with flow-disturbing dish 2, and gas hydrogen liquid collecting cavity 23 is divided into two cavitys up and down.As shown in Figure 4, described flow-disturbing dish 2 has the plane disc structure of through hole for the center, and the surface has some through hole D11, and the number of through hole D11 is preferably more than 90, is fixed in gas hydrogen liquid collecting cavity 23 centers, and the surface of flow-disturbing dish is surperficial parallel with the ejector filler head.
As Fig. 5, described firing chamber 4 is a hollow structure, the outer wall at 4 tops, firing chamber circumferentially is fixed with flange plate A12, is connected with ejector filler head 1 by this flange plate A12, and the through hole H that is specially flange plate A12 and ejector filler head 1 edge is bolted to connection.The structure of flange plate A as shown in Figure 6.Be connected by the bottom with ejector filler head 1, the groove A7 of ejector filler head 1 and firing chamber 4 top link positions also are fixed with spray panel 3, make the bottom surface of spray panel seal the top of the hollow of firing chamber 4.As Fig. 7, described spray panel 3 is a disk construction, and the spray panel has groove B13 on the upper surface of groove A, and the spray face plate center has through hole E14, by the fixing spark plug of through hole E14 and through hole A8.Be evenly distributed with a plurality of ladder hole F15 in the periphery of through hole E14, be used for fixing gas hydrogen nozzle 21, the lower surface of spray panel is exposed in the bottom of gas hydrogen nozzle 21, places in the firing chamber.Described ladder hole F15 is preferably 6-12.
The bottom of described firing chamber 4 is connected with gas oxygen spray ring 5, the outer wall of the outer rim of 4 bottoms, firing chamber and gas oxygen spray ring 5 circumferentially is fixed with flange plate B16, flange plate B16 circumferentially is evenly distributed with a plurality of through hole G17 (being preferably 8), and between the center of through hole G17 and flange plate B16, also be symmetrically distributed with 2 shoulder hole K22, as shown in Figure 8, through hole G17 is fixing by bolt and jet pipe 6, shoulder hole K22 is used to install gas oxygen connecting-tube nozzle, below shoulder hole K22, flange plate B16 also has annular chamber B24, as shown in Figure 9, gas oxygen spray ring is the ring flake structure of hollow, be evenly distributed with a plurality of hole M25 on its wall, be used to the oxygen that circulates, the sidewall at the close flange plate B16 center of the outer wall looping chamber B24 of gas oxygen spray ring 5, make gas oxygen through shoulder hole K22, flow among the annular chamber B24, arrive 4 inside, firing chamber through annular chamber B24 by the hole M25 on the gas oxygen spray ring 5 again, central axis and the horizontal plane of its mesopore M25 form an angle, hole M25 promptly forms gas oxygen nozzle, is used for spray oxygen.
The bottom of gas oxygen spray ring 5 connects jet pipe 6, nozzle structure as shown in figure 10, the outer wall at jet pipe 6 tops is fixed with flange plate C18, fixes by flange plate C18 and flange plate B16, and then realizes fixing of jet pipe 6 and firing chamber 4.The upper surface of flange plate C18 (with flange plate B16 facing surfaces) has annular chamber C19, the top of this annular chamber C19 is communicated with the bottom of annular chamber B24, annular chamber B24 and annular chamber C18 form the cavity of a closure, provide bigger flowing lumen for gas flows into 4 inside, firing chamber.
As shown in Figure 1, gas hydrogen is from gas hydrogen connecting-tube nozzle (the hole B9 of ejector filler head 1, hole C10) enters in turn in the gas hydrogen nozzle 21 among the ladder hole F15 on through hole D11 on ejector filler head 1, the flow-disturbing dish 2, gas hydrogen liquid collecting cavity 23, the spray panel 3, form gas hydrogen circulation passage.Gas oxygen enters flange plate B16 from the gas oxygen connecting-tube nozzle (shoulder hole K22) of flange plate B16, enter annular chamber C19 then, the hole M25 of the formation gas oxygen nozzle on the gas oxygen spray ring 5 sprays in the firing chamber 4 along firing chamber 4 internal faces obliquely, forms gas oxygen flow circulation passage.
Outstandingly among the present invention designed gas hydrogen nozzle 21 and stretched into the length of firing chamber and the setting at gas oxygen nozzle N27 angle of inclination.The length that gas hydrogen nozzle stretches into the firing chamber is 20%～30% of firing chamber radius, and gas hydrogen nozzle is fixed among the ladder hole F15 of spray panel, and the length of exposing spray panel lower surface is the length that gas hydrogen nozzle stretches into the firing chamber.The central axis of the hole M25 of formation gas oxygen nozzle and the angle of horizontal plane angle are 10 °～25 °.Hard-wired gas hydrogen nozzle 21 on spray panel 3, end stretches among the firing chamber 4, the combustion centre zone of firing chamber 4 is moved down, and spray panel 3 is formed effectively protection; The gas oxygen nozzle N27 that 4 bottom gas oxygen spray rings 5 are installed in the firing chamber sprays in the firing chamber 4 obliquely along firing chamber 4 internal faces, has improved the stability of outer vortex, and firing chamber 4 internal face temperature are reduced.
Claims (7)
1. gas hydrogen/gas oxygen eddy current Cooling Thrust Chamber ejector filler is characterized in that: comprise ejector filler head, flow-disturbing dish, spray panel, firing chamber, gas oxygen spray ring and jet pipe;
Described ejector filler head is a slab construction, the bottom has groove A, the ejector filler head is evenly distributed with a plurality of through hole H at the outward edge of groove A, the central position of ejector filler head has through hole A, in the through hole A spark plug is installed, at the bilateral symmetry of through hole A distribute porose B and hole C, the below that is positioned at hole B and hole C is provided with the gas hydrogen liquid collecting cavity of annular, this gas hydrogen liquid collecting cavity is communicated with hole B, hole C, the neutral position of gas hydrogen liquid collecting cavity depth direction is fixed with the flow-disturbing dish, and gas hydrogen liquid collecting cavity is divided into two cavitys up and down;
Described firing chamber is a hollow structure, and the outer wall of top of combustion chamber circumferentially is fixed with flange plate A, and the through hole H on flange plate A and the ejector filler head is bolted to connection; Also be fixed with the spray panel between the groove A of ejector filler head and the top of combustion chamber;
Described spray panel is a disk construction, the spray panel has groove B on the upper surface of groove A, the spray face plate center has through hole E, by the fixing spark plug of through hole E and through hole A, be evenly distributed with a plurality of ladder hole F in the periphery of through hole E, be used for fixing gas hydrogen nozzle;
The bottom of described firing chamber is connected with gas oxygen spray ring, gas oxygen spray ring is the ring flake structure of hollow, be evenly distributed with a plurality of hole M on its wall, the outer rim of bottom, firing chamber and the outer wall of gas oxygen spray ring circumferentially are fixed with flange plate B, flange plate B circumferentially is evenly distributed with a plurality of through hole G, and also be symmetrically distributed with 2 shoulder hole K between the center of through hole G and flange plate B, through hole G fixes by bolt and jet pipe, and shoulder hole K is used to install gas oxygen connecting-tube nozzle; Flange plate B below shoulder hole K also has annular chamber B, the sidewall at the close flange plate B center of the outer wall looping chamber B of gas oxygen spray ring, gas oxygen flows among the annular chamber B through shoulder hole, and the hole M on gas oxygen spray ring arrives inside, firing chamber again, and hole M forms gas oxygen nozzle;
The bottom of gas oxygen spray ring connects jet pipe, and the outer wall at jet pipe top is fixed with flange plate C, fixes by flange plate C and flange plate B, realizes the fixing of jet pipe and firing chamber; The upper surface of flange plate C has annular chamber C, and this annular chamber C top is communicated with the bottom of annular chamber B, forms closed cavity.
2. a kind of gas hydrogen according to claim 1/gas oxygen eddy current Cooling Thrust Chamber ejector filler, it is characterized in that: the length that described gas hydrogen nozzle stretches into the firing chamber is 20%～30% of firing chamber radius.
3. a kind of gas hydrogen according to claim 1/gas oxygen eddy current Cooling Thrust Chamber ejector filler, it is characterized in that: the central axis of described hole M and the angle of horizontal plane are 10 °～25 °.
4. a kind of gas hydrogen according to claim 1/gas oxygen eddy current Cooling Thrust Chamber ejector filler, it is characterized in that: described flow-disturbing dish is the plane disc structure that the center has through hole, the surface has some through hole D, and the surface of flow-disturbing dish is surperficial parallel with the ejector filler head.
5. a kind of gas hydrogen according to claim 1/gas oxygen eddy current Cooling Thrust Chamber ejector filler, it is characterized in that: the number of described through hole H is more than 8.
6. a kind of gas hydrogen according to claim 1/gas oxygen eddy current Cooling Thrust Chamber ejector filler, it is characterized in that: the number of described ladder hole F is 6～12.
7. a kind of gas hydrogen according to claim 1/gas oxygen eddy current Cooling Thrust Chamber ejector filler, it is characterized in that: the number of described through hole G is 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110107651 CN102207043B (en) | 2011-04-27 | 2011-04-27 | Gaseous hydrogen/gaseous oxygen eddy current cooling thrust chamber injector |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110107651 CN102207043B (en) | 2011-04-27 | 2011-04-27 | Gaseous hydrogen/gaseous oxygen eddy current cooling thrust chamber injector |
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| CN102207043A true CN102207043A (en) | 2011-10-05 |
| CN102207043B CN102207043B (en) | 2013-06-19 |
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| CN104330520A (en) * | 2014-10-30 | 2015-02-04 | 西北工业大学 | Testing device and testing method of constant volume combustion of solid propellant |
| CN105332822A (en) * | 2015-11-27 | 2016-02-17 | 北京航天动力研究所 | Combined-type multifunctional combustion device |
| CN105863881A (en) * | 2016-04-06 | 2016-08-17 | 北京航空航天大学 | Miniature thrust generation device capable of being subjected to fuel charging repeatedly and operation method thereof |
| CN108278166A (en) * | 2017-12-20 | 2018-07-13 | 北京控制工程研究所 | A kind of step-like thrust chamber applied to double elements liquid-propellant rocket engine |
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| CN108894893A (en) * | 2018-06-26 | 2018-11-27 | 西北工业大学 | Rocket punching press combined engine Film cooling Rocket ejector motor power room |
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| CN110242440A (en) * | 2019-07-23 | 2019-09-17 | 西安航天动力研究所 | A kind of high pressure staged combustion cycle engine Multifunctional split-type thrust chamber protective device |
| CN112012850A (en) * | 2020-08-25 | 2020-12-01 | 大连理工大学 | Method for improving performance of vortex combustion cold wall engine |
| CN112523898A (en) * | 2020-11-20 | 2021-03-19 | 西安航天动力研究所 | Device and method for harmless treatment of large-flow toxic propellant oxygen-enriched gas |
| CN113006969A (en) * | 2021-04-16 | 2021-06-22 | 西安航天动力研究所 | Gas-liquid injector for depth variable thrust rocket engine |
| CN114427506A (en) * | 2021-12-23 | 2022-05-03 | 西安航天动力研究所 | High-frequency longitudinal combustion chamber suitable for impact injector |
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| CN105332822A (en) * | 2015-11-27 | 2016-02-17 | 北京航天动力研究所 | Combined-type multifunctional combustion device |
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