CN104948347A - Thrust chamber collector with flow uniformizing function - Google Patents
Thrust chamber collector with flow uniformizing function Download PDFInfo
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- CN104948347A CN104948347A CN201410124535.XA CN201410124535A CN104948347A CN 104948347 A CN104948347 A CN 104948347A CN 201410124535 A CN201410124535 A CN 201410124535A CN 104948347 A CN104948347 A CN 104948347A
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- collector
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Abstract
The invention relates to the liquid rocket propulsion technology, and particularly discloses a thrust chamber collector with a flow uniformizing function. A body shell is composed of an inner wall and an outer wall together. A cylinder formed when the inner wall is closed serves as a combustion chamber. An interlayer between the inner wall and the outer wall forms a cooling passageway. Annular grooves are formed in the inlet and the outlet of the cooling passageway. A bent pipe of the collector is welded and connected to the body shell at the annular groove in the inlet of the cooling passageway. A collector cavity is formed by the bent pipe and the body shell. The opening of the collector cavity is welded and connected to an inlet flange to form a collector inlet. Due to the double-collection-cavity structure, fluid is secondarily uniformized before entering the cooling passageway; by means of a horn-shaped expansion inlet with a reverse-Y-shaped diversion piece, fluid can more stably turn at the collector inlet, pressure fluctuation at the inlet and the two sides is reduced, local pressure loss can be reduced, and the diversion piece can play a role in reinforcing structure supporting.
Description
Technical field
The invention belongs to liquid propellant rocket engine designing technique, be specifically related to a kind of condensing funnel of liquid rocket engine thrust chamber.
Background technique
Liquid rocket engine thrust chamber inner chamber is the combustion gas of high temperature, high pressure, in order to avoid locular wall generation ablative degradation, is provided with cooling jacket between the inner walls and the outer, introduces cryogen and cools locular wall.The effect of inlet collector is exactly be assigned to by the fluid that motor general assembly Pipeline transport is come in every bar autonomous channel of cooling jacket complete cycle distribution.Comparatively even in order to ensure the flow distribution of cooling channel, to avoid combustion gas sidewall temperature circumferential asymmetry even, require that the pressure distribution in condensing funnel outlet port is more evenly better.
As depicted in figs. 1 and 2, existing condensing funnel is designed to the circular single cavity structure with circular cross-section, and condensing funnel chamber 5 is directly connected with cooling channel 6 import, and pipe somewhere arranges a suction flange 1 and is connected with general assembly pipeline, and inlet is without flow guide device.This kind of condensing funnel structure has the following disadvantages: the pressure reduction that (1) fluid is formed along the flowing of condensing funnel chamber 5 hoop directly causes condensing funnel outlet pressure uneven; (2) right-angle turning that ingress is close to 90 degree causes inlet region pressure distribution fluctuation comparatively violent.
Summary of the invention
The object of the present invention is to provide a kind of outlet pressure evenly, inlet fluid turns round comparatively mild, pressure surge and the less thrust chamber condensing funnel with flow equalizing function of local pressure loss.
Technological scheme of the present invention is as follows:
A kind of thrust chamber condensing funnel with flow equalizing function, it comprises columnar inwall, is located at the columnar outer wall of inner wall outside, inwall is closed and is formed firing chamber, formation cooling channel, space between inner and outer wall, the sidewall of the ingress of outer wall is circumferentially processed with annular groove, be fixed with annular distance seat outside the ingress of described outer wall, described annular distance seat extenal fixation is provided with condensing funnel bend pipe; Described annular distance seat is disc, is circular arc outside cross section, is shoulder structure inside cross section, and shoulder is fixedly connected with inner inner and outer wall; The radial direction of described annular distance seat is processed with several radial hole along complete cycle, and each radial hole runs through the inside and outside both sides in annular distance seat cross section; Be processed with arc opening inside described condensing funnel bend pipe, the outside of pipe is provided with flange; The cross section outer arc shape of described annular distance seat and the arc opening of above-mentioned condensing funnel bend pipe form complete circle;
A kind ofly have in the thrust chamber condensing funnel of flow equalizing function above-mentioned: the outside of described pipe processes an entrance, and ingress is provided with expanding suction flange, and ingress is fixed with " people " shape guide plate simultaneously.
A kind ofly have in the thrust chamber condensing funnel of flow equalizing function above-mentioned: the aperture of each described radial hole is different.
A kind ofly have in the thrust chamber condensing funnel of flow equalizing function above-mentioned: the form that the aperture of described radial hole is different is, be respectively minimum and maximum hole, aperture from condensing funnel entrance two radial holes recently and farthest, then to entrance both sides, radial hole circumferentially diminishes in aperture successively respectively.
Remarkable result of the present invention is: due at condensing funnel bend pipe design and installation annular distance seat, make to be formed between the inwall of condensing funnel bend pipe and annular distance seat and gather chamber outward, chamber is gathered in being formed between annular distance seat and burning chamber shell, two set cavity configuration, realizes secondary current-sharing before making fluid enter cooling channel.
Radial bore apertures between external set chamber and interior set chamber adopts not equal aperture design, the pore size of radial hole is devised according to the circumferential pressure difference in outer set chamber, make the circumferential pressure difference adjustment in outer set chamber adapt to pore size, make the interior set cavity pressure before passage be tending towards even.
Condensing funnel elbow inlet adopts the tubaeform expanded flange structure of band " people " shape guide plate, condensing funnel ingress fluid is turned round more mild, reduces the pressure surge of entrance and two lateral areas, and can reduce local pressure loss; Guide plate can also play the effect strengthening entrance structure inner chamber bearing capacity in addition.
Accompanying drawing explanation
Fig. 1 is single chamber condensing funnel structural front view in prior art;
Fig. 2 is the A-A sectional view of Fig. 1;
Fig. 3 is the thrust chamber condensing funnel structural representation with flow equalizing function;
Fig. 4 is the B-B sectional view of Fig. 3;
Fig. 5 is the stereochemical structure sectional drawing of the thrust chamber condensing funnel with flow equalizing function;
In figure: 1. suction flange; 2. condensing funnel bend pipe; 3. inwall; 4. outer wall; 5. condensing funnel chamber; 6. cooling channel; 7. expanding suction flange; 8. annular distance seat; 9. outside, gather chamber; 10. radial hole; Set chamber in 11.; 12. guide plates; 13. firing chambers.
Embodiment
Below in conjunction with drawings and the specific embodiments, the present invention is described in further detail.
As shown in Figure 3 and Figure 4, the bend pipe that the pipe that described condensing funnel bend pipe 2 is circle for cross section surrounds, and the inner side of bend pipe is processed with arc opening, and the external circumferential arbitrary position of pipe processes an entrance.In this ingress, expanding suction flange 7 is installed, is welded and fixed " people " shape guide plate 12 in ingress simultaneously.
The arc opening of the inner side of pipe welds annular distance seat 8, described welding annular distance seat 8 is disc, the shape in its cross section as shown in Figure 3, be circular arc outside cross section, the cross section of itself and above-mentioned condensing funnel bend pipe 2 forms complete circle, be with shoulder structure inside cross section, shoulder fixedly welds with inner inwall 3 and outer wall 4.The radial direction of annular distance seat 8 is processed with several radial hole 10 along complete cycle, and in the present embodiment, the number of radial hole 10 is 36.Each radial hole 10 runs through the inside and outside both sides in annular distance seat 8 cross section.
In order to make interior set cavity pressure be tending towards even, the circumferential pressure difference in outer set chamber is adjusted, and each radial hole 10 aperture adopts not equal aperture design.As shown in Figure 4, in the present embodiment, be designed to minimum and maximum hole, aperture respectively by from condensing funnel entrance two radial holes 10 recently and farthest, then to entrance both sides, radial hole 10 circumferentially diminishes in aperture successively respectively.
The same with existing condensing funnel, condensing funnel of the present invention also has closes by inwall 3 firing chamber 13 formed, and inwall 3 outside is provided with outer wall 4, the formation cooling channel, space 6 between inwall 3 and outer wall 4.The sidewall of the ingress of outer wall 4 is circumferentially processed with annular groove.
The inner side of above-mentioned annular distance seat 8 is just welded on the annular groove place of outer wall 4 ingress, just can see from Fig. 3 and Fig. 4 like this, the cavity formed between the inwall of condensing funnel bend pipe 2 and annular distance seat 8 is outer set chamber 9, and between the housing of the firing chamber 13 that annular distance seat 8 and inwall 3 outer wall 4 are formed jointly, namely in the space at the annular groove place of outer wall 4 ingress, so-called interior set chamber 11 is defined.As can be seen from Figure 4, above-mentioned outer set chamber 9 and interior set chamber 11 are annular chamber, and outer set chamber 9 and interior set chamber 11 are communicated by the radial hole 10 of processing on annular space seat 8.
After fluid enters expanding suction flange 7, under the acting in conjunction of expanding suction flange 7 and guide plate 12, level and smooth enters outer set chamber 9 along guide plate 12 both sides, making to be effectively suppressed in the pressure at inlet fluctuation of condensing funnel bend pipe 2.In addition, when fluid enters into interior set chamber 11 from outer set chamber 9 by radial hole 10, radial hole 10 makes the pressure distribution in interior condensing funnel chamber 11 be optimized, larger near entrance, aperture, position that static pressure is low, less away from entrance, aperture, position that static pressure is high, so just make fluid gather the pressure reduction that in chamber 9, hoop flowing is formed outside and can obtain effective attenuation after radial hole 10, again after secondary distribution is carried out in interior set chamber 11, the pressure of cooling channel 6 entrance can be made to be tending towards even.
Claims (4)
1. one kind has the thrust chamber condensing funnel of flow equalizing function, it comprises columnar inwall (3), is located at the columnar outer wall (4) in inwall (3) outside, inwall (3) is closed and is formed firing chamber (13), formation cooling channel, space (6) between inwall (3) and outer wall (4), the sidewall of the ingress of outer wall (4) is circumferentially processed with annular groove, it is characterized in that: be fixed with annular distance seat (8) outside the ingress of described outer wall (4), described annular distance seat (8) extenal fixation is provided with condensing funnel bend pipe (2); Described annular distance seat (8) is disc, is circular arc outside cross section, is shoulder structure inside cross section, and shoulder is fixedly connected with outer wall (4) with inner inwall (3); The radial direction of described annular distance seat (8) is processed with several radial hole (10) along complete cycle, and each radial hole (10) runs through the inside and outside both sides in annular distance seat (8) cross section; Described condensing funnel bend pipe (2) inner side is processed with arc opening, and the outside of pipe is provided with flange; The cross section outer arc shape of described annular distance seat (8) and the arc opening of above-mentioned condensing funnel bend pipe (2) form complete circle.
2. a kind of thrust chamber condensing funnel with flow equalizing function as claimed in claim 1, it is characterized in that: the outside of described pipe processes an entrance, ingress is provided with expanding suction flange (7), and ingress is fixed with " people " shape guide plate (12) simultaneously.
3. a kind of thrust chamber condensing funnel with flow equalizing function as claimed in claim 1, is characterized in that: the aperture of described each radial hole (10) is different.
4. a kind of thrust chamber condensing funnel with flow equalizing function as claimed in claim 3, it is characterized in that: the form that the aperture of described radial hole (10) is different is, be respectively minimum and maximum hole, aperture with two radial holes (10) farthest recently from condensing funnel entrance, then diminish in aperture successively to entrance both sides difference radial hole (10) circumferentially.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410124535.XA CN104948347B (en) | 2014-03-31 | 2014-03-31 | Thrust chamber collector with flow uniformizing function |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410124535.XA CN104948347B (en) | 2014-03-31 | 2014-03-31 | Thrust chamber collector with flow uniformizing function |
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| CN104948347A true CN104948347A (en) | 2015-09-30 |
| CN104948347B CN104948347B (en) | 2017-02-15 |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106286007A (en) * | 2016-09-23 | 2017-01-04 | 北京动力机械研究所 | A kind of gas collection ring cavity rectifier structure improving cooling edema caused by disorder of QI cloth |
| CN106383972A (en) * | 2016-11-04 | 2017-02-08 | 北京航天动力研究所 | Collector for rocket engine thrust chamber and radial hole current sharing design method thereof |
| CN107940157A (en) * | 2017-11-20 | 2018-04-20 | 西安航天动力研究所 | A kind of re-generatively cooled gas conduct pipe and its processing method |
| CN108825406A (en) * | 2018-08-29 | 2018-11-16 | 北京航天动力研究所 | A kind of liquid rocket engine thrust chamber body portion outer wall construction |
| CN108979900A (en) * | 2018-08-29 | 2018-12-11 | 北京航天动力研究所 | A kind of collection pendular ring in liquid rocket engine thrust chamber body portion |
| CN109779790A (en) * | 2019-03-11 | 2019-05-21 | 北京星际荣耀空间科技有限公司 | A kind of thrust chamber of liquid-propellant rocket engine |
| CN110282163A (en) * | 2019-07-08 | 2019-09-27 | 盐城科宇机械制造有限公司 | A kind of flanged (FLGD) collector of space flight |
| CN111456866A (en) * | 2020-04-14 | 2020-07-28 | 合肥中科重明科技有限公司 | Cooling liquid film forming structure of liquid rocket engine |
| CN111963338A (en) * | 2020-08-11 | 2020-11-20 | 西安航天动力研究所 | Flow guiding device of gas branch pipeline |
| CN112145316A (en) * | 2018-01-23 | 2020-12-29 | 陕西蓝箭航天技术有限公司 | Liquid engine |
| CN112253333A (en) * | 2020-09-17 | 2021-01-22 | 北京航天动力研究所 | Collector inlet flow guide structure with flow equalizing function |
| CN114571053A (en) * | 2022-03-18 | 2022-06-03 | 北京航天动力研究所 | Titanium alloy vacuum diffusion welding spray pipe and design method |
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| US4055044A (en) * | 1973-11-13 | 1977-10-25 | Messerschmitt-Bolkow-Blohm Gmbh | Rocket engine construction and connection for closed and opened fluid cooling circuits for the walls thereof |
| CN203130283U (en) * | 2013-03-15 | 2013-08-14 | 北京航天动力研究所 | Flow equalizer for suppressing flow distortion |
| US20130232950A1 (en) * | 2012-03-09 | 2013-09-12 | Pratt & Whitney | Exit Manifold Flow Guide |
| CN203796441U (en) * | 2014-03-31 | 2014-08-27 | 北京航天动力研究所 | Thrust chamber collector with flow equalizing function |
-
2014
- 2014-03-31 CN CN201410124535.XA patent/CN104948347B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4055044A (en) * | 1973-11-13 | 1977-10-25 | Messerschmitt-Bolkow-Blohm Gmbh | Rocket engine construction and connection for closed and opened fluid cooling circuits for the walls thereof |
| US20130232950A1 (en) * | 2012-03-09 | 2013-09-12 | Pratt & Whitney | Exit Manifold Flow Guide |
| CN203130283U (en) * | 2013-03-15 | 2013-08-14 | 北京航天动力研究所 | Flow equalizer for suppressing flow distortion |
| CN203796441U (en) * | 2014-03-31 | 2014-08-27 | 北京航天动力研究所 | Thrust chamber collector with flow equalizing function |
Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106286007B (en) * | 2016-09-23 | 2018-03-20 | 北京动力机械研究所 | A kind of gas collection ring cavity rectifier structure for improving cooling qi leel cloth |
| CN106286007A (en) * | 2016-09-23 | 2017-01-04 | 北京动力机械研究所 | A kind of gas collection ring cavity rectifier structure improving cooling edema caused by disorder of QI cloth |
| CN106383972A (en) * | 2016-11-04 | 2017-02-08 | 北京航天动力研究所 | Collector for rocket engine thrust chamber and radial hole current sharing design method thereof |
| CN107940157B (en) * | 2017-11-20 | 2020-07-24 | 西安航天动力研究所 | Regenerative cooling gas guide pipe and processing method thereof |
| CN107940157A (en) * | 2017-11-20 | 2018-04-20 | 西安航天动力研究所 | A kind of re-generatively cooled gas conduct pipe and its processing method |
| CN112145316B (en) * | 2018-01-23 | 2021-07-23 | 陕西蓝箭航天技术有限公司 | Liquid engine |
| CN112145316A (en) * | 2018-01-23 | 2020-12-29 | 陕西蓝箭航天技术有限公司 | Liquid engine |
| CN108825406A (en) * | 2018-08-29 | 2018-11-16 | 北京航天动力研究所 | A kind of liquid rocket engine thrust chamber body portion outer wall construction |
| CN108979900A (en) * | 2018-08-29 | 2018-12-11 | 北京航天动力研究所 | A kind of collection pendular ring in liquid rocket engine thrust chamber body portion |
| CN109779790A (en) * | 2019-03-11 | 2019-05-21 | 北京星际荣耀空间科技有限公司 | A kind of thrust chamber of liquid-propellant rocket engine |
| CN110282163A (en) * | 2019-07-08 | 2019-09-27 | 盐城科宇机械制造有限公司 | A kind of flanged (FLGD) collector of space flight |
| CN111456866A (en) * | 2020-04-14 | 2020-07-28 | 合肥中科重明科技有限公司 | Cooling liquid film forming structure of liquid rocket engine |
| CN111963338A (en) * | 2020-08-11 | 2020-11-20 | 西安航天动力研究所 | Flow guiding device of gas branch pipeline |
| CN111963338B (en) * | 2020-08-11 | 2022-08-12 | 西安航天动力研究所 | Flow guiding device of gas branch pipeline |
| CN112253333A (en) * | 2020-09-17 | 2021-01-22 | 北京航天动力研究所 | Collector inlet flow guide structure with flow equalizing function |
| CN112253333B (en) * | 2020-09-17 | 2021-08-10 | 北京航天动力研究所 | Collector inlet flow guide structure with flow equalizing function |
| CN114571053A (en) * | 2022-03-18 | 2022-06-03 | 北京航天动力研究所 | Titanium alloy vacuum diffusion welding spray pipe and design method |
| CN114571053B (en) * | 2022-03-18 | 2023-12-12 | 北京航天动力研究所 | Titanium alloy vacuum diffusion welding spray pipe and design method |
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| CN104948347B (en) | 2017-02-15 |
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