CN107120210B - Supersonic jet pipe - Google Patents
Supersonic jet pipe Download PDFInfo
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- CN107120210B CN107120210B CN201710490461.5A CN201710490461A CN107120210B CN 107120210 B CN107120210 B CN 107120210B CN 201710490461 A CN201710490461 A CN 201710490461A CN 107120210 B CN107120210 B CN 107120210B
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- flow passage
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/40—Nozzles having means for dividing the jet into a plurality of partial jets or having an elongated cross-section outlet
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- Engineering & Computer Science (AREA)
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Abstract
The supersonic jet pipe comprises a supersonic jet pipe, a supersonic speed convergence section, a supersonic speed expansion section and a control section, wherein the supersonic speed jet pipe is fixedly connected with an inlet equal straight section, the subsonic speed convergence section, the initial supersonic speed expansion section and the supersonic speed expansion section are hollow revolution bodies, and the revolution shafts are the same; the inner flow passage of the subsonic convergence section is a continuously contracted circular arc shaft revolution surface, the inner flow passage of the initial supersonic expansion section is a continuously expanded circular arc shaft revolution surface, and the inner flow passage of the supersonic expansion section is a circular table surface; the radius of the subsonic convergence section arc is the same as that of the initial supersonic expansion section arc, and the connecting section of the subsonic convergence section and the internal flow channel of the initial supersonic expansion section is the section of the throat; the generatrix of the circular table of the inner flow passage of the supersonic expansion section is tangent to the tail end of the continuous expansion circular arc of the inner flow passage of the initial supersonic expansion section. Under the condition that the total pressure of the gas is basically the same as the total pressure loss of the traditional Laval spraying gas, the manufacturing difficulty and the cost of the supersonic jet pipe can be greatly reduced, and the supersonic jet pipe can be used for mass production of the supersonic jet pipe.
Description
Technical Field
The invention relates to a spray pipe, in particular to a supersonic spray pipe.
Background
With the increasing maturity of engines, the application of supersonic engines is becoming wider, on this basis, when being used for the supersonic engines of aircraft especially unmanned aerial vehicle and engine ground test, all involve the use of supersonic jet pipe, and the supersonic jet pipe in the true sense, its interior runner needs to satisfy the runner geometric parameters requirement of Laval nozzle, and the Laval nozzle in traditional sense, its runner curved surface changes complicacy, the processing degree of difficulty is high, thereby lead to the cost to increase by a wide margin, can't realize mass production, in the prior art, in order to reduce the cost, realize the mass production of supersonic jet pipe, simplify the interior runner of supersonic jet pipe by Laval nozzle curved surface into the interior runner of fixed connection in proper order and be the convergent section of convergence circle mesa, interior runner is the straight section and interior runner of cylinder face be the expansion section of expansion circle mesa, although the cost is reduced, the setting of straight convergent section, expansion section leads to the total pressure loss of gas by a wide margin, economic nature and environmental protection are not possessed.
Disclosure of Invention
The technical solution of the invention is as follows: overcomes the defects of the prior art and provides a supersonic jet pipe.
The technical scheme of the invention is as follows: a supersonic jet pipe comprises an inlet equal straight section, a subsonic converging section, an initial supersonic expansion section and a supersonic expansion section which are coaxially and fixedly connected in sequence;
the inlet equal-straight section, the subsonic converging section, the initial supersonic expansion section and the supersonic expansion section are hollow revolution bodies, and the inlet equal-straight section, the subsonic converging section and the initial supersonic expansion section have the same revolution axis;
the inner flow passage of the subsonic convergence section is a continuously contracted circular arc shaft revolution surface, the inner flow passage of the initial supersonic expansion section is a continuously expanded circular arc shaft revolution surface, and the inner flow passage of the supersonic expansion section is a circular table surface;
the radius of the continuous contracted circular arc of the inner flow passage of the subsonic converging section is the same as the radius of the continuous expanded circular arc of the inner flow passage of the initial supersonic expansion section, and the connecting section of the inner flow passage of the subsonic converging section and the inner flow passage of the initial supersonic expansion section is the section of the throat; the generatrix of the circular table of the inner flow passage of the supersonic expansion section is tangent to the tail end of the continuous expansion circular arc of the inner flow passage of the initial supersonic expansion section.
Subsonic gas enters through the nozzle inlet, namely the inlet and other straight section inlets, is accelerated to reach the sonic speed through the subsonic convergent section until reaching the sonic speed through the throat, and reaches supersonic speed after being expanded through the initial supersonic expansion section and the supersonic expansion section.
Further, the internal dimensions of the nozzle flow channel satisfy the following conditions:
the rotary axis of the spray pipe is coincident with the X axis, the Y axis and the X axis vertically intersect at an O point on the throat interface, the diameter of the inlet of the spray pipe is do, and the diameter of the throat is d ac k p Yt is the radius of the throat on the Y axis, X b The distance from the O point on the X axis to the outlet of the spray pipe is defined as the p point, which is the tangent point between the generatrix of the inner flow passage circular table of the supersonic expansion section and the tail end of the continuous expansion circular arc of the inner flow passage of the initial supersonic expansion section, the radius of the continuous contraction circular arc of the inner flow passage of the subsonic convergence section is the same as the radius of the continuous expansion circular arc of the inner flow passage of the initial supersonic expansion section, the R is the same as the radius of the continuous expansion circular arc of the inner flow passage of the initial supersonic expansion section, the included angle between the generatrix of the inner flow passage circular table of the supersonic expansion section and the X axis is beta, and the diameter of the outlet of the spray pipe is da; wherein the diameter of the nozzle inlet and the diameter of the throat are known,
the abscissa and ordinate of the p point are Xp and Yp, respectively, and Xp and Yp satisfy the following formula:
Xp＝Rsinβ
Yp＝R+Yt-Rcosβ
the abscissa and the ordinate of the outlet diameter b point of the spray pipe are respectively X b And Y b The X is b And Y b Satisfies the following formula:
X b ＝Xp+(0.5da-Xp)/tanβ
Y b ＝0.5da
further, the radius of the continuous contracted circular arc of the inner flow passage of the subsonic convergent section is at least 4 times the diameter of the throat.
Further, an angle between a generatrix of the inner flow passage circular table surface of the supersonic expansion section and a rotation axis of the supersonic expansion section is more than or equal to 6 degrees and less than or equal to 8 degrees.
Compared with the prior art, the invention has the advantages that:
the supersonic jet pipe provided by the invention has the advantages that through reasonably simplifying the Laval jet pipe molded surface, namely, the subsonic convergence section adopts a continuously contracted circular arc axisymmetric curved surface, the initial expansion and the supersonic section molded surface adopt a simplified method of circular arc plus straight axisymmetric curved surface, so that the airflow starts to form spring flow expansion from the sonic surface and then expands to the Mach number at the design point, when the airflow finishes the initial expansion through the spring flow area, the airflow is further expanded to the Mach number at the design point under the condition that the expansion angle is kept unchanged, and the manufacturing difficulty and the manufacturing cost are greatly reduced under the condition that the total pressure of the air is basically the same as the total pressure loss of the traditional Laval jet gas, and the supersonic jet pipe can be used for mass production.
Drawings
FIG. 1 is a schematic structural view of a supersonic nozzle of the present invention.
FIG. 2 is a schematic illustration of the geometry of the internal flow path of the supersonic nozzle of the present invention.
Detailed Description
1-2, a supersonic jet pipe comprises an inlet equal straight section 1, a subsonic convergence section 2, an initial supersonic expansion section 4 and a supersonic expansion section 5 which are coaxially and fixedly connected in sequence; the inlet equal straight section 1, the subsonic converging section 2, the initial supersonic expansion section 4 and the supersonic expansion section 5 are hollow revolution bodies, and the inlet equal straight section 1, the subsonic converging section 2, the initial supersonic expansion section 4 and the supersonic expansion section 5 have the same revolution axis; the inner flow passage of the subsonic convergence section 2 is a continuously contracted circular arc shaft revolution surface, the inner flow passage of the initial supersonic expansion section 4 is a continuously expanded circular arc shaft revolution surface, and the inner flow passage of the supersonic expansion section 5 is a circular truncated cone surface; the radius of the continuous contracted circular arc of the inner flow passage of the subsonic converging section 2 is the same as the radius of the continuous expanded circular arc of the inner flow passage of the initial supersonic expansion section 4, and the connecting section of the inner flow passages of the subsonic converging section 2 and the initial supersonic expansion section 4 is the section of the throat 3; the generatrix of the circular truncated cone of the inner flow passage of the supersonic expansion section 5 is tangent to the tail end of the continuous expansion circular arc of the inner flow passage of the initial supersonic expansion section 4.
Preferably, the internal dimensions of the nozzle flow channel satisfy the following conditions:
the revolving axis of the spray pipe is coincident with the X axis, the Y axis and the X axis vertically intersect at the O point on the section of the throat 3, the diameter of the inlet of the spray pipe is do, and the diameter of the throat 3 is d ac k p Yt is the radius of the throat 3 on the Y axis, X b The distance from the O point to the outlet of the spray pipe on the X axis is equal to the radius of the continuous contracted circular arc of the inner flow passage of the subsonic convergent section 2 and the radius of the continuous expanded circular arc of the inner flow passage of the initial supersonic expansion section 4, the included angle between the generatrix of the circular table of the inner flow passage of the supersonic expansion section 5 and the X axis is beta, and the diameter of the outlet of the spray pipe is da; wherein the nozzle inlet diameter and the diameter of the throat 3 are known,
the abscissa and ordinate of the p point are Xp and Yp, respectively, and Xp and Yp satisfy the following formula:
Xp＝Rsinβ
Yp＝R+Yt-Rcosβ
the abscissa and the ordinate of the outlet diameter b point of the spray pipe are respectively X b And Y b The X is b And Y b Satisfies the following formula:
X b ＝Xp+(0.5da-Xp)/tanβ
Y b ＝0.5da
preferably, the radius of the continuous convergent arc of the inner flow passage of the subsonic convergent section 2 is at least 4 times the diameter of the throat 3.
Preferably, the angle between the generatrix of the inner flow passage circular table surface of the supersonic expansion section 5 and the rotation axis of the supersonic expansion section 5 is not less than 6 ° and not more than 8 °.
The working process of the supersonic jet pipe of the invention is as follows: subsonic gas enters through the nozzle inlet, namely the inlet and other straight section inlets, is accelerated to reach sonic speed through the subsonic convergent section until reaching sonic speed through the throat, is initially expanded through the initial supersonic expansion section, and is further expanded to a designed Mach number under the condition that the expansion angle of the gas flow is kept unchanged when the gas flow passes through the spring flow area to complete the initial expansion, and is sprayed out from the nozzle outlet, namely the supersonic expansion section outlet.
What is not described in detail in the present specification belongs to the known technology of those skilled in the art.
Claims (2)
1. The supersonic jet pipe is characterized by comprising an inlet equal straight section (1), a subsonic converging section (2), an initial supersonic expansion section (4) and a supersonic expansion section (5) which are coaxially and fixedly connected in sequence;
the inlet equal straight section (1), the subsonic convergence section (2), the initial supersonic expansion section (4) and the supersonic expansion section (5) are hollow revolution bodies, and the inlet equal straight section (1), the subsonic convergence section (2), and the rotation shafts of the initial supersonic expansion section (4) and the supersonic expansion section (5) are the same;
the inner flow passage of the subsonic convergence section (2) is a continuously contracted circular arc shaft revolution surface, the inner flow passage of the initial supersonic expansion section (4) is a continuously expanded circular arc shaft revolution surface, and the inner flow passage of the supersonic expansion section (5) is a circular truncated cone surface;
the radius of the continuous contracted circular arc of the inner flow passage of the subsonic converging section (2) is the same as the radius of the continuous expanded circular arc of the inner flow passage of the initial supersonic expansion section (4), and the connecting section of the subsonic converging section (2) and the inner flow passage of the initial supersonic expansion section (4) is the section of the throat (3); the generatrix of the round table of the inner flow passage of the supersonic expansion section (5) is tangent with the tail end of the continuous expansion circular arc of the inner flow passage of the initial supersonic expansion section (4);
the internal dimensions of the nozzle flow passage meet the following conditions:
the revolving axis of the spray pipe is coincident with the X axis, the Y axis and the X axis vertically intersect at the O point on the section of the throat (3), the diameter of the inlet of the spray pipe is do, and the diameter of the throat (3) is d ac k p Yt is the radius of the throat (3) on the Y axis, X b The distance from the O point on the X axis to the nozzle outlet is equal to the radius of the continuous contracted circular arc of the inner flow passage of the subsonic convergent section (2) and the radius of the continuous expanded circular arc of the inner flow passage of the initial supersonic expansion section (4), wherein the p point is the tangent point between the generatrix of the circular table of the inner flow passage of the supersonic expansion section (5) and the tail end of the continuous expanded circular arc of the inner flow passage of the initial supersonic expansion section (4), the two radii are R, the included angle between the generatrix of the circular table of the inner flow passage of the supersonic expansion section (5) and the X axis is beta, and the diameter of the nozzle outlet is da; wherein the diameter of the nozzle inlet and the diameter of the throat (3) are known,
the abscissa and ordinate of the p point are Xp and Yp, respectively, and Xp and Yp satisfy the following formula:
Xp＝Rsinβ
Yp＝R+Yt-Rcosβ
the abscissa and the ordinate of the outlet diameter b point of the spray pipe are respectively X b And Y b The X is b And Y b Satisfies the following formula:
X b ＝Xp+(0.5da-Xp)/tanβ
Y b ＝0.5da；
the radius of the continuous contracted circular arc of the inner flow passage of the subsonic converging section (2) is at least 4 times of the diameter of the throat (3).
2. The spout of claim 1 wherein: the angle between the generatrix of the inner flow passage circular table surface of the supersonic expansion section (5) and the rotating shaft of the supersonic expansion section (5) is more than or equal to 6 degrees and less than or equal to 8 degrees.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710490461.5A CN107120210B (en) | 2017-06-25 | 2017-06-25 | Supersonic jet pipe |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710490461.5A CN107120210B (en) | 2017-06-25 | 2017-06-25 | Supersonic jet pipe |
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| Publication Number | Publication Date |
|---|---|
| CN107120210A CN107120210A (en) | 2017-09-01 |
| CN107120210B true CN107120210B (en) | 2023-05-23 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201710490461.5A Active CN107120210B (en) | 2017-06-25 | 2017-06-25 | Supersonic jet pipe |
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Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108592500A (en) * | 2018-06-29 | 2018-09-28 | 南通四方冷链装备股份有限公司 | A kind of superonic flow nozzzle for the defrosting of instant freezer evaporator |
| CN109141909B (en) * | 2018-10-05 | 2020-04-17 | 北京航天三发高科技有限公司 | Application method of supersonic engine test bed |
| CN109357877B (en) * | 2018-10-05 | 2020-04-17 | 北京航天三发高科技有限公司 | Supersonic heat exchanger using method and engine multi-state air inlet simulation test method |
| CN109141907A (en) * | 2018-10-05 | 2019-01-04 | 北京航天三发高科技有限公司 | A kind of supersonic speed engine testsand |
| CN109282990B (en) * | 2018-10-05 | 2020-04-17 | 北京航天三发高科技有限公司 | Application method of supersonic engine test bed air inlet system |
| CN109187031B (en) * | 2018-10-05 | 2023-09-12 | 北京航天三发高科技有限公司 | Supersonic heat exchanger and use method thereof |
| CN111396276B (en) * | 2020-03-16 | 2022-04-08 | 大连理工大学 | Supersonic electric heating type stamping aerospace engine |
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| GB1132236A (en) * | 1965-08-03 | 1968-10-30 | Mini Of Technology | Supersonic fluid flow exhaust nozzles |
| GB9106049D0 (en) * | 1990-03-31 | 1991-05-08 | Messerschmitt Boelkow Blohm | Hypersonic engine combustion chamber |
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| CN105351100A (en) * | 2015-10-29 | 2016-02-24 | 西北工业大学 | Structural design of inlet isolation segment of rocket-based-combined-cycle engine |
| CN106762218A (en) * | 2017-01-05 | 2017-05-31 | 南京工业职业技术学院 | A kind of method and jet pipe for improving pulse detonation engine thrust coefficient |
| CN207048877U (en) * | 2017-06-25 | 2018-02-27 | 北京航天三发高科技有限公司 | A kind of supersonic nozzle |
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2017
- 2017-06-25 CN CN201710490461.5A patent/CN107120210B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB894450A (en) * | 1960-05-18 | 1962-04-18 | Gen Electric | Improvements in converging-diverging jet propulsion nozzle |
| GB1132236A (en) * | 1965-08-03 | 1968-10-30 | Mini Of Technology | Supersonic fluid flow exhaust nozzles |
| GB9106049D0 (en) * | 1990-03-31 | 1991-05-08 | Messerschmitt Boelkow Blohm | Hypersonic engine combustion chamber |
| CN101787937A (en) * | 2010-02-08 | 2010-07-28 | 北京航空航天大学 | Porous wall expanding type dual throat nozzle |
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| CN203441627U (en) * | 2013-05-21 | 2014-02-19 | 南京航空航天大学 | Supersonic/hypersonic aerocraft engine overexpansion nozzle bypass type device |
| CN105351100A (en) * | 2015-10-29 | 2016-02-24 | 西北工业大学 | Structural design of inlet isolation segment of rocket-based-combined-cycle engine |
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| CN107120210A (en) | 2017-09-01 |
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