CN1419044A - Stopper type jet pipe - Google Patents
Stopper type jet pipe Download PDFInfo
- Publication number
- CN1419044A CN1419044A CN02158695A CN02158695A CN1419044A CN 1419044 A CN1419044 A CN 1419044A CN 02158695 A CN02158695 A CN 02158695A CN 02158695 A CN02158695 A CN 02158695A CN 1419044 A CN1419044 A CN 1419044A
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- Prior art keywords
- plug
- nozzle
- shape
- awl
- profile
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- Turbine Rotor Nozzle Sealing (AREA)
- Jet Pumps And Other Pumps (AREA)
Abstract
The present invention discloses a plug jet pipe. It is formed from several internal jet pipes and plug cone. Its internal jet pipe is made into axially-symmetrical structure, and its plug cone is designed into "tile"-shaped curved surface, said internal jet pipe can be divided into convergent part, throat portion and expanding part, and the internal jet pipes and plug cone can be designed into cone body. Said invention plug jet pipe can be used in aerial and outer-space engine, its flow field evenness degree is good and its performance is high.
Description
Technical field
The present invention relates to a kind of plug nozzle, specifically, relate to use on a kind of Aero-Space motor " watt " shape structure plug nozzle.
Background technique
Jet pipe is a vitals in the Aero-Space propulsion system, and traditional jet pipe generally is the jet pipe of a fixed-area ratio, only has higher performance at design point.Along with development of aviation and aerospace technology, various new concept engines all wish further to improve performance, making jet pipe also can obtain superior performance at the off-design point height is an otherwise effective technique approach, develops and the plug nozzle designing technique adapts to this requirement just.The plug nozzle complex structure has proposed multiple organization plan, the present invention proposes a kind of and the diverse organization plan of other scheme.
Summary of the invention
The purpose of this invention is to provide a kind of axially symmetric structure " watt " shape plug formula inner nozzle, this inner nozzle is according to the thermal parameter of combustion gas working medium and the size of throat region, the utilization Optimized Program determine " watt " the main profile parameter of shape plug formula inner nozzle, determine the inner nozzle inclination angle and fill in tapered according to the back pressure of inner nozzle and the environmental stress of design point, after making gas flow cross whole plug awl, the deflection angle of fuel gas flow direction then just equals the inner nozzle inclination angle.
A kind of plug nozzle of the present invention is made up of a plurality of inner nozzles, plug awl, and its inner nozzle is an axially symmetric structure, the plug awl be designed to " watt " the shape curved surface, inner nozzle can be divided into converging portion, throat, extending section, inner nozzle and plug are bored to one and are designed.
Described plug nozzle, its profile can be calculated generation with equation, and the inner nozzle profile is expressed as y=a
nx
n+ a
N-1x
N-1+ ... + a
1X+a
0, a in the formula
i(i=0,1 ..., n) be the profile design parameter; Watt tapered The Representation Equation of shape curved surface plug is y=b
nx
n+ b
N-1x
N-1+ ... + b
1X+b
0, b in the formula
i(i=0,1 ..., n) be the profile design parameter; The expansion ratio ε of inner nozzle
iFor the ratio of inner nozzle outlet diameter and throat diameter square, ε
i=1～10, overall expansion ratio ε
tFor inner nozzle outlet edge position to the ratio of the distance of engine spindle line and throat diameter square, ε
t=10～300.
Described plug nozzle, profile also can adopt direct curved surface method of formation to generate the profile data point.
Described plug nozzle, the brachymemma coefficient scope of its plug awl is 20～100%.
Described plug nozzle, the initial position in its plug awl gap is consistent with the initial position of plug awl, extends to plug awl bottom always, forms enclosed construction, and its angle excursion is 1 °～60 °.
Described plug nozzle, its plug nozzle can be designed to direct-exhausting type " watt " the shape plug nozzle or can be designed to the row's of ring formula " watt " the shape plug nozzle.
Described plug nozzle, the shape of its plug awl bottom is relevant according to the composite structure shape of plug nozzle unit.
Described plug nozzle, the shape of its plug awl bottom can be the arch bridge shape or can be petal.
Of the present invention " watt " shape plug formula inner nozzle, the even flow field degree is good, performance is high, be easy to process realization, be easy to cool off, the design of thrust chamber and inner nozzle uses that inheritance is good, compound mode is flexible.
Description of drawings
Fig. 1 is a modular construction schematic representation of the present invention.
Fig. 2 be direct-exhausting type of the present invention " watt " shape plug nozzle design sketch.
Fig. 3 be ring of the present invention row formula " watt " shape plug nozzle design sketch.
Fig. 4 is existing axisymmetric inner nozzle and axisymmetric plug awl scheme design sketch.
Fig. 5 is an existing circular throat square outlet inner nozzle direct-exhausting type scheme design sketch.
Fig. 6 be direct-exhausting type of the present invention " watt " shape plug nozzle bottom shape schematic representation.
Fig. 7 be ring of the present invention row formula " watt " shape plug nozzle bottom shape schematic representation.
Fig. 8 be Unit six " watt " shape plug nozzle implementation result figure.
Among the figure: 1. the awl gaps are filled in 6. watts of shape curved surfaces of plug nozzle unit 2. axisymmetric inner nozzles, 3. inner nozzle converging portion 4. inner nozzle throats, 5. inner nozzle extending sections plug awl, 7. plug awl bottoms 8.
Embodiment
The present invention is further illustrated below in conjunction with accompanying drawing and example.
See also Fig. 1, Fig. 2, shown in Figure 3, a kind of plug nozzle of the present invention comprises a plurality of plug nozzles unit 1, is made up of an axisymmetric inner nozzle 2 and a watt shape curved surface plug awl 6.Leave the gap between jet pipe and the jet pipe, plug awl gap 9 makes its structural integrity.The end of watt shape curved surface plug awl 6 forms the shape of plug awl bottom 7 according to the needs of the plug nozzle shape of design, as the row's of ring formula " watt " the shape plug nozzle, its plug awl bottom 7 is for having petal interior toroidal, as direct-exhausting type " watt " the shape plug nozzle, its plug awl bottom 7 is arch-shaped shape.
Main profile design in the present invention is as follows: (1) according to the thermal parameter of combustion gas working medium and the size of throat region, below the utilization Optimized Program is determined " watt " value of the main profile design parameter of shape plug nozzle: design pressure ratio, interior expansion ratio, inner nozzle throat downstream arc round angle, inner nozzle exit angle.(2) determine the profile of inner nozzle extending section according to top inner nozzle geometric parameter.(3) determine the inner nozzle inclination angle and fill in tapered, make under design situation that after gas flow was crossed whole plug awl, the deflection angle of fuel gas flow direction then just equaled the inner nozzle inclination angle according to the back pressure of inner nozzle and the environmental stress of design point.
Based on the throat region thermal protection and reduce the consideration that throat ablates, the inner nozzle throat section of plug nozzle generally all is a circular cross-section.If but adopt traditional axisymmetric nozzle, as shown in Figure 4, can between each inner nozzle unit, produce bigger gap, thus the performance loss that brings whole plug nozzle.Therefore, in order to reduce the gap, adopted the inner nozzle design proposal of the square outlet of circular throat, as shown in Figure 5, but this inner nozzle configuration is very complicated, and is all very inconvenient to cooling and manufacturing, realizes that difficulty is very big.
In the present invention, profile can be calculated generation with equation, inner nozzle 2 profiles be expressed as y=a
nx
n+ a
N-1x
N-1+ ... + a
1X+a
0, a in the formula
i(i=0,1 ..., n) be the profile design parameter; It is y=b that watt shape curved surface plug is bored 6 profile The Representation Equation
nx
n+ b
N-1x
N-1+ ... + b
1X+b
0, b in the formula
i(i=0,1 ..., n) be the profile design parameter; The expansion ratio ε of inner nozzle 2
iFor inner nozzle 2 outlet diameters and throat's 4 diameter ratios square, ε
i=1～10, overall expansion ratio ε
iFor inner nozzle 2 outlet edge positions to the ratio of the distance of engine spindle line and throat diameter square, ε
t=10～300.
Described plug nozzle, profile also can adopt direct curved surface method of formation to generate the profile data point.
Described plug nozzle, the brachymemma coefficient scope of its plug awl 6 is 20～100%.The initial position in plug awl gap 8 is consistent with the initial position of plug awl 6, extends to plug awl bottom 7 always, forms enclosed construction, and its angle excursion is 1 °～60 °.
The design method of utilizing the present invention to propose designs and has processed test engine, has carried out cold flow and heat examination experiment, proves that this kind scheme has very high high low-altitude performance, and is easy to process realization.This kind plug nozzle organization plan, can be applied to various requirement along with variable height has the aircraft propelling motor of performance compensation ability, its major advantage is: the even flow field degree is good, performance is high, be easy to process realization, be easy to cool off, the design of thrust chamber and inner nozzle uses that inheritance is good, compound mode is flexible.Fig. 8 be Unit six " watt " shape plug nozzle test engine.Its major parameter and profile equation are as follows: inner nozzle throat diameter 14mm, and interior expansion ratio is 4, and overall expansion ratio is 35, and inner nozzle extending section profile parabolic equation is (X, the unit of Y is m):
Y=0.0067069111+0.2981401 * X-2.95283 * X * X " watt " tapered equation of shape curved surface plug form (X, the unit of Y is m) by two sections curves:
(1)Y＝-0.010769502-0.1028684×X+0.6063579×X
2
(2)Y＝-0.031854074+0.034586377×X+0.4111022×
X
2-0.096615128×X
3
Plug nozzle utilization of the present invention field is extensive, as the propulsion system of (1) reusable vehicle; (2) the high-altitude large size is than high-performance propelling motor; (3) sky and space plane engine jet pipe.
Claims (10)
1. plug nozzle, form by a plurality of inner nozzles, plug awl, it is characterized in that: inner nozzle (2) is an axially symmetric structure, plug awl (6) be designed to " watt " the shape curved surface, inner nozzle (2) can be divided into converging portion (3), throat (4), extending section (5), and inner nozzle (2) and plug awl (6) design for one.
2. plug nozzle according to claim 1 is characterized in that: profile can be calculated generation with equation, and inner nozzle (2) profile The Representation Equation is y=a
nx
n+ a
N-1x
N-1+ ... + a
1X+a
0, a in the formula
i(i=0,1 ..., n) be the profile design parameter; Watt shape curved surface plug awl (6) profile The Representation Equation is y=b
nx
n+ b
N-1x
N-1+ ... + b
1X+b
0, b in the formula
i(i=0,1 ..., n) be the profile design parameter; The expansion ratio ε of inner nozzle (2)
iFor inner nozzle (2) outlet diameter and throat (4) diameter ratio square, ε
i=1～10, overall expansion ratio ε
tFor inner nozzle (2) outlet edge position to the ratio of the distance of engine spindle line and throat diameter square, ε
t=10～300.
3. plug nozzle according to claim 1 is characterized in that: also can adopt direct curved surface method of formation to generate the profile data point.
4. plug nozzle according to claim 1 is characterized in that: the brachymemma coefficient scope of plug awl (6) is 20～100%.
5. plug nozzle according to claim 1 is characterized in that: the initial position in plug awl gap is consistent with the initial position of plug awl, extends to plug awl bottom always, forms enclosed construction, and its angle excursion is 1 °～60 °.
6. according to claim 1,2,3 described plug nozzles, it is characterized in that: plug nozzle can be designed to direct-exhausting type " watt " the shape plug nozzle.
7. according to claim 1,2,3 described plug nozzles, it is characterized in that: plug nozzle can be designed to the row's of ring formula " watt " the shape plug nozzle.
8. plug nozzle according to claim 1 is characterized in that: the shape of plug awl bottom (7) is relevant according to the composite structure shape of plug nozzle unit (1).
9. according to claim 6,7 described plug nozzles, it is characterized in that: the shape of plug awl bottom (7) can be the arch bridge shape.
10. according to claim 6,7 described plug nozzles, it is characterized in that: the shape of plug awl bottom (7) can be petal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB021586950A CN1224779C (en) | 2002-12-26 | 2002-12-26 | Stopper type jet pipe |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB021586950A CN1224779C (en) | 2002-12-26 | 2002-12-26 | Stopper type jet pipe |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1419044A true CN1419044A (en) | 2003-05-21 |
| CN1224779C CN1224779C (en) | 2005-10-26 |
Family
ID=4753155
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB021586950A Expired - Fee Related CN1224779C (en) | 2002-12-26 | 2002-12-26 | Stopper type jet pipe |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1224779C (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102536514A (en) * | 2012-01-17 | 2012-07-04 | 南京航空航天大学 | Binary plug nozzle of turbofan engine with afterburning |
| CN102635464A (en) * | 2012-04-05 | 2012-08-15 | 北京航空航天大学 | Double-unit symmetric distribution linear plug nozzle cold-flow tester |
| CN102635463A (en) * | 2012-04-05 | 2012-08-15 | 北京航空航天大学 | Cold-flow test device for one-unit linear plug spray pipe |
| CN102817745A (en) * | 2012-08-16 | 2012-12-12 | 北京航空航天大学 | Low-cost and simple unit round-to-square plug nozzle test device |
| CN102817744A (en) * | 2012-08-16 | 2012-12-12 | 北京航空航天大学 | Six-unit tile-shaped plug nozzle cold flow test device |
| CN102828851A (en) * | 2012-08-16 | 2012-12-19 | 北京航空航天大学 | Cold flow test device for scaling linear plug type spray pipe carrier |
| CN103196348A (en) * | 2013-03-07 | 2013-07-10 | 中国航空工业集团公司沈阳发动机设计研究所 | Design method of plug-type axial symmetry spray pipe outlet diameter measuring tool |
| CN103470400A (en) * | 2013-07-24 | 2013-12-25 | 南京航空航天大学 | Design method of exhaust nozzle with controllable inlet and outlet shapes for air-breathing hypersonic flight vehicle |
| CN107165739A (en) * | 2017-07-26 | 2017-09-15 | 北京航空航天大学 | Solid-liquid rocket circular seam type plug nozzle |
| CN109139296A (en) * | 2018-09-11 | 2019-01-04 | 中国人民解放军国防科技大学 | Rocket-based combined cycle engine |
| CN109538375A (en) * | 2019-01-11 | 2019-03-29 | 中国人民解放军国防科技大学 | Injection rocket applied to rocket-based combined cycle engine |
-
2002
- 2002-12-26 CN CNB021586950A patent/CN1224779C/en not_active Expired - Fee Related
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102536514A (en) * | 2012-01-17 | 2012-07-04 | 南京航空航天大学 | Binary plug nozzle of turbofan engine with afterburning |
| CN102635464A (en) * | 2012-04-05 | 2012-08-15 | 北京航空航天大学 | Double-unit symmetric distribution linear plug nozzle cold-flow tester |
| CN102635463A (en) * | 2012-04-05 | 2012-08-15 | 北京航空航天大学 | Cold-flow test device for one-unit linear plug spray pipe |
| CN102817745B (en) * | 2012-08-16 | 2014-06-18 | 北京航空航天大学 | Low-cost and simple unit round-to-square plug nozzle test device |
| CN102817744A (en) * | 2012-08-16 | 2012-12-12 | 北京航空航天大学 | Six-unit tile-shaped plug nozzle cold flow test device |
| CN102828851A (en) * | 2012-08-16 | 2012-12-19 | 北京航空航天大学 | Cold flow test device for scaling linear plug type spray pipe carrier |
| CN102817745A (en) * | 2012-08-16 | 2012-12-12 | 北京航空航天大学 | Low-cost and simple unit round-to-square plug nozzle test device |
| CN102817744B (en) * | 2012-08-16 | 2014-09-17 | 北京航空航天大学 | Six-unit tile-shaped plug nozzle cold flow test device |
| CN103196348A (en) * | 2013-03-07 | 2013-07-10 | 中国航空工业集团公司沈阳发动机设计研究所 | Design method of plug-type axial symmetry spray pipe outlet diameter measuring tool |
| CN103196348B (en) * | 2013-03-07 | 2016-08-03 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of method for designing of plug axisymmetric nozzle outlet diameter measuring tool |
| CN103470400A (en) * | 2013-07-24 | 2013-12-25 | 南京航空航天大学 | Design method of exhaust nozzle with controllable inlet and outlet shapes for air-breathing hypersonic flight vehicle |
| CN107165739A (en) * | 2017-07-26 | 2017-09-15 | 北京航空航天大学 | Solid-liquid rocket circular seam type plug nozzle |
| CN109139296A (en) * | 2018-09-11 | 2019-01-04 | 中国人民解放军国防科技大学 | Rocket-based combined cycle engine |
| CN109139296B (en) * | 2018-09-11 | 2020-01-24 | 中国人民解放军国防科技大学 | Rocket-based combined cycle engine |
| CN109538375A (en) * | 2019-01-11 | 2019-03-29 | 中国人民解放军国防科技大学 | Injection rocket applied to rocket-based combined cycle engine |
| CN109538375B (en) * | 2019-01-11 | 2020-01-21 | 中国人民解放军国防科技大学 | Injection rocket applied to rocket-based combined cycle engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN1224779C (en) | 2005-10-26 |
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