CN107229798A - A kind of pair of S bending nozzle design method - Google Patents
A kind of pair of S bending nozzle design method Download PDFInfo
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- CN107229798A CN107229798A CN201710412232.1A CN201710412232A CN107229798A CN 107229798 A CN107229798 A CN 107229798A CN 201710412232 A CN201710412232 A CN 201710412232A CN 107229798 A CN107229798 A CN 107229798A
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- jet pipe
- offset distance
- section
- nozzle
- bending
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2113/00—Details relating to the application field
- G06F2113/14—Pipes
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/18—Manufacturability analysis or optimisation for manufacturability
Abstract
The invention provides a kind of pair of S bending nozzle design method, it is related to aero-engine field, including obtaining initial design parameters, calculate major semiaxis a (x) and semi-minor axis b (x) of the jet pipe along journey hyperelliptic section changing rule, hyperelliptic shape index n is determined, the curved longitudinal offset distance Δ Y of first paragraph S are determined1With the curved longitudinal offset distance Δ Y of second segment S2.The present invention solves the problem of quickly being designed double S bending nozzles under different designs parameter, largely improves the Stealth Fighter of modeling efficiency and jet pipe.
Description
Technical field
The present invention relates to aero-engine field, more particularly, to the double S bending nozzles design sides of aero-engine gas extraction system
Method.
Background technology
With the development of various anti-stealth technololgys, designed by Stealth shape, cooling technology and traditional stealth material are realized
The technical advantage of the active service invisbile plane (such as F-22 fighter planes and B-2 bombers) of low detectable Stealth Fighter is oversize without Faville
Time.Now it is necessary to from body and engine integration stealthing design theory, seek new stealthy approach, such
Under background, S bending nozzles are arisen at the historic moment.At present, the country is all outer has carried out beforehand research for several possible pair of S bending nozzle schemes, but
It is during this kind of R ＆ D design, to lack and flow to the performances such as nozzle section area, cross sectional shape for jet pipe center line, edge
The double S bending nozzles stealthing design methods considered of parameter, so as to influence the efficiency of the R ＆ D design of double S bending nozzles.
The content of the invention
It is curved to solve double S present in prior art it is an object of the invention to provide a kind of pair of S bending nozzle design method
The technical problem that jet pipe stealth structure design is present, on the premise of aeroperformance is taken into account, adds the design effect of double S bending nozzles
Rate, precision and versatility.
A kind of pair of S bending nozzle design method that the present invention is provided, including：
Initial design parameters are obtained, the initial design parameters include：Nozzle inlet diameter of section rin, jet pipe S segment length
L, jet pipe total offset distance S, the width W of nozzle exit sectioneWith the height H of nozzle exit sectione, wherein the jet pipe S segment length L
For the sum of first curved axial length of S of jet pipe and second curved axial length of S of jet pipe, the total offset distance S of jet pipe is nozzle exit
The fore-and-aft distance of center line and center line of suction, the nozzle exit section is rectangle；
According to initial design parameters, the variable area given rule using jet pipe along journey section calculates jet pipe and cut along journey hyperelliptic
The major semiaxis a (x) and semi-minor axis b (x) in face changing rule；
According to jet pipe along journey area of section, major semiaxis a (x) changing rules and semi-minor axis b (x) changing rules, determine super ellipse
Toroidal index n.
Blocked completely according to jet pipe, using the given total offset distance S of jet pipe, determine the curved longitudinal offset distance Δ Y of first paragraph S1With
The curved longitudinal offset distance Δ Y of two sections of S2。
Relative to prior art, of the present invention pair of S bending nozzle design method has the advantage that：Overcome traditional
Hyperelliptic method is when design S is curved, and form factor n selection needs to table look-up to determine, not only takes, and accuracy is not high,
Sharply changing section is easily produced, the problem of being influenceed on stream in air intake duct or jet pipe and the stagnation pressure of outlet, the present invention establishes one
Plant and only need to consider jet pipe import and export parameter, the adaptive modeling method that interlude cross section parameter can be uniquely determined, very big journey
Modeling efficiency and accuracy are improved on degree.
Brief description of the drawings
, below will be to specific in order to illustrate more clearly of the specific embodiment of the invention or technical scheme of the prior art
The accompanying drawing used required in embodiment or description of the prior art is briefly described, it should be apparent that, in describing below
Accompanying drawing is some embodiments of the present invention, for those of ordinary skill in the art, before creative work is not paid
Put, other accompanying drawings can also be obtained according to these accompanying drawings.
Fig. 1 is provided in an embodiment of the present invention pair of S bending nozzle mentality of designing flow chart；
Fig. 2 is that provided in an embodiment of the present invention pair of S bending nozzle blocks schematic diagram completely；
Fig. 3 is the double S bending nozzle design parameter schematic diagrames of the embodiment of the present invention；
Fig. 4 is the double S bending nozzle overall schematics of the embodiment of the present invention；
Fig. 5 a, Fig. 5 b and Fig. 5 c are double S bending nozzles moulds of the double S bending nozzle different area transition equations of the embodiment of the present invention
Type；
Fig. 5 d are that double S bending nozzle models progress numerical value of the embodiment of the present invention according to Fig. 5 a, Fig. 5 b and Fig. 5 c is obtained
Jet pipe Ma distribution；
Fig. 6 a, Fig. 6 b and Fig. 6 c are different double Ss curved models of the offset distance than S/D of the double S bending nozzles of the embodiment of the present invention；
Fig. 6 d are that double S bending nozzle models progress numerical value of the embodiment of the present invention according to Fig. 6 a, Fig. 6 b and Fig. 6 c is obtained
Jet pipe Ma distribution；
Fig. 7 a, Fig. 7 b and Fig. 7 c are the different the ratio of width to height W/H of the double S bending nozzles of the embodiment of the present invention curved models of double S；
Fig. 7 d are that double S bending nozzle models progress numerical value of the embodiment of the present invention according to Fig. 7 a, Fig. 7 b and Fig. 7 c is obtained
Jet pipe Ma distribution；
Fig. 8 a, Fig. 8 b, Fig. 8 c, Fig. 8 d and Fig. 8 e are by implementing double S bending nozzles experimental pieces that the embodiment of the present invention makes.
Embodiment
Technical scheme is clearly and completely described below in conjunction with accompanying drawing, it is clear that described implementation
Example is a part of embodiment of the invention, rather than whole embodiments.Based on the embodiment in the present invention, ordinary skill
The every other embodiment that personnel are obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.
In the description of the invention, it is necessary to explanation, term " " center ", " on ", " under ", "left", "right", " vertical ",
The orientation or position relationship of the instruction such as " level ", " interior ", " outer " be based on orientation shown in the drawings or position relationship, merely to
Be easy to the description present invention and simplify description, rather than indicate or imply signified device or element must have specific orientation,
With specific azimuth configuration and operation, therefore it is not considered as limiting the invention.In addition, term " first ", " second ",
" the 3rd " is only used for describing purpose, and it is not intended that indicating or implying relative importance.
In the description of the invention, it is necessary to illustrate, unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection " should be interpreted broadly, for example, it may be being fixedly connected or being detachably connected, or be integrally connected；Can
To be mechanical connection or electrical connection；Can be joined directly together, can also be indirectly connected to by intermediary, Ke Yishi
The connection of two element internals.For the ordinary skill in the art, with concrete condition above-mentioned term can be understood at this
Concrete meaning in invention.
The invention will be further described below in conjunction with the accompanying drawings.
The consideration center line changing rule of the present invention, variable area given rule, hyperelliptic equation and rule, flow are blocked completely
Figure is as shown in figure 1, specific implementation step of the present invention is as follows：
Step 1：Obtain initial design parameters
According to the size of engine other structures, the installation site of engine jet pipe and bulk, nozzle inlet is determined
Diameter of a circle rin, jet pipe S segment length L, L=L1+L2Wherein, L1It is first curved axial length of S of jet pipe, L2It is second S of jet pipe
Curved axial length；It is the fore-and-aft distance of nozzle exit center line and center line of suction to determine the total offset distance S of jet pipe, the total offset distance S of jet pipe,
Nozzle exit area and outlet the ratio of width to height are determined, equivalent radius r is calculatede, according to area formula π re 2=We×He, obtain exporting square
The width W of tee sectioneAnd height He。
Step 2：Jet pipe is calculated along each section major semiaxis a (x) of journey and semi-minor axis b (x) changing rule
According to initial design parameters, according to the jet pipe of formula (1) along journey variable area given rule：
In formula, x is the abscissa of jet pipe, and L is jet pipe S segment length (i.e. L=L1+L2), AeFor nozzle exit area, AinFor
Nozzle inlet area.Here k1And k2It is recommended as 3 and 2 respectively.
Nozzle inlet, outlet and middle arbitrary section are assumed to be circle, therefore (1) formula is variable turns to：
In formula, rinFor nozzle inlet radius, reFor nozzle exit equivalent radius, r is middle arbitrary section radius.
Order
Assuming that arbitrary section is hyperelliptic in the middle of jet pipe, it can thus be concluded that the oval major semiaxis a (x) in jet pipe intermediate cross-section and short
The changing rule of semiaxis b (x) length is：
In formula, ae, beRespectively nozzle exit square-section WeAnd HeHalf.
Step 3：Determine hyperelliptic shape index n
According to hyperelliptic area integral formula：
Order
By variable area given rule, major semiaxis and semi-minor axis a (x), b (x) changing rules formula can determine arbitrary section face
Product and corresponding major semiaxis a, semi-minor axis b, so the index n of arbitrary section is unique, according to hyperelliptic area of section formula
(6) cross-section index n, is gone out by dichotomy iteration.
Pass through above method, it may be determined that three parameters of hyperelliptic curve, hyperelliptic curve is calculated using recursive algorithm
Required discrete coordinate.
The expression formula of recurrence formula is：
In formula, Δ δ is the step-length of recursive operation.
Obtain Xi+1And Yi+1Afterwards, hyperelliptic coordinate points are calculated with formula (8).
Step 4：Obtain the curved longitudinal offset distance Δ Y of first paragraph S1With the curved longitudinal offset distance Δ Y of second segment S2
Required to determine the installing space size of engine jet pipe according to preliminary design of aircraft, determine the total offset distance S conducts of jet pipe
Input parameter, then determines the curved longitudinal offset distance Δ Y of first paragraph S1With the curved longitudinal offset distance Δ Y of second segment S2。
The coordinate system set up as shown in Figure 2, B point coordinates is (0 ,-R), and N point coordinates is (L1+L2,ΔY2-ΔY1-1/2He),
M point coordinates is (L1,bm-ΔY1).According to rule is blocked completely, when B-M-N three point on a straight line, the curved longitudinal directions of first paragraph S are can obtain inclined
Away from Δ Y1With the curved longitudinal offset distance Δ Y of second segment S2Critical value, now do not see nozzle entry and its upstream completely from jet pipe rear
Part, to reduce the infra-red radiation of Caudad, while from nozzle exit any angle all can not direct detection to high temperature turbine parts.
S=△ Y2-△Y1 (10)
Simultaneous formula (9) and formula (10), can respectively obtain the curved and curved second segment S longitudinal offset distance critical values of first paragraph S.
For example, double S bending nozzles design methods that the present embodiment is provided, it is therefore intended that solve present in prior art
The technical problem that double S bending nozzles stealth structure designs are present, on the premise of aeroperformance is taken into account, adds double S bending nozzles
Design efficiency, precision and versatility.For example：The double S bending nozzles design methods design provided by the present embodiment obtains 3 kinds of double S
The physical model of the geometric parameter of bending nozzle, specifically can be as shown in Fig. 5 a, Fig. 5 b and Fig. 5 c.Wherein, after delaying before Fig. 5 a belong to
Anxious area transition rule；The area transition rule delayed before Fig. 5 b belong to after urgency；Fig. 5 c belong to the suitable area transition rule of emergency
Rule.
Again for example：The double S bending nozzles design methods design provided by the present embodiment obtains the geometry of 3 kinds of double S bending nozzles
The physical model of parameter, specifically can be as shown in Fig. 6 a, Fig. 6 b and Fig. 6 c.Wherein, Fig. 6 a, offset distance compares S/D=0；Fig. 6 b, S/D
=0.5；Fig. 6 c, S/D=1.
Again for example：The double S bending nozzles design methods design provided by the present embodiment obtains the geometry of 3 kinds of double S bending nozzles
The physical model of parameter, specifically can be as shown in Fig. 7 a, Fig. 7 b and Fig. 7 c.Wherein, Fig. 7 a, the ratio of width to height W/H=3.3；Fig. 7 b, W/
H=5；Fig. 7 c, W/H=6.7.
Wherein, numerical simulation is carried out to double S bending nozzles models as shown in Fig. 5 a, Fig. 5 b and Fig. 5 c, can obtained such as Fig. 5 d institutes
The jet pipe Ma distributions shown, it can be seen that do not flow back and separate in jet pipe, double S bending nozzles gas designed by the present embodiment
It is dynamic functional.
Numerical simulation is carried out to double S bending nozzles models as shown in Fig. 6 a, Fig. 6 b and Fig. 6 c, spray as shown in fig 6d can be obtained
Pipe Ma is distributed, it can be seen that does not flow back and separates in jet pipe, double S bending nozzles aeroperformances designed by the present embodiment
Well.
Numerical simulation is carried out to double S bending nozzles models as shown in Fig. 7 a, Fig. 7 b and Fig. 7 c, spray as shown in figure 7d can be obtained
Pipe Ma is distributed, it can be seen that does not flow back and separates in jet pipe, double S bending nozzles aeroperformances designed by the present embodiment
Well.
Further, the double S bending nozzles design methods proposed using the present embodiment, in the condition that the ratio of width to height is W/H=3.3
Under, 5 jet pipe experimental pieces are made, material is stainless steel, as shown in Fig. 8 a-8e.
Finally it should be noted that：Various embodiments above is merely illustrative of the technical solution of the present invention, rather than its limitations；To the greatest extent
The present invention is described in detail with reference to foregoing embodiments for pipe, it will be understood by those within the art that：Its according to
The technical scheme described in foregoing embodiments can so be modified, or which part or all technical characteristic are entered
Row equivalent substitution；And these modifications or replacement, the essence of appropriate technical solution is departed from various embodiments of the present invention technology
The scope of scheme.
Claims (4)
1. a kind of pair of S bending nozzle design method, it is characterised in that including：
Initial design parameters are obtained, the initial design parameters include：Nozzle inlet diameter of section rin, jet pipe S segment length L, spray
Manage total offset distance S, the width W of nozzle exit sectioneWith the height H of nozzle exit sectione, wherein the jet pipe S segment length L is spray
The sum of first curved axial length of S of pipe and second curved axial length of S of jet pipe, the total offset distance S of jet pipe is nozzle exit center
The fore-and-aft distance of line and center line of suction, the nozzle exit section is rectangle；
According to initial design parameters, the variable area given rule using jet pipe along journey section calculates jet pipe along journey hyperelliptic section
Major semiaxis a (x) and semi-minor axis b (x) changing rule；
According to jet pipe along journey area of section, major semiaxis a (x) changing rules and semi-minor axis b (x) changing rules, hyperelliptic shape is determined
Shape index n.
Blocked completely according to jet pipe, using the given total offset distance S of jet pipe, determine the curved longitudinal offset distance Δ Y of first paragraph S1With second segment S
Curved longitudinal offset distance Δ Y2。
2. according to claim 1 pair of S bending nozzle design method, it is characterised in that by the nozzle inlet section and institute
State nozzle exit section and be set as circle, and the major semiaxis a (x) and the semi-minor axis b (x) according to described along journey section face
Product change calculating is obtained.
3. according to claim 1 pair of S bending nozzle design method, it is characterised in that the hyperelliptic shape index n according to
Change adjust automatically of the jet pipe along journey area of section, major semiaxis a (x) and semi-minor axis b (x).
4. according to claim 1 pair of S bending nozzle design method, it is characterised in that the determination jet pipe first paragraph S is curved vertical
To offset distance Δ Y1With the curved longitudinal offset distance Δ Y of second segment S2, including：The critical condition blocked completely according to jet pipe and given spray
Total offset distance S is managed, first paragraph S bend into a mouthful bottom end points, second segment S bend into mouthful top end and second segment S bows out a mouthful bottom end
Point three point on a straight line, calculates the curved longitudinal offset distance Δ Y of first paragraph S respectively1With the curved longitudinal offset distance Δ Y of second segment S2Critical value.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113279860A (en) * | 2021-06-07 | 2021-08-20 | 西北工业大学 | Inner bulge S-shaped air inlet channel with middle control section and method |
| CN114776461A (en) * | 2022-03-25 | 2022-07-22 | 中国民用航空飞行学院 | S-shaped spray pipe for aircraft engine and design method thereof |
| CN114837846A (en) * | 2022-04-18 | 2022-08-02 | 中国航发沈阳发动机研究所 | Pneumatic and infrared comprehensive design method for low-detectability large-curvature spray pipe |
| CN115855514A (en) * | 2023-03-02 | 2023-03-28 | 中国航发四川燃气涡轮研究院 | Double-bending special-shaped variable cross-section air inlet test device for turboprop power high-altitude platform test |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113279860A (en) * | 2021-06-07 | 2021-08-20 | 西北工业大学 | Inner bulge S-shaped air inlet channel with middle control section and method |
| CN113279860B (en) * | 2021-06-07 | 2022-03-22 | 西北工业大学 | Inner bulge S-shaped air inlet channel with middle control section and method |
| CN114776461A (en) * | 2022-03-25 | 2022-07-22 | 中国民用航空飞行学院 | S-shaped spray pipe for aircraft engine and design method thereof |
| CN114837846A (en) * | 2022-04-18 | 2022-08-02 | 中国航发沈阳发动机研究所 | Pneumatic and infrared comprehensive design method for low-detectability large-curvature spray pipe |
| CN115855514A (en) * | 2023-03-02 | 2023-03-28 | 中国航发四川燃气涡轮研究院 | Double-bending special-shaped variable cross-section air inlet test device for turboprop power high-altitude platform test |
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