CN103823921B - A kind of large-bypass-ratio engine split Nozzle Design method - Google Patents
A kind of large-bypass-ratio engine split Nozzle Design method Download PDFInfo
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- CN103823921B CN103823921B CN201310659759.6A CN201310659759A CN103823921B CN 103823921 B CN103823921 B CN 103823921B CN 201310659759 A CN201310659759 A CN 201310659759A CN 103823921 B CN103823921 B CN 103823921B
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Abstract
A kind of large-bypass-ratio engine split Nozzle Design method, intension jet pipe and the outer design for containing jet pipe suitable for large-bypass-ratio engine split jet pipe；Using Parametric designing, jet pipe wall surface is constructed with smooth continuous curve, determines jet pipe along journey area change, detailed process along journey variable area given rule using reasonable converging portion are as follows: for the step of defining jet pipe pneumatic design initial parameter and assignment one；For the step of solving plane molded line in jet pipe two；For solving the step of jet pipe is along journey variable area given rule three；For the step of solving jet pipe inside and outside wall surface molded line four；For the step of calculating jet pipe aeroperformance five；Converging form is pressed when design on flow area.Advantages of the present invention: can quickly design a kind of large-bypass-ratio engine jet pipe flow path scheme and adjust the trend of jet pipe according to the actual situation, can significantly reduce the design cycle using this design method.
Description
Technical field
The present invention relates to aero-engine Nozzle Design field, in particular to a kind of large-bypass-ratio engine split spray
Pipe design method.
Background technique
Jet pipe is the important component of large-bypass-ratio engine, and performance has very for high-performance transport
It is apparent to influence, aeroplane performance can be made to generate biggish change its performance has slight change.Split ejector exhaust pipe is
Current most widely used large-bypass-ratio engine ejector exhaust pipe form, intension jet pipe and outer culvert jet pipe have similar geometry
Shape can take identical design method when carrying out pneumatic design.Traditional large-bypass-ratio engine Nozzle Design uses
Method be several geometric parameters of building, founding mathematical models construct the flow path shape of jet pipe.The shape of jet pipe wall surface is by one group
Line segment indicates, is smoothly connected between line segment using circular arc.It is inconsistent due to straight line and circular arc curvature, lead to the junction of curve
There are the discontinuous transition points of curvature, are also easy to produce the mutation of speed and pressure in curvature discrete point, reduce the property of jet pipe
Energy.
Summary of the invention
It is an object of the present invention to provide a kind of large-bypass-ratio engine split jet pipe Pneumatic design methods, are both suitable for
Military transportation airplane, and it is suitable for seating plane.
The present invention provides a kind of large-bypass-ratio engine split Nozzle Design methods, it is characterised in that: big bypass ratio
Engine split Nozzle Design method, large-bypass-ratio engine jet pipe Pneumatic design method is suitable for large-bypass-ratio engine point
Intension jet pipe and the outer design for containing jet pipe in open type jet pipe.
Using Parametric designing, jet pipe wall surface is constructed with smooth continuous curve, using reasonable converging portion along journey area
Changing rule determines jet pipe along journey area change, detailed process are as follows:
For the step of defining jet pipe pneumatic design initial parameter and assignment one；
For the step of solving plane molded line in jet pipe two；
For solving the step of jet pipe is along journey variable area given rule three；
For the step of solving jet pipe inside and outside wall surface molded line four；
For the step of calculating jet pipe aeroperformance five.
Converging form is pressed when design on flow area.
Initial parameter in step 1 include nozzle inlet internal diameter, middle plane molded line inlet radius, nozzle inlet outer diameter, in
Plane molded line entrance angle, nozzle exit internal diameter, middle plane molded line exit radius, nozzle exit outer diameter, the outlet of middle plane molded line
Angle, jet pipe length, jet pipe are along journey variable area given rule.
The step two, Step 3: step 4 and step 5 are the middle plane molded line with computer Program Generating jet pipe
And nozzle contour, wherein MATLAB, VB, C language establishment can be used in calculation procedure；The nozzle contour file of program output can be used
General or commercial fluid calculation software is read, and calculates its aeroperformance according to input parameter.
Plane molded line uses smooth, continuous polynomial curve or B-spline curves, converging portion variable area given rule in jet pipe
It is selected from Batchelor-Shaw curve, Pennylvania curve, Wei Xinsi base curves, quintic curve, bicubic curve
It selects.
Pneumatic design, specific steps are carried out in accordance with the following steps to large-bypass-ratio engine jet pipe are as follows:
Define jet pipe pneumatic design initial parameter the step of one, including nozzle inlet internal diameter R_in_1, middle plane molded line into
Port radius R_in_m, nozzle inlet outer diameter R_in_2, middle plane molded line entrance angle α, nozzle exit internal diameter R_out_1, middle position
Face molded line exit radius R_out_m, nozzle exit outer diameter R_out_2, middle plane molded line exit angle β, jet pipe length L, jet pipe
Along journey variable area given rule S_d.
The definition of 1 nozzle contour geometric parameter variable of table, the signal of Fig. 1 nozzle contour geometric parameter.
The step of solving the equation or function of plane molded line in jet pipe according to initial parameter two.Shown with quintic algebra curve curve
Plane molded line solution procedure in example jet pipe.
Quintic algebra curve curve controlled equation are as follows: y=a0+a1x+a2x2+a3x3+a4x4+a5x5。
Its first derivative are as follows: y'=a1+2a2x+3a3x2+4a4x3+5a5x4。
Its second dervative are as follows: y''=2a2+6a3x+12a4x2+20a5x3。
Starting point coordinate, first derivative and the second dervative for setting quintic algebra curve curve are respectively (x1,y1)、y1’、
y1' ', terminating point coordinate, first derivative and second dervative are respectively (x2,y2)、y2’、y2' ', it is found out according to system of linear equations (1)
a0、a1、a2、a3、a4、a5.By a0、a1、a2、a3、a4、a5Substituting into equation can be obtained the curvilinear equation.
Plane molded line inlet point coordinate is (0, R_in_m) in jet pipe, first derivative values at plane molded line inlet point in jet pipe
R_in_m '=tan α, second dervative is 0 at plane molded line inlet point in jet pipe.In jet pipe plane molded line exit point coordinate be (L,
R_out_m), plane molded line exit point first derivative values R_out_m '=tan β in jet pipe, plane molded line exit point in jet pipe
Second dervative is 0.Each initial parameter substitution linear equation (1) can be acquired to the controlling party of plane molded line in quintic algebra curve jet pipe
Journey.
The step of jet pipe is along journey variable area given rule three is solved according to initial parameter.Jet pipe has more along journey variable area given rule
Kind expression-form, with Wei Xinsi base curves example jet pipe along journey area change.
The expression formula of Wei Xinsi base curves is shown in formula (2), wherein R1Indicate nozzle entry equivalent radius, wherein R2Indicate spray
Pipe exports equivalent radius.
The step of solving wall surface inside and outside jet pipe according to plane molded line in jet pipe and evolution with distance rule four.Using the above method
Inside and outside the jet pipe of generation wall surface molded line, middle plane molded line and Fig. 2 is seen along journey area change example.
The step of application specific software for calculation or business computing software calculate jet pipe aeroperformance five.
1 jet pipe pneumatic design initial parameter of table
| 1 | R_in_1 | Nozzle inlet internal diameter, the preparatory assignment of initial parameter |
| 2 | R_in_m | Middle plane molded line inlet radius, the preparatory assignment of initial parameter |
| 3 | R_in_2 | Nozzle inlet outer diameter, the preparatory assignment of initial parameter |
| 4 | α | Middle plane molded line entrance angle, the preparatory assignment of initial parameter |
| 5 | R_out_1 | Nozzle exit internal diameter, the preparatory assignment of initial parameter |
| 6 | R_out_m | Middle plane molded line exit radius, the preparatory assignment of initial parameter |
| 7 | R_out_2 | Nozzle exit outer diameter, the preparatory assignment of initial parameter |
| 8 | β | Middle plane molded line exit angle, the preparatory assignment of initial parameter |
| 9 | L | Jet pipe length, the preparatory assignment of initial parameter |
| 10 | S_d | Jet pipe is along journey variable area given rule, the preparatory assignment of initial parameter |
Advantages of the present invention:
Large-bypass-ratio engine jet pipe Pneumatic design method provided by the invention can quickly design a kind of big duct
The trend for adjusting jet pipe than engine jet pipe flow path scheme and according to the actual situation, can significantly reduce design using this design method
Period.
Detailed description of the invention
With reference to the accompanying drawing and embodiment the present invention is described in further detail:
Fig. 1 is nozzle contour geometric parameter schematic diagram；
Fig. 2 is for wall surface molded line, middle plane molded line inside and outside jet pipe and along journey area change schematic diagram.
Specific embodiment
Embodiment 1
Present embodiments provide a kind of large-bypass-ratio engine split Nozzle Design method, it is characterised in that: big duct
Than engine split Nozzle Design method, large-bypass-ratio engine jet pipe Pneumatic design method is suitable for large-bypass-ratio engine
Intension jet pipe and the outer design for containing jet pipe in split jet pipe.
Using Parametric designing, jet pipe wall surface is constructed with smooth continuous curve, using reasonable converging portion along journey area
Changing rule determines jet pipe along journey area change, detailed process are as follows:
For the step of defining jet pipe pneumatic design initial parameter and assignment one；
For the step of solving plane molded line in jet pipe two；
For solving the step of jet pipe is along journey variable area given rule three；
For the step of solving jet pipe inside and outside wall surface molded line four；
For the step of calculating jet pipe aeroperformance five.
Converging form is pressed when design on flow area.
Initial parameter in step 1 include nozzle inlet internal diameter, middle plane molded line inlet radius, nozzle inlet outer diameter, in
Plane molded line entrance angle, nozzle exit internal diameter, middle plane molded line exit radius, nozzle exit outer diameter, the outlet of middle plane molded line
Angle, jet pipe length, jet pipe are along journey variable area given rule.
The step two, Step 3: step 4 and step 5 are the middle plane molded line with computer Program Generating jet pipe
And nozzle contour, wherein MATLAB, VB, C language establishment can be used in calculation procedure；The nozzle contour file of program output can be used
General or commercial fluid calculation software is read, and calculates its aeroperformance according to input parameter.
Plane molded line uses smooth, continuous polynomial curve or B-spline curves, converging portion variable area given rule in jet pipe
It is selected from Batchelor-Shaw curve, Pennylvania curve, Wei Xinsi base curves, quintic curve, bicubic curve
It selects.
Pneumatic design, specific steps are carried out in accordance with the following steps to large-bypass-ratio engine jet pipe are as follows:
Define jet pipe pneumatic design initial parameter the step of one, including nozzle inlet internal diameter R_in_1, middle plane molded line into
Port radius R_in_m, nozzle inlet outer diameter R_in_2, middle plane molded line entrance angle α, nozzle exit internal diameter R_out_1, middle position
Face molded line exit radius R_out_m, nozzle exit outer diameter R_out_2, middle plane molded line exit angle β, jet pipe length L, jet pipe
Along journey variable area given rule S_d.
The definition of 1 nozzle contour geometric parameter variable of table, the signal of Fig. 1 nozzle contour geometric parameter.
The step of solving the equation or function of plane molded line in jet pipe according to initial parameter two.Shown with quintic algebra curve curve
Plane molded line solution procedure in example jet pipe.
Quintic algebra curve curve controlled equation are as follows: y=a0+a1x+a2x2+a3x3+a4x4+a5x5。
Its first derivative are as follows: y'=a1+2a2x+3a3x2+4a4x3+5a5x4。
Its second dervative are as follows: y''=2a2+6a3x+12a4x2+20a5x3。
Starting point coordinate, first derivative and the second dervative for setting quintic algebra curve curve are respectively (x1,y1)、y1’、
y1' ', terminating point coordinate, first derivative and second dervative are respectively (x2,y2)、y2’、y2' ', it is found out according to system of linear equations (1)
a0、a1、a2、a3、a4、a5.By a0、a1、a2、a3、a4、a5Substituting into equation can be obtained the curvilinear equation.
Plane molded line inlet point coordinate is (0, R_in_m) in jet pipe, first derivative values at plane molded line inlet point in jet pipe
R_in_m '=tan α, second dervative is 0 at plane molded line inlet point in jet pipe.In jet pipe plane molded line exit point coordinate be (L,
R_out_m), plane molded line exit point first derivative values R_out_m '=tan β in jet pipe, plane molded line exit point in jet pipe
Second dervative is 0.Each initial parameter substitution linear equation (1) can be acquired to the controlling party of plane molded line in quintic algebra curve jet pipe
Journey.
The step of jet pipe is along journey variable area given rule three is solved according to initial parameter.Jet pipe has more along journey variable area given rule
Kind expression-form, with Wei Xinsi base curves example jet pipe along journey area change.
The expression formula of Wei Xinsi base curves is shown in formula (2), wherein R1Indicate nozzle entry equivalent radius, wherein R2Indicate spray
Pipe exports equivalent radius.
The step of solving wall surface inside and outside jet pipe according to plane molded line in jet pipe and evolution with distance rule four.Using the above method
Inside and outside the jet pipe of generation wall surface molded line, middle plane molded line and Fig. 2 is seen along journey area change example.
The step of application specific software for calculation or business computing software calculate jet pipe aeroperformance five.
Claims (1)
1. a kind of large-bypass-ratio engine split Nozzle Design method, it is characterised in that: the spray of large-bypass-ratio engine split
Pipe design method intension jet pipe and outer design for containing jet pipe suitable for large-bypass-ratio engine split jet pipe；
Using Parametric designing, jet pipe wall surface is constructed with smooth continuous curve, using reasonable converging portion along journey area change
Rule determines jet pipe along journey area change, detailed process are as follows:
For the step of defining jet pipe pneumatic design initial parameter and assignment one；
For the step of solving plane molded line in jet pipe two；
For solving the step of jet pipe is along journey variable area given rule three；
For the step of solving jet pipe inside and outside wall surface molded line four；
For the step of calculating jet pipe aeroperformance five；
Converging form is pressed when design on flow area；
Initial parameter in step 1 includes nozzle inlet internal diameter, middle plane molded line inlet radius, nozzle inlet outer diameter, middle plane
Molded line entrance angle, nozzle exit internal diameter, middle plane molded line exit radius, nozzle exit outer diameter, middle plane molded line exit angle,
Jet pipe length, jet pipe are along journey variable area given rule；
The step two, Step 3: step 4 and step 5 are with the middle plane molded line of computer Program Generating jet pipe and spray
Pipe shape, wherein MATLAB, VB, C language establishment can be used in calculation procedure；The nozzle contour file of program output can be used general
Or commercial fluid calculation software read, and its aeroperformance is calculated according to input parameter；
In jet pipe plane molded line use smooth, continuous polynomial curve or B-spline curves, converging portion variable area given rule from
Batchelor-Shaw curve, Wei Xinsi base curves, quintic curve, is selected in bicubic curve Pennylvania curve
It selects；
Pneumatic design, specific steps are carried out in accordance with the following steps to large-bypass-ratio engine split jet pipe are as follows:
The step of defining jet pipe pneumatic design initial parameter one, including nozzle inlet internal diameter R_in_1, middle plane molded line import half
Diameter R_in_m, nozzle inlet outer diameter R_in_2, middle plane molded line entrance angle α, nozzle exit internal diameter R_out_1, middle plane type
Line exit radius R_out_m, nozzle exit outer diameter R_out_2, middle plane molded line exit angle β, jet pipe length L, jet pipe are along journey
Variable area given rule S_d；
The step of solving the equation or function of plane molded line in jet pipe according to initial parameter two；In the jet pipe of quintic algebra curve curve
Plane molded line solution procedure；
Quintic algebra curve curve controlled equation are as follows: y=a0+a1x+a2x2+a3x3+a4x4+a5x5；
Its first derivative are as follows: y'=a1+2a2x+3a3x2+4a4x3+5a5x4；
Its second dervative are as follows: y "=2a2+6a3x+12a4x2+20a5x3；
Starting point coordinate, first derivative and the second dervative for setting quintic algebra curve curve are respectively (x1,y1)、y1’、y1", it terminates
Point coordinate, first derivative and second dervative are respectively (x2,y2)、y2’、y2", a is found out according to system of linear equations (1)0、a1、a2、a3、
a4、a5；By a0、a1、a2、a3、a4、a5Substituting into equation can be obtained quintic algebra curve curve controlled equation；
Plane molded line inlet point coordinate is (0, R_in_m) in jet pipe, first derivative values R_ at plane molded line inlet point in jet pipe
In_m '=tan α, second dervative is 0 at plane molded line inlet point in jet pipe；Plane molded line exit point coordinate is (L, R_ in jet pipe
Out_m), plane molded line exit point first derivative values R_out_m '=tan β in jet pipe, plane molded line exit point in jet pipe
Second dervative is 0；Each initial parameter substitution linear equation (1) can be acquired to the controlling party of plane molded line in quintic algebra curve jet pipe
Journey；
The step of jet pipe is along journey variable area given rule three is solved according to initial parameter；According to plane molded line and evolution with distance in jet pipe
Rule solves the step of wall surface inside and outside jet pipe four；Application specific software for calculation or business computing software calculate jet pipe aeroperformance
Step 5.
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| CN105197255B (en) * | 2015-09-25 | 2018-03-02 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of air intake duct curve design method |
| CN117685098B (en) * | 2024-02-01 | 2024-04-05 | 西安航空学院 | Stepless adjusting device for outer duct of variable-cycle engine |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101676918A (en) * | 2008-09-18 | 2010-03-24 | 中国航空工业第一集团公司沈阳发动机设计研究所 | Pneumatic design method for separation type exhaust jet pipe of high bypass ratio engine |
| CN203249769U (en) * | 2013-04-16 | 2013-10-23 | 中国航空工业集团公司沈阳发动机设计研究所 | Net-type distortion device used for high-bypass ratio engine |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101676918A (en) * | 2008-09-18 | 2010-03-24 | 中国航空工业第一集团公司沈阳发动机设计研究所 | Pneumatic design method for separation type exhaust jet pipe of high bypass ratio engine |
| CN203249769U (en) * | 2013-04-16 | 2013-10-23 | 中国航空工业集团公司沈阳发动机设计研究所 | Net-type distortion device used for high-bypass ratio engine |
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