CN113361027B - Design method of hidden afterburner flow guide support plate - Google Patents

Design method of hidden afterburner flow guide support plate Download PDF

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CN113361027B
CN113361027B CN202110561658.XA CN202110561658A CN113361027B CN 113361027 B CN113361027 B CN 113361027B CN 202110561658 A CN202110561658 A CN 202110561658A CN 113361027 B CN113361027 B CN 113361027B
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flow guide
support plate
afterburner
guide support
point
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CN113361027A (en
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马宏宇
程荣辉
刘伟琛
曹茂国
姜雨
刘宝
徐兴平
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AECC Shenyang Engine Research Institute
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    • G06—COMPUTING; CALCULATING OR COUNTING
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    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
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    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
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    • G06F30/15—Vehicle, aircraft or watercraft design
    • 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
    • G06F30/28—Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]
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    • G06F2119/08—Thermal analysis or thermal optimisation
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    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
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Abstract

The application belongs to the field of aircraft engine design, and relates to a design method of a flow guide support plate of a hidden afterburner. The method comprises the following steps: step S1, determining structural parameters of the flow guide support plate according to boundary conditions of the flow guide support plate design, wherein the structural parameters comprise the number, the position and the length of the flow guide support plate; step S2, dividing the flow guide support plate into a plurality of radial positions, and obtaining a characteristic streamline of each radial position according to a three-dimensional simulation calculation result; step S3, performing polar coordinate transformation on the characteristic streamline according to the stealth shielding requirement to obtain an initial support plate profile; and step S4, locally correcting the partial molded surface which does not meet the pneumatic requirement through three-dimensional simulation iteration to obtain the final molded surface of the support plate. This application can be fast, convenient design the water conservancy diversion extension board, has improved the stealthy performance of aircraft engine.

Description

Design method of hidden afterburner flow guide support plate
Technical Field
The application belongs to the field of aircraft engine design, and particularly relates to a design method of a flow guide support plate of a hidden afterburner.
Background
From the development trend of fighters at home and abroad, the backward stealth is an important component of the omnidirectional stealth of the aircraft, and the design of the diversion support plate of the stealth afterburner is the most key to realize the backward stealth. The flow guide support plate not only needs to meet the physical requirements for shielding the turbine blade, but also needs to meet the flow field requirements of afterburning tissues under different inlet conditions, so the modeling design of the flow guide support plate is very difficult.
At present, no mature design method is available at home and abroad for designing the hidden afterburner flow guide support plate. The mainstream method applied at present is to design a flow guide support plate by modifying a classical blade profile, and the combustion organization requirement of an afterburner is not fully considered. The method has obvious defects, firstly, the traditional design method cannot give consideration to the shielding requirement of the turbine and the requirement of an afterburner flow field, and especially, on the premise of not considering a diffusion flow path of an afterburner, the traditional design method cannot ensure that the diffusion flow path is not subjected to pneumatic separation. Secondly, the design efficiency is very low, the design period is long, multiple times of iterative trimming are needed, and three-dimensional simulation needs to be carried out every time of trimming. Therefore, a design method of a hidden afterburner flow guide support plate is needed to guide the quick and convenient design of the flow guide support plate, and standardize, systematize and program the design process.
Disclosure of Invention
In order to solve the problems, the design method of the fully-shielding afterburner flow guide support plate is standardized, systematized and programmed, so that the design method of the hidden afterburner flow guide support plate can be suitable for designing flow guide support plates with different structural sizes and afterburner inlet flow fields, and the flow guide support plate which meets the requirements of shielding a turbine and organizing an afterburner flow field can be quickly and conveniently designed.
The application discloses stealthy afterburner water conservancy diversion extension board design method, the water conservancy diversion extension board sets up on afterburning inner cone, and is located before afterburning stabilizer of afterburning inner cone, the stealthy of afterburning room that the water conservancy diversion extension board realized visual direction through the bending shelters from, and this design method includes:
step S1, determining structural parameters of the flow guide support plate according to boundary conditions of the flow guide support plate design, wherein the structural parameters comprise the number, the position and the length of the flow guide support plate;
step S2, dividing the flow guide support plate into a plurality of radial positions, and obtaining a characteristic streamline of each radial position according to a three-dimensional simulation calculation result;
step S3, performing polar coordinate transformation on the characteristic streamline according to the stealth shielding requirement to obtain an initial support plate profile;
and step S4, locally correcting the partial molded surface which does not meet the pneumatic requirement through three-dimensional simulation iteration to obtain the final molded surface of the support plate.
Preferably, in step S1, the boundary conditions include the number of the flow guide plates, the geometric boundary of the flow guide plate, and the corresponding aerodynamic boundary of the flow guide plate during installation.
Preferably, in step S1, determining the number of the flow guide plates includes determining that the number of the flow guide plates is the same as the number of the stressing stabilizers behind the flow guide plates.
Preferably, the geometric boundary of the flow guiding plate installation includes a base merging ring profile, a base inner cone profile, an afterburner initial position, and a afterburner front installation edge geometric position, and in step S1, determining the position of the flow guiding plate includes:
the arrangement position of the flow guide support plate and the rear casing support plate of the turbine form an integral periodic corresponding relation; determining the initial position of the flow guide support plate according to the boundary limit of the inner cone and the confluence ring structure; and determining the termination position of the flow guide support plate according to the structural boundary limit of the stress application stabilizer.
Preferably, the aerodynamic boundary comprises an afterburner inlet total temperature profile, a turbine outlet fluid velocity profile, and in step S2, the three-dimensional simulation calculation comprises:
and performing three-dimensional simulation calculation by taking the total temperature distribution of an inlet of the afterburner and the fluid velocity distribution of an outlet of the turbine as input conditions and taking an afterburner diffusion flow path formed by the flow guide supporting plates as a calculation model.
Preferably, the computational model comprises a diffuser flow path formed by a converging ring and an inner cone.
Preferably, in step S2, the number of the radial positions is at least 10, and each radial position forms a characteristic streamline along the flowing direction of the airflow, and the characteristic streamline is composed of a plurality of point coordinates.
Preferably, in step S3, the polar coordinate transformation includes:
determining a coordinate offset coefficient delta;
determining a point E to be offset1And adjacent point D1A first angular offset Δ therebetween, said adjacent point D1Is the point E to be deviated from1Adjacent coordinate points located in the same original characteristic streamline;
determining the offset point E of the point to be offset after the offset is carried out2Relative to its neighboring point D2By a second angular offset of Δ2Δ × δ, wherein said neighboring point D2Is related to the offset point E2Adjacent coordinate points located in the same original characteristic streamline, and the adjacent point D2Is a neighboring point D1The coordinate points after the offset;
determining the offset point E according to the second angular offset2Polar coordinates of (a).
Preferably, determining the coordinate offset coefficient δ includes:
δ＝360/a/(θ1-θ)
wherein a is the number of the stress application stabilizers, theta1The angular coordinate of the streamline termination point is shown, and theta is the angular coordinate of the streamline starting point.
Preferably, in step S4, the partial profile not meeting the aerodynamic requirement is a position where a local aerodynamic separation exists in the simulation process.
This application can be fast, convenient design the water conservancy diversion extension board, has improved the stealthy performance of aircraft engine.
Drawings
FIG. 1 is a flow chart of a preferred embodiment of the method for designing a flow guide plate of a hidden afterburner.
Fig. 2 is a schematic layout of the flow guide plate of the present application.
FIG. 3 is a schematic view of the characteristic cross-sectional streamline offset of the flow directing plate of the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
The application provides a design method for a flow guide support plate of a hidden afterburner, the flow guide support plate is arranged on an afterburning inner cone and is positioned in front of an afterburning stabilizer of the afterburning inner cone, the flow guide support plate realizes the hidden shielding of the afterburning chamber in the visible direction through bending, and as shown in figure 1, the design method comprises the following steps:
step S1, determining structural parameters of the flow guide support plate according to boundary conditions of the flow guide support plate design, wherein the structural parameters comprise the number, the position and the length of the flow guide support plate;
step S2, dividing the flow guide support plate into a plurality of radial positions, and obtaining a characteristic streamline of each radial position according to a three-dimensional simulation calculation result;
step S3, performing polar coordinate transformation on the characteristic streamline according to the stealth shielding requirement to obtain an initial support plate profile;
and step S4, locally correcting the partial molded surface which does not meet the pneumatic requirement through three-dimensional simulation iteration to obtain the final molded surface of the support plate.
The details will be described below.
In step S1, first, a design input needs to be determined; before designing the stress application and flow guide support plate, various boundary conditions need to be determined. Wherein the necessary boundary conditions include: the number a of the afterburners, the geometric boundary (a basic converging ring profile, a basic inner cone profile, a stabilizer initial position c and a front mounting edge geometric position) and the aerodynamic boundary (afterburner inlet total temperature distribution and turbine outlet speed distribution).
Secondly, determining the key size of the flow guide support plate; and determining the integral scheme of the flow guide support plate according to the basic characteristics of the afterburner and the structural characteristics of the rear casing support plate of the turbine, wherein the integral scheme comprises the number and the arrangement positions of the support plates. The specific method is that the number of the selected flow guide support plates is the same as the number a of the stress application stabilizers, so that the arrangement positions of the stress application flow guide support plates and the casing support plates behind the turbine need to be in an integral periodic corresponding relation, and the flowing conditions between every two support plates are similar. And determining the initial position b of the flow guide support plate according to the boundary limitation of the inner cone and the confluence ring structure. And determining the termination position c of the flow guide plate according to the structural boundary limit of the stabilizer.
A coordinate system is constructed as shown in fig. 2, where the X direction is an airflow flowing direction, and the Y direction is an engine radial direction, and in fig. 2, determining the geometric boundary of the flow guide plate includes: determining a stabilizer arrangement area M and a flow guide support plate arrangement area N in a basic diffusion flow path T by taking a basic profile 1 of an inner cone, a basic profile 2 of a confluence ring, a front mounting edge 3 of an afterburner, a stabilizer starting point 4 and a stabilizer terminal point 5 as boundary conditions, wherein the flow guide support plate terminal point is the stabilizer starting point, and the flow guide support plate starting point 6 is arranged at the rear side of the front mounting edge 3 of the afterburner.
In step S2, the characteristic streamlines at each radial position of the flow guide support plate are determined, the inlet boundary conditions of the afterburner are used as input (three-dimensional temperature and velocity fields), the diffusion flow path (including only the converging ring and the inner cone, but not including the stabilizer) of the afterburner is used as a calculation model, and the coordinates of the constituent points of the characteristic streamlines at each radial position are obtained through three-dimensional simulation calculation, wherein the number of specific radial positions can be determined according to the radial dimension of the support plate, so that the fitting of the profile in step S3 is facilitated.
In some alternative embodiments, in step S3, the polar coordinate transformation includes:
determining a coordinate offset coefficient delta;
determining a point E to be offset1And adjacent point D1A first angular offset Δ therebetween, said adjacent point D1Is the point E to be deviated from1Within the same original characteristic stream lineAdjacent coordinate points of (a);
determining an offset point E of the point to be offset after offset2Relative to its neighboring point D2By a second angular offset of Δ2Δ × δ, wherein the neighboring point D2Is related to the offset point E2Adjacent coordinate points located in the same original characteristic streamline, and the adjacent point D2Is a neighboring point D1The coordinate points after the offset;
determining the polar coordinates of the offset point E2 according to the second angular offset.
In the application, a polar coordinate transformation is used for obtaining a characteristic streamline which can meet the shielding requirement; on the premise of ensuring that the initial point coordinates A (r, theta) of the streamline and the length c of the streamline in the flow direction are unchanged, the coordinates of the streamline composition points moving to the ideal position are obtained through a polar coordinate transformation method. As shown in FIG. 3, X is the flow direction, Z is the circumferential direction, the streamline starting point A (r, theta), the streamline ending point B1(r1,θ1) With two adjacent points E on the original characteristic streamline L1 at a radial position1And D1After polar coordinate transformation, the characteristic streamline L2 of a certain radial position corresponds to two adjacent points E2And D2. Polar coordinate E of any point in the middle of the streamline1(re1,θe1) Move to E by coordinate transformation2(re2,θe2) For example, the specific implementation method of the polar coordinate change is as follows: first, a coordinate offset coefficient δ of 360/a/(θ) is determined1- θ); then determining two adjacent points D of the original streamline1And E1Angle offset of (a) thetae1-θd1(ii) a Then by D2Move to E2Can be determined as delta2＝Δ×δ＝(θe1-θd1)×(360/a/(θ1- θ)); then the polar coordinate of E2 after the shift is transformed to E2(re1,θe1+Δ2) And so on.
Then fitting the molded surface of the flow support plate; and fitting the obtained characteristic flow lines at different radial positions by using three-dimensional modeling software to obtain a first round of three-dimensional flow guide support plate model.
Finally, in step S4, a three-dimensional simulation pneumatic check is performed, and the flow guide plate profile obtained by the fitting is added to a diffusion flow path (including a converging ring, an inner cone and a stabilizer) of the afterburner with afterburner inlet boundary conditions as input (three-dimensional temperature and velocity field), and the flow guide plate profile is used as a calculation model to perform three-dimensional simulation calculation. And analyzing and judging the flow fields at different radial positions in the simulation result, finding out all the radial positions with local separation, locally correcting the profile of the flow guide support plate, repeating the steps on the radial flow lines with the local separation, adjusting the polar coordinates of the support plate characteristic flow lines at the radial positions with the local separation, and correcting the local profile of the flow guide support plate.
This application can be fast, convenient design the water conservancy diversion extension board, has improved the stealthy performance of aircraft engine.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims (9)

1. A design method of a hidden afterburner flow guide support plate is characterized in that the flow guide support plate is arranged on an afterburning inner cone and is positioned in front of an afterburning stabilizer of the afterburning inner cone, and the flow guide support plate realizes hidden shielding of the afterburning chamber in a visual direction through bending, and the design method comprises the following steps:
step S1, determining structural parameters of the flow guide support plate according to boundary conditions of the flow guide support plate design, wherein the structural parameters comprise the number, the position and the length of the flow guide support plate;
step S2, dividing the flow guide support plate into a plurality of radial positions, and obtaining a characteristic streamline of each radial position according to a three-dimensional simulation calculation result;
step S3, performing polar coordinate transformation on the characteristic streamline according to the stealth shielding requirement to obtain an initial support plate profile;
step S4, carrying out local correction on the partial molded surface which does not meet the pneumatic requirement through three-dimensional simulation iteration to obtain the final molded surface of the support plate;
in step S3, the polar coordinate transformation includes:
determining a coordinate offset coefficient delta;
determining a point E to be offset1And adjacent point D1A first angular offset Δ therebetween, said adjacent point D1Is the point E to be deviated from1Adjacent coordinate points located in the same original characteristic streamline;
determining the offset point E of the point to be offset after the offset is carried out2Relative to its neighboring point D2By a second angular offset of Δ2Δ × δ, wherein the neighboring point D2Is related to the offset point E2Adjacent coordinate points located in the same original characteristic streamline, and the adjacent point D2Is a neighboring point D1The coordinate points after the offset;
determining the offset point E according to the second angular offset2Polar coordinates of (a).
2. The method for designing the flow guiding plate of the stealth afterburner as claimed in claim 1, wherein in step S1, the boundary conditions include the number of flow guiding plates to be installed, the geometric boundary of the flow guiding plates to be installed, and the corresponding aerodynamic boundary of the flow guiding plates to be installed.
3. The method for designing a flow guide plate for a concealed afterburner as recited in claim 2, wherein in step S1, determining the number of flow guide plates to be installed comprises determining the number of flow guide plates to be the same as the number of afterburners behind the flow guide plates.
4. The method for designing a flow guiding plate of a concealed afterburner according to claim 2, wherein the flow guiding plate mounting geometric boundary comprises a base converging ring profile, a base inner cone profile, an afterburner starting position and an afterburner front mounting edge geometric position, and the step S1 of determining the position of the flow guiding plate comprises the following steps:
the arrangement positions of the guide support plates are in one-to-one correspondence with the rear casing support plates of the turbine; determining the initial position of the flow guide support plate according to the boundary limit of the inner cone and the confluence ring structure; and determining the termination position of the flow guide support plate according to the structural boundary limit of the stress application stabilizer.
5. The method for designing a hidden afterburner flow guide plate as claimed in claim 2, wherein the aerodynamic boundary comprises an afterburner inlet total temperature distribution and a turbine outlet fluid velocity distribution, and in step S2, the three-dimensional simulation calculation comprises:
and performing three-dimensional simulation calculation by taking the total temperature distribution of an inlet of the afterburner and the fluid velocity distribution of an outlet of the turbine as input conditions and taking an afterburner diffusion flow path formed by the flow guide supporting plates as a calculation model.
6. The method of claim 5, wherein the computational model comprises a diffuser flow path comprising a converging ring and an inner cone.
7. The method for designing the flow guiding plate of the stealth afterburner as claimed in claim 1, wherein in step S2, the number of the radial positions is at least 10, and each radial position forms a characteristic streamline along the airflow flowing direction, and the characteristic streamline is formed by a plurality of point coordinates.
8. The method for designing a flow guide plate of a stealth afterburner as defined in claim 1, wherein determining the coordinate offset coefficient δ comprises:
δ＝360/a/(θ1-θ)
wherein a is the number of the stress application stabilizers, theta1And theta is the angular coordinate of the streamline ending point, and theta is the angular coordinate of the streamline starting point.
9. The method for designing the flow guiding plate of the stealth afterburner as defined in claim 1, wherein in the step S4, the part of the profile which does not meet the aerodynamic requirement is a position where a local aerodynamic separation exists in the simulation process.
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CN107092748A (en) * 2017-04-21 2017-08-25 中国航发沈阳发动机研究所 A kind of afterburner noz(zle) layout method
CN112417596A (en) * 2020-11-20 2021-02-26 北京航空航天大学 Parallel grid simulation method for through-flow model of combustion chamber of aero-engine

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CN111553976B (en) * 2020-04-27 2023-05-12 南昌航空大学 Design method of three-dimensional inward rotation air inlet channel with controllable shock wave and pressure distribution
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CN107092748A (en) * 2017-04-21 2017-08-25 中国航发沈阳发动机研究所 A kind of afterburner noz(zle) layout method
CN112417596A (en) * 2020-11-20 2021-02-26 北京航空航天大学 Parallel grid simulation method for through-flow model of combustion chamber of aero-engine

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