CN115455597A - Tail cone design method for improving matching performance of S-shaped spray pipe of aircraft engine - Google Patents

Tail cone design method for improving matching performance of S-shaped spray pipe of aircraft engine Download PDF

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CN115455597A
CN115455597A CN202211143100.0A CN202211143100A CN115455597A CN 115455597 A CN115455597 A CN 115455597A CN 202211143100 A CN202211143100 A CN 202211143100A CN 115455597 A CN115455597 A CN 115455597A
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tail cone
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central line
spray pipe
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杨坤
杜凯
于明飞
邓洁
黄标
李环
姚伦标
刘静雨
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AECC Guiyang Engine Design Research Institute
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Abstract

A method for designing a tail cone for improving matching performance of an S-shaped spray pipe of an aircraft engine is disclosed, wherein the tail cone is of an S-shaped structure, and the method comprises the following steps: determining a constraint parameter; determining the change rule of the tail cone along the center line of the section; determining a control rule of the change of the area of the section of the tail cone along the way; solving the area and the diameter of the round section along the way; establishing a relation between the on-way circular section and the central line; smoothly transitionally connecting contour lines of a plurality of sections along the way; carrying out S bent spray pipe flow field simulation analysis, and determining an improvement direction by taking the bypass ratio of a simulation result as a basis; redesigning the S-shaped tail cone according to the improvement direction and carrying out simulation evaluation until the design requirement is met. The S-shaped tail cone designed by the invention has the advantages that other parameters are consistent with structural parameters of the improved front tail cone except the on-way section eccentricity, meanwhile, the change rule of the central line of the S-shaped tail cone is determined according to the rule of the central line of the runner profile of the S-shaped spray pipe, the obtained S-shaped tail cone profile adapts to the S-shaped spray pipe profile, the circumferential unevenness of air flow is reduced, and the S-shaped matching performance is further improved.

Description

Tail cone design method for improving matching performance of S-shaped spray pipe of aircraft engine
Technical Field
The invention relates to the technical field of design of jet pipes of aero-engines, in particular to a tail cone design method for improving matching of S-shaped jet pipes of aero-engines.
Background
The S-shaped bent nozzle of the aircraft engine has excellent stealth performance and is widely applied, and a plurality of documents disclose relevant technologies about the S-shaped bent nozzle. If the publication number is CN208310917U discloses a changeover portion structure of solving S curved spray pipe and turbofan engine matching problem, through install the changeover portion structure additional between turbofan engine afterbody exhaust mixer and S curved spray pipe, can effectively solve the engine bypass ratio increase problem that arouses behind the S curved spray pipe by original axisymmetric spray pipe repacking at turbofan engine afterbody, thereby make behind the repacking S curved spray pipe, the operating condition of engine is compared in the operating condition when installing the axisymmetric spray pipe unanimously basically, and then make the aircraft have high aerodynamic performance and high stealthy performance concurrently, the aerial comprehensive strength of aircraft has been improved.
Although the S-shaped bent spray pipe has excellent stealth performance, when the S-shaped bent spray pipe is assembled with a complete machine, the circumferential unevenness of the air flow is easily increased, and the bypass ratio after the S-shaped bent spray pipe is replaced is changed, so that the S-shaped bent spray pipe and the complete machine are poor in matching performance. The conventional method for improving the matching performance of the S-shaped spray pipe comprises two methods, namely adjusting the molded surface of the S-shaped spray pipe, reducing the flow separation phenomenon caused by large curvature, reducing the pneumatic loss of the spray pipe and improving the matching performance of the S-shaped spray pipe and the whole machine; and secondly, the switching section structure is designed in front of the S-shaped spray pipe and behind the mixer casing, the area of an outer culvert outlet is adjusted, the flow distribution of the inner culvert and the outer culvert is controlled, and the matching of the S-shaped spray pipe and the whole mixer is improved. However, the two methods need to redesign the molded surface of the S-shaped bent spray pipe, even change the physical state of the S-shaped bent spray pipe, and have high cost and long period. In view of this, a new idea is changed, the molded surface of the S-shaped bent nozzle is not adjusted at all, and a tail cone design method for improving the matching performance of the S-shaped bent nozzle of the aircraft engine is provided. Although the S-shaped spray pipe disclosed in the above patent CN208310917U is provided with the tail cone structure therein, the tail cone is conical, the area of an air flow channel formed by the conical tail cone and the S-shaped spray pipe is circumferentially distributed unevenly, and then the pressure distribution on the section of the rear end of the tail cone is uneven, the connotation back pressure is increased, the connotation flow is increased, the connotation ratio is increased, and the coniform tail cone is not matched with the S-shaped tail cone.
Disclosure of Invention
The invention mainly aims to provide a tail cone design method for improving the matching performance of an S-shaped spray pipe of an aircraft engine, and aims to solve the technical problems.
In order to achieve the purpose, the invention provides a tail cone design method for improving the matching performance of an S-shaped spray pipe of an aircraft engine, wherein the tail cone is of an S-shaped structure, and the S-shaped tail cone design method comprises the following steps:
step S1: determining a constraint parameter: except the eccentricity Delta S of the section along the way, the other parameters are consistent with the structural parameters of the improved front tail cone;
step S2: determining the change rule of the central line of the on-way section of the S-shaped caudal vertebra: the change rule of the central line of the S-shaped tail cone is controlled by adopting a Lee curve, a Wittonsisky curve or a polynomial equation with different change degrees;
and step S3: determining a control rule of the change of the area of the section of the S-shaped caudal vertebra along the way;
and step S4: solving the area and the diameter of the round section along the way: according to the area change rule in the step S3, under the condition that the areas of the front end and the rear end of the tail cone are known, the area and the diameter of the round section along the way are solved;
step S5: establishing a relation between the on-way circular section and the central line;
step S6: and connecting contour lines of a plurality of sections along the way in a smooth transition manner to obtain the S-shaped tail cone profile.
In step S1, the constraint parameters include maximum constraints of the circular cross-sectional area Ai and the diameter Di at the front end of the tail cone, the eccentricity Δ S of the section along the way, the total axial length, and the circular cross-sectional area Ao and the diameter Do at the rear end of the tail cone.
Preferably, in step S2, the change rule of the central line of the S-shaped tail cone is controlled by a slow-rapid equivalent Lee curve, and the control formula is as follows:
Figure BDA0003854286760000021
in the formula: in the formula, x i 、y i Respectively an x coordinate and a y coordinate at the ith point of the central line; y is 0 Represents the centerline initial y-coordinate; Δ Y j Representing the inlet-outlet offset of the central line, namely the eccentricity Delta S of the section along the way; l is a radical of an alcohol j The axial overall length of the central line of the caudal vertebra.
Optionally, in step S2, the change rule of the central line of the S-shaped tail cone is controlled by a Lee curve with a slow front and a fast back, and the control formula is as follows:
Figure BDA0003854286760000022
in the formula: in the formula, x i 、y i Respectively an x coordinate and a y coordinate at the ith point of the central line; y is 0 Represents the centerline initial y-coordinate; Δ Y j Representing the inlet-outlet offset of the central line, namely the eccentricity Delta S of the section along the way; l is a radical of an alcohol j The axial overall length of the central line of the caudal vertebra.
Optionally, in step S2, the change rule of the center line of the S-shaped tail cone is controlled by a front sharp curve and a rear sharp curve, and the control formula is as follows:
Figure BDA0003854286760000031
in the formula: in the formula, x i 、y i Respectively an x coordinate and a y coordinate at the ith point of the central line; y is 0 Represents the centerline initial y-coordinate; delta Y j Representing the inlet-outlet offset of the central line, namely the eccentricity Delta S of the section along the way; l is a radical of an alcohol j Is the axial total length of the central line of the caudal vertebra.
Preferably, in step S3, the S-shaped end cone is circular in cross section; the change along the path area is controlled by adopting a Vitosynsky curve or Lee curve rule.
Preferably, in step S5, the en-route centerline determined in step S2 is passed through and perpendicular to the several cross-sectional centers on the en-route determined in step S4 according to the following formula:
z′ k ＝z k ；
x′ k ＝(x k -x i )·cosα+(y k -y i )·sinα+x i ；
y′ k ＝-(x k -x i )·sinα+(y k -y i )·cosα+y i ；
wherein the centerline is in the xy plane, (x) i ,y i ) Denotes the coordinates of the centerline at point i, and α denotes the point on the centerline (x) i ,y i ) The end cone of (a) is rotated around the z-axis along the round section of (x) k ,y k ,z k ) Is the coordinate before rotation (x' k ,y' k ,z' k ) The coordinates after rotation.
Preferably, the method further comprises the step S7: and carrying out simulation analysis on the flow field of the S-shaped bent spray pipe, and evaluating the influence of the S-shaped tail cone on the bypass ratio.
In step S7, if the pressure unevenness of the rear end section of the S-shaped tail cone perpendicular to the flow channel direction is large, and the bypass ratio is still larger than the target bypass ratio, the offset distance of the S-shaped tail cone needs to be continuously adjusted.
In step S7, when the offset distance of the S-shaped tail cone is adjusted, the offset distance of the S-shaped tail cone is one fourth to one half of the diameter of the front end of the tail cone.
Due to the adoption of the technical scheme, the invention has the following beneficial effects:
(1) According to the invention, except the on-way section eccentricity of the designed S-shaped tail cone, other parameters are consistent with structural parameters of the improved front tail cone, and meanwhile, the change rule of the center line of the S-shaped tail cone is determined according to the center line rule of the flow passage profile of the S-shaped spray pipe, so that the obtained S-shaped tail cone profile adapts to the profile of the S-shaped spray pipe, the circumferential unevenness of air flow is reduced, and the S-shaped matching performance is further improved.
(2) Compared with the existing conical type caudal vertebra, the improved S-shaped caudal vertebra has the advantages that the parameters of the improved S-shaped caudal vertebra are consistent with those of the caudal vertebra before the improvement except that the eccentricity of the section along the way is changed, so that the improved S-shaped caudal vertebra can be installed without changing the existing connecting structure, the structure is simple, and the design period is short.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
FIG. 1 is a schematic view of the structure of the invention in which an S-shaped tail cone is matched with an S-shaped nozzle;
FIG. 2 is a flow chart of the design of the S-shaped end cone of the present invention;
FIG. 3 is a graph comparing the Mach number distribution of the symmetric surfaces when the cone-shaped tail cone of the prior art and the S-shaped tail cone of the present invention are installed in the S-shaped nozzle.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be obtained by a person skilled in the art without inventive step based on the embodiments of the present invention, are within the scope of protection of the present invention.
It should be noted that all directional indicators (such as up, down, left, right, front, back \8230;) in the embodiments of the present invention are only used to explain the relative positional relationship between the components, the motion situation, etc. in a specific posture (as shown in the attached drawings), and if the specific posture is changed, the directional indicator is changed accordingly.
Referring to fig. 1 and 2, a method for designing a tail cone for improving the matching performance of an S-bend nozzle of an aircraft engine is provided, wherein the tail cone is of an S-shaped structure, and the method for designing the S-shaped tail cone comprises the following steps:
step S1: determining a constraint parameter: the constraint parameters comprise the maximum constraints of the circular section area Ai and the diameter Di at the front end of the tail cone, the eccentricity Delta S of the section along the way, the total axial length, the circular section area Ao at the rear end of the tail cone and the diameter Do, and the rest parameters are consistent with the structural parameters of the improved front tail cone except the eccentricity Delta S of the section along the way; the reason for determining the parameters is that the main index influencing the whole machine matching performance of the S-shaped spray pipe is the bypass ratio which is mainly determined by the internal and external bypass areas at the outlet of the mixer and the pressure unevenness at the rear end of the tail cone, and the method does not relate to the internal and external bypass areas at the outlet of the mixer, so the pressure unevenness at the rear end of the tail cone is the important factor to be considered by the method. It is found through research that the eccentricity Δ S of the cross section along the way has a large influence on the above parameters.
Step S2: determining the change rule of the central line of the on-way section of the S-shaped caudal vertebra: in order to match the S-shaped curved nozzle runner profile, the change rule of the S-shaped tail cone central line is determined according to the central line rule of the S-shaped curved nozzle runner profile, and a Lee curve, a Witoshiba curve or a polynomial equation with different change degrees is adopted for control.
And step S3: determining the control rule of the change of the area of the section of the S-shaped caudal vertebra along the way: in order to better play a role in rectification and reduce the circumferential unevenness of the on-way pressure, the on-way section of the S-shaped tail cone is designed to be circular; the change of the on-way area is controlled by adopting a Wittonsisky curve or Lee curve rule, and the change of the on-way area of the flow passage without the inverse pressure gradient can be obtained.
And step S4: solving the area and the diameter of the round section along the way: and (4) according to the area change rule in the step (S3), under the condition that the areas of the front end and the rear end of the tail cone are known, solving the area and the diameter of the round section along the way.
Step S5: establishing a relation between the round section and the central line along the way;
step S6: and connecting contour lines of a plurality of sections along the way in a smooth transition manner to obtain the S-shaped tail cone profile.
Step S7: carrying out simulation analysis on the flow field of the S-shaped tail cone, evaluating the influence of the S-shaped tail cone on the bypass ratio, taking the bypass ratio as an improved design target, researching the flow field of the S-shaped tail cone, if the pressure unevenness of the section of the rear end of the S-shaped tail cone, which is perpendicular to the direction of the flow channel, is large, and the bypass ratio is still larger than the target bypass ratio, continuing to adjust the offset distance of the S-shaped tail cone, and when the offset distance of the S-shaped tail cone is adjusted, the offset distance of the S-shaped tail cone is one fourth to one half of the diameter of the front end of the tail cone.
Step S8: and redesigning the S-shaped tail cone according to the improved direction in the step S7 and carrying out simulation evaluation until the bypass ratio of the S-shaped bent spray pipe meets the design requirement, wherein the error of the improved bypass ratio compared with the S-shaped bent spray pipe before replacement is within 0.5% to be considered as meeting the design requirement.
Specifically, in this embodiment, in step S2, the variation law of the centerline of the S-shaped tail cone is controlled by using a Lee curve of a slow-rapid equivalent type, and the control formula is as follows:
Figure BDA0003854286760000051
in the formula: in the formula, x i 、y i Respectively an x coordinate and a y coordinate at the ith point of the central line; y is 0 Represents the centerline initial y-coordinate; delta Y j Representing the inlet-outlet offset of the central line, namely the eccentricity Delta S of the section along the way; l is j The axial overall length of the central line of the caudal vertebra.
Optionally, in step S2, the change rule of the central line of the S-shaped tail cone is controlled by a Lee curve with a slow front and a fast rear, and the control formula is as follows:
Figure BDA0003854286760000061
in the formula: in the formula, x i 、y i Respectively an x coordinate and a y coordinate at the ith point of the central line; y is 0 Represents the centerline initial y-coordinate; delta Y j Representing the inlet-outlet offset of the central line, namely the eccentricity Delta S of the section along the way; l is j Is the axial total length of the central line of the caudal vertebra.
Optionally, in step S2, the change rule of the central line of the S-shaped tail cone is controlled by a front sharp curve and a rear gentle curve, and the control formula is as follows:
Figure BDA0003854286760000062
in the formula: in the formula, x i 、y i Respectively an x coordinate and a y coordinate at the ith point of the central line; y is 0 Represents the centerline initial y-coordinate; delta Y j Representing the inlet-outlet offset of the central line, namely the eccentricity Delta S of the section along the way; l is j The axial overall length of the central line of the caudal vertebra.
In this embodiment, in step S5, the on-way center line determined in step S2 is passed through and perpendicular to the section centers determined in step S4 according to the following formula:
z′ k ＝z k ；
x′ k ＝(x k -x i )·cosα+(y k -y i )·sinα+x i ；
y′ k ＝-(x k -x i )·sinα+(y k -y i )·cosα+y i ；
wherein the centerline is in the xy plane, (x) i ,y i ) Denotes the coordinates of the centerline at point i, and α denotes the point on the centerline (x) i ,y i ) At the end cone along the way circular section, the angle of rotation around the z-axis (x) k ,y k ,z k ) Is the coordinate before rotation (x' k ,y' k ,z' k ) The coordinates after rotation.
Fig. 3 is a graph showing a comparison between the distribution of mach numbers on the symmetrical surfaces of the conical tail cone of the prior art and the S-shaped tail cone of the present invention when they are installed in the S-bend nozzle. The drawing is composed of the following parts: the improved S-shaped spray pipe comprises an S-shaped spray pipe 10, a mixer 20, a conical tail cone 30 before improvement and an S-shaped tail cone 40 after improvement. It can be clearly seen in the figure that flow separation occurs at the downstream of the conical tail cone 30 before the improvement, the pressure unevenness of the section at the rear end of the conical tail cone 30 is large, the rear end of the improved S-shaped tail cone 40 has no flow separation, the unevenness is obviously reduced, the bypass ratio of the S-shaped bent nozzle with the improved tail cone is increased by 10% compared with that before the S-shaped bent nozzle is replaced, and the bypass ratio of the S-shaped bent nozzle with the improved S-shaped tail cone 40 is increased by only 0.2% compared with that before the S-shaped bent nozzle is replaced. The S-shaped inner cone is applied, the airflow flowing cross section is more uniform, the pressure unevenness of the cross section at the rear end of the S-shaped inner cone is reduced, the influence on the distribution of the airflow of the inner culvert and the outer culvert is smaller, and finally the culvert ratio meets the design requirement.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, and all modifications and equivalents made by the contents of the present specification and drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.

Claims (10)

1. A tail cone design method for improving matching performance of an S-shaped spray pipe of an aircraft engine is characterized in that a tail cone is of an S-shaped structure, and the S-shaped tail cone design method comprises the following steps:
step S1: determining a constraint parameter: except the eccentricity Delta S of the section along the way, the other parameters are consistent with the structural parameters of the improved front tail cone;
step S2: determining the change rule of the central line of the on-way section of the S-shaped caudal vertebra: determining the change rule of the center line of the S-shaped tail cone according to the center line rule of the molded surface of the S-shaped spray pipe flow passage, and controlling by adopting Lee curves, witoshib curves or polynomial equations with different change degrees;
and step S3: determining a control rule of the change of the area of the section of the S-shaped caudal vertebra along the way;
and step S4: solving the area and the diameter of the round section along the way: according to the area change rule in the step S3, under the condition that the areas of the front end and the rear end of the tail cone are known, the area and the diameter of the round section along the way are solved;
step S5: establishing a relation between the round section and the central line along the way;
step S6: and connecting contour lines of a plurality of sections along the way in a smooth transition manner to obtain the S-shaped tail cone profile.
2. The method for designing the tail cone for improving the matching performance of the S-shaped spray pipe of the aircraft engine as claimed in claim 1, wherein the method comprises the following steps: in step S1, the constraint parameters include maximum constraints of the circular cross-sectional area Ai and the diameter Di at the front end of the tail cone, the eccentricity Δ S of the section along the way, the total axial length, and the circular cross-sectional area Ao and the diameter Do at the rear end of the tail cone.
3. The method for designing the tail cone for improving the matching performance of the S-shaped spray pipe of the aircraft engine as claimed in claim 1, wherein the method comprises the following steps: in step S2, the change rule of the central line of the S-shaped tail cone is controlled by a slow-fast equivalent Lee curve, and the control formula is as follows:
Figure FDA0003854286750000011
in the formula: in the formula, x i 、y i Respectively an x coordinate and a y coordinate at the ith point of the central line; y is 0 Represents the centerline initial y-coordinate; Δ Y j Representing the inlet-outlet offset of the central line, namely the eccentricity Delta S of the section along the way; l is j Is the axial total length of the central line of the caudal vertebra.
4. The method for designing the tail cone for improving the matching performance of the S-shaped spray pipe of the aircraft engine as claimed in claim 1, wherein the method comprises the following steps: in step S2, the change rule of the central line of the S-shaped tail cone is controlled by a Lee curve with a slow front and a sharp rear, and the control formula is as follows:
Figure FDA0003854286750000021
in the formula: in the formula, x i 、y i Respectively an x coordinate and a y coordinate at the ith point of the central line; y is 0 Represents the centerline initial y-coordinate; delta Y j Representing the inlet-outlet offset of the central line, namely the eccentricity Delta S of the section along the way; l is j The axial overall length of the central line of the caudal vertebra.
5. The method for designing the tail cone for improving the matching performance of the S-shaped spray pipe of the aircraft engine as claimed in claim 1, wherein the method comprises the following steps: in step S2, the change rule of the central line of the S-shaped tail cone is controlled by a front sharp and rear gentle Lee curve, and the control formula is as follows:
Figure FDA0003854286750000022
in the formula: in the formula, x i 、y i Respectively an x coordinate and a y coordinate at the ith point of the central line; y is 0 Represents the centerline initial y-coordinate; delta Y j Representing the inlet-outlet offset of the central line, namely the eccentricity Delta S of the section along the way; l is j Is the axial total length of the central line of the caudal vertebra.
6. The method for designing the tail cone for improving the matching of the S-shaped nozzle of the aircraft engine as claimed in claim 1, wherein the method comprises the following steps: in step S3, the section of the S-shaped tail cone along the way is designed to be circular; the change along the path area is controlled by adopting a Vitosynsky curve or Lee curve rule.
7. The method for designing the tail cone for improving the matching performance of the S-shaped spray pipe of the aircraft engine as claimed in claim 1, wherein the method comprises the following steps: in step S5, the centerline of the path determined in step S2 is passed through and perpendicular to the center of the cross-sections of the path determined in step S4 according to the following formula:
z′ k ＝z k ；
x′ k ＝(x k -x i )·cosα+(y k -y i )·sinα+x i ；
y′ k ＝-(x k -x i )·sinα+(y k -y i )·cosα+y i ；
wherein the centerline is in the xy plane, (x) i ,y i ) Denotes the coordinates of the centerline at point i, and α denotes the point on the centerline (x) i ,y i ) At the end cone along the way circular section, the angle of rotation around the z-axis (x) k ,y k ,z k ) Is the coordinate before rotation, (x' k ,y' k ,z' k ) The coordinates after rotation.
8. The method for designing the tail cone for improving the matching performance of the S-shaped spray pipe of the aircraft engine as claimed in claim 1, wherein the method comprises the following steps: further comprising step S7: and carrying out simulation analysis on the flow field of the S-shaped bent spray pipe, and evaluating the influence of the S-shaped tail cone on the bypass ratio.
9. The method for designing the tail cone for improving the matching of the S-shaped nozzle of the aircraft engine as recited in claim 8, wherein: in step S7, if the pressure unevenness of the rear end cross section of the S-shaped end cone perpendicular to the flow channel direction is large, and the bypass ratio is still larger than the target bypass ratio, the offset distance of the S-shaped end cone needs to be continuously adjusted.
10. The method for designing the tail cone for improving the matching of the S-bend nozzle of the aircraft engine as recited in claim 9, wherein: the offset distance of the S-shaped tail cone is one fourth to one half of the diameter of the front end of the tail cone.
CN202211143100.0A 2022-09-20 2022-09-20 Tail cone design method for improving matching performance of S-shaped spray pipe of aircraft engine Pending CN115455597A (en)

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