CN115114736B - Bird strike resistant design method for front edge of fan rotor blade of aero-engine - Google Patents
Bird strike resistant design method for front edge of fan rotor blade of aero-engine Download PDFInfo
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- CN115114736B CN115114736B CN202210895279.9A CN202210895279A CN115114736B CN 115114736 B CN115114736 B CN 115114736B CN 202210895279 A CN202210895279 A CN 202210895279A CN 115114736 B CN115114736 B CN 115114736B
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- 238000004088 simulation Methods 0.000 claims abstract description 9
- 230000008719 thickening Effects 0.000 claims description 9
- 238000005457 optimization Methods 0.000 claims description 3
- 238000013435 augmentation design Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Abstract
The application provides a bird strike resistant design method for the front edge of a fan rotor blade of an aeroengine, which comprises the following steps: bird strike simulation analysis or test is carried out on the fan rotor blade after bird strike, so that the damage condition of the front edge of the fan rotor blade after bird strike is obtained; evaluating the damage condition of the front edge of the fan rotor blade after bird strike; determining weak parts according to the damage evaluation result; extracting a blade front edge damage deformation area and parameters of the thin part; extracting the thickness and the distribution curve of the thickness within the range of the loss deformation area; increasing the thickness in the range of the loss deformation region; performing bird strike simulation analysis on the improved fan rotor blade to obtain the damage condition of the front edge of the blade after bird strike; if the damage of the front edge of the blade does not occur beyond the damage required by the design, the bird strike resistant design of the front edge of the blade is finished; if the damage of the front edge of the blade exceeds the damage of the design requirement, the design requirement of aerodynamic performance is reduced, and the thickness of the front edge area of the blade is increased until the design requirement is met.
Description
Technical Field
The application belongs to the technical field of aeroengines, and particularly relates to a bird strike resistant design method for the front edge of a fan rotor blade of an aeroengine.
Background
Bird strike of the aero-engine is always a serious accident seriously endangering the flight safety of an aircraft, after the bird strike of the aero-engine, the bird can strike the fan rotor blade at the inlet of the engine, so that the front edge of the impacted position of the fan rotor blade is sunken, deformed, torn and cracked, broken, and the like, thereby causing the thrust of the engine to be reduced, sometimes causing secondary damage to the engine, even causing non-contained serious accidents, and the bird strike resistance of the fan blade of the aero-engine becomes an important assessment index for the design of the engine.
Bird strike damage is a major concern in the leading edge of the blade, and therefore the leading edge bird strike protection design is one of the most important aspects of the blade bird strike protection design.
For bird strike resistant design of the blade leading edge, the prior art realizes the design by adjusting the angle of the blade leading edge, but the method is generally only suitable for the preliminary design stage of the blade; and the adjustment of the angle of the front edge of the blade has a large influence on the aerodynamic performance of the blade, and is not suitable for engines with high aerodynamic requirements.
Disclosure of Invention
It is an object of the present application to provide an aircraft engine fan rotor blade leading edge bird strike protection design method to address or mitigate at least one problem in the background art.
The technical scheme of the application is as follows: a method of bird strike protection design for an aircraft engine fan rotor blade leading edge, the method comprising:
s1, performing bird strike simulation analysis or test on the fan rotor blade according to all bird strike states to be evaluated, and obtaining the damage condition of the front edge of the fan rotor blade after bird strike under all evaluation states;
s2, evaluating damage conditions of the front edge of the rotor blade of the fan after bird strike, and ending the bird strike resistant design of the front edge of the blade if the damage of the front edge of the blade does not occur beyond the damage required by the design; if the damage of the front edge of the blade exceeds the damage required by the design, entering the next step;
s3, determining a weak part of the front edge of the blade for bird strike resistance according to the damage evaluation results of the front edge of the blade after bird strike in all evaluation states, and determining the state of the maximum bird strike damage of the weak part in all evaluation states and the corresponding damage condition;
s4, extracting a damaged deformation area of the blade and parameters of the damaged deformation area according to the state of the biggest bird strike damage and the corresponding damage condition;
s5, extracting the thickness and the distribution curve of the thickness within the range of the damage deformation area;
s6, increasing the thickness in the damaged deformation area range, and then performing pneumatic integral fairing and pneumatic optimization design;
s7, performing bird strike simulation analysis on the optimized fan rotor blade under all evaluation states to obtain blade front edge damage conditions after bird strike under all evaluation states;
s8, evaluating the damage condition of the front edge of the blade under all the evaluation states obtained in the step 7, and ending the bird strike resistant design of the front edge of the blade if the damage of the front edge of the blade does not occur beyond the damage required by the design; if the damage of the front edge of the blade exceeds the damage of the design requirement, the design requirement of aerodynamic performance is reduced, the thickness of the front edge area of the blade is increased, and the steps 3 to 8 are repeated until the design requirement is met.
Further, the blade leading edge damage includes dishing, tearing, and chipping.
Further, the damage deformation parameters comprise a radial area H for concavely deforming the front edge of the blade and a longitudinal area L along the blade profile.
Further, the thickness in the damaged deformation area range is h ij In the formula, i represents the radial position number in the radial height range, and j represents the vane direction position number in the vane direction range.
Further, the damaged deformed area range extracted in step S5 is increased by a predetermined value from the damaged deformed area of the blade extracted in step S4.
Further, the predetermined value is 10%.
Further, the process of increasing the thickness in the damaged deformation area comprises the following steps:
a) If the blade with similar structure and bird strike resistance meeting the requirement is provided, the thickness h of the corresponding area range of the blade is referred to ij Performing thickening design;
b) If the blade has no similar structure and the bird strike resistance meets the requirement, firstly, the thickness h of the forefront edge is thickened on the basis of ensuring the design of the blade form fairing and the design of the aerodynamic performance ij And then, under the condition of ensuring the fairing design and the aerodynamic performance design of the blade profile, the thickness h of the range of the deformation area of the weak part extracted in the step S5 is calculated according to the maximum thickening limit ij Thickening is carried out.
The bird strike resistant design method for the front edge of the rotor blade of the aeroengine fan can be suitable for bird strike resistant design of each stage of the blade, and is small in structural improvement and small in influence on the overall structure and performance of the blade.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following description will briefly refer to the accompanying drawings. It will be apparent that the figures described below are only some embodiments of the present application.
FIG. 1 is a flow chart of a method of bird strike protection design for a leading edge of a fan rotor blade according to the present application.
Fig. 2 is a schematic diagram of parameters of an extracted blade damage deformation region in the present application.
Fig. 3 is a schematic view of the thickness in the range of the extraction deformation region in the present application.
Detailed Description
In order to make the purposes, technical solutions and advantages of the implementation of the present application more clear, 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 order to overcome the problems in the background art, the application provides a new blade bird strike resistant design method, which can be suitable for each design stage of an engine blade and can improve the bird strike resistant capability of the blade under the condition of less influence on the aerodynamic performance, the strength and the like.
As shown in fig. 1, the bird strike resistant design method for the front edge of the fan rotor blade of the aeroengine specifically comprises the following steps:
s1) blade damage analysis after bird strike.
Aiming at all bird strike states needing to be evaluated, such as bird strike during take-off or bird strike during flat flight, simulation analysis or test of bird strike of the fan rotor blade is carried out, and blade damage conditions after bird strike in all evaluation states are obtained.
S2) evaluating the front edge damage.
According to the damage condition of the blade obtained by the simulation or test of the fan rotor blade performed in the step S1, the damage condition of the front edge of the fan rotor blade is evaluated, and typical damage of the front edge of the blade comprises sinking, tearing and chipping.
If the damage of the front edge of the blade is small, the damage exceeding the design requirement does not occur, and the blade is directly ended; if the damage of the front edge of the blade exceeds the damage required by the design, the next step of design is carried out.
S3) determining the bird strike resistant weak part of the front edge.
In step S2, according to the blade damage evaluation conditions after bird strike in all evaluation states, a weak part of the blade leading edge against bird strike is determined, and the state of the weak part with the biggest bird strike damage in all evaluation states and the corresponding damage condition are determined.
S4) extracting damage deformation of the weak part.
Aiming at the maximum damage condition of the weak part of the front edge determined in the step S3, the damage deformation of the blade is extracted, and parameters to be extracted are shown in the figure 2, wherein the parameters comprise a radial area H where the front edge is concavely deformed and a longitudinal area L along the blade profile.
S5) extracting the thickness distribution parameters of the weak areas.
Extracting the thickness h in the deformation region range for the leading edge weak-resistant part determined in the step S3 ij And distribution curves, as shown in the figure3, wherein i denotes an inner radial position number in the radial height range, j denotes a airfoil direction position number in the airfoil direction range, and the extracted area is increased by a predetermined value, which may be 10%, for example, from the leading edge concave deformation area extracted in step S4.
S6) optimally designing the thickness distribution of the weak part.
Blade thickness h for the range of the weak portion deformation region extracted in step S5 ij And (5) performing augmentation design, and then performing pneumatic integral fairing and pneumatic optimization.
Thickness h ij The augmentation design process includes:
a) If the blade has a similar structure and meets the requirements of bird strike resistance, the thickness h of the corresponding area of the blade can be referred to ij Performing thickening design;
b) If no referenceable design is available, the following method can be used: firstly, the thickness h of the forefront edge is thickened on the basis of ensuring the fairing design and the aerodynamic performance design of the blade profile ij And then, under the condition of ensuring the fairing design and the aerodynamic performance design of the blade profile, the thickness h of the range of the deformation area of the weak part extracted in the step 5 is calculated according to the maximum thickening limit ij Thickening is carried out.
S7) improving post-leaf bird strike analysis.
And carrying out bird strike simulation analysis on the optimized blades in all evaluation states to obtain the damage condition of the front edge of the blades after bird strike in all evaluation states.
S8) leading edge damage assessment.
Evaluating the damage condition of the front edge of the blade under all the evaluation states obtained in the step S7, and ending the bird strike resistant design of the front edge of the blade if the damage of the front edge of the blade is smaller and the damage exceeding the design requirement does not occur; and if the damage of the front edge of the blade exceeds the damage of the design requirement, repeating the steps S3 to S8 until the design requirement is met.
Wherein. And when the step S6 from the step S3 to the step S8 is repeated, the aerodynamic performance design requirement is reduced, the thickness of the front edge area of the blade is further increased, and the bird strike resistance of the blade is improved.
The bird strike resistant design method for the front edge of the rotor blade of the aeroengine fan can be suitable for bird strike resistant design of each stage of the blade, and is small in structural improvement and small in influence on the overall structure and performance of the blade.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in 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 (6)
1. A method of bird strike protection design for a leading edge of a fan rotor blade of an aircraft engine, the method comprising:
s1, performing bird strike simulation analysis or test on the fan rotor blade according to all bird strike states to be evaluated, and obtaining the damage condition of the front edge of the fan rotor blade after bird strike under all evaluation states;
s2, evaluating damage conditions of the front edge of the rotor blade of the fan after bird strike, and ending the bird strike resistant design of the front edge of the blade if the damage of the front edge of the blade does not occur beyond the damage required by the design; if the damage of the front edge of the blade exceeds the damage required by the design, entering the next step;
s3, determining a weak part of the front edge of the blade for bird strike resistance according to the damage evaluation results of the front edge of the blade after bird strike in all evaluation states, and determining the state of the maximum bird strike damage of the weak part in all evaluation states and the corresponding damage condition;
s4, extracting a damaged deformation area of the blade and parameters of the damaged deformation area according to the state of the biggest bird strike damage and the corresponding damage condition;
s5, extracting the thickness and the distribution curve of the thickness within the range of the damage deformation area;
s6, increasing the thickness in the damaged deformation area range, and then performing pneumatic integral fairing and pneumatic optimization design;
s7, performing bird strike simulation analysis on the optimized fan rotor blade under all evaluation states to obtain blade front edge damage conditions after bird strike under all evaluation states;
s8, evaluating the damage condition of the front edge of the blade under all the evaluation states obtained in the step 7, and ending the bird strike resistant design of the front edge of the blade if the damage of the front edge of the blade does not occur beyond the damage required by the design; if the damage of the front edge of the blade exceeds the damage of the design requirement, reducing the design requirement of aerodynamic performance, increasing the thickness of the front edge area of the blade, and repeating the steps 3 to 8 until the design requirement is met, wherein the process of increasing the thickness in the damaged deformation area comprises the following steps:
a) If the blade with similar structure and bird strike resistance meeting the requirement is provided, the thickness h of the corresponding area range of the blade is referred to ij Performing thickening design;
b) If the blade has no similar structure and the bird strike resistance meets the requirement, firstly, the thickness h of the forefront edge is thickened on the basis of ensuring the design of the blade form fairing and the design of the aerodynamic performance ij And then, under the condition of ensuring the fairing design and the aerodynamic performance design of the blade profile, the thickness h of the range of the deformation area of the weak part extracted in the step S5 is calculated according to the maximum thickening limit ij Thickening is carried out.
2. The method of claim 1, wherein said blade leading edge damage comprises pitting, tearing, chipping.
3. The aircraft engine fan rotor blade leading edge bird strike protection design method of claim 1, wherein the damage deformation parameters include a radial region H of blade leading edge dent deformation and a length region along the airfoil L.
4. A method of bird strike protection design for an aircraft engine fan rotor blade leading edge according to claim 3 wherein the thickness in the region of the damage deformation zone is h ij Wherein i represents the radial position number in the radial height range, and j represents the vane profile in the vane profile direction rangeDirection position number.
5. The method for bird strike protection design of an aircraft engine fan rotor blade leading edge of claim 4, wherein the range of damage deformation areas extracted in step S5 is increased by a predetermined value over the damage deformation areas of the blade extracted in step S4.
6. The aircraft engine fan rotor blade leading edge bird strike protection design method of claim 5, wherein said predetermined value is 10%.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210895279.9A CN115114736B (en) | 2022-07-26 | 2022-07-26 | Bird strike resistant design method for front edge of fan rotor blade of aero-engine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210895279.9A CN115114736B (en) | 2022-07-26 | 2022-07-26 | Bird strike resistant design method for front edge of fan rotor blade of aero-engine |
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| CN115114736A CN115114736A (en) | 2022-09-27 |
| CN115114736B true CN115114736B (en) | 2024-03-19 |
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| CN101182784A (en) * | 2007-12-03 | 2008-05-21 | 南京航空航天大学 | Ultrasound profile applied to aerial engine fan/compressor rotor and design method thereof |
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Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4557397B2 (en) * | 2000-09-05 | 2010-10-06 | 本田技研工業株式会社 | Blade shape design method and information medium |
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| CN101182784A (en) * | 2007-12-03 | 2008-05-21 | 南京航空航天大学 | Ultrasound profile applied to aerial engine fan/compressor rotor and design method thereof |
| CN109263861A (en) * | 2017-07-18 | 2019-01-25 | 中国航空工业集团公司西安飞机设计研究所 | The leading edge of a wing covering that the anti-bird of wave transparent is hit |
| CN109543252A (en) * | 2018-11-05 | 2019-03-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of security of system appraisal procedure hit based on bird |
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