Aero-engine blade damage quantification evaluation method

Abstract

The application provides an aero-engine blade damage quantification evaluation method, the aero-engine blade comprises multiple stages, each stage has multiple blades, the damage deformation position and the damage deformation size of the deformed blade of each blade are measured; the damage deformation position and the damage deformation size of each blade are quantitatively processed to obtain the damage deformation quantification total parameter S of each blade; a damage deformation model of the blade is established based on the damage deformation position and the damage deformation size; a plurality of single damage deformation models are combined to form a one-stage rotor blade damage deformation model, the damage deformation position and the damage deformation size of the blade are changed to obtain a multi-stage rotor blade damage deformation model, aerodynamic simulation is performed on each rotor blade damage deformation model to obtain the engine performance parameter of each rotor blade damage deformation model, and a damage influence curve diagram of the engine performance parameter and the damage deformation quantification total parameter S of each stage blade is established. 总 ​

Description

Technical Field

[0001] This application belongs to the field of aero-engine testing, and specifically relates to a method for quantitative evaluation of aero-engine blade damage. Background Technology

[0002] During flight, aircraft engines may ingest foreign objects such as ice or birds, which can damage the engine's rotating blades. To assess the impact of blade damage on engine operation and safety, it is necessary to measure and record the damage. Currently, the assessment of blade damage mainly relies on damage mode identification, measurement of the damaged area, recording of the damaged area's dimensions, determination of maintenance standards based on engineering development experience, and determination of whether the blade needs repair or continues to be used based on the size of the damage.

[0003] Current technology for identifying blade damage only addresses a single damaged blade, while foreign objects typically damage multiple blades. There is currently no clear method for assessing the impact of multiple damaged blades on engine operation and safety. Summary of the Invention

[0004] To address the aforementioned issues, this application provides a method for quantitatively evaluating damage to aero-engine blades. Step S1: The aero-engine blade comprises multiple stages, each stage having multiple blades. The location and magnitude of damage deformation of each blade are measured.

[0005] Step S2: Quantify the location and magnitude of damage and deformation for each blade to obtain the total quantitative parameter S of damage and deformation for each blade.

[0006] Step S3: Based on the location and magnitude of damage and deformation, establish a damage and deformation model for each blade;

[0007] Step S4: Combine multiple damage and deformation models to form a single-level blade damage and deformation model. By changing the location and magnitude of damage and deformation on the blade, multiple levels of blade damage and deformation models can be obtained.

[0008] Step S5: Perform aerodynamic simulation on the damage and deformation model of each stage blade to obtain the engine performance parameters of each stage blade damage and deformation model, and establish the engine performance parameters and the total quantitative parameter S of damage and deformation of each stage blade. 总 The damage effect curve is shown, where the total parameter S for deformation quantification at each damage level is... 总 The total parameter S of the blade damage deformation quantification is obtained from the calculation.

[0009] Preferably, the location of the damage deformation is the distance R from the point of maximum deformation to the engine axis; the magnitude of the damage deformation includes: the deformation height D of the point of maximum deformation along the vertical airflow direction, and the radial range L of the blade deformation area.

[0010] Preferably, the method for calculating the total damage deformation quantification parameter S for each blade is as follows:

[0011] S = R·L·D.

[0012] Preferably, the total parameter S for quantifying damage and deformation of each stage of the blade is... 总 The calculation method is as follows:

[0013] S 总 =S 1+ S 2+ S3+……

[0014] S1, S2, S3... are the total parameters for quantifying the damage and deformation of multiple blades.

[0015] Preferably, after establishing the damage effect curve, a whole engine blade damage test is conducted, and the damage effect curve is calibrated through the whole engine blade damage test.

[0016] Preferably, the method for calibrating the damage influence curve of the damaged blades in the whole engine through blade-mounted test specifically includes: measuring the location and magnitude of damage deformation of the actually damaged blades; obtaining multiple different total quantitative parameters S of blade damage deformation; combining the measured blades into multiple levels of blades; and calculating the total quantitative parameters S of damage deformation for each level of blade. 总 Furthermore, whole-machine blade loading tests were conducted on multiple stages of blades to obtain the true total quantitative parameter S of damage and deformation of each stage of blades. 总 The corresponding engine performance parameters were also determined, and the damage effect curve was calibrated.

[0017] Preferably, the engine performance parameters include engine thrust and engine margin. The advantages of this application include: the present invention, through damage classification and damage area quantification methods, can quantify the impact parameters of multiple damaged blades on engine use and safety; the present invention can quantitatively assess the impact of blade damage on engine performance. Attached Figure Description

[0018] Figure 1 This is a schematic diagram showing the distance R from the point of maximum deformation to the engine axis;

[0019] Figure 2 This is a schematic diagram showing the radial dimension L of the blade deformation region;

[0020] Figure 3This is a schematic diagram of the deformation height D of the point with the maximum deformation along the vertical airflow direction;

[0021] Figure 4 The damage effect curve S 总 With margin curve;

[0022] Figure 5 The damage effect curve S 总 Compared with the engine thrust curve. Detailed Implementation

[0023] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. 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 only some, not all, of the embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without inventive effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0024] Blade damage primarily manifests in four forms: cracks, tears, spalling, and deformation. The first three types of damage constitute structural failure of the blade, requiring immediate replacement in aero-engines and rendering them unusable; therefore, an assessment of the damage severity is unnecessary. Deformed blades, however, generally do not expand their damaged area, resulting in minimal impact on structural safety, and can therefore continue to be used under certain conditions.

[0025] Although deformed blades can still be used, the deformed area will cause uneven flow field, affecting the aerodynamic stability of the engine, and in severe cases, even causing engine surge. Therefore, a method is needed to quantify the impact of blade deformation damage on the engine.

[0026] A method for quantitative evaluation of damage to aero-engine blades, step S1: the aero-engine blade consists of multiple stages, each stage has multiple blades, and the location and magnitude of damage deformation of each blade are measured.

[0027] Step S2: Quantify the location and magnitude of damage and deformation of each blade to obtain the total quantitative parameter S of damage and deformation for each blade. That is, the degree of damage of each damaged blade is represented by a parameter, namely the total quantitative parameter S of damage and deformation.

[0028] Step S3: Based on the location and magnitude of damage and deformation, establish a damage and deformation model for each blade. Model the blades that have been measured to obtain the damage and deformation model for each blade.

[0029] Step S4: Combine multiple damage and deformation models to form a level of blade damage and deformation model. By changing the location and magnitude of damage and deformation of the blade, multiple levels of blade damage and deformation models can be obtained. In other words, the modeling of each blade can obtain the desired damage form by inputting different parameters. By changing these parameters, multiple blades with different degrees of damage can be obtained. Assemble multiple blades to form a level of blade, which in turn forms a complete fan.

[0030] Step S5: Perform aerodynamic simulation on the damage and deformation model of each stage blade to obtain the engine performance parameters of each stage blade damage and deformation model, and establish the engine performance parameters and the total quantitative parameter S of damage and deformation of each stage blade. 总 The damage effect curve is shown, where the total parameter S for deformation quantification at each damage level is... 总 The total parameter S of the blade damage deformation quantification is obtained from the calculation.

[0031] In some optional embodiments, the location of the damage deformation is the distance R from the point of maximum deformation to the engine axis; the magnitude of the damage deformation includes: the deformation height D of the point of maximum deformation along the vertical airflow direction, and the radial range L of the blade deformation area, such as... Figures 1-3 As shown.

[0032] In some alternative implementations, the total damage deformation quantification parameter S for each blade is calculated as follows:

[0033] S = R·L·D.

[0034] In some alternative implementations, the total parameter S for quantifying damage and deformation of each stage of the blade is... 总 The calculation method is as follows:

[0035] S 总 =S 1+ S 2+ S3+……

[0036] S1, S2, S3... are the total parameters for quantifying the damage and deformation of multiple blades.

[0037] In some alternative implementations, after establishing the damage effect curve, a whole engine blade damage test is conducted, and the damage effect curve is calibrated through the whole engine blade damage test.

[0038] In some optional embodiments, the method for calibrating the damage effect curve of the damaged blades in the whole engine through blade-mounted test specifically includes: measuring the location and magnitude of damage deformation of the actually damaged blades; obtaining multiple different total parameters S for quantifying blade damage deformation; combining the measured blades into multiple levels of blades; and calculating the total parameters S for quantifying damage deformation of each level of blade. 总 Furthermore, whole-machine blade loading tests were conducted on multiple stages of blades to obtain the true total quantitative parameter S of damage and deformation of each stage of blades. 总 And its corresponding engine performance parameters, and calibrate the damage effect curve, such as Figures 4-5 As shown.

[0039] In some alternative implementations, the engine performance parameters include engine thrust and engine margin.

[0040] The advantages of this application include: the present invention can quantify the impact parameters of multiple damaged blades on engine use and safety through damage classification and damage area quantification methods; the present invention can quantitatively evaluate the impact of blade damage on engine performance.

[0041] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A method for quantitatively evaluating damage to aero-engine blades, characterized in that: Step S1: The aero-engine blade consists of multiple stages, each stage having multiple blades. The location and magnitude of damage and deformation of each blade are measured. Step S2: Quantify the location and magnitude of damage and deformation for each blade to obtain the total quantitative parameter S of damage and deformation for each blade. Step S3: Based on the location and magnitude of damage and deformation, establish a damage and deformation model for each blade; Step S4: Combine multiple damage and deformation models to form a single-level blade damage and deformation model. By changing the location and magnitude of damage and deformation on the blade, multiple levels of blade damage and deformation models can be obtained. Step S5: Perform aerodynamic simulation on the damage and deformation model of each stage blade to obtain the engine performance parameters of each stage blade damage and deformation model, and establish the engine performance parameters and the total quantitative parameter S of damage and deformation of each stage blade. 总 The damage effect curve is shown, where the total parameter S for deformation quantification at each damage level is... 总 The total parameter S of the blade damage deformation quantification is obtained from the calculation.

2. The method for quantitative evaluation of aero-engine blade damage as described in claim 1, characterized in that, The location of the damage and deformation is the distance R from the point of maximum deformation to the engine axis; The damage and deformation magnitude includes: the deformation height D of the point with the maximum deformation along the vertical airflow direction, and the radial range L of the blade deformation area.

3. The method for quantitative evaluation of aero-engine blade damage as described in claim 2, characterized in that, The method for calculating the total damage deformation quantification parameter S for each blade is as follows: S=RLD.

4. The method for quantitative evaluation of aero-engine blade damage as described in claim 3, characterized in that, The total parameter S for quantifying damage and deformation of each stage of the blade 总 The calculation method is as follows: S 总 =S1+S2+S3+…… S1, S2, S3... are the total parameters for quantifying the damage and deformation of multiple blades.

5. The method for quantitative evaluation of aero-engine blade damage as described in claim 1, characterized in that, After establishing the damage effect curve, a blade-attached test of the damaged engine is conducted, and the damage effect curve is calibrated through the blade-attached test of the damaged engine.

6. The method for quantitative evaluation of aero-engine blade damage as described in claim 5, characterized in that, The method for calibrating the damage effect curve of the damaged blades in the whole engine through blade-mounted test includes: measuring the location and magnitude of damage deformation of the actual damaged blades; obtaining multiple different total parameters S for quantifying blade damage deformation; combining the measured blades into multiple levels of blades; and calculating the total parameters S for damage deformation of each level of blade. 总 Furthermore, whole-machine blade loading tests were conducted on multiple stages of blades to obtain the true total quantitative parameter S of damage and deformation of each stage of blades. 总 The corresponding engine performance parameters were also determined, and the damage effect curve was calibrated.

7. The method for quantitative evaluation of aero-engine blade damage as described in claim 1, characterized in that, The engine performance parameters include the engine's thrust and engine margin.

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