Compressor stator blade coping method

Abstract

The invention relates to the technical field of aero-engines, and discloses a gas compressor stator blade coping method which comprises the following steps: quantifying the assembly tolerance of each stage of stator blade and rotor blade by establishing a gas compressor axial fit dimension chain model; determining dimensional tolerance based on the drawing design size and the component actual measurement size; the grinding amount of the front edge or the tail edge of the stator blade is determined through stator blade and rotor blade axial gap closed ring tolerance dimension chain analysis; the optimal grinding parameters of the front edge or the tail edge of the stator blade are determined by combining the pneumatic simulation model and the structural mechanical model; and the front edge or the tail edge of the stator blade is ground according to the optimal grinding parameters. Based on a multidisciplinary collaborative quantitative design method, the pneumatic simulation model and the structural mechanical model are combined, the grinding parameters are determined through collaborative optimization, the grinding performance is guaranteed, and the requirements for the pneumatic performance, the structural strength and the axial clearance safety after the front edge or the tail edge of the stator blade is ground are met.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engines, and in particular to a method for grinding compressor stator blades. Background Art

[0002] In the compressor of an aircraft engine, whether the axial clearance between the stator blades and the rotor blades can be precisely controlled directly affects the aerodynamic efficiency and safety of the aircraft engine. The axial clearance between the stator blades and the rotor blades includes: the axial clearance between the trailing edge of the rotor blade and the leading edge of the stator blade, and the axial clearance between the trailing edge of the stator blade and the leading edge of the rotor blade. In the prior art, the axial clearance between the stator blades and the rotor blades is generally ensured by grinding the stator blades, and the processing technology is complicated. The grinding amount of the stator blades is usually determined by empirical judgment or single-disciplinary simulation. It is difficult to accurately determine the grinding amount of the stator blades, resulting in aerodynamic losses and insufficient strength of the aircraft engine, and significantly increasing the risk of collision and wear between the rotor blades and the stator blades. Summary of the Invention

[0003] In view of this, the present invention provides a method for grinding compressor stator blades to solve the problem that when grinding the stator blades of the compressor, the grinding amount of the stator blades usually depends on experience judgment or single-disciplinary simulation, and it is difficult to accurately determine the grinding amount of the stator blades, resulting in aerodynamic loss and insufficient strength of the aircraft engine, and significantly increasing the risk of collision between the rotor blades and the stator blades.

[0004] The present invention provides a method for grinding compressor stator blades, comprising:

[0005] By establishing a compressor axial fit dimension chain model, the assembly tolerances of stator blades and rotor blades at each level are quantified. Based on the design dimensions in the drawings and the measured assembly dimension data of the components, the dimensional tolerance range of each component is determined. Through the axial clearance closed ring tolerance dimension chain analysis of the stator blades and rotor blades, the grinding amount of the leading or trailing edge of the stator blade is determined.

[0006] Determine the optimal grinding parameters for the leading edge or trailing edge of the stator blade by combining the aerodynamic simulation model and the structural mechanics model; the optimal grinding parameters are: optimal grinding modulus and optimal grinding area;

[0007] The leading edge or trailing edge of the stator blade is ground according to the optimal grinding parameters, and the axial clearance between the stator blade and the rotor blade is precisely controlled. Beneficial effect: This application adopts the above technical solution, based on a multidisciplinary collaborative quantitative design method, taking into account the influence of assembly tolerance on the axial clearance between the stator blade and the rotor blade, combining the aerodynamic simulation model with the structural mechanics model, and collaboratively optimizing to quickly determine the grinding parameters, accurately determine the grinding modulus, ensure the grinding performance, prevent over-grinding and under-grinding, and take into account the aerodynamic performance, structural strength and axial clearance safety requirements of the stator blade after the leading edge or trailing edge is ground, significantly reducing the risk of collision and wear between the rotor blade and the stator blade.

[0008] Optionally, combining the aerodynamic simulation model and the structural mechanics model to determine the optimal grinding parameters of the leading edge or the trailing edge of the stator blade includes:

[0009] The aerodynamic performance of the leading or trailing edge of the stator blade before and after grinding is simulated based on the aerodynamic simulation model to ensure that the aerodynamic performance of the stator blade after leading or trailing edge grinding meets the requirements;

[0010] Use structural mechanics models to analyze the stress distribution and deformation trend of the leading or trailing edge of the stator blade before and after grinding to ensure that the structural strength of the stator blade after grinding meets the requirements;

[0011] Through a multi-objective optimization algorithm, the grinding parameters are used as variables to balance aerodynamic performance and structural strength to obtain the optimal solution. The optimal solution is then subjected to a joint CFD simulation and finite element analysis to verify the aerodynamic and structural performance.

[0012] Optionally, the aerodynamic performance includes: stator total pressure recovery coefficient and compressor surge margin.

[0013] Optionally, the variation range of the aerodynamic performance is determined according to different grinding angles and different axial grinding lengths.

[0014] Optionally, balancing aerodynamic performance and structural strength refers to maximizing the static total pressure recovery coefficient and minimizing the maximum stress.

[0015] Optionally, grinding the leading edge or trailing edge of the stator blade according to the optimal grinding parameters includes:

[0016] Wax is poured into the tip flow channel area of the stator blade and solidified to form a support layer;

[0017] Grinding the blade tip flow channel, blade tip leading edge or blade tip trailing edge;

[0018] The wax is removed by heating. Beneficial Effects: This application adopts the above technical solution to reduce the number of clamping times, avoid the positioning errors and deformations of traditional step-by-step grinding, and significantly improve processing efficiency and processing accuracy.

[0019] Optionally, it also includes:

[0020] The tip leading edge or the tip trailing edge of the stator blade after grinding is strengthened. Beneficial effect: This application adopts the above technical solution to significantly improve the erosion and corrosion resistance of the tip leading edge or the tip trailing edge of the stator blade, enhance the deformation resistance, and improve the long-term safety and stability of the aircraft engine.

[0021] Optionally, the strengthening treatment includes:

[0022] Using laser shock peening equipment to perform local processing on the leading edge or trailing edge of the stator blade;

[0023] Inducing residual compressive stress on the surface of the leading edge or trailing edge of the stator blade by high-energy laser pulses;

[0024] Gradient heat treatment technology is used to control the temperature gradient distribution in the leading edge or trailing edge of the stator blade tip. Beneficial Effect: This application adopts the above technical solution to induce residual compressive stress through high-energy laser pulses to improve fatigue resistance; and gradient heat treatment technology is used to control the temperature gradient distribution, optimize the material microstructure, refine the grain size, and enhance the creep and fretting wear resistance.

[0025] Optionally, it also includes:

[0026] The effect of the strengthening treatment is verified by non-destructive testing.

[0027] Optionally, the non-destructive testing is ultrasonic testing. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the specific embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0029] Figure 1 Schematic diagram of the tolerance dimension chain of the axial clearance closed ring of the stator blades and the rotor blades provided in an embodiment of the present invention;

[0030] Figure 2 A schematic diagram of a partial cross-sectional structure of a single-stage compressor provided in an embodiment of the present invention;

[0031] Figure 3 A schematic diagram of the cross-sectional structure of a blade tip provided in an embodiment of the present invention;

[0032] Figure 4A schematic cross-sectional view of the grinding of the leading edge or trailing edge of a stator blade tip provided in an embodiment of the present invention;

[0033] Figure 5 The figure is a flow chart of a compressor stator blade grinding method provided in an embodiment of the present invention.

[0034] Description of reference numerals:

[0035] 1. Zero-stage guide vanes; 2. First-stage rotor blades; 3. First-stage stator blades; 4. Casing; 5. Stator blades; 6. Blade tip. DETAILED DESCRIPTION

[0036] To make the purpose, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without making creative efforts shall fall within the scope of protection of the present invention.

[0037] In the prior art, when grinding the tip flow path, leading edge, or trailing edge of a stator blade, a multi-step grinding process and multiple clamping and positioning steps are used, which significantly prolongs the processing cycle. This not only reduces processing efficiency but also easily introduces shape errors, resulting in extremely poor shape consistency. After grinding the stator blade, the tip leading edge or trailing edge of the stator blade is removed due to material removal, which weakens the erosion and corrosion resistance of the stator blade tip, seriously affecting the long-term safety and stability of the aircraft engine. For these reasons, the present application proposes a method for grinding compressor stator blades.

[0038] like Figures 1 to 5 A specific embodiment of the compressor stator blade grinding method shown includes the following steps:

[0039] S1. Quantify the assembly tolerances of the stator blades 5 and rotor blades at each level by establishing a compressor axial fit dimension chain model; determine the dimensional tolerance range of each component based on the design dimensions of the drawings and the measured assembly dimensional data of the components; determine the grinding amount of the leading or trailing edge of the stator blade 5 through the axial clearance closed loop tolerance dimension chain analysis between the stator blade 5 and the rotor blade.

[0040] like Figure 3 As shown, the stator blade 5 is installed in the casing 4, and the stator blade 5 includes: a blade tip 6, a blade body and a blade root. Figure 2 As shown, for a single-stage compressor, there are zero-stage guide vanes 1, first-stage rotor blades 2, and first-stage stator blades 3; the zero-stage guide vanes 1 and first-stage stator blades 3 are both stator blades 5, and the first-stage rotor blades 2 are rotor blades. Figure 1 The figure shows the tolerance dimension chain of the axial clearance closed ring of the stator blades 5 and the rotor blades, wherein L1 represents the tolerance dimension of the first ball bearing, L2 represents the tolerance dimension of the front grate ring, L3 represents the tolerance dimension of the zero-stage guide vane 1, L6 represents the tolerance dimension of the intake casing welding assembly, L7 represents the tolerance dimension of the front spring support, L8 represents the tolerance dimension of the stress ring, L9 represents the tolerance dimension of the second ball bearing, L10 represents the tolerance dimension of the first-stage rotor blade 2, L11 represents the tolerance dimension of the inner ring of the first-stage guide vane, L12 represents the tolerance dimension of the exhaust casing machine assembly, L13 represents the tolerance dimension of the axial flow casing, L14 represents the tolerance dimension of the adjustment pad, L15 represents the tolerance dimension of the zero-stage guide vane casing, C represents the axial clearance of the ball bearing, and Δ2 is the axial clearance between the inner ring of the first-stage stator blade 3 and the first-stage rotor blade 2. For example: in the compressor axial matching dimension chain model, the design requirement for the axial clearance from the trailing edge of the rotor blade to the leading edge of the stator blade 5 is 2.0±0.2mm. After the rotor blade is installed, the trailing edge position deviates backward by 0.3mm, and the leading edge position of the stator blade 5 deviates forward by 0.2mm. After actual clearance superposition analysis, the axial clearance from the trailing edge of the rotor blade to the leading edge of the stator blade 5 is 1.3mm~1.7mm, which exceeds the range of the axial clearance design requirement. The leading edge of the stator blade 5 needs to be ground, and the grinding amount is 0.3mm~0.5mm.

[0041] S2. Determine optimal grinding parameters for the leading edge or trailing edge of the stator blade 5 by combining the aerodynamic simulation model and the structural mechanics model; the optimal grinding parameters are: optimal grinding modulus and optimal grinding area.

[0042] S3. Grind the leading edge or the trailing edge of the stator blade 5 according to the optimal grinding parameters to accurately control the axial clearance between the stator blade 5 and the rotor blade.

[0043] Specifically, the method of combining the aerodynamic simulation model and the structural mechanics model to determine the optimal grinding parameters of the leading edge or the trailing edge of the stator blade 5 includes the following steps:

[0044] S21. Based on the aerodynamic simulation model, simulate the aerodynamic performance of the leading edge or trailing edge of the stator blade 5 before and after grinding to ensure that the aerodynamic performance of the stator blade 5 after the leading edge or trailing edge grinding meets the requirements; specifically, the aerodynamic performance includes: stator total pressure recovery coefficient and compressor surge margin, etc. Determine the range of aerodynamic performance according to different grinding angles and different axial grinding lengths. Figure 4As shown, for blade tip 6, the grinding angle on the first side is α1, and the distance from the grinding position on the first side to the reference plane is AE1; the grinding angle on the second side is α2, and the distance from the grinding position on the second side to the reference plane is AE2. The grinding angle can be: 15°, 20°, 25°, 30°, or 35°; the axial grinding length can be: 0.1mm, 0.2mm, 0.3mm, 0.4mm, or 0.5mm.

[0045] S22. Analyze the stress distribution and deformation trend of the leading edge or trailing edge of the stator blade 5 before and after grinding using a structural mechanics model to ensure that the structural strength of the leading edge or trailing edge of the stator blade 5 meets the requirements;

[0046] S23. Using a multi-objective optimization algorithm, using the grinding parameters as variables, balance aerodynamic performance and structural strength to obtain an optimal solution. This optimal solution is then subjected to a combined CFD (computational fluid dynamics) and finite element analysis simulation to verify aerodynamic and structural performance. Specifically, balancing aerodynamic performance and structural strength means maximizing the stator total pressure recovery coefficient and minimizing the maximum stress.

[0047] Multi-objective optimization algorithms consider multiple objectives during optimization; for example, aerodynamic performance and structural strength can be optimized simultaneously. Existing multi-objective optimization algorithms include the non-dominated sorting genetic algorithm, particle swarm optimization, artificial neural network agent models combined with genetic algorithms, response surface methodology and gradient optimization, and Pareto optimality.

[0048] The use of the multi-objective optimization algorithm described in this application includes the following steps:

[0049] S231. Clarify the quantitative indicators of aerodynamic performance and structural strength, and select the grinding parameters of the stator blades as variables; the aerodynamic performance can be the stator total pressure recovery coefficient, and the structural strength can be the stress distribution.

[0050] S232. Generate sample data through computational fluid dynamics simulation and finite element analysis, and use a multi-objective optimization algorithm to establish a mapping relationship between the objective function and the variables, replacing high-cost simulation. The multi-objective optimization algorithm can be a neural network algorithm. The neural network algorithm can be an artificial neural network agent model combined with a genetic algorithm.

[0051] S233. Utilize the above multi-objective optimization algorithm to obtain the optimal solution after initialization, iterative optimization and sensitivity analysis.

[0052] S234. Perform computational fluid dynamics simulation and finite element analysis joint simulation on the optimal solution to verify the aerodynamic and structural performance.

[0053] The compressor stator blade grinding method described in this application, step S3 includes the following steps:

[0054] S31, pouring wax into the flow channel area of the blade tip 6 of the stator blade 5 and solidifying it to form a support layer;

[0055] S32, grinding the blade tip 6 flow channel, the blade tip 6 leading edge or the blade tip 6 trailing edge; specifically, a multi-axis linkage grinding machine tool can be used to synchronously grind the blade tip 6 flow channel, the blade tip 6 leading edge or the blade tip 6 trailing edge area along a preset path to ensure geometric consistency.

[0056] S33, removing the wax by heating.

[0057] The compressor stator blade grinding method described in the present application further includes the following steps:

[0058] S4. Strengthening treatment is performed on the leading edge of the blade tip 6 or the trailing edge of the blade tip 6 of the stator blade 5 after grinding.

[0059] Specifically, the strengthening treatment includes the following steps:

[0060] S41, using laser shock peening equipment to perform local processing on the leading edge of the blade tip 6 or the trailing edge of the blade tip 6 of the stator blade 5;

[0061] S42, inducing residual compressive stress on the surface of the leading edge of the blade tip 6 or the trailing edge of the blade tip 6 of the stator blade 5 by a high-energy laser pulse;

[0062] S43. Use gradient heat treatment technology to control the temperature gradient distribution in the leading edge or trailing edge area of the blade tip 6 of the stator blade 5.

[0063] The compressor stator blade grinding method described in the present application further includes the following steps:

[0064] S5. Inspecting the effect of the strengthening treatment by non-destructive testing. Specifically, the non-destructive testing is ultrasonic testing.

[0065] Although the embodiments of the present invention have been described with reference to the accompanying drawings, those skilled in the art may make various modifications and variations without departing from the spirit and scope of the present invention. Such modifications and variations are all within the scope defined by the appended claims.

Claims

1. A method for grinding compressor stator blades, characterized in that: include: By establishing a compressor axial matching dimension chain model, the assembly tolerances of the stator blades (5) and the rotor blades at each level are quantified; based on the design dimensions of the drawings and the measured assembly dimension data of the components, the dimension tolerance range of each component is determined; through the axial clearance closed ring tolerance dimension chain analysis of the stator blades (5) and the rotor blades, the grinding amount of the leading edge or trailing edge of the stator blades (5) is determined; Combining the aerodynamic simulation model and the structural mechanics model, determining the optimal grinding parameters of the leading edge or the trailing edge of the stator blade (5); the optimal grinding parameters are: the optimal grinding modulus and the optimal grinding area; The leading edge or the trailing edge of the stator blade (5) is ground according to the optimal grinding parameters, and the axial clearance between the stator blade (5) and the rotor blade is precisely controlled.

2. The compressor stator blade grinding method according to claim 1, characterized in that: The method of combining the aerodynamic simulation model and the structural mechanics model to determine the optimal grinding parameters of the leading edge or the trailing edge of the stator blade (5) includes: Simulating the aerodynamic performance of the leading edge or the trailing edge of the stator blade (5) before and after grinding based on the aerodynamic simulation model to ensure that the aerodynamic performance of the stator blade (5) after the leading edge or the trailing edge is ground meets the requirements; Using a structural mechanics model to analyze the stress distribution and deformation trend of the leading edge or the trailing edge of the stator blade (5) before and after grinding, to ensure that the structural strength of the stator blade (5) after the leading edge or the trailing edge is ground meets the requirements; Through a multi-objective optimization algorithm, the grinding parameters are used as variables to balance aerodynamic performance and structural strength to obtain the optimal solution. The optimal solution is then subjected to a joint CFD simulation and finite element analysis to verify the aerodynamic and structural performance.

3. The compressor stator blade grinding method according to claim 2, characterized in that: The aerodynamic performance includes: stator total pressure recovery coefficient and compressor surge margin.

4. The compressor stator blade grinding method according to claim 2, characterized in that: The variation range of aerodynamic performance is determined according to different grinding angles and different axial grinding lengths.

5. The compressor stator blade grinding method according to claim 2, characterized in that: The balance between aerodynamic performance and structural strength refers to maximizing the static total pressure recovery coefficient and minimizing the maximum stress.

6. The compressor stator blade grinding method according to any one of claims 1 to 5, characterized in that: Grinding the leading edge or the trailing edge of the stator blade (5) according to the optimal grinding parameters comprises: Wax is poured into the flow channel area of the blade tip (6) of the stator blade (5) and solidified to form a support layer; Grinding the blade tip (6) flow channel, the blade tip (6) leading edge or the blade tip (6) trailing edge; The wax is removed by heating.

7. The compressor stator blade grinding method according to any one of claims 1 to 5, characterized in that: Also includes: The blade tip (6) leading edge or the blade tip (6) trailing edge of the ground stator blade (5) is subjected to strengthening treatment.

8. The compressor stator blade grinding method according to claim 7, characterized in that: The strengthening treatment includes: Using laser shock peening equipment to perform local processing on the leading edge of the blade tip (6) or the trailing edge of the blade tip (6) of the stator blade (5); Inducing residual compressive stress on the surface of the leading edge of the blade tip (6) or the trailing edge of the blade tip (6) of the stator blade (5) by high-energy laser pulses; A gradient heat treatment technology is used to control the temperature gradient distribution in the leading edge area of the blade tip (6) or the trailing edge area of the blade tip (6) of the stator blade (5).

9. The compressor stator blade grinding method according to claim 7, characterized in that: Also includes: The effect of the strengthening treatment is verified by non-destructive testing.

10. The compressor stator blade grinding method according to claim 9, characterized in that: The non-destructive testing is ultrasonic testing.

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