Anti-micro-motion and anti-fatigue method for tenon of aero-engine

Abstract

The invention relates to the technical field of aero-engines, and provides an anti-fretting and anti-fatigue method for an aero-engine tenon, and the method comprises the steps: carrying out various types of reinforcement treatment on a tenon test piece, and obtaining a plurality of reinforced tenon test pieces; applying a preset fatigue load to the plurality of reinforced tenon test pieces through the loading test assembly to obtain fretting fatigue data corresponding to the plurality of reinforced tenon test pieces; and based on the fretting fatigue data, determining shot peening strengthening as a target fretting fatigue resisting processing mode when the actual load amplitude is smaller than the target load amplitude, and determining shot peening and activation combined strengthening as the target fretting fatigue resisting processing mode when the actual load amplitude is larger than the target load amplitude. According to the method, the tenon test piece is subjected to various strengthening treatment and fatigue loading, and based on the fretting fatigue data, the most suitable fretting fatigue resisting treatment mode can be selected according to the relation between the actual load amplitude and the target load amplitude, so that the fretting fatigue resisting performance of the tenon is improved, and the service life is prolonged.

Description

Technical Field

[0001] The invention relates to the technical field of aeroengines, and in particular to a method for resisting fretting and fatigue of tenons of an aeroengine. Background Art

[0002] As the core power unit of modern aircraft, the performance of aircraft engines is directly related to flight safety and efficiency. However, during the long-term service of aircraft engines, especially under complex load environments such as high temperature, high pressure, high speed and alternating load, the internal connection structure of the aircraft engine is susceptible to severe multi-axial loads, resulting in fatigue failure of the connection structure. Relevant studies have shown that about 1 / 6 of the failures caused by fatigue in aircraft engines are caused by micro-motion fatigue. Micro-motion fatigue failure at the tenon-mortise joint accounts for 1 / 5 of the mechanical failures of aircraft engines, which in turn leads to engine failure and even serious flight accidents.

[0003] Existing anti-fretting fatigue technology mainly focuses on material selection and structural optimization, but it still has certain limitations and cannot fully meet the requirements of long life of aircraft engines. Therefore, how to effectively improve the anti-fretting fatigue performance of turbine blade tenons is a key technical problem that the industry needs to solve urgently. Summary of the invention

[0004] In view of the deficiencies in the prior art, the present invention provides a method for resisting fretting and fatigue of a tenon of an aero-engine. By strengthening a tenon test piece, the fretting fatigue life of the tenon of an aero-engine can be improved.

[0005] The present invention provides a method for resisting fretting and fatigue of a tenon of an aero-engine. The method is based on a fretting test system. The fretting test system comprises a tenon test piece and a loading test assembly. The tenon test piece has fretting planes on two opposite sides along the width direction. The loading test assembly is used to apply a fatigue load to the tenon test piece. The method comprises: Performing a plurality of strengthening treatments on the tenon test piece to obtain a plurality of strengthened tenon test pieces; the plurality of strengthening treatments include laser shock strengthening, shot peening strengthening, and combined strengthening of shot peening and energization; Applying a preset fatigue load to the plurality of reinforced tenon test pieces by means of the loading test assembly to obtain fretting fatigue data corresponding to the plurality of reinforced tenon test pieces; Based on the fretting fatigue data, it is determined that when the actual load amplitude is less than the target load amplitude, the shot peening strengthening is determined as the target anti-fretting fatigue treatment method, and when the actual load amplitude is greater than the target load amplitude, the shot peening and energizing combined strengthening is determined as the target anti-fretting fatigue treatment method.

[0006] A method for resisting fretting and fatigue of an aeroengine tenon according to the present invention, wherein the loading test assembly includes a first clamping member and a second clamping member arranged oppositely along the length direction of the tenon test piece. The first clamping member is used for clamping the tenon test piece. The second clamping member has a clamping portion located outside the fretting plane. The clamping portion has a receiving groove, and the receiving groove has a contact member that abuts against the fretting plane.

[0007] A method for resisting fretting and fatigue of an aeroengine tenon according to the present invention, wherein the first clamping member has a first positioning portion, the second clamping member has a second positioning portion, and the center lines of the first positioning portion and the second positioning portion coincide.

[0008] A method for resisting fretting and fatigue of an aeroengine tenon according to the present invention, wherein the dimensions of the clamping portion and the contact member along the thickness direction of the tenon test piece are greater than the thickness of the tenon test piece, and the tenon test piece abuts against the middle of the contact member.

[0009] A method for resisting fretting and fatigue of an aeroengine tenon according to the present invention, wherein the contact member includes a flat surface and arc surfaces located on both sides of the flat surface, and the flat surface abuts against the fretting plane.

[0010] A method for resisting fretting and fatigue of an aeroengine tenon according to the present invention, after obtaining the fretting fatigue data corresponding to multiple strengthened tenon test pieces, the method further includes: Based on the fretting fatigue data corresponding to multiple strengthened tenon test pieces, obtaining a relationship curve between the fretting fatigue life and the load amplitude corresponding to multiple strengthened tenon test pieces; Determining the load amplitude corresponding to the intersection point with the maximum fretting fatigue life among the intersection points of multiple relationship curves as the target load amplitude.

[0011] A method for resisting fretting and fatigue of an aeroengine tenon according to the present invention, before performing various strengthening treatments on the tenon test piece, the method further includes: Polishing the contact surface between the tenon test piece and the contact member.

[0012] A method for resisting fretting and fatigue of an aeroengine tenon according to the present invention, one end of the tenon test piece along the length direction has a mounting portion for connecting with the first clamping member, the other end of the tenon test piece along the length direction has a test portion, the width of the test portion gradually increases from one end close to the mounting portion to the end far from the mounting portion, and the side surface of the test portion constitutes the fretting plane.

[0013] The present invention also provides an electronic device, including a memory, a processor, and a computer program stored on the memory and executable on the processor. When the processor executes the computer program, the method for resisting fretting and fatigue of an aero-engine tenon as described in any one of the above is implemented.

[0014] The present invention also provides a non-transitory computer-readable storage medium, on which a computer program is stored. When the computer program is executed by a processor, the method for resisting fretting and fatigue of an aero-engine tenon as described in any one of the above is implemented.

[0015] The method for resisting fretting and fatigue of an aero-engine tenon provided by the present invention can simulate the fretting fatigue situation of an aero-engine tenon in the actual working environment by combining a tenon test piece and a loading test assembly. Through various strengthening treatments and fatigue loading on the tenon test piece, and based on the fretting fatigue data, the most suitable fretting fatigue resistance treatment method can be selected according to the relationship between the actual load amplitude and the target load amplitude. Therefore, the selected fretting fatigue resistance treatment method can significantly improve the fretting fatigue resistance performance of the tenon and extend the service life. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions in the present invention or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0017] Figure 1 is one of the flow diagrams of the method for resisting fretting and fatigue of an aero-engine tenon provided by the present invention.

[0018] Figure 2 is one of the structural diagrams of the fretting test system provided by the present invention.

[0019] Figure 3 is the second structural diagram of the fretting test system provided by the present invention.

[0020] Figure 4 is the structural diagram of the loading test assembly provided by the present invention.

[0021] Figure 5 is one of the structural diagrams of the tenon test piece provided by the present invention.

[0022] Figure 6 is the second structural diagram of the tenon test piece provided by the present invention.

[0023] Figure 7 is the second flow diagram of the method for resisting fretting and fatigue of an aero-engine tenon provided by the present invention.

[0024] Figure 8 is a tree diagram between the fatigue load and the number of failure cycles provided by the present invention.

[0025] Figure 9 is a relationship curve between the fatigue load and the number of failure cycles provided by the present invention.

[0026] Figure 10 is a schematic structural diagram of the electronic device provided by the present invention.

[0027] Reference numerals: 10, tenon test piece; 11, fretting plane; 12, mounting part; 13, first flat plate; 14, second flat plate; 20, loading test assembly; 21, first clamping member; 211, clamping plate; 2111, second mounting hole; 22, second clamping member; 221, clamping part; 2211, accommodating groove; 222, accommodating space; 223, second positioning part; 23, contact member. Detailed implementation manners

[0028] To make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the present invention will be clearly and completely described below with reference to the accompanying drawings in the present invention. Obviously, the described embodiments are some but not all of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art without making creative efforts based on the embodiments in the present invention belong to the scope of protection of the present invention.

[0029] Next, in combination with Figures 1 - 9 describe the method for resisting fretting and fatigue of the tenon of an aeroengine of the present invention.

[0030] An embodiment of the first aspect of the present invention proposes a method for resisting fretting and fatigue of the tenon of an aeroengine, as Figure 1 shown. This method for resisting fretting and fatigue is based on a fretting test system and specifically includes the following steps: Step 100: Perform various strengthening treatments on the tenon simulation part 10 to obtain multiple tenon strengthening test pieces; the various strengthening treatments include laser shock peening, shot peening, and a combination of shot peening and laser shock peening.

[0031] Among them, as Figure 2 and as shown in FIG. 3, the fretting test system includes a tenon simulation part 10 and a loading test assembly 20. The two opposite sides of the tenon simulation part 10 in the width direction have fretting planes 11, and the loading test assembly 20 is used to apply a fatigue load to the tenon simulation part 10.

[0032] It is understandable that the tenon simulator 10 is designed according to the tenon structure at the blade root. One end of the tenon simulator 10 can be installed on the loading test assembly 20, and the loading test assembly 20 can apply a load to the fretting plane 11 at the other end of the tenon simulator 10 to simulate the fretting fatigue condition of the aero-engine tenon in the actual working environment.

[0033] Exemplarily, there are three strengthening treatment processes including laser shock peening, shot peening, and a combination of shot peening and laser shock peening. Three different strengthening treatments are respectively performed on three tenon simulators 10 to obtain three tenon strengthened test pieces. It should be noted that the number of tenon simulators 10 corresponds to the number of strengthening treatment processes. For example, the number of tenon simulators 10 can be an integer multiple of the number of strengthening treatment processes. Multiple tenon strengthened test pieces after the same strengthening treatment process are respectively loaded with different load values.

[0034] Step 200: Apply a preset fatigue load to multiple tenon strengthened test pieces through the loading test assembly 20 to obtain fretting fatigue data corresponding to the multiple tenon strengthened test pieces.

[0035] It is understandable that each tenon strengthened test piece is clamped on the loading test assembly 20, and a preset fatigue load is applied to the tenon strengthened test piece through the loading test assembly 20 to obtain fretting fatigue data; thus, multiple tenon strengthened test pieces can obtain corresponding multiple fretting fatigue data.

[0036] Step 300: Based on the fretting fatigue data, determine that shot peening is the target anti-fretting fatigue treatment method when the actual load amplitude is less than the target load amplitude, and determine that the combination of shot peening and laser shock peening is the target anti-fretting fatigue treatment method when the actual load amplitude is greater than the target load amplitude.

[0037] It is understandable that the target load amplitude is determined based on the fretting fatigue data. In actual application, the most suitable anti-fretting fatigue treatment method is selected according to the magnitude relationship between the actual load amplitude and the target load amplitude. Specifically, when the actual load amplitude is less than the target load amplitude, shot peening is determined as the target anti-fretting fatigue treatment method, and when the actual load amplitude is greater than the target load amplitude, the combination of shot peening and laser shock peening is determined as the target anti-fretting fatigue treatment method. It should be noted here that the target anti-fretting fatigue treatment method is the preferred strengthening treatment method for the aero-engine tenon.

[0038] It should be noted that strengthening the surface of the aero-engine tenon by using the target anti-fretting fatigue treatment method can significantly improve the anti-fretting fatigue performance of the tenon, extend the service life of the turbine blade, reduce the engine failure rate, and enhance flight safety.

[0039] The method for resisting fretting and fatigue of an aero-engine tenon provided by the embodiment of the present invention can simulate the fretting fatigue situation of the aero-engine tenon in the actual working environment by combining the tenon simulation piece 10 and the loading test assembly 20. By performing various strengthening treatments and fatigue loading on the tenon simulation piece 10, and based on the fretting fatigue data, the most suitable anti-fretting fatigue treatment method can be selected according to the relationship between the actual load amplitude and the target load amplitude. Thus, the selected anti-fretting fatigue treatment method can significantly improve the anti-fretting fatigue performance of the tenon and extend the service life.

[0040] In an embodiment of the present invention, as Figures 2 - 6 shown, the loading test assembly 20 includes a first clamping member 21 and a second clamping member 22 arranged oppositely along the length direction of the tenon simulation piece. The first clamping member 21 is used to clamp the tenon simulation piece 10, and the second clamping member 22 has a clamping portion 221 located outside the fretting plane 11. The clamping portion 221 has a receiving groove 2211, and the receiving groove 2211 has a contact member 23 that abuts against the fretting plane 11.

[0041] It can be understood that one end of the second clamping member 22 near the first clamping member 21 has two clamping portions 221 arranged at intervals, and a receiving space 222 is formed between the two clamping portions 221; one end of the tenon simulation piece 10 is clamped by the first clamping member 21, and the other end of the tenon simulation piece 10 is located in the receiving space 222. The two clamping portions 221 are located outside the fretting plane 11 of the tenon simulation piece 10, and the contact member 23 is arranged between the clamping portion 221 and the fretting plane 11. Applying a fatigue load to the second clamping member 22, the second clamping member 22 reciprocates along the length direction of the tenon simulation piece, driving the contact member 23 to reciprocate relative to the fretting plane 11 to perform a fretting fatigue test on the tenon simulation piece 10.

[0042] Optionally, the dimensions of the clamping portion 221 and the contact member 23 along the thickness direction of the tenon simulation piece 10 are greater than the thickness of the tenon simulation piece 10, and the tenon simulation piece 10 abuts against the middle of the contact member 23.

[0043] Furthermore, the contact member 23 includes a flat surface and arc surfaces located on both sides of the flat surface. The flat surface abuts against the fretting plane 11. Thus, the contact form between the contact member 23 and the tenon simulation piece 10 is "plane - plane" contact form, with a larger contact area, more uniform stress distribution, avoiding local stress concentration phenomenon, reducing local heat accumulation, and reducing the degradation of material properties caused by high temperature. It should be noted here that the "plane - plane" contact form is convenient for laser shock peening, shot peening, and the combined strengthening process of shot peening and laser shock peening.

[0044] Exemplarily, as Figure 2As shown in the figure, the tenon simulation part 10 is arranged vertically. The width direction of the tenon simulation part 10 is the first horizontal direction, denoted as X; the thickness direction of the tenon simulation part 10 is the second horizontal direction, that is, Y; the length direction of the tenon simulation part 10 is the height direction, denoted as Z. The second clamping part 22 is located above the first clamping part 21. The lower end of the tenon simulation part 10 is fixed to the first clamping part 21. The upper end of the tenon simulation part 10 has two micro-motion planes 11 arranged oppositely in the first horizontal direction. The two clamping parts 221 of the second clamping part 22 are respectively located outside the two micro-motion planes 11. The opposite surfaces of the two clamping parts 221 have accommodation grooves 2211. One side of the contact part 23 is arranged in the accommodation groove 2211, and the other side of the contact part 23 abuts against the micro-motion plane 11. The dimension of the clamping part 221 in the second horizontal direction is greater than the thickness of the tenon simulation part 10, and the dimension of the contact part 23 in the second horizontal direction is greater than the thickness of the tenon simulation part 10.

[0045] Further, the dimensions of the clamping part 221 and the contact part 23 in the second horizontal direction are equal and are 4 to 5 times the thickness of the tenon simulation part 10. The tenon simulation part 10 abuts against the middle of the contact part 23.

[0046] It should be noted that the clamping part 221 and the contact part 23 are 4 to 5 times the thickness of the tenon simulation part 10, which improves the strength and stiffness of the clamping part 221 and can accurately simulate the change in the contact state of the micro-motion plane 11 due to the deformation of the clamping part 221 during the micro-motion fatigue test.

[0047] In an embodiment of the present invention, as Figure 3 shown, the first clamping part 21 has a first positioning part (not shown in the figure), and the second clamping part 22 has a second positioning part 223. The center lines of the first positioning part and the second positioning part 223 coincide.

[0048] It can be understood that one end of the first clamping part 21 away from the second clamping part 22 has a first positioning part, and one end of the second clamping part 22 away from the first clamping part 21 has a second positioning part 223. By making the center lines of the first positioning part and the second positioning part 223 coincide, the positioning and centering of the first clamping part 21 and the second clamping part 22 are realized; one end of the first clamping part 21 close to the second clamping part 22 has an installation position. By installing the tenon simulation part 10 in this installation position, the positioning and centering of the tenon simulation part 10 and the second clamping part 22 can be realized.

[0049] Exemplarily, the micro-motion test system includes a fatigue testing machine, a tenon simulation part 10, and a loading test assembly 20. The first clamping part 21 and the second clamping part 22 are arranged on the fatigue testing machine. The second clamping part 22 is located above the first clamping part 21. The first clamping part 21 and the second clamping part 22 are respectively connected to the fatigue testing machine, and the fatigue testing machine applies a fatigue load.

[0050] The first positioning portion is a first positioning hole, and the second positioning portion 223 is a second positioning hole. The upper part of the fatigue testing machine has a first positioning shaft connected to the first positioning hole, and the fatigue testing machine has a second positioning shaft connected to the second positioning hole. Alignment is achieved through the first positioning shaft and the second positioning shaft, that is, the axes of the first positioning shaft and the second positioning shaft coincide, which means the axes of the first positioning hole and the second positioning hole coincide. Thus, through the shaft-hole fit between the first positioning hole and the first positioning shaft, and the shaft-hole fit between the second positioning hole and the second positioning shaft, rapid positioning and alignment of the first clamping member 21 and the second clamping member 22 can be realized, and further rapid positioning and assembly of the tenon head simulation member 10 and the second clamping member 22 can be achieved.

[0051] In an embodiment of the present invention, as Figure 5 and Figure 6 shown, one end of the tenon head simulation member 10 in the length direction has a mounting portion 12 for connecting to the first clamping member 21, and the other end of the tenon head simulation member 10 in the length direction has a test portion. The width of the test portion gradually increases from the end close to the mounting portion 12 to the end far from the mounting portion 12, and the side surface of the test portion constitutes a fretting plane 11.

[0052] It should be noted that the structural dimensions and surface states of the tenon head simulation member 10 are basically the same as those of the real blade root tenon head. The surfaces or structures not related to the fretting plane 11 can be simplified to facilitate the processing and manufacturing of the tenon head simulation member 10 and the tests.

[0053] Optionally, the tenon head simulation member 10 has a first flat plate 13 and a second flat plate 14 connected in the length direction. The first flat plate 13 is used to connect to the first clamping member 21. The thickness of the first flat plate 13 is greater than the thickness of the second flat plate 14. The mounting portion 12 is a first mounting hole opened on the first flat plate 13; a test portion is formed at the end of the second flat plate 14 far from the first flat plate 13.

[0054] It can be understood that, as Figure 3 and Figure 4 shown, the first clamping member 21 has two clamping plates 211 arranged at intervals in the thickness direction of the first flat plate 13. The clamping plates 211 have second mounting holes 2111 that cooperate with the first mounting hole. A clamping cavity is formed between the two clamping plates 211. The first flat plate 13 is assembled in the clamping cavity and is connected to the first mounting hole and the second mounting hole 2111 through a connecting member to achieve the assembly of the tenon head simulation member 10 and the first clamping member 21.

[0055] It should be noted that by making the thickness of the first flat plate 13 greater than the thickness of the second flat plate 14, the fixing strength and stiffness of the first clamping member 21 to the tenon head simulation member 10 are improved.

[0056] In this embodiment, the first flat plate 13 and the second flat plate 14 are connected with an arc transition.

[0057] Furthermore, the second flat plate 14 includes a first plate segment and a second plate segment connected along the length direction. One end of the first plate segment far from the second plate segment is connected to the first flat plate 13. The width of the first plate segment is smaller than the width of the second plate segment, and the width of the first plate segment is smaller than the width of the first flat plate 13. The width of the second plate segment gradually increases from the end connected to the first plate segment to the end far from the first plate segment part, so as to form a test part.

[0058] In a specific embodiment of the present invention, as Figures 2 - 6 shown, the fretting test system includes a tenon head simulation part 10 and a loading test component 20.

[0059] The tenon head simulation part 10 includes a first flat plate 13 and a second flat plate 14 connected along the length direction. A first mounting hole is provided on the first flat plate 13. The thickness of the second flat plate 14 is smaller than the thickness of the first flat plate 13. The second flat plate 14 has a test part, and the width of the test part gradually increases from the end close to the first flat plate 13 to the end far from the first flat plate 13. The side surface of the test part constitutes a fretting plane 11.

[0060] The loading test component 20 includes a pair of contact parts 23, a first clamping part 21 and a second clamping part 22 located above the first clamping part 21. The first clamping part 21 and the second clamping part 22 are respectively connected to the upper chuck and the lower chuck of the fatigue testing machine; the first clamping part 21 and the second clamping part 22 can adopt a fixture structure. The upper end of the first clamping part 21 has two clamping plates 211, and a clamping cavity is formed between the two clamping plates 211. The clamping plate 211 has a second mounting hole 2111 that cooperates with the first mounting hole; the second clamping part 22 has two opposite clamping parts 221, and a receiving space 222 is formed between the two clamping parts 221. The opposite side surfaces of the two clamping parts 221 have receiving grooves 2211. A pair of contact parts 23 includes two contact parts 23 arranged oppositely. One sides of the two contact parts 23 are respectively arranged in the two receiving grooves 2211; the contact part 23 includes a flat surface and arc surfaces located on both sides of the flat surface, and the flat surface abuts against the fretting plane 11.

[0061] It is installed in the clamping cavity through the first flat plate 13 and is connected to the first mounting hole and the second mounting hole 2111 through a connecting piece, so as to realize the assembly of the tenon head simulation part 10 and the first clamping part 21; meanwhile, the two fretting planes 11 at the upper end of the tenon head simulation part 10 respectively abut against the two contact parts 23, so as to simulate the tenon joint structure of a real blade and a compressor disk.

[0062] In this embodiment, the thickness of the second flat plate 14 is 4 mm, the thickness of the contact member 23 (i.e., the dimension along the second horizontal direction) is 22 mm, the length of the flat surface of the contact member 23 is 2 mm, and the diameter of the arc surface is 3 mm. Thus, a "plane-plane" contact form is established between the contact member 23 and the tenon simulation member 10, and the size specification of the contact surface is a rectangle of 2 mm × 4 mm.

[0063] It should be noted that fretting is a kind of damage caused by reciprocating motion of a small magnitude between contact surfaces. Therefore, the rectangular contact surface of 2 mm × 4 mm in this embodiment can accurately simulate the fretting fatigue situation of the aero-engine tenon in the actual working environment.

[0064] The fatigue testing machine can be a QBG-100 high-frequency fatigue testing machine. Before the test, the fatigue testing machine is run and debugged. The equipment runs stably and normally, and the alignment of the fatigue testing machine (the alignment of the first positioning shaft and the second positioning shaft) is checked. After meeting the requirements, the tenon simulation member 10 is installed, and then the fretting fatigue test is carried out.

[0065] In an embodiment of the present invention, as Figure 7 shown, after step 200, the method further includes the following steps: Step 400: Based on the fretting fatigue data corresponding to multiple tenon strengthening test pieces, obtain the relationship curves between the fretting fatigue life and the load amplitude corresponding to the multiple tenon strengthening test pieces.

[0066] Step 500: Determine the load amplitude corresponding to the intersection point with the maximum fretting fatigue life among the intersection points of the multiple relationship curves as the target load amplitude.

[0067] For example, three tenon simulation members 10 are respectively subjected to laser shock peening, shot peening, and a combination of shot peening and laser shock peening to obtain three tenon strengthening test pieces. By applying a preset fatigue load to each tenon strengthening test piece through the loading test assembly 20, multiple load amplitudes and the corresponding fretting fatigue lives are obtained. Based on the multiple load amplitudes and the multiple fretting fatigue lives, the relationship curves between the fretting fatigue life and the load amplitude can be obtained. Thus, three tenon strengthening test pieces can obtain three relationship curves between the fretting fatigue life and the load amplitude. Determine the load amplitude corresponding to the intersection point with the maximum fretting fatigue life among the intersection points of the three relationship curves as the target load amplitude.

[0068] Optionally, before step 100, the method further includes the following: Polish the contact surface between the tenon simulation member 10 and the contact member 23.

[0069] It can be understood that after the tenon simulator 10 is processed, the contact surface between the tenon simulator 10 and the contact member 23 is finely polished so that the surface finish reaches 0.4 μm to accurately simulate the fretting fatigue of the aero-engine tenon in the actual working environment.

[0070] In a specific embodiment of the present invention, the anti-fretting and anti-fatigue method specifically includes the following steps: S1. Three surface strengthening treatment processes are respectively carried out on the surfaces of three groups of tenon simulators to obtain three groups of tenon strengthened test pieces.

[0071] It can be understood that each group of tenon simulators includes at least three tenon simulators. The three groups of tenon simulators are respectively strengthened by three strengthening treatment processes to obtain the corresponding three groups of tenon strengthened test pieces. It should be noted that all physical parameters such as the material and size of the tenon simulators are the same.

[0072] Among them, the three strengthening treatment processes are respectively laser shock peening (LSP), shot peening (SP), and a combined strengthening of shot peening and laser shock peening (LSP + SP), a total of three strengthening treatment processes.

[0073] The combined strengthening of shot peening and laser shock peening (LSP + SP) is a combination of laser shock peening (LSP) and shot peening (SP).

[0074] Shot peening is a strengthening method that uses a large number of high-speed moving projectiles as a medium to impact the surface of the material. Shot peening exhibits excellent residual compressive stress generation and fatigue enhancement capabilities. Laser shock peening is an anti-fatigue surface treatment technology. The basic principle is to utilize the "mechanical effect" of a short pulse width (ns), high power (GW / cm 2 ) laser-induced plasma shock wave (GPa) to cause plastic deformation of the metal material at an ultra-high strain rate (>106 / s), forming a gradient residual compressive stress (up to 2 mm and above) and gradient microstructural changes, thereby improving the fatigue performance of the material.

[0075] It should be noted that the strengthening treatment can be only carried out on the fretting plane 11 area where the tenon simulator 10 cooperates with the contact member 23.

[0076] In this embodiment, before the strengthening treatment is carried out on the surface of the tenon simulator 10, the contact surfaces of all the tenon simulators 10 are polished with 800# to 2000# SiC sandpaper, and then cleaned with acetone and absolute ethanol.

[0077] LSP: LSP was carried out using an Nd:YAG laser device (YD60-R200B) with a wavelength of 1064 nm and a pulse width of 20 ns. Among them, the spot diameter Φ was 2 mm, the overlap rate was 50%, the absorption protection layer was black tape, the constraint layer was water, and the number of impacts was 1 time. It should be noted that when performing laser shock, the incident angle needs to be adjusted so that the laser incident direction is perpendicular to the fretting plane 11, and the scanning path completely covers the side surface of the tenon simulation part 10.

[0078] SP: It was carried out on a JY-120WB sandblasting machine, using S110 cast steel with a diameter of 1.3 mm, a speed of 60 mm / min, a strength of 0.3 mmN, a coverage rate of 100%, a pressure of 0.13 MPa, a shot flow rate of 7 kg / min, a spraying distance of 150 mm, and a spraying angle of 45° - 90°.

[0079] LSP + SP: The process sequence of LSP first and then SP strengthening was preferably adopted. The same equipment and working parameters as those of the single LSP and SP processes were used, and the LSP + SP combined treatment was carried out in the order of LSP prior to SP.

[0080] S2. The three groups of tenon strengthening test pieces were respectively clamped on the first clamping piece 21 of the loading test assembly 20, and a preset fatigue load was applied to the second clamping piece 22 through a fatigue testing machine to obtain the fretting fatigue data corresponding to the multiple tenon strengthening test pieces.

[0081] Specifically, the three groups of tenon strengthening test pieces corresponding to the LSP, SP, and LSP + SP strengthening treatments were respectively recorded as the first group of tenon strengthening test pieces, the second group of tenon strengthening test pieces, and the third group of tenon strengthening test pieces.

[0082] The first group of tenon strengthening test pieces (three tenon strengthening test pieces) were respectively clamped on the first clamping piece 21 of the loading test assembly 20, and fatigue loads of 8 kN, 10 kN, and 12 kN (the maximum axial load, that is, the load amplitude, unit: kilonewton) were respectively applied by the fatigue testing machine to obtain the corresponding three failure cycle numbers (that is, the fretting fatigue life, unit: number of times). According to the data corresponding to the load amplitude and the fretting fatigue life, as Figure 8 shown, and based on the data of the load amplitude and the fretting fatigue life, a relationship curve between the fretting fatigue life corresponding to LSP and the load amplitude was plotted, as Figure 9 curve a in. It should be noted that in order to improve the accuracy of the load amplitude and fretting fatigue life data, multiple fatigue loading tests can be carried out under the same fatigue load, so that multiple fretting fatigue lives can be obtained under the same load amplitude.

[0083] The second group of tenon strengthening test pieces were subjected to fatigue load application in the same manner as the first group of tenon strengthening test pieces to obtain the data corresponding to the load amplitude and the fretting fatigue life corresponding to SP, asFigure 8 as shown; and the relationship curve between fretting fatigue life and load amplitude, such as Figure 9 the b curve in. The third group of tenon reinforcement test pieces were applied with fatigue loads in the same way as the first group of tenon reinforcement test pieces, and the corresponding data of the load amplitude and fretting fatigue life corresponding to LSP + SP were obtained, such as Figure 8 as shown; and the relationship curve between fretting fatigue life and load amplitude, such as Figure 9 the c curve in.

[0084] It should be noted that the un-reinforced tenon simulation piece 10 was clamped by the first clamping piece 21 of the loading test assembly 20, and fatigue loads of 8 kN, 10 kN and 12 kN were applied to the second clamping piece 22 through a fatigue testing machine to obtain the corresponding three failure cycle numbers (i.e., fretting fatigue life). According to the corresponding data of load amplitude and fretting fatigue life, the relationship curve between the untreated fretting fatigue life and load amplitude was plotted, such as Figure 9 the d curve in.

[0085] It can be seen that the fretting fatigue life decreases with the increase of fatigue load, and all three reinforcement treatment processes significantly improve the fretting fatigue life of the tenon simulation piece 10.

[0086] S3. Compare the three relationship curves to determine the target load amplitude.

[0087] The load amplitude corresponding to the intersection point with the maximum fretting fatigue life among the intersection points of the three relationship curves (a curve, b curve and c curve) is determined as the target load amplitude, that is, 8.5 kN is indeed the target load amplitude.

[0088] Therefore, in the actual use process, when the actual maximum load is greater than 8.5 kN, LSP + SP is used to strengthen the aeroengine tenon so that the fatigue life of the aeroengine tenon strengthened by LSP + SP has the largest increase. When the actual maximum load is less than 8.5 kN, SP is used to strengthen the aeroengine tenon so that the fatigue life of the aeroengine tenon strengthened by SP has the largest increase, thereby providing a reliable theoretical basis and application support for the anti-fretting fatigue design, life determination and life extension of aeroengine turbine blades.

[0089] It can be understood that by introducing residual compressive stress in the fretting plane 11 of the tenon simulation piece 10 through LSP and SP, the fretting fatigue life can be significantly improved, and as the amplitude of the residual compressive stress increases, the fretting fatigue life increases accordingly. The amplitude of the residual compressive stress introduced by LSP + SP on the surface of the tenon simulation piece is the largest.

[0090] It should be noted that when the actual maximum load is less than 8.5 kN, the fatigue life increases significantly (exceeding 105 cycles), and the influence of the roughness size on the fretting fatigue life increases. Under the combined action of the residual compressive stress and the roughness, the fretting fatigue life of the tenon treated by SP is improved most significantly, followed by LSP+SP, and finally SP.

[0091] Figure 10 The schematic physical structure diagram of an electronic device is illustrated, as Figure 10 shown. The electronic device may include: a processor 1010, a communications interface 1020, a memory 1030, and a communication bus 1040. Among them, the processor 1010, the communications interface 1020, and the memory 1030 complete mutual communication through the communication bus 1040. The processor 1010 can call the logical instructions in the memory 1030 to execute a method for resisting fretting and fatigue of an aeroengine tenon. The method is based on a fretting test system, which includes a tenon test piece and a loading test component. The two opposite sides of the tenon test piece in the width direction have fretting planes. The loading test component is used to apply a fatigue load to the tenon test piece. The method includes: performing multiple strengthening treatments on the tenon test piece to obtain multiple strengthened tenon test pieces; the multiple strengthening treatments include laser shock peening, shot peening, and a combination of shot peening and laser shock peening; applying a preset fatigue load to the multiple strengthened tenon test pieces through the loading test component to obtain the fretting fatigue data corresponding to the multiple strengthened tenon test pieces; based on the fretting fatigue data, determining that shot peening is the target anti-fretting fatigue treatment method when the actual load amplitude is less than the target load amplitude, and determining that the combination of shot peening and laser shock peening is the target anti-fretting fatigue treatment method when the actual load amplitude is greater than the target load amplitude.

[0092] In addition, when the logical instructions in the above-mentioned memory 1030 are implemented in the form of software functional units and sold or used as an independent product, they can be stored in a computer-readable storage medium. Based on such an understanding, the technical solution of the present invention, in essence, or the part that makes a contribution to the prior art, or a part of the technical solution, can be embodied in the form of a software product. The computer software product is stored in a storage medium and includes several instructions for causing a computer device (which may be a personal computer, a server, or a network device, etc.) to execute all or part of the steps of the methods of the various embodiments of the present invention. The foregoing storage medium includes: USB flash drives, mobile hard disks, read-only memories (ROM, Read-Only Memory), random access memories (RAM, Random Access Memory), magnetic disks, or optical disks, and other various media that can store program codes.

[0093] On the other hand, the present invention also provides a computer program product. The computer program product includes a computer program that can be stored on a non-transitory computer-readable storage medium. When the computer program is executed by a processor, the computer can execute the anti-fretting and anti-fatigue method for the aero-engine tenon provided by each of the above methods. The method is based on a fretting test system, which includes a tenon test piece and a loading test component. The two opposite sides of the tenon test piece in the width direction have fretting planes. The loading test component is used to apply a fatigue load to the tenon test piece. The method includes: performing various strengthening treatments on the tenon test piece to obtain multiple strengthened tenon test pieces; the various strengthening treatments include laser shock peening, shot peening, and a combination of shot peening and laser shock peening; applying a preset fatigue load to the multiple strengthened tenon test pieces through the loading test component to obtain the fretting fatigue data corresponding to the multiple strengthened tenon test pieces; based on the fretting fatigue data, determining that shot peening is the target anti-fretting and anti-fatigue treatment method when the actual load amplitude is less than the target load amplitude, and determining that the combination of shot peening and laser shock peening is the target anti-fretting and anti-fatigue treatment method when the actual load amplitude is greater than the target load amplitude.

[0094] In another aspect, the present invention also provides a non-transitory computer-readable storage medium, on which a computer program is stored. When the computer program is executed by a processor, it realizes the anti-fretting and anti-fatigue method for the aero-engine tenon provided by each of the above methods. The method is based on a fretting test system, which includes a tenon test piece and a loading test component. The two opposite sides of the tenon test piece in the width direction have fretting planes. The loading test component is used to apply a fatigue load to the tenon test piece. The method includes: performing various strengthening treatments on the tenon test piece to obtain multiple strengthened tenon test pieces; the various strengthening treatments include laser shock peening, shot peening, and a combination of shot peening and laser shock peening; applying a preset fatigue load to the multiple strengthened tenon test pieces through the loading test component to obtain the fretting fatigue data corresponding to the multiple strengthened tenon test pieces; based on the fretting fatigue data, determining that shot peening is the target anti-fretting and anti-fatigue treatment method when the actual load amplitude is less than the target load amplitude, and determining that the combination of shot peening and laser shock peening is the target anti-fretting and anti-fatigue treatment method when the actual load amplitude is greater than the target load amplitude.

[0095] The device embodiments described above are merely illustrative. The units described as separate components may or may not be physically separated, and the components shown as units may or may not be physical units, that is, they may be located in one place or distributed to multiple network units. Some or all of the modules can be selected according to actual needs to achieve the purpose of the solution of this embodiment. Those of ordinary skill in the art can understand and implement it without creative efforts.

[0096] Through the description of the above embodiments, those skilled in the art can clearly understand that each embodiment can be implemented by means of software plus a necessary general hardware platform, and of course, it can also be implemented by hardware. Based on this understanding, the essence of the above technical solution or the part that contributes to the prior art can be embodied in the form of a software product. The computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, magnetic disk, optical disk, etc., and includes several instructions for causing a computer device (which can be a personal computer, a server, or a network device, etc.) to execute the methods of each embodiment or some parts of the embodiments.

[0097] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit them. Although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions recorded in the foregoing embodiments or perform equivalent replacements for some of the technical features. These modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for resisting fretting and fatigue of aero-engine tenons, characterized in that Based on a fretting test system, the fretting test system includes a tenon head simulation component and a loading test component. The two opposite sides of the tenon head simulation component in the width direction have fretting planes, and the loading test component is used to apply a fatigue load to the tenon head simulation component; the method includes: Performing multiple strengthening treatments on the tenon head simulation component to obtain multiple tenon head strengthened test pieces; the multiple strengthening treatments include laser shock peening, shot peening, and a combination of shot peening and laser shock peening; Applying a preset fatigue load to the multiple tenon head strengthened test pieces through the loading test component to obtain fretting fatigue data corresponding to the multiple tenon head strengthened test pieces; Based on the fretting fatigue data, when the actual load amplitude is less than the target load amplitude, determining shot peening as the target anti-fretting fatigue treatment method, and when the actual load amplitude is greater than the target load amplitude, determining the combination of shot peening and laser shock peening as the target anti-fretting fatigue treatment method.

2. The anti-fretting and anti-fatigue method for the tenon of an aeroengine according to claim 1, wherein The loading test component includes a first clamping member and a second clamping member arranged oppositely along the length direction of the tenon head simulation component. The first clamping member is used to clamp the tenon head simulation component. The second clamping member has a clamping portion located outside the fretting plane. The clamping portion has a receiving groove, and the receiving groove has a contact member that abuts against the fretting plane.

3. The method for resisting fretting and fatigue of an aero-engine tenon according to claim 2, wherein, The first clamping member has a first positioning portion, and the second clamping member has a second positioning portion. The centerlines of the first positioning portion and the second positioning portion coincide.

4. The method for resisting fretting and fatigue of an aero-engine tenon according to claim 2, characterized in that The dimensions of the clamping portion and the contact member in the thickness direction of the tenon head simulation component are greater than the thickness of the tenon head simulation component, and the tenon head simulation component abuts against the middle of the contact member.

5. The method for resisting fretting and fatigue of an aeroengine tenon according to claim 2, characterized in that, The contact member includes a flat surface and arc surfaces located on both sides of the flat surface, and the flat surface abuts against the fretting plane.

6. The method for resisting fretting and fatigue of aeroengine tenons according to any one of claims 1 to 5, characterized in that After obtaining the fretting fatigue data corresponding to the multiple tenon head strengthened test pieces, the method further includes: Based on the fretting fatigue data corresponding to the multiple tenon head strengthened test pieces, obtaining a relationship curve between the fretting fatigue life and the load amplitude corresponding to the multiple tenon head strengthened test pieces; Determining the load amplitude corresponding to the intersection point with the maximum fretting fatigue life among the intersection points of the multiple relationship curves as the target load amplitude.

7. The method for resisting fretting and fatigue of an aero-engine tenon according to any one of claims 2 to 5, characterized in that, Before performing the multiple strengthening treatments on the tenon head simulation component, the method further includes: Polishing the contact surface between the tenon head simulation component and the contact member.

8. The method for resisting fretting and fatigue of an aero-engine tenon according to any one of claims 2 to 5, characterized in that, One end of the tenon head simulation component in the length direction has a mounting portion for connecting with the first clamping member. The other end of the tenon head simulation component in the length direction has a test portion. The width of the test portion gradually increases from one end close to the mounting portion to the end far from the mounting portion, and the side surface of the test portion constitutes the fretting plane.

9. An electronic device, comprising a memory, a processor, and a computer program stored on the memory and executable on the processor, characterized in that, When the processor executes the computer program, it implements the method for anti-fretting and anti-fatigue of an aero-engine tenon head as described in any one of claims 1 to 8.

10. A non-transitory computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by the processor, it implements the method for anti-fretting and anti-fatigue of an aero-engine tenon head as described in any one of claims 1 to 8.

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