Non-destructive disassembly method and non-destructive disassembly device for liquid rocket engine rotor

Abstract

The present invention relates to the technical field of liquid rocket engine assembly, and in particular to a non-destructive decomposition method and device for a liquid rocket engine rotor. The non-destructive decomposition method comprises the following steps: step 1: preparing a comparative test piece based on a part to be decomposed that is heated as required; calculating the decomposition temperature of the part to be decomposed; step 2: providing instantaneous heat to the comparative test piece while measuring the real-time temperature of the comparative test piece; upon detecting that the surface temperature of the comparative test piece reaches the decomposition temperature, cutting off the heat source and separating the comparative test piece from the interference fit portion on the shaft; determining the decomposition parameters of the comparative test piece; step 3: providing instantaneous heat to the part to be decomposed and measuring the real-time temperature of the part to be decomposed based on the decomposition parameters determined in step 2; stopping the heat supply upon detecting that the temperature of the part to be decomposed reaches the decomposition temperature; and completing the non-destructive decomposition of the part to be decomposed and the shaft. The present invention can ensure more precise control of the heating process during rotor decomposition and guarantee the surface quality of the interference fit after decomposition.

Description

Technical Field

[0001] The present invention relates to the technical field of liquid rocket engine assembly, in particular to a non-destructive disassembly method and a non-destructive disassembly device for a liquid rocket engine rotor. Background Art

[0002] During high-speed rotation of the rotor of a high-thrust liquid rocket engine, centrifugal force can cause deformation and loosening of shafting components such as the inducer and centrifugal wheel, leading to vibration and friction, accelerated bearing wear, and reduced engine reliability. To effectively control rotor loosening during operation, most rotor assembly structures use an interference fit structure. By selecting a reasonable interference fit of 0.01-0.08mm, the loosening speed is controlled within a safe range. Before assembling a rocket engine, the shafting components must be assembled into a rotor and subjected to an overall dynamic balancing test. Only after passing the test can the rotor be disassembled for formal assembly. Therefore, the rotor interference fit structure must be both installable and removable. Currently, the disassembly of interference fit parts is mostly performed using impact methods, static pressure drawing methods, hydraulic methods, etc., which are time-consuming and labor-intensive, and can cause damage such as furrows and scratches on the interference fit contact surface, seriously restricting the assembly accuracy and reusable service life of the rotor.

[0003] Currently, most of the interference-fit shaft parts are non-destructively decomposed using the temperature difference method. For example, the invention patent with publication number CN108110966 discloses a method for disassembling a shaft assembly, which completes the non-destructive decomposition of the shaft assembly by heating and liquid nitrogen. The invention patent with publication number CN106624743 discloses a device for disassembling interference-fit parts on a shaft, which uses ultrasonic vibration and a puller to complete the disassembly and decomposition of the parts. The invention patent with publication number CN106736238 discloses a method for disassembling an interference-fitted hollow shaft, which uses liquid nitrogen and a hot air gun to complete the decomposition of the interference-fitted hollow shaft. The invention patent with publication number CN104368954 discloses a method for disassembling a nickel-based high-temperature alloy ring part after interference assembly, which completes the decomposition of the nickel-based high-temperature alloy ring part of an aircraft engine after interference assembly by heating and liquid nitrogen.

[0004] The above methods are relatively simple, mostly regular rotating parts. However, the inducer on a liquid rocket engine rotor is a hollow hub with uniformly spaced blades. Its inner bore forms an interference fit with the shaft. These methods have been tried and failed to meet the requirements for nondestructive disassembly. Therefore, how to quickly and efficiently separate the interference fit of the inducer has become an urgent problem in this field. Summary of the Invention

[0005] The technical problem to be solved by the present invention is to overcome the above-mentioned shortcomings of the prior art and provide a non-destructive decomposition method and non-destructive decomposition device for a liquid rocket engine rotor, so as to achieve non-destructive, rapid and efficient separation of the rotor.

[0006] To solve the above technical problems, the technical solution of the present invention is: a non-destructive decomposition method of a liquid rocket engine rotor, comprising the following steps:

[0007] Step 1: Prepare comparative test pieces based on the parts to be decomposed that need to be heated;

[0008] Calculate the decomposition temperature of the parts to be decomposed;

[0009] Step 2: Use a non-destructive disassembly device to support the comparison test piece and the shaft in an interference fit state;

[0010] Provide instantaneous heat to the comparative test piece and measure the real-time temperature of the comparative test piece at the same time;

[0011] When it is detected that the surface temperature of the comparative test piece reaches the decomposition temperature, the heat source is quickly cut off and the comparative test piece is separated from the interference fit portion on the shaft;

[0012] Determine the decomposition parameters of the comparison test piece;

[0013] Step 3: Use a non-destructive disassembly device to support the parts to be disassembled and the shaft in an interference fit state;

[0014] According to the decomposition parameters determined in step 2, instantaneous heat is provided to the part to be decomposed and the real-time temperature of the part to be decomposed is measured;

[0015] When it is detected that the temperature of the part to be decomposed reaches the decomposition temperature, the heating supply is stopped;

[0016] The parts and shafts to be disassembled are disassembled non-destructively.

[0017] In the above-mentioned non-destructive decomposition method of the liquid rocket engine rotor, in step one, the material and the interference contact inner hole wall thickness of the comparison test piece are the same as those of the part to be decomposed, ensuring that the heating parameters are consistent during decomposition.

[0018] In the above-mentioned non-destructive disassembly method of the liquid rocket engine rotor, in step three, when non-destructively disassembling the parts to be disassembled and the shaft, a process limit sleeve is set on the lower side of the parts to be disassembled, and the supporting surface of the process limit sleeve maintains a set distance from the parts to be disassembled, and the set distance is greater than the fitting size of the interference contact inner hole of the parts to be disassembled and the shaft.

[0019] In the above-mentioned non-destructive disassembly method of the liquid rocket engine rotor, in steps 2 and 3, a high-frequency electromagnetic induction heater is used for heating; a flexible cable is connected to the cable interface of the high-frequency electromagnetic induction heater, and the flexible cable is wrapped and fixed along the outer side of the part to be disassembled or the comparison test piece; after the high-frequency electromagnetic induction heater is started, a strong eddy current is generated inside the induction coil, causing the temperature of the surrounded part to be disassembled or the comparison test piece to rise rapidly.

[0020] A non-destructive disassembly device for implementing the above-mentioned non-destructive disassembly method for a liquid rocket engine rotor comprises a rotor disassembly platform, a heating component, and a temperature measuring component;

[0021] The rotor disassembly platform is used to support the rotor, and includes a base, an operating table, a positioning seat, a column, a crossbeam, and a clamping ring; the operating table and the positioning seat are both fixed to the base, the positioning seat is located on the lower side of the operating table, and is used to limit the lower end of the rotating shaft; the operating table is provided with a through hole at a position opposite the positioning seat for the rotating shaft to pass through; the column is fixed to the operating table, and the crossbeam is detachably mounted on the column; the clamping ring is composed of two symmetrically arranged half rings, one end of the half ring is rotatably connected to the crossbeam, and the other end is connected to each other to form a radial limiting hole, which is used to limit the upper end of the rotating shaft;

[0022] The heating component includes a high-frequency induction heater and a flexible cable, wherein the flexible cable is connected to the cable interface of the high-frequency induction heater to form a loop;

[0023] The temperature measuring component includes a thermocouple, a wire, a wiring plug and a data acquisition board. One end of the wire is connected to the thermocouple, and the other end is connected to the temperature measuring component interface of the data acquisition board through the wiring plug. The data acquisition board sends the acquired temperature information to the controller of the high-frequency induction heater and displays it on a display screen.

[0024] In the above-mentioned non-destructive decomposition device, the rotor decomposition platform also includes a support rod, which is fixedly connected to the base and the operating table; the base, operating table, positioning seat, support rod, and column are welded to form an integral component; the upper end of the column is provided with a shaft neck, and the outer circumferential surface of the shaft neck is provided with a thread, and the shaft neck is threadedly connected to the nut to fix and support the crossbeam.

[0025] In the above-mentioned non-destructive decomposition device, the rotor decomposition platform also includes a process limiting sleeve, which is tubular. When in use, the process limiting sleeve is located on the lower side of the part to be decomposed and is used to support the part to be decomposed after decomposition.

[0026] In the above-mentioned non-destructive decomposition device, an internal thread is provided in the process limiting sleeve for threaded connection with the rotor.

[0027] In the above-mentioned non-destructive decomposition device, the temperature measuring component also includes a measuring rod and a measuring handle. The measuring rod is fixedly arranged at one end of the measuring handle, and the wire passes through the inner cavity of the measuring rod and the measuring handle; the thermocouple is fixed on the head of the measuring rod.

[0028] In the above-mentioned non-destructive decomposition device, the heating component also includes a measuring component holder and a cable fixing clamp; the cable fixing clamp is used to fix the flexible cable after it is wrapped; the measuring component holder is fixed to the high-frequency induction heater housing by a threaded connection, and is used to fix the measuring handle.

[0029] Compared with the prior art, the non-destructive disassembly method and non-destructive disassembly device of a liquid rocket engine rotor of the present invention has the following advantages:

[0030] (1) The induction heating cable has good flexibility and can be tightly wound along the contour of the part. It has a strong "skin effect", a high heater induction frequency, a thick cable diameter, and high heating efficiency. The heat-resistant rubber wrapped around the cable sheath has a high temperature resistance and can be used for a long time at 250°C without aging, making it safe to operate and use.

[0031] (2) It can be used for parts with irregular shapes to be disassembled. By applying the principle of high-frequency induction heating, an electromagnetic induction coil is wound along the parts to be disassembled to generate strong eddy currents, which rapidly increase the temperature of the parts to be disassembled, causing the interference contact inner hole to expand and become larger. The interference contact area between the rotor and the inducer can be separated without disassembly force, meeting the requirements for non-destructive disassembly of parts when the liquid rocket engine rotor is repeatedly disassembled and assembled.

[0032] (3) A temperature measuring component is set outside the induction heater to provide real-time feedback on the heating temperature of the parts, making the induction temperature control more accurate.

[0033] (4) Compared with the impact method and the static pressure drawing method, the non-destructive rotor disassembly method does not require the production of special drawing tooling during the disassembly process, and does not require the application of disassembly force in the axial direction. It only needs to wind the coil and fix it. It can disassemble the interference-fitted shaft system parts on the rotor intactly without damaging the interference-fitted contact interface, with low labor intensity, and improve work efficiency and operation safety.

[0034] (5) Compared with the induction heating decomposition method of regular parts (bearing inner ring, shaft sleeve, etc.), the rotor non-destructive decomposition method has a wider range of applications and is more flexible in application. The coil can be wound close to the part surface, and the number of coil turns and radius can be adjusted.

[0035] (6) Compared with the traditional induction heating method, the rotor non-destructive decomposition method makes comparison test pieces and determines the parameters before heating decomposition, which ensures more precise control of the heating process during rotor decomposition, prevents overheating, and ensures the surface quality of the interference fit after decomposition. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Figure 1 It is a schematic diagram of the three-dimensional structure of the liquid rocket engine rotor non-destructive disassembly device;

[0037] Figure 2 This is the front view of the liquid rocket engine rotor non-destructive disassembly device;

[0038] Figure 3 It is a structural diagram of the rotor decomposition platform;

[0039] Figure 4It is a schematic diagram of the assembly structure of the beam and the column, and the clamp and the beam;

[0040] Figure 5 It is a structural diagram of a high-frequency induction heater and a cable fixing clamp;

[0041] Figure 6 This is a schematic diagram of the back structure of the high-frequency induction heater;

[0042] Figure 7 It is a structural diagram of the temperature measuring component.

[0043] In the picture:

[0044] 1-Rotor disassembly platform; 1-1-Base; 1-2-Operating table; 1-3-Positioning seat; 1-4-Support rod; 1-5-Column; 1-6-Crossbeam; 1-7-Snap ring; 1-8-Process limit sleeve; 1-9-Connecting bolt; 1-10-Limit screw; 1-11-Nut;

[0045] 2-Heating component; 2-1-High-frequency induction heater; 2-2-Display screen; 2-3-Control buttons; 2-4-Cable interface; 2-5-Flexible cable; 2-6-Cable fixing clamp; 2-7-Measuring component tray; 2-8-Temperature measuring component interface; 2-9-Handle; 2-10-Cooling fan; 2-11-Power cord;

[0046] 3-temperature measuring component; 3-1-thermocouple; 3-2-measuring rod; 3-3-measuring handle; 3-4-lead wire; 3-5-connection plug;

[0047] 4-rotor; 4-1-centrifugal wheel; 4-2-inducer wheel. DETAILED DESCRIPTION

[0048] The present invention will be further described below in conjunction with the embodiments.

[0049] like Figure 1 As shown, a liquid rocket engine rotor 4 includes a rotating shaft, a centrifugal wheel 4-1, and an inducer wheel 4-2, which are interference-fitted with the rotating shaft. The non-destructive disassembly method and apparatus for a liquid rocket engine rotor proposed in this invention are suitable for repeated assembly and disassembly of a liquid rocket engine rotor 4. This method achieves non-destructive disassembly without disassembly force by allowing the centrifugal wheel 4-1 or inducer wheel 4-2 to rapidly expand and elastically deform the disassembled parts.

[0050] The non-destructive disassembly method for a liquid rocket engine rotor includes the following steps:

[0051] Step 1: Create a comparison test piece based on the part to be decomposed. This piece should be made of the same material and have the same interference fit inner wall thickness as the part to be decomposed, ensuring consistent heating parameters during decomposition. Optimally, the comparison test piece should be identical in structure and material to the part to be decomposed.

[0052] Calculate the decomposition temperature, that is, calculate the heating temperature required for the decomposition of the parts to be decomposed; calculate and select the limits and interference fits according to the national standard GB-T 5371-2004, and use the temperature difference method.

[0053] Step 2: Use a non-destructive disassembly device to support the comparison test piece and the shaft in an interference fit state;

[0054] Provide instantaneous heat to the comparative test piece and measure the real-time temperature of the comparative test piece at the same time;

[0055] When it is detected that the temperature of the comparative test piece reaches the decomposition temperature, the heat source is quickly cut off and the comparative test piece is separated from the interference fit portion on the shaft;

[0056] Determine the decomposition parameters of the comparison test piece.

[0057] Step 3: Use a non-destructive disassembly device to support the parts to be disassembled and the shaft in an interference fit state;

[0058] According to the decomposition parameters determined in step 2, instantaneous heat is provided to the part to be decomposed and the real-time temperature of the part to be decomposed is measured;

[0059] When it is detected that the temperature of the part to be decomposed reaches the decomposition temperature, the heating is stopped. The time delay shall not exceed 3s to ensure that the decomposition part is not overheated;

[0060] The parts and shafts to be disassembled are disassembled non-destructively.

[0061] In steps 2 and 3, the high-frequency electromagnetic induction heater 2-1 is used to heat the reference test piece and the part to be disassembled. Specifically, a flexible cable 2-5 is connected to the cable interface 2-4 of the high-frequency electromagnetic induction heater 2-1. The flexible cable 2-5 is wrapped around the outer surface of the part to be disassembled and secured by a cable clamp 2-6. The high-frequency electromagnetic induction heater 2-1 is activated to heat the part to be disassembled or the reference test piece, generating strong eddy currents within the induction coil, causing the temperature of the surrounded part to be disassembled or the reference test piece to rise rapidly.

[0062] The decomposition parameters to be determined include the heating temperature, heating time, the number of turns of the flexible cable 2-5, and the operating parameters of the high-frequency electromagnetic induction heater 2-1, such as power and rated current. For a non-destructive decomposition device, the operating parameters of the high-frequency electromagnetic induction heater 2-1 are generally fixed, so only the heating temperature, heating time, and number of turns need to be recorded. The number of turns of the flexible cable 2-5 is positively correlated with the interference fit, material, and thickness of the comparison test piece. The heating time and temperature can be changed by adjusting the number of turns. For example, when the wall thickness of the interference fit surface of the part to be decomposed is 10-20mm, the maximum power of the heating component is 20kW, the rated current is 30A, the number of turns of the flexible cable 2-5 is 2-3, the heating time is 8-15s, and the heating temperature is 90-120°C. When using the high-frequency electromagnetic induction heater 2-1 to provide decomposition heat, the number of turns, heating time, and heating temperature must be set to the same for the comparison test piece and the part to be decomposed.

[0063] In step three, when non-destructively decomposing the parts to be decomposed and the shaft, while ensuring that the parts to be decomposed have sufficient blanking space, in order to avoid damage to the parts to be decomposed during blanking, a process limit sleeve 1-8 is set on the lower side of the parts to be decomposed. The process limit sleeve 1-8 can be sleeved on the outside of the shaft, or can be distributed on the outside of the shaft in a point-like manner; the support surface at the upper end of the process limit sleeve 1-8 maintains a set distance from the parts to be decomposed, and the set distance can be set according to the axial size of the interference contact inner hole of the parts to be decomposed, and can be larger than the fitting and assembly size of the interference contact inner hole and the shaft, to ensure that the interference fit surface is completely separated after heating and expansion to prevent it from being tightened again during cooling.

[0064] The non-destructive decomposition device includes a rotor decomposition platform 1, a heating component 2, and a temperature measuring component 3. The rotor decomposition platform 1 is secured to the rotor 4 via axial and circumferential restraints, providing stable support when the rotor 4 is erected and preventing the centrifugal wheel 4-1 and inducer wheel 4-2 from falling after decomposition. The heating component 2 heats the parts to be decomposed, while the temperature measuring component 3 measures the temperature of the parts in real time and provides feedback.

[0065] like Figure 2 and Figure 3As shown, the rotor disassembly platform 1 includes a base 1-1, an operating table 1-2, a positioning seat 1-3, a support rod 1-4, a column 1-5, a crossbeam 1-6, a retaining ring 1-7, a process limit sleeve 1-8, a connecting bolt 1-9, a limit screw 1-10, a nut 1-11, etc. Among them, the base 1-1, the operating table 1-2, the positioning seat 1-3, the support rod 1-4, and the column 1-5 are welded to form an integral component. The operating table 1-2 is located on the upper side of the base 1-1 and is fixedly mounted on the upper side of the base 1-1 by multiple support rods 1-4. The operating table 1-2 is spaced apart from the base 1-1, and there is a certain space between the two. The operating table 1-2 is provided with a through hole for the rotating shaft to pass through, and the positioning seat 1-3 is located on the lower side of the through hole. The positioning seat 1-3 is fixedly mounted on the base 1-1.

[0066] Column 1-5 is fixed to operating table 1-2 and extends vertically above it. Column 1-5 is located to one side of the through-hole, avoiding the installation space for rotor 4. Crossbeam 1-6 is connected to column 1-5 via nut 1-11. Specifically, a journal is provided at the upper end of column 1-5, with threads formed on its circumferential surface. This journal is threadedly engaged with nut 1-11, securing and supporting crossbeam 1-6.

[0067] The snap ring 1-7 is composed of two symmetrical half rings, one end of the half ring is connected to the crossbeam 1-6 through a limit screw 1-10, and the other end is connected to the two open snap rings 1-7 by a connecting bolt 1-9 to form a radial limit hole.

[0068] The process limit sleeve 1-8 is tubular, with an inner diameter larger than the outer diameter of the rotating shaft and an outer diameter smaller than the outer diameter of the part to be disassembled; when in use, the process limit sleeve 1-8 is located on the lower side of the part to be disassembled, forming an axial limit when the part to be disassembled is disassembled, preventing the part to be disassembled from falling after disassembly.

[0069] Among them, the process limit sleeve 1-8 can be placed on the operating table 1-2, and can also be detachably installed on the operating table 1-2. The external thread on the rotating shaft can also be used, and the internal thread is set in the process limit sleeve 1-8 to be threadedly connected with the rotor 4.

[0070] The material of the process limit sleeves 1-8 can be the same as the parts to be decomposed, or a rubber sleeve, a plastic sleeve, etc. can be selected, and the material with a lower hardness than the parts to be decomposed is preferred.

[0071] like Figure 4 、 5As shown in Figure 6, the heating component 2 includes a high-frequency induction heater 2-1, a flexible cable 2-5, a measuring component holder 2-7, a cable fixing clamp 2-6, and a temperature measuring component interface 2-8. Among them, the high-frequency induction heater 2-1 has a display screen 2-2, a control button 2-3, a cable interface 2-4, a handle 2-9, a cooling fan 2-10, and a power cord 2-11. This is the prior art. The flexible cable 2-5 is connected to the cable interface 2-4 to form a loop. When in use, the flexible cable 2-5 is wound around the part to be decomposed to form an induction coil. When the high-frequency induction heater 2-1 is started, a strong eddy current is generated inside the induction coil, causing the temperature of the surrounded part to be decomposed to rise rapidly. The cable fixing clamp 2-6 is used to fix the flexible cable 2-5 after it is wound.

[0072] like Figure 6 As shown, the measuring component holder 2-7 is fixed to the housing of the high-frequency induction heater 2-1 by a threaded connection; the temperature measuring component interface 2-8 is located on the back of the high-frequency induction heater 2-1.

[0073] like Figure 7 As shown, the temperature measurement component 3 includes a thermocouple 3-1, a measuring rod 3-2, a measuring handle 3-3, a wire 3-4, and a wiring plug 3-5. The measuring rod 3-2 is fixed at one end of the measuring handle 3-3, and the wire 3-4 passes through the inner cavities of the measuring rod 3-2 and the measuring handle 3-3. One end of the metal sheet of the thermocouple 3-1 is welded to the inner side of the housing at the head of the measuring rod 3-2, and the other end is welded to the wire 3-4 to form a temperature measurement circuit. The wire 3-4 is connected to the wiring plug 3-5, which is connected to the temperature measurement component interface 2-8 on the high-frequency induction heater 2-1. The wiring plug 3-5 transmits the resistance change signal to the data processing board on the high-frequency induction heater 2-1. The process by which the data processing board acquires the signal from the thermocouple 3-1, converts it into temperature data, and displays it on the display 2-2 is existing technology. The inventors have simply adapted this process for use in the non-destructive decomposition device. When the rubber wrapped around the flexible cable 2-5 is flame-retardant and high-temperature resistant fluororubber, the safe tolerance temperature is 280°C. At this time, the maximum temperature detected by the temperature measuring component 3 shall not exceed 250°C.

[0074] When the non-destructive decomposition device is not in operation, the measuring handle 3-3 is located on the measuring component holder 2-7. During use, the measuring handle 3-3 is held against the temperature measuring contacts on the thermocouple 3-1 to measure the part to be decomposed. The thermocouple 3-1 contacts the surface of the part to be decomposed and is connected to the temperature measuring component interface 2-8 on the high-frequency induction heater 2-1 via a wire 3-4 and a wiring plug 3-5. The data processing board on the high-frequency induction heater 2-1 receives the resistance change signal from the thermocouple 3-1, processes the data, and transmits the real-time temperature value to the display 2-2.

[0075] In the above-mentioned liquid rocket engine rotor non-destructive disassembly device, the rotor disassembly platform 1 axially limits the rotor 4 through the positioning seat 1-3, and radially fixes it through the retaining ring 1-7 at the upper end, providing stable support for the rotor 4 when it is erected; the process limit sleeve 1-8 provides axial limiting protection for the parts to be disassembled to prevent the parts from falling and causing collisions after disassembly. The heating component 2 provides instantaneous heat to the parts to be disassembled through the high-frequency electromagnetic induction heater 2-1 and the flexible cable 2-5, causing the inner hole of the interference contact to expand and enlarge, thereby separating the interference contact parts from each other; the temperature measuring component 3 contacts the parts to be disassembled through the contact thermocouple 3-1, obtains real-time data when the parts to be disassembled are heated, and transmits the data to the data processing board in the heating component 2, thereby displaying the real-time temperature on the display screen 2-2.

[0076] The application of the liquid rocket engine rotor non-destructive disassembly device to disassemble the inducer 4-2 includes the following steps:

[0077] Step 1: Prepare a comparative test piece of the inducer 4-2 that requires induction heating;

[0078] First, a comparative test piece is made with reference to the material of inducer 4-2 and the wall thickness of the interference contact inner hole. The comparative test piece is made of the same material GH4061 as inducer 4-2 and has a wall thickness of 15mm for the interference contact inner hole to ensure that the comparative test piece has the same structure as the part to be heated of inducer 4-2.

[0079] Calculate the decomposition temperature of inducer 4-2, that is, the heating temperature required for decomposition of inducer 4-2; calculate using the temperature difference method based on the calculation and selection of limits and interference fits in the national standard GB-T5371-2004.

[0080] Step 2: Use high-frequency induction heater 2-1 to heat the comparison test piece and record the heating parameters;

[0081] Wrap the flexible cable 2-5 around the outer ring of the comparative test piece 2-3 times, and fix both ends of the flexible cable 2-5 to the cable interface 2-4 of the high-frequency induction heater 2-1. Place the thermocouple 3-1 of the temperature measuring component 3 close to the end face of the comparative test piece.

[0082] Set the high-frequency induction heater 2-1 to a maximum input power of 20KW, a maximum input current of 30A, a rated output power of 20KW, and an output frequency range of 18-50KHZ;

[0083] Turn on the power of high-frequency induction heater 2-1 to heat the comparison test piece. The heating temperature is set to a maximum of 120°C and the heating time is set to a maximum of 15 seconds. Start heating component 2.

[0084] When the test temperature of the comparison test piece is close to the theoretically calculated decomposition temperature, the power supply of the high-frequency induction heater 2-1 is cut off, and the actual heating temperature and heating time are recorded as the heating parameters when the inducer 4-1 decomposes.

[0085] Step 3: Decompose the inducer 4-2 according to the decomposition parameters determined in step 2.

[0086] The rotor 4 is fixed vertically on the rotor disassembly platform 1, and the process limit sleeve 1-8 is tightened on the rotor 4, and the flexible cable 2-5 is wound along the surface of the inducer 4-2 and fixed;

[0087] Then, adjust the heating temperature and heating time by using the control button 2-3 of the high-frequency induction heater 2-1, and start the heating component 2; at the same time, place the thermocouple 3-1 of the temperature measuring component 3 close to the end face of the inducer, and observe the real-time temperature on the display screen 2-2;

[0088] After the heating temperature reaches the decomposition temperature, the power is quickly cut off, and the inducer 4-2 is separated from the interference fit portion on the shaft and fits into the process limit sleeve 1-8.

[0089] After the disassembly is completed, the wound flexible cable 2-5 is removed from the inducer 4-2, the process limit sleeve 1-8 is loosened and the inducer 4-2 is taken out.

[0090] The above-mentioned non-destructive disassembly device can also be used in similar interference fit structures, and is not limited to interference fit rotors of liquid rocket engines.

[0091] Although the present invention has been disclosed above in terms of preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solutions of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the scope of protection of the technical solutions of the present invention.

[0092] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

Claims

1. A non-destructive disassembly method for a liquid rocket engine rotor, characterized in that: The following steps are involved: Step 1: Prepare comparative test pieces based on the parts to be decomposed that need to be heated; Calculate the decomposition temperature of the parts to be decomposed; Step 2: Use a non-destructive disassembly device to support the comparison test piece and the shaft in an interference fit state; Provide instantaneous heat to the comparative test piece and measure the real-time temperature of the comparative test piece at the same time; When it is detected that the surface temperature of the comparative test piece reaches the decomposition temperature, the heat source is quickly cut off and the comparative test piece is separated from the interference fit portion on the shaft; Determine the decomposition parameters of the comparison test piece; Step 3: Use a non-destructive disassembly device to support the parts to be disassembled and the shaft in an interference fit state; According to the decomposition parameters determined in step 2, instantaneous heat is provided to the part to be decomposed and the real-time temperature of the part to be decomposed is measured; When it is detected that the temperature of the part to be decomposed reaches the decomposition temperature, the heating supply is stopped; The parts and shafts to be disassembled are disassembled without loss; The non-destructive decomposition device comprises a rotor decomposition platform (1), a heating component (2), and a temperature measuring component (3); The rotor disassembly platform (1) is used to support the rotor (4), and includes a base (1-1), an operating table (1-2), a positioning seat (1-3), a column (1-5), a crossbeam (1-6), and a snap ring (1-7); the operating table (1-2) and the positioning seat (1-3) are both fixed on the base (1-1), the positioning seat (1-3) is located on the lower side of the operating table (1-2), and is used to limit the lower end of the rotating shaft; a through hole is provided at a position of the operating table (1-2) facing the positioning seat (1-3), and is used to allow the rotating shaft to pass through; the column (1-5) is fixed on the operating table (1-2), and the crossbeam (1-6) is detachably mounted on the column (1-5); the snap ring (1-7) is composed of two symmetrically arranged half rings, one end of the half ring is rotatably connected to the crossbeam (1-6), and the other end is connected to each other to form a radial limiting hole, which is used to limit the upper end of the rotating shaft; The heating component (2) comprises a high-frequency electromagnetic induction heater (2-1) and a flexible cable (2-5), wherein the flexible cable (2-5) is connected to a cable interface (2-4) of the high-frequency electromagnetic induction heater (2-1) to form a loop; The temperature measuring component (3) comprises a thermocouple (3-1), a wire (3-4), a wiring plug (3-5) and a data acquisition board. One end of the wire (3-4) is connected to the thermocouple (3-1), and the other end is connected to the temperature measuring component interface (2-8) of the data acquisition board via the wiring plug (3-5). The data acquisition board sends the acquired temperature information to the controller of the high-frequency electromagnetic induction heater (2-1) and displays it via the display screen (2-2).

2. The non-destructive disassembly method of a liquid rocket engine rotor according to claim 1, characterized in that: In step 1, the material and the wall thickness of the interference contact inner hole of the comparison test piece are the same as those of the part to be decomposed.

3. The non-destructive disassembly method of a liquid rocket engine rotor according to claim 2, characterized in that: In step three, when the part to be decomposed and the shaft are decomposed non-destructively, a process limit sleeve (1-8) is set on the lower side of the part to be decomposed, and the supporting surface of the process limit sleeve (1-8) maintains a set distance with the part to be decomposed, and the set distance is greater than the matching size of the interference contact inner hole of the part to be decomposed and the shaft.

4. The non-destructive disassembly method of a liquid rocket engine rotor according to claim 1, characterized in that: In steps 2 and 3, a high-frequency electromagnetic induction heater (2-1) is used for heating; a flexible cable (2-5) is connected to a cable interface (2-4) of the high-frequency electromagnetic induction heater (2-1), and the flexible cable (2-5) is wound along the outer side of the part to be decomposed or the comparison test piece and fixed; after the high-frequency electromagnetic induction heater (2-1) is started, an eddy current is generated inside the induction coil, causing the temperature of the surrounded part to be decomposed or the comparison test piece to rise rapidly.

5. The non-destructive disassembly method of a liquid rocket engine rotor according to claim 1, characterized in that: The rotor disassembly platform (1) further comprises a support rod (1-4), wherein the support rod (1-4) is fixedly connected to the base (1-1) and the operating table (1-2); the base (1-1), the operating table (1-2), the positioning seat (1-3), the support rod (1-4), and the column (1-5) are welded to form an integral assembly; the upper end of the column (1-5) is provided with a shaft neck, the outer circumferential surface of the shaft neck is provided with a thread, the shaft neck is threadedly connected to the nut (1-11) and fixes and supports the crossbeam (1-6).

6. The non-destructive disassembly method of a liquid rocket engine rotor according to claim 1, characterized in that: The rotor disassembly platform (1) further comprises a process limiting sleeve (1-8), which is tubular. When in use, the process limiting sleeve (1-8) is located on the lower side of the part to be disassembled and is used to support the part to be disassembled after disassembly.

7. The non-destructive disassembly method of a liquid rocket engine rotor according to claim 6, characterized in that: An internal thread is provided in the process limiting sleeve (1-8) for threaded connection with the rotor.

8. The non-destructive disassembly method of a liquid rocket engine rotor according to claim 1, characterized in that: The temperature measuring component (3) further comprises a measuring rod (3-2) and a measuring handle (3-3); the measuring rod (3-2) is fixedly arranged at one end of the measuring handle (3-3); a lead (3-4) passes through the inner cavities of the measuring rod (3-2) and the measuring handle (3-3); and a thermocouple (3-1) is fixed to the head of the measuring rod (3-2).

9. The non-destructive disassembly method of a liquid rocket engine rotor according to claim 8, characterized in that: The heating component (2) further comprises a measuring component holder (2-7) and a cable fixing clamp (2-6); the cable fixing clamp (2-6) is used to fix the flexible cable (2-5) after being wound; the measuring component holder (2-7) is fixed to the housing of the high-frequency electromagnetic induction heater (2-1) by means of a threaded connection, and is used to fix the measuring handle (3-3).

Images