Design method for preventing bolt-free turbine rotor baffle from flying away
By obtaining the mating positions and key parameters of the boltless turbine rotor, constructing a real material constitutive model, performing finite element analysis, and optimizing the mating tolerances and dimensional parameters, the problem of boltless turbine rotor baffle slippage under high temperature and high speed environments was solved, ensuring engine safety.
Patent Information
- Application Number
- CN202511171000.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-08-21
- Publication Date
- 2025-10-21
AI Technical Summary
In high-temperature and high-speed environments, the working clearance between the baffle and the disc in boltless turbine rotors is unstable, which may cause the baffle to fly off, posing a risk of non-containment accidents.
By obtaining the mating positions and key parameters of the boltless turbine rotor, a real material constitutive model is constructed, finite element analysis is performed, and the mating tolerances and dimensional parameters are optimized to prevent baffle loss.
It effectively prevents boltless turbine rotor baffles from flying off, ensuring engine structural integrity and improving flight safety.
Smart Images
Figure CN120822288A_ABST
Abstract
Description
Technical Field
[0001] The invention relates to the technical field of aviation engines, in particular to a design method for preventing a boltless turbine rotor baffle from flying off. Background Art
[0002] like Figure 1 As shown in the figure, the current boltless turbine rotor for aircraft engines primarily consists of a front baffle, a turbine disc, a rear baffle, a front retaining ring, a rear retaining ring, and blades. The front and rear baffles primarily serve to axially position the blades and form a flow seal, forcing cooling air into the blade cavities along the designed flow path for cooling. The baffles and turbine disc utilize a boltless connection structure, with front and rear retaining rings ensuring stable axial and radial positioning of the baffles, preventing them from falling off.
[0003] Boltless turbine rotors are often operated in a high-temperature, high-speed environment. If the design is unreasonable, the baffle and the disc will deform uncoordinatedly under the action of temperature and centrifugal load, resulting in axial and radial working clearances. When the clearance is too large, the baffle and the disc cannot form a stable positioning, and the baffle will fly off.
[0004] As one of the key components of aircraft engines, the loss of the baffle often causes non-contained accidents, posing a huge hidden danger to flight safety. Therefore, it is necessary to design the boltless turbine rotor baffle to prevent loss in order to meet the structural integrity design requirements and ensure engine safety. Summary of the Invention
[0005] In view of this, the present invention provides a design method for preventing a boltless turbine rotor baffle from flying off.
[0006] The present invention discloses a design method for preventing a boltless turbine rotor baffle from flying off, which comprises: Step 1: Obtain the fitting positions and corresponding fitting tolerances between the components of the boltless turbine rotor; Step 2: Obtain key parameters that affect the loss of the front baffle in the boltless turbine rotor; Step 3: Construct the real material constitutive model of the boltless turbine rotor; Step 4: Calculate the displacement and working clearance of the boltless turbine rotor under normal working load; Step 5: Calculate the displacement and working clearance of the boltless turbine rotor under overspeed load; Step 6: Determine whether the front baffle of the boltless turbine rotor is missing; if the front baffle is missing, proceed to step 7; Step 7: Iterate steps 4 to 6 to optimize the fit tolerance in step 1 and the key parameters in step 2 to ensure that the front baffle of the boltless turbine rotor does not fly off.
[0007] Furthermore, the step 1 includes: The components of the boltless turbine rotor include a front baffle, a rear baffle, a front retaining ring, a rear retaining ring, working blades and a turbine disk; the fitting positions between the components of the boltless turbine rotor include the axial fitting position Z1 of the front baffle and the turbine disk, the axial fitting position Z2 of the front retaining ring and the disk, the axial fitting position Z3 of the front retaining ring and the front baffle, the radial fitting position J1 of the front baffle and the turbine disk, and the radial fitting position J2 of the front baffle and the front retaining ring, and the lower limit values of the fitting tolerance corresponding to each fitting position are obtained in turn: ⊿t1, ⊿t2, ⊿t3, ⊿t4, and ⊿t5.
[0008] Furthermore, the key parameters include the radial length p1 and axial thickness p2 of the web between the throat fillet of the turbine disc and the root fillet of the front hook of the turbine disc, the theoretical axial distance p3 from the front end face of the front retaining ring to the mating position Z2, the radial length p4 of the mating position Z2, the radial distance p5 from the bottom of the front retaining ring to the bottom of the front hook fillet of the turbine disc, the front axial distance p6 from the rear end of the front retaining ring to the turbine disc, and the axial length p7 of the mating position J2.
[0009] Furthermore, the step 3 includes: Step 31: Obtain the engineering full stress-strain curve OBCD of the material used for the turbine disk at the operating temperature according to the material data sheet. The stress at point B on the engineering full stress-strain curve OBCD corresponds to the yield strength of the material. , the strain becomes , , E is the elastic modulus and the slope of the OB segment of the engineering full stress-strain curve OBCD. The stress at point C corresponds to the ultimate strength of the material. , the strain becomes , the stress at point D corresponds to the fracture strength of the material , strain is elongation ; Step 32: Based on the engineering full stress-strain curve OBCD, construct the engineering full stress-strain curve OB'C'D' of the turbine disk sample in the same furnace. The stress at point B' on the engineering full stress-strain curve OB'C'D' corresponds to the yield strength of the turbine disk sample in the same furnace. , the strain becomes , The stress at point C' corresponds to the ultimate strength of the turbine disk sample in the same furnace: , the strain becomes , and same; Step 33: Convert the constructed engineering full stress-strain curve OB'C'D' into a true stress-strain curve OB''C''D''. The true stress-strain OB''C''D'' is the true material constitutive law at the operating temperature of the turbine disc. Step 34: By analogy with steps 31 to 33, the actual material constitutive model of the blades, front and rear baffles, and front and rear retaining rings at the operating temperature is obtained.
[0010] Furthermore, the step 32 includes: For the engineering full stress-strain curve OB'C'D', the curve between the B'C' segments conforms to the relationship shown in formula (1): (1) in,( , ) is a point on the BC segment of the engineering full stress-strain curve OBCD, is a point on segment B'C', ; For the engineering full stress-strain curve OB'C'D', the C'D' segment conforms to the relationship shown in formula (2): (2) in,( , ) is a point on the CD segment of the engineering full stress-strain curve OBCD, is a point on segment C'D', .
[0011] Furthermore, the step 33 includes: The true stress-strain curve OB''C''D'' conforms to the relationship shown in formula (3): (3) in, It is a point on the engineering full stress-strain curve OB'C'D', It is a point on the true stress-strain curve OB''C''D''.
[0012] Furthermore, the step 4 includes: Finite element analysis was performed on the boltless turbine rotor. A finite element model was constructed in the finite element software: the turbine disk and front and rear baffles were simulated using 2D axisymmetric elements, the blades and front and rear retaining rings were simulated using plane stress elements with thickness, and each mating position Z1 to Z3, J1, and J2 were simulated using contact standard elements. During the simulation, the mating tolerance was set, the radial displacement of the two mating surfaces corresponding to J2 was coupled, and the axial displacement of the two mating surfaces corresponding to Z2 and Z3 were coupled. Set the mesh properties of the finite element model. Input the true material constitutive values of the turbine disk, blades, front and rear baffles, and front and rear retaining rings obtained in step 3 into the finite element model. Input the material density and linear expansion coefficient. Input the operating speed and temperature load of each state under the typical engine load spectrum. Perform displacement and clearance analysis under each operating state. Analyze the radial displacement difference ⊿Ux1=Uxa-Uxb between the bottom a of the front retaining ring and the outer edge b of the front hook of the turbine disk during each acceleration process and load holding project. Obtain the maximum value ⊿Ux1max of the radial displacement difference ⊿Ux1. Analyze the working clearance ⊿Uz1 at the mating position Z1 and the working clearance ⊿Ux2 at the mating position J1 during each deceleration process. Obtain the maximum clearance value ⊿Uz1max of the working clearance ⊿Ux1 and the maximum clearance value ⊿Ux2max of the working clearance ⊿Ux2, respectively. Uxa is the radial displacement of the bottom a of the front retaining ring, and Uxb is the radial displacement of the outer edge b of the front hook of the turbine disk. The states include acceleration process, load holding project, and deceleration process.
[0013] Furthermore, the step 5 includes: Use the finite element model in step 4 to calculate the stress of the turbine disk at the highest steady state ; The following formula is used to calculate the boltless turbine rotor rupture speed: = (4) in, is the radial rupture speed of the turbine disk, rad / s; is the circumferential rupture speed of the turbine disk, rad / s; is the maximum steady-state operating speed of the boltless turbine rotor, rad / s; is the radial material utilization coefficient, is the circumferential material utilization coefficient, is the tensile strength of the material, MPa; is the average radial stress of the most dangerous section of the turbine disk, MPa; is the average circumferential stress of the turbine disk meridian surface, MPa; obtain the minimum rupture speed =min( , ); Analysis of the acceleration process "0- "The radial displacement difference ⊿Ux1'=Uxa'-Uxb' between the bottom a of the front retaining ring and the outer edge b of the turbine disc front hook is obtained, and the maximum value ⊿Ux1max' of the radial displacement difference ⊿Ux1' is obtained to analyze the deceleration process." -0” at the mating position Z1 of the mating working clearance ⊿Uz1' and the mating working clearance ⊿Ux2' at the mating position J1, respectively obtain the maximum clearance value ⊿Uz1max' of the mating working clearance ⊿Uz1' and the maximum clearance value ⊿Ux2max' of the mating working clearance ⊿Ux2'.
[0014] Further, the step 6 includes: If max(⊿Ux1max + ⊿t4 + ⊿t5, ⊿Ux1max' + ⊿t4 + ⊿t5, 2⊿Ux2max + 2⊿t4 + 2⊿t5, 2⊿Ux2max' + 2⊿t4 + 2⊿t5) < 1.5 p4 and max(⊿Uz1max + ⊿t1 + ⊿t2 + ⊿t3, ⊿Uz1max' + ⊿t1 + ⊿t2 + ⊿t3) < 1.5 p7, then the front baffle will not fly off, otherwise it will fly off.
[0015] Further, the step 7 includes: With p4 < p5, p3 < p6, > 1.22, ⊿t1~⊿t5 < N as the constraint conditions, the disc weight as the objective function, iterate steps 4 to 6, optimize the values of p1, p2, p4, p7, ⊿t1~⊿t5, and ensure that the structural parameters of the front retaining ring and the disc max(⊿Ux1max + ⊿t4 + ⊿t5, ⊿Ux1max' + ⊿t4 + ⊿t5, 2⊿Ux2max + 2⊿t4 + 2⊿t5, 2⊿Ux2max' + 2⊿t4 + 2⊿t5) < 1.5 p4 and max(⊿Uz1max + ⊿t1 + ⊿t2 + ⊿t3, ⊿Uz1max' + ⊿t1 + ⊿t2 + ⊿t3) < 1.5 p7, that is, ensure that the front baffle of the boltless turbine rotor does not fly off; N is the assembly requirement limit value; After the step 7, it further includes: using the method of steps 1 to 7 to ensure that the rear baffle of the boltless turbine rotor does not fly off.
[0016] Due to the adoption of the above technical solutions, the present invention has the following advantages: The present invention first obtains the true material constitutions of the baffle and the turbine disc, then based on the true material constitutions, uses finite element analysis to analyze the mating working clearance conditions of the baffle and the turbine disc under normal and abnormal working loads of the engine, and finally reasonably designs the mating tolerances and the dimensions of the turbine disc and the retaining ring on the basis of the clearance analysis to prevent the baffle of the boltless turbine rotor from flying off, thereby preventing the occurrence of non-inclusive accidents and ensuring flight safety. BRIEF DESCRIPTION OF THE DRAWINGS
[0017] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments described in the embodiments of the present invention. For ordinary technicians in this field, other drawings can also be obtained based on these drawings.
[0018] Figure 1 This is a schematic diagram of the structure of a boltless turbine rotor for an aircraft engine; Figure 2 Schematic diagram of the mating position of a boltless turbine rotor according to an embodiment of the present invention; Figure 3 Schematic diagram of key parameters affecting the loss of the front baffle according to an embodiment of the present invention; Figure 4 is a schematic diagram of a full stress-strain curve according to an embodiment of the present invention; Figure 5 Schematic diagram of the operating speed of each state under a typical load spectrum of an engine according to an embodiment of the present invention; Figure 6 The present invention is a flowchart of a design method for preventing a boltless turbine rotor baffle from flying off according to an embodiment of the present invention. DETAILED DESCRIPTION
[0019] The present invention will be further described with reference to the accompanying drawings and embodiments. The embodiments described are only a part of the embodiments of the present invention, not all of the embodiments. All other embodiments obtained by those skilled in the art should fall within the scope of protection of the embodiments of the present invention.
[0020] See also Figure 6 The present invention provides an embodiment of a design method for preventing a boltless turbine rotor baffle from flying off, which comprises: Step 1: Obtain the fitting tolerances of the boltless turbine rotor: Figure 2 As shown in the figure, the boltless turbine rotor fit mainly includes the axial fit position Z1 between the front baffle and the turbine disk, the axial fit position Z2 between the front retaining ring and the turbine disk, the axial fit position Z3 between the front retaining ring and the front baffle, the radial fit position J1 between the front baffle and the turbine disk, and the radial fit position J2 between the front baffle and the front retaining ring. The lower tolerance limit values ⊿t1~⊿t5 of the above fits are obtained in turn.
[0021] Step 2: Obtain the key parameters that affect the loss of the front baffle: Figure 3As shown, the main items to be obtained are the radial length p1 and axial thickness p2 of the web between the chamfer of the disc throat and the chamfer of the root of the front hook of the turbine disc, the theoretical axial distance p3 from the front end face of the front retaining ring to the fitting position Z2, the radial length p4 of the fitting position Z2, the radial distance p5 from the bottom of the front retaining ring to the bottom of the chamfer of the front hook of the turbine disc, the axial distance p6 from the rear end of the front retaining ring to the front of the turbine disc, and the axial length p7 of the fitting position J2.
[0022] Step 3: Construct the real material constitutive model of the boltless turbine rotor: Figure 4 As shown, first, the engineering full stress-strain curve OBCD of the material used for the turbine disk at the operating temperature is obtained according to the material data manual, where the stress at point B on the engineering full stress-strain curve OBCD corresponds to the yield strength of the material. , the strain becomes , , the elastic modulus E is the slope of the OB segment, and the stress at point C corresponds to the ultimate strength of the material , the strain becomes , the stress at point D corresponds to the fracture strength of the material , strain is elongation (elongation); secondly, the engineering full stress-strain curve OB'C'D' of the turbine disk sample in the same furnace is constructed based on the engineering full stress-strain curve OBCD, where the stress at point B' on the engineering full stress-strain curve OB'C'D' corresponds to the yield strength of the turbine disk sample in the same furnace , the strain becomes , The stress at point C' corresponds to the ultimate strength of the turbine disk sample in the same furnace: , the strain becomes and The same. For the engineering full stress-strain curve OB'C'D', the curve between the B'C' segments should conform to the following relationship (1): .........(1) In formula (1), ( , ) is a point on the BC segment of the engineering full stress-strain curve OBCD, is a point on segment B'C' .
[0023] For the engineering full stress-strain curve OB'C'D', the curve between the C'D' segments should conform to the following relationship (2): ..............................(2) In formula (2), ( , ) is a point on the CD segment of the engineering full stress-strain curve OBCD, is a point on segment C'D', .
[0024] Finally, the constructed engineering full stress-strain curve OB'C'D' is converted into the true stress-strain curve OB''C''D''. The true stress-strain curve OB''C''D'' should conform to the following relationship (3): ..............................(3) In formula (3) It is a point on the engineering full stress-strain curve OB'C'D', It is a point on the true stress-strain curve OB''C''D''; The OB''C''D'' obtained above is the true material constitutive model of the turbine disc at the operating temperature. The true material constitutive models of the same blades, front and rear baffles, and front and rear retaining rings at the operating temperature can be obtained by referring to this step.
[0025] Step 4: Calculate the displacement and working clearance of the boltless turbine rotor under normal working load, perform finite element analysis on the boltless turbine rotor, select the quadrilateral eight-node PLANE183 unit (grid property), simulate the turbine disk and front and rear baffles with 2D axisymmetric units, simulate the blades and front and rear retaining rings with plane stress units with thickness, simulate the mating positions Z1~Z3, J1, and J2 with contact standard units, set the tolerance to 0 during simulation, couple the radial displacement of the two mating surfaces of J2, and couple the axial displacement of the two mating surfaces of Z2 and Z3, enter the true material constitutive model of the turbine disk, blades, front and rear baffles, and front and rear retaining rings obtained in step 3, enter the material density and linear expansion coefficient, and enter Figure 5 The working speed of each state under the typical load spectrum of the engine is shown, and the displacement and clearance analysis of each working state is carried out. Figure 5 The radial displacement difference ⊿Ux1=Uxa-Uxb between the bottom a of the front retaining ring and the outer edge b of the front hook of the disc in each acceleration process 1 and the load protection project 2 is obtained, and the maximum value of the radial displacement difference ⊿Ux1⊿Ux1max is obtained. Figure 5 In each deceleration process 3, the matching working clearance ⊿Uz1 of Z1 and the matching working clearance ⊿Ux2 of J1 are obtained, and the maximum clearance value ⊿Uz1max of the matching working clearance ⊿Uz1 and ⊿Ux2max of the matching working clearance ⊿Ux2 are obtained respectively.
[0026] Step 5: Calculate the displacement and working clearance of the turbine rotor during overspeed. First, use the finite element model in step 4 to calculate the stress of the turbine disk under the highest working steady state. ; Secondly, the turbine rotor rupture speed is calculated using formula (4): = ……… ... in, is the radial rupture speed of the turbine disk, rad / s; is the circumferential rupture speed of the turbine disk, rad / s; is the maximum steady-state speed of the engine, rad / s; is the radial material utilization coefficient, is the circumferential material utilization coefficient, is the tensile strength of the material, MPa; is the average radial stress of the most dangerous section of the turbine disk, MPa; is the average circumferential stress of the turbine disk meridian surface, MPa; obtain the minimum rupture speed =min( , ); Finally, the analysis of the acceleration process "0- "The radial displacement difference ⊿Ux1'=Uxa'-Uxb' between the bottom a of the front retaining ring and the outer edge b of the front hook of the disc is obtained. The maximum value of the radial displacement difference ⊿Ux1'⊿Ux1max' is obtained to analyze the deceleration process." -0”, the fitting working clearance ⊿Uz1' of Z1 and the fitting working clearance ⊿Ux2' of J1 are obtained, and the maximum clearance value ⊿Uz1max' of the fitting working clearance ⊿Uz1' and ⊿Ux2max' of the fitting working clearance ⊿Ux2' are obtained respectively.
[0027] Step 6: Determine whether the front baffle is missing. If max(⊿Ux1max+⊿t4+⊿t5,⊿Ux1max'+⊿t4+⊿t5,2⊿Ux2max+2⊿t4+2⊿t5,2⊿Ux2max'+2⊿t4+2⊿t5)<1.5 p4 and max(⊿Uz1max+⊿t1+⊿t2+⊿t3,⊿Uz1max'+⊿t1+⊿t2+⊿t3)<1.5 If the front panel is not lost, go to step 7.
[0028] Step 7: Structural optimization, using parametric modeling, constructing agent models and neural network genetic algorithm optimization technology, with p4 <p5,p3<p6, >>1.22, with ⊿t1~⊿t5 < N (assembly requirement limit value) as the constraint condition and the disc weight as the objective function (minimal increase in turbine disc weight), iterate steps 4 to step 6, optimize the values of p1, p2, p4, p7, and ⊿t1~⊿t5, and ensure that max(⊿Ux1max + ⊿t4 + ⊿t5, ⊿Ux1max' + ⊿t4 + ⊿t5, 2⊿Ux2max + 2⊿t4 + 2⊿t5, 2⊿Ux2max' + 2⊿t4 + 2⊿t5) < 1.5 p4 and max(⊿Uz1max + ⊿t1 + ⊿t2 + ⊿t3, ⊿Uz1max' + ⊿t1 + ⊿t2 + ⊿t3) < 1.5 p7, that is, ensure that the front baffle does not fly off.
[0029] After step 7, step 8 is further included. Step 8: Use the method of steps 1 to step 7 to ensure that the rear baffle does not fly off.
[0030] 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 it. Although the present invention has been described in detail with reference to the above embodiments, those of ordinary skill in the art should understand that: modifications or equivalent replacements can still be made to the specific implementation manners of the present invention, and any modification or equivalent replacement that does not depart from the spirit and scope of the present invention shall be covered by the protection scope of the claims of the present invention.
Claims
1. A design method for preventing boltless turbine rotor baffles from flying off, characterized in that: include: Step 1: Obtain the fitting positions and corresponding fitting tolerances between the components of the boltless turbine rotor; Step 2: Obtain key parameters that affect the loss of the front baffle in the boltless turbine rotor; Step 3: Construct the real material constitutive model of the boltless turbine rotor; Step 4: Calculate the displacement and working clearance of the boltless turbine rotor under normal working load; Step 5: Calculate the displacement and working clearance of the boltless turbine rotor under overspeed load; Step 6: Determine whether the front baffle of the boltless turbine rotor is missing; if the front baffle is missing, proceed to step 7; Step 7: Iterate steps 4 to 6 to optimize the fit tolerance in step 1 and the key parameters in step 2 to ensure that the front baffle of the boltless turbine rotor does not fly off.
2. The method according to claim 1, characterized in that The step 1 comprises: The components of the boltless turbine rotor include a front baffle, a rear baffle, a front retaining ring, a rear retaining ring, working blades and a turbine disk; the fitting positions between the components of the boltless turbine rotor include the axial fitting position Z1 of the front baffle and the turbine disk, the axial fitting position Z2 of the front retaining ring and the disk, the axial fitting position Z3 of the front retaining ring and the front baffle, the radial fitting position J1 of the front baffle and the turbine disk, and the radial fitting position J2 of the front baffle and the front retaining ring, and the lower limit values of the fitting tolerance corresponding to each fitting position are obtained in turn: ⊿t1, ⊿t2, ⊿t3, ⊿t4, and ⊿t5.
3. The method according to claim 2, characterized in that The key parameters include the radial length p1 and axial thickness p2 of the web between the throat fillet of the turbine disc and the root fillet of the front hook of the turbine disc, the theoretical axial distance p3 from the front end face of the front retaining ring to the mating position Z2, the radial length p4 of the mating position Z2, the radial distance p5 from the bottom of the front retaining ring to the bottom of the front hook fillet of the turbine disc, the front axial distance p6 from the rear end of the front retaining ring to the turbine disc, and the axial length p7 of the mating position J2.
4. The method according to claim 2, characterized in that The step 3 comprises: Step 31: Obtain the engineering full stress-strain curve OBCD of the material used for the turbine disk at the operating temperature according to the material data sheet. The stress at point B on the engineering full stress-strain curve OBCD corresponds to the yield strength of the material. , the strain becomes , , E is the elastic modulus and the slope of the OB segment of the engineering full stress-strain curve OBCD. The stress at point C corresponds to the ultimate strength of the material. , the strain becomes , the stress at point D corresponds to the fracture strength of the material , strain is elongation ; Step 32: Based on the engineering full stress-strain curve OBCD, construct the engineering full stress-strain curve OB'C'D' of the turbine disk sample in the same furnace. The stress at point B' on the engineering full stress-strain curve OB'C'D' corresponds to the yield strength of the turbine disk sample in the same furnace. , the strain becomes , The stress at point C' corresponds to the ultimate strength of the turbine disk sample in the same furnace: , the strain becomes , and same; Step 33: Convert the constructed engineering full stress-strain curve OB'C'D' into a true stress-strain curve OB''C''D''. The true stress-strain OB''C''D'' is the true material constitutive law at the operating temperature of the turbine disc. Step 34: By analogy with steps 31 to 33, the actual material constitutive model of the blades, front and rear baffles, and front and rear retaining rings at the operating temperature is obtained.
5. The method according to claim 4, characterized in that The step 32 includes: For the engineering full stress-strain curve OB'C'D', the curve between the B'C' segments conforms to the relationship shown in formula (1): (1) in,( , ) is a point on the BC segment of the engineering full stress-strain curve OBCD, is a point on segment B'C', ; For the engineering full stress-strain curve OB'C'D', the C'D' segment conforms to the relationship shown in formula (2): (2) in,( , ) is a point on the CD segment of the engineering full stress-strain curve OBCD, is a point on segment C'D', .
6. The method according to claim 4, characterized in that The step 33 includes: The true stress-strain curve OB''C''D'' conforms to the relationship shown in formula (3): (3) in, It is a point on the engineering full stress-strain curve OB'C'D', It is a point on the true stress-strain curve OB''C''D''.
7. The method according to claim 1, characterized in that The step 4 comprises: Finite element analysis was performed on the boltless turbine rotor. A finite element model was constructed in the finite element software: the turbine disk and front and rear baffles were simulated using 2D axisymmetric elements, the blades and front and rear retaining rings were simulated using plane stress elements with thickness, and each mating position Z1 to Z3, J1, and J2 were simulated using contact standard elements. During the simulation, the mating tolerance was set, the radial displacement of the two mating surfaces corresponding to J2 was coupled, and the axial displacement of the two mating surfaces corresponding to Z2 and Z3 were coupled. Set the mesh properties of the finite element model. Input the true material constitutive values of the turbine disk, blades, front and rear baffles, and front and rear retaining rings obtained in step 3 into the finite element model. Input the material density and linear expansion coefficient. Input the operating speed and temperature load for each state under the typical engine load spectrum. Perform displacement and clearance analysis under each operating state. Analyze the radial displacement difference ⊿Ux1 = Uxa - Uxb between the bottom a of the front retaining ring and the outer edge b of the turbine disk front hook during each acceleration process and load holding process. Obtain the maximum value ⊿Ux1max of the radial displacement difference ⊿Ux1. Analyze the working clearance ⊿Uz1 at the mating position Z1 and the working clearance ⊿Ux2 at the mating position J1 during each deceleration process. Obtain the maximum clearance value ⊿Uz1max of the working clearance ⊿Uz1 and ⊿Ux2max of the working clearance ⊿Ux2, respectively. Uxa is the radial displacement of the bottom a of the front retaining ring, and Uxb is the radial displacement of the outer edge b of the turbine disk front hook. The states include acceleration process, load holding process, and deceleration process.
8. The method according to claim 1, characterized in that The step 5 comprises: Use the finite element model in step 4 to calculate the stress of the turbine disk at the highest steady state ; The following formula is used to calculate the boltless turbine rotor rupture speed: = (4) in, is the radial rupture speed of the turbine disk, rad / s; is the circumferential rupture speed of the turbine disk, rad / s; is the maximum steady-state operating speed of the boltless turbine rotor, rad / s; is the radial material utilization coefficient, is the circumferential material utilization coefficient, is the tensile strength of the material, MPa; is the average radial stress of the most dangerous section of the turbine disk, MPa; is the average circumferential stress of the turbine disk meridian surface, MPa; obtain the minimum rupture speed =min( , ); Analysis of the acceleration process"0- "The radial displacement difference between the bottom a of the center front retaining ring and the outer edge b of the turbine disc front hook ⊿Ux1'=Uxa'-Uxb'. Obtain the maximum value of the radial displacement difference ⊿Ux1' ⊿Ux1max' and analyze the deceleration process." -0" of the fitting working clearance ⊿Uz1' of the fitting position Z1 and the fitting working clearance ⊿Ux2' of the fitting position J1, and obtain the maximum clearance value ⊿Uz1max' of the fitting working clearance ⊿Uz1' and the maximum clearance value ⊿Ux2max' of the fitting working clearance ⊿Ux2' respectively.
9. The method according to claim 1, characterized in that The step 6 comprises: If max(⊿Ux1max+⊿t4+⊿t5,⊿Ux1max'+⊿t4+⊿t5,2⊿Ux2max+2⊿t4+2⊿t5,2⊿Ux2max'+2⊿t4+2⊿t5)<1.5 p4 and max(⊿Uz1max+⊿t1+⊿t2+⊿t3,⊿Uz1max'+⊿t1+⊿t2+⊿t3)<1.5 p7, the front baffle will not fly off, otherwise it will fly off.
10. The method according to claim 1, characterized in that The step 7 comprises: With p4 < p5, p3 < p6, > 1.22, ⊿t1 ~ ⊿t5 < N as the constraint conditions, and the disc weight as the objective function, iterate steps 4 to step 6, optimize the values of p1, p2, p4, p7, ⊿t1 ~ ⊿t5, and ensure that the structural parameters of the front snap ring and the disc max(⊿Ux1max + ⊿t4 + ⊿t5, ⊿Ux1max' + ⊿t4 + ⊿t5, 2⊿Ux2max + 2⊿t4 + 2⊿t5, 2⊿Ux2max' + 2⊿t4 + 2⊿t5) < 1.5 p4 and max(⊿Uz1max + ⊿t1 + ⊿t2 + ⊿t3, ⊿Uz1max' + ⊿t1 + ⊿t2 + ⊿t3) < 1.5 p7, that is, ensure that the front baffle of the boltless turbine rotor does not fly off; N is the limit value of the assembly requirement; After step 7, the method further includes: adopting the methods of steps 1 to 7 to ensure that the rear baffle of the boltless turbine rotor does not fly off.