Simulation method of aero-engine elastic ring damper support considering dynamic-static pressure effect

Abstract

The application belongs to the technical field of aero-engine vibration control and rotor dynamics simulation, and particularly relates to an aero-engine elastic ring damping support simulation method considering dynamic-static pressure effect. The method comprises the following steps: calculating the elastic ring deformation under the action of convex contact by using a finite element method, and obtaining the radial deformation of the elastic ring node; establishing a geometric and deformation coordination relationship of the damper-rotor system, and describing the real-time form of the oil film gap; constructing a flow and flow resistance model and solving the dynamic-static pressure distribution based on the volume change rate of each relative closed oil film cavity; introducing the dynamic-static pressure distribution as an initial value into the Reynolds equation, and solving the total pressure of the whole oil film in combination with the real-time contact state of the convex; and obtaining the convergent oil film characteristic results through bidirectional fluid-structure coupling iteration. The method can accurately reproduce the step-like characteristics of the oil film pressure under large amplitude working conditions, and significantly improves the accuracy of damper performance prediction under complex working conditions of aero-engines.

Description

Technical Field

[0001] This invention belongs to the field of aero-engine vibration control and rotor dynamics simulation technology, specifically relating to a simulation method for aero-engine elastic ring damping support considering dynamic-static pressure effects. Background Technology

[0002] To achieve higher thrust-to-weight ratios and thermal efficiency, advanced aero-engines typically employ high-speed, high-load flexible rotor structures, often spanning multiple critical speeds within their operating range. This results in complex vibration response characteristics. To effectively suppress vibration amplitude during rotor over-critical periods and ensure system stability, high-performance damping devices are widely used. Among these, the Elastic Ring Squeeze Film Damper (ERSFD) combines the advantages of elastic support and squeeze film damping. It provides stiffness and damping through the deformation of a thin-walled elastic ring with inner and outer bosses and the squeeze flow of oil films inside and outside the ring. With advantages such as compact structure and adjustable nonlinear stiffness, it has become a key component in aero-engine rotor vibration reduction design.

[0003] Despite the promising application prospects of ERSFD, its working mechanism involves a complex fluid-structure interaction process. Under high-speed rotor whirl conditions, the elastic ring undergoes significant elastic deformation, leading to periodic contact and separation between its inner and outer bosses and the bearing housing or rotor journal. This dynamic structural change directly determines the mechanical properties of the oil film. However, existing ERSFD oil film characteristic simulation methods are typically based on traditional hydrodynamic lubrication theory, only considering squeezing and shearing effects to solve the Reynolds equation, which has significant limitations in modeling and calculation.

[0004] Specifically, existing technologies have the following shortcomings: First, traditional simulation models often ignore the discontinuity of the contact interface. In actual operation, the contact state of the elastic ring boss changes in real time with the rotor movement. This contact-separation behavior leads to abrupt changes in the oil film boundary conditions, while existing methods often simplify the boundary to a continuous or fixed state, failing to accurately reflect this physical process. Second, existing methods fail to accurately describe the dynamic evolution of the oil film domain affected by the boss contact state. Since the boss divides the oil film into several relatively independent oil film cavities, the deformation of the elastic ring causes drastic fluctuations in the volume of the oil film cavities, resulting in significant dynamic-static pressure effects (i.e., pressure fluctuations driven by the rate of volume change). However, traditional methods struggle to capture this fluid behavior caused by changes in the flow channel topology. Finally, the aforementioned simplifications make it difficult for existing technologies to accurately simulate the nonlinearity of the oil film's mechanical properties. Actual observations show that the oil film pressure distribution, considering contact and volume effects, exhibits a stepped characteristic, while the pressure distribution predicted by traditional methods is often too smooth, leading to significant deviations in the prediction of oil film load-bearing capacity and damping characteristics under conditions of large eccentricity or large amplitude.

[0005] In summary, there is currently a lack of a comprehensive simulation method that can simultaneously consider the discontinuous changes in the contact interface of the elastic ring, the dynamic effect of the oil film cavity volume, and the resulting dynamic-static pressure effect. This severely restricts the accurate design and performance evaluation of the elastic ring extrusion oil film damper for aero-engines. Summary of the Invention

[0006] This invention relates to a simulation method for elastic ring damping supports in aero-engines that considers the dynamic-static pressure effect. This method targets the high-speed flexible rotor-support structure system of advanced aero-engines and aims to address the serious limitations of existing simulation methods. Traditional methods often neglect the discontinuity of the contact interface caused by elastic ring deformation, failing to accurately describe the dynamic evolution of the oil film flow domain under the real-time influence of boss contact states (contact sealing or separation leakage), and also failing to cover the dynamic-static pressure effect caused by drastic changes in the oil film cavity volume. This results in difficulty simulating the nonlinearity of the oil film mechanical characteristics of the elastic ring compressing the oil film damper under complex operating conditions, leading to large simulation prediction deviations. This invention, by considering the real-time contact of the elastic ring bosses and the oil film flow domain characteristics determined by them, introduces the dynamic-static pressure effect, achieving the simulation of the aforementioned complex fluid-structure interaction behavior.

[0007] To achieve the above-mentioned objectives, the present invention proposes a simulation method for elastic ring damping supports of aero-engines that considers dynamic and static pressure effects. The specific technical solution is as follows: Step S1: Calculate the deformation of the elastic ring under real-time contact action of the bosses using the finite element method: First, establish a dynamic finite element model for the elastic ring extrusion oil film damper-rotor system. Under the initial state without considering the fluid force of the oil film, simulate the rotor journal whirling with a set eccentricity and angular velocity. Use the finite element analysis method (FEM) to solve the stress and deformation state of the elastic ring. The elastic ring has several inner and outer bosses, which divide the oil film gap into several independent oil film cavities. The oil film cavities are connected through the damping holes on the elastic ring. In solving the stress and deformation state of the elastic ring, the real-time contact nonlinear characteristics between the inner and outer bosses of the elastic ring and the mating surface are considered. The radial deformation of all nodes of the dynamic finite element model under rotor motion excitation is calculated, providing a structural basis for the subsequent determination of the flow field geometric boundary.

[0008] Step S2: Establish the geometric and deformation compatibility relationship of the elastic ring extrusion oil film damper-rotor system: Define the structural parameters of the elastic ring extrusion oil film damper: the mid-surface radius of the elastic ring is... r axial length is Rotor displacement eccentricity vector , e Indicates the eccentric distance. Representing the eccentric phase angle, the heights of the inner and outer bosses are respectively... , In angular coordinates and time Under these conditions, the elastic ring undergoes radial deformation. , The first-order partial derivative with respect to time is Define the inner oil film thickness and outer oil film thickness The geometric relationships are as follows: ; ; The above-mentioned coordination relationship describes the real-time geometric shape of the oil film gap during rotor motion.

[0009] Step S3: Solving for dynamic-static pressure based on oil film cavity volume change: Unlike traditional methods that only consider shear flow and extrusion flow, since the oil film cavities segmented by the elastic ring boss are relatively closed, the deformation of the elastic ring directly changes the volume of the oil film cavity, thereby generating dynamic-static pressure through throttling via the damping orifice. This step introduces the oil film cavity volume change effect caused by the deformation of the elastic ring. At the same time, the contact characteristics of the elastic ring boss are incorporated to fully model the flow resistance characteristics of the oil film domain, specifically including: Step S3.1: Calculate the volume change rate of each oil film cavity: based on the current time... t and the previous moment tThe state is -1, and the time difference between the two moments is denoted as... Calculate the first i Volume change of each internal oil film cavity , No. i Volume change of each external oil film cavity Then, calculate the rate of volume change based on the amount of volume change. , : ; ; in, Represents the angular coordinates in the circumferential direction. and Represent the angular coordinates of the inner and outer bosses, respectively, with subscripts... i Indicates the first i The oil film cavity and the first i Each oil film cavity corresponds to a protrusion, and the subscript 'c' indicates the current time. t The current state is shown below, and the subscript 'l' indicates the previous time step. t The state at -1 Indicates the current time t The eccentric phase angle below, Indicates the previous moment t Off-center phase angle at -1; Step S3.2: Establish flow rate and flow resistance models for each oil film cavity, including the flow rate through the damping orifice and the flow rate through the boss mating gap. The fluid flows through two main paths between the oil film cavities: one is through the damping orifice on the elastic ring, and the other is through the boss mating gap (when the boss separates). Based on the principle of fluid continuity, for any oil film cavity, the rate of volume change is balanced with the inflow / outflow rate. ; in, Indicates the first i The volume change of an inner or outer oil film cavity. This indicates the flow rate of lubricating oil through the damping orifice. This represents the flow rate of lubricating oil through the gap between the bosses caused by the deformation of the elastic ring; assuming the fluid flows through a diameter of... , length is For the damping orifice, according to the Hagen-Poiseuille equation, the flow rate Q is related to the pressure difference. Relationship and damping orifice flow resistance considering local losses and boss flow resistance for: ; ; in, The viscosity of the lubricating oil. and These are the local loss coefficients at the inlet and outlet of the damping orifice, respectively. Indicates fluid density, Indicates the circumferential width of the boss. and These are the local loss coefficients for the inlet and outlet of the boss, respectively. This refers to the clearance between the boss and the mating surface. Step S3.3: Construct and solve the full oil film flow resistance matrix equation: For the oil film containing For a system with an oil film cavity, define the flow resistance matrix. The matrix elements are determined based on the connection relationships between each oil film cavity, where the diagonal elements... The sum of the reciprocals of the flow resistances of all flow paths connected to the oil film cavity, with off-diagonal elements. oil film cavity With oil film cavity The negative value of the reciprocal of the flow resistance between them, that is: ; Flow resistance matrix Represented as: ; Therefore, the full oil film flow resistance matrix equation for solving the dynamic-static pressure of each oil film cavity is established: ; in Let be the dynamic-static pressure vectors of each oil film cavity to be solved. Given the volume change rate vector of each oil film cavity, the dynamic-static pressure distribution of each oil film cavity caused by the deformation of the elastic ring is obtained by solving the full oil film flow resistance matrix equation. Step S4: Solve the total pressure of the thin oil film in each oil film cavity based on the dynamic-static pressure of each oil film cavity: Take the dynamic-static pressure distribution driven by volume change obtained in step S3 as the initial value, introduce the hydrodynamic lubrication theory, establish the Reynolds equation governing equations for the inner and outer oil films, and solve the Reynolds equations by numerical solution of partial differential equations such as finite difference. In the solution process, combine the contact state of the boss (contact sealing or separation leakage) to dynamically update the fluid domain pressure boundary conditions, thereby calculating the total pressure distribution of the entire oil film determined by the dynamic-static pressure distribution and the hydrodynamic effect. Step S5: Iteratively solve to obtain the convergence result of the full oil film pressure distribution of the elastic ring extrusion oil film damper-rotor system: Using a two-way fluid-structure coupling iterative strategy, the total oil film pressure distribution calculated in step S4 is fed back to the elastic ring structure to update the deformation state of the elastic ring; then, steps S2 to S4 are re-executed using the new deformation state, and the calculation is repeated cyclically; a convergence criterion is set, and when the convergence criterion is met, the final oil film pressure field and damping characteristics at the current time step are output, and the process is advanced to the next time step, finally realizing the simulation of the elastic ring damping support of the aero-engine considering the dynamic-static pressure effect.

[0010] Compared to the traditional method of obtaining the mechanical properties of the elastic annular oil film by transiently solving the Reynolds equation, the advantages of this invention are: (1) This invention breaks through the limitations of traditional methods that only focus on hydrodynamic effects. For the first time, it introduces the dynamic-static pressure effect caused by the elastic deformation of the elastic ring by establishing a detailed oil film cavity volume change model in the simulation. This improvement fully reflects the physical nature of the elastic ring squeeze oil film damper as a complex mechanism that is both elastic and damping, with its oil film cavity being relatively closed and its volume fluctuating drastically with deformation, thus revealing its intrinsic damping and vibration reduction mechanism more accurately. (2) Simulation results show that the oil film pressure distribution calculated by the method of the present invention exhibits a significant step-like feature, which is fundamentally different from the smooth distribution that only considers the Reynolds equation. Especially under the large amplitude vortex condition, the dynamic-static pressure effect dominates the pressure distribution, making the predicted pressure peak significantly higher than that of the traditional model. This high-precision pressure field prediction is of decisive significance for accurately evaluating the load-bearing capacity, fatigue strength and critical speed passing capability of the elastic ring, and provides a more practical and reliable theoretical tool for the structural optimization design of the aero-engine rotor system. Attached Figure Description

[0011] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0012] Figure 1 A schematic diagram of the structural features of an aero-engine elastic ring compression oil film damper-rotor system in one embodiment; Figure 2 A schematic diagram of an elastic ring extrusion oil film damper structure in one embodiment; Figure 3 This is a simplified flowchart of the simulation method for elastic ring damping support of aero-engine considering dynamic-static pressure effects; Figure 4 This is the single-step simulation result of solving the dynamic pressure of the thin oil film in step S4; Figure 5 It is the convergence result of the full oil film pressure distribution of the elastic ring squeeze oil film damper considering the dynamic-static pressure effect of rotor motion. Detailed Implementation

[0013] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0014] This invention proposes a simulation method for the oil film characteristics of an aero-engine elastic ring extrusion oil film damper, considering the influence of dynamic and static pressure effects caused by rotor motion. Compared with other existing methods, this method not only considers the hydrodynamic effects of traditional extrusion oil film, but also introduces the dynamic and static pressure effects caused by the change in oil film cavity volume due to the deformation of the elastic ring under rotor motion by establishing a refined oil film cavity volume change model. This comprehensively considers the oil film mechanical characteristics and damping and vibration reduction mechanism of the elastic ring extrusion oil film damper, thereby enabling more accurate prediction of the system's dynamic response characteristics.

[0015] To further verify and illustrate the simulation method of the elastic ring extrusion oil film damper for aero-engines considering the influence of dynamic and static pressure effects of rotor motion, a representative example of an elastic ring extrusion oil film damper-rotor system model is used to conduct dynamic numerical solutions and result comparison analysis. The structural schematic of this elastic ring extrusion oil film damper-rotor system is shown below. Figure 1 As shown, the structure includes a first bearing 1, a second bearing 2, a third bearing 4, a fourth bearing 5, a shaft 3, and a turbine assembly 6. An elastic ring is arranged on the third bearing 4 and the fourth bearing 5. The rotor length is 130 mm, the turbine assembly mass is 63 kg, and the material's elastic modulus is 195 GPa. The elastic ring structure is as follows: Figure 2 As shown, the upper part is provided with an elastic ring boss 7 and a damping hole 8. In the designed working state, the gap formed between the elastic ring and the mating surface is filled with lubricating oil. This allows the lubricating oil to flow through the damping hole during the deformation of the elastic ring by the rotor, thereby generating flow damping, suppressing and dissipating vibration energy. Structurally, the axial length of the elastic ring is 21mm, the elastic modulus of the material is 205GPa, the wall thickness of the elastic ring is 1mm, the diameter of the damping hole is 0.8mm, the diameter of the elastic ring is 80mm, the height of the boss is 0.2mm, and the number of bosses is 8.

[0016] like Figure 3 As shown, the specific steps of the simulation method described in this embodiment are as follows: Step S1: Calculate the deformation of the elastic ring considering the real-time contact action of the bosses using the finite element method. This step solves for the radial deformation of the elastic ring at various points caused by the rotor journal whirling with a set eccentricity and angular velocity under the action of no oil film by establishing an elastic ring compression oil film damper-rotor system model. The elastic ring has several inner and outer bosses, which divide the oil film gap into several independent oil film cavities, which are connected by damping holes on the elastic ring. Since the finite element method used in this part is mature, widely used in scientific research and engineering, and easy to implement, and is not an innovative part of this invention, the specific process of this part is omitted. Step S2: Establish the geometric and deformation compatibility relationship of the elastic ring extrusion oil film damper-rotor system: Define the structural parameters of the elastic ring extrusion oil film damper: the mid-surface radius of the elastic ring is... r axial length is Rotor displacement eccentricity vector , e Indicates the eccentric distance. Representing the eccentric phase angle, the heights of the inner and outer bosses are respectively... , In angular coordinates and time Under these conditions, the elastic ring undergoes radial deformation. , The first-order partial derivative with respect to time is Define the inner oil film thickness and outer oil film thickness The geometric relationships are as follows: ; ; The above-mentioned coordination relationship describes the real-time geometric shape of the oil film gap during rotor motion.

[0017] Step S3: Solve the dynamic-static pressure based on the change in oil film cavity volume: Unlike traditional methods that only consider shear flow and extrusion flow, since each oil film cavity divided by the elastic ring boss is relatively closed, the deformation of the elastic ring will directly change the volume of the oil film cavity, and thus generate dynamic-static pressure through the damping orifice throttling. This step introduces the effect of oil film cavity volume change caused by the deformation of the elastic ring. At the same time, the contact characteristics of the elastic ring boss are brought in to fully model the flow resistance characteristics of the oil film domain. Step S3.1: Calculate the volume change rate of each oil film cavity: based on the current time... t and the previous moment t The state is -1, and the time difference between the two moments is denoted as... Calculate the first i Volume change of each internal oil film cavity , No.i Volume change of each external oil film cavity Then, calculate the rate of volume change based on the amount of volume change. , : ; ; in, Represents the angular coordinates in the circumferential direction. and Represent the angular coordinates of the inner and outer bosses, respectively, with subscripts... i Indicates the first i The oil film cavity and the first i Each oil film cavity corresponds to a protrusion, and the subscript 'c' indicates the current time. t The current state is shown below, and the subscript 'l' indicates the previous time step. t The state at -1 Indicates the current time t The eccentric phase angle, Indicates the previous moment t Off-center phase angle at -1.

[0018] Step S3.2: Establish flow rate and flow resistance models for each oil film cavity, including the flow rate through the damping orifice and the flow rate through the boss mating gap. The fluid flows primarily through two paths between the oil film cavities: one is through the damping orifice on the elastic ring, and the other is through the boss mating gap (when the boss separates). Based on the principle of fluid continuity, for any oil film cavity, the rate of volume change is balanced with the inflow / outflow rate. ; in, Indicates the first i The volume change of an inner or outer oil film cavity. This indicates the flow rate of lubricating oil through the damping orifice. This represents the flow rate of lubricating oil through the gap between the bosses caused by the deformation of the elastic ring; assuming the fluid flows through a diameter of... , length is For the damping orifice, according to the Hagen-Poiseuille equation, the flow rate is related to the pressure difference. Relationship and damping orifice flow resistance considering local losses and boss flow resistance for: ; ; in, The viscosity of the lubricating oil. and These are the local loss coefficients at the inlet and outlet of the damping orifice, respectively. Indicates fluid density, Indicates the circumferential width of the boss. and These are the local loss coefficients for the inlet and outlet of the boss, respectively. This refers to the clearance between the boss and the mating surface. Step S3.3: Construct and solve the full oil film flow resistance matrix equation: For the oil film containing For a system with an oil film cavity, define the flow resistance matrix. The matrix elements are determined based on the connection relationships between each oil film cavity, where the diagonal elements... The sum of the reciprocals of the flow resistances of all flow paths connected to the oil film cavity, with off-diagonal elements. oil film cavity With oil film cavity The negative value of the reciprocal of the flow resistance between them, that is: ; Flow resistance matrix Represented as: ; Therefore, the full oil film flow resistance matrix equation for solving the dynamic-static pressure of each oil film cavity is established: ; in Let be the dynamic-static pressure vectors of each oil film cavity to be solved. Given the volume change rate vector of each oil film cavity, the dynamic-static pressure distribution of each oil film cavity caused by the deformation of the elastic ring is obtained by solving the full oil film flow resistance matrix equation. Step S4: Calculate the total pressure of the thin oil film in each oil film cavity based on the dynamic and static pressure of each oil film cavity: Total lubricating oil pressure within the oil film cavity. P The oil film pressure is determined by both static and dynamic pressure. Using the dynamic-static pressure distribution of each oil film cavity obtained in step S3 as the initial value, the total oil film pressure is calculated using the Reynolds equation. The governing equations for the inner and outer oil film pressures are also used. and They are respectively: ; ; The above equations are solved numerically using a partial differential equation numerical solution method (any method is acceptable, but the finite difference method is used in this embodiment) to obtain the total pressure distribution of the entire oil film. During the solution process, the pressure boundary conditions of the fluid domain need to be updated in real time in conjunction with the contact state of the boss (contact sealing or separation leakage).

[0019] Step S5: Iteratively solve to obtain the convergence result of the full oil film pressure distribution of the elastic ring squeeze oil film damper-rotor system fluid-structure interaction: Apply the numerical result of the total oil film pressure distribution as pressure to the elastic ring, thereby updating the deformation state of the elastic ring structure, and perform iterative calculation again. Repeat this iterative calculation step. When the change in oil film pressure or pressure peak value in adjacent iteration time steps is lower than the set tolerance (such as 1%), it is considered that the oil film pressure field in this time step has converged. Output the final oil film pressure field and damping characteristics in the current time step, and advance to the next time step, finally realizing the simulation of the elastic ring damping support of the aero-engine considering the dynamic-static pressure effect.

[0020] In this embodiment, with a rotor whirl amplitude of 0.1 mm, the oil film pressure distribution is obtained using the traditional numerical simulation method for elastic ring compression oil film dampers, as shown below. Figure 4 As shown: the oil film pressure depends only on the wall boundary conditions, thus the pressure distribution in each oil film cavity is relatively continuous, exhibiting a curved surface variation in the compression and expansion zones; however, using the simulation method specified in this invention, the pressure distribution within each oil film cavity shows a significant step-like characteristic, and the pressure changes in each oil film cavity exhibit significant abrupt discontinuities, such as... Figure 5 As shown, this is a typical dynamic-static pressure effect driven by the rate of volume change. Especially under large amplitudes, the dynamic-static pressure effect dominates the pressure distribution, resulting in pressure peaks significantly higher than the simulation predictions of traditional models considering only the Reynolds equation. In summary, this implementation method meticulously demonstrates the calculation process of the oil film characteristics of an elastic ring extrusion oil film damper considering the influence of the dynamic-static pressure effect of rotor motion, providing a practical and feasible new method for accurate prediction of the vibration response and structural optimization design of the elastic ring extrusion oil film damper-rotor system in aero-engines.

[0021] The specific embodiments described above are merely preferred embodiments of the present invention. It should be understood that the scope of protection of the present invention is not limited to the specific embodiments. Without departing from the principles of the present invention, any modifications, alterations, substitutions, or replacements of the simulation object made by those skilled in the art to the technical solutions of the present invention, or any changes to the simulation object, should fall within the scope of protection defined by the claims of the present invention.

Claims

1. A simulation method for elastic ring damping support of aero-engine considering dynamic-static pressure effects, characterized in that, Includes the following steps: Step S1: Calculate the deformation of the elastic ring under the real-time contact action of the bosses using the finite element method: Establish a dynamic finite element model for the elastic ring extrusion oil film damper-rotor system. When simulating the rotor journal whirling with a set eccentricity and angular velocity, solve the stress and deformation state of the elastic ring. The elastic ring has several inner and outer bosses. The inner and outer bosses divide the oil film gap into several independent oil film cavities. The oil film cavities are connected through the damping holes on the elastic ring. Considering the real-time contact nonlinear characteristics between the inner and outer bosses of the elastic ring and the mating surface, obtain the radial deformation of all nodes of the dynamic finite element model under the rotor motion excitation. Step S2: Establish the geometric and deformation coordination relationship of the elastic ring squeeze oil film damper-rotor system: Based on the mid-surface radius, axial length, boss height and distribution parameters of the elastic ring, combined with the radial deformation obtained in step S1, define the geometric relationship between the inner oil film thickness and the outer oil film thickness, and describe the real-time geometric shape of the oil film gap during rotor motion. Step S3: Solve the dynamic-static pressure based on the change in oil film cavity volume: Introduce the effect of oil film cavity volume change caused by the deformation of the elastic ring, and calculate the volume change rate of each oil film cavity; Based on the principle of fluid continuity, a flow rate and flow resistance model for each oil film cavity, including the flow rate of the damping orifice and the flow rate of the boss mating gap, is established; the full oil film flow resistance matrix equation is constructed and solved to obtain the dynamic-static pressure distribution of each oil film cavity caused by the deformation of the elastic ring; Step S4: Solve the total pressure of the thin oil film in each oil film cavity based on the dynamic-static pressure of each oil film cavity: Using the dynamic-static pressure distribution obtained in step S3 as the initial value, the Reynolds equations for the inner and outer oil films are established and solved by introducing the hydrodynamic lubrication theory; during the solution process, the fluid domain pressure boundary conditions are dynamically updated in combination with the real-time contact state of the boss, and the total pressure distribution of the entire oil film determined by the dynamic-static pressure distribution and the hydrodynamic effect is calculated. Step S5: Iteratively solve to obtain the convergence result of the full oil film pressure distribution of the elastic ring extrusion oil film damper-rotor system: Using a two-way fluid-structure coupling iterative strategy, the total pressure distribution of the full oil film calculated in step S4 is fed back to the elastic ring structure to update the deformation state of the elastic ring, and steps S2 to S4 are repeatedly executed until the convergence criterion is met, and the final oil film pressure field and damping characteristics at the current time step are output.

2. The simulation method for elastic ring damping support of aero-engine considering dynamic-static pressure effect according to claim 1, characterized in that, In step S2, the mid-surface radius of the elastic ring is... r axial length is Rotor displacement eccentricity , e Indicates the eccentric distance. This indicates the eccentric phase angle, and the heights of the inner and outer bosses are respectively... , In angular coordinates and time Under these conditions, the elastic ring undergoes radial deformation. , The first-order partial derivative with respect to time is Define the inner oil film thickness and outer oil film thickness The geometric relationships are as follows: ； 。 3. The simulation method for elastic ring damping support of aero-engine considering dynamic-static pressure effect according to claim 2, characterized in that, In step S3, calculating the volume change rate of each oil film cavity specifically involves: based on the current time... t and the previous moment t The state is -1, and the time difference between the two moments is denoted as... Calculate the first i Volume change of each internal oil film cavity , No. i Volume change of each external oil film cavity Then, calculate the rate of volume change based on the amount of volume change. , : ； ； in, Represents the angular coordinates in the circumferential direction. and Represent the angular coordinates of the inner and outer bosses, respectively, with subscripts... i Indicates the first i The oil film cavity and the first i Each oil film cavity corresponds to a protrusion, and the subscript 'c' indicates the current time. t The state below, where the subscript l indicates the previous time step. t The state at -1 Indicates the current time t The eccentric phase angle below, Indicates the previous moment t Off-center phase angle at -1.

4. The simulation method for elastic ring damping support of aero-engine considering dynamic-static pressure effect according to claim 3, characterized in that, In step S3, establishing the flow rate and flow resistance model for each oil film cavity, including the flow rate of the damping orifice and the flow rate of the boss mating gap, specifically involves: based on the principle of fluid continuity, for any oil film cavity, the volume change rate and the inflow / outflow flow rate are balanced. ； in, Indicates the first i The volume change of an inner or outer oil film cavity. This indicates the flow rate of lubricating oil through the damping orifice. This represents the flow rate of lubricating oil through the gap between the bosses caused by the deformation of the elastic ring; assuming the fluid flows through a diameter of... , length is The damping orifice, according to the Hagen-Poiseuille equation, has a flow rate Q With pressure difference Relationship and damping orifice flow resistance considering local losses and boss flow resistance for: ； ； in, The viscosity of the lubricating oil. and These are the local loss coefficients at the inlet and outlet of the damping orifice, respectively. Indicates fluid density, Indicates the circumferential width of the boss. and These are the local loss coefficients at the entrance and exit of the boss, respectively. This refers to the clearance between the boss and the mating surface.

5. The simulation method for elastic ring damping support of aero-engine considering dynamic-static pressure effect according to claim 1, characterized in that, In step S3, the constructed full oil film flow resistance matrix equation is expressed as: ； in Here is the flow resistance matrix. The diagonal elements are the sum of the reciprocals of the flow resistance of all flow paths connected to the oil film cavity, and the off-diagonal elements are the negative values ​​of the reciprocals of the flow resistance between the oil film cavities. Let be the dynamic-static pressure vectors of each oil film cavity to be solved. Given the volume change rate vector of each oil film cavity, the dynamic-static pressure distribution of each oil film cavity caused by the deformation of the elastic ring is obtained by solving the full oil film flow resistance matrix equation.

6. The simulation method for elastic ring damping support of aero-engine considering dynamic-static pressure effect according to claim 1, characterized in that, In step S5, the convergence criterion is to set the change in oil film pressure or pressure peak value in adjacent iteration time steps to be lower than a set tolerance. When the convergence criterion is met, it is determined that the oil film pressure field in the current time step has converged and is advanced to the next time step.

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