CN-122021427-A - Stator structure design method and device

CN122021427ACN 122021427 ACN122021427 ACN 122021427ACN-122021427-A

Abstract

The invention provides a stator structure design method and a stator structure design device, which belong to the technical field of aeroengines, wherein the method comprises the steps of determining the sizes of a stator outer ring, a stator inner ring and a blade profile hole on a rubber damping block according to the blade profile of a stator blade; the method comprises the steps of carrying out assembly verification on a stator outer ring, a stator inner ring, blades and rubber damping blocks which meet the performance requirements of preset materials, ensuring that the blades can pass through a blade-shaped hole, selecting materials of the rubber damping blocks based on vibration characteristic analysis results of the blades, carrying out strength analysis on stator components comprising the selected rubber damping blocks, judging whether strength conditions are met, forming a stator structure design scheme if the strength conditions are met, carrying out test verification, and completing design if the test passes. Through rubber damping piece material selection and vibration characteristic analysis design, need not to adjust the blade profile and can realize blade frequency adjustment and wrong frequency design, reduce stator blade vibration stress, promote the fatigue life of quiet cotyledon ring, ensure that the pneumatic efficiency of air compressor satisfies the design requirement.

Inventors

FU ZONGLI
ZHU YINFANG
WEN YA
LAO XIANHAO
DENG JINGLIANG
FAN SHUANGMING
YANG WANLI

Assignees

中国航发湖南动力机械研究所

Dates

Publication Date: 20260512
Application Date: 20260127

Claims (10)

1. A stator structure design method, the method comprising: determining the sizes of the blade profile holes on the stator outer ring, the stator inner ring and the rubber damping block according to the blade profile of the stator blade; Assembling verification is carried out on the stator outer ring, the stator inner ring, the blades and the rubber damping blocks which meet the performance requirements of preset materials, so that the blades can pass through the blade-shaped holes; selecting a material of the rubber damping block based on the vibration characteristic analysis result of the blade; Carrying out strength analysis on the stator component containing the selected rubber damping block, and judging whether the stator component meets strength conditions or not; if the strength condition is met, a stator structure design scheme is formed, test verification is carried out, and if the verification is passed, the design is completed.
2. The stator structural design method according to claim 1, wherein determining the sizes of the stator outer ring, the stator inner ring, and the vane profile holes on the rubber damper block according to the vane profile of the stator vane comprises: based on the blade profile of the stator blade, a blade profile hole matching the blade profile is formed in a digital model of the stator outer ring, stator inner ring and rubber damping block, the blade profile hole being shaped to allow the blade to pass through when assembled.
3. The stator structural design method according to claim 1, wherein the assembling verification of the stator outer ring, the stator inner ring, the vane and the rubber damper block satisfying the preset material performance requirement is performed to ensure that the vane can pass through the vane-type hole, comprising: After confirming that the material properties of the stator outer ring, the stator inner ring, the blades and the rubber damping blocks meet the requirements of environmental temperature, stress level and mechanical properties, assembling; if the blade cannot pass through the blade profile hole in the assembly process, correcting the three-dimensional model of the related part to increase the size of the blade profile hole until the assembly requirement is met.
4. The stator structure design method according to claim 1, wherein selecting a material of the rubber damper block based on a vibration characteristic analysis result of the blade comprises: establishing a finite element model of the stator assembly, and evaluating the inherent vibration frequency and resonance margin of the blade through modal analysis; and selecting the material of the rubber damping block according to the evaluation result so as to ensure that the vibration characteristics of the blade meet the design requirements.
5. The method of claim 4, wherein the design requirement of the resonance margin includes avoiding the resonance frequency or the resonance frequency margin is greater than a preset threshold.
6. The stator structure design method of claim 5, wherein the predetermined threshold is 12%.
7. The method of claim 1, wherein the step of analyzing the strength of the stator assembly including the selected rubber damper block to determine whether the strength condition is satisfied comprises: Establishing a finite element model of the stator assembly, applying corresponding load and boundary conditions, and then performing strength analysis to obtain stress distribution of a stator outer ring, a stator inner ring, a blade and a rubber damping block; Judging whether the ultimate equivalent stress and the ultimate first main stress are lower than allowable stress of the corresponding material; If yes, judging that the strength condition is met, otherwise, adjusting the structure or the material of the part and then re-analyzing until the strength condition is met.
8. The method of claim 1, wherein the test verification includes at least one of a frequency test, a component performance test, and a endurance test.
9. The stator structure design method of claim 8, wherein the frequency test requires that the measured blade frequency be consistent with the simulation result, wherein the stator blade frequency dispersion is no greater than 30%; the component performance test is used for verifying the pneumatic performance of the stator structure; the endurance test is used to simulate typical sustained operating conditions of an engine, verifying fatigue resistance and long-term structural integrity of the stator structure by applying vibratory, thermal and pneumatic loads.
10. A stator structural design apparatus, comprising: the parameter determining module is used for determining the sizes of the stator outer ring, the stator inner ring and the blade profile holes on the rubber damping block according to the blade profile of the stator blade; the assembly verification module is used for carrying out assembly verification on the stator outer ring, the stator inner ring, the blades and the rubber damping blocks which meet the performance requirements of preset materials, and ensuring that the blades can pass through the blade-shaped holes; the material selection module is used for selecting the material of the rubber damping block based on the vibration characteristic analysis result of the blade; The strength analysis module is used for carrying out strength analysis on the stator assembly containing the selected rubber damping block and judging whether the stator assembly meets the strength condition or not; And the verification and output module is used for forming a stator structure design scheme and performing test verification if the strength condition is met, and finishing the design if the verification is passed.

Description

Stator structure design method and device Technical Field The application belongs to the technical field of aeroengines, and particularly relates to a stator structure design method and device. Background In the development and use process of an aeroengine, blade vibration and crack are core technical problems commonly existing. When the engine runs in the full-working envelope, the blade can not completely avoid resonance almost without realization, so that the design and the test can avoid harmful resonance of the blade enough to cause high-cycle fatigue damage, and the blade becomes a key requirement for guaranteeing the reliability of the engine. The stator vane ring is used as a core component of an air flow channel of the aeroengine, the structural design of the stator vane ring directly influences the vibration characteristics of the vane and the integral operation safety of the engine, and the stator vane ring structure mainly used in the current mainstream is divided into a single support (without an inner ring or an outer ring, and the vane is in a cantilever state) and a double support (with an inner ring and an outer ring and respectively connected with two ends of the vane). For stator blades with longer size, the double-support structure can remarkably improve the self-vibration frequency of the blades and inhibit resonance fatigue caused by airflow pulsation, and is more widely applied than a single-support structure. In the existing double-support stator vane ring, the whole machine-added type structure, the vane and the inner and outer ring are in two main stream structures, wherein the welded structure realizes fixation by welding two ends of the stator vane in reserved holes or grooves of the inner and outer rings, and the double-support stator vane ring has the advantages of simple connection structure and lower processing cost and is particularly commonly applied to engineering. However, such welded double support structures are essentially rigid joints, which in practice expose a number of technical drawbacks that are difficult to overcome: the rigid connection cannot consume vibration energy and reduce stress of the blade in a mode of increasing structural damping, and the blade is easy to generate high cycle fatigue under the action of vibration load for a long time, so that the service life of the blade is seriously influenced; If harmful resonance is to be avoided through the wrong frequency design, the method can be realized only by adjusting the blade profile parameters, but the change of the blade profile possibly damages the original pneumatic optimization design, so that the pneumatic efficiency of the engine is reduced, and the problem that the resonance is difficult to avoid by adjusting the blade profile is proved by practice; the inner ring is usually matched with a rotary sealing structure (such as a comb tooth), and blade vibration can be directly transmitted to the inner ring through rigid connection, so that the inner ring is greatly deformed, scraping of rotor and stator components is easily caused, and the operation safety of an engine is threatened. In order to solve the defects of the rigid connection, a stator vane ring structure with rubber damping vibration attenuation is generated. The structure can effectively reduce the fatigue damage of the blades caused by rotary pulsation load, improves the reliability of the engine, has obvious vibration reduction effect and has good engineering application prospect. However, in the prior art, aiming at the novel rubber damping vibration reduction structure, a design method of a system is not formed yet, and related mechanical characteristic analysis is also relatively deficient, so that the structural optimization of the novel rubber damping vibration reduction structure lacks theoretical support, is difficult to accurately match with vibration control requirements of different engines, and severely restricts engineering popularization and application efficiency improvement of the vibration reduction structure. In summary, the existing double-support stator vane ring structure has the problems of insufficient vibration reduction, limited frequency-misplacement design and high safety risk due to rigid connection, or the core requirements of an aeroengine on stator vane ring of low vibration, long service life and high safety cannot be met due to the fact that a rubber damping vibration reduction function is introduced but a matched design method and mechanical analysis support are lacked. Disclosure of Invention In order to solve the above problems, the present application provides a stator structure design method, which includes: determining the sizes of the blade profile holes on the stator outer ring, the stator inner ring and the rubber damping block according to the blade profile of the stator blade; Assembling verification is carried out on the stator outer ring, the stator inner ring, the blades and the rubber damp