CN112025561A - Method for determining surface integrity requirement of aeroengine turbine disc - Google Patents
Method for determining surface integrity requirement of aeroengine turbine disc Download PDFInfo
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- CN112025561A CN112025561A CN202010885464.0A CN202010885464A CN112025561A CN 112025561 A CN112025561 A CN 112025561A CN 202010885464 A CN202010885464 A CN 202010885464A CN 112025561 A CN112025561 A CN 112025561A
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- surface integrity
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
- B24C1/00—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods
- B24C1/10—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods for compacting surfaces, e.g. shot-peening
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
- B24C9/00—Appurtenances of abrasive blasting machines or devices, e.g. working chambers, arrangements for handling used abrasive material
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention belongs to the field of aviation, and provides a method for determining the requirement on the surface integrity of a turbine disc of an aero-engine. The invention adopts a simulation method to carry out test verification so as to determine the shot blasting strength and the shot blasting coverage rate requirements of different structural feature parts. At present, no literature about a method for determining the surface integrity requirement of the aeroengine turbine disk at home and abroad is retrieved. Combining the structural characteristics and the process capability, the roughness requirement can be properly lowered for the part with smaller stress in the strength calculation result, and the roughness requirement is improved for the part with larger stress; and (4) giving reasonable roughness requirements by considering the actual process capability. The method combines the simulation calculation of the turbine disk and the test result of the characteristic simulation part, and is convenient and easy to operate. The method is also suitable for the compressor and the fan disc.
Description
Technical Field
The invention belongs to the field of aviation, and provides a method for determining the requirement on the surface integrity of a turbine disc of an aero-engine.
Background
The service life of the aeroengine turbine disc determines the service life of the whole engine, the damage form of the aeroengine turbine disc in the normal working process mainly takes low cycle fatigue as the main part, and the surface integrity of the failure part has great influence on the low cycle fatigue life of the wheel disc, so a set of scientific and feasible method for determining the surface integrity requirement of each part of the turbine disc is very important.
The low cycle life of the aeroengine turbine disc is related to the material characteristics of the disc and the environment, stress level, structural characteristics, surface roughness, shot blasting strength, shot blasting coverage rate and the like of the disc in a working state, so that the stress distribution condition of the actual working environment and the working state of the turbine disc needs to be considered when the surface integrity requirement of the turbine disc is provided so as to determine the part needing the surface integrity requirement, and the requirement of the surface integrity needs to be combined with the stress distribution condition and the processing technology capability so as to determine the roughness requirement of the part. Meanwhile, the shot blasting strength and the shot blasting coverage rate of different structural feature parts of the turbine disk are not necessarily the larger the better, and quantitative research on the relationship between the shot blasting strength and the shot blasting coverage rate and the service lives of the different structural feature parts is lacked in the industry at present, so that the specific requirements of the shot blasting strength and the shot blasting coverage rate need to be determined by tests in the requirements of surface integrity.
Disclosure of Invention
The purpose of the invention is as follows: a method for determining the surface integrity requirement of an aeroengine turbine disc is used for meeting the surface integrity requirement of a weak part in service life in the design process of the aeroengine turbine disc.
In consideration of the fact that the wheel disc is high in test cost and has no operational significance, the method adopts a simulation piece method to carry out test verification so as to determine the requirements of shot blasting strength and shot blasting coverage rate of different structural feature parts. At present, no literature about a method for determining the surface integrity requirement of the aeroengine turbine disk at home and abroad is retrieved.
The technical scheme is as follows: a method for determining the requirement of the surface integrity of a turbine disk of an aircraft engine comprises the following steps:
the shot blasting coverage rate is 50% -300%; the method is consistent with the actual process coverage rate, and can ensure that each part of the wheel disc is smoothly implemented when being strengthened.
The shot blasting intensity is 0.24-0.45N.
The primary stress gradients are consistent to ensure that the maximum primary stress gradients are consistent within the three-dimensional scale.
And the stress distribution in the step 1 is an elasticity calculation result.
The parts to be shot-peened in step 1 should include parts with high average stress and parts with high peak stress at the stress concentration.
And by combining the structural characteristics and the process capability, the roughness requirement can be properly lowered for the part with smaller stress in the strength calculation result.
The size and dimension of the simulation piece are the same as the size and dimension of the simulated part of the wheel disc.
The beneficial technical effects are as follows:
and determining the surface strengthening part of the aeroengine turbine disc by combining the simulation calculation result, proposing the roughness requirement by combining the simulation calculation result and the machining process, and simultaneously determining the optimal shot blasting intensity and shot blasting coverage rate by using the simulation test result. The method determines the requirement of the surface integrity of the characteristic part of the aeroengine turbine disc by combining simulation calculation and test verification, and is scientific, reasonable, simple, convenient and feasible.
Drawings
FIG. 1 is a schematic view of a surface enhancement portion of a turbine disk;
FIG. 2 is a schematic view of a turbine disk mortise location.
Detailed Description
The present invention is described in further detail below. A method for determining the surface integrity of an aircraft engine turbine disk comprises the following specific implementation steps:
1. simulating and calculating the strength of each part of the aero-engine turbine disc under the most harsh working condition in actual use to obtain the stress distribution condition of each part of the turbine disc, and then providing the part needing shot peening strengthening according to the stress distribution condition; for example, the positions S1-S8 in fig. 1 and 2 are locations with higher stress in the strength calculation result, and need to be strengthened.
2. For the part needing shot peening strengthening, the surface roughness requirement of the part is put forward by combining the stress calculation result with the structural characteristics and the process capability of the part, the principle is that the capability which can be achieved by combining the process is combined, the roughness requirement is lowered for the part with smaller stress, and the roughness requirement is increased for the part with larger stress, particularly for the part with concentrated stress;
3. designing a simulation piece of each part, and performing simulation calculation on stress distribution of the simulation piece, wherein the applied temperature in the simulation calculation is the same as the most harsh temperature of the simulated wheel disc part under the actual working condition of an engine, the load is capable of ensuring that the main stress gradient after the simulation piece is loaded is consistent with the main stress gradient of the wheel disc under the most harsh working condition, and the roughness of the simulation piece in the machining process is the same as the roughness of a turbine disc;
4. shot blasting treatment with different shot blasting intensities and shot blasting coverage rates is respectively set for the simulation piece at the same part, and grouping is carried out, wherein each group is not less than three sub-samples, and the more the sub-samples are, the higher the reliability of the test result is; after the test is finished, performing fatigue tests in groups, determining the test temperature and the load according to the simulation calculation result in the step 3, performing the tests and respectively recording the fatigue life;
5. according to the test result, the requirements of the surface integrity of the structural feature parts of the turbine disc, including roughness, shot blasting strength and shot blasting coverage rate, are determined by combining the service life requirements and the process capability of the turbine disc, and the requirements of the reliability and the service life of the turbine disc are ensured on the principle;
the shot blasting coverage rate is 50% -300%; the method is consistent with the actual process coverage rate, and can ensure that each part of the wheel disc is smoothly implemented when being strengthened.
The shot strength is 0.24-0.45N or 0.1-0.22A. The method is consistent with the actual process coverage rate, and can ensure that each part of the wheel disc is smoothly implemented when being strengthened.
The primary stress gradients are consistent to ensure that the maximum primary stress gradients are consistent within the three-dimensional scale. The structure and the service life of the simulation part and the wheel disc simulation part are equivalent.
And the stress distribution in the step 1 is an elasticity calculation result. The stress distribution state of the wheel disc can be truly reflected.
The parts to be shot-peened in step 1 should include parts with high average stress and parts with high peak stress at the stress concentration. And considering all parts needing strengthening according to the intensity calculation result.
Combining the structural characteristics and the process capability, the roughness requirement can be properly lowered for the part with smaller stress in the strength calculation result, and the roughness requirement is improved for the part with larger stress; and (4) giving reasonable roughness requirements by considering the actual process capability.
The size and dimension of the simulation piece are the same as the size and dimension of the simulated part of the wheel disc. The simulation piece can be ensured to truly simulate the structural characteristics of the wheel disc.
Claims (8)
1. A method for determining the requirement of the surface integrity of a turbine disk of an aircraft engine is characterized by comprising the following steps:
step 1, simulating and calculating the strength of each part of a turbine disk of the aero-engine to obtain the stress distribution condition of each part of the turbine disk, and then providing the part needing shot peening strengthening according to the stress distribution condition;
step 2, for the part needing shot peening, combining the stress calculation result with the structural characteristics and the process capability of the part to provide the surface roughness requirement of the part;
step 3, designing simulation parts of all parts, and ensuring that the main stress gradient of the loaded simulation parts is consistent with the main stress gradient of the working state of the wheel disc under the condition of the same temperature, and simultaneously ensuring that the roughness of the simulation parts is the same as that of the turbine disc;
step 4, shot blasting treatment with different shot blasting strengths and shot blasting coverage rates is respectively set for the simulation parts at the same part, grouping is carried out, each group should be not less than three sub-samples, after the completion, fatigue test is carried out in groups, and the fatigue life is respectively recorded;
and 5, determining the surface integrity requirements of the structural feature parts of the turbine disc, including roughness, shot blasting strength and shot blasting coverage rate, according to the test result and by combining the use working condition and the process capability of the turbine disc.
2. The method for determining the surface integrity requirement of an aircraft engine turbine disk as claimed in claim 1, wherein the shot peening coverage is 50% -300%.
3. The method for determining the surface integrity requirement of an aircraft engine turbine disk as claimed in claim 1, wherein the shot peening intensity is 0.24-0.45N.
4. The method for determining the surface integrity requirement of an aircraft engine turbine disk as claimed in claim 1, wherein the principal stress gradients are uniform so as to ensure that the maximum principal stress gradients are uniform in three dimensions.
5. The method for determining the surface integrity requirement of the aeroengine turbine disk as claimed in claim 1, wherein the stress distribution in the step 1 is an elasticity calculation result.
6. The method for determining the surface integrity requirement of the aircraft engine turbine disk as claimed in claim 1, wherein the regions to be shot peened in step 1 include regions with higher average stress and regions with higher peak stress at the stress concentration.
7. The method for determining the requirement for the integrity of the surface of the aircraft engine turbine disk as claimed in claim 1, wherein the roughness requirement is lowered for the part with lower stress in the strength calculation result by combining the structural characteristics and the process capability.
8. The method for determining the surface integrity requirement of an aircraft engine turbine disk as claimed in claim 1, wherein the size and dimensions of the dummy are the same as the size and dimensions of the simulated portion of the disk.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113553788A (en) * | 2021-07-23 | 2021-10-26 | 中国航发贵阳发动机设计研究所 | Simulation calculation method for ventilation capacity of aircraft engine lubricating system |
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| CN112025561B (en) | 2022-11-18 |
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