CN111748677A - Method for evaluating shot peening effect of turbine disk - Google Patents
Method for evaluating shot peening effect of turbine disk Download PDFInfo
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- CN111748677A CN111748677A CN202010526089.0A CN202010526089A CN111748677A CN 111748677 A CN111748677 A CN 111748677A CN 202010526089 A CN202010526089 A CN 202010526089A CN 111748677 A CN111748677 A CN 111748677A
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- C21—METALLURGY OF IRON
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- C21D7/00—Modifying the physical properties of iron or steel by deformation
- C21D7/02—Modifying the physical properties of iron or steel by deformation by cold working
- C21D7/04—Modifying the physical properties of iron or steel by deformation by cold working of the surface
- C21D7/06—Modifying the physical properties of iron or steel by deformation by cold working of the surface by shot-peening or the like
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Abstract
The invention belongs to the technical field of part surface treatment, and relates to a method for evaluating a shot peening strengthening effect of a turbine disc; the typical parts selected by the method, namely the mortise, the spoke plate and the disc center are all parts with prominent fatigue failure problems, and have good representativeness; the selected sample form and fatigue test method can reflect the typical fatigue failure mode of the typical part; an orthogonal method or a dichotomy is adopted, the process parameter combination and the number of samples take the double requirements of scientific research and production into consideration, and the method can be used for in-depth research and can also meet the production verification requirement; the selected surface integrity parameters, namely microhardness, surface residual stress and surface roughness, are parameters with higher detection accuracy and are also the most main parameters influencing fatigue performance; the surface roughness of the strengthened mortise, the spoke plate and the central hole is smaller than 1.2 mu m, the residual surface compressive stress is improved to-900 MPa, the depth of a hardened layer is obviously increased, and the method has obvious innovation.
Description
Technical Field
The invention belongs to the technical field of part surface treatment, and relates to a method for evaluating a shot peening strengthening effect of a turbine disc.
Background
The service environment of the turbine disc of the aircraft engine is very severe, and the risk of fatigue failure is high under the action of multiple cyclic loads such as high temperature, centrifugal force and the like. Shot peening strengthening is an effective method for improving the fatigue performance of metal parts based on surface plastic deformation strengthening, and is a processing method for improving the overall fatigue performance of materials by repeatedly carrying out elastic-plastic deformation on the surfaces of the materials through high-speed impact of a large number of shots to form a tissue strengthening layer and a residual compressive stress layer with certain depth. Because of the obvious anti-fatigue effect, the shot blasting process is widely applied to the processing and manufacturing of aeroengine turbine disks at home and abroad at present.
In the design and development process of the turbine disc, the structure and strength requirements need to be considered, and the weight reduction requirement needs to be met, so that the fatigue strength of the turbine disc needs to be improved by adopting various means. Shot peening is an effective technique. The traditional turbine disk peening process has single parameter, and fails to carry out the screening and optimization of peening process parameters in a targeted manner according to the service load, temperature and other differences of each key part of the turbine disk, and fails to fully exert the fatigue strength gain effect of peening. Therefore, it is urgently needed to develop diversified shot blasting process methods, and it is also urgently needed to adopt an evaluation method to provide guidance for screening and optimizing shot blasting process parameters. At present, a common evaluation method only takes surface integrity as a judgment basis or fatigue performance at a sample level as a judgment basis, and fails to consider structural singleness of a sample and structural complexity of part implementation, and fails to establish an evaluation mechanism of shot peening effect of a real part; in addition, the existing evaluation method also has the problem that the accuracy of the optimized process screening is reduced due to inconsistent judgment bases.
Disclosure of Invention
The purpose of the invention is: the method for evaluating the shot peening strengthening effect of the turbine disk can solve the problem that the screening basis and the evaluation method of the shot peening process of the typical part of the turbine disk are not systematic and comprehensive, provides a test means for fully exerting the shot peening strengthening effect, and meets the requirements of design and development of the turbine disk.
The technical scheme of the invention is as follows:
a method for evaluating the shot peening effect of a turbine disk is characterized by comprising the following steps: the method comprises the following steps:
1) dividing the turbine disc into three typical parts, namely a mortise, a spoke plate and a disc center hole, and respectively obtaining characteristic information of the typical parts;
2) respectively designing a rotary bending fatigue notch sample, an axial low-circumference notch sample and an axial low-circumference center hole sample according to the characteristic information of three typical positions of a mortise, a spoke plate and a disc center hole;
3) 3-6 groups of shot blasting process parameters are respectively selected for the three samples of the rotating bending fatigue notch sample, the axial low-circumference notch sample and the axial low-circumference center hole to carry out shot blasting reinforcement on each group of samples of each sample;
4) carrying out surface integrity analysis on each group of samples in the step 3);
5) simulating characteristic parameters of service temperature, load, loading frequency and stress ratio of a typical part, and testing the fatigue performance of the three samples to obtain a fatigue life gain effect;
6) establishing a corresponding relation among the technological parameters, the surface integrity and the fatigue life gain, and selecting the technological parameters with better fatigue performance and better surface integrity as the optimized technological parameters of a typical part;
7) shot peening strengthening is carried out on three typical parts, namely a mortise, a spoke plate and a disk center hole of the turbine disk by respectively adopting optimized process parameters;
8) respectively carrying out surface integrity analysis on three typical parts of the mortise, the spoke plate and the disc center hole after shot peening strengthening;
9) comparing and analyzing the surface integrity differences of the three typical parts of the turbine disc and the samples corresponding to the optimized process parameters, and evaluating the implementation effect of the optimized process on the turbine disc;
10) and if the effect is not good, adjusting the implementation method of the optimized shot blasting process, and repeating the step 7) to ensure that the surface integrity of the turbine disk is basically consistent with the surface integrity of the test sample corresponding to the optimized process parameters.
In the step 1), the characteristic information of the typical part mainly comprises service temperature, load, loading frequency, stress concentration, a processing method and structural interference.
And 3) performing shot peening strengthening in the step 3), wherein an orthogonal method or a dichotomy method is adopted.
The number of the samples used by each group of process parameters is 5-10.
The process parameters are shot blasting strength, coverage rate and shot.
The surface integrity in the step 4) mainly comprises the depth of a micro-hardening layer, the surface roughness and the surface residual stress.
In the step 5), simulating the service temperature and load of the mortise part, and carrying out high-temperature high-cycle fatigue test on the rotating bending fatigue notch sample; simulating the service temperature, load and loading frequency of the spoke plate part, and carrying out high-temperature low-cycle fatigue test on the axial low-cycle notch sample; and simulating the service temperature, load and loading frequency of the central hole part of the disc, and carrying out high-temperature low-cycle fatigue test on the axial low-cycle central hole sample.
In the step 6), the surface integrity preferably means a lower surface roughness value, a higher residual compressive stress value or a greater depth of hardened layer.
The invention has the advantages that:
firstly, the structure, strength, service and process characteristics of different parts of the turbine disk are fully considered, the screening and optimization of the shot blasting process of the turbine disk are carried out in a targeted manner, and the fatigue performance gain effect of shot blasting reinforcement is fully exerted; the typical parts selected by the method, namely the mortise, the spoke plate and the disc center are all parts with prominent fatigue failure problems, and have good representativeness; the selected sample form and fatigue test method can reflect the typical fatigue failure mode of the typical part; an orthogonal method or a dichotomy is adopted, the process parameter combination and the number of samples take the double requirements of scientific research and production into consideration, and the method can be used for in-depth research and can also meet the production verification requirement; the selected surface integrity parameters, namely microhardness, surface residual stress and surface roughness, are parameters with higher detection accuracy and are also the most main parameters influencing fatigue performance; the surface roughness of the strengthened mortise, the spoke plate and the central hole is smaller than 1.2 mu m, the residual surface compressive stress is improved to-900 MPa, the depth of a hardened layer is obviously increased, and the method has obvious innovation.
And secondly, the composite material has better fatigue strengthening effect. The method takes fatigue performance as a main criterion, takes the requirement of surface integrity into consideration, takes the sample-level performance as a reference, takes the strengthening effect improvement of a real turbine disk as a final basis, has clear target and feasible technical approach, and shows the result that the fatigue life and the fatigue strength of the sample and the turbine disk can be obviously improved by the optimized technological parameters obtained by the method.
Thirdly, the application prospect is wide, the high-temperature alloy turbine disc is widely applied to aerospace engines, but the service reliability of the high-temperature alloy turbine disc limits the popularization and application of the high-temperature alloy turbine disc. The evaluation method provided by the method is applied to the close-fitting engineering, is simple and effective, and has huge and wide application prospect.
Detailed Description
A method of evaluating the effects of shot peening of a turbine disk, the method comprising the steps of:
1) dividing the turbine disc into three typical parts, namely a mortise, a spoke plate and a disc center hole, and respectively obtaining characteristic information of the typical parts; the characteristic information of the typical part mainly comprises service temperature, load, loading frequency, stress concentration, a processing method, structural interference and the like;
2) respectively designing a rotary bending fatigue notch sample, an axial low-circumference notch sample and an axial low-circumference center hole sample according to the characteristic information of the typical part;
3) shot peening the three samples; and (3) designing 3-6 groups of process parameters by adopting an orthogonal method or a bisection method to carry out shot peening strengthening on each sample, wherein the number of the samples used in each group of process parameters is 5-10, and the shot peening process parameters comprise shot peening intensity, coverage rate and shots.
4) Carrying out surface integrity analysis on the three samples; surface integrity includes, among other things, micro-hardened layer depth, surface roughness, and surface residual stress.
5) Simulating characteristic parameters of a typical part, such as service temperature, load, loading frequency, stress ratio and the like, and carrying out fatigue performance test on the three samples to obtain a fatigue life gain effect; simulating the service temperature and load of the mortise part, and carrying out high-temperature high-cycle fatigue test on the rotating bending fatigue notch sample; simulating the service temperature, load and loading frequency of the spoke plate part, and carrying out high-temperature low-cycle fatigue test on the axial low-cycle notch sample; and simulating the service temperature, load and loading frequency of the central hole part of the disc, and carrying out high-temperature low-cycle fatigue test on the axial low-cycle central hole sample.
6) Establishing a corresponding relation among the technological parameters, the surface integrity and the fatigue life gain, and selecting the technological parameters with better fatigue performance and better surface integrity as the optimized technological parameters of a typical part; more preferred surface integrity means a lower surface roughness value, a higher residual compressive stress value or a greater depth of hardened layer.
7) Shot peening strengthening is carried out on three typical parts, namely a mortise, a spoke plate and a disk center hole of the turbine disk by respectively adopting optimized process parameters;
8) respectively carrying out surface integrity analysis on the three typical positions;
9) comparing and analyzing the surface integrity differences of the three typical parts of the turbine disc and the samples corresponding to the optimized process parameters;
10) and if the effect is not good, adjusting the implementation method of the optimized shot blasting process, and repeating the step 7) to ensure that the surface integrity of the turbine disk is basically consistent with the surface integrity of the test sample corresponding to the optimized process parameters.
The working principle of the invention is as follows:
the method takes fatigue performance as a main criterion, takes the requirement of surface integrity into consideration, takes sample-level performance as a reference, takes the enhancement effect improvement of a real turbine disk as a final target, obtains an optimized anti-fatigue enhancement effect by establishing the correlation between the sample-level surface integrity and the fatigue performance, and establishes a shot peening enhancement effect evaluation method of a part level (the real turbine disk) by taking the surface integrity as a basis.
Example 1
The following detailed description of the embodiments of the present invention is provided in conjunction with the following embodiments, but the present invention should not be limited to the embodiments:
a method of evaluating the effects of shot peening of a turbine disk, the method comprising the steps of:
1) dividing a certain high-temperature alloy turbine disc into three typical parts, namely a mortise, a web and a disc core hole, wherein the service temperature of the mortise is 500 ℃, the service temperature of the web is 300 ℃, and the service temperature of the disc core hole is 200 ℃;
2) according to the service temperature of the typical part, designing a rotary bending fatigue notch sample according to HB 5153-;
3) shot peening is carried out on the three samples by adopting parameter combinations in the table 1;
4) carrying out surface integrity analysis on the three samples, wherein the surface roughness value, the surface residual compressive stress value and the depth value of the hardened layer are shown in a table 2;
5) simulating the service temperature and load of the mortise part, and carrying out high-temperature high-cycle fatigue test on the rotating bending fatigue notch sample under the test conditions of 500 ℃, 300rpm and 500MPa of external load; simulating the service temperature, load and loading frequency of a radial plate part, and carrying out high-temperature low-cycle fatigue test on an axial low-cycle notch sample under the test conditions of 300 ℃, the total strain being 1%, the stress ratio R being-1, the frequency being 1Hz and triangular waves; simulating the service temperature, load and loading frequency of the disc center hole part, and carrying out high-temperature low-cycle fatigue test on the axial low-cycle center hole sample under the test conditions of 200 ℃, the total strain of 1%, the stress ratio R of-1, the frequency of 0.33Hz and triangular waves; the fatigue life gain effects are shown in table 3;
6) as can be seen from table 3, in the present embodiment, a corresponding relationship between the process parameters, the surface integrity and the fatigue life gain is established, the fatigue life gain effect and the surface integrity data are comprehensively considered, and for the mortise part, the process No. 2 is selected as the optimization process; selecting the No. 6 process as an optimized process for the spoke plate part; for the core hole, process No. 10 was selected as the optimized process.
7) In the embodiment, a certain high-temperature alloy turbine disk is selected, and shot blasting strengthening is performed on three typical parts of a mortise, a spoke plate and a disk center hole of the turbine disk by respectively adopting optimized process parameters;
8) surface integrity analysis was performed on each of the three representative sites, as shown in table 4;
9) by comparing the turbine disc mortise and the No. 2 process sample, the web and the No. 6 process sample, and the disc center hole and the No. 10 process sample, it can be found that the surface integrity typical parameters of the three parts, namely the surface roughness value, the surface residual stress value and the depth value of the micro-hardened layer, are basically consistent with those of the sample, which indicates that the implementation effect of the optimization process on the real turbine disc is good.
TABLE 1 shot peening Process parameter combinations
TABLE 2 surface roughness values, surface residual compressive stress values and depth values of hardened layer of samples after different shot blasting processes
TABLE 3 fatigue life gain effects of different shot peening processes
TABLE 4 surface roughness, residual compressive stress and depth of hardened layer of real turbine disk after optimized shot blasting
Claims (8)
1. A method for evaluating the shot peening effect of a turbine disk is characterized by comprising the following steps: the method comprises the following steps:
1) dividing the turbine disc into three typical parts, namely a mortise, a spoke plate and a disc center hole, and respectively obtaining characteristic information of the typical parts;
2) respectively designing a rotary bending fatigue notch sample, an axial low-circumference notch sample and an axial low-circumference center hole sample according to the characteristic information of three typical positions of a mortise, a spoke plate and a disc center hole;
3) 3-6 groups of shot blasting process parameters are respectively selected for the three samples of the rotating bending fatigue notch sample, the axial low-circumference notch sample and the axial low-circumference center hole to carry out shot blasting reinforcement on each group of samples of each sample;
4) carrying out surface integrity analysis on each group of samples in the step 3);
5) simulating characteristic parameters of service temperature, load, loading frequency and stress ratio of a typical part, and testing the fatigue performance of the three samples to obtain a fatigue life gain effect;
6) establishing a corresponding relation among the technological parameters, the surface integrity and the fatigue life gain, and selecting the technological parameters with better fatigue performance and better surface integrity as the optimized technological parameters of a typical part;
7) shot peening strengthening is carried out on three typical parts, namely a mortise, a spoke plate and a disk center hole of the turbine disk by respectively adopting optimized process parameters;
8) respectively carrying out surface integrity analysis on three typical parts of the mortise, the spoke plate and the disc center hole after shot peening strengthening;
9) comparing and analyzing the surface integrity differences of the three typical parts of the turbine disc and the samples corresponding to the optimized process parameters, and evaluating the implementation effect of the optimized process on the turbine disc;
10) and if the effect is not good, adjusting the implementation method of the optimized shot blasting process, and repeating the step 7) to ensure that the surface integrity of the turbine disk is basically consistent with the surface integrity of the test sample corresponding to the optimized process parameters.
2. The method for evaluating the shot peening effect of the turbine disk as claimed in claim 1, wherein: in the step 1), the characteristic information of the typical part mainly comprises service temperature, load, loading frequency, stress concentration, a processing method and structural interference.
3. The method for evaluating the shot peening effect of the turbine disk as claimed in claim 1, wherein: and 3) performing shot peening strengthening in the step 3), wherein an orthogonal method or a dichotomy method is adopted.
4. The method for evaluating the shot peening effect of the turbine disk as claimed in claim 1, wherein: the number of the samples used by each group of process parameters is 5-10.
5. The method for evaluating the shot peening effect of the turbine disk as recited in claim 4, wherein: the process parameters are shot blasting strength, coverage rate and shot.
6. The method for evaluating the shot peening effect of the turbine disk as claimed in claim 1, wherein: the surface integrity in the step 4) mainly comprises the depth of a micro-hardening layer, the surface roughness and the surface residual stress.
7. The method for evaluating the shot peening effect of the turbine disk as claimed in claim 1, wherein: in the step 5), simulating the service temperature and load of the mortise part, and carrying out high-temperature high-cycle fatigue test on the rotating bending fatigue notch sample; simulating the service temperature, load and loading frequency of the spoke plate part, and carrying out high-temperature low-cycle fatigue test on the axial low-cycle notch sample; and simulating the service temperature, load and loading frequency of the central hole part of the disc, and carrying out high-temperature low-cycle fatigue test on the axial low-cycle central hole sample.
8. The method for evaluating the shot peening effect of the turbine disk as claimed in claim 1, wherein: in the step 6), the surface integrity preferably means a lower surface roughness value, a higher residual compressive stress value or a greater depth of hardened layer.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112338814A (en) * | 2020-10-29 | 2021-02-09 | 中国航发南方工业有限公司 | Composite shot blasting method for turbine disk |
| CN114250343A (en) * | 2021-12-10 | 2022-03-29 | 浙江欧迪恩传动科技股份有限公司 | Production, calculation, heating and verification method for reducing strength difference of mandrel |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070003418A1 (en) * | 2005-06-30 | 2007-01-04 | Rockstroh Todd J | Countering laser shock peening induced airfoil twist using shot peening |
| CN103196916A (en) * | 2013-02-27 | 2013-07-10 | 中航飞机股份有限公司西安飞机分公司 | Surface quality detection method and template for shot blasting of wing panel |
| CN104245188A (en) * | 2012-06-27 | 2014-12-24 | 新东工业株式会社 | Shot peening method, shot peening evaluation method, and shot peening evaluation assembly structure |
| CN105651957A (en) * | 2016-01-06 | 2016-06-08 | 广东工业大学 | Method for assessing laser shot peening effect |
| CN106636589A (en) * | 2016-10-08 | 2017-05-10 | 中国航空工业集团公司北京航空制造工程研究所 | Shot peening strengthening method for controlling hollow blade deformation |
-
2020
- 2020-06-10 CN CN202010526089.0A patent/CN111748677B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070003418A1 (en) * | 2005-06-30 | 2007-01-04 | Rockstroh Todd J | Countering laser shock peening induced airfoil twist using shot peening |
| CN104245188A (en) * | 2012-06-27 | 2014-12-24 | 新东工业株式会社 | Shot peening method, shot peening evaluation method, and shot peening evaluation assembly structure |
| CN103196916A (en) * | 2013-02-27 | 2013-07-10 | 中航飞机股份有限公司西安飞机分公司 | Surface quality detection method and template for shot blasting of wing panel |
| CN105651957A (en) * | 2016-01-06 | 2016-06-08 | 广东工业大学 | Method for assessing laser shot peening effect |
| CN106636589A (en) * | 2016-10-08 | 2017-05-10 | 中国航空工业集团公司北京航空制造工程研究所 | Shot peening strengthening method for controlling hollow blade deformation |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112338814A (en) * | 2020-10-29 | 2021-02-09 | 中国航发南方工业有限公司 | Composite shot blasting method for turbine disk |
| CN114250343A (en) * | 2021-12-10 | 2022-03-29 | 浙江欧迪恩传动科技股份有限公司 | Production, calculation, heating and verification method for reducing strength difference of mandrel |
| CN114250343B (en) * | 2021-12-10 | 2023-10-31 | 浙江欧迪恩传动科技股份有限公司 | Production, calculation, heating and verification method for reducing mandrel strength difference |
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