CN116050194B - Method for determining radial matching tightness of bolt-free baffle of turbine rotor - Google Patents
Method for determining radial matching tightness of bolt-free baffle of turbine rotor Download PDFInfo
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- CN116050194B CN116050194B CN202310340754.0A CN202310340754A CN116050194B CN 116050194 B CN116050194 B CN 116050194B CN 202310340754 A CN202310340754 A CN 202310340754A CN 116050194 B CN116050194 B CN 116050194B
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Abstract
The invention relates to the technical field of aeroengines, and discloses a method for determining radial matching tightness of a bolt-free baffle plate of a turbine rotor, wherein the upper limit value of the radial tightness between the baffle plate and a radial positioning surface of a turbine disc is obtained by carrying out stress and stress analysis of the baffle plate and a rotor assembly under different radial tightness when the engine is in a 0-maximum state process; and carrying out deformation analysis on the baffle plate and the rotor assembly under different radial tightness when the engine continuously maximum state is converted into the slow-running state, and obtaining a radial tightness lower limit value. According to the invention, the use characteristics of the bolt-free baffle of the turbine rotor in the aeroengine and the key transition state processes of stress, deformation and separation of the baffle are comprehensively considered, so that the upper limit value and the lower limit value of the radial tightness of the baffle are obtained, the reasonable radial tightness design value of the bolt-free baffle can be rapidly determined, the problem of radial expansion in the engine test process is effectively avoided, and the potential safety hazard caused by unbalance amount surge of the turbine rotor system in the engine working or test process is reduced.
Description
Technical Field
The invention relates to the technical field of aeroengines, and discloses a method for determining radial matching tightness of a bolt-free baffle of a turbine rotor.
Background
The structure of the baffle plate without the bolts is a structure form (figure 1) commonly adopted by turbine rotors of turbofan engines with high thrust-weight ratio and high performance at home and abroad, and is also an important part for preventing cooling air leakage and guiding the cooling air to enter the inner cavity of the blade according to a designed flow path, but because the baffle plate is of a thin-wall structure, the rigidity is smaller, the radius of the center of mass is high, the centrifugal load of the baffle plate cannot be born, and the baffle plate is required to be supported at the edge part of a turbine disc through a radial positioning cylindrical surface so as to ensure the reliable exertion of the functions of the baffle plate.
The domestic publication of the bolt-free connection structure of the turbine disk and the baffle plate indicates that the turbine disk has a thermal response slower than that of the baffle plate, and gaps can appear on the radial matching surface in the process of engine test run, so that the unbalance amount of the turbine rotor system is increased rapidly, potential safety hazards are caused, and a solution idea for applying tightness is provided. The radial tightness is usually applied by using experience to solve the problem by using mature engines abroad in engineering, but a method for determining the tightness is lacked. Excessive radial tightness may lead to local stress rise of the baffle to crack or low cycle fatigue failure, and smaller tightness may not achieve the goal of avoiding radial expansion of the baffle, so reasonable tightness design is crucial.
Disclosure of Invention
The invention aims to provide a method for determining radial matching tightness of a bolt-free baffle of a turbine rotor, which can rapidly determine a reasonable radial tightness design value of the bolt-free baffle while meeting the static strength and the low cycle fatigue life, and effectively avoid the problem of radial expansion in the process of engine test run.
In order to achieve the technical effects, the technical scheme adopted by the invention is as follows:
a method of determining radial fit tightness of a bolt-free baffle of a turbine rotor, comprising:
establishing the radial tightness of contact between a first radial positioning surface of the baffle plate and a second radial positioning surface of the turbine disk; the first radial positioning surface is arranged between the inner edge and the outer edge of the baffle, and the second radial positioning surface is positioned on the turbine disc and matched with the first radial positioning surface to form a contact pair;
carrying out stress and stress analysis on the baffle plate and the rotor assembly under different radial tightness in the 0-maximum state process of the engine to obtain the upper limit value of the radial tightness;
carrying out deformation analysis on the baffle plate and the rotor assembly under different radial tightness when the continuous maximum state of the engine is converted into the slow-running state, and obtaining a radial tightness lower limit value;
and determining the range from the lower limit value of the radial tightness to the upper limit value of the radial tightness as the design range of the radial tightness of the baffle.
Further, carrying out stress and stress analysis of the baffle plate and the rotor assembly under different radial tightnesses during the 0-maximum process of the engine to obtain a radial tightness upper limit value, wherein the method comprises the following steps:
obtaining the maximum extrusion force between the first radial positioning surface and the second radial positioning surface under different radial tightness and the stress value of the baffle;
calculating extrusion yield reserves under different radial tightnesses, fitting the extrusion yield reserves according to the different radial tightnesses and the corresponding extrusion yield reserves to obtain a function expression of the extrusion yield reserves and the radial tightnesses, and obtaining a first upper limit value of the radial tightnesses according to the minimum required design value of the extrusion yield reserves;
calculating stress values of the baffle plates with different radial tightnesses and corresponding stress values of the baffle plates, obtaining a functional expression of the stress values of the baffle plates and the radial tightnesses, and obtaining a second upper limit value of the radial tightnesses according to the maximum local plastic strain index requirement of the baffle plates;
calculating the cycle fatigue life of the baffle according to the baffle stress values of different radial tightnesses, and obtaining a third upper limit value of the radial tightnesses according to the required value of the cycle fatigue life of the engine design;
and taking the minimum value of the first upper limit value, the second upper limit value and the third upper limit value as the radial tightness upper limit value of the baffle plate.
Further, the squeeze yield reserve design requires a minimum of 1.5.
Further, the maximum local plastic strain index of the baffle is 0.5 times of the elongation of the baffle material.
Further, carrying out deformation analysis of the baffle plate and the rotor assembly under different radial tightness when the continuous maximum state of the engine is converted into the slow vehicle state, and obtaining a radial tightness lower limit value, wherein the method comprises the following steps of:
and obtaining axial clearance values between the outer edge of the baffle plate, which is close to the outer end face of the rim of the turbine disc, and the outer end face of the rim of the turbine disc according to deformation analysis, and determining that the radial tightness with the axial clearance value of zero is a radial tightness lower limit value.
Compared with the prior art, the invention has the following beneficial effects:
according to the invention, through comprehensively considering the use characteristics of the bolt-free baffle of the turbine rotor in the aeroengine, the key transition state processes of stress, deformation and separation of the baffle are fully considered, the upper limit value and the lower limit value of the radial tightness of the baffle are obtained, the reasonable radial tightness design value of the bolt-free baffle can be rapidly determined, the problem of radial expansion in the engine test run process is effectively avoided, and the potential safety hazard caused by unbalance amount surge of the turbine rotor system in the engine work or test run process is reduced.
Drawings
FIG. 1 is a block diagram of a turbine rotor bolting-free baffle and turbine disk installation in an embodiment;
FIG. 2 is an enlarged schematic view of portion A of FIG. 1;
1, a first radial positioning surface; 2. a second radial locating surface; 3. a baffle; 4. a turbine disk; 5. and a limiting ring.
Detailed Description
The present invention will be described in further detail with reference to the following examples and drawings. It should not be construed that the scope of the above subject matter of the present invention is limited to the following embodiments, and all techniques realized based on the present invention are within the scope of the present invention.
Examples
Referring to fig. 1-2, a method for determining radial matching tightness of a bolt-free baffle plate of a turbine rotor is provided, wherein the bolt-free baffle plate 3 of the turbine rotor is coaxially arranged with a turbine disc 4, the inner edge of the baffle plate 3 is fixedly connected with the installation edge of the turbine disc 4 through a limiting ring 5, and the limiting ring 5 is used for realizing axial and circumferential limiting of the installation edge of the baffle plate 3 and the turbine disc 4; the outer edge of the baffle plate 3 is positioned close to the outer end face of the rim of the turbine disc 4, a first radial positioning surface 1 which interacts with the turbine disc 4 is arranged between the inner edge and the outer edge of the baffle plate 3, and a second radial positioning surface 2 which is matched with the first radial positioning surface 1 is arranged on the turbine disc 4; the method comprises the following steps:
establishing the contact-to-radial tightness between the first radial positioning surface 1 of the baffle plate 3 and the second radial positioning surface 2 of the turbine disk 4;
carrying out stress and stress analysis on the baffle plate 3 and the rotor assembly under different radial tightness in the 0-maximum state process of the engine to obtain the upper limit value of the radial tightness;
carrying out deformation analysis of the baffle plate 3 and the rotor assembly under different radial tightness when the continuous maximum state of the engine is converted into the slow-running state, and obtaining a radial tightness lower limit value;
the range from the lower limit value of the radial tightness to the upper limit value of the radial tightness is determined as the design range of the radial tightness of the baffle plate 3.
In this embodiment, the relationship of the extrusion force of the radial positioning surface of the baffle 3 with time in the transition state "0-maximum state" is: the extrusion force of the radial positioning surface of the baffle plate 3 is increased in the pushing-up process of the throttle lever, and the stay stage is gradually reduced; the extrusion force of the radial positioning surface of the baffle 3 is reduced and even 0 in the process of pulling down the throttle lever; the first radial positioning surface 1 of the baffle plate 3 is maximum in extrusion force at the stage of starting to the maximum state, so that the extrusion force is determined as the upper limit value of radial tightness; deformation analysis of the baffle plate 3 and the rotor assembly under different radial tightnesses when the engine is continuously in the maximum state and is converted into the slow-running state, and the corresponding tightnesses are lower limit values when the axial clearance between the baffle plate 3 and the turbine disc 4 is 0. According to the invention, the use characteristics of the bolt-free baffle 3 of the turbine rotor in the aeroengine are comprehensively considered, the key transition state histories of stress, deformation and separation of the baffle 3 are fully considered, the upper limit value and the lower limit value of the radial tightness of the baffle 3 are obtained, the reasonable radial tightness design value of the bolt-free baffle 3 can be rapidly determined, the problem of radial expansion in the engine test run process is effectively avoided, and the potential safety hazard caused by the unbalance amount surge of the turbine rotor system in the engine work or test run process is reduced.
In this embodiment, in order to prevent the radial positioning surface of the baffle plate 3 from yielding due to excessive extrusion force, a certain extrusion yield reserve is ensured during design, and meanwhile, local stress strain control of the baffle plate 3 is ensured to be within a certain range, so that static strength (the burst rotational speed reserve is greater than 1.22) and low cycle fatigue life meet design requirements (the design requirements of an engine are met), and therefore, stress and stress analysis of the baffle plate 3 and a rotor assembly under different radial tightnesses during the process of '0-maximum state' of the engine is performed to obtain an upper limit value of the radial tightnesses, which comprises:
obtaining the maximum extrusion force between the first radial positioning surface 1 and the second radial positioning surface 2 under different radial tightness and the stress value of the baffle plate 3;
calculating to obtain extrusion yield reserves (maximum extrusion force/radial positioning surface contact area) under different radial tightness; fitting according to different radial tightnesses and corresponding extrusion yield reserves to obtain a function expression of the extrusion yield reserves and the radial tightnesses, and obtaining a first upper limit value of the radial tightnesses according to the minimum extrusion yield reserve design requirement (for example, the minimum extrusion yield reserve design requirement is 1.5 in the embodiment);
calculating stress values of the baffle plate 3 corresponding to different radial tightnesses, obtaining a functional expression of the stress values of the baffle plate 3 and the radial tightnesses, and obtaining a second upper limit value of the radial tightnesses according to the maximum local plastic strain index requirement of the baffle plate 3 (for example, the maximum local plastic strain index of the baffle plate 3 is 0.5 times of the material elongation rate of the baffle plate 3 in the embodiment);
calculating the cycle fatigue life (such as stress-life curve of the baffle plate 3, namely S-N curve) of the baffle plate 3 according to the stress values of the baffle plate 3 with different radial tightness, and obtaining a third upper limit value of the radial tightness according to the required value of the cycle fatigue life of the engine design;
the minimum value among the first upper limit value, the second upper limit value, and the third upper limit value is taken as the radial tightness upper limit value of the baffle 3.
By determining the minimum value of the first upper limit value, the second upper limit value and the third upper limit value as the radial tightness upper limit value of the baffle plate 3, the minimum radial extrusion yield reserve, the static strength and the low cycle fatigue life of the baffle plate 3 which simultaneously meet the design requirements can be ensured.
In this embodiment, deformation analysis of the baffle plate 3 and the rotor assembly under different radial tightnesses when the engine continuously maximum state is converted to the slow vehicle state is performed, and a radial tighteness lower limit value is obtained, including:
and under the condition that the continuous maximum state is converted into the slow-running state, calculating to obtain the axial clearance value of the baffle plate 3 and the turbine disc 4 by applying different radial tightnesses until the axial clearance is 0, and stopping until the radial tightnesses corresponding to the axial clearance of the baffle plate 3 and the turbine disc 4 are zero are lower limit values.
Or under the condition that the continuous maximum state is converted into the slow-running state, calculating to obtain the axial clearance value of the baffle plate 3 and the turbine disc 4 by applying a plurality of groups of different radial tightnesses, taking the axial clearance value as an independent variable, obtaining a function expression of the axial clearance and the radial tightnesses by least square fitting the radial tightnesses as a dependent variable, calculating to obtain the radial tightnesses corresponding to the axial clearance of 0 according to the function expression, and determining the radial tightnesses as a lower limit value Xmin.
And obtaining axial clearance values between the outer edge of the baffle plate 3, which is close to the outer end face of the rim of the turbine disc 4, and the outer end face of the rim of the turbine disc 4 according to deformation analysis, and determining the radial tightness with the axial clearance value of zero as a radial tightness lower limit value.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the invention.
Claims (3)
1. A method of determining radial fit tightness of a bolt-free baffle of a turbine rotor, comprising:
establishing the radial tightness of contact between a first radial positioning surface of the baffle plate and a second radial positioning surface of the turbine disk; the first radial positioning surface is arranged between the inner edge and the outer edge of the baffle, and the second radial positioning surface is positioned on the turbine disc and matched with the first radial positioning surface to form a contact pair;
carrying out stress and stress analysis on the baffle plate and the rotor assembly under different radial tightness in the 0-maximum state process of the engine to obtain the maximum extrusion force between the first radial positioning surface and the second radial positioning surface under different radial tightness and the stress value of the baffle plate;
calculating extrusion yield reserves under different radial tightnesses, fitting the extrusion yield reserves according to the different radial tightnesses and the corresponding extrusion yield reserves to obtain a function expression of the extrusion yield reserves and the radial tightnesses, and obtaining a first upper limit value of the radial tightnesses according to the minimum required design value of the extrusion yield reserves;
calculating stress values of the baffle plates with different radial tightnesses and corresponding stress values of the baffle plates, obtaining a functional expression of the stress values of the baffle plates and the radial tightnesses, and obtaining a second upper limit value of the radial tightnesses according to the maximum local plastic strain index requirement of the baffle plates;
calculating the cycle fatigue life of the baffle according to the baffle stress values of different radial tightnesses, and obtaining a third upper limit value of the radial tightnesses according to the required value of the cycle fatigue life of the engine design;
taking the minimum value of the first upper limit value, the second upper limit value and the third upper limit value as the radial tightness upper limit value of the baffle;
carrying out deformation analysis on the baffle plate and the rotor assembly under different radial tightness when the continuous maximum state of the engine is converted into the slow-running state, obtaining an axial clearance value between the outer edge of the baffle plate and the outer end face of the rim of the turbine disc under different radial tightness according to the deformation analysis, and determining that the radial tightness with zero axial clearance value is a radial tightness lower limit value;
and determining the range from the lower limit value of the radial tightness to the upper limit value of the radial tightness as the design range of the radial tightness of the baffle.
2. The method of determining the radial fit of a screw-less baffle for a turbine rotor of claim 1, wherein the minimum extrusion yield reserve design requirement is 1.5.
3. The method of determining the radial fit of a screw-free baffle for a turbine rotor of claim 1, wherein the baffle has a maximum local plastic strain index of 0.5 times the elongation of the baffle material.
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| CN116562106B (en) * | 2023-07-04 | 2023-10-03 | 中国航发四川燃气涡轮研究院 | Method for designing tightness of rotor spigot of aero-engine compressor |
| CN117744284B (en) * | 2024-02-21 | 2024-05-03 | 中国航发四川燃气涡轮研究院 | Method and device for designing length of pressure surface of spigot of compressor rotor |
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| CN111604734A (en) * | 2020-04-30 | 2020-09-01 | 中国航发南方工业有限公司 | Aeroengine compressor rotor grinding apex location aligning device |
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| WO2013053301A1 (en) * | 2011-10-11 | 2013-04-18 | 国家核电技术有限公司 | Hoisting method and hoisting system for hoisting assembling module of large-scale container |
| CN105822366B (en) * | 2016-04-20 | 2017-07-21 | 中国科学院工程热物理研究所 | A kind of engine low pressure rotor supporting structure that there is fusing to design |
| CN109356662B (en) * | 2018-11-27 | 2021-06-18 | 中国航发沈阳黎明航空发动机有限责任公司 | Process method for assembling low-pressure turbine rotor of aircraft engine |
| CN114662212B (en) * | 2022-02-22 | 2024-03-19 | 中国航发沈阳发动机研究所 | Method for determining typical transient operation process spectrum of aero-engine |
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| CN111604734A (en) * | 2020-04-30 | 2020-09-01 | 中国航发南方工业有限公司 | Aeroengine compressor rotor grinding apex location aligning device |
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