CN115420481A - Debugging method for non-uniform temperature field in thermomechanical fatigue wall thickness direction of turbine blade of aero-engine - Google Patents
Debugging method for non-uniform temperature field in thermomechanical fatigue wall thickness direction of turbine blade of aero-engine Download PDFInfo
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Abstract
The invention relates to a debugging method for a non-uniform temperature field in the thermomechanical fatigue wall thickness direction of a turbine blade of an aero-engine, which comprises the following steps of (1) carrying out three-dimensional modeling on the turbine blade, and determining the non-uniform temperature distribution of the inner wall and the outer wall of the turbine blade according to the temperature check requirement of the turbine blade; (2) Carrying out heat transfer analysis on the turbine blade in finite element software, setting an outer wall surface temperature field, and continuously debugging the ventilation flow passing through the turbine blade so that the inner wall surface temperature field meets the examination requirements; (3) Manufacturing a turbine blade, and preparing a blade clamping and temperature control system before testing; (4) And (3) carrying out a test on the fatigue machine, controlling the temperature of the outer wall surface by the heating subsystem, controlling the temperature of the inner wall surface by the cooling subsystem, monitoring and checking the temperature by the thermocouple, and verifying whether the flow of the cooling air determined in the step (2) meets the requirement or not. The invention takes the finite element calculation method into consideration in debugging the temperature field in the wall thickness direction, and makes up for the deficiency of related research.
Description
Technical Field
The invention belongs to the technical field of aerospace engines, and particularly relates to a debugging method for a non-uniform temperature field in the thermal mechanical fatigue wall thickness direction of a turbine blade of an aerospace engine.
Background
The turbine blade is a key part for bearing high temperature and centrifugal stress in an aeroengine, alternating mechanical load and thermal load caused by starting, stopping and irregular maneuvering of the engine need to be borne in the service process of the turbine blade, the thermal mechanical fatigue is a main failure mode of the turbine blade, and the evaluation of the thermal mechanical fatigue life of the turbine blade is an important step in the design process of the engine. In the prior art, when the thermomechanical fatigue life of a single crystal blade is evaluated, a material test, a high cycle fatigue test and a low cycle fatigue test of parts are required, the tests all have corresponding temperature field requirements, if the temperature field does not meet the requirements, the service life of the evaluated blade is different from the actual condition, and serious fatigue damage accidents may occur when an engine works. Meanwhile, when the temperature fields of different blades are debugged, the positions of the heating equipment and the blades need to be repeatedly adjusted, if the debugging is directly carried out on a testing machine, the testing cost is extremely high, the testing efficiency is extremely low, and the progress of fatigue performance evaluation of the turbine blades is influenced.
The existing literature ' test research on the surface temperature field and comprehensive cooling effect of turbine blades ' J ' Dunlijie ' Xuangui ' on Cao Bo, yang Wei Hua ' Nanjing university school of aerospace, 2021,53 (03): 442-448) ' the change of the temperature field of the turbine blade along the wall thickness direction is not considered.
The finite element calculation method proposed by the existing Chinese invention patent CN111639401A, namely a method for calculating a temperature field in front of a turbine by using a temperature field behind the turbine, does not consider the temperature change along the wall thickness direction of the blade.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides a method for debugging the nonuniform temperature field in the thermomechanical fatigue wall thickness direction of the turbine blade of the aero-engine, which reduces the test cost by debugging and determining the cooling air flow in finite element software under the condition of fully reflecting the temperature field distribution of the inner wall and the outer wall of the turbine blade in the thermomechanical fatigue, and services and supports the thermomechanical fatigue test of the turbine blade of the aero-engine.
The technical solution of the invention is as follows: a method for debugging a nonuniform temperature field in the wall thickness direction of thermomechanical fatigue of a turbine blade of an aeroengine reduces test cost by a method for debugging and determining the flow of cooling air in finite element software under the condition of fully reflecting the temperature field distribution of the inner wall and the outer wall of the turbine blade in the thermomechanical fatigue, establishes an effective temperature field debugging method, and comprises the following steps:
step (1): performing three-dimensional modeling on the turbine blade, determining the examination temperature requirement of the turbine blade according to the actual working condition of the aero-engine, extracting the working temperature of key parts of the inner wall surface and the outer wall surface of the turbine blade, and examining the thermal mechanical fatigue performance of the turbine blade in the working temperature range;
step (2): carrying out finite element calculation on the temperature field of the turbine blade, and determining the temperature field of the outer wall surface of the turbine blade according to the examination temperature requirement of the outer wall surface; the quality flow of the cooling air is adjusted, so that the examination temperature of the inner wall surface of the turbine blade also meets the requirement, and the quality flow of the cooling air, which enables the examination temperatures of the inner wall and the outer wall of the turbine blade to meet the requirement at the same time, is obtained;
and (3): manufacturing a turbine blade, and performing a thermo-mechanical fatigue examination test on a thermo-mechanical fatigue test bed to complete clamping of the turbine blade and debugging work of the test bed;
and (4): when a thermomechanical fatigue examination test of the turbine blade is carried out, the temperature of the outer wall surface of the turbine blade is controlled through a heating subsystem of the thermomechanical fatigue test bed, and meanwhile, the mass flow of introduced cooling air is controlled through a cooling subsystem of the thermomechanical fatigue test bed, so that the temperature of the inner wall surface of the turbine blade is controlled.
Further, the method of determining the examination temperatures of the inner and outer wall surfaces of the turbine blade in the step (2) while satisfying the test requirements is a method in which the temperature deviation of the outer wall surface is ± 10 ℃ and the temperature deviation of the inner wall surface is ± 20 ℃.
Further, after the temperature field of the outer wall surface of the turbine blade is determined according to the examination temperature requirement of the outer wall surface in the step (2), the mass flow of the cooling air is adjusted through finite element simulation heat transfer calculation, and the mass flow of the cooling air when the examination temperature of the inner wall surface meets the requirement is determined.
Compared with the prior art, the invention has the advantages that: the invention relates to a method for debugging a non-uniform temperature field in a wall thickness direction, which can determine the mass flow of cooling air through finite element calculation after determining the examination temperature requirement of the outer wall surface of a turbine blade, so that the examination temperature of the inner wall surface also meets the requirement.
Drawings
FIG. 1 is an implementation flow of a debugging method of a non-uniform temperature field in the thermomechanical fatigue wall thickness direction of a turbine blade of an aeroengine, according to the invention;
FIG. 2 is a position check of the turbine blade of the present invention;
FIG. 3 is a finite element model of a turbine blade check site of the present invention;
FIG. 4 is a plot of the temperature at the check position after the cooling air is introduced to the turbine blade of the present invention;
FIG. 5 is a block diagram of a turbine blade thermal mechanical fatigue testing system of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and do not limit the invention. In addition, the technical features involved in the embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
The technical scheme of the debugging method for the non-uniform temperature field in the thermomechanical fatigue wall thickness direction of the turbine blade of the aero-engine is further explained by way of example with reference to the accompanying drawings. The test object of the example is an aeroengine turbine blade, the examination part is a blade middle section, and the specific implementation process is as follows:
firstly, determining a test object as a second-stage turbine blade of a certain type of aeroengine, and completing 1. Quantitative analysis is carried out on the working environment and the maximum stress position of the turbine blade, the position needing to be examined is selected as the middle section of the turbine blade according to the load condition of the turbine blade when the engine works, and the distribution of specific examination is shown in figure 2. The extracted finite element model of the assessment part is shown in figure 3, and the thermal mechanical fatigue resistance test research of the turbine blade is developed subsequently according to GJB 450A-2004 general requirements for equipment reliability work to assess the thermal mechanical fatigue resistance of the turbine blade.
And secondly, carrying out finite element calculation of the temperature field distribution of the turbine blade along the wall thickness direction on the basis of obtaining the three-dimensional model of the turbine blade and the test and assessment requirements. According to the temperature requirement of the outer wall examination, the temperature distribution along the wall periphery is interpolated and set in finite element analysis software Ansys-Fluent, and the cooling air is normal temperature air with the temperature set at 25 ℃. From the forced convection of the gas in the convection heat transfer, it was found that the convection heat transfer coefficient between the turbine blades and the gas was 28W/(m) 2 C.g. to be prepared into a preparation. After boundary conditions are set and the energy model is selected by the calculation model, the convective heat transfer analysis of the turbine blade and the cold air is carried out based on finite element analysis software Fluent,and determining the temperature field distribution of the turbine blade check part. And (3) continuously adjusting the mass and the flow of the cooling air passing through each cavity of the turbine blade, finally determining the flow of the cooling air, and enabling the examined temperatures of the inner wall and the outer wall of the turbine blade to all meet the requirements when the flow rate of the cooling air obtained in the calculation is 0.05m/s, wherein a temperature cloud chart of an examined section is shown in figure 4.
And thirdly, manufacturing the turbine blade and testing on a professional thermal mechanical fatigue testing stand. As shown in fig. 5, the test stand includes loading, heating, cooling, and control subsystems. The loading subsystem comprises a fatigue testing machine and a special clamp for the turbine blade. The heating subsystem comprises an induction coil and a high-frequency induction heating furnace. The control subsystem comprises a load controller, a normally closed electromagnetic valve and a temperature controller. The cooling subsystem is further divided into an air cooling subsystem and a water cooling subsystem according to a cooling mode. The air cooling subsystem comprises a three-way joint, a mass flow controller, a pressure reducing and stabilizing valve and an air compressor. The water cooling subsystem comprises a water storage tank and a water pump. And clamping the test blade on the fatigue testing machine through a special clamp for the turbine blade, heating the test blade through the high-frequency induction heating furnace and the induction coil after completing the debugging of the stress field, and controlling the mass flow of the introduced cold air through the air compressor and the mass flow controller.
The fourth step: according to the finite element calculation result of the second step, firstly, when a test temperature field is debugged, the examination temperature of the outer wall surface of the test blade is controlled by the heating subsystem, and the relative position of the induction coil and the examined test blade is continuously adjusted in the process to enable the examination temperature of the outer wall surface to meet the requirement, wherein the temperature deviation is +/-10 ℃; and controlling the mass flow of the introduced cooling air by a cooling subsystem, wherein the mass flow of the cooling air is determined according to the simulation result of the second step, the mass flow of the cooling air in the test is ensured to be consistent with that in the simulation, namely the flow rate of the cooling air is controlled to be 0.05m/s, so that the examination temperature of the inner wall surface of the test blade is controlled to meet the requirement, namely the temperature deviation of the outer wall surface of the turbine blade examination is +/-10 ℃, and the temperature deviation of the inner wall surface is +/-20 ℃.
The above examples are provided for the purpose of describing the present invention only, and are not intended to limit the scope of the present invention. The scope of the invention is defined by the appended claims. Various equivalent substitutions and modifications can be made without departing from the spirit and principles of the invention, and are intended to be included within the scope of the invention.
Claims (3)
1. A method for debugging a non-uniform temperature field in the thermomechanical fatigue wall thickness direction of a turbine blade of an aeroengine is characterized by comprising the following steps of:
step (1): carrying out three-dimensional modeling on the turbine blade, determining the examination temperature requirement of the turbine blade according to the actual working condition of the aero-engine, extracting the working temperature of key parts of the inner and outer wall surfaces of the turbine blade, and examining the thermal mechanical fatigue performance of the turbine blade within the working temperature range;
step (2): carrying out finite element calculation on the temperature field of the turbine blade, and determining the temperature field of the outer wall surface of the turbine blade according to the examination temperature requirement of the outer wall surface; the quality flow of the cooling air is adjusted, so that the examination temperature of the inner wall surface of the turbine blade also meets the requirement, and the quality flow of the cooling air, which enables the examination temperature of the inner wall surface and the outer wall surface of the turbine blade to meet the requirement at the same time, is obtained;
and (3): manufacturing a turbine blade, and performing a thermal mechanical fatigue examination test on a thermal mechanical fatigue test bed to finish the clamping of the turbine blade and the debugging work of the test bed;
and (4): when a thermomechanical fatigue examination test of the turbine blade is carried out, the temperature of the outer wall surface of the turbine blade is controlled through a heating subsystem of the thermomechanical fatigue test bed, and meanwhile, the mass flow of introduced cooling air is controlled through a cooling subsystem of the thermomechanical fatigue test bed, so that the temperature of the inner wall surface of the turbine blade is controlled.
2. The debugging method for the non-uniform temperature field in the wall thickness direction of the thermomechanical fatigue wall of the turbine blade of the aircraft engine according to claim 1 is characterized in that: the method for determining the examination temperatures of the inner wall surface and the outer wall surface of the turbine blade in the step (2) and simultaneously meeting the test requirements is that the temperature deviation of the outer wall surface is +/-10 ℃ and the temperature deviation of the inner wall surface is +/-20 ℃.
3. The debugging method for the non-uniform temperature field in the wall thickness direction of the thermomechanical fatigue wall of the aeroengine turbine blade as claimed in claim 1, wherein the debugging method comprises the following steps: after the temperature field of the outer wall surface of the turbine blade is determined according to the examination temperature requirement of the outer wall surface in the step (2), the mass flow of the cooling air is debugged through finite element simulation heat transfer calculation, and the mass flow of the cooling air when the examination temperature of the inner wall surface meets the requirement is determined.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US20230032755A1 (en) * | 2021-07-28 | 2023-02-02 | Nanjing University Of Aeronautics And Astronautics | High-temperature biaxial strength tester for ceramic matrix composite (cmc) turbine vane and test method thereof |
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