CN111950169A - Method and device for determining vibration limit of blade tip of rotor blade of aircraft engine - Google Patents
Method and device for determining vibration limit of blade tip of rotor blade of aircraft engine Download PDFInfo
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Abstract
The invention provides a method for determining blade tip vibration limitation of an aeroengine rotor blade, which is characterized in that a GoodMan curve of a blade is determined by multiplying a correction coefficient obtained by a blade vibration fatigue test by a GoodMan curve of a blade material, and a safety coefficient is set for the GoodMan curve; carrying out static strength analysis and modal analysis on the blade to obtain static strength analysis results and modal analysis results at different rotating speeds; obtaining allowable vibration stress of each point on the blade at different rotating speeds by combining the GoodMan curve of the blade and the static stress obtained by the static strength analysis result; and evaluating the danger degree of each point of the blade by adopting the AF dynamic stress reserve coefficient eta, and limiting the blade tip vibration of the blade according to the AF dynamic stress reserve coefficient eta. The invention also provides a determining device for executing the method. The method can be used for determining the vibration limit of the blade tip of the rotor blade of the aircraft engine.
Description
Technical Field
The invention relates to a method and a device for determining blade tip vibration limit of an aeroengine rotor blade
Background
In an aircraft turbine engine, the blades are susceptible to vibration. Statistics show that damage incidents (cracks, fractures, etc.) of the blade are mostly due to vibrations. The vibratory stresses are the basis for determining whether the blade can withstand such vibrations or for estimating the life of the blade.
The typical method in the field of blade vibration measurement is to monitor the state of a rotating blade by sticking a resistance strain gauge, and to measure the dynamic stress value and the vibration frequency of the blade during vibration, so as to evaluate the running state of the blade. However, the rotating blade is mostly under working conditions of high temperature, high pressure, impact load, high rotating speed and the like, the reliability of strain gauge measurement is difficult to guarantee in the complex environment, and the condition of failure of a patch signal is easily generated. Meanwhile, the method of attaching the strain gauge has the following problems: 1) the strain gauge destroys the dynamic performance of the blade and even influences the pneumatic efficiency; 2) the requirement on the position of a patch is high, and stress values of different sticking positions may differ by several times; 3) the whole measurement of the whole-stage blade in the whole machine is difficult, the dispersion of the blade cannot be considered, and the monitoring hidden trouble is generated.
Therefore, the non-contact type blade vibration monitoring technology has great advantages, the non-contact type measuring method widely used at present is a blade tip timing method, and the vibration condition of the blade is analyzed by measuring the time of the rotating blade reaching the sensor and the lead and lag of the theoretical reaching time through the sensor arranged on the solid casing.
In the test process of the aircraft engine, in order to ensure the safe operation of a test piece, the vibration stress of the blade needs to be monitored in real time, and whether the vibration stress exceeds the limit is identified and judged. When the vibration stress exceeds the limit, the design is combined to judge and make measures, so that the catastrophic consequences caused by the initiation and the diffusion of the blade cracks due to the vibration stress exceeding the limit are prevented.
Therefore, when the blade tip timing method (BTT) is used to monitor the vibration state of the blade, the blade tip vibration limitation needs to be determined, including the evaluation of the risk level of each point of the blade, or the setting of the limit value (including the alarm value and the limit value) of the blade tip amplitude, which is used to reflect the state of the most dangerous point on the blade, so as to ensure the safe operation of the test piece.
Disclosure of Invention
It is an object of the present invention to provide a method by which the limit of blade tip vibration of an aircraft engine rotor blade can be determined.
The invention providesThe method for determining the blade tip vibration limit of the rotor blade of the aircraft engine is characterized in that a GoodMan curve of a blade is determined by multiplying a correction coefficient obtained by a blade vibration fatigue test by a GoodMan curve of a blade material, and a safety coefficient is set for the GoodMan curve; carrying out static strength analysis and modal analysis on the blade to obtain static strength analysis results and modal analysis results at different rotating speeds; obtaining allowable vibration stress of each point on the blade at different rotating speeds by combining the GoodMan curve of the blade and the static stress obtained by the static strength analysis result; evaluating the danger degree of each point of the blade by adopting AF dynamic stress reserve coefficient eta, wherein sigmaAfRepresenting the modal stress of the corresponding point of the blade in unit Af; sigmaAllowable useRepresenting allowable vibration stress of the corresponding point; sigmaModalityRepresenting the modal stress of the corresponding point, A representing the maximum displacement of the blade body in the corresponding mode, f representing the vibration frequency of the blade in the corresponding mode, and sigmaModalityA, f is determined from the modal analysis results; calculating the Af dynamic stress reserve coefficient eta of all the points of the blade,
the smaller the value of eta is, the more dangerous the node position on the blade is, and the blade tip vibration is limited according to the AF dynamic stress reserve coefficient eta.
In one embodiment, the Af dynamic stress reserve coefficient for the most dangerous point is the smallest, labeled as ηmin(ii) a According to the modal analysis result, acquiring the circumferential displacement of the blade tip position corresponding to the BTT sensor position: u shapeCircumferential directionDetermining a limit value of the amplitude of the blade tip, the limit value including an alarm value and a limit value, the limit value being marked uExtreme limitThe alarm value is marked as uAlarm device，
uAlarm device＝uExtreme limitAlarm coefficient
The alarm coefficient is less than 1.
In one embodiment, the safety factor is between 30% and 50%. .
In one embodiment, the alarm coefficient is 0.75.
In one embodiment, the correction factor is related to the size, forming process and/or surface treatment of the blade.
In one embodiment, the blade static strength analysis and the modal analysis are performed by using a finite element simulation method.
In one embodiment, the material parameters of the computational model of the finite element simulation method are set in relation to temperature.
The invention also provides a device for determining the limit of the blade tip vibration of the rotor blade of the aircraft engine, which comprises a controller, wherein the controller comprises a memory and a processor, the memory stores a computer program, and when the program is executed by the processor, the risk degree of points on the blade can be determined by utilizing the Af dynamic stress reserve coefficient eta obtained by the method, so that the blade tip vibration is limited according to the AF dynamic stress reserve coefficient eta.
The invention also provides a device for determining the limit of blade tip vibration of a rotor blade of an aeroengine, comprising a controller including a memory and a processor, the memory storing a computer program which, when executed by the processor, enables u to be obtained using the method described aboveExtreme limit、uAlarm deviceA tip amplitude limit is determined.
In the method and the device for determining the blade tip vibration limitation of the rotor blade of the aero-engine, correction coefficients such as size, forging machine processing and surface treatment correction coefficients are adopted to obtain a part-level GoodMan curve of the blade, namely the GoodMan curve of the blade based on a material-level GoodMan curve, namely the GoodMan curve of the blade material. Wherein, the correction coefficient is obtained by accumulation on the basis of a previous test. Thereby further developing the vibration fatigue test of the blades in large batch.
The AF dynamic stress reserve coefficient eta is adopted to judge the most dangerous point on the blade. Wherein, the smaller the AF dynamic stress reserve coefficient eta is, the more dangerous the corresponding position of the node is. When the most dangerous point on the blade is judged, the influence of static strength on the most dangerous point is considered by combining a GoodMan curve.
The blade tip amplitude limiting value is obtained and can be used for testing safety monitoring. The limiting value has different values at different rotation speeds and different orders. The state of the most dangerous point on the blade is reflected by determining the amplitude limit value of the blade tip, and support is provided for safe operation of the test.
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The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:
FIG. 1 is a schematic diagram of a determination method according to one embodiment.
Detailed Description
The present invention will be further described with reference to the following detailed description and the accompanying drawings, wherein the following description sets forth further details for the purpose of providing a thorough understanding of the present invention, but it is apparent that the present invention can be embodied in many other forms other than those described herein, and it will be readily apparent to those skilled in the art that the present invention may be embodied in many different forms without departing from the spirit or scope of the invention.
For example, a first feature described later in the specification may be formed over or on a second feature, and may include embodiments in which the first and second features are formed in direct contact, and may also include embodiments in which additional features may be formed between the first and second features, such that the first and second features may not be in direct contact. Additionally, reference numerals and/or letters may be repeated in the various examples throughout this disclosure. This repetition is for the purpose of simplicity and clarity and does not in itself dictate a relationship between the various embodiments and/or configurations discussed. Further, when a first element is described as being coupled or coupled to a second element, the description includes embodiments in which the first and second elements are directly coupled or coupled to each other, as well as embodiments in which one or more additional intervening elements are added to indirectly couple or couple the first and second elements to each other.
It is to be noted that the conversion modes in the different embodiments may be appropriately combined, and the described order of the steps may also be converted.
The invention relates to a method for determining the blade tip vibration limit of an aeroengine rotor blade, which comprises the following steps:
step one (S11 in fig. 1): and multiplying the correction coefficient a obtained by the blade vibration fatigue test by the GoodMan curve of the blade material to determine the GoodMan curve of the blade, and setting a safety factor b for the GoodMan curve.
The GoodMan curve for a blade material, otherwise known as a material grade GoodMan curve, may be obtained, for example, by consulting a materials handbook, without which at least the fatigue & tensile limits of the materials used would need to be consulted. This data may reflect a correlation with temperature.
The correction coefficient a may be obtained by querying a vibration fatigue test library, and may include, for example, a size, a forging machine, a surface treatment correction coefficient, and the like, that is, the correction coefficient a may be related to a size, a forming process, and/or a surface treatment of the blade.
The material grade GoodMan curve may be multiplied by a correction factor a to obtain a blade GoodMan curve, for example, which may be obtained by multiplying both the ordinate and the abscissa of the material grade GoodMan curve by the correction factor a. This data may reflect a correlation with temperature.
The safety factor b set for the GoodMan curve may be, for example, 30% to 50% or the like, depending on the engineering safety factor requirements.
The fatigue limit of the blade, which is a parameter of the GoodMan curve, may be used to determine the allowable vibratory stress of the blade at a given static stress. The fatigue limit of the blade and the material grade fatigue limit are different because the raw materials, forging process, machining process, surface treatment, etc. all affect the fatigue limit of the blade. In the first step, based on the developed blade vibration fatigue test, a material-grade GoodMan curve is compared to obtain a relevant correction coefficient (a size correction coefficient, a forging machine machining correction coefficient and a surface treatment correction coefficient), and then the GoodMan curve of the blade is obtained according to the relevant correction coefficient and the material-grade GoodMan curve. Thus, the above-described factors can all be taken into consideration, so that more accurate blade vibration fatigue characteristics can be obtained.
Step two (S2 in fig. 1): the static strength analysis (S12 in fig. 1) and the modal analysis (S21 in fig. 1) of the blade are performed to obtain static strength analysis results and modal analysis results at different rotation speeds.
Referring to fig. 1, the blade static strength analysis and the modal analysis may be performed by using a finite element simulation method, for example. For example, as shown in fig. 1, finite element simulation is adopted, and the static strength calculation of the blade at different rotating speeds is firstly carried out; then carrying out modal analysis with prestress at different rotating speeds by adopting finite element simulation based on a static strength result; to obtain the static strength analysis results and modal analysis structure at different rotation speeds, e.g. static stress sigma at different rotation speedsQuietAnd modal stress σModality. The modal analysis may compute a cell solution.
The danger points are not always consistent under different rotating speeds, and the probability of resonance occurring under different rotating speeds according to the Campbell diagram is also different, so that the development of static strength analysis and modal analysis under different rotating speeds is favorable for judging the danger points.
Before the finite element simulation is carried out, input information required for carrying out finite element simulation calculation can be prepared, as shown in fig. 1, the input information can comprise a geometric model, load information (rotating speed, aerodynamic load, temperature field, cavity pressure and the like) and material parameters (density, elastic modulus, poisson ratio, thermal expansion coefficient and the like), and then a finite element model for blade simulation analysis or a calculation model can be established according to the prepared input information. Therein, the material parameter of the computational model of the finite element simulation method may be set in relation to the temperature, i.e. the material parameter is temperature dependent, so that the change of the material parameter with the temperature may be reflected.
Step three (S22 in fig. 1): static stress sigma obtained by combining the GoodMan curve of the blade and the result of the static strength analysisQuietObtaining allowable vibration of each point on the blade at different rotating speedsStress sigmaAllowable use。
Wherein allowable vibration stress sigmaAllowable useThe calculation of (c) may take into account the safety factor b in step one or S11.
Step four (not shown in fig. 1): and (3) evaluating the danger degree of each point of the blade by adopting the AF dynamic stress reserve coefficient eta.
Wherein σAfRepresenting the modal stress of the corresponding point of the blade in unit Af; sigmaAllowable useRepresenting allowable vibration stress of the corresponding point; sigmaModalityThe modal stress of the corresponding point is represented, A represents the maximum displacement of the blade body under the corresponding mode, and f represents the vibration frequency of the blade under the corresponding mode. SigmaModalityA, f may each be determined from the modal analysis results described above; calculating the Af dynamic stress reserve coefficient eta of all the points of the blade,
the smaller the value of η, the more dangerous the position of this node on the blade.
And the Af dynamic stress reserve coefficient eta of the most dangerous point is minimum, so that the most dangerous point on the blade at different rotating speeds can be obtained, and the point with the minimum eta value is the most dangerous point.
And in the fourth step, finite element simulation calculation is adopted, the static strength analysis and the modal analysis of the blade at different rotating speeds are carried out, and the GoodMan curve of the blade is combined, so that the dangerous points at different rotating speeds can be obtained.
Step five (not shown in fig. 1): the blade tip vibration can be limited according to the AF dynamic stress reserve coefficient eta subsequently.
The method for determining the blade tip vibration limitation of the rotor blade of the aero-engine, provided by the invention, can be used for judging the most dangerous point of the blade at different rotating speeds. The determination of the most dangerous point of the blade can simultaneously consider the static strength and the vibration stress. When the rotating speed changes, aerodynamic load, temperature field and centrifugal force load all change, and the most dangerous point of the change can be the maximum point of static strength, the maximum point of modal stress or the point with larger static strength and modal stress. The determination method according to the present invention may evaluate the risk level of each point of the blade by taking all the above factors into consideration, and may determine the most dangerous point.
As shown in fig. 1, the method for determining the vibration limit of the blade tip of the aircraft engine rotor blade according to the present invention further involves determining a blade tip amplitude limit value, which may be used for test safety monitoring. In fig. 1, the first-order mode shape is taken as an example (for example, the first-order bending mode shape of the blade), and other order mode shapes are also applicable.
Specifically, referring to fig. 1, through the fourth step, the most dangerous point on the blade at different rotating speeds, i.e., S32 in fig. 1, is obtained, and the Af dynamic stress reserve coefficient η of the most dangerous point is the minimum and is marked as ηmin。
The determination method further includes:
step six (S31 in fig. 1): according to the modal analysis result, acquiring the circumferential displacement of the blade tip position corresponding to the BTT sensor position: u shapeCircumferential direction。
Prior to S31, at S20, the axial position of the tip timing (BTT) sensor mounted on the case is obtained. The position corresponds to a certain axial position on the blade tip of the movable blade. And then obtaining the circumferential displacement U of the blade tip position corresponding to the BTT sensor position based on the modal analysis in S21Circumferential direction。
Step seven (S4 in fig. 1): determining a limit value of the blade tip amplitude, the limit value including an alarm value and a limit value, the limit value being marked uExtreme limitThe alarm value is marked as uAlarm device，
uAlarm device＝uExtreme limitAlarm coefficient
Wherein the alarm coefficient is less than 1. For example, the alarm coefficient may be 0.75.
The limiting values (including alarm values and limiting values) of the blade tip vibration amplitude in the test can be determined through the means, so that the alarm and limiting states of the most dangerous points of the blade can be reflected. And when carrying out the aeroengine test, for adopting apex timing (BTT) monitoring blade vibration and confirming the limiting value (alarm value and limiting value) of apex amplitude, thereby can support test piece safe operation. Meanwhile, the method can play a positive supporting role when the CCAR-33.83 clause is carried out for airworthiness evidence collection.
The invention also provides a device for determining the vibration limit of the blade tip of the rotor blade of the aircraft engine, which comprises a controller, wherein the controller comprises a memory and a processor. A controller such as one or more combinations of microcontrollers, microprocessors, Reduced Instruction Set Computers (RISC), Application Specific Integrated Circuits (ASIC), application specific instruction integrated processors (ASIP), Central Processing Units (CPU), Graphics Processing Units (GPU), Physical Processing Units (PPU), microcontroller units, Digital Signal Processors (DSP), Field Programmable Gate Arrays (FPGA), Advanced RISC Machines (ARM), Programmable Logic Devices (PLD), any circuit or processor capable of executing one or more functions, or the like.
The memory stores a computer program which, when executed by the processor, can determine the risk level of a point on the blade by using the Af dynamic stress reserve coefficient η obtained by the above method, and further limit the blade tip vibration according to the Af dynamic stress reserve coefficient η.
Further, the program can be obtained by using u obtained by the above method when being executed by a processorExtreme limit、uAlarm deviceA tip amplitude limit is determined.
In conclusion, the static strength and modal analysis is carried out based on finite element simulation, the most dangerous point is judged through the AF dynamic stress reserve coefficient by combining a blade grade GoodMan curve, and the blade tip amplitude limiting value is further calculated and obtained on the basis, and can be used for blade tip amplitude safety monitoring of an aeroengine test BTT.
Although the present invention has been disclosed in terms of the preferred embodiment, it is not intended to limit the invention, and variations and modifications may be made by one skilled in the art without departing from the spirit and scope of the invention. Therefore, any modification, equivalent change and modification of the above embodiments according to the technical essence of the present invention are within the protection scope defined by the claims of the present invention, unless the technical essence of the present invention departs from the content of the present invention.
Claims (9)
1. A method for determining the vibration limit of the blade tip of a rotor blade of an aeroengine is characterized in that,
multiplying a GoodMan curve of a blade material by a correction coefficient obtained by a blade vibration fatigue test to determine the GoodMan curve of the blade, and setting a safety coefficient for the GoodMan curve;
carrying out static strength analysis and modal analysis on the blade to obtain static strength analysis results and modal analysis results at different rotating speeds;
obtaining allowable vibration stress of each point on the blade at different rotating speeds by combining the GoodMan curve of the blade and the static stress obtained by the static strength analysis result;
the AF dynamic stress reserve coefficient eta is adopted to evaluate the danger degree of each point of the blade,
wherein σAfRepresenting the modal stress of the corresponding point of the blade in unit Af; sigmaAllowable useRepresenting allowable vibration stress of the corresponding point; sigmaModalityRepresenting the modal stress of the corresponding point, A representing the maximum displacement of the blade body in the corresponding mode, f representing the vibration frequency of the blade in the corresponding mode, and sigmaModalityA, f is determined from the modal analysis results; calculating the Af dynamic stress reserve coefficient eta of all the points of the blade,
the smaller the value of η, the more dangerous the position of this node on the blade is represented,
and limiting the blade tip vibration according to the AF dynamic stress reserve coefficient eta.
2. The method of claim 1,
the most dangerous point has the smallest Af dynamic stress reserve coefficient marked as etamin；
According to the modal analysis result, acquiring the circumferential displacement of the blade tip position corresponding to the BTT sensor position: u shapeCircumferential direction，
Determining a limit value of the amplitude of the blade tip, wherein the limit value comprises an alarm value and a limit value, and the limit value is marked as uExtreme limitThe alarm value is marked as uAlarm device，
uAlarm device＝uExtreme limitAlarm coefficient
The alarm coefficient is less than 1.
3. The method of claim 1, wherein the safety factor is 30% to 50%.
4. The method of claim 2, wherein the alarm coefficient is 0.75.
5. The method according to claim 1, wherein the correction factor is related to the size of the blade, the forming process and/or the surface treatment.
6. The method of claim 1, wherein the blade static strength analysis and the modal analysis are performed using a finite element simulation method.
7. The method of claim 6, wherein the material parameters of the computational model of the finite element simulation method are set in relation to temperature.
8. An apparatus for determining the limit of blade tip vibration of a rotor blade of an aeroengine, comprising a controller including a memory and a processor, said memory storing a computer program which, when executed by the processor, is capable of determining the risk level of a point on the blade using the Af dynamic stress reserve η obtained by the method of claim 1, and limiting the blade tip vibration in dependence on said Af dynamic stress reserve η.
9. An apparatus for determining vibration limits of the tips of aeroengine rotor blades, comprising a controller including a memory and a processor, said memory storing a computer program that when executed by the processor is able to use u obtained by the method of claim 2Extreme limit、uAlarm deviceA tip amplitude limit is determined.
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