CN114357911A - Turbine blade life determining method and device, electronic device and storage medium - Google Patents
Turbine blade life determining method and device, electronic device and storage medium Download PDFInfo
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Abstract
The application provides a method and a device for determining the service life of a turbine blade, electronic equipment and a storage medium, wherein the method comprises the following steps: acquiring the inlet flow of a compressor, the outlet pressure of the compressor, the outlet temperature of the compressor and the inlet temperature of a turbine of a gas turbine unit in work in different working periods; calculating temperature fields corresponding to turbine blades in the gas turbine unit in different working time periods according to the inlet flow of the gas compressor, the outlet pressure of the gas compressor, the outlet temperature of the gas compressor and the inlet temperature of the turbine; determining a stress tensor matrix corresponding to the turbine blade aiming at an elastic matrix of the turbine blade, a temperature field corresponding to each working time of the turbine blade and a blade rotating speed corresponding to the working time of the turbine blade in the historical working process; and determining the life of the turbine blade according to all the stress tensor matrixes and the stress life formula. By means of the method and the device, the calculation amount can be reduced, and the time for determining the service life of the turbine blade is saved.
Description
Technical Field
The present disclosure relates to the field of turbine blade technologies, and in particular, to a method and an apparatus for determining a lifetime of a turbine blade, an electronic device, and a storage medium.
Background
With the development of the industry, gas turbines are applied to various fields, but during the start and stop of the gas turbine, the load on the turbine blades in the gas turbine can shorten the service life of the turbine blades and reduce the reliability of the use of the blades. The safety period of the blade can be determined only if the thermomechanical fatigue life of the blade is accurately predicted, and the use reliability of the blade is guaranteed.
In the prior art, a numerical simulation calculation method is adopted for determining the service life of the turbine blade, and the three parts of a combustion engine, namely a compressor, a combustor and a turbine, need to be simulated respectively to obtain detailed flow and heat transfer information of the three parts, and then the information is converted into data required by a blade transient temperature field and blade service life simulation calculation through a large amount of calculation. Obviously, this method is very computationally intensive and takes a lot of time.
Disclosure of Invention
In view of the above, an object of the present invention is to provide a method, an apparatus, an electronic device, and a storage medium for determining the life of a turbine blade, which can reduce the amount of calculation and save the time for determining the life of the turbine blade.
In a first aspect, an embodiment of the present application provides a method for determining a lifetime of a turbine blade, the method including:
acquiring the inlet flow of a compressor, the outlet pressure of the compressor, the outlet temperature of the compressor and the inlet temperature of a turbine of a gas turbine unit in work in different working periods;
calculating temperature fields corresponding to turbine blades in the gas turbine unit in different working time periods according to the inlet flow of the gas compressor, the outlet pressure of the gas compressor, the outlet temperature of the gas compressor and the inlet temperature of the turbine;
determining a stress tensor matrix corresponding to the turbine blade aiming at an elastic matrix of the turbine blade, a temperature field corresponding to each working time of the turbine blade and a blade rotating speed corresponding to the working time of the turbine blade in the historical working process;
and determining the life of the turbine blade according to all the stress tensor matrixes and the stress life formula.
In one possible embodiment, obtaining the compressor inlet flow, the compressor outlet pressure, the compressor outlet temperature and the turbine inlet temperature of the gas turbine set in operation at different operation periods comprises:
acquiring inlet flow of a compressor, outlet pressure of the compressor, outlet temperature of the compressor and inlet temperature of a turbine of a gas turbine set in operation in different working periods according to a preset initial time interval;
calculating heat exchange boundary values corresponding to the turbine blades in different working time periods according to the inlet flow of the compressor, the outlet pressure of the compressor, the outlet temperature of the compressor and the inlet temperature of the turbine; the heat exchange boundary values include heat exchange coefficient and fluid temperature;
judging whether the absolute value of the difference value of the heat exchange boundary values of two temporally adjacent working durations meets a preset threshold value or not;
if the absolute value does not meet the preset threshold value, inserting an acquisition point between the end time points corresponding to the two working durations respectively; judging whether the absolute value of the difference value of the heat exchange boundary values of two temporally adjacent working durations in the current working process meets a preset threshold value or not again according to a preset initial time interval and all the acquisition points;
and if the absolute value meets the preset threshold value, taking the compressor inlet flow, the compressor outlet pressure, the compressor outlet temperature and the turbine inlet temperature of the gas turbine unit obtained in the current working process in different working periods as final obtaining results.
In one possible embodiment, calculating temperature fields corresponding to different working periods of turbine blades in a gas turbine unit according to a compressor inlet flow, a compressor outlet pressure, a compressor outlet temperature and a turbine inlet temperature comprises:
meshing the three-dimensional model of the turbine blade according to the shape characteristics and the heat transfer characteristics of the turbine blade; the heat transfer characteristics comprise heat exchange coefficient and heat flow density;
calculating the temperature of the position of each grid of the turbine blade in different working durations according to the heat exchange boundary value of each working duration and the position of each grid;
and determining the temperature fields corresponding to the turbine blades in different working periods according to the temperature of the position of each grid of the turbine blades in different working periods.
In one possible embodiment, determining a stress tensor matrix for a turbine blade for an elasticity matrix of the turbine blade, a temperature field for the turbine blade at each operating time period, and a blade speed for the turbine blade during historical operating periods corresponding to the operating time period includes:
applying a blade rotation speed and temperature field corresponding to the working time of the turbine blade in the current working process in the historical working process to the turbine blade;
and determining a stress tensor matrix corresponding to the position of each grid in different working periods in the current working process of the turbine blade according to the elastic matrix of the turbine blade and the temperature fields in different working periods based on the yield criterion of the turbine blade.
In one possible embodiment, determining the life of the turbine blade from all of the stress tensor matrices and the stress life equations includes:
according to all the stress tensor matrixes, calculating the difference value between the maximum stress tensor value and the minimum stress tensor value of each node position in each grid of the turbine blade in the current working process to obtain the stress tensor amplitude of each node position;
calculating the low cycle fatigue life of the position of each node by adopting a stress life formula according to the stress tensor amplitude;
the minimum low cycle fatigue life is determined as the life of the turbine blade.
In a second aspect, embodiments of the present application further provide a life determining apparatus for a turbine blade, the apparatus including:
the acquiring module is used for acquiring the inlet flow of the compressor, the outlet pressure of the compressor, the outlet temperature of the compressor and the inlet temperature of the turbine of the gas turbine set in work in different working periods;
the calculation module is used for calculating temperature fields corresponding to the turbine blades in the gas turbine unit in different working time periods according to the inlet flow of the gas compressor, the outlet pressure of the gas compressor, the outlet temperature of the gas compressor and the inlet temperature of the turbine;
a determination module: the stress tensor matrix corresponding to the turbine blade is determined according to the elastic matrix of the turbine blade, the temperature field corresponding to each working time length of the turbine blade and the blade rotating speed corresponding to the working time length of the turbine blade in the historical working process;
and the determining module is also used for determining the service life of the turbine blade according to all the stress tensor matrixes and the stress service life formula.
In a possible implementation manner, the obtaining module is specifically configured to obtain, according to a preset initial time interval, compressor inlet flow, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature of a gas turbine unit in operation at different operating durations; calculating heat exchange boundary values corresponding to the turbine blades in different working time periods according to the inlet flow of the compressor, the outlet pressure of the compressor, the outlet temperature of the compressor and the inlet temperature of the turbine; the heat exchange boundary values include heat exchange coefficient and fluid temperature; judging whether the absolute value of the difference value of the heat exchange boundary values of two temporally adjacent working durations meets a preset threshold value or not; if the absolute value does not meet the preset threshold value, inserting an acquisition point between the end time points corresponding to the two working durations respectively; judging whether the absolute value of the difference value of the heat exchange boundary values of two temporally adjacent working durations in the current working process meets a preset threshold value or not again according to a preset initial time interval and all the acquisition points; and if the absolute value meets the preset threshold value, taking the compressor inlet flow, the compressor outlet pressure, the compressor outlet temperature and the turbine inlet temperature of the gas turbine unit obtained in the current working process in different working periods as final obtaining results.
In one possible embodiment, the calculation module is specifically configured to mesh the three-dimensional model of the turbine blade according to the shape characteristics and the heat transfer characteristics of the turbine blade; the heat transfer characteristics comprise heat exchange coefficient and heat flow density; calculating the temperature of the position of each grid of the turbine blade in different working durations according to the heat exchange boundary value of each working duration and the position of each grid; and determining the temperature fields corresponding to the turbine blades in different working periods according to the temperature of the position of each grid of the turbine blades in different working periods.
In one possible embodiment, the determination module is specifically configured to apply a blade rotational speed and temperature field of the turbine blade during historical operation, which corresponds to the operating time of the turbine blade during the current operation, to the turbine blade; and determining a stress tensor matrix corresponding to the position of each grid in different working periods in the current working process of the turbine blade according to the elastic matrix of the turbine blade and the temperature fields in different working periods based on the yield criterion of the turbine blade.
In a possible implementation manner, the determining module is further configured to calculate, according to all the stress tensor matrices, a difference value between a maximum stress tensor value and a minimum stress tensor value of a position where each node in each grid is located in the current working process of the turbine blade, so as to obtain a stress tensor amplitude of the position where each node is located; calculating the low cycle fatigue life of the position of each node by adopting a stress life formula according to the stress tensor amplitude; the minimum low cycle fatigue life is determined as the life of the turbine blade.
In a third aspect, an electronic device includes: a processor, a memory and a bus, the memory storing machine readable instructions executable by the processor, the processor and the memory communicating over the bus when the electronic device is running, the machine readable instructions when executed by the processor performing the steps of the method of determining the life of a turbine blade as described above in the first aspect.
In a fourth aspect, a computer readable storage medium has stored thereon a computer program which, when executed by a processor, performs the steps of the method of determining the life of a turbine blade as described above in the first aspect.
The application provides a method and a device for determining the service life of a turbine blade, electronic equipment and a storage medium, wherein the method comprises the following steps: acquiring the inlet flow of a compressor, the outlet pressure of the compressor, the outlet temperature of the compressor and the inlet temperature of a turbine of a gas turbine unit in work in different working periods; calculating temperature fields corresponding to turbine blades in the gas turbine unit in different working time periods according to the inlet flow of the gas compressor, the outlet pressure of the gas compressor, the outlet temperature of the gas compressor and the inlet temperature of the turbine; determining a stress tensor matrix corresponding to the turbine blade aiming at an elastic matrix of the turbine blade, a temperature field corresponding to each working time of the turbine blade and a blade rotating speed corresponding to the working time of the turbine blade in the historical working process; and determining the life of the turbine blade according to all the stress tensor matrixes and the stress life formula. According to the method and the device, the inlet flow of the gas compressor, the outlet pressure of the gas compressor, the outlet temperature of the gas compressor and the inlet temperature of the turbine of the gas turbine unit in different working hours are obtained, the temperature fields corresponding to the different working hours are calculated, then the stress tensor matrix corresponding to the turbine blades in the different working hours is determined, finally, the service life of the turbine blades is determined according to the stress life formula, the calculated amount is reduced, and the time for determining the service life of the turbine blades is saved.
In order to make the aforementioned objects, features and advantages of the present application more comprehensible, preferred embodiments accompanied with figures are described in detail below.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present application and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained from the drawings without inventive effort.
FIG. 1 illustrates a flow chart of a method for determining a life of a turbine blade provided by an embodiment of the present application;
FIG. 2 illustrates a flow chart of another method of determining a life of a turbine blade provided by an embodiment of the present application;
FIG. 3 is a schematic structural diagram illustrating a life determining apparatus for a turbine blade according to an embodiment of the present disclosure;
fig. 4 shows a schematic structural diagram of an electronic device provided in an embodiment of the present application.
Detailed Description
In order to make the purpose, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it should be understood that the drawings in the present application are for illustrative and descriptive purposes only and are not used to limit the scope of protection of the present application. Additionally, it should be understood that the schematic drawings are not necessarily drawn to scale. The flowcharts used in this application illustrate operations implemented according to some embodiments of the present application. It should be understood that the operations of the flow diagrams may be performed out of order, and steps without logical context may be performed in reverse order or simultaneously. One skilled in the art, under the guidance of this application, may add one or more other operations to, or remove one or more operations from, the flowchart.
In addition, the described embodiments are only a part of the embodiments of the present application, and not all of the embodiments. The components of the embodiments of the present application, generally described and illustrated in the figures herein, can be arranged and designed in a wide variety of different configurations. Thus, the following detailed description of the embodiments of the present application, presented in the accompanying drawings, is not intended to limit the scope of the claimed application, but is merely representative of selected embodiments of the application. All other embodiments, which can be derived by a person skilled in the art from the embodiments of the present application without making any creative effort, shall fall within the protection scope of the present application.
To enable one skilled in the art to use the present disclosure, the following embodiments are presented in conjunction with a particular application scenario, "turbine blade technology area". It will be apparent to those skilled in the art that the general principles defined herein may be applied to other embodiments and applications without departing from the spirit and scope of the application. Although the present application is described primarily in the context of "turbine blade technology," it should be understood that this is merely one exemplary embodiment.
The following is a detailed description of a method for determining the life of a turbine blade provided in an embodiment of the present application.
Referring to fig. 1, fig. 1 is a flowchart illustrating a method for determining a lifetime of a turbine blade according to an embodiment of the present disclosure.
The following describes exemplary steps in an embodiment of the present application:
s101, obtaining inlet flow of a compressor, outlet pressure of the compressor, outlet temperature of the compressor and inlet temperature of a turbine of a gas turbine set in work in different working periods.
Further, according to a preset initial time interval, obtaining the inlet flow of the compressor, the outlet pressure of the compressor, the outlet temperature of the compressor and the inlet temperature of the turbine of the gas turbine set in operation in different working periods.
For example, if the preset initial time interval is 1s, the compressor inlet flow, the compressor outlet pressure, the compressor outlet temperature and the turbine inlet temperature of the turbine blade in the working process with the working time duration of 1s, 2s, 3s, … …, Ns are obtained.
And further, calculating heat exchange boundary values corresponding to the turbine blades in different working time periods according to the inlet flow of the compressor, the outlet pressure of the compressor, the outlet temperature of the compressor and the inlet temperature of the turbine.
The heat exchange boundary value comprises a heat exchange coefficient and a fluid temperature, the heat exchange coefficient comprises an inner side heat exchange coefficient and an outer side heat exchange coefficient, and the fluid temperature comprises an inner side fluid temperature and an outer side fluid temperature.
For example, the inlet flow rate of the compressor, the outlet pressure of the compressor, the outlet temperature of the compressor, and the inlet temperature of the turbine are acquired for 1s, 2s, and 3s, and then the heat exchange boundary values for 1s, 2s, and 3s are calculated respectively according to the inlet flow rate of the compressor, the outlet pressure of the compressor, the outlet temperature of the compressor, and the inlet temperature of the turbine for 1s, 2s, and 3 s.
Here, the outside heat transfer coefficient h is calculated according to the following formulagAnd outside fluid temperature Tg,local：
Tg,local＝f2(T2,T3,P)×f1(x,y)，
kg＝f4(Tg,local)＝(0.086×Tg,local-0.885)*0.001；
Wherein, C0M is the compressor inlet flow, mu, is a known constantgIs the local gas dynamic viscosity, kgIs the local heat conductivity of the gas, f1、f2、f3、f4Respectively as a function of the gas side, (x, y) the position coordinates of the outlet cross section of the burner, p is the compressor outlet pressure, T2For the compressor outlet temperature, T3Is the turbine inlet temperature.
Here, the inside heat transfer coefficient h is calculated according to the following formulacAnd outside fluid temperature Tc,local：
Tc,local＝f5(T2,T3,p)×f6(x,y,z)，
kc＝f8(Tc,local)＝(0.0507×Tc,local+14.3931)*0.001；
Wherein, C1M is the compressor inlet flow, mu, is a known constantcIs the local cold gas dynamic viscosity, kcIs the local cold air thermal conductivity coefficient, f5、f6、f7、f8Respectively corresponding gas side function, (x, y, z) is the space coordinate of the turbine blade, p is the outlet pressure of the compressor, T2For the compressor outlet temperature, T3Is the turbine inlet temperature.
Further, judging whether the absolute value of the difference value of the heat exchange boundary values of two adjacent working time lengths in terms of time meets a preset threshold value or not; if the absolute value does not meet the preset threshold value, inserting an acquisition point between the end time points corresponding to the two working durations respectively; judging whether the absolute value of the difference value of the heat exchange boundary values of two temporally adjacent working durations in the current working process meets a preset threshold value or not again according to a preset initial time interval and all the acquisition points; and if the absolute value meets the preset threshold value, taking the compressor inlet flow, the compressor outlet pressure, the compressor outlet temperature and the turbine inlet temperature of the gas turbine unit obtained in the current working process in different working periods as final obtaining results.
If the absolute value meets the preset threshold value, heat exchange boundary values corresponding to the turbine blades in different working time periods are calculated according to the inlet flow of the compressor, the outlet pressure of the compressor, the outlet temperature of the compressor and the inlet temperature of the turbine in the current working process to serve as final calculation results.
The difference value of the heat exchange boundary values comprises a difference value of inner side heat exchange coefficients, a difference value of outer side heat exchange coefficients, a difference value of inner side fluid temperatures and a difference value of outer side fluid temperatures, and the absolute value of any difference value which does not meet the preset condition is that the absolute value does not meet the preset threshold value.
For example, the preset initial time interval is 1s, and the heat exchange boundary values of the working durations 1s, 2s and 3s are obtained through calculation, so that it is determined whether the absolute value of the difference between the heat exchange boundary values of two temporally adjacent working durations (the working duration is 1s, the working duration is 2s and the working duration is 3s) satisfies the preset threshold.
If the difference between the heat exchange boundary values with the working time length of 1s and the working time length of 2s does not satisfy the preset threshold value, and the difference between the heat exchange boundary values with the working time length of 2s and the working time length of 3s satisfies the preset threshold value, an acquisition point is inserted between the working time length of 1s and the working time length of 2s, the heat exchange boundary values with the working time length of 1s, 1.5s, 2s and 3s in the current working process are calculated according to the preset initial time interval and all the acquisition points, whether the absolute value of the difference between the heat exchange boundary values of two temporally adjacent working time lengths (the working time length of 1s, the working time length of 1.5s, the working time length of 2s and the working time length of 3s) satisfies the preset threshold value is judged again, if the judgment result is that only the absolute value of the difference between the working time length of 2s and the heat exchange boundary value of 3s does not satisfy the preset threshold value, and inserting a collection point between the working time of 2s and the working time of 3s, calculating the heat exchange boundary values of 1s, 1.5s, 2s, 2.5s and 3s of the working time in the current working process, and judging again.
And if the difference values of the heat exchange boundary values with the working time of 1s, the working time of 2s and the working time of 3s all meet the preset threshold value, taking the compressor inlet flow, the compressor outlet pressure, the compressor outlet temperature and the turbine inlet temperature of the gas turbine unit obtained in the current working process at different working times as final obtained results.
S102, calculating temperature fields corresponding to the turbine blades in the gas turbine unit in different working time periods according to the inlet flow of the gas compressor, the outlet pressure of the gas compressor, the outlet temperature of the gas compressor and the inlet temperature of the turbine.
Further, according to the shape characteristics and the heat transfer characteristics of the turbine blade, grid division is carried out on the three-dimensional model of the turbine blade; the heat transfer characteristics include heat transfer coefficient and heat flow density.
Wherein, the shape characteristic refers to the curvature of the surface of the turbine blade, and the heat transfer characteristic comprises a heat exchange coefficient and a heat flux density.
The cooling structure of the inner surface of the turbine blade is a cooling structure with small sizes such as an air film hole, a turbulent flow column, a flow surrounding rib, a tail edge cleft and the like, the mesh size is 0.2D, the D is a cooling characteristic size, the mesh size is 0.03S and the S is a turbine blade chord length, the mesh size is 0.01L and the L is a characteristic size of the surface of the outer surface with large curvature such as the front edge, the tail edge, the blade top and the like of the turbine blade.
Further, according to the heat exchange boundary value of each working duration and the position of each grid, calculating the temperature of the position of each grid of the turbine blade in different working durations;
here, the heat exchange boundary values corresponding to the turbine blade at different operating times as the final calculation result in step S101 are applied to the positions of the meshes located on the geometric surface of the turbine blade, and the following equation is solved to obtain the temperature of the position of each mesh of the turbine blade at different operating times.
Heat conduction calculation equation:
wherein T is the temperature of the grid position, Lambda m is the heat conductivity coefficient of the turbine blade material, rho is the density of the turbine blade material, c is the specific heat capacity of the turbine blade material, and x, y and z are the coordinates of the grid position.
Further, according to the temperature of the position of each grid of the turbine blade in different working periods, the temperature fields corresponding to the turbine blade in different working periods are determined.
S103, determining a stress tensor matrix corresponding to the turbine blade according to the elastic matrix of the turbine blade, the temperature field corresponding to each working time of the turbine blade and the blade rotating speed corresponding to the working time of the turbine blade in the historical working process.
Further, applying a blade rotation speed and temperature field of the turbine blade in the historical working process, which corresponds to the working time of the turbine blade in the current working process, to the turbine blade;
for example, the blade speed and temperature field corresponding to the current operating time of the turbine blade in the historical operating process is applied to the operating time of the turbine blade in the current operating process, for example, if the current operating time of the turbine blade is 1s, the blade speed and temperature field corresponding to the operating time of the turbine blade in the historical operating process is applied to the turbine blade when the current operating time of the turbine blade is 1 s.
Further, based on the yield criterion of the turbine blade, according to the elastic matrix of the turbine blade and the temperature fields of different working durations, determining a stress tensor matrix corresponding to the position of each grid in the current working process of the turbine blade in different working durations.
Wherein, the yield criterion is the yield criterion corresponding to the material of the turbine blade, if the turbine blade is the same-polarity material, the Von Mises Stress yield criterion is adopted, and if the turbine blade is the anisotropic material, the Hill 48 yield criterion is adopted.
Here, the yield criterion is based on the turbine bladeAcquiring turbine blade stress fields corresponding to different working durations of the turbine blade in the current working process according to the elastic matrix of the turbine blade and the temperature fields of the turbine blade in the different working durations, and then extracting stress tensor matrices corresponding to different working durations of each grid in the current working process of the turbine blade
Wherein the elastic matrix is an elastic matrix corresponding to the material of the turbine blade, σijThe stress tensor for each node in the ij direction.
And S104, determining the service life of the turbine blade according to all the stress tensor matrixes and the stress service life formula.
Further, according to all the stress tensor matrixes, calculating the difference value between the maximum stress tensor value and the minimum stress tensor value of each node in each grid of the turbine blade in the current working process, and obtaining the stress tensor amplitude of each node.
And further, calculating the low-cycle fatigue life of the position of each node by adopting a stress life formula according to the stress tensor amplitude.
Here, the equivalent stress magnitude at the position of each node is first calculated by the following formula:
wherein the content of the first and second substances,
for equivalent stress amplitude, Δ σijThe stress magnitude in the ij direction is taken as the position of each node.
Then, calculating the low cycle fatigue life of each node position through a stress life formula:
wherein N isfFor low cycle fatigue life, BLIs the fatigue strength coefficient, nLIs a fatigue strength index.
Further, a minimum low cycle fatigue life is determined as the life of the turbine blade.
The application provides a method for determining the life of a turbine blade, comprising: acquiring the inlet flow of a compressor, the outlet pressure of the compressor, the outlet temperature of the compressor and the inlet temperature of a turbine of a gas turbine unit in work in different working periods; calculating temperature fields corresponding to turbine blades in the gas turbine unit in different working time periods according to the inlet flow of the gas compressor, the outlet pressure of the gas compressor, the outlet temperature of the gas compressor and the inlet temperature of the turbine; determining a stress tensor matrix corresponding to the turbine blade aiming at an elastic matrix of the turbine blade, a temperature field corresponding to each working time of the turbine blade and a blade rotating speed corresponding to the working time of the turbine blade in the historical working process; and determining the life of the turbine blade according to all the stress tensor matrixes and the stress life formula. According to the method and the device, the inlet flow of the gas compressor, the outlet pressure of the gas compressor, the outlet temperature of the gas compressor and the inlet temperature of the turbine of the gas turbine unit in different working hours are obtained, the temperature fields corresponding to the different working hours are calculated, then the stress tensor matrix corresponding to the turbine blades in the different working hours is determined, finally, the service life of the turbine blades is determined according to the stress life formula, the calculated amount is reduced, and the time for determining the service life of the turbine blades is saved.
Referring to fig. 2, fig. 2 is a flowchart of another method for determining a lifetime of a turbine blade according to an embodiment of the present disclosure, where the descriptions of S201 to S205 may refer to the description of S101, and the same technical effect may be achieved, and repeated contents are not repeated, and the method includes:
s201, acquiring inlet flow of a compressor, outlet pressure of the compressor, outlet temperature of the compressor and inlet temperature of a turbine of a gas turbine unit in operation in different working periods according to a preset initial time interval.
The preset initial time interval is not limited specifically, and may be determined according to actual conditions.
S202, calculating heat exchange boundary values corresponding to the turbine blades in different working time periods according to the inlet flow of the compressor, the outlet pressure of the compressor, the outlet temperature of the compressor and the inlet temperature of the turbine.
S203, judging whether the absolute value of the difference value of the heat exchange boundary values of two adjacent working durations in time meets a preset threshold value.
Here, the preset threshold value means that the absolute value of the difference between the heat exchange boundary values of the two adjacent operating time periods exceeds twenty percent of the heat exchange boundary value of the previous operating time period in the two adjacent operating time periods.
S204, if the absolute value does not meet the preset threshold, inserting an acquisition point between the end time points corresponding to the two working durations respectively; and judging whether the absolute value of the difference value of the heat exchange boundary values of two temporally adjacent working durations in the current working process meets the preset threshold value again according to the preset initial time interval and all the acquisition points.
S205, if the absolute value meets the preset threshold, the compressor inlet flow, the compressor outlet pressure, the compressor outlet temperature and the turbine inlet temperature of the gas turbine unit obtained in the current working process in different working periods are used as final obtaining results.
The method provided by the embodiment of the application acquires the inlet flow of the gas compressor, the outlet pressure of the gas compressor, the outlet temperature of the gas compressor and the inlet temperature of the turbine in different working periods by setting an initial time interval, then judges whether the absolute value of the difference value of the heat exchange boundary values of two temporally adjacent working periods meets a preset threshold value or not and adds a set acquisition point, and finally determines the final acquisition working period to acquire the inlet flow of the gas compressor, the outlet pressure of the gas compressor, the outlet temperature of the gas compressor and the inlet temperature of the turbine in different working periods of the turbine blade. Compared with the prior art for acquiring all the inlet flow of the compressor, the outlet pressure of the compressor, the outlet temperature of the compressor and the inlet temperature of the turbine in the working process of the turbine blade, the calculation amount is reduced, and the time for determining the service life of the turbine blade is saved.
Referring to fig. 3, fig. 3 is a schematic structural diagram of a life determining device for a turbine blade according to the present application. The life determining apparatus of a turbine blade as shown in fig. 3 includes:
the acquiring module 301 is used for acquiring the inlet flow rate of the compressor, the outlet pressure of the compressor, the outlet temperature of the compressor and the inlet temperature of the turbine of the gas turbine set in operation in different working periods;
the calculating module 302 is used for calculating temperature fields corresponding to turbine blades in the gas turbine unit in different working time periods according to the inlet flow of the gas compressor, the outlet pressure of the gas compressor, the outlet temperature of the gas compressor and the inlet temperature of the turbine;
the determination module 303: the stress tensor matrix corresponding to the turbine blade is determined according to the elastic matrix of the turbine blade, the temperature field corresponding to each working time length of the turbine blade and the blade rotating speed corresponding to the working time length of the turbine blade in the historical working process;
the determining module 303 is further configured to determine the life of the turbine blade according to all the stress tensor matrices and the stress life formula.
In a possible embodiment, the obtaining module 301 is specifically configured to obtain, according to a preset initial time interval, compressor inlet flow, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature of a gas turbine unit in operation at different operating durations; calculating heat exchange boundary values corresponding to the turbine blades in different working time periods according to the inlet flow of the compressor, the outlet pressure of the compressor, the outlet temperature of the compressor and the inlet temperature of the turbine; the heat exchange boundary values include heat exchange coefficient and fluid temperature; judging whether the absolute value of the difference value of the heat exchange boundary values of two temporally adjacent working durations meets a preset threshold value or not; if the absolute value does not meet the preset threshold value, inserting an acquisition point between the end time points corresponding to the two working durations respectively; judging whether the absolute value of the difference value of the heat exchange boundary values of two temporally adjacent working durations in the current working process meets a preset threshold value or not again according to a preset initial time interval and all the acquisition points; and if the absolute value meets the preset threshold value, taking the compressor inlet flow, the compressor outlet pressure, the compressor outlet temperature and the turbine inlet temperature of the gas turbine unit obtained in the current working process in different working periods as final obtaining results.
In one possible embodiment, the calculation module 302 is specifically configured to mesh the three-dimensional model of the turbine blade according to the shape characteristics and the heat transfer characteristics of the turbine blade; the heat transfer characteristics comprise heat exchange coefficient and heat flow density; calculating the temperature of the position of each grid of the turbine blade in different working durations according to the heat exchange boundary value of each working duration and the position of each grid; and determining the temperature fields corresponding to the turbine blades in different working periods according to the temperature of the position of each grid of the turbine blades in different working periods.
In one possible embodiment, the determination module 303 is specifically configured to apply to the turbine blade a blade rotational speed and temperature field of the turbine blade during historical operation corresponding to an operating time period during the current operation; and determining a stress tensor matrix corresponding to the position of each grid in different working periods in the current working process of the turbine blade according to the elastic matrix of the turbine blade and the temperature fields in different working periods based on the yield criterion of the turbine blade.
In a possible embodiment, the determining module 303 is further configured to calculate, according to all the stress tensor matrices, a difference between a maximum stress tensor value and a minimum stress tensor value of a position where each node in each grid is located in the current working process of the turbine blade, so as to obtain a stress tensor amplitude of the position where each node is located; calculating the low cycle fatigue life of the position of each node by adopting a stress life formula according to the stress tensor amplitude; the minimum low cycle fatigue life is determined as the life of the turbine blade.
The present application provides a life determining apparatus for a turbine blade, the apparatus including: the acquiring module 301 is used for acquiring the inlet flow rate of the compressor, the outlet pressure of the compressor, the outlet temperature of the compressor and the inlet temperature of the turbine of the gas turbine set in operation in different working periods; the calculating module 302 is used for calculating temperature fields corresponding to turbine blades in the gas turbine unit in different working time periods according to the inlet flow of the gas compressor, the outlet pressure of the gas compressor, the outlet temperature of the gas compressor and the inlet temperature of the turbine; the determination module 303: determining a stress tensor matrix corresponding to the turbine blade aiming at an elastic matrix of the turbine blade, a temperature field corresponding to each working time of the turbine blade and a blade rotating speed corresponding to the working time of the turbine blade in the historical working process; the determining module 303 is further configured to determine the life of the turbine blade according to all the stress tensor matrices and the stress life formula. According to the method and the device, the inlet flow of the gas compressor, the outlet pressure of the gas compressor, the outlet temperature of the gas compressor and the inlet temperature of the turbine of the gas turbine unit in different working hours are obtained, the temperature fields corresponding to the different working hours are calculated, then the stress tensor matrix corresponding to the turbine blades in the different working hours is determined, finally, the service life of the turbine blades is determined according to the stress life formula, the calculated amount is reduced, and the time for determining the service life of the turbine blades is saved.
Referring to fig. 4, fig. 4 is a schematic structural diagram of an electronic device according to an embodiment of the present disclosure. As shown in fig. 4, the electronic device 400 includes a processor 401, a memory 402, and a bus.
The memory 402 stores machine-readable instructions executable by the processor 401, when the electronic device 400 runs, the processor 401 and the memory 402 communicate through a bus, and when the machine-readable instructions are executed by the processor 401, the steps of the method for determining the life of the turbine blade in the method embodiment shown in fig. 1 and fig. 2 may be executed.
An embodiment of the present application further provides a computer-readable storage medium, where a computer program is stored on the computer-readable storage medium, and when the computer program is executed by a processor, the steps of the method for determining the life of a turbine blade in the method embodiments shown in fig. 1 and fig. 2 may be executed.
It is clear to those skilled in the art that, for convenience and brevity of description, the specific working processes of the above-described systems, apparatuses and units may refer to the corresponding processes in the foregoing method embodiments, and are not described herein again.
In the several embodiments provided in the present application, it should be understood that the disclosed system, apparatus and method may be implemented in other ways. The above-described embodiments of the apparatus are merely illustrative, and for example, the division of the units is only one logical division, and there may be other divisions when actually implemented, and for example, a plurality of units or components may be combined or integrated into another system, or some features may be omitted, or not executed. In addition, the shown or discussed mutual coupling or direct coupling or communication connection may be an indirect coupling or communication connection of devices or units through some communication interfaces, and may be in an electrical, mechanical or other form.
The units described as separate parts may or may not be physically separate, and parts displayed as units may or may not be physical units, may be located in one place, or may be distributed on a plurality of network units. Some or all of the units can be selected according to actual needs to achieve the purpose of the solution of the embodiment.
In addition, functional units in the embodiments of the present application may be integrated into one processing unit, or each unit may exist alone physically, or two or more units are integrated into one unit.
The functions, if implemented in the form of software functional units and sold or used as a stand-alone product, may be stored in a non-volatile computer-readable storage medium executable by a processor. Based on such understanding, the technical solution of the present application or portions thereof that substantially contribute to the prior art may be embodied in the form of a software product stored in a storage medium and including instructions for causing a computer device (which may be a personal computer, a server, or a network device) to execute all or part of the steps of the method according to the embodiments of the present application. And the aforementioned storage medium includes: various media capable of storing program codes, such as a usb disk, a removable hard disk, a Read-Only Memory (ROM), a Random Access Memory (RAM), a magnetic disk, or an optical disk.
Finally, it should be noted that: the above-mentioned embodiments are only specific embodiments of the present application, and are used for illustrating the technical solutions of the present application, but not limiting the same, and the scope of the present application is not limited thereto, and although the present application is described in detail with reference to the foregoing embodiments, those skilled in the art should understand that: any person skilled in the art can modify or easily conceive the technical solutions described in the foregoing embodiments or equivalent substitutes for some technical features within the technical scope disclosed in the present application; such modifications, changes or substitutions do not depart from the spirit and scope of the exemplary embodiments of the present application, and are intended to be covered by the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. A method of determining the life of a turbine blade, the method comprising:
acquiring the inlet flow of a compressor, the outlet pressure of the compressor, the outlet temperature of the compressor and the inlet temperature of a turbine of a gas turbine unit in work in different working periods;
calculating temperature fields corresponding to the turbine blades in the gas turbine unit in different working time periods according to the inlet flow of the gas compressor, the outlet pressure of the gas compressor, the outlet temperature of the gas compressor and the inlet temperature of the turbine;
determining a stress tensor matrix corresponding to the turbine blade aiming at the elastic matrix of the turbine blade, the temperature field corresponding to each working time length of the turbine blade and the blade rotating speed corresponding to the working time length of the turbine blade in the historical working process;
determining the life of the turbine blade according to all the stress tensor matrixes and the stress life formula.
2. The method of claim 1, wherein the obtaining compressor inlet flow, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature for different operating periods of the operating gas turbine assembly comprises:
acquiring the inlet flow of a compressor, the outlet pressure of the compressor, the outlet temperature of the compressor and the inlet temperature of a turbine of the gas turbine set in operation in different working periods according to a preset initial time interval;
calculating heat exchange boundary values corresponding to the turbine blades in different working time periods according to the compressor inlet flow, the compressor outlet pressure, the compressor outlet temperature and the turbine inlet temperature; the heat exchange boundary values include a heat exchange coefficient and a fluid temperature;
judging whether the absolute value of the difference value of the heat exchange boundary values of two temporally adjacent working durations meets a preset threshold value or not;
if the absolute value does not meet the preset threshold, inserting an acquisition point in the middle of the end time points corresponding to the two working durations respectively; judging whether the absolute value of the difference value of the heat exchange boundary values of two temporally adjacent working durations in the current working process meets a preset threshold value or not again according to a preset initial time interval and all the acquisition points;
and if the absolute value meets a preset threshold value, taking the compressor inlet flow, the compressor outlet pressure, the compressor outlet temperature and the turbine inlet temperature of the gas turbine unit obtained in the current working process in different working periods as final obtaining results.
3. The method of claim 2, wherein calculating temperature fields corresponding to different operating periods of turbine blades in the gas turbine assembly based on the compressor inlet flow, the compressor outlet pressure, the compressor outlet temperature, and the turbine inlet temperature comprises:
meshing the three-dimensional model of the turbine blade according to the shape characteristics and the heat transfer characteristics of the turbine blade; the heat transfer characteristics comprise heat exchange coefficient and heat flow density;
calculating the temperature of the position of each grid of the turbine blade in different working durations according to the heat exchange boundary value of each working duration and the position of each grid;
and determining the temperature fields corresponding to the turbine blades in different working periods according to the temperature of the position of each grid of the turbine blades in different working periods.
4. The method of claim 3, wherein determining the stress tensor matrix for the turbine blade for the elasticity matrix for the turbine blade, the temperature field for the turbine blade for each operating time period, and the blade speed for the turbine blade for the operating time period over historical operating processes comprises:
applying a blade speed and temperature field of the turbine blade during historical operation corresponding to an operating time of the turbine blade during a current operation to the turbine blade;
and determining a stress tensor matrix corresponding to the position of each grid in different working periods in the current working process of the turbine blade according to the elastic matrix of the turbine blade and the temperature fields in different working periods based on the yield criterion of the turbine blade.
5. The method of claim 4, wherein said determining the life of the turbine blade from all of the stress tensor matrices and stress life equations comprises:
calculating the difference value between the maximum stress tensor value and the minimum stress tensor value of each node in each grid of the turbine blade in the current working process according to all the stress tensor matrixes to obtain the stress tensor amplitude of each node;
calculating the low-cycle fatigue life of the position of each node by adopting a stress life formula according to the stress tensor amplitude;
determining a minimum low cycle fatigue life as the life of the turbine blade.
6. A turbine blade life determining apparatus, the apparatus comprising:
the acquiring module is used for acquiring the inlet flow of the compressor, the outlet pressure of the compressor, the outlet temperature of the compressor and the inlet temperature of the turbine of the gas turbine set in work in different working periods;
the calculation module is used for calculating temperature fields corresponding to the turbine blades in the gas turbine unit in different working time periods according to the inlet flow of the gas compressor, the outlet pressure of the gas compressor, the outlet temperature of the gas compressor and the inlet temperature of the turbine;
the determining module is used for determining a stress tensor matrix corresponding to the turbine blade aiming at the elastic matrix of the turbine blade, the temperature field corresponding to the turbine blade in each working period and the blade rotating speed corresponding to the working period in the historical working process of the turbine blade;
the determining module is further configured to determine the life of the turbine blade according to all the stress tensor matrices and the stress life formulas.
7. The turbine blade life determining apparatus of claim 6, wherein the obtaining module is specifically configured to:
acquiring the inlet flow of a compressor, the outlet pressure of the compressor, the outlet temperature of the compressor and the inlet temperature of a turbine of the gas turbine set in operation in different working periods according to a preset initial time interval;
calculating heat exchange boundary values corresponding to the turbine blades in different working time periods according to the compressor inlet flow, the compressor outlet pressure, the compressor outlet temperature and the turbine inlet temperature; the heat exchange boundary values include a heat exchange coefficient and a fluid temperature;
judging whether the absolute value of the difference value of the heat exchange boundary values of two temporally adjacent working durations meets a preset threshold value or not;
if the absolute value does not meet the preset threshold, inserting an acquisition point in the middle of the end time points corresponding to the two working durations respectively; judging whether the absolute value of the difference value of the heat exchange boundary values of two temporally adjacent working durations in the current working process meets a preset threshold value or not again according to a preset initial time interval and all the acquisition points;
and if the absolute value meets a preset threshold value, taking the compressor inlet flow, the compressor outlet pressure, the compressor outlet temperature and the turbine inlet temperature of the gas turbine unit obtained in the current working process in different working periods as final obtaining results.
8. The apparatus of claim 7, wherein the computing module is specifically configured to:
meshing the three-dimensional model of the turbine blade according to the shape characteristics and the heat transfer characteristics of the turbine blade; the heat transfer characteristics comprise heat exchange coefficient and heat flow density;
calculating the temperature of the position of each grid of the turbine blade in different working durations according to the heat exchange boundary value of each working duration and the position of each grid;
and determining the temperature fields corresponding to the turbine blades in different working periods according to the temperature of the position of each grid of the turbine blades in different working periods.
9. An electronic device, comprising: a processor, a memory and a bus, the memory storing machine readable instructions executable by the processor, the processor and the memory communicating over the bus when the electronic device is running, the processor executing the machine readable instructions to perform the steps of the method of determining the life of a turbine blade according to any one of claims 1 to 5.
10. A computer-readable storage medium, characterized in that a computer program is stored on the computer-readable storage medium, which computer program, when being executed by a processor, performs the steps of the method for determining the life of a turbine blade according to any one of claims 1 to 5.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115130234A (en) * | 2022-05-29 | 2022-09-30 | 中国船舶重工集团公司第七0三研究所 | Air-cooled turbine guide vane modeling method for pressure side exhaust |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115130234A (en) * | 2022-05-29 | 2022-09-30 | 中国船舶重工集团公司第七0三研究所 | Air-cooled turbine guide vane modeling method for pressure side exhaust |
| CN115130234B (en) * | 2022-05-29 | 2023-04-07 | 中国船舶重工集团公司第七0三研究所 | Air-cooled turbine guide vane modeling method for pressure side exhaust |
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