KR101930592B1 - Apparatus and method for calculating usage time of high temperature parts of gas turbine - Google Patents

Abstract

The present invention relates to an apparatus and method for calculating service life of a high temperature part of a gas turbine, comprising the steps of: calculating a first operating value based on fatigue failure in a first section of a transient state drive period of a high temperature part; Calculating a second operation value based on a creep failure in a second section which is a drive section, calculating a third operation value based on fatigue failure in the second section, And calculating the service life of the high temperature part based on the calculated service life of the gas turbine high temperature part and the service life of the high temperature part.

Description

BACKGROUND OF THE INVENTION 1. Field of the Invention [0001] The present invention relates to an apparatus and a method for calculating a service life of a gas turbine,

The present invention relates to an apparatus and a method for calculating the service life of a gas turbine high temperature part.

For combined-cycle power plants that generate electricity using gas turbines, most of the operating costs of operating the plant are used to replace high-temperature components in fuel and gas turbines. Particularly, expensive materials are used in manufacturing at high temperature, and parts such as blades and vanes requiring high technology are consuming a great deal of cost depending on the frequency of replacement. Systematic management of high temperature components is essential to minimize these costs.

Most domestic and overseas power generation companies operate their own management systems for high-temperature components. Most of them use only uniformly the same criteria as ES (Equivalent Starts), EOH (Equivalent Operating Hours) and EBH (Equivalent Baseload Hours) It is in use. For example, the power generation companies were provided with a table for judging the maintenance / replacement timing of the high temperature parts provided by the gas turbine manufacturer, as shown in FIG. 2, and performed maintenance of the high temperature parts. Referring to FIG. 2, EBH reference values or ES reference values that require maintenance or replacement of hot parts are set for each blade and each vane. The table of FIG. 2 reflects the usage life calculation concept used in the gas turbine manufacturer as shown in FIG.

However, the service life of high temperature components may vary depending on the operating conditions. As described above, the maintenance / replacement criteria of unilateral high temperature components provided by the manufacturer does not accurately reflect the service life of high temperature components.

The present invention has been made in view of the above problems, and it is an object of the present invention to provide a method and an apparatus for calculating service life of a gas turbine high-temperature part having high reliability.

According to an aspect of the present invention, there is provided a method for calculating service life of a high temperature component of a gas turbine, comprising the steps of: calculating a service life of a gas turbine high temperature component based on fatigue failure in a first section, Calculating a second operation value based on creep failure in a second section that is a steady-state drive section of the high-temperature component, calculating a third operation value based on fatigue failure in the second section, And calculating the service life of the high temperature part based on the first to third operation values. The present invention also provides a method for calculating the service life of a high temperature part of a gas turbine.

According to another aspect of the present invention, the third operation value includes an operation value calculated as (operation time x temperature change amount x weight value) for each of a plurality of temperature increase sections and a plurality of temperature decrease sections included in the second section And the calculated operation values can be summed and calculated. At this time, the weight can be determined according to the temperature change amount in each of the plurality of temperature increase periods and the plurality of temperature decrease periods.

According to still another aspect of the present invention, the first operation value is calculated for each of a plurality of temperature increase sections and a plurality of temperature decrease sections in the first section (operation time x temperature change amount x weight value operated in the corresponding section) , And calculate the operation values by summing the calculated operation values and the trip weight caused by the trip generation.

According to still another aspect of the present invention, the second operation value is obtained by dividing the temperature range in which the second section is defined into a plurality of lower temperature sections, and for each lower temperature section (the total operation time x weight value), and calculates the sum of the calculated operation values. At this time, the weight can be set differently according to the lower temperature range.

According to still another aspect of the present invention, the weights used for calculating the first to third operation values can be set differently according to the model of the gas turbine.

According to another aspect of embodiments of the present invention, there is provided an apparatus for calculating service life of a high temperature part of a gas turbine, comprising: a temperature measurement unit for measuring a combustion temperature of the gas turbine; a time measurement unit for measuring an operation time of the gas turbine; A first operation value based on the fatigue failure in the first section which is the transient state drive period of the high temperature component and a second operation value based on the creep failure in the second section which is the steady state drive period of the high temperature component, A second operation value, and a third operation value based on the fatigue failure in the second section; and a control unit that calculates the service life of the high temperature part based on the calculated first to third operation values A service life calculation device for a gas turbine high temperature part including a service life calculation part is provided.

According to another aspect of the present invention, the operation value calculating section obtains an operation value calculated by (operation time x temperature change amount x weight value) for each of a plurality of temperature increase sections and a plurality of temperature decrease sections in the second section, The third operation value can be calculated by summing the calculated operation values.

With the above-described arrangements, it is possible to provide a method and an apparatus for calculating the service life of a gas turbine high-temperature part with high reliability, whereby maintenance and regeneration of the high temperature part can be performed at an appropriate time, The cost can be reduced.

1 is a diagram showing a concept of calculating a maintenance cycle provided by a gas turbine manufacturer in the past.
Figure 2 is a table provided by the gas turbine manufacturer to determine when maintenance / replacement of hot parts should be made.
3 is a graph showing the temperature change due to the operation of the gas turbine hot parts.
4 is a graph showing a temperature change value occurring in a steady state of a gas turbine hot component.
5 is a block diagram showing a configuration of a gas turbine service life calculation device according to an embodiment of the present invention.
6 is a block diagram showing a configuration of a control unit according to an embodiment of the present invention.
7 is a graph showing the scrap rate according to the degree of use of the gas turbine high temperature part.

BRIEF DESCRIPTION OF THE DRAWINGS The present invention is capable of various modifications and various embodiments, and specific embodiments are illustrated in the drawings and described in detail in the detailed description. It is to be understood, however, that the invention is not to be limited to the specific embodiments, but includes all modifications, equivalents, and alternatives falling within the spirit and scope of the invention. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, the present invention will be described in detail with reference to the accompanying drawings.

The terminology used in this application is used only to describe a specific embodiment and is not intended to limit the invention. The singular expressions include plural expressions unless the context clearly dictates otherwise. In the present application, the terms "comprises" or "having" and the like are used to specify that there is a feature, a number, a step, an operation, an element, a component or a combination thereof described in the specification, But do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, or combinations thereof.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings. Referring to the accompanying drawings, the same or corresponding components are denoted by the same reference numerals, .

First, the temperature state when operating the gas turbine will be described with reference to FIG. Fig. 3 is a graph exemplarily showing a temperature change due to operation of a gas turbine high temperature part.

As shown in Fig. 3, when the gas turbine changes from the stationary state to the operating state and is operated, the temperature of the gas turbine rises. The process in which the state of the gas turbine changes to become a constant high temperature state is transient, and this section is part of the transient section.

Then, the gas turbine is operated in a steady state at a predetermined temperature interval. That is, this section is the normal section, and the gas turbine operates in this steady state with relatively little temperature change.

Finally, the temperature of the gas turbine is lowered to end the operation and change from the operating state to the stop state again. This section is also part of the transitional section and the gas turbine runs in an overt state.

The section in which the gas turbine is in the operating state, that is, the transient section operating in the transient state and the normal section operating in the steady state, is the target section for analyzing the service life.

In the above-mentioned gas turbine operation cycle, the useful life of the high temperature part is calculated considering only the operation value due to the fatigue failure occurring in the transient state and the operation value due to the creep failure occurring in the steady state. However, there was a temperature change in the normal section, which was assumed to have little temperature change, to have a significant effect on lifetime. The measurement of the temperature change in the steady state when the gas turbine was actually operated is shown in FIG.

4 is a graph showing a temperature change value generated in a steady state of a gas turbine high temperature part, which is a result of extraction from actual operation data. As shown in FIG. 4, a considerably large temperature change occurred in the normal section assuming that the temperature was kept constant.

In high temperature components such as blades and vanes, a TBC coating layer is formed to help protect and cool components. If temperature changes occur, the TBC coating layer may be damaged due to differences in thermal expansion coefficient. However, if the TBC coating layer that helps to cool the base material is damaged, the damage of the base material, that is, the blade or the vane itself, is abruptly progressed.

In addition, gas turbine high temperature components are mainly used as peak loads in Korea. In this case, only low cycle fatigue failure due to frequent start / stop operation affects service life of high temperature components. The calculation method is not suitable for the actual use environment in Korea, and the reliability of calculating the service life is not high. That is, there is a need to reflect the fatigue failure due to the high cyclic temperature change in the steady state to the service life calculation.

Hereinafter, a specific apparatus and method for calculating the service life of a gas turbine high-temperature component will be described based on the above-described problem recognition and a solution for solving the problem.

5 is a block diagram showing a configuration of a gas turbine service life calculation device according to an embodiment of the present invention.

Referring to FIG. 5, a gas turbine service life calculating apparatus 100 according to the present embodiment includes a control unit 10, a temperature measuring unit 20, a tamer 30, And the like. The use life calculation apparatus 100 may further include a gas turbine drive unit 40 and a gas turbine 50. It is to be noted that the present invention is not limited to the use life calculation apparatus 100, It will be understood by those of ordinary skill in the art.

The control unit 10 controls the operation of the entire service life calculation apparatus 100. [ The control unit 10 also calculates the service life of the hot parts included in the gas turbine 50 based on the temperature value from the temperature measurement unit 20 and the time value measured based on the timer 30. [ The service life calculation method of the high temperature parts by the control unit 10 will be described later.

The temperature measuring section 20 measures the temperature of the high temperature part to be measured in the gas turbine 50 or the gas turbine 50. For example, the temperature measuring unit 20 measures the combustion temperature of the gas turbine 50. [ The temperature measuring unit 20 measures the temperature in real time and provides the measured temperature to the control unit 10.

The timer 30 generates a clock and enables time measurement accordingly. That is, the timer 30 functions as a time measuring unit. Based on the time measured by the timer 30, the controller 10 measures the operating time according to the driving of the gas turbine. For example, various conditions (temperature interval, temperature change, etc.) will exist while the gas turbine 50 is being driven, and the operating time corresponding to each condition will be measured.

The gas turbine drive unit 40 controls driving of the gas turbine 50 based on a control signal from the control unit 10. [ That is, the gas turbine driving section 40 controls the operation and stop of the gas turbine 50 based on the control of the control section 10.

The gas turbine (50) generates power by burning fuel based on the control of the gas turbine driving part (40).

Hereinafter, a specific method of the service life calculation method by the control unit 10 will be described.

6 is a block diagram showing the configuration of the control unit 10 according to an embodiment of the present invention.

6, the control unit 10 includes a first operation value calculation unit 11, a second operation value calculation unit 12, a third operation value calculation unit 13, a parameter value storage unit 14, And a life calculation unit 15.

First, referring to the parameter value storage unit 14, the parameter value storage unit 14 stores values of various parameters used in calculating the operation value in the first to third operation value calculation units 11 to 13 do. For example, the parameter value storage unit 14 may store a weight or a trip weight according to a temperature required for calculating an operation value. The parameter value storage unit 14 may store a weight or a trip weight according to the temperature for each model of the gas turbine 50.

The first operation value calculation unit 11 calculates the first operation value based on the fatigue failure in the first section, which is the transient state drive period of the high temperature part, based on the measured temperature and the operation time. The first operating value will correspond to the service life based on the fatigue failure in the transient operating period. The first operation value calculation unit 11 uses the weight value from the parameter value storage unit 14 in the first operation value calculation.

Specifically, the first operation value calculation unit 11 may calculate the first operation value in the following manner.

[ Equation 1 ]

(OH_A1) * Temperature change (ΔT_A1) * Weight (a1) + Operation time (OH_A2) * Temperature change amount (ΔT_A2) * Weight (a2) + ..... + Operation time (OH_An) * Temperature change (ΔT_An) * Weight (an) + Trip weight (d)

The operating time refers to the operating time for each of the increased or decreased temperature ranges, and the temperature variation refers to the temperature difference over the corresponding range. For example, in the interval between P0 and P1 in FIG. 3, the time between P0 and P1 is the operation time of the corresponding interval, and the temperature difference between P0 and P1 is the temperature variation of the corresponding interval.

The weight (a) is a value reflecting the stress (stress) caused by different thermal expansion coefficients between the TBC coating layer and the parent material due to the temperature change in each section. These weights can be set differently for each section. For example, the magnitude of the weight may be set differently according to the temperature range including the corresponding section.

In addition, in the case of a gas turbine, when a trip occurs, a stress greater than a stress due to a general temperature change is generated. Therefore, the trip weight d for the trip occurrence is further reflected in the transient state.

The second operation value calculation unit 12 calculates the second operation value based on the creep failure in the second section which is the steady state drive section of the high temperature part, based on the measured temperature and the operation time. The second operating value will correspond to the service life based on the creep failure in the steady state drive period. The second operation value calculation unit 12 uses the weight value from the parameter value storage unit 14 in the second operation value calculation.

Specifically, the second operation value calculation unit 12 may calculate the second operation value in the following manner.

& Quot; (2 ) & quot ;

Operation time (OH_Bn) * Weight (bn) + Operation time (OH_B2) * Weight (b2) + ..... + Operation time (OH_Bn) * Operation time (OH_total)

The second operation value is a value for reflecting the creep failure. Accordingly, in calculating the second operation value, the temperature range within the operation section recognized as the steady state of the gas turbine is divided into a plurality of lower temperature sections, and the operation time divided in each lower temperature section is divided and measured. For example, when the section recognized as a steady state is 1,000 ° C or higher, 1,000-1,100 ° C can be set as a first lower temperature section, and 1,100-1,200 ° C as a second low temperature section.

The weight (b) may be set differently depending on the temperature, that is, the lower temperature interval. For example, as the gas turbine runs at high temperatures, the service life will increase rapidly, so that the weight of the high temperature interval can be set to be larger than the weight of the low temperature interval.

The third operation value calculation unit 13 calculates the third operation value based on the fatigue failure in the second section. The third operating value will correspond to the service life based on the fatigue failure in the steady state drive period. The third operation value calculation unit 13 uses the weight from the parameter value storage unit 14 in the third operation value calculation.

Specifically, the third operation value calculation unit 13 may calculate the third operation value in the following manner.

& Quot; (3 ) & quot ;

(OH_C1) * Weight (c1) + Operation time (OH_C2) * Temperature change (ΔT_C2) * Weight (c2) + ..... + Operation time (OH_Cn) * Temperature change (ΔT_Cn) * Weight (cn)

Equation (3) is similar to Equation (1) except that there is no trip weight. This is because the third operation value also reflects the fatigue failure according to the temperature change in the service life.

Therefore, when calculating the third operation value, the temperature change amount and the operation time and weight of the portion where the temperature change occurs are taken into consideration for all the sections where the temperature increases or decreases in the steady state section.

In other words, the amount of temperature change occurring in the steady state section is continuously monitored through the temperature measuring unit 20, and the magnitude of the temperature change amount, the operation time thereof, and the magnitude of the temperature change amount And their operating hours. Then, the product of the temperature change amount and the operation time is multiplied by a weight to calculate an operation value in a section where the temperature increases or in a section in which the temperature decreases, and the third operation value is calculated by summing all the calculated operation values.

Of course, the weight (c) is also a value reflecting the stress (stress) caused by the different thermal expansion coefficients between the TBC coating layer and the base material due to the temperature change in each section. Therefore, the weight (c) may also be set differently for each section. For example, the magnitude of the weight may be set differently according to the temperature range including the corresponding section.

The functions of the operation value calculation unit may be performed by the first to third operation value calculation units 11 to 13 described above.

The first to third operation value calculation units 11 to 13 directly receive the time measurement values for determining the temperature measurement value and the operation time from the temperature measurement unit 20 and the timer 30, But the present invention is not limited thereto. For example, in a separate configuration in the control unit 10, the value of the measured temperature over time is converted into a database, and the first to third operating value calculating units 11 to 13 calculate the temperature and the operating time You can also extract the values. Or the information on the temperature measurement values required for the first to third operation value calculating sections 11 to 13 and the corresponding operation time is supplied from the temperature side loader 20 and the timer 30 or directly from the database To the third operation value calculating units 11 to 13, respectively.

The service life calculation unit 15 calculates the service life of the high temperature parts based on the first to third operation values calculated by the first to third operation value calculation units 11 to 13. [ The service life calculation unit 15 may simply calculate the service life by summing the first to third operation values. However, the present invention is not limited thereto. For example, it is also possible to multiply the respective operation values by different weights, and then sum them.

On the other hand, when the service life of the high temperature part calculated by the service life calculation part 15 exceeds the predetermined reference value, the technician or the manager who operates the power plant performs maintenance or replacement of the high temperature part. Although not shown, a table serving as a reference for maintenance or replacement of each high-temperature component may be provided similar to that shown in FIG. 2, and may include a configuration that automatically notifies a technician or an administrator if the calculated service life exceeds a predetermined criterion will be. Or the service life of the high temperature part calculated by the service life calculation part 15 may be displayed on the display screen so that the technician or the manager can check it.

FIG. 7 is a graph showing a result of applying the high temperature part service life calculation method according to the present invention, and FIG. 7 is a graph showing the scrap ratio according to the degree of use of the gas turbine high temperature part.

More specifically, FIG. 7 shows that the results obtained by the service life calculation method according to the present invention are in good agreement with the scrap rates according to the optimum operation cycle for the high temperature components of gas turbines actually used.

Of course, in FIG. 7, the scrap rate according to the optimum operation cycle is represented by a graph of a linear equation, but it may appear differently depending on the type of gas turbine (for example, an exponential function).

As described above, there is a problem that the reliability of judgment is deteriorated because the actual use environment of the gas turbine can not be reflected when determining the maintenance and replacement by calculating the service life in the manner provided by the manufacturer.

However, through the above-mentioned constitution and method, it is possible to provide a method and apparatus for calculating the service life of gas turbine high-temperature parts with high reliability, thereby enabling maintenance and regeneration of high-temperature parts at an appropriate time, It is possible to reduce the cost of the system.

Currently, the domestic gas turbine replacement market is worth W300bn annually, and the maintenance market is worth W200bn, and all the high-temperature components are imported from overseas. Therefore, it is expected that 20 to 30% of the operating cost of high-temperature parts can be saved by optimizing the service life of high-temperature parts according to the service life calculation method according to the present invention.

The specific acts described in the present invention are, by way of example, not intended to limit the scope of the invention in any way. For brevity of description, descriptions of conventional electronic configurations, control systems, software, and other functional aspects of such systems may be omitted. Also, the connections or connecting members of the lines between the components shown in the figures are illustrative of functional connections and / or physical or circuit connections, which may be replaced or additionally provided by a variety of functional connections, physical Connection, or circuit connections. Also, unless explicitly mentioned, such as " essential ", " importantly ", etc., it may not be a necessary component for application of the present invention.

The use of the terms " above " and similar indication words in the specification of the present invention (particularly in the claims) may refer to both singular and plural. In addition, in the present invention, when a range is described, it includes the invention to which the individual values belonging to the above range are applied (unless there is contradiction thereto), and each individual value constituting the above range is described in the detailed description of the invention The same. Finally, the steps may be performed in any suitable order, unless explicitly stated or contrary to the description of the steps constituting the method according to the invention. The present invention is not necessarily limited to the order of description of the above steps. The use of all examples or exemplary language (e.g., etc.) in this invention is for the purpose of describing the present invention only in detail and is not to be limited by the scope of the claims, It is not. It will also be appreciated by those skilled in the art that various modifications, combinations, and alterations may be made depending on design criteria and factors within the scope of the appended claims or equivalents thereof.

100 High-temperature part service life calculation device
10 Control unit 11 First operation value calculating unit
12 second operation value calculating unit 13 third operation value calculating unit
14 Parameter value storage part 15 Service life calculation part
20 Temperature measurement section 30 Timer
40 Gas turbine drive part 50 Gas turbine

Claims (9)

As a service life calculation method of a gas turbine high temperature part,
Calculating a first operation value based on fatigue failure in a first section that is a transient state drive period of the high temperature part;
Calculating a second operation value based on a creep failure in a second section that is a steady-state driving section of the high-temperature component;
Calculating a third operation value based on fatigue failure in the second section; And
And calculating the service life of the high-temperature part based on the first operation value to the third operation value,
Wherein the first operation value is obtained by calculating an operation value calculated for each of a plurality of temperature increase sections and a plurality of temperature decrease sections in the first section (operation time x temperature change amount x weight value operated in the corresponding section) And calculating a sum of the calculated operation values and the trip weight caused by the trip occurrence to calculate the service life of the gas turbine high temperature part. The method according to claim 1,
The third operation value is obtained by calculating an operation value calculated by (operation time x temperature change amount x weight value) for each of a plurality of temperature increase sections and a plurality of temperature decrease sections included in the second section, And calculating the service life of the high temperature part of the gas turbine. The method of claim 2,
Wherein the weight used for calculating the third operation value is determined according to the temperature variation amount in each of the plurality of temperature increase sections and the plurality of temperature decrease sections. delete The method according to claim 1,
The second operation value is obtained by dividing the temperature range in which the second section is defined into a plurality of lower temperature sections and calculating the driving range of the lower temperature section (the total operation time x weighted value operated in the lower temperature section) And calculating the operating life of the gas turbine high temperature part by summing the calculated operating values. The method of claim 5,
Wherein the weight used for calculating the second operation value is set differently according to the lower temperature range. The method according to any one of claims 1, 2, 3, 5, and 6,
Wherein the weight used for calculating the first operation value to the third operation value is set differently according to the type of the gas turbine. A service life calculating device for a gas turbine high temperature part,
A temperature measuring unit for measuring a combustion temperature of the gas turbine;
A time measuring unit measuring an operation time of the gas turbine;
A first operation value based on the fatigue failure in the first section which is the transient state drive period of the high temperature part, a creep failure in the second section which is the steady state drive section of the high temperature part, A second operation value based on the first operation value and a third operation value based on the fatigue failure in the second section; And
And a service life calculation unit for calculating a service life of the high temperature part based on the calculated first to third operation values,
Wherein the first operation value is obtained by calculating an operation value calculated for each of a plurality of temperature increase sections and a plurality of temperature decrease sections in the first section (operation time x temperature change amount x weight value operated in the corresponding section) And calculating a sum of the calculated operation values and the trip weight caused by the trip generation. The method of claim 8,
The operation value calculation section calculates an operation value calculated by (operation time x temperature change amount x weight value) for each of a plurality of temperature increase sections and a plurality of temperature decrease sections in the second section, To calculate the third operating value of the gas turbine high-temperature part.

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