KR101683673B1 - Device for anticipating of compressor performance map - Google Patents

Abstract

The present invention relates to an apparatus and a method for predicting a performance map of a compressor and relates to a gas turbine compressor performance map which is important data in predicting the performance of the gas turbine in accordance with the operating environment of the gas turbine, And more particularly, The compressor performance map predicting apparatus according to an embodiment of the present invention includes a design analysis module that calculates design parameter and material property information by performing design analysis of a turbine according to input parameters and a compressor performance map Dimensional non-dimensional rotation number information, relative non-dimensional flow amount information, and pressure ratio information, and changes the calculated relative non-dimensional rotation number information, relative non-dimensional flow amount information, and pressure ratio information to match the design parameters according to the change in outside temperature Design analysis module that simulates the compressor performance map of the gas turbine.

Description

≪ Desc / Clms Page number 1 > DEVICE FOR ANTICIPATING OF COMPRESSOR PERFORMANCE MAP < RTI ID =

The present invention relates to an apparatus and a method for predicting a performance map of a compressor and relates to a gas turbine compressor performance map which is important data in predicting the performance of the gas turbine in accordance with the operating environment of the gas turbine, And more particularly,

The importance of new and renewable energy is increasing due to the continuation of the high oil price situation and the progress of the Convention on Climate Change. Biogas power generation during new and renewable energy generation is a method of generating biogas generated by fermenting landfill gas, food waste and sewage sludge in an anaerobic state. Most of the biogas are composed of methane and carbon dioxide. Therefore, biogas has lower methane content and lower calorific value than natural gas.

In the case of a gas turbine designed for use as a natural gas fuel, the operating point of the gas turbine will change if the biogas is used as fuel. The change of the operating point of the gas turbine changes the performance of the gas turbine and affects the respective constituent parts constituting the gas turbine.

Generally, a gas turbine consists of a compressor, a combustor, and a turbine. The air that enters the compressor inlet is compressed, combusted in a combustor, and then expanded in a turbine to produce an output. To predict the performance of the gas turbine due to the operating environment of the gas turbine and the load variation, a downscale analysis is required.

The design of the gas turbine is first analyzed by design simulation of the gas turbine and then it is repeatedly calculated by using the performance map of the compressor until the operating point of the compressor and the turbine is matched according to the operating environment and load variation The point is calculated to predict the performance change of the gas turbine.

Therefore, the performance map data of the compressor is important in predicting the performance change depending on the operating environment and the load variation. In general, since the compressor performance map of each gas turbine is not disclosed, it is impossible to analyze the performance of the gas turbine using the compressor performance map have.

Therefore, this method is applied to the 5MW gas turbine designed to use natural gas as the fuel, because the biogas generated through the anaerobic digestion process in food waste, landfill gas, sewage sludge, etc. is used as the fuel of the gas turbine, The performance of the gas turbine is changed. At this time, a performance map of the compressor is required to accurately analyze the performance change. However, since the compressor performance map of the gas turbine is not provided by the manufacturer, it is difficult to interpret the performance change.

In order to perform the off-design analysis using the compressor performance diagram which was impossible with the conventional gas turbine analysis method, it is possible to perform more accurate performance analysis by predicting and applying the performance performance of the compressor using the data provided by the manufacturer There is an advantage of this method.

Provides accurate system performance analysis data using the compressor performance map prediction method without providing the compressor performance map of the manufacturer's gas turbine.

The performance map of the gas turbine compressor includes the parameters that predict the performance of the gas turbine and it is the data that indicates the long experience of production and the level of the technology of the gas turbine manufacturer. It is possible to predict the performance of the gas turbine system using the biogas effectively by predicting the compressor performance map.

According to an aspect of the present invention, a compressor performance map prediction apparatus is provided.

The compressor performance map predicting apparatus according to an embodiment of the present invention includes a design analysis module that calculates design parameter and material property information by performing design analysis of a turbine according to input parameters and a compressor performance map Dimensional non-dimensional rotation number information, relative non-dimensional flow amount information, and pressure ratio information, and changes the calculated relative non-dimensional rotation number information, relative non-dimensional flow amount information, and pressure ratio information to match the design parameters according to the change in outside temperature Design analysis module that simulates the compressor performance map of the gas turbine.

According to an aspect of the present invention, a method for estimating a compressor performance map is provided.

The compressor performance map predicting method according to an embodiment of the present invention includes the steps of calculating design parameter and property information by performing design analysis of a turbine according to an input parameter and calculating a relative performance of a compressor performance map using the design analysis parameter and property information Dimensional flow rate information, pressure ratio information, relative non-dimensional flow rate information, pressure ratio information, and relative non-dimensional flow rate information, relative non-dimensional flow rate information, and pressure ratio information, Lt; RTI ID = 0.0 > performance map < / RTI >

Biogas has lower calorific value because it contains less methane than natural gas. Since the gas turbine is designed as a natural gas fuel, when the biogas is applied as fuel, the operating point of the gas turbine is moved and the performance at the off-design point is shown. Compressor performance maps are very important to accurately perform these off-design analyzes. Performance analysis of a gas turbine system using biogas can be carried out without difficulty by using the compressor performance map obtained through the performance prediction method of the present compressor. Also, a change in operating point of the gas turbine will affect the life of the gas turbine It is anticipated that a suitable predictable operating point for solving the problem of reducing the life of the gas turbine can be provided. It is expected that the accident prevention and maintenance cost of gas turbine will be reduced. It is possible to predict the stable supply of electricity through prediction of the performance change of the gas turbine. In addition, due to the government's policy on Renewable Portfolio Standards (RPS) and the prohibition of marine dumping of organic wastes from 2013, it is expected that this MW-class biogas turbine power generation system will be expanded and expanded. The technical effect of this method is considered to be significant.

FIG. 1 is a block diagram of a compressor performance map predicting apparatus according to an embodiment of the present invention; FIG.
4 is a flowchart illustrating a method of predicting a compressor performance map according to an embodiment of the present invention.
FIG. 5 is a diagram illustrating a prediction result of a compressor performance map according to an embodiment of the present invention. FIG.
6 is a diagram for describing gas turbine design parameters and performance data according to an embodiment of the present invention;
7 is a view for explaining a result of an output change analysis according to outdoor temperature when natural gas is used as a fuel using a predicted compressor map according to an embodiment of the present invention.
8 is a view for explaining a result of a compressor performance analysis according to an embodiment of the present invention.

While the present invention has been described in connection with certain exemplary embodiments, it is to be understood that the invention is not limited to the disclosed embodiments, but, on the contrary, is intended to cover various modifications and similarities. 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 In the following description of the present invention, detailed description of known related arts will be omitted when it is determined that the gist of the present invention may be unnecessarily obscured. In addition, numerals (e.g., first, second, etc.) used in the description of the present invention are merely an identifier for distinguishing one component from another.

Also, in this specification, when an element is referred to as being "connected" or "connected" with another element, the element may be directly connected or directly connected to the other element, It should be understood that, unless an opposite description is present, it may be connected or connected via another element in the middle.

1 to 3 are block diagrams of a compressor performance map predicting apparatus according to an embodiment of the present invention.

Referring to FIG. 1, a compressor performance map predicting apparatus 100 includes a design analysis module 120 and a design removal analysis module 140.

The design analysis module 120 performs the design analysis of the turbine according to the input parameters to calculate the design parameters and the property information.

Referring to FIG. 2, the design analysis module 120 includes a parameter input unit 122 and a parameter calculation unit 124.

The parameter input unit 122 receives parameters including pressure ratio, gas flow rate, turbine outlet temperature, and turbine inlet temperature information.

The parameter calculation unit 124 calculates the design parameter and the property information of each constituent part of the gas turbine until the efficiency agrees with the output of the gas turbine using the input parameters. Here, the design parameters include pressure ratio information of the compressor, outlet gas flow rate information, efficiency information of the compressor, efficiency information of the gas turbine, cooling air flow rate information, and information of air and gas composition ratio, temperature information, pressure information, And may include physical property information including the physical property information.

The off-design analysis module 140 calculates the relative non-dimensional rotation number information, the relative non-dimensional flow amount information, and the pressure ratio information of the compressor performance map using the design analysis parameter and the material property information, The relative non-dimensional flow rate information and the pressure ratio information are changed to simulate the compressor performance map of the gas turbine so as to match the design parameters according to the change in the outside air temperature.

3, the off-design analysis module 140 includes an relative dimensionless rotation number calculation module 142, an outside temperature non-dimensional flow amount information calculation module 144, an operation point information calculation module 146, Module 148 and a compressor performance map prediction module 150. [

The relative non-dimensional rotation number calculation module 142 calculates the non-dimensional flow information of the compressor and the non-dimensional flow information of the turbine by using the design parameter and the material property information, and outputs the compressor performance map and the outside air temperature data The relative non-dimensional rotation number is calculated.

The outdoor temperature non-dimensional flow rate information calculation module 144 calculates the non-dimensional flow rate information at the corresponding outdoor temperature assuming a point corresponding to the relative non-dimensional flow rate information and the pressure ratio information belonging to the relative non-dimensional rotation number line shown in the compressor performance map The actual flow rate information and the outlet pressure information of the compressor are calculated.

The operating point information calculation module 146 corrects and corrects the actual flow rate information and the outlet pressure information of the calculated compressor until the choking condition of the gas turbine is matched with the point corresponding to the non-dimensional flow rate information and the pressure ratio information, .

The operating point information re-calculation module 148 confirms that the output and efficiency information of the actual gas turbine coincide with the calculated operating point data, and if not, the relative non-dimensional rotation number line in the compressor performance map Dimensional flow information and pressure ratio information, and recalculates the operating point data.

The compressor performance map predicting module 150 simulates a compressor performance map by performing iterative calculation while changing a predetermined range of outside temperature information.

4 is a flowchart illustrating a method of predicting a compressor performance map according to an embodiment of the present invention.

The performance map of the gas turbine can be predicted by using the performance change data of the gas turbine according to the outside temperature change when natural gas is used and the performance map of the gas turbine can be predicted and the performance map of the gas turbine using the biogas as fuel .

Hereinafter, the present method will be described in detail.

), 터빈출구 온도(TET), 터빈입구온도(TIT, 혹은 터빈 로터 입구온도(TRIT))를 입력받는다.Referring to FIG. 4, in step S410, the compressor performance map predicting apparatus 100 first determines a parameter pressure ratio (PR), a gas flow rate

), Turbine outlet temperature (TET), turbine inlet temperature (TIT, or turbine rotor inlet temperature (TRIT)).

), 터빈효율(

), 냉각 공기유량(

)을 가정하여, 가스터빈의 출력과 효율이 일치할 때 까지 수정, 반복하여 계산하여 가스터빈 각 구성부의 파라미터(PR,

,

,

,

)와 물성치(공기 및 가스 성분비, 온도, 압력, 몰질량등)를 산출한다.
In step S420, the compressor performance map predicting apparatus 100 determines the compressor efficiency ("

), Turbine efficiency

), Cooling air flow rate (

) And corrects and repeatedly calculates the parameters of the gas turbine components (PR,

,

,

,

) And physical properties (air and gas composition ratio, temperature, pressure, molar mass, etc.).

The efficiency equation of the compressor used is as follows.

(1)

(One)

는 효율, h는 엔탈피, in은 입구, out은 출구, c는 압축기, s는 등엔트로피 상태이다.
From here

Is the enthalpy, h is the enthalpy, in is the inlet, out is the outlet, c is the compressor, and s is the entropy state.

The efficiency equation of the turbine used is as follows.

(2)

(2)

는 효율,

는 출력,

은 질량유량, h는 엔탈피,

로터냉각공기 출력의 기여도, in은 입구, out은 출구, T는 터빈, s는 등엔트로피 상태, nc는 노즐 냉각공기, rc는 로터냉각공기이다.
From here

Efficiency,

Output,

Is the mass flow rate, h is the enthalpy,

The contribution of the rotor cooling air output, in, is the inlet, out is the outlet, T is the turbine, s is the entropy state, nc is the nozzle cooling air, and rc is the rotor cooling air.

The output formula of the gas turbine used is as follows.

(3)

(3)

는 효율,

는 출력, GT는 가스터빈, T는 터빈,c는 압축기 gear은 기어박스, gen은 발전기
From here

Efficiency,

Output, GT gas turbine, T turbine, c compressor gearbox gearbox, gen generator

The efficiency equation of the gas turbine used is as follows.

(4)

(4)

는 효율,

는 출력, GT는 가스터빈,

은 질량유량, LHV는 저위발열량이다.
From here

Efficiency,

Output, GT is a gas turbine,

Is the mass flow rate, and LHV is the low calorific value.

과 터빈에서의 무차원 유량

을 산출한다.In step S430, the compressor performance map predicting apparatus 100 receives each component parameter and the property value from the design module,

And non-dimensional flow in the turbine

.

The compressor performance map predicting apparatus 100 inputs a compressor performance map of a gas turbine which is generally publicized after that, inputs the lowest outside temperature of the data, and calculates a relative non-dimensional rotation number corresponding to the outside temperature, (5).

(5)

(5)

N is the number of revolutions, T is the compressor inlet temperature, MW is the molecular weight, and d is the design point. At the design point, the compressor inlet temperature is 15 ° C and the inlet pressure is 1 atm.

In step S440, the compressor performance map predicting apparatus 100 calculates the non-dimensional flow rate information at the corresponding outside temperature, assuming a point corresponding to the relative dimensionless flow rate information and pressure ratio information belonging to the relative dimensionless revolution number line indicated in the compressor performance map And calculates actual flow rate information and outlet pressure information of the compressor.

Since the compressor performance map predicting apparatus 100 operates at a point belonging to the relative dimensionless revolution number line obtained by the gas turbine on the compressor performance map under the corresponding ambient temperature condition, the relative non-dimensional flow quantity belonging to the relative non- Assuming that the pressure ratio is assumed, the actual flow rate and outlet pressure of the compressor can be obtained by obtaining the non-dimensional flow rate at the corresponding outside air temperature.

The relative non-dimensional flow equation of the compressor map used is as follows.

(6)

(6)

은 질량유량, P는 압축기 입구 압력, T는 압축기 입구 온도, R은 기체상수, MW는 분자량, d는 설계점이다.

Is the mass flow rate, P is the compressor inlet pressure, T is the compressor inlet temperature, R is the gas constant, MW is the molecular weight, and d is the design point.

The pressure ratio formula of the compressor map used is as follows.

(7)

(7)

The relative efficiency formula used is as follows.

(8)

(8)

In step S450, the compressor performance map predicting apparatus 100 corrects the actual flow rate information and the outlet pressure information of the calculated compressor by correcting the point corresponding to the non-dimensional flow rate information and the pressure ratio information until the choking condition of the gas turbine is matched And calculates operating point information.

The compressor performance map predicting apparatus 100 estimates the non-dimensional flow rate and the pressure ratio until the compressor and the turbine are matched by satisfying the choking condition in the turbine using the actual flow rate and outlet pressure value of the calculated compressor Calculate the point of excitation and repeat it. Through this process, the operating point is obtained and the performance is predicted during the designing.

The choking condition used in the turbine is as follows.

(9)

(9)

은 질량유량, A는 면적, P는 압력, T는 온도, T는 터빈, in은 입구, R은 기체상수이다.From here

Is the mass flow, A is the area, P is the pressure, T is the temperature, T is the turbine, in is the inlet and R is the gas constant.

The compressor performance map predicting apparatus 100 according to an embodiment of the present invention can obtain a compressor performance diagram as shown in FIG. As can be seen from FIG. 7, when the natural gas is used as the fuel, the compressor performance map is predicted to give a result similar to the output change data according to the outside temperature change

In step S460, the compressor performance map predicting apparatus 100 determines whether the predicted output of the gas turbine, the efficiency, the flow rate, the turbine outlet temperature, and the like are consistent with the data.

In step S465, the compressor performance map predicting apparatus 100 moves the corresponding dimensionless revolution number line if it does not match, and repeats the calculation until the output, efficiency, flow rate, and turbine outlet temperature of the gas turbine on the data coincide do.

In step S470 and step S475, the compressor performance map predicting apparatus 100 performs the iterative calculation while changing the outside air temperature until the outside outside air temperature range is satisfied for the maximum outside air temperature condition. Through this process, the compressor performance map can be predicted.

6 to 8 are diagrams for explaining the accuracy of compressor map performance simulation according to an embodiment of the present invention.

Referring to FIGS. 6 to 8, the results of performance analysis using the compressor performance diagram predicted by the present method are as follows. As can be seen from FIG. 6, the compressor performance map predicting apparatus 100 can be understood that the design analysis is performed well first. As a result of the performance analysis using the predicted compressor performance diagram based on this method, as shown in FIG. 7 and FIG. 8, the output data of the gas turbine is within the error range of ± 2% . Therefore, the predicted compressor performance of the gas turbine through this method can be seen as well predicted.

In the gas turbine performance analysis, the operating point of the gas turbine is determined more influenced by the performance performance of the compressor, so that the accuracy of the predicted compressor performance lead to a great influence on the performance analysis of the gas turbine. It is expected that the performance analysis of the gas turbine when the biogas is applied to the gas turbine as a fuel is also within ± 2% of the error range since the predicted compressor performance curve of the currently predicted gas turbine meets the value within the error range of ± 2% .

Embodiments of the invention may include a computer readable medium having program instructions for performing various computer implemented operations. The computer-readable medium may include program instructions, local data files, local data structures, etc., alone or in combination. The media may be those specially designed and constructed for the present invention or may be those known to those skilled in the computer software.

It will be apparent to those skilled in the art that various modifications and variations can be made in the present invention without departing from the spirit or scope of the invention as defined in the appended claims. Changes and modifications may be made without departing from the spirit and scope of the invention.

Claims (11)

A design analysis module that performs design analysis of the turbine according to input parameters and calculates design parameter and material property information; And
Dimensional flow rate information and pressure ratio information of the compressor performance map by using the design parameter and the property information, and calculates the relative non-dimensional flow rate information, the relative non-dimensional flow rate information, and the pressure ratio information And a de-design analysis module for simulating the compressor performance map of the gas turbine so as to match the design parameters according to the change in outside temperature,
The design interpretation module
A parameter input for receiving the input parameter, the input parameter including pressure ratio, gas flow rate, turbine outlet temperature, and turbine inlet temperature information; And
A parameter calculation section for calculating design parameters and physical property information of each constituent part of the gas turbine until the efficiency agrees with the output of the gas turbine using the input parameters, the design parameters including pressure ratio information of the compressor, outlet gas flow rate information, Wherein the compressor performance map includes at least one of a compressor efficiency information, a efficiency information, a gas turbine efficiency information, a cooling air flow rate information, and air and gas composition ratio information, temperature information, pressure information, and molar mass information. Prediction device.
delete The method according to claim 1,
The de-design analysis module
Dimensional flow rate information of the compressor and the non-dimensional flow rate information of the turbine by using the design parameter and the material property information, and calculates the relative non-dimensional rotation number by inputting the compressor performance map and the outside air temperature data of the gas turbine, A relative non-dimensional rotation number calculation module;
Dimensionless flow rate information at the corresponding outside temperature by assuming a point corresponding to the relative dimensionless flow rate information and the pressure ratio information belonging to the relative dimensionless revolution number line indicated in the compressor performance map and calculating actual flow rate information and outlet pressure information of the compressor An outdoor temperature non-dimensional flow rate information calculation module; And
An operating point information calculation module for calculating operating point information by correcting and repeating the points corresponding to the non-dimensional flow rate information and pressure ratio information until the actual flow rate information and the outlet pressure information of the calculated compressor are matched with the choking condition of the gas turbine A compressor performance map predicting device;
The method of claim 3,
Correcting the relative non-dimensional flow rate information and the pressure ratio information belonging to the relative non-dimensional rotation number line indicated in the compressor performance map, if the output and efficiency information of the actual gas turbine match with the calculated operating point data, Further comprising an operating point information re-calculating module for recalculating the operating point data.
5. The method of claim 4,
Further comprising: a compressor performance map predicting module for performing repetitive calculation while changing outside air temperature information in a predetermined range to simulate a compressor performance map.
Calculating a design parameter and physical property information by performing a design analysis of a turbine according to an input parameter; And
Dimensional flow rate information and pressure ratio information of the compressor performance map by using the design parameter and the property information, and calculates the relative non-dimensional flow rate information, the relative non-dimensional flow rate information, and the pressure ratio information To simulate the compressor performance map of the gas turbine so as to match the design parameters according to the change in outside temperature,
The step of calculating the design parameter and the property information
Receiving the input parameter, the input parameter including a parameter pressure ratio, a gas flow rate, a turbine outlet temperature, and a turbine inlet temperature information; And
Calculating design parameter and physical property information of each constituent part of the gas turbine until efficiency of the gas turbine is matched with the output of the gas turbine using the input parameter, the design parameters including pressure ratio information of the compressor, outlet gas flow rate information, , A parameter including the efficiency information of the gas turbine, the information including the cooling air flow rate information, and the air and gas composition ratio information, the temperature information, the pressure information, and the molar mass information. .
delete The method according to claim 6,
The step of simulating the compressor performance map of the gas turbine
Dimensional flow rate information of the compressor and the non-dimensional flow rate information of the turbine by using the design parameter and the material property information, and calculates the relative non-dimensional rotation number by inputting the compressor performance map and the outside air temperature data of the gas turbine, ;
Dimensional flow rate information and pressure ratio information belonging to the relative non-dimensional flow rate line indicated in the compressor performance map, calculates the non-dimensional flow rate information at the corresponding outdoor temperature, and calculates the actual flow rate information and the outlet pressure information of the compressor ; And
Calculating the actual flow rate information and the outlet pressure information of the calculated compressor by correcting and repeating the point corresponding to the non-dimensional flow rate information and the pressure ratio information until the choking condition of the gas turbine is matched, How to predict performance maps.
9. The method of claim 8,
Correcting the relative non-dimensional flow rate information and the pressure ratio information belonging to the relative non-dimensional rotation number line indicated in the compressor performance map, if the output and efficiency information of the actual gas turbine match with the calculated operating point data, Further comprising recalculating the operating point data.
10. The method of claim 9,
And repeating calculation while changing the outside-air temperature information in a predetermined range to simulate a compressor performance map. A computer program for executing the method according to any one of claims 6, 8, 9 and 10, wherein the computer program is recorded.

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