CN111079236B - Method for obtaining matching points of female machine for capacity increase of gas compressor of ship gas turbine - Google Patents

Method for obtaining matching points of female machine for capacity increase of gas compressor of ship gas turbine Download PDF

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CN111079236B
CN111079236B CN201911275867.7A CN201911275867A CN111079236B CN 111079236 B CN111079236 B CN 111079236B CN 201911275867 A CN201911275867 A CN 201911275867A CN 111079236 B CN111079236 B CN 111079236B
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compressor
female
modified
total pressure
pressure ratio
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CN111079236A (en
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李冬
隋雪
汪作心
邓庆锋
万新超
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703th Research Institute of CSIC
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Abstract

A method for obtaining a matching point of a female machine for compressor capacity increase of a ship gas turbine relates to the field of gas turbine industry. The invention aims to solve the problem that the existing method for accurately and quickly designing capacity increasing and grade increasing for the gas compressor is lacked. The flow rate and the total pressure ratio of the mother type compressor are obtained through some parameters on the mother type compressor and through setting the flow rate and the total pressure ratio of the modified compressor, the obtained flow rate and the obtained total pressure ratio of the mother type compressor are drawn in a general characteristic diagram of the mother type compressor and are used as corresponding matching points on the mother type compressor, the two matching points are connected to form a straight line, and the capacity increasing and the stage increasing design are carried out on the modified compressor according to the straight line. The method is used for finding matching points convenient for capacity and grading on a master machine so as to carry out capacity and grading design.

Description

Mother model machine matching point obtaining method for ship gas turbine compressor capacity increasing
Technical Field
The invention relates to a method for acquiring matching points of a master model machine. Belongs to the field of gas turbine industry.
Background
The technology of gas turbines, particularly the technology of gas compressors, is complex, and much effort and cost are needed to obtain a gas turbine with excellent performance and higher power. Therefore, after a master machine (a master compressor) is available, the design of increasing capacity of the machine set becomes a main means for further developing the gas turbine. The compressor is used as a tap and a key of the gas turbine, plays a decisive role in the capacity increase of the unit, and the starting point of the capacity increase of the gas turbine is the capacity increase of the compressor. The compressor pressurization is a main means of the high-power compressor capacity-increasing improvement design, the flow and pressure ratio of the compressor and the power of a unit can be greatly improved, and the excellent pneumatic performance and the structural reliability of a mother machine can be fully inherited. In the process of compressor upgrading design, the selection of the matching point of the female die machine directly determines the performance of a modified machine (modified compressor, namely the modified female die compressor). How to quickly and accurately calculate the distribution of matching points of a master model machine on a general characteristic diagram of the master model machine according to various design indexes of the modification machine in the index demonstration process of the modification machine is a key technology and a technical difficulty of capacity increasing and grading pneumatic design of a gas compressor.
Disclosure of Invention
The invention aims to solve the problem that the existing method for accurately and quickly designing capacity increasing and grade increasing for the gas compressor is lacked. The method for obtaining the matching point of the female die machine for the capacity increasing of the gas compressor of the ship gas turbine is provided.
The method for obtaining the matching point of the female die machine for the capacity expansion of the gas compressor of the ship gas turbine is characterized by comprising the following steps of:
the method comprises the following steps of firstly, obtaining the inlet total temperature of the modified compressor according to the rotating speed of the female compressor, the inlet temperature of the female compressor and the set rotating speed of the modified compressor;
step two, obtaining the zero-level total pressure ratio of the modified compressor according to the total inlet temperature of the modified compressor, the inlet temperature of the female compressor and the variable efficiency of the zero level of the female compressor;
step three, obtaining the inlet total pressure of the modified compressor according to the zero-level total pressure ratio of the modified compressor and the inlet total pressure of the female compressor;
step four, obtaining the flow of the mother type compressor according to the total inlet pressure of the modified compressor, the total inlet pressure of the mother type compressor, the inlet temperature of the mother type compressor, the total inlet temperature of the modified compressor and the set flow of the modified compressor;
obtaining the total pressure ratio of the mother type compressor according to the zero-level total pressure ratio of the modified compressor and the set total pressure ratio of the modified compressor;
and step five, according to the flow rate of the female compressor and the total pressure ratio of the female compressor, drawing the flow rate of the female compressor and the total pressure ratio of the female compressor on a general characteristic diagram of the female compressor to serve as two matching points on the female compressor, connecting the two matching points to obtain a straight line, and performing capacity increasing and stage increasing on the female compressor according to the straight line.
Preferably, in the step one, the total temperature of the inlet of the compressor is modified
Figure BDA0002315540380000021
Expressed as:
Figure BDA0002315540380000022
in the formula (I), the compound is shown in the specification,
Figure BDA0002315540380000023
inlet temperature, n, of the compressor of the female type φ For a set modified compressor speed, n m The rotating speed of the female compressor.
Preferably, in the second step, the zero-stage total pressure ratio of the modified compressor
Figure BDA0002315540380000024
Expressed as:
Figure BDA0002315540380000025
wherein k is the adiabatic exponent, η n Is the variable efficiency of the zero level of the female compressor.
Preferably, in the third step, the total pressure of the inlet of the modified compressor is
Figure BDA0002315540380000026
Expressed as:
Figure BDA0002315540380000027
in the formula (I), the compound is shown in the specification,
Figure BDA0002315540380000028
the inlet total pressure of the female type compressor.
Preferably, in the fourth step, the flow G of the female compressor m Expressed as:
Figure BDA0002315540380000029
in the formula, G φ To retrofit the compressor flow.
Preferably, in the fourth step, the total pressure ratio of the female-type compressor
Figure BDA00023155403800000210
Expressed as:
Figure BDA00023155403800000211
in the formula (I), the compound is shown in the specification,
Figure BDA00023155403800000212
the total pressure ratio of the set modified compressor is adopted.
The invention has the beneficial effects that:
the flow rate and the total pressure ratio of the master compressor are obtained through some parameters on the master compressor and through setting the flow rate and the total pressure ratio of the modified compressor, the obtained flow rate and the obtained total pressure ratio of the master compressor are drawn in a general characteristic diagram of the master compressor and are used as corresponding matching points on the master compressor, the two matching points are connected to form a straight line, the modified compressor is subjected to capacity increasing and stage increasing design according to the straight line, and the proper matching points are finally found through continuously adjusting the set flow rate and the set total pressure ratio of the modified compressor. And the optimal capacity increasing and grading design of the modified compressor is realized.
By adopting the method to increase the capacity and the level of the female-type compressor, the inherited predicted operating point of the female-type compressor and the performance of the modified compressor can be directly seen in a general characteristic diagram of the female-type compressor. The performance of the design point of the modified compressor can be analyzed intuitively, quickly and accurately, and the optimal design parameter is determined.
The application particularly relates to a novel method for calculating and drawing distribution of matching points of a capacity-increasing and grading design master machine of a gas compressor of a high-power ship gas turbine. The method can be widely applied to the processes of capacity increasing and grading matching calculation of the gas compressor and design index demonstration of the remodeling machine in the field of ship gas turbines, and the distribution of matching points of the prototype can be rapidly and accurately determined.
Drawings
Fig. 1 is a flowchart of a method for obtaining matching points of a master model machine for compressor capacity augmentation of a ship gas turbine according to a first embodiment;
FIG. 2 is a distribution diagram of a corresponding distribution line of matched points obtained on a general characteristic diagram of a master model machine by designing the flow rate and total pressure ratio of a single modified model machine;
FIG. 3 is a distribution diagram of distribution lines of three corresponding matching points obtained on a general characteristic diagram of a master model machine by designing flow and total pressure ratios of three modified models;
Detailed Description
The first embodiment is as follows: specifically describing the embodiment with reference to fig. 1, the method for obtaining the matching point of the female die machine for the compressor capacity increase of the ship gas turbine in the embodiment includes the following steps:
the method comprises the following steps of firstly, obtaining the inlet total temperature of the modified compressor according to the rotating speed of the female compressor, the inlet temperature of the female compressor and the set rotating speed of the modified compressor;
step two, obtaining the zero-level total pressure ratio of the modified compressor according to the total inlet temperature of the modified compressor, the inlet temperature of the female compressor and the variable efficiency of the zero level of the female compressor;
step three, obtaining the inlet total pressure of the modified compressor according to the zero-level total pressure ratio of the modified compressor and the inlet total pressure of the female compressor;
step four, obtaining the flow of the master compressor according to the total inlet pressure of the modified compressor, the total inlet pressure of the master compressor, the inlet temperature of the master compressor, the total inlet temperature of the modified compressor and the set flow of the modified compressor;
obtaining the total pressure ratio of the mother type compressor according to the zero-level total pressure ratio of the modified compressor and the set total pressure ratio of the modified compressor;
and step five, according to the flow rate of the female compressor and the total pressure ratio of the female compressor, drawing the flow rate of the female compressor and the total pressure ratio of the female compressor on a general characteristic diagram of the female compressor to serve as two matching points on the female compressor, connecting the two matching points to obtain a straight line, and performing capacity increasing and grading on the female compressor according to the straight line.
In the embodiment, according to the original parameters of the master compressor, the flow and total pressure ratio of the master compressor are obtained by combining the set flow and total pressure ratio of the retrofit compressor, the obtained flow and total pressure ratio of the master compressor is drawn on a general characteristic diagram of the master compressor to serve as two matching points on the master compressor, the two matching points are connected to obtain a straight line, all available matching points meeting the design parameters (pressure ratio and flow) of the retrofit compressor are located on the straight line and the extension line of the straight line, and the matching point of one master compressor corresponds to the design rotating speed of one retrofit compressor.
And (3) reselecting the design pressure ratio and flow rate of a plurality of modified compressors, calculating to obtain a plurality of straight lines, wherein each straight line corresponds to the design pressure ratio and flow rate of one modified compressor, and determining the optimal matching point of the master model machine and the design index of the modified compressor.
In the embodiment, firstly, a master model machine characteristic diagram is shown in fig. 2, the flow rate 123kg/s and the pressure ratio 6.65 of the modified compressor are selected as targets, the design rotation speed 7400rpm and 7600rpm of the modified compressor are selected as target rotation speeds, iterative calculation is carried out according to the steps from one step to the fourth step, the matching points of the master model compressor are determined as shown by two black points in fig. 2, the parameters of the iteratively calculated matching points are shown in table 1, all points on the connecting line of the two black points and the extending line thereof are the matching points of the design targets (the flow rate 123kg/s and the pressure ratio 6.65) of the modified compressor, and the design rotation speed of the modified compressor at each matching point is different. By matching the point distribution line and calculating the total efficiency of the remodeled compressor, the inherited expected operating point of the master model machine and the performance of the remodeled compressor can be directly seen.
Then, the design targets (flow rate and pressure ratio) of the modification machine are changed, and the calculation steps are repeated, so that a series of straight lines can be obtained, as shown in fig. 3, wherein each straight line corresponds to one design flow rate and pressure ratio.
Finally, according to a series of linear clusters, the performance of the design point of the remodeling machine can be rapidly analyzed according to the theoretical matching point of the master machine, and the optimal design parameter is determined.
Table 1 results of matching calculations for two design objectives in fig. 1
Figure BDA0002315540380000041
Figure BDA0002315540380000051
The total efficiency of the modified compressor can be calculated according to a formula 6
Figure BDA0002315540380000052
Expressed as:
Figure BDA0002315540380000053
in the formula (I), the compound is shown in the specification,
Figure BDA0002315540380000054
in order to improve the overall efficiency of the compressor,
Figure BDA0002315540380000055
expressed as the zero-level isentropic efficiency of the retrofit compressor,
Figure BDA0002315540380000056
the second embodiment is as follows: the embodiment further describes a method for obtaining a matching point of a female die machine for capacity increase of a gas compressor of a ship gas turbine in the first embodiment
Figure BDA0002315540380000057
Expressed as:
Figure BDA0002315540380000058
in the formula (I), the compound is shown in the specification,
Figure BDA0002315540380000059
inlet temperature, n, of the compressor of the female type φ For a set retrofit compressor speed, n m Speed of compressor。
The third concrete implementation mode: in the second step, the zero-order total pressure ratio of the modified compressor is obtained by performing the first step of the second step of the
Figure BDA00023155403800000510
Expressed as:
Figure BDA0002315540380000061
wherein k is the adiabatic exponent, η n Is the variable efficiency of the zero level of the female compressor.
The fourth concrete implementation mode: in the third embodiment, the method for obtaining the matching point of the female die machine for the capacity increase of the gas compressor of the ship gas turbine is further described
Figure BDA0002315540380000062
Expressed as:
Figure BDA0002315540380000063
in the formula (I), the compound is shown in the specification,
Figure BDA0002315540380000064
the total pressure of an inlet of the female compressor is obtained.
The fifth concrete implementation mode: the present embodiment further describes a method for obtaining a matching point of a female mold machine for volume increase of a gas compressor of a ship gas turbine according to the fourth embodiment, where in the fourth embodiment, the flow G of the female mold compressor is obtained m Expressed as:
Figure BDA0002315540380000065
in the formula, G φ To retrofit the compressor flow.
The sixth specific implementation mode is as follows: in the fifth embodiment, the method for obtaining the matching point of the female die machine for the capacity increase of the gas compressor of the ship gas turbine is further described, in the fourth embodiment, the total pressure ratio of the female die compressor is obtained
Figure BDA0002315540380000066
Expressed as:
Figure BDA0002315540380000067
in the formula (I), the compound is shown in the specification,
Figure BDA0002315540380000068
the total pressure ratio of the set modified compressor is adopted.

Claims (1)

1. The method for acquiring the matching point of the female die machine for the compressor capacity increase of the ship gas turbine is characterized by comprising the following steps of:
the method comprises the following steps of firstly, obtaining the inlet total temperature of the modified compressor according to the rotating speed of the female compressor, the inlet temperature of the female compressor and the set rotating speed of the modified compressor;
step two, obtaining the zero-level total pressure ratio of the modified compressor according to the total inlet temperature of the modified compressor, the inlet temperature of the female compressor and the variable efficiency of the zero level of the female compressor;
step three, obtaining the inlet total pressure of the modified compressor according to the zero-level total pressure ratio of the modified compressor and the inlet total pressure of the female compressor;
step four, obtaining the flow of the master compressor according to the total inlet pressure of the modified compressor, the total inlet pressure of the master compressor, the inlet temperature of the master compressor, the total inlet temperature of the modified compressor and the set flow of the modified compressor;
obtaining the total pressure ratio of the mother type compressor according to the zero-level total pressure ratio of the modified compressor and the set total pressure ratio of the modified compressor;
step five, according to the flow rate of the female compressor and the total pressure ratio of the female compressor, the flow rate of the female compressor and the total pressure ratio of the female compressor are drawn on a general characteristic diagram of the female compressor to serve as two matching points on the female compressor, the two matching points are connected to obtain a straight line, and the female compressor is subjected to capacity increasing and stage increasing according to the straight line;
in the first step, the total inlet temperature of the modified compressor
Figure FDA0003649831190000011
Expressed as:
Figure FDA0003649831190000012
in the formula (I), the compound is shown in the specification,
Figure FDA0003649831190000013
inlet temperature, n, of the compressor of the female type φ For a set retrofit compressor speed, n m The rotating speed of the female compressor;
in the second step, the zero-level total pressure ratio of the modified compressor
Figure FDA0003649831190000014
Expressed as:
Figure FDA0003649831190000015
wherein k is the adiabatic exponent, eta n The variable efficiency of the zero level of the mother type compressor is obtained;
in the third step, the total pressure of the inlet of the modified compressor
Figure FDA0003649831190000016
Expressed as:
Figure FDA0003649831190000021
in the formula (I), the compound is shown in the specification,
Figure FDA0003649831190000022
the total pressure of an inlet of a female compressor is measured;
in the fourth step, the flow G of the female compressor m Expressed as:
Figure FDA0003649831190000023
in the formula, G φ To retrofit the flow of the compressor;
in the fourth step, the total pressure ratio of the mother type compressor
Figure FDA0003649831190000024
Expressed as:
Figure FDA0003649831190000025
in the formula (I), the compound is shown in the specification,
Figure FDA0003649831190000026
the total pressure ratio of the set modified compressor is adopted.
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CN102121566A (en) * 2010-01-11 2011-07-13 李林 Method and equipment for processing water vapor before use
CN108661801A (en) * 2018-07-04 2018-10-16 崔荣繁 A kind of remodeling heavy duty gas turbine

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KR20140142737A (en) * 2012-04-02 2014-12-12 파워페이즈 엘엘씨 Compressed air injection system method and apparatus for gas turbine engines
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CN102121566A (en) * 2010-01-11 2011-07-13 李林 Method and equipment for processing water vapor before use
CN108661801A (en) * 2018-07-04 2018-10-16 崔荣繁 A kind of remodeling heavy duty gas turbine

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