CN115203962A - Method and device for simulating parameters of cooling air system of single-rotor gas turbine engine - Google Patents
Method and device for simulating parameters of cooling air system of single-rotor gas turbine engine Download PDFInfo
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Abstract
The application discloses a method and a device for simulating cooling air system parameters of a single-rotor gas turbine engine, wherein the method for simulating the cooling air system parameters of the single-rotor gas turbine engine innovatively utilizes actual measurement data of an engine complete machine test, characteristic data of combustion chamber components and characteristic data of turbine components, iterative computation is carried out through a gas turbine engine gas compressor, a combustion chamber and turbine component variable heat computing method and a single-rotor gas turbine engine common working condition, a final computing result obtained by the method is closer to a real working condition, the correction of the overall performance scheme of the single-rotor gas turbine engine can be effectively supported to be complete, the research and development efficiency of the single-rotor gas turbine engine can be improved, and the economic and time losses caused by the iteration of the overall performance scheme of the single-rotor gas turbine engine can be reduced. The method can also provide method support for researching the influence of the process parameter change measured by the complete machine test on the single-rotor gas turbine engine cooling air system parameters.
Description
Technical Field
The application relates to the technical field of turbine engines, in particular to a parameter simulation method and device for a cooling air system of a single-rotor gas turbine engine.
Background
In the calculation of the overall performance of the gas turbine engine, whether the calculation is carried out at a design point or a non-design point, cooling air system parameters (mainly the cooling air amount and the cooling air distribution ratio) must be determined firstly, so that the accuracy of the cooling air system parameters directly influences the rationality and the accuracy of the calculation of the overall performance of the engine, particularly, the cooling air system parameters of an engine with high thermodynamic cycle parameters influence the calculation of the overall performance of the engine far beyond that of an engine with low thermodynamic cycle parameters due to the fact that the proportion of the cooling air amount to the core flow can reach 25%. At present, the cooling air parameters of the gas turbine engine are obtained through iterative calculation of multi-wheel overall performance, components and an air system, and the actual working conditions of the cooling air system of the gas turbine engine cannot be truly reflected due to the lack of support of actual measurement data of a complete machine test. In addition, due to the complexity of the cooling air system of the gas turbine engine, it is not possible to directly measure the cooling air amount and the cooling air distribution ratio in a complete machine test, that is, it is not possible to directly verify whether the cooling air amount and the cooling air distribution ratio in the overall performance scheme are reasonable and accurate through the test.
Disclosure of Invention
The method aims to solve the technical problems that the existing method for calculating the parameters of the cooling air system of the gas turbine engine needs to be obtained through iterative calculation of multiple rounds of overall performance, components and the air system, and the calculation result cannot truly reflect the real working condition of the cooling air system of the gas turbine engine.
The technical scheme adopted by the application is as follows:
a parameter simulation method for a cooling air system of a single-rotor gas turbine engine comprises the following steps:
s1, obtaining complete machine test measurement parameters of a single-rotor gas turbine engine, and obtaining characteristics of combustion chamber parts and characteristics of turbine parts;
s2, calculating to obtain total enthalpy of an inlet of the compressor, total enthalpy of an outlet of the compressor, a pressurization ratio of the compressor, efficiency of the compressor and power of the compressor by a compressor component heat-transfer ratio calculation method based on the obtained measurement parameters of the whole machine test in the step S1;
s3, selecting the total cooling air quantity of the engine and the cooling air quantity of the guide vane of the gas turbine as iteration variables, and giving initial values of iterative calculation;
s4, obtaining cooling air quantity of a gas turbine movable blade, total cooling air enthalpy of the engine, total cooling air enthalpy of the gas turbine guide blade, total cooling air enthalpy of the gas turbine movable blade, distribution ratio of each cooling air in the total cooling air, total pressure, total temperature, total enthalpy, air physical flow and air conversion flow at an inlet of a combustion chamber based on the known complete machine test measurement parameters in the step S1 and the given total cooling air quantity of the engine and the given cooling air quantity of the gas turbine guide blade in the step S3;
s5, calculating to obtain total pressure, total temperature, total enthalpy, gas flow and gas-oil ratio at the outlet of the combustion chamber by a combustion chamber part variable specific heat calculation method based on the known complete machine test measurement parameters and the characteristics of the combustion chamber part in the step S1 and the total pressure, the total temperature, the total enthalpy, the physical air flow and the converted air flow at the inlet of the combustion chamber obtained in the step S4;
s6, calculating to obtain a gas turbine conversion rotating speed, a total pressure at an inlet of a gas turbine movable blade, a total temperature, a total enthalpy, a gas physical flow, a gas conversion flow and a gas-oil-gas ratio based on the known complete machine test measurement parameters in the step S1, the gas turbine guide blade cooling air amount obtained in the step S3, the total gas turbine guide blade cooling air enthalpy obtained in the step S4 and the total pressure, the total temperature, the total enthalpy, the gas flow and the gas-oil ratio at the outlet of the combustion chamber obtained in the step S5;
s7, obtaining the converted rotating speed of the gas turbine, the total pressure, the total temperature, the total enthalpy, the physical gas flow, the converted gas flow and the gas-oil-gas ratio at the inlet of the movable blade of the gas turbine based on the known characteristics of the turbine part in the step S1 and the step S6, and calculating the power of the gas turbine, the converted gas flow required by the turbine part and the total pressure, the total temperature, the total enthalpy, the gas flow and the gas-oil-gas ratio at the outlet of the gas turbine by using a turbine part heat conversion ratio calculation method;
and S8, according to the common working condition of the single-rotor gas turbine engine, comparing whether the sum of the overall test measurement parameters known in the step S1 and the compressor power obtained in the step S2 is balanced with the gas turbine power obtained in the step S7, comparing whether the converted flow of the gas at the inlet of the gas turbine movable blade obtained in the step S6 is balanced with the converted flow required by the turbine part obtained in the step S7, and if the calculated flow is not balanced, returning to the step S3 to modify the total cooling air quantity of the engine and the cooling air quantity of the gas turbine guide vane to continuously iterate until the calculated flow is balanced so as to obtain a final parameter simulation result of the cooling air system of the single-rotor gas turbine engine.
Further, in step S1, the parameters measured in the whole machine test include physical air flow at the inlet of the engine, total pressure at the inlet of the compressor, total temperature at the inlet of the compressor, total pressure at the outlet of the compressor, total temperature at the outlet of the compressor, fuel flow, physical rotation speed of the rotor of the engine, and work extracted by accessories of the fuel generator.
Further, the step S2 specifically includes the steps of:
and calculating to obtain the total enthalpy of the inlet of the compressor, the total enthalpy of the outlet of the compressor, the pressurization ratio of the compressor, the efficiency of the compressor and the work of the compressor by a compressor component heat-ratio calculation method based on the conditions of the physical flow of the air at the inlet of the engine, the total pressure of the inlet of the compressor, the total temperature of the inlet of the compressor, the total pressure of the outlet of the compressor and the total temperature of the outlet of the compressor, which are obtained in the step S1.
Further, the step S4 specifically includes the steps of:
and obtaining the cooling air quantity of the gas turbine movable blades, the total enthalpy of the engine cooling air, the total enthalpy of the gas turbine guide blade cooling air, the total enthalpy of the gas turbine movable blade cooling air, the distribution ratio of each cooling air in the total cooling air, and the total pressure, the total temperature, the total enthalpy, the air physical flow and the air conversion flow at the inlet of the combustion chamber based on the known physical flow of the engine inlet air, the total compressor outlet pressure and the total compressor outlet temperature of the compressor and the given total engine cooling air quantity and the gas turbine guide blade cooling air quantity in the step S3.
Further, the step S5 specifically includes the step
And calculating the total pressure, the total temperature, the total enthalpy, the gas flow and the gas-oil ratio at the outlet of the combustion chamber by using a combustion chamber part variable specific heat calculation method based on the known fuel oil flow and the known combustion chamber part characteristics in the step S1 and the total pressure, the total temperature, the total enthalpy, the air physical flow and the air conversion flow at the inlet of the combustion chamber obtained in the step S4.
Further, the step S6 specifically includes the steps of:
and calculating to obtain the gas turbine conversion rotation speed, the total pressure at the inlet of the gas turbine movable blade, the total temperature, the total enthalpy, the gas physical flow, the gas conversion flow and the gas oil-gas ratio based on the known engine rotor physical rotation speed in the step S1, the gas turbine guide blade cooling air amount obtained in the step S3, the total gas turbine guide blade cooling air enthalpy obtained in the step S4 and the total pressure, the total temperature, the total enthalpy, the gas flow and the gas oil-gas ratio at the outlet of the combustion chamber obtained in the step S5.
Further, the step S8 specifically includes the steps of:
and according to the common working conditions of the single-rotor gas turbine engine, comparing whether the sum of the gas generator accessory extraction work known in the step S1 and the compressor work obtained in the step S2 is balanced with the gas turbine work obtained in the step S7, comparing whether the gas turbine rotor blade inlet gas converted flow obtained in the step S6 is balanced with the gas converted flow required by the turbine part obtained in the step S7, and if the gas turbine rotor blade inlet gas converted flow is unbalanced, returning to the step S3 to modify the total cooling air amount of the engine and the cooling air amount of the gas turbine guide vane to continuously iterate until the gas turbine rotor blade inlet gas converted flow is balanced, so that a final cooling air system parameter simulation result of the single-rotor gas turbine engine is obtained.
The embodiment of another aspect of the present application further provides a parameter simulation apparatus for a cooling air system of a gas turbine with a single rotor, including:
the complete machine parameter acquisition module is used for acquiring complete machine test measurement parameters of the single-rotor gas turbine engine and acquiring characteristics of combustion chamber components and characteristics of turbine components;
the compressor parameter technical module is used for calculating to obtain total enthalpy of an inlet of the compressor, total enthalpy of an outlet of the compressor, a pressurization ratio of the compressor, efficiency of the compressor and a compressor function through a compressor component heat-transfer ratio calculation method based on the whole machine test measurement parameters obtained in the step S1;
the iterative variable setting module is used for selecting the total cooling air quantity of the engine and the cooling air quantity of the guide vane of the gas turbine as iterative variables and endowing the iterative variables with initial values for iterative calculation;
a cooling air and combustion chamber outlet parameter calculation module, configured to obtain a gas turbine blade cooling air amount, a total cooling air enthalpy of the engine, a total cooling air enthalpy of the gas turbine guide vane, a total cooling air enthalpy of the gas turbine blade, a distribution ratio of each cooling air in the total cooling air, and a total pressure, a total temperature, a total enthalpy, a physical air flow rate, and an air conversion flow rate at an inlet of the combustion chamber, based on the complete machine test measurement parameter known in step S1 and the total cooling air amount and the gas turbine guide vane cooling air amount given in step S3;
the combustion chamber inlet and outlet parameter technical module is used for calculating and obtaining the total pressure, the total temperature, the total enthalpy, the gas flow and the gas-oil ratio at the outlet of the combustion chamber through a combustion chamber part heat transfer ratio calculation method based on the known complete machine test measurement parameters and the characteristics of the combustion chamber parts in the step S1 and the total pressure, the total temperature, the total enthalpy, the physical air flow and the converted air flow at the inlet of the combustion chamber obtained in the step S4;
the gas turbine movable blade parameter calculation module is used for calculating and obtaining the gas turbine conversion rotating speed, the total pressure, the total temperature, the total enthalpy, the gas physical flow, the gas conversion flow and the gas oil-gas ratio at the inlet of the gas turbine movable blade based on the known complete machine test measurement parameters obtained in the step S1, the gas turbine guide blade cooling air amount obtained in the step S3, the total gas turbine guide blade cooling air enthalpy obtained in the step S4 and the total pressure, the total temperature, the total enthalpy, the gas flow and the gas oil-gas ratio at the outlet of the combustion chamber obtained in the step S5;
the gas conversion flow and gas turbine outlet parameter calculation module is used for obtaining the gas turbine conversion rotating speed, the total pressure, the total temperature, the total enthalpy, the gas physical flow, the gas conversion flow and the gas-oil-gas ratio at the inlet of the gas turbine movable blade based on the known turbine part characteristics obtained in the step S1 and the step S6, and calculating the gas turbine work, the gas conversion flow required by the turbine part and the total pressure, the total temperature, the total enthalpy, the gas flow and the gas-oil-gas ratio at the outlet of the gas turbine through a turbine part heat conversion calculation method;
and the parameter balance judging and iterating module is used for comparing whether the sum of the overall test measurement parameters known in the step S1 and the compressor power obtained in the step S2 is balanced with the gas turbine power obtained in the step S7 or not according to the common working conditions of the single-rotor gas turbine engine, comparing whether the converted flow of the gas at the inlet of the gas turbine movable blade obtained in the step S6 is balanced with the converted flow required by the turbine part obtained in the step S7 or not, and if the converted flow is not balanced, returning to the step S3 to modify the total cooling air quantity of the engine and the cooling air quantity of the gas turbine guide blade to continue iterating until the converted flow is balanced so as to obtain a final parameter simulation result of the cooling air system of the single-rotor gas turbine engine.
In another aspect, an embodiment of the present application further provides an electronic device, including a memory, a processor and a computer program stored in the memory and executable on the processor, wherein the processor executes the program to implement the steps of the method for simulating the parameters of the cooling air system of the single-rotor gas turbine engine.
In another aspect, the present invention further provides a storage medium, which includes a stored program, and when the program runs, the apparatus on which the storage medium is located is controlled to execute the steps of the method for simulating the parameters of the cooling air system of the single-rotor gas turbine engine.
Compared with the prior art, the method has the following beneficial effects:
the parameter simulation method for the cooling air system of the single-rotor gas turbine engine innovatively utilizes the actual measurement data of the whole engine test, the characteristic data of combustion chamber components and the characteristic data of turbine components, and carries out iterative computation through the common working condition of a gas compressor, a combustion chamber and a turbine component variable specific heat computation method of the gas turbine engine and the single-rotor gas turbine engine. The method can also provide method support for researching the influence of the process parameter change measured by the complete machine test on the single-rotor gas turbine engine cooling air system parameters.
In addition to the objects, features and advantages described above, other objects, features and advantages will be apparent from the present application. The present application will now be described in further detail with reference to the accompanying drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, are included to provide a further understanding of the application, and the description of the exemplary embodiments of the application are intended to be illustrative of the application and are not intended to limit the application. In the drawings:
FIG. 1 is a flow chart of a method for simulating cooling air system parameters of a single spool gas turbine engine in accordance with a preferred embodiment of the present application.
FIG. 2 is a schematic flow chart of a method for simulating cooling air system parameters of a single rotor gas turbine engine according to another preferred embodiment of the present application.
FIG. 3 is a schematic diagram of a single spool gas turbine engine cooling air system parameter simulation device module in accordance with a preferred embodiment of the present application.
Fig. 4 is a schematic block diagram of an electronic device entity of the preferred embodiment of the present application.
Fig. 5 is an internal structural view of a computer device according to a preferred embodiment of the present application.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
Referring to FIG. 1, a preferred embodiment of the present application provides a method for single spool gas turbine engine cooling air system parameter simulation comprising the steps of:
s1, obtaining complete machine test measurement parameters of a single-rotor gas turbine engine, and obtaining characteristics of combustion chamber parts and characteristics of turbine parts;
s2, calculating to obtain total enthalpy of an inlet of the compressor, total enthalpy of an outlet of the compressor, a pressurization ratio of the compressor, efficiency of the compressor and power of the compressor by a compressor component heat-transfer ratio calculation method based on the obtained measurement parameters of the whole machine test in the step S1;
s3, selecting the total cooling air quantity of the engine and the cooling air quantity of the guide vane of the gas turbine as iteration variables, and giving initial values of iterative calculation;
s4, obtaining cooling air quantity of a gas turbine movable blade, total cooling air enthalpy of the engine, total cooling air enthalpy of the gas turbine guide blade, total cooling air enthalpy of the gas turbine movable blade, distribution ratio of each cooling air in the total cooling air, total pressure, total temperature, total enthalpy, air physical flow and air conversion flow at an inlet of a combustion chamber based on the known complete machine test measurement parameters in the step S1 and the given total cooling air quantity of the engine and the given cooling air quantity of the gas turbine guide blade in the step S3;
s5, calculating to obtain total pressure, total temperature, total enthalpy, gas flow and gas-oil ratio at the outlet of the combustion chamber by a combustion chamber part variable specific heat calculation method based on the known complete machine test measurement parameters and the characteristics of the combustion chamber part in the step S1 and the total pressure, the total temperature, the total enthalpy, the physical air flow and the converted air flow at the inlet of the combustion chamber obtained in the step S4;
s6, calculating to obtain a gas turbine conversion rotating speed, a total pressure, a total temperature, a total enthalpy, a gas physical flow, a gas conversion flow and a gas oil-gas ratio at the inlet of a gas turbine movable blade based on the known complete machine test measurement parameters in the step S1, the gas turbine guide blade cooling air amount obtained in the step S3, the total gas turbine guide blade cooling air enthalpy obtained in the step S4 and the total pressure, the total temperature, the total enthalpy, the gas flow and the gas oil-gas ratio at the outlet of the combustion chamber obtained in the step S5;
s7, obtaining the converted rotating speed of the gas turbine, the total pressure, the total temperature, the total enthalpy, the physical gas flow, the converted gas flow and the gas-oil-gas ratio at the inlet of the movable blade of the gas turbine based on the known characteristics of the turbine part in the step S1 and the step S6, and calculating the power of the gas turbine, the converted gas flow required by the turbine part and the total pressure, the total temperature, the total enthalpy, the gas flow and the gas-oil-gas ratio at the outlet of the gas turbine by using a turbine part heat conversion ratio calculation method;
s8, according to the common working conditions of the single-rotor gas turbine engine, comparing whether the sum of the overall machine test measurement parameters obtained in the step S1 and the compressor power obtained in the step S2 is balanced with the gas turbine power obtained in the step S7, comparing whether the converted flow of the gas at the inlet of the gas turbine movable blade obtained in the step S6 is balanced with the converted flow required by the turbine part obtained in the step S7, and if the sum is not balanced, returning to the step S3 to modify the total cooling air quantity of the engine and the cooling air quantity of the gas turbine guide vane to continuously iterate until the sum is balanced, so that a final parameter simulation result of the cooling air system of the single-rotor gas turbine engine is obtained.
The embodiment provides a parameter simulation method for a cooling air system of a single-rotor gas turbine engine, which innovatively utilizes actual measurement data of an engine complete machine test, characteristic data of combustion chamber components and characteristic data of turbine components, and carries out iterative computation through a common working condition of a gas compressor, a combustion chamber and a turbine component heat-transfer ratio computing method of the gas turbine engine and the single-rotor gas turbine engine. The method can also provide method support for researching the influence of the process parameter change measured by the complete machine test on the parameters of the cooling air system of the single-rotor gas turbine engine.
Specifically, in step S1, the parameters measured in the complete machine test include physical air flow at an inlet of the engine, total pressure at an inlet of the compressor, total temperature at an inlet of the compressor, total pressure at an outlet of the compressor, total temperature at an outlet of the compressor, fuel flow, physical rotating speed of a rotor of the engine, and work extracted by accessories of the fuel generator.
Preferably, the step S2 specifically includes the steps of:
and calculating to obtain total enthalpy of the inlet of the compressor, total enthalpy of the outlet of the compressor, supercharging ratio of the compressor, efficiency of the compressor and power of the compressor by a compressor component heat-transfer ratio calculation method based on the conditions of the physical flow of the air at the inlet of the engine, the total pressure of the inlet of the compressor, the total temperature of the inlet of the compressor, the total pressure of the outlet of the compressor and the total temperature of the outlet of the compressor obtained in the step S1.
Preferably, the step S4 specifically includes the steps of:
and obtaining the cooling air quantity of the gas turbine blades, the total enthalpy of the cooling air of the engine, the total enthalpy of the cooling air of the gas turbine blades, the distribution ratio of each cooling air in the total cooling air, and the total pressure, the total temperature, the total enthalpy, the air physical flow and the air conversion flow at the inlet of the combustion chamber based on the known physical flow of the air at the inlet of the engine, the total pressure and the total temperature at the outlet of the compressor, the given total cooling air quantity of the engine and the cooling air quantity of the gas turbine blades in the step S3.
Preferably, the step S5 specifically includes the step
And calculating the total pressure, the total temperature, the total enthalpy, the gas flow and the gas-oil ratio at the outlet of the combustion chamber by using a combustion chamber part variable specific heat calculation method based on the known fuel oil flow and the known combustion chamber part characteristics in the step S1 and the total pressure, the total temperature, the total enthalpy, the air physical flow and the air conversion flow at the inlet of the combustion chamber obtained in the step S4.
Preferably, the step S6 specifically includes the steps of:
and calculating to obtain the gas turbine conversion rotation speed, the total pressure at the inlet of the gas turbine movable blade, the total temperature, the total enthalpy, the gas physical flow, the gas conversion flow and the gas oil-gas ratio based on the known engine rotor physical rotation speed in the step S1, the gas turbine guide blade cooling air amount obtained in the step S3, the total gas turbine guide blade cooling air enthalpy obtained in the step S4 and the total pressure, the total temperature, the total enthalpy, the gas flow and the gas oil-gas ratio at the outlet of the combustion chamber obtained in the step S5.
Preferably, the step S8 specifically includes the steps of:
and according to the common working conditions of the single-rotor gas turbine engine, comparing whether the sum of the gas generator accessory extraction work known in the step S1 and the compressor work obtained in the step S2 is balanced with the gas turbine work obtained in the step S7, comparing whether the gas turbine rotor blade inlet gas converted flow obtained in the step S6 is balanced with the gas converted flow required by the turbine part obtained in the step S7, and if the gas turbine rotor blade inlet gas converted flow is unbalanced, returning to the step S3 to modify the total cooling air amount of the engine and the cooling air amount of the gas turbine guide vane to continuously iterate until the gas turbine rotor blade inlet gas converted flow is balanced, so that a final cooling air system parameter simulation result of the single-rotor gas turbine engine is obtained.
The gas turbine engine compressor, combustor, and turbine component heat variation ratio calculation methods mentioned in this application are known and accepted techniques in the art and are not described herein in detail.
The present application is applicable to a single spool gas turbine engine of the type shown in FIG. 1, comprising: turbojet engines for single rotor gas turbine generators, and turboshaft/turboprop engines for single rotor gas turbine generators. The parameter simulation method is based on data measured by a complete machine test of the single-rotor gas turbine engine, characteristic data of combustion chamber parts and characteristic data of turbine parts, adopts a calculation method of the heat-transfer ratio of a gas compressor, a combustion chamber and a turbine part of the gas turbine engine, and obtains parameters of the cooling air system of the single-rotor gas turbine engine which are closer to the real working condition through iterative calculation according to the common working condition of the single-rotor gas turbine engine. FIG. 2 is a flow chart of a method for simulating cooling air system parameters of a single rotor gas turbine engine according to another preferred embodiment of the present application.
As shown in FIG. 3, another embodiment of the present application further provides a parameter simulation apparatus for a cooling air system of a single-rotor gas turbine engine, including:
the complete machine parameter acquisition module is used for acquiring complete machine test measurement parameters of the single-rotor gas turbine engine and acquiring characteristics of combustion chamber components and characteristics of turbine components;
the compressor parameter technical module is used for calculating to obtain total enthalpy of an inlet of the compressor, total enthalpy of an outlet of the compressor, a pressurization ratio of the compressor, efficiency of the compressor and a compressor function through a compressor component heat-transfer ratio calculation method based on the whole machine test measurement parameters obtained in the step S1;
the iterative variable setting module is used for selecting the total cooling air quantity of the engine and the cooling air quantity of the guide vane of the gas turbine as iterative variables and endowing the iterative variables with initial values for iterative calculation;
a cooling air and combustion chamber outlet parameter calculation module, configured to obtain a gas turbine blade cooling air amount, a total cooling air enthalpy of the engine, a total cooling air enthalpy of the gas turbine guide vane, a total cooling air enthalpy of the gas turbine blade, a distribution ratio of each cooling air in the total cooling air, and a total pressure, a total temperature, a total enthalpy, a physical air flow rate, and an air conversion flow rate at an inlet of the combustion chamber, based on the complete machine test measurement parameter known in step S1 and the total cooling air amount and the gas turbine guide vane cooling air amount given in step S3;
a combustion chamber inlet and outlet parameter technology module which is used for calculating to obtain the total pressure, the total temperature, the total enthalpy, the gas flow and the gas-oil ratio at the outlet of the combustion chamber through a combustion chamber component heat ratio calculation method based on the known complete machine test measurement parameters in the step S1, the characteristics of combustion chamber components and the total pressure, the total temperature, the total enthalpy, the physical air flow and the converted air flow at the inlet of the combustion chamber obtained in the step S4;
the gas turbine movable blade parameter calculation module is used for calculating and obtaining the gas turbine conversion rotating speed, the total pressure, the total temperature, the total enthalpy, the gas physical flow, the gas conversion flow and the gas oil-gas ratio at the inlet of the gas turbine movable blade based on the known complete machine test measurement parameters obtained in the step S1, the gas turbine guide blade cooling air amount obtained in the step S3, the total gas turbine guide blade cooling air enthalpy obtained in the step S4 and the total pressure, the total temperature, the total enthalpy, the gas flow and the gas oil-gas ratio at the outlet of the combustion chamber obtained in the step S5;
the gas conversion flow and gas turbine outlet parameter calculation module is used for obtaining the gas turbine conversion rotating speed, the total pressure, the total temperature, the total enthalpy, the gas physical flow, the gas conversion flow and the gas-oil-gas ratio at the inlet of the gas turbine movable blade based on the known turbine part characteristics obtained in the step S1 and the step S6, and calculating the gas turbine work, the gas conversion flow required by the turbine part and the total pressure, the total temperature, the total enthalpy, the gas flow and the gas-oil-gas ratio at the outlet of the gas turbine through a turbine part heat conversion calculation method;
and the parameter balance judging and iterating module is used for comparing whether the sum of the overall test measurement parameters known in the step S1 and the compressor power obtained in the step S2 is balanced with the gas turbine power obtained in the step S7 or not according to the common working conditions of the single-rotor gas turbine engine, comparing whether the converted flow of the gas at the inlet of the gas turbine movable blade obtained in the step S6 is balanced with the converted flow required by the turbine part obtained in the step S7 or not, and if the converted flow is not balanced, returning to the step S3 to modify the total cooling air quantity of the engine and the cooling air quantity of the gas turbine guide blade to continue iterating until the converted flow is balanced so as to obtain a final parameter simulation result of the cooling air system of the single-rotor gas turbine engine.
The various modules in the above-described apparatus may be implemented in whole or in part by software, hardware, and combinations thereof. The modules can be embedded in a hardware form or independent of a processor in the computer device, and can also be stored in a memory in the computer device in a software form, so that the processor can call and execute operations corresponding to the modules.
As shown in fig. 4, the preferred embodiment of the present application further provides an electronic device, which includes a memory, a processor and a computer program stored in the memory and executable on the processor, and the processor executes the computer program to implement the method for simulating cooling air system parameters of a single-rotor gas turbine engine in the above embodiments.
As shown in fig. 5, the preferred embodiment of the present application also provides a computer device, the internal structure of which can be as shown in fig. 5. The computer device includes a processor, a memory, and a network interface connected by a system bus. Wherein the processor of the computer device is configured to provide computing and control capabilities. The memory of the computer device comprises a nonvolatile storage medium and an internal memory. The non-volatile storage medium stores an operating system and a computer program. The internal memory provides an environment for the operation of an operating system and computer programs in the non-volatile storage medium. The network interface of the computer device is used for communicating with other external computer devices through network connection. The computer program is executed by a processor to implement the single spool gas turbine engine cooling air system parameter simulation method described above.
Those skilled in the art will appreciate that the architecture illustrated in FIG. 5 is merely a block diagram of some of the structures associated with the disclosed aspects and is not intended to limit the scope of the present disclosure, as some embodiments may include more or less devices than those illustrated, or some of the devices may be combined, or have a different arrangement of devices.
The preferred embodiments of the present application also provide a storage medium including a stored program which, when executed, controls an apparatus in which the storage medium is located to perform the steps of the single spool gas turbine engine cooling air system parameter simulation method.
It should be noted that the steps illustrated in the flowcharts of the figures may be performed in a computer system such as a set of computer-executable instructions and that, although a logical order is illustrated in the flowcharts, in some cases, the steps illustrated or described may be performed in an order different than presented herein.
The functions of the method of the present embodiment, if implemented in the form of software functional units and sold or used as independent products, may be stored in one or more storage media readable by a computing device. Based on such understanding, part of the technical solutions or portions of the embodiments contributing 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 computing device (which may be a personal computer, a server, a mobile computing device, a network device, or the like) to perform all or part of the steps of the methods described in the embodiments of the present application. And the aforementioned storage medium includes: a U-disk, a removable hard disk, a Read-Only Memory (ROM), a Random Access Memory (RAM), a magnetic disk or an optical disk, and other various media capable of storing program codes.
The above description is only a preferred embodiment of the present application and should not be taken as limiting the present application, and any modifications, equivalents, improvements and the like that are made within the spirit and principle of the present application should be included in the protection scope of the present application.
Claims (10)
1. A method for simulating parameters of a cooling air system of a single-rotor gas turbine engine is characterized by comprising the following steps:
s1, obtaining complete machine test measurement parameters of a single-rotor gas turbine engine, and obtaining characteristics of combustion chamber parts and characteristics of turbine parts;
s2, calculating to obtain total enthalpy of an inlet of the compressor, total enthalpy of an outlet of the compressor, a pressurization ratio of the compressor, efficiency of the compressor and work of the compressor by a compressor component heat-ratio calculation method based on the whole machine test measurement parameters obtained in the step S1;
s3, selecting the total cooling air quantity of the engine and the cooling air quantity of the guide vane of the gas turbine as iteration variables, and giving initial values of iterative calculation;
s4, obtaining cooling air quantity of a gas turbine movable blade, total cooling air enthalpy of the engine, total cooling air enthalpy of a gas turbine guide blade, total cooling air enthalpy of the gas turbine movable blade, distribution ratio of each cooling air in the total cooling air, total pressure, total temperature, total enthalpy, air physical flow and air conversion flow at an inlet of a combustion chamber based on the known complete machine test measurement parameters in the step S1 and the given total cooling air quantity of the engine and the given cooling air quantity of the gas turbine guide blade in the step S3;
s5, calculating to obtain total pressure, total temperature, total enthalpy, gas flow and gas-oil ratio at the outlet of the combustion chamber by a combustion chamber part variable specific heat calculation method based on the known complete machine test measurement parameters and the characteristics of the combustion chamber part in the step S1 and the total pressure, the total temperature, the total enthalpy, the physical air flow and the converted air flow at the inlet of the combustion chamber obtained in the step S4;
s6, calculating to obtain a gas turbine conversion rotating speed, a total pressure, a total temperature, a total enthalpy, a gas physical flow, a gas conversion flow and a gas oil-gas ratio at the inlet of a gas turbine movable blade based on the known complete machine test measurement parameters in the step S1, the gas turbine guide blade cooling air amount obtained in the step S3, the total gas turbine guide blade cooling air enthalpy obtained in the step S4 and the total pressure, the total temperature, the total enthalpy, the gas flow and the gas oil-gas ratio at the outlet of the combustion chamber obtained in the step S5;
s7, obtaining the converted rotating speed of the gas turbine, the total pressure, the total temperature, the total enthalpy, the physical gas flow, the converted gas flow and the gas-oil-gas ratio at the inlet of the movable blade of the gas turbine based on the known characteristics of the turbine part in the step S1 and the step S6, and calculating the power of the gas turbine, the converted gas flow required by the turbine part and the total pressure, the total temperature, the total enthalpy, the gas flow and the gas-oil-gas ratio at the outlet of the gas turbine by using a turbine part heat conversion ratio calculation method;
and S8, according to the common working condition of the single-rotor gas turbine engine, comparing whether the sum of the overall test measurement parameters known in the step S1 and the compressor power obtained in the step S2 is balanced with the gas turbine power obtained in the step S7, comparing whether the converted flow of the gas at the inlet of the gas turbine movable blade obtained in the step S6 is balanced with the converted flow required by the turbine part obtained in the step S7, and if the calculated flow is not balanced, returning to the step S3 to modify the total cooling air quantity of the engine and the cooling air quantity of the gas turbine guide vane to continuously iterate until the calculated flow is balanced so as to obtain a final parameter simulation result of the cooling air system of the single-rotor gas turbine engine.
2. The method for simulating parameters of a cooling air system of a single-rotor gas turbine engine as recited in claim 1, wherein in step S1, the parameters measured in the complete machine test include physical flow rate of air at an inlet of the engine, total pressure at an inlet of the compressor, total temperature at an inlet of the compressor, total pressure at an outlet of the compressor, total temperature at an outlet of the compressor, flow rate of fuel, physical rotation speed of a rotor of the engine, and work extracted by accessories of the gas generator.
3. The single spool gas turbine engine cooling air system parameter simulation method of claim 1, wherein the step S2 specifically comprises the steps of:
and calculating to obtain total enthalpy of the inlet of the compressor, total enthalpy of the outlet of the compressor, supercharging ratio of the compressor, efficiency of the compressor and power of the compressor by a compressor component heat-transfer ratio calculation method based on the conditions of the physical flow of the air at the inlet of the engine, the total pressure of the inlet of the compressor, the total temperature of the inlet of the compressor, the total pressure of the outlet of the compressor and the total temperature of the outlet of the compressor obtained in the step S1.
4. The method for simulating parameters of a cooling air system of a gas turbine with a single rotor as claimed in claim 1, wherein the step S4 comprises the steps of:
and obtaining the cooling air quantity of the gas turbine blades, the total enthalpy of the cooling air of the engine, the total enthalpy of the cooling air of the gas turbine blades, the distribution ratio of each cooling air in the total cooling air, and the total pressure, the total temperature, the total enthalpy, the air physical flow and the air conversion flow at the inlet of the combustion chamber based on the known physical flow of the air at the inlet of the engine, the total pressure and the total temperature at the outlet of the compressor, the given total cooling air quantity of the engine and the cooling air quantity of the gas turbine blades in the step S3.
5. The method for single spool gas turbine engine cooling air system parameter simulation of claim 1, wherein said step S5 specifically includes the step of
And calculating the total pressure, the total temperature, the total enthalpy, the gas flow and the gas-oil ratio at the outlet of the combustion chamber by using a combustion chamber part variable specific heat calculation method based on the known fuel oil flow and the known combustion chamber part characteristics in the step S1 and the total pressure, the total temperature, the total enthalpy, the air physical flow and the air conversion flow at the inlet of the combustion chamber obtained in the step S4.
6. The single spool gas turbine engine cooling air system parameter simulation method of claim 1, wherein the step S6 specifically comprises the steps of:
and calculating to obtain the gas turbine conversion rotation speed, the total pressure at the inlet of the gas turbine movable blade, the total temperature, the total enthalpy, the gas physical flow, the gas conversion flow and the gas oil-gas ratio based on the known engine rotor physical rotation speed in the step S1, the gas turbine guide blade cooling air amount obtained in the step S3, the total gas turbine guide blade cooling air enthalpy obtained in the step S4 and the total pressure, the total temperature, the total enthalpy, the gas flow and the gas oil-gas ratio at the outlet of the combustion chamber obtained in the step S5.
7. The single spool gas turbine engine cooling air system parameter simulation method of claim 1, wherein the step S8 specifically comprises the steps of:
and according to the common working condition of the single-rotor gas turbine engine, comparing whether the known gas generator accessory extraction work obtained in the step S1 and the sum of the compressor work obtained in the step S2 are balanced with the gas turbine work obtained in the step S7, comparing whether the gas turbine movable blade inlet gas converted flow obtained in the step S6 is balanced with the gas converted flow required by the turbine part obtained in the step S7, and if the gas turbine movable blade inlet gas converted flow is unbalanced, returning to the step S3 to modify the total cooling air quantity of the engine and the cooling air quantity of the gas turbine guide vane to continuously iterate until the gas turbine movable blade inlet gas converted flow is balanced, so that the final cooling air system parameter simulation result of the single-rotor gas turbine engine is obtained.
8. A single spool gas turbine engine cooling air system parameter simulation apparatus, comprising:
the complete machine parameter acquisition module is used for acquiring complete machine test measurement parameters of the single-rotor gas turbine engine and acquiring characteristics of combustion chamber components and characteristics of turbine components;
the compressor parameter technical module is used for calculating to obtain total enthalpy of an inlet of the compressor, total enthalpy of an outlet of the compressor, a pressurization ratio of the compressor, efficiency of the compressor and a compressor function through a compressor component heat-transfer ratio calculation method based on the whole machine test measurement parameters obtained in the step S1;
the iterative variable setting module is used for selecting the total cooling air quantity of the engine and the cooling air quantity of the guide vane of the gas turbine as iterative variables and endowing the iterative variables with initial values for iterative calculation;
a cooling air and combustion chamber outlet parameter calculation module, configured to obtain a gas turbine blade cooling air amount, a total cooling air enthalpy of the engine, a total cooling air enthalpy of the gas turbine guide vane, a total cooling air enthalpy of the gas turbine blade, a distribution ratio of each cooling air in the total cooling air, and a total pressure, a total temperature, a total enthalpy, a physical air flow rate, and an air conversion flow rate at an inlet of the combustion chamber, based on the complete machine test measurement parameter known in step S1 and the total cooling air amount and the gas turbine guide vane cooling air amount given in step S3;
the combustion chamber inlet and outlet parameter technical module is used for calculating and obtaining the total pressure, the total temperature, the total enthalpy, the gas flow and the gas-oil ratio at the outlet of the combustion chamber through a combustion chamber part heat transfer ratio calculation method based on the known complete machine test measurement parameters and the characteristics of the combustion chamber parts in the step S1 and the total pressure, the total temperature, the total enthalpy, the physical air flow and the converted air flow at the inlet of the combustion chamber obtained in the step S4;
the gas turbine movable blade parameter calculation module is used for calculating and obtaining the gas turbine conversion rotating speed, the total pressure, the total temperature, the total enthalpy, the gas physical flow, the gas conversion flow and the gas oil-gas ratio at the inlet of the gas turbine movable blade based on the known complete machine test measurement parameters obtained in the step S1, the gas turbine guide blade cooling air amount obtained in the step S3, the total gas turbine guide blade cooling air enthalpy obtained in the step S4 and the total pressure, the total temperature, the total enthalpy, the gas flow and the gas oil-gas ratio at the outlet of the combustion chamber obtained in the step S5;
the gas conversion flow and gas turbine outlet parameter calculation module is used for obtaining a gas turbine conversion rotating speed, total pressure, total temperature, total enthalpy, gas physical flow, gas conversion flow and gas-oil-gas ratio at an inlet of a gas turbine movable blade based on the known turbine part characteristics in the step S1 and the step S6, and calculating gas turbine work, gas conversion flow required by the turbine part and the total pressure, total temperature, total enthalpy, gas flow and gas-oil-gas ratio at an outlet of the gas turbine by using a turbine part heat conversion ratio calculation method;
and the parameter balance judging and iterating module is used for comparing whether the sum of the overall test measurement parameters known in the step S1 and the compressor power obtained in the step S2 is balanced with the gas turbine power obtained in the step S7 or not according to the common working conditions of the single-rotor gas turbine engine, comparing whether the converted flow of the gas at the inlet of the gas turbine movable blade obtained in the step S6 is balanced with the converted flow required by the turbine part obtained in the step S7 or not, and if the converted flow is not balanced, returning to the step S3 to modify the total cooling air quantity of the engine and the cooling air quantity of the gas turbine guide blade to continue iterating until the converted flow is balanced so as to obtain a final parameter simulation result of the cooling air system of the single-rotor gas turbine engine.
9. An electronic device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, wherein the processor when executing the program performs the steps of the method for simulation of cooling air system parameters for a single spool gas turbine engine as set forth in any one of claims 1 to 7.
10. A storage medium comprising a stored program which, when executed, controls an apparatus in which the storage medium resides to perform the steps of the single spool gas turbine engine cooling air system parameter simulation method.
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| CN202210883977.7A CN115203962A (en) | 2022-07-26 | 2022-07-26 | Method and device for simulating parameters of cooling air system of single-rotor gas turbine engine |
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