Single-rotor Gas Turbine Engine Cooling Air System Parameter Simulation Method and Device

Abstract

The present application discloses a method and device for simulating parameters of a cooling air system of a single-rotor gas turbine engine. The method for simulating parameters of the cooling air system of the single-rotor gas turbine engine innovatively utilizes the measured data of the overall engine test, the characteristic data of the combustion chamber components, and the characteristic data of the turbine components. Through the variable specific heat calculation methods of the compressor, combustion chamber, and turbine components of the gas turbine engine and the common working conditions of the single-rotor gas turbine engine, iterative calculations are carried out. The final calculation results obtained by using this method are closer to the actual working conditions, can effectively support the modification and improvement of the overall performance scheme of the single-rotor gas turbine engine, improve the R & D efficiency of the single-rotor gas turbine engine, and reduce the economic and time losses caused by the iteration of the overall performance scheme of the single-rotor gas turbine engine. The present application can also provide method support for studying the influence of the change of the process parameters measured in the overall engine test on the parameters of the cooling air system of the single-rotor gas turbine engine.

Description

Technical Field

[0001] The present application relates to the technical field of turbine engines, and in particular, to a method and device for simulating parameters of a cooling air system of a single-rotor gas turbine engine. Background Art

[0002] In the overall performance calculation of a gas turbine engine, whether it is the design point calculation or the off-design point calculation, it is necessary to first determine the cooling air system parameters (mainly the cooling air quantity and the cooling air distribution ratio). Therefore, the accuracy of the cooling air system parameters directly affects the rationality and accuracy of the overall performance calculation of the engine. Especially for engines with high thermal cycle parameters, since the proportion of the cooling air quantity in the core flow can reach the order of 25%, the influence of the cooling air system parameters of the high thermal cycle parameter engine on the overall performance calculation of the engine far exceeds that of the low thermal cycle parameter engine. At present, the cooling air parameters of a gas turbine engine need to be obtained through multiple rounds of iterative calculations of the overall performance, components, and air system. And due to the lack of actual measured data support from the full-scale test, it cannot truly reflect the actual working conditions of the cooling air system of the gas turbine engine. In addition, due to the complexity of the cooling air system of the gas turbine engine, it is currently impossible to directly measure the cooling air quantity and the cooling air distribution ratio in the full-scale test, that is, it is impossible to directly verify whether the cooling air quantity and the cooling air distribution ratio in the overall performance scheme are reasonable and accurate through tests. Summary of the Invention

[0003] On the one hand, the present application provides a method for simulating parameters of a cooling air system of a single-rotor gas turbine engine, aiming to solve the technical problem that the existing calculation method for the cooling air system parameters of a gas turbine engine needs to be obtained through multiple rounds of iterative calculations of the overall performance, components, and air system, and its calculation results cannot truly reflect the actual working conditions of the cooling air system of the gas turbine engine.

[0004] The technical solution adopted by the present application is as follows:

[0005] A method for simulating parameters of a cooling air system of a single-rotor gas turbine engine includes the steps of:

[0006] S1. Obtain the measured parameters of the full-scale test of the single-rotor gas turbine engine, and obtain the characteristics of the combustion chamber component and the turbine component;

[0007] S2. Based on the measured parameters of the full-scale test obtained in step S1, calculate the total enthalpy at the compressor inlet, the total enthalpy at the compressor outlet, the compressor pressure ratio, the compressor efficiency, and the compressor work through the variable specific heat calculation method of the compressor component;

[0008] S3. Select the total cooling air quantity of the engine and the cooling air quantity of the gas turbine guide vane as the iteration variables, and assign the initial values for the iterative calculation;

[0009] S4. Based on the overall engine test measurement parameters known in step S1 and the total engine cooling air quantity and gas turbine guide vane cooling air quantity given in step S3, obtain the gas turbine rotor blade cooling air quantity, total enthalpy of the total engine cooling air, total enthalpy of the gas turbine guide vane cooling air, total enthalpy of the gas turbine rotor blade cooling air, the distribution ratio of each cooling air in the total cooling air, and the total pressure, total temperature, total enthalpy, physical air flow rate, and corrected air flow rate at the combustor inlet;

[0010] S5. Based on the overall engine test measurement parameters known in step S1, the combustor component characteristics, and the total pressure, total temperature, total enthalpy, physical air flow rate, and corrected air flow rate at the combustor inlet obtained in step S4, calculate the total pressure, total temperature, total enthalpy, gas flow rate, and gas - fuel ratio at the combustor outlet through the variable specific heat calculation method of the combustor component;

[0011] S6. Based on the overall engine test measurement parameters known in step S1, the gas turbine guide vane cooling air quantity obtained in step S3, the total enthalpy of the gas turbine guide vane cooling air obtained in step S4, and the total pressure, total temperature, total enthalpy, gas flow rate, and gas - fuel ratio at the combustor outlet obtained in step S5, calculate the corrected speed of the gas turbine, the total pressure, total temperature, total enthalpy, physical gas flow rate, corrected gas flow rate, and gas - fuel ratio at the gas turbine rotor blade inlet;

[0012] S7. Based on the turbine component characteristics known in step S1 and the corrected speed of the gas turbine, the total pressure, total temperature, total enthalpy, physical gas flow rate, corrected gas flow rate, and gas - fuel ratio at the gas turbine rotor blade inlet obtained in step S6, calculate the work of the gas turbine, the corrected gas flow rate required by the turbine component, and the total pressure, total temperature, total enthalpy, gas flow rate, and gas - fuel ratio at the gas turbine outlet through the variable specific heat calculation method of the turbine component;

[0013] S8. According to the common working conditions of the single - spool gas turbine engine, compare whether the sum of the overall engine test measurement parameters known in step S1 and the compressor work obtained in step S2 is balanced with the work of the gas turbine obtained in step S7, and compare whether the corrected gas flow rate at the gas turbine rotor blade inlet obtained in step S6 is balanced with the corrected gas flow rate required by the turbine component obtained in step S7. If not balanced, return to step S3 to modify the total engine cooling air quantity and the gas turbine guide vane cooling air quantity and continue the iteration until balanced, so as to obtain the final simulation results of the cooling air system parameters of the single - spool gas turbine engine.

[0014] Furthermore, in step S1, the overall engine test measurement parameters include the physical air flow rate at the engine inlet, the total pressure at the compressor inlet, the total temperature at the compressor inlet, the total pressure at the compressor outlet, the total temperature at the compressor outlet, the fuel flow rate, the physical speed of the engine rotor, and the extracted work of the gas generator accessories.

[0015] Further, step S2 specifically includes the following steps:

[0016] Based on the conditions of the engine inlet air physical flow rate, compressor inlet total pressure, compressor inlet total temperature, compressor outlet total pressure, and compressor outlet total temperature obtained in step S1, the compressor inlet total enthalpy, compressor outlet total enthalpy, compressor pressure ratio, compressor efficiency, and compressor work are calculated by the variable specific heat calculation method of the compressor component.

[0017] Further, step S4 specifically includes the following steps:

[0018] Based on the engine inlet air physical flow rate, compressor outlet total pressure, and compressor outlet total temperature known in step S1 and the total engine cooling air volume and gas turbine guide vane cooling air volume given in step S3, the gas turbine blade cooling air volume, total enthalpy of the total engine cooling air, total enthalpy of the gas turbine guide vane cooling air, total enthalpy of the gas turbine blade cooling air, the distribution ratio of each cooling air in the total cooling air, and the total pressure, total temperature, total enthalpy, air physical flow rate, and air conversion flow rate at the inlet of the combustion chamber are obtained.

[0019] Further, step S5 specifically includes the following steps

[0020] Based on the fuel flow rate known in step S1, the characteristics of the combustion chamber component, and the total pressure, total temperature, total enthalpy, air physical flow rate, and air conversion flow rate at the inlet of the combustion chamber obtained in step S4, the total pressure, total temperature, total enthalpy, gas flow rate, and gas - oil ratio at the outlet of the combustion chamber are calculated by the variable specific heat calculation method of the combustion chamber component.

[0021] Further, step S6 specifically includes the following steps:

[0022] Based on the physical rotational speed of the engine rotor known in step S1, the gas turbine guide vane cooling air volume obtained in step S3, the total enthalpy of the gas turbine guide vane cooling air obtained in step S4, and the total pressure, total temperature, total enthalpy, gas flow rate, and gas - oil ratio at the outlet of the combustion chamber obtained in step S5, the gas turbine conversion rotational speed, the total pressure, total temperature, total enthalpy, gas physical flow rate, gas conversion flow rate, and gas - oil ratio at the inlet of the gas turbine blade are calculated.

[0023] Further, step S8 specifically includes the following steps:

[0024] According to the common working conditions of a single-spool gas turbine engine, compare whether the sum of the work extracted by the gas generator accessories known in step S1 and the compressor work obtained in step S2 is balanced with the gas turbine work obtained in step S7, and compare whether the converted gas flow rate at the inlet of the gas turbine rotor blades obtained in step S6 is balanced with the converted gas flow rate required by the turbine components obtained in step S7. If not balanced, return to step S3 to modify the total engine cooling air volume and the cooling air volume of the gas turbine guide vanes and continue the iteration until balanced, so as to obtain the final simulation results of the cooling air system parameters of the single-spool gas turbine engine.

[0025] Another embodiment of the present application further provides a simulation device for the cooling air system parameters of a single-spool gas turbine engine, including:

[0026] An overall engine parameter acquisition module, configured to acquire the overall engine test measurement parameters of the single-spool gas turbine engine, and acquire the characteristics of the combustion chamber components and the turbine components;

[0027] A compressor parameter technology module, configured to calculate the total enthalpy at the compressor inlet, the total enthalpy at the compressor outlet, the compressor pressure ratio, the compressor efficiency, and the compressor work based on the overall engine test measurement parameters acquired in step S1 through the compressor component variable specific heat calculation method;

[0028] An iteration variable setting module, configured to select the total engine cooling air volume and the cooling air volume of the gas turbine guide vanes as iteration variables and assign initial values for the iterative calculation;

[0029] A cooling air and combustion chamber outlet parameter calculation module, configured to obtain the cooling air volume of the gas turbine rotor blades, the total enthalpy of the total engine cooling air, the total enthalpy of the cooling air of the gas turbine guide vanes, the total enthalpy of the cooling air of the gas turbine rotor blades, the distribution ratio of each cooling air in the total cooling air, and the total pressure, total temperature, total enthalpy, physical air flow rate, and converted air flow rate at the inlet of the combustion chamber based on the overall engine test measurement parameters known in step S1 and the total engine cooling air volume and the cooling air volume of the gas turbine guide vanes given in step S3;

[0030] A combustion chamber inlet and outlet parameter technology module, configured to calculate the total pressure, total temperature, total enthalpy, gas flow rate, and gas-oil ratio at the outlet of the combustion chamber through the combustion chamber component variable specific heat calculation method based on the overall engine test measurement parameters known in step S1, the characteristics of the combustion chamber components, and the total pressure, total temperature, total enthalpy, physical air flow rate, and converted air flow rate at the inlet of the combustion chamber obtained in step S4;

[0031] The gas turbine rotor blade parameter calculation module is used to calculate the converted speed of the gas turbine, the total pressure, total temperature, total enthalpy, physical gas flow rate, converted gas flow rate, and gas-oil ratio at the inlet of the gas turbine rotor blade based on the overall engine test measurement parameters known in step S1, the cooling air volume of the gas turbine guide vane obtained in step S3, the total enthalpy of the cooling air of the gas turbine guide vane obtained in step S4, and the total pressure, total temperature, total enthalpy, gas flow rate, and gas-oil ratio at the outlet of the combustion chamber obtained in step S5;

[0032] The converted gas flow rate and parameter calculation module at the outlet of the gas turbine is used to calculate the work of the gas turbine, the converted gas flow rate required by the turbine component, and the total pressure, total temperature, total enthalpy, gas flow rate, and gas-oil ratio at the outlet of the gas turbine through the variable specific heat calculation method of the turbine component based on the turbine component characteristics known in step S1 and the converted speed of the gas turbine, the total pressure, total temperature, total enthalpy, physical gas flow rate, converted gas flow rate, and gas-oil ratio at the inlet of the gas turbine rotor blade obtained in step S6;

[0033] The parameter balance judgment and iteration module is used to compare whether the sum of the overall engine test measurement parameters known in step S1 and the compressor work obtained in step S2 is balanced with the work of the gas turbine obtained in step S7 according to the common working conditions of the single-spool gas turbine engine, and to compare whether the converted gas flow rate at the inlet of the gas turbine rotor blade obtained in step S6 is balanced with the converted gas flow rate required by the turbine component obtained in step S7. If not balanced, return to step S3 to modify the total cooling air volume of the engine and the cooling air volume of the gas turbine guide vane and continue to iterate until balanced, so as to obtain the final simulation result of the cooling air system parameters of the single-spool gas turbine engine.

[0034] Another embodiment of the present application also provides an electronic device, including a memory, a processor, and a computer program stored on the memory and executable on the processor. When the processor executes the program, the steps of the simulation method for the cooling air system parameters of the single-spool gas turbine engine are implemented.

[0035] Another embodiment of the present application also provides a storage medium. The storage medium includes a stored program. When the program runs, it controls the device where the storage medium is located to execute the steps of the simulation method for the cooling air system parameters of the single-spool gas turbine engine.

[0036] Compared with the prior art, the present application has the following beneficial effects:

[0037] The present application provides a method and device for simulating parameters of a cooling air system of a single-rotor gas turbine engine. The method for simulating parameters of the cooling air system of the single-rotor gas turbine engine innovatively utilizes the measured data of the whole engine test, the characteristic data of the combustion chamber components, and the characteristic data of the turbine components. Through the variable specific heat calculation methods of the compressor, combustion chamber, and turbine components of the gas turbine engine and the common working conditions of the single-rotor gas turbine engine, iterative calculations are performed. The final calculation results obtained by this method are closer to the actual working conditions, can effectively support the correction and improvement of the overall performance scheme of the single-rotor gas turbine engine, improve the R & D efficiency of the single-rotor gas turbine engine, and reduce the economic and time losses caused by the iteration of the overall performance scheme of the single-rotor gas turbine engine. The present application can also provide method support for studying the influence of the change of the process parameters measured in the whole engine test on the parameters of the cooling air system of the single-rotor gas turbine engine.

[0038] In addition to the purposes, features, and advantages described above, the present application has other purposes, features, and advantages. The following will refer to the accompanying drawings to further elaborate on the present application in detail. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] The drawings constituting a part of the present application are used to provide a further understanding of the present application. The schematic embodiments of the present application and their descriptions are used to explain the present application and do not constitute an improper limitation to the present application. In the drawings:

[0040] Figure 1 is a schematic flow chart of the method for simulating parameters of the cooling air system of the single-rotor gas turbine engine according to the preferred embodiment of the present application.

[0041] Figure 2 is a schematic flow chart of the method for simulating parameters of the cooling air system of the single-rotor gas turbine engine according to another preferred embodiment of the present application.

[0042] Figure 3 is a schematic block diagram of the modules of the device for simulating parameters of the cooling air system of the single-rotor gas turbine engine according to the preferred embodiment of the present application.

[0043] Figure 4 is a schematic block diagram of the entity of the electronic device according to the preferred embodiment of the present application.

[0044] Figure 5 is the internal structure diagram of the computer device according to the preferred embodiment of the present application. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0045] It should be noted that, without conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The following will refer to the accompanying drawings and combine with the embodiments to elaborate on the present application in detail.

[0046] Refer to Figure 1, a preferred embodiment of the present application provides a simulation method for the parameters of a single-rotor gas turbine engine cooling air system, including the steps:

[0047] S1. Obtain the measured parameters of the single-rotor gas turbine engine during the whole-engine test, and obtain the characteristics of the combustion chamber components and the turbine components;

[0048] S2. Based on the measured parameters of the whole-engine test obtained in step S1, calculate the total enthalpy at the compressor inlet, the total enthalpy at the compressor outlet, the compressor pressure ratio, the compressor efficiency, and the compressor work through the variable specific heat calculation method of the compressor components;

[0049] S3. Select the total engine cooling air volume and the cooling air volume of the gas turbine guide vane as the iterative variables, and assign the initial values for the iterative calculation;

[0050] S4. Based on the measured parameters of the whole-engine test known in step S1 and the total engine cooling air volume and the cooling air volume of the gas turbine guide vane given in step S3, obtain the cooling air volume of the gas turbine rotor blade, the total enthalpy of the total engine cooling air, the total enthalpy of the cooling air of the gas turbine guide vane, the total enthalpy of the cooling air of the gas turbine rotor blade, the distribution ratio of each cooling air in the total cooling air, and the total pressure, total temperature, total enthalpy, physical air flow rate, and converted air flow rate at the inlet of the combustion chamber;

[0051] S5. Based on the measured parameters of the whole-engine test known in step S1, the characteristics of the combustion chamber components, and the total pressure, total temperature, total enthalpy, physical air flow rate, and converted air flow rate at the inlet of the combustion chamber obtained in step S4, calculate the total pressure, total temperature, total enthalpy, gas flow rate, and gas-oil ratio at the outlet of the combustion chamber through the variable specific heat calculation method of the combustion chamber components;

[0052] S6. Based on the measured parameters of the whole-engine test known in step S1, the cooling air volume of the gas turbine guide vane obtained in step S3, the total enthalpy of the cooling air of the gas turbine guide vane obtained in step S4, and the total pressure, total temperature, total enthalpy, gas flow rate, and gas-oil ratio at the outlet of the combustion chamber obtained in step S5, calculate the converted speed of the gas turbine, the total pressure, total temperature, total enthalpy, physical gas flow rate, converted gas flow rate, and gas-oil ratio at the inlet of the gas turbine rotor blade;

[0053] S7. Based on the characteristics of the turbine components known in step S1 and the converted speed of the gas turbine, the total pressure, total temperature, total enthalpy, physical gas flow rate, converted gas flow rate, and gas-oil ratio at the inlet of the gas turbine rotor blade obtained in step S6, calculate the work of the gas turbine, the converted gas flow rate required by the turbine components, and the total pressure, total temperature, total enthalpy, gas flow rate, and gas-oil ratio at the outlet of the gas turbine through the variable specific heat calculation method of the turbine components;

[0054] S8. According to the common working conditions of a single-spool gas turbine engine, compare whether the sum of the measured parameters of the whole-engine test known in step S1 and the compressor work obtained in step S2 is balanced with the gas turbine work obtained in step S7, and compare whether the converted gas flow rate at the inlet of the gas turbine moving blade obtained in step S6 is balanced with the converted gas flow rate required by the turbine component obtained in step S7. If not balanced, return to step S3 to modify the total engine cooling air quantity and the cooling air quantity of the gas turbine guide vane and continue the iteration until balanced, so as to obtain the final simulation result of the cooling air system parameters of the single-spool gas turbine engine.

[0055] This embodiment provides a method for simulating the parameters of the cooling air system of a single-spool gas turbine engine. The method for simulating the parameters of the cooling air system of the single-spool gas turbine engine innovatively uses the measured data of the whole-engine test of the engine, the characteristic data of the combustion chamber component, and the characteristic data of the turbine component, and performs iterative calculations through the variable specific heat calculation methods of the compressor, combustion chamber, and turbine components of the gas turbine engine and the common working conditions of the single-spool gas turbine engine. The final calculation result obtained by using this method is closer to the actual working condition, can effectively support the correction and improvement of the overall performance scheme of the single-spool gas turbine engine, improve the R & D efficiency of the single-spool gas turbine engine, and reduce the economic and time losses caused by the iteration of the overall performance scheme of the single-spool gas turbine engine. This application can also provide method support for studying the influence of the change of the process parameters measured in the whole-engine test on the parameters of the cooling air system of the single-spool gas turbine engine.

[0056] Specifically, in step S1, the measured parameters of the whole-engine test include the physical air flow rate at the engine inlet, the total pressure at the compressor inlet, the total temperature at the compressor inlet, the total pressure at the compressor outlet, the total temperature at the compressor outlet, the fuel flow rate, the physical speed of the engine rotor, and the extracted work of the gas generator accessories.

[0057] Preferably, step S2 specifically includes the steps of:

[0058] Based on the conditions of the physical air flow rate at the engine inlet, the total pressure at the compressor inlet, the total temperature at the compressor inlet, the total pressure at the compressor outlet, and the total temperature at the compressor outlet obtained in step S1, calculate the total enthalpy at the compressor inlet, the total enthalpy at the compressor outlet, the compressor pressure ratio, the compressor efficiency, and the compressor work through the variable specific heat calculation method of the compressor component.

[0059] Preferably, step S4 specifically includes the steps of:

[0060] Based on the physical flow rate of the engine inlet air, the total pressure at the compressor outlet, the total temperature at the compressor outlet known in step S1, and the total engine cooling air volume and the cooling air volume of the gas turbine guide vane given in step S3, obtain the cooling air volume of the gas turbine rotor blades, the total enthalpy of the total engine cooling air, the total enthalpy of the cooling air of the gas turbine guide vane, the total enthalpy of the cooling air of the gas turbine rotor blades, the distribution ratio of each cooling air in the total cooling air, and the total pressure, total temperature, total enthalpy, physical air flow rate, and converted air flow rate at the inlet of the combustion chamber.

[0061] Preferably, step S5 specifically includes the steps

[0062] Based on the fuel flow rate known in step S1, the characteristics of the combustion chamber components, and the total pressure, total temperature, total enthalpy, physical air flow rate, and converted air flow rate at the inlet of the combustion chamber obtained in step S4, calculate the total pressure, total temperature, total enthalpy, gas flow rate, and gas-oil ratio at the outlet of the combustion chamber through the combustion chamber component variable specific heat calculation method.

[0063] Preferably, step S6 specifically includes the steps:

[0064] Based on the physical rotational speed of the engine rotor known in step S1, the cooling air volume of the gas turbine guide vane obtained in step S3, the total enthalpy of the cooling air of the gas turbine guide vane obtained in step S4, and the total pressure, total temperature, total enthalpy, gas flow rate, and gas-oil ratio at the outlet of the combustion chamber obtained in step S5, calculate the converted rotational speed of the gas turbine, the total pressure, total temperature, total enthalpy, physical gas flow rate, converted gas flow rate, and gas-oil ratio at the inlet of the gas turbine rotor blades.

[0065] Preferably, step S8 specifically includes the steps:

[0066] According to the common working conditions of a single-spool gas turbine engine, compare whether the sum of the extraction work of the gas generator accessories known in step S1 and the compressor work obtained in step S2 is balanced with the gas turbine work obtained in step S7, and compare whether the converted gas flow rate at the inlet of the gas turbine rotor blades obtained in step S6 is balanced with the converted gas flow rate required by the turbine components obtained in step S7. If not balanced, return to step S3 to modify the total engine cooling air volume and the cooling air volume of the gas turbine guide vane and continue the iteration until balanced, so as to obtain the final simulation results of the cooling air system parameters of the single-spool gas turbine engine.

[0067] The variable specific heat calculation methods for the compressor, combustion chamber, and turbine components of the gas turbine engine mentioned in this application are well-known and publicly recognized technical methods in the industry, and will not be elaborated here.

[0068] This application is applicable to Figure 1The single-rotor gas turbine engine types shown include: turbojet engines with single-rotor gas turbine generators, and turboprop / turboshaft engines with single-rotor gas turbine generators. This parameter simulation method is based on the data measured from the overall machine tests of single-rotor gas turbine engines, the characteristic data of combustion chamber components, and the characteristic data of turbine components. It uses the variable specific heat calculation method for the compressor, combustion chamber, and turbine components of gas turbine engines. According to the common working conditions of single-rotor gas turbine engines, iterative calculations are performed to obtain the cooling air system parameters of single-rotor gas turbine engines that are closer to the actual working conditions. Figure 2 Schematic diagram of the process for simulating the cooling air system parameters of a single-rotor gas turbine engine according to another preferred embodiment of the present application.

[0069] As Figure 3 shown, on the other hand, an embodiment of the present application also provides a device for simulating the cooling air system parameters of a single-rotor gas turbine engine, including:

[0070] An overall machine parameter acquisition module, used to acquire the parameters measured from the overall machine tests of a single-rotor gas turbine engine, and acquire the characteristics of combustion chamber components and turbine components;

[0071] A compressor parameter technology module, used to calculate the total enthalpy at the compressor inlet, the total enthalpy at the compressor outlet, the compressor pressure ratio, the compressor efficiency, and the compressor work through the variable specific heat calculation method of the compressor component based on the parameters measured from the overall machine tests obtained in step S1;

[0072] An iterative variable setting module, used to select the total engine cooling air volume and the cooling air volume of the gas turbine guide vane as iterative variables and assign the initial values for iterative calculations;

[0073] A cooling air and combustion chamber outlet parameter calculation module, used to obtain the cooling air volume of the gas turbine moving blades, the total enthalpy of the total engine cooling air, the total enthalpy of the cooling air of the gas turbine guide vane, the total enthalpy of the cooling air of the gas turbine moving blades, the distribution ratio of each cooling air in the total cooling air, and the total pressure, total temperature, total enthalpy, physical air flow rate, and converted air flow rate at the inlet of the combustion chamber based on the parameters measured from the overall machine tests known in step S1 and the total engine cooling air volume and the cooling air volume of the gas turbine guide vane given in step S3;

[0074] A combustion chamber inlet and outlet parameter technology module, used to calculate the total pressure, total temperature, total enthalpy, gas flow rate, and gas-oil ratio at the outlet of the combustion chamber through the variable specific heat calculation method of the combustion chamber component based on the parameters measured from the overall machine tests known in step S1, the characteristics of the combustion chamber components, and the total pressure, total temperature, total enthalpy, physical air flow rate, and converted air flow rate at the inlet of the combustion chamber obtained in step S4;

[0075] The gas turbine moving blade parameter calculation module is used to calculate the gas turbine converted speed, the total pressure, total temperature, total enthalpy, gas physical flow rate, gas converted flow rate, and gas oil-gas ratio at the inlet of the gas turbine moving blade based on the overall engine test measurement parameters known in step S1, the cooling air volume of the gas turbine guide vane obtained in step S3, the total enthalpy of the cooling air of the gas turbine guide vane obtained in step S4, and the total pressure, total temperature, total enthalpy, gas flow rate, and gas oil-gas ratio at the outlet of the combustion chamber obtained in step S5;

[0076] The gas converted flow rate and parameter calculation module at the outlet of the gas turbine is used to calculate the gas turbine work, the gas converted flow rate required by the turbine component, and the total pressure, total temperature, total enthalpy, gas flow rate, and gas oil-gas ratio at the outlet of the gas turbine through the variable specific heat calculation method of the turbine component based on the turbine component characteristics known in step S1 and the gas turbine converted speed, the total pressure, total temperature, total enthalpy, gas physical flow rate, gas converted flow rate, and gas oil-gas ratio at the inlet of the gas turbine moving blade obtained in step S6;

[0077] The parameter balance judgment and iteration module is used to compare whether the sum of the overall engine test measurement parameters known in step S1 and the compressor work obtained in step S2 is balanced with the gas turbine work obtained in step S7, and compare whether the gas converted flow rate at the inlet of the gas turbine moving blade obtained in step S6 is balanced with the gas converted flow rate required by the turbine component obtained in step S7 according to the common working conditions of the single-rotor gas turbine engine. If not balanced, it returns to step S3 to modify the total cooling air volume of the engine and the cooling air volume of the gas turbine guide vane and continues to iterate until balanced, so as to obtain the final simulation results of the cooling air system parameters of the single-rotor gas turbine engine.

[0078] Each module in the above device can be implemented in whole or in part by software, hardware, and their combination. The above modules can be embedded in the processor in the computer device in the form of hardware or independent of it, or stored in the memory of the computer device in the form of software, so that the processor can call and execute the operations corresponding to the above modules.

[0079] As Figure 4 shown, a preferred embodiment of the present application also provides an electronic device, including a memory, a processor, and a computer program stored on the memory and executable on the processor. When the processor executes the program, it implements the simulation method for the cooling air system parameters of the single-rotor gas turbine engine in the above embodiment.

[0080] As Figure 5 shown, a preferred embodiment of the present application also provides a computer device, and its internal structure diagram can be as Figure 5As shown. The computer device includes a processor, a memory, and a network interface connected via a system bus. Among them, the processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile 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 the operating system and the computer program in the non-volatile storage medium. The network interface of the computer device is used to communicate with other external computer devices via a network connection. When the computer program is executed by the processor, it implements the above-mentioned single-rotor gas turbine engine cooling air system parameter simulation method.

[0081] Those skilled in the art can understand that Figure 5 the structure shown in is only a block diagram of some structures related to the solution of this application, and does not constitute a limitation on the computer device to which the solution of this application is applied. Specifically, the computer device may include more or fewer devices than those shown in the figure, or combine certain devices, or have different device arrangements.

[0082] A preferred embodiment of this application also provides a storage medium. The storage medium includes a stored program that controls the device where the storage medium is located to execute the steps of the above-mentioned single-rotor gas turbine engine cooling air system parameter simulation method when the program runs.

[0083] It should be noted that the steps shown in the flowchart of the accompanying drawings can be executed in a computer system such as a set of computer-executable instructions. And although the logical order is shown in the flowchart, in some cases, the steps shown or described can be executed in a different order than here.

[0084] If the functions of the method in this embodiment are implemented in the form of software function units and sold or used as an independent product, they can be stored in one or more computer-readable storage media. Based on this understanding, the part that makes a contribution to the prior art or part of this technical solution in the embodiments of this application can be embodied in the form of a software product. The software product is stored in a storage medium and includes several instructions to enable a computing device (which can be a personal computer, a server, a mobile computing device, or a network device, etc.) to execute all or part of the steps of the methods described in various embodiments of this application. And the aforementioned storage medium includes: USB flash drive, mobile hard disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), magnetic disk or optical disk and other various media that can store program codes.

[0085] The above are only the preferred embodiments of the present application and are not intended to limit the present application. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present application shall be included within the protection scope of the present application.

Claims

1. A simulation method for parameters of a cooling air system of a single-rotor gas turbine engine, characterized in that, Including the steps: S1. Obtain the measured parameters of the whole single-spool gas turbine engine during the whole-engine test, and obtain the characteristics of the combustion chamber components and the turbine components; S2. Based on the measured parameters of the whole-engine test obtained in step S1, calculate the total enthalpy at the compressor inlet, the total enthalpy at the compressor outlet, the compressor pressure ratio, the compressor efficiency, and the compressor work through the variable specific heat calculation method of the compressor components; S3. Select the total engine cooling air flow rate and the cooling air flow rate of the gas turbine guide vane as the iterative variables, and assign the initial values for iterative calculation; S4. Based on the measured parameters of the whole-engine test known in step S1 and the total engine cooling air flow rate and the cooling air flow rate of the gas turbine guide vane given in step S3, obtain the cooling air flow rate of the gas turbine rotor blades, the total enthalpy of the total engine cooling air, the total enthalpy of the cooling air of the gas turbine guide vane, the total enthalpy of the cooling air of the gas turbine rotor blades, the distribution ratio of each cooling air in the total cooling air, and the total pressure, total temperature, total enthalpy, physical air flow rate, and corrected air flow rate at the combustion chamber inlet; S5. Based on the measured parameters of the whole-engine test known in step S1, the characteristics of the combustion chamber components, and the total pressure, total temperature, total enthalpy, physical air flow rate, and corrected air flow rate at the combustion chamber inlet obtained in step S4, calculate the total pressure, total temperature, total enthalpy, gas flow rate, and gas-fuel ratio at the combustion chamber outlet through the variable specific heat calculation method of the combustion chamber components; S6. Based on the measured parameters of the whole-engine test known in step S1, the cooling air flow rate of the gas turbine guide vane obtained in step S3, the total enthalpy of the cooling air of the gas turbine guide vane obtained in step S4, and the total pressure, total temperature, total enthalpy, gas flow rate, and gas-fuel ratio at the combustion chamber outlet obtained in step S5, calculate the corrected speed of the gas turbine, the total pressure, total temperature, total enthalpy, physical gas flow rate, corrected gas flow rate, and gas-fuel ratio at the inlet of the gas turbine rotor blades; S7. Based on the characteristics of the turbine components known in step S1 and the corrected speed of the gas turbine, the total pressure, total temperature, total enthalpy, physical gas flow rate, corrected gas flow rate, and gas-fuel ratio at the inlet of the gas turbine rotor blades obtained in step S6, calculate the gas turbine work, the corrected gas flow rate required by the turbine components, and the total pressure, total temperature, total enthalpy, gas flow rate, and gas-fuel ratio at the outlet of the gas turbine through the variable specific heat calculation method of the turbine components; S8. According to the co-working conditions of the single-spool gas turbine engine, compare whether the sum of the measured parameters of the whole-engine test known in step S1 and the compressor work obtained in step S2 is balanced with the gas turbine work obtained in step S7, and compare whether the corrected gas flow rate of the gas turbine rotor blade inlet obtained in step S6 is balanced with the corrected gas flow rate required by the turbine components obtained in step S7. If not balanced, return to step S3 to modify the total engine cooling air flow rate and the cooling air flow rate of the gas turbine guide vane and continue the iteration until balanced, so as to obtain the final simulation results of the cooling air system parameters of the single-spool gas turbine engine.

2. The simulation method of the cooling air system parameters of the single-rotor gas turbine engine according to claim 1, wherein In step S1, the measured parameters of the whole-engine test include the physical air flow rate at the engine inlet, the total pressure at the compressor inlet, the total temperature at the compressor inlet, the total pressure at the compressor outlet, the total temperature at the compressor outlet, the fuel flow rate, the physical speed of the engine rotor, and the extracted work of the gas generator accessories.

3. The simulation method for the cooling air system parameters of a single-spool gas turbine engine according to claim 1, characterized in that, The specific steps of step S2 include the following steps: Based on the conditions of the engine inlet air physical flow rate, compressor inlet total pressure, compressor inlet total temperature, compressor outlet total pressure, and compressor outlet total temperature obtained in step S1, the compressor inlet total enthalpy, compressor outlet total enthalpy, compressor pressure ratio, compressor efficiency, and compressor work are calculated through the variable specific heat calculation method of the compressor component.

4. The simulation method for the cooling air system parameters of a single-rotor gas turbine engine according to claim 1, wherein, The specific steps of step S4 include the following steps: Based on the engine inlet air physical flow rate, compressor outlet total pressure, and compressor outlet total temperature known in step S1, and the total engine cooling air volume and gas turbine guide vane cooling air volume given in step S3, the gas turbine rotor blade cooling air volume, total engine cooling air total enthalpy, gas turbine guide vane cooling air total enthalpy, gas turbine rotor blade cooling air total enthalpy, the distribution ratio of each cooling air in the total cooling air, and the total pressure, total temperature, total enthalpy, air physical flow rate, and air conversion flow rate at the inlet of the combustion chamber are obtained.

5. The simulation method for the cooling air system parameters of a single-rotor gas turbine engine according to claim 1, characterized in that, The specific steps of step S5 include Based on the fuel flow rate known in step S1, the characteristics of the combustion chamber component, and the total pressure, total temperature, total enthalpy, air physical flow rate, and air conversion flow rate at the inlet of the combustion chamber obtained in step S4, the total pressure, total temperature, total enthalpy, gas flow rate, and gas-oil ratio at the outlet of the combustion chamber are calculated through the variable specific heat calculation method of the combustion chamber component.

6. The simulation method for the cooling air system parameters of a single-spool gas turbine engine according to claim 1, characterized in that, The specific steps of step S6 include the following steps: Based on the physical rotational speed of the engine rotor known in step S1, the gas turbine guide vane cooling air volume obtained in step S3, the total enthalpy of the gas turbine guide vane cooling air obtained in step S4, and the total pressure, total temperature, total enthalpy, gas flow rate, and gas-oil ratio at the outlet of the combustion chamber obtained in step S5, the gas turbine conversion rotational speed, the total pressure, total temperature, total enthalpy, gas physical flow rate, gas conversion flow rate, and gas-oil ratio at the inlet of the gas turbine rotor blade are calculated.

7. The simulation method for the cooling air system parameters of a single-rotor gas turbine engine according to claim 1, characterized in that The specific steps of step S8 include the following steps: According to the common working conditions of the single-rotor gas turbine engine, compare whether the sum of the extracted work of the gas generator accessories known in step S1 and the compressor work obtained in step S2 is balanced with the gas turbine work obtained in step S7, and compare whether the gas turbine rotor blade inlet gas conversion flow rate obtained in step S6 is balanced with the gas turbine component required gas conversion flow rate obtained in step S7. If not balanced, return to step S3 to modify the total engine cooling air volume and gas turbine guide vane cooling air volume and continue to iterate until balanced, so as to obtain the final simulation results of the single-rotor gas turbine engine cooling air system parameters.

8. A simulation device for parameters of a cooling air system of a single-rotor gas turbine engine, characterized in that, Including: An overall machine parameter acquisition module, used to acquire the overall machine test measurement parameters of the single-rotor gas turbine engine, and acquire the characteristics of the combustion chamber component and the turbine component; A compressor parameter technology module, used to calculate the compressor inlet total enthalpy, compressor outlet total enthalpy, compressor pressure ratio, compressor efficiency, and compressor work based on the overall machine test measurement parameters obtained in step S1 through the variable specific heat calculation method of the compressor component; An iteration variable setting module, used to select the total engine cooling air volume and the gas turbine guide vane cooling air volume as iteration variables and assign the initial values of the iterative calculation; Cooling air and combustion chamber outlet parameter calculation module, which is used to obtain the cooling air volume of the gas turbine moving blades, the total enthalpy of the engine's total cooling air, the total enthalpy of the cooling air of the gas turbine guide vanes, the total enthalpy of the cooling air of the gas turbine moving blades, the distribution ratio of each cooling air in the total cooling air, and the total pressure, total temperature, total enthalpy, physical air flow rate, and converted air flow rate at the combustion chamber inlet based on the overall engine test measurement parameters known in step S1 and the total cooling air volume of the engine and the cooling air volume of the gas turbine guide vanes given in step S3; Combustion chamber inlet and outlet parameter technology module, which is used to calculate the total pressure, total temperature, total enthalpy, gas flow rate, and gas-oil ratio at the combustion chamber outlet through the combustion chamber component variable specific heat calculation method based on the overall engine test measurement parameters known in step S1, the combustion chamber component characteristics, and the total pressure, total temperature, total enthalpy, physical air flow rate, and converted air flow rate at the combustion chamber inlet obtained in step S4; Gas turbine moving blade parameter calculation module, which is used to calculate the converted speed of the gas turbine, the total pressure, total temperature, total enthalpy, physical gas flow rate, converted gas flow rate, and gas-oil ratio at the inlet of the gas turbine moving blades based on the overall engine test measurement parameters known in step S1, the cooling air volume of the gas turbine guide vanes obtained in step S3, the total enthalpy of the cooling air of the gas turbine guide vanes obtained in step S4, and the total pressure, total temperature, total enthalpy, gas flow rate, and gas-oil ratio at the combustion chamber outlet obtained in step S5; Converted gas flow rate and gas turbine outlet parameter calculation module, which is used to calculate the gas turbine work, the converted gas flow rate required by the turbine components, and the total pressure, total temperature, total enthalpy, gas flow rate, and gas-oil ratio at the gas turbine outlet through the turbine component variable specific heat calculation method based on the turbine component characteristics known in step S1 and the converted speed of the gas turbine, the total pressure, total temperature, total enthalpy, physical gas flow rate, converted gas flow rate, and gas-oil ratio at the inlet of the gas turbine moving blades obtained in step S6; Parameter balance judgment and iteration module, which is used to compare whether the sum of the compressor work obtained in step S2 is balanced with the gas turbine work obtained in step S7 according to the common working conditions of the single-rotor gas turbine engine, and compare whether the converted gas flow rate at the inlet of the gas turbine moving blades obtained in step S6 is balanced with the converted gas flow rate required by the turbine components obtained in step S7. If not balanced, return to step S3 to modify the total cooling air volume of the engine and the cooling air volume of the gas turbine guide vanes and continue to iterate until balanced, so as to obtain the final simulation results of the cooling air system parameters 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, characterized in that, When the processor executes the program, it realizes the steps of the single-rotor gas turbine engine cooling air system parameter simulation method according to any one of claims 1 to 7.

10. A storage medium, which includes a stored program that controls the device where the storage medium is located to execute the steps of the single-rotor gas turbine engine cooling air system parameter simulation method when the program runs.

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