A simulation model for the starting performance of a variable cycle engine core

Abstract

The present invention provides a simulation model for the starting performance of a variable cycle engine core, belonging to the technical field of aeroengines. By developing modules and combinations capable of simulating adjustable mechanism components, this simulation model realizes the modeling and simulation of the starting performance of the variable cycle engine core under different working modes and different adjustment plans.

Description

Technical Field

[0001] The present invention belongs to the field of aeroengines, and particularly relates to a simulation model for the starting performance of a variable cycle engine core. Background Art

[0002] The core of a variable cycle engine is the most important part of a variable cycle engine, and is composed of an air inlet, a core driven fan (CDFS), a compressor, a combustion chamber, a turbine, a nozzle, an outer casing with a mode selection valve (MSV) and a front bypass air injector (FVABI), an outer bypass nozzle, a shaft, and a starter. Its adjustable mechanisms include the angle of the inlet guide vane of the CDFS, the angle of the inlet guide vane of the compressor, the area of the high-pressure turbine guide vane, the area of the front bypass air injector (FVABI), and the opening degree of the mode selection valve (MSV). The working mode is determined by the opening degree of the mode selection valve (MSV).

[0003] Existing engine starting performance calculation models and related programs / software do not cover the core of this special configuration, and do not consider the influence of the adjustment of adjustable mechanisms on the starting performance. Therefore, it is impossible to calculate and evaluate the starting performance of the core of this unconventional configuration.

[0004] Therefore, it is necessary to establish a starting performance model for the core of this structural type to calculate and evaluate the starting performance of the variable cycle engine core under different modes and different adjustment plans. Summary of the Invention

[0005] The purpose of the present invention is to provide a simulation model for the starting performance of a variable cycle engine core to realize the modeling and simulation of the starting performance of the variable cycle engine core under different working modes and different adjustment plans.

[0006] To achieve the above purpose, the present invention provides the following technical solutions:

[0007] A simulation model for the starting performance of a variable cycle engine core. The simulation model includes an inlet duct module, a CDFS component module, a compressor module, a combustor module, a high-pressure turbine module, a nozzle module, an outer casing module, an outer nozzle module, a starter module, and a shaft module. Among them, the inlet duct module is used for calculating the total temperature, total pressure, flight speed, and total pressure recovery coefficient at the inlet and outlet of the intake device; the CDFS component module includes an adjustable inlet guide vane model for the CDFS, which is used for calculating relevant parameters at the inlet and outlet of the CDFS. The CDFS component module receives the total temperature, total pressure, flight speed, and total pressure recovery coefficient at the inlet and outlet of the intake device calculated by the inlet duct module; the compressor module includes an adjustable inlet guide vane model for the compressor, which is used for calculating relevant parameters at the inlet and outlet of the compressor. The compressor module receives relevant parameters of the CDFS outlet airflow; the combustor module is used for calculating relevant parameters at the inlet and outlet of the combustor. The combustor module receives relevant parameters of the compressor outlet airflow; the high-pressure turbine module includes an adjustable guide vane model for calculating relevant parameters at the inlet and outlet of the turbine. The high-pressure turbine module receives relevant parameters of the combustor outlet airflow; the nozzle module is used for calculating relevant parameters at the inlet and outlet of the nozzle. The nozzle module receives relevant parameters of the turbine outlet airflow; the outer casing module includes a mixer / abrupt expansion loss model. The mixer / abrupt expansion loss model selects different working modes through the switch of the MSV, and calculates relevant parameters of the mixer and the pressure loss caused by the abrupt expansion of the front bypass ejector area under different working modes, so as to obtain relevant parameters at the outlet of the outer casing. The outer casing module receives the total temperature, total pressure, flight speed, and total pressure recovery coefficient at the inlet and outlet of the intake device calculated by the inlet duct module and the relevant parameters at the inlet and outlet of the CDFS; the outer nozzle module is used for calculating relevant parameters at the inlet and outlet of the outer nozzle. The outer nozzle module receives the relevant parameters at the outlet of the outer casing; the starter module is used for calculating the output power of the starter; the shaft module is used for calculating relevant parameters of the shaft. The shaft module receives the relevant parameters of the CDFS outlet, the relevant parameters of the compressor, the relevant parameters at the inlet and outlet of the turbine, and the output power of the starter.

[0008] The simulation model for the starting performance of the core engine of the variable cycle engine provided by the present invention also has the following characteristics. The relevant parameters at the inlet and outlet of the CDFS include the total pressure / total temperature / flow rate at the inlet and outlet, the pressure ratio of the CDFS, the efficiency of the CDFS, and the power of the CDFS; the relevant parameters at the inlet and outlet of the compressor include the total pressure / total temperature / flow rate at the inlet and outlet of the compressor, the pressure ratio of the compressor, the efficiency of the compressor, and the power of the compressor; the relevant parameters at the inlet and outlet of the combustor include the total pressure at the inlet and outlet of the combustor, the total temperature at the inlet and outlet of the combustor, the flow rate at the inlet and outlet of the combustor, and the total pressure recovery coefficient at the inlet and outlet of the combustor; the relevant parameters at the inlet and outlet of the turbine include the total temperature at the inlet and outlet of the turbine, the total pressure at the inlet and outlet of the turbine, the flow rate at the inlet and outlet of the turbine, the expansion ratio at the inlet and outlet of the turbine, the efficiency of the turbine, and the power of the turbine; the relevant parameters at the inlet and outlet of the nozzle include the total pressure of the gas flow at the inlet and outlet of the nozzle, the total temperature of the gas flow at the inlet and outlet of the nozzle, the flow rate of the gas flow at the inlet and outlet of the nozzle, the expansion ratio at the inlet and outlet of the nozzle, the flow coefficient of the gas flow at the inlet and outlet of the nozzle, the velocity coefficient of the gas flow at the inlet and outlet of the nozzle, and the velocity of the gas flow at the inlet and outlet of the nozzle; the relevant parameters of the mixer include the main flow inlet, the secondary flow inlet, and the flow rate / total temperature / total pressure / Mach number at the outlet of the mixing chamber; the relevant parameters at the outlet of the outer casing include the total temperature / total pressure / flow rate of the gas flow at the outlet of the outer casing; the relevant parameters at the inlet and outlet of the outer nozzle include the total pressure of the gas flow at the inlet and outlet of the outer nozzle, the total temperature of the gas flow at the inlet and outlet of the outer nozzle, the flow rate of the gas flow at the inlet and outlet of the outer nozzle, the expansion ratio of the gas flow at the inlet and outlet of the outer nozzle, the flow coefficient of the gas flow at the inlet and outlet of the outer nozzle, the velocity coefficient of the gas flow at the inlet and outlet of the outer nozzle, and the velocity of the gas flow at the inlet and outlet of the outer nozzle.

[0009] The relevant parameters of the shaft include the shaft rotor acceleration and the shaft speed.

[0010] The simulation model for the starting performance of the core engine of the variable cycle engine provided by the present invention also has the following characteristics. The data processing method inside the CDFS component module is as follows:

[0011] The influence of the CDFS inlet guide vane adjustment on the reference characteristics is as follows:

[0012]

[0013] In the formula: W, η, and π respectively represent the flow rate, efficiency, and pressure ratio; θ represents the deviation between the actual angle of the CDFS inlet guide vane and the reference angle; the subscript 0 represents the reference; k w , k η , k π are respectively the correction factors for the flow rate, efficiency, and pressure ratio, k = f(θ, n cor ), n cor is the relative corrected speed of the CDFS.

[0014] The simulation model for the starting performance of the core engine of the variable cycle engine provided by the present invention also has the following characteristics. The data processing method inside the compressor module is as follows:

[0015] The influence of the adjustment of the compressor inlet guide vane on the reference characteristics is as follows:

[0016]

[0017] Where: W, η, and π respectively represent the flow rate, efficiency, and pressure ratio; θ represents the deviation between the actual angle of the compressor inlet guide vane and the reference angle; the subscript 0 represents the reference; k w , k η , k π are respectively the correction factors for the flow rate, efficiency, and pressure ratio, k = f(θ, n cor ), n cor is the relative converted speed of the compressor.

[0018] The simulation model for the starting performance of the core engine of the variable cycle engine provided by the present invention also has the following characteristics. The internal data processing method of the high-pressure turbine module is as follows:

[0019] The influence of the adjustment of the turbine variable guide vane on the reference characteristics is as follows:

[0020]

[0021] Wherein, W and η respectively represent the flow rate and efficiency; A represents the actual area of the throat of the turbine guide vane; the subscript 0 represents the reference; k W , k η represent the correction factors for the flow rate and efficiency.

[0022] The simulation model for the starting performance of the core engine of the variable cycle engine provided by the present invention also has the following characteristics. When the MSV is opened, the mixer / abrupt expansion loss model is regarded as the mixer model for calculating the relevant parameters of the mixer;

[0023] When the MSV is closed, the mixer / abrupt expansion loss model is regarded as the abrupt expansion loss model for calculating the pressure loss caused by the abrupt expansion of the area of the front bypass duct ejector.

[0024] The simulation model for the starting performance of the core engine of the variable cycle engine provided by the present invention also has the following characteristics. The mathematical model obtained by the simulation model for describing the working state of the core engine is as follows:

[0025]

[0026] Wherein, f1 represents the flow rate balance between the compressor and the turbine, f2 represents the flow rate balance between the turbine and the inner nozzle, f3 represents the flow rate balance between the outer bypass duct casing and the outer bypass duct nozzle, n is the physical speed of the rotor, π cd is the CDFS pressure ratio, π c is the compressor pressure ratio, π ht is the high-pressure turbine expansion ratio, wf is the fuel flow rate; α cdis the CDFS inlet guide vane angle, α c is the compressor inlet guide vane angle, A ht is the high-pressure turbine guide vane area, A FVABI is the front bypass duct ejector area, A MSV is the mode selection valve opening area, ΔN H is the remaining power on the shaft, J is the rotor moment of inertia, is the rotor acceleration rate.

[0027] Advantageous effects

[0028] A variable cycle engine core engine starting performance simulation model provided by the present invention realizes the modeling and simulation of the starting performance of the variable cycle engine core engine under different working modes and different adjustment plans by developing modules and combinations capable of simulating adjustable mechanism components. Brief description of the drawings

[0029] In order to more clearly illustrate the technical solutions of the present invention for patents, the following will briefly introduce the drawings required for use in the description of the implementation cases or the prior art. Obviously, the drawings in the following description are only some implementation cases of the present invention for patents. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0030] Figure 1 is a schematic diagram of the variable cycle engine core engine starting performance simulation model provided by the embodiment of the present invention;

[0031] Figure 2 is a schematic diagram of the variable cycle engine core engine structure;

[0032] Figure 3 is the preliminary pneumatic fuel supply control plan diagram in the embodiment of the present invention;

[0033] Figure 4 is the starting fuel supply law diagram in the embodiment of the present invention;

[0034] Figure 5 is the rotational speed curve obtained in the embodiment of the present invention;

[0035] Figure 6 is the component margin curve obtained in the embodiment of the present invention;

[0036] Figure 7 is the turbine outlet temperature curve obtained in the embodiment of the present invention. Specific implementation manners

[0037] The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. However, it should be noted that these embodiments are not intended to limit the present invention. Any equivalent transformation or substitution in terms of function, method, or structure made by those of ordinary skill in the art based on these embodiments shall fall within the protection scope of the present invention.

[0038] In the description of the embodiments of the present invention, it is to be understood that the terms "center", "longitudinal", "transverse", "up", "down", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings. These are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation to the present invention.

[0039] In addition, the terms "first", "second", "third", etc. are only used for descriptive purposes and cannot be construed as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, features defined with "first", "second", etc. may explicitly or implicitly include one or more of such features. In the description of the present invention, unless otherwise specified, the meaning of "a plurality" is two or more.

[0040] The terms "mounted", "connected", "coupled" should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral connection; it may be a mechanical connection or an electrical connection; it may be a direct connection or an indirect connection through an intermediate medium, and it may be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0041] Such as Figure 2As shown in the figure, it is a schematic diagram of the core engine structure of a variable cycle engine. The core engine of the variable cycle engine includes an intake device 1, a mode selection valve (MSV) 2, a core driven fan (CDFS) 3, a front bypass ejector mixer (FVABI) 4, a compressor 5, a combustion chamber 6, a high-pressure turbine 7, a nozzle 8, an outer bypass casing 9, an outer bypass nozzle 10, and a shaft 11. The outlet of the intake device 1 is respectively connected to the inlets of the CDFS 3 and the outer bypass casing 9. The outlet of the CDFS 3 is respectively connected to the inlets of the intake casing 1 and the compressor 5. The outlet of the compressor 5 is connected to the inlet of the combustion chamber 6. The outlet of the combustion chamber 6 is connected to the inlet of the high-pressure turbine 7. The outlet of the high-pressure turbine 7 is connected to the inlet of the nozzle 8. The outlet of the outer bypass casing 9 is connected to the inlet of the outer bypass nozzle 10. The CDFS 3, the compressor 5, the high-pressure turbine 7 are connected to the shaft 11. The intake device 1 is simulated and calculated by the intake device module. The CDFS 3 is simulated and calculated by the CDFS module. The compressor 5 is simulated and calculated by the compressor module. The combustion chamber 6 is simulated and calculated by the combustion chamber module. The high-pressure turbine 7 is simulated and calculated by the high-pressure turbine module. The nozzle 8 is simulated and calculated by the nozzle module. The outer bypass casing 9 is simulated and calculated by the outer bypass casing module. The outer bypass nozzle 10 is simulated and calculated by the outer bypass nozzle module. The shaft 11 is simulated and calculated by the shaft module. The starter is simulated and calculated by the starter module

[0042] As Figure 1 As shown in the figure, this embodiment provides a simulation model for the starting performance of the core engine of a variable cycle engine. The simulation model includes an intake duct module, a CDFS component module, a compressor module, a combustion chamber module, a high-pressure turbine module, a nozzle module, an outer bypass casing module, an outer bypass nozzle module, a starter module, and a shaft module. Among them,

[0043] The intake duct module is used for calculating the total temperature, total pressure, flight speed, and total pressure recovery coefficient at the inlet and outlet of the intake device;

[0044] The CDFS component module includes an adjustable inlet guide vane model for the CDFS, which is used for calculating relevant parameters at the inlet and outlet of the CDFS. The CDFS component module receives the total temperature, total pressure, flight speed, and total pressure recovery coefficient at the inlet and outlet of the intake device calculated by the intake duct module;

[0045] The compressor module includes an adjustable inlet guide vane model for the compressor, which is used for calculating relevant parameters at the inlet and outlet of the compressor. The compressor module receives the relevant parameters of the airflow at the outlet of the CDFS;

[0046] The combustion chamber module is used for calculating relevant parameters at the inlet and outlet of the combustion chamber. The combustion chamber module receives the relevant parameters of the airflow at the outlet of the compressor;

[0047] The high-pressure turbine module includes an adjustable guide vane model, which is used for calculating relevant parameters at the inlet and outlet of the turbine. The high-pressure turbine module receives the relevant parameters of the airflow at the outlet of the combustion chamber;

[0048] The nozzle module is used for calculating relevant parameters of the nozzle inlet and outlet, and the nozzle module receives relevant parameters of the turbine outlet airflow;

[0049] The outer casing module includes a mixer / abrupt expansion loss model. The mixer / abrupt expansion loss model selects different working modes through the switch of the MSV, calculates relevant parameters of the mixer and the pressure loss caused by the abrupt expansion of the area of the front bypass ejector under different working modes, and then obtains relevant parameters of the outer casing outlet. The outer casing module receives the total temperature, total pressure, flight speed, and total pressure recovery coefficient of the inlet and outlet of the intake device calculated by the intake duct module and the relevant parameters of the CDFS inlet and outlet;

[0050] The outer nozzle module is used for calculating relevant parameters of the outer nozzle inlet and outlet, and the outer nozzle module receives the relevant parameters of the outer casing outlet;

[0051] The starter module is used for calculating the output power of the starter;

[0052] The shaft module is used for calculating relevant parameters of the shaft. The shaft module receives the relevant parameters of the CDFS outlet, the relevant parameters of the compressor, the relevant parameters of the turbine inlet and outlet, and the output power of the starter.

[0053] In some embodiments,

[0054] The relevant parameters of the CDFS inlet and outlet include the total pressure / total temperature / flow rate at the inlet and outlet, the CDFS pressure ratio, the CDFS efficiency, and the CDFS power;

[0055] The relevant parameters of the compressor inlet and outlet include the total pressure / total temperature / flow rate at the compressor inlet and outlet, the compressor pressure ratio, the compressor efficiency, and the compressor power;

[0056] The relevant parameters of the combustion chamber inlet and outlet include the total pressure at the combustion chamber inlet and outlet, the total temperature at the combustion chamber inlet and outlet, the flow rate at the combustion chamber inlet and outlet, and the total pressure recovery coefficient at the combustion chamber inlet and outlet;

[0057] The relevant parameters of the turbine inlet and outlet include the total temperature at the turbine inlet and outlet, the total pressure at the turbine inlet and outlet, the flow rate at the turbine inlet and outlet, the expansion ratio at the turbine inlet and outlet, the turbine efficiency, and the turbine power;

[0058] The relevant parameters of the nozzle inlet and outlet include the total pressure of the airflow at the nozzle inlet and outlet, the total temperature of the airflow at the nozzle inlet and outlet, the flow rate of the airflow at the nozzle inlet and outlet, the expansion ratio at the nozzle inlet and outlet, the flow coefficient of the airflow at the nozzle inlet and outlet, the velocity coefficient of the airflow at the nozzle inlet and outlet, and the velocity of the airflow at the nozzle inlet and outlet;

[0059] The relevant parameters of the mixer include the main flow inlet, the secondary flow inlet, and the flow rate / total temperature / total pressure / Mach number at the outlet of the mixing chamber;

[0060] The relevant parameters at the outlet of the outer casing include the total temperature / total pressure / mass flow rate of the airflow at the outlet of the outer casing;

[0061] The relevant parameters at the inlet and outlet of the outer nozzle include the total pressure of the airflow at the inlet and outlet of the outer nozzle, the total temperature of the airflow at the inlet and outlet of the outer nozzle, the mass flow rate of the airflow at the inlet and outlet of the outer nozzle, the expansion ratio of the airflow at the inlet and outlet of the outer nozzle, the flow coefficient of the airflow at the inlet and outlet of the outer nozzle, the velocity coefficient of the airflow at the inlet and outlet of the outer nozzle, and the velocity of the airflow at the inlet and outlet of the outer nozzle;

[0062] The relevant parameters of the shaft include the shaft rotor acceleration and the shaft speed.

[0063] In some embodiments, the data processing method inside the CDFS component module is as follows:

[0064] The influence of the CDFS inlet guide vane adjustment on the reference characteristics is as follows:

[0065]

[0066] In the formula: W, η, and π respectively represent the mass flow rate, efficiency, and pressure ratio; θ represents the deviation between the actual angle of the CDFS inlet guide vane and the reference angle; the subscript 0 represents the reference; k w , k η , k π are respectively the correction factors for the mass flow rate, efficiency, and pressure ratio, k = f(θ, n cor ), n cor is the relative corrected speed of the CDFS.

[0067] In some embodiments, the data processing method inside the compressor module is as follows:

[0068] The influence of the compressor inlet guide vane adjustment on the reference characteristics is as follows:

[0069]

[0070] In the formula: W, η, and π respectively represent the mass flow rate, efficiency, and pressure ratio; θ represents the deviation between the actual angle of the compressor inlet guide vane and the reference angle; the subscript 0 represents the reference; k w , k η , k π are respectively the correction factors for the mass flow rate, efficiency, and pressure ratio, k = f(θ, n cor ), n cor is the relative corrected speed of the compressor.

[0071] In some embodiments, the data processing method inside the high-pressure turbine module is as follows:

[0072] The influence of the adjustable turbine guide vane adjustment on the reference characteristics is as follows:

[0073]

[0074] In the formula, W and η represent flow rate and efficiency respectively; A represents the actual area of the throat of the turbine guide vane; the subscript 0 represents the reference; k W and k η represent the correction factors for flow rate and efficiency.

[0075] In some embodiments,

[0076] When the MSV is open, the mixer / abrupt expansion loss model is regarded as the mixer model and is used to calculate the parameters related to the mixer;

[0077] When the MSV is closed, the mixer / abrupt expansion loss model is regarded as the abrupt expansion loss model and is used to calculate the pressure loss caused by the abrupt expansion of the area of the front bypass ejector.

[0078] In some embodiments, the mathematical model obtained by the simulation model for describing the working state of the core engine is as follows:

[0079]

[0080] In the formula, f1 represents the flow rate balance between the compressor and the turbine, f2 represents the flow rate balance between the turbine and the inner nozzle, f3 represents the flow rate balance between the outer casing and the outer nozzle, n is the physical rotational speed of the rotor, π cd is the CDFS pressure ratio, π c is the compressor pressure ratio, π ht is the high-pressure turbine expansion ratio, w f is the fuel flow rate; α cd is the angle of the inlet guide vane of the CDFS, α c is the angle of the inlet guide vane of the compressor, A ht is the area of the high-pressure turbine guide vane, A FVABI is the area of the front bypass ejector, A MSV is the opening area of the mode selection valve, ΔN H is the remaining power on the shaft, J is the moment of inertia of the rotor rotation, is the rotor acceleration rate.

[0081] Working process:

[0082] During the start-up simulation process, the fuel flow rate w f is determined by the start-up fuel supply law, α cd , α c , A ht , A FVABI , A MSVDetermined by the adjustment plan, so that the mathematical model used to describe the working state of the core engine can be used to determine the state of the core engine at a certain moment during the starting process, which is called the dynamic equilibrium point. The entire starting process is composed of dynamic equilibriums increasing in time steps, so that the starting performance of the core engine under different working modes and different adjustment plans can be obtained.

[0083] In some embodiments, taking the starting performance simulation evaluation of the core engine of a variable cycle engine in a single outer bypass mode as an example, the input of the calculation example is that the mode selection valve is closed (A MSV =0), A ht is the design value of the throat area of the turbine nozzle guide vane (that is, the influence of the turbine nozzle guide vane area on the characteristics is not considered), A FVABI is set as the maximum area of the front bypass ejector, α cd , α c and the starting fuel supply control plan are shown in Figure 3 and Figure 4 respectively. Through the simulation calculation of the established starting performance simulation model of the core engine of the variable cycle engine, the starting performance of the core engine in the single outer bypass mode can be obtained as shown in Figures 5 to 7 .

[0084] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent replacements, and improvements made within the spirit and principle of the present invention shall be included in the protection scope of the present invention. The above is only the preferred implementation manner of the present invention. It should be noted that for those of ordinary skill in the art, without departing from the technical principle of the present invention, several improvements and modifications can still be made, and these improvements and modifications should also be regarded as the protection scope of the present invention.

Claims

1. A simulation model for the starting performance of a variable cycle engine core, characterized in that, The simulation model includes an inlet module, a CDFS component module, a compressor module, a combustor module, a high-pressure turbine module, a nozzle module, an outer casing module, an outer nozzle module, a starter module, and a shaft module. Among them, the inlet module is used for calculating the total temperature, total pressure, flight speed, and total pressure recovery coefficient at the inlet and outlet of the air intake device; the CDFS component module includes an adjustable inlet guide vane model for CDFS, which is used for calculating relevant parameters at the inlet and outlet of CDFS. The CDFS component module receives the total temperature, total pressure, flight speed, and total pressure recovery coefficient at the inlet and outlet of the air intake device calculated by the inlet module; the compressor module includes an adjustable inlet guide vane model for the compressor, which is used for calculating relevant parameters at the inlet and outlet of the compressor. The compressor module receives relevant parameters of the CDFS outlet air flow; the combustor module is used for calculating relevant parameters at the inlet and outlet of the combustor. The combustor module receives relevant parameters of the compressor outlet air flow; the high-pressure turbine module includes an adjustable guide vane model for calculating relevant parameters at the inlet and outlet of the turbine. The high-pressure turbine module receives relevant parameters of the combustor outlet air flow; the nozzle module is used for calculating relevant parameters at the inlet and outlet of the nozzle. The nozzle module receives relevant parameters of the turbine outlet air flow; the outer casing module includes a mixer / abrupt expansion loss model. The mixer / abrupt expansion loss model selects different working modes through the switch of the MSV, calculates relevant parameters of the mixer and the pressure loss caused by the abrupt expansion of the area of the front bypass duct ejector under different working modes, and then obtains relevant parameters at the outlet of the outer casing. The outer casing module receives the total temperature, total pressure, flight speed, and total pressure recovery coefficient at the inlet and outlet of the air intake device calculated by the inlet module and the relevant parameters at the inlet and outlet of CDFS; the outer nozzle module is used for calculating relevant parameters at the inlet and outlet of the outer nozzle. The outer nozzle module receives the relevant parameters at the outlet of the outer casing; the starter module is used for calculating the output power of the starter; the shaft module is used for calculating relevant parameters of the shaft. The shaft module receives relevant parameters at the CDFS outlet, relevant parameters at the inlet and outlet of the compressor, relevant parameters at the inlet and outlet of the turbine, and the output power of the starter.

2. The variable cycle engine core engine starting performance simulation model according to claim 1, wherein the relevant parameters at the inlet and outlet of CDFS include the total pressure / total temperature / flow rate at the inlet and outlet, CDFS pressure ratio, CDFS efficiency, and CDFS power; the relevant parameters at the inlet and outlet of the compressor include the total pressure / total temperature / flow rate at the inlet and outlet of the compressor, compressor pressure ratio, compressor efficiency, and compressor power; the relevant parameters at the inlet and outlet of the combustor include the total pressure at the inlet and outlet of the combustor, the total temperature at the inlet and outlet of the combustor, the flow rate at the inlet and outlet of the combustor, and the total pressure recovery coefficient at the inlet and outlet of the combustor; the relevant parameters at the inlet and outlet of the turbine include the total temperature at the inlet and outlet of the turbine, the total pressure at the inlet and outlet of the turbine, the flow rate at the inlet and outlet of the turbine, the expansion ratio at the inlet and outlet of the turbine, turbine efficiency, and turbine power; The relevant parameters at the inlet and outlet of the nozzle include the total pressure of the inlet and outlet airflows of the nozzle, the total temperature of the inlet and outlet airflows of the nozzle, the mass flow rate of the inlet and outlet airflows of the nozzle, the expansion ratio of the inlet and outlet of the nozzle, the flow coefficient of the inlet and outlet airflows of the nozzle, the velocity coefficient of the inlet and outlet airflows of the nozzle, and the velocity of the inlet and outlet airflows of the nozzle; The relevant parameters of the mixer include the main flow inlet, the secondary flow inlet, and the flow rate / total temperature / total pressure / Mach number at the outlet of the mixing chamber of the mixer; The relevant parameters at the outlet of the outer casing include the total temperature / total pressure / mass flow rate of the airflow at the outlet of the outer casing; The relevant parameters at the inlet and outlet of the outer nozzle include the total pressure of the inlet and outlet airflows of the outer nozzle, the total temperature of the inlet and outlet airflows of the outer nozzle, the mass flow rate of the inlet and outlet airflows of the outer nozzle, the expansion ratio of the inlet and outlet airflows of the outer nozzle, the flow coefficient of the inlet and outlet airflows of the outer nozzle, the velocity coefficient of the inlet and outlet airflows of the outer nozzle, and the velocity of the inlet and outlet airflows of the outer nozzle; The relevant parameters of the shaft include the acceleration of the shaft rotor and the shaft speed.

3. The variable cycle engine core engine starting performance simulation model according to claim 1, characterized in that The data processing method inside the CDFS component module is as follows: The influence of the adjustment of the CDFS inlet guide vane on the reference characteristics is as follows: Wherein: , , respectively represent flow rate, efficiency, and pressure ratio; represents the deviation of the actual angle of the CDFS inlet guide vane from the reference angle; the subscript 0 represents the reference; , , are the correction factors for flow rate, efficiency, and pressure ratio respectively, , is the relative conversion speed of the CDFS.

4. The variable cycle engine core engine starting performance simulation model according to claim 1, wherein The data processing method inside the compressor module is as follows: The influence of the adjustment of the compressor inlet guide vane on the reference characteristics is as follows: In the formula: , , respectively represent flow rate, efficiency, and pressure ratio; represents the deviation between the actual angle of the inlet guide vane of the compressor and the reference angle; the subscript 0 represents the reference; , , are the correction factors for flow rate, efficiency, and pressure ratio respectively, , is the relative converted speed of the compressor.

5. The variable cycle engine core engine starting performance simulation model according to claim 1, wherein The data processing method inside the high-pressure turbine module is as follows: The influence of the adjustment of the turbine variable guide vane on the reference characteristics is as follows: In the formula, and represent flow rate and efficiency respectively; represents the actual area of the throat of the turbine guide vane; the subscript 0 represents the reference; and represent the correction factors of flow rate and efficiency.

6. The variable cycle engine core engine starting performance simulation model according to claim 1, characterized in that When the MSV is opened, the mixer / abrupt expansion loss model is regarded as the mixer model and is used to calculate the relevant parameters of the mixer; When the MSV is closed, the mixer / abrupt expansion loss model is regarded as the abrupt expansion loss model and is used to calculate the pressure loss caused by the abrupt expansion of the area of the front bypass ejector.

7. The variable cycle engine core engine starting performance simulation model according to claim 1, characterized in that The mathematical model obtained by the simulation model for describing the working state of the core engine is as follows: In the formula, represents the flow balance between the compressor and the turbine, represents the flow balance between the turbine and the core nozzle, represents the flow balance between the outer casing and the outer nozzle, is the physical rotational speed of the rotor, is the CDFS pressure ratio, is the compressor pressure ratio, is the high-pressure turbine expansion ratio, is the fuel flow rate; is the CDFS inlet guide vane angle, is the compressor inlet guide vane angle, is the high-pressure turbine guide vane area, is the front bypass ejector area, is the mode selection valve opening area, is the remaining power on the shaft, is the rotor moment of inertia, is the rotor acceleration rate.

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