One-dimensional design method of axial rotating wave partition engine

Abstract

The application provides a one-dimensional design method of an axial flow rotating wave partition engine, and belongs to the technical field of engine design. The one-dimensional design method of the axial flow rotating wave partition engine is characterized in that the compressible flow total static parameter relationship, the velocity triangle relationship, the flow continuity relationship, the shock wave total pressure recovery relationship, the combustion energy conservation relationship and the turbine expansion one-dimensional relationship are combined to achieve the interface matching among the rotating wave compression rotor, the annular center stationary body type trapped vortex combustion chamber and the partition type turbine. Firstly, the input parameters of the whole engine are established, and then the parameter transmission and closed solution are carried out according to the actual connection sequence of the components: the one-dimensional design of the compressor, the one-dimensional design of the combustion chamber and the one-dimensional design of the partition type turbine are sequentially carried out. The parameter closed solution of the axial flow rotating wave partition engine from the compressor to the turbine is realized, and a complete and systematic one-dimensional overall design system is formed.

Description

Technical Field

[0001] This invention belongs to the field of engine design technology, specifically relating to a one-dimensional design method for an axial-flow rotating wave baffle engine. Background Technology

[0002] Axial-flow rotating wave baffle engines arrange the compression, combustion, and expansion thermodynamic processes in series along the axial direction. During engineering design, a one-dimensional design is typically performed first to establish end-to-end parameter matching, determining the engine's basic framework and core parameters, such as flow channel geometry, number of component stages, overall length, and axial load distribution. This forms the foundation and starting point for the entire engine design system. Simultaneously, it provides crucial boundary conditions and initial estimates for subsequent, more precise two-dimensional and three-dimensional designs, effectively guiding refined design and reducing overall R&D costs and risks.

[0003] Because the components of an axial-flow rotating wave deflector engine are relatively independent in physical space, existing one-dimensional designs mostly focus on single-component design or prototype verification. This involves first providing overall parameters, then establishing one-dimensional or mean-line models for the compressor, combustion chamber, and turbine separately, and calculating parameters for each side. However, when designing components independently, mismatches can easily occur in parameter transfer between the compressor outlet, combustion chamber inlet / outlet, and turbine inlet, leading to disconnected design results. This necessitates repeated adjustments using three-dimensional CFD or prototype testing, resulting in low design iteration efficiency. Summary of the Invention

[0004] To address the shortcomings of existing technologies in the one-dimensional design of axial-flow rotating wave baffle engines, this invention provides a one-dimensional design method for axial-flow rotating wave baffle engines.

[0005] To achieve the above objectives, the present invention provides the following technical solution: A one-dimensional design method for an axial-flow rotating wave baffle engine, the axial-flow rotating wave baffle engine comprising a rotating ram compressor, an annular central resident vortex combustion chamber, and a baffle turbine arranged sequentially along the airflow direction, characterized in that the method includes the following steps: Obtain the global design parameters of the axial-flow rotating wave baffle engine; Based on global design parameters, the rotary ram compressor performs parameter calculations for the adjustable guide vanes before the compressor rotor, the rotor inlet to throat, the throat to outlet, and the rear stationary vane, according to the actual airflow channel sequence, to obtain the aerodynamic parameter set at the compressor outlet. This parameter set at the compressor outlet is then used as the inlet boundary condition for the annular central evaporative vortex combustor. Combined with a preset combustion process parameter set, the energy conservation relationship of the combustor is solved to output the thermodynamic parameter set and gas parameter set at the outlet of the annular central evaporative vortex combustor. Finally, this thermodynamic and gas parameter set is used as the inlet boundary condition for the diaphragm turbine. The parameters for the guide vane cascade before expansion, the rotor parameters, and the rear stationary vane parameters are calculated sequentially, outputting the thermodynamic, aerodynamic, and geometric parameter sets for key sections in the diaphragm turbine. The set of parameters sequentially transferred between the rotary ram compressor, the annular central vortex combustion chamber, and the diaphragm turbine is taken as the one-dimensional design result of the whole machine.

[0006] Preferably, the rotary ram compressor performs calculations of the adjustable guide vane parameters before the compressor rotor, the parameters from the rotor inlet to the throat, the parameters from the throat to the outlet, and the parameters of the rear stationary vane according to the actual airflow channel sequence to obtain the aerodynamic parameter set of the compressor outlet. Specifically, this includes the following steps: Import the global design parameters, construct a velocity triangle based on the inlet boundary conditions and the target airflow angle, calculate and output the aerodynamic parameter set at the guide vane outlet; Based on the aforementioned guide vane outlet parameter set, calculate the throat shock wave parameters, and output the throat characteristic parameter set by combining the flow balance and adiabatic relationship. Based on the throat characteristic parameter set, a total pressure recovery coefficient for the diffuser section is introduced. The rotor outlet parameter set is calculated and output using the flow balance and adiabatic flow relationship. The total pressure recovery coefficient of the adjustable guide vane before the compression rotor is determined according to the speed loss coefficient of the adjustable guide vane. The total pressure at the outlet of the adjustable guide vane before the compression rotor is equal to the total pressure at the inlet of the adjustable guide vane before the compression rotor multiplied by the total pressure recovery coefficient. Using the rotor outlet parameter set as the inlet boundary condition of the rear stator, and combining it with the preset rear stator velocity loss coefficient, the aerodynamic parameter set of the compressor outlet is calculated.

[0007] Preferably, the parameter set at the compressor outlet is used as the inlet boundary condition of the annular central stationary vortex combustor. Specifically, it takes the outlet parameters of the rotary ram compressor's post-stationary vanes, uses the total outlet temperature of the rotary ram compressor as the total inlet temperature of the combustor, and uses the total outlet pressure of the rotary ram compressor as the total inlet pressure of the combustor.

[0008] Preferably, the thermodynamic parameter set and gas parameter set of the annular central evaporative vortex combustor outlet are output based on the energy conservation relationship of the combustion chamber, specifically including the following processing steps: The system reads the preset combustion efficiency and total pressure recovery coefficient, calculates the fuel flow rate based on the air mass flow rate, actual air-fuel ratio, stoichiometric air-fuel ratio, and equivalence ratio, and then superimposes the results to obtain the gas mass flow rate. Based on the energy conservation equation, it calculates and outputs the total temperature at the outlet of the annular central evaporative vortex combustor by combining the specific heat capacity of air at constant pressure and the specific heat capacity of gas at constant pressure. Based on the total pressure recovery relationship, it calculates and outputs the total pressure at the outlet of the annular central evaporative vortex combustor by combining the inlet total pressure, and outputs the thermodynamic parameter set and gas parameter set at the outlet of the annular central evaporative vortex combustor. Among these parameters, the fuel flow rate is derived from the relationship between the air flow rate, stoichiometric air-fuel ratio, and equivalence ratio, and the gas flow rate is determined by the sum of the air flow rate and the fuel flow rate.

[0009] Preferably, using the thermodynamic parameter set and the gas parameter set as the inlet boundary conditions of the diaphragm turbine specifically means using the total outlet temperature and total outlet pressure of the annular central evaporative vortex combustion chamber as the total inlet temperature and total inlet pressure of the one-dimensional design of the diaphragm turbine.

[0010] Preferably, the global design parameters specifically include: inlet air mass flow rate, inlet total temperature, inlet total pressure, rotor speed, velocity loss coefficient of the adjustable guide vanes before the compression rotor and the inlet guide vanes of the expansion rotor, velocity loss coefficient of the rear stationary vanes, total pressure recovery coefficient of the combustion chamber, average rotor inlet radius, rotor flow coefficient, absolute airflow angle at the rotor inlet, adiabatic index, gas constant, rotor inlet-outlet area ratio, rotor throat length-to-diameter ratio, absolute airflow angle at the compressor outlet, and absolute Mach number at the compressor outlet.

[0011] Preferably, the method further includes verifying the one-dimensional design results of the whole machine by calculating whether the mass conservation, energy conservation, power matching and back pressure matching are satisfied. If satisfied, the design is completed; if not satisfied, the design parameters are changed and the calculation is re-executed until the one-dimensional design results of the whole machine are self-consistent and closed.

[0012] This invention also provides a one-dimensional design system for an axial-flow rotating wave deflector engine, specifically comprising: The input module is used to obtain the global design parameters of the axial-flow rotating wave baffle engine.

[0013] A closed-loop calculation module is used to calculate the parameters of the adjustable guide vanes before the compressor rotor, the parameters from the rotor inlet to the throat, the parameters from the throat to the outlet, and the parameters of the rear stationary vanes, based on global design parameters and in the actual airflow channel sequence, to obtain the aerodynamic parameter set at the compressor outlet. This parameter set at the compressor outlet is then used as the inlet boundary condition for the annular central evaporative vortex combustor. Combined with a preset combustion process parameter set, the module solves the energy conservation relationship of the combustor to output the thermodynamic parameter set and gas parameter set at the outlet of the annular central evaporative vortex combustor. Finally, this thermodynamic and gas parameter set is used as the inlet boundary condition for the diaphragm turbine. The module then sequentially calculates the parameters of the guide vane cascade before expansion, the rotor parameters, and the rear stationary vane parameters, outputting the thermodynamic, aerodynamic, and geometric parameter set for key sections in the diaphragm turbine. The set of parameters sequentially transferred between the rotary ram compressor, the annular central vortex combustion chamber, and the diaphragm turbine is taken as the one-dimensional design result of the whole machine.

[0014] The one-dimensional design method for an axial-flow rotating wave baffle engine provided by this invention has the following beneficial effects: This invention, based on the energy transfer sequence of compression, combustion, and expansion, connects three core components in series: a rotary ram compressor, an annular central vortex combustor, and a diaphragm turbine, performing coupled calculations on each component along the airflow direction. Forced geometric inheritance between components ensures that key component parameters are passively determined entirely by upstream inflow parameters. By directly using the upstream component's outlet geometry as the downstream component's inlet geometry, a smooth axial transition and physical spatial compatibility of the entire engine flow path are guaranteed, transforming post-processing adjustments into pre-processing design margins. It also ensures that the engine's overall thermodynamic state conforms to physical laws during compression heating, combustion heating, and expansion power generation, guaranteeing thermodynamic parameter consistency. This forms a closed-loop one-dimensional design, effectively avoiding the problem of mismatched interface parameters between components. Rapidly and systematically acquiring aerodynamic and geometric parameters of key cross-sections of the entire engine in the early stages of engine development effectively shortens the engine development cycle. Attached Figure Description

[0015] To more clearly illustrate the embodiments and design schemes of the present invention, the accompanying drawings required for this embodiment will be briefly described below. The drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0016] Figure 1 This is a flowchart of a one-dimensional design method for an axial-flow rotating wave baffle engine according to the present invention.

[0017] Figure 2 This is a flow diagram of an axial-flow rotating wave baffle engine in an embodiment of the present invention.

[0018] Figure 3 This is a schematic diagram of the axial-flow rotating wave baffle engine in an embodiment of the present invention.

[0019] Figure 4 This is a schematic diagram of the flow path of the axial-flow rotating wave baffle engine in an embodiment of the present invention.

[0020] Figure 5 This is a schematic diagram of the velocity triangle from the inlet to the throat of the rotary stamping compression rotor in an embodiment of the present invention.

[0021] Figure 6 This is a schematic diagram of the velocity triangle from the throat of the rotary stamping and compression rotor to the outlet of the rotary stamping and compression rotor in an embodiment of the present invention.

[0022] Figure 7 This is a schematic diagram of the velocity triangle of the diaphragm turbine rotor in an embodiment of the present invention.

[0023] Among them, 1: intake duct; 2: adjustable inlet guide vane; 3: rotary ram air compressor rotor; 4: compressor rotor outlet stator vane; 5: annular central vortex combustion chamber; 6: diaphragm turbine inlet guide vane grating; 7: expansion rotor; 8: expansion rotor outlet stator vane; 9: tail spray exhaust. Detailed Implementation

[0024] To enable those skilled in the art to better understand and implement the technical solutions of the present invention, the present invention will be described in detail below with reference to the accompanying drawings and specific embodiments. The following embodiments are only used to more clearly illustrate the technical solutions of the present invention and should not be construed as limiting the scope of protection of the present invention.

[0025] Example The axial-flow rotating wave deflector engine to be designed in this embodiment is as follows: Figure 3As shown, the single-rotor structure, along the airflow direction, includes, in sequence, an intake duct 1, adjustable guide vanes 2, a compression rotor 3, a first outlet stator vane 4, a combustion chamber 5, a guide vane 6, an expansion rotor 7, a second outlet stator vane 8, and an exhaust section 9. The intake duct 1 introduces air, and the adjustable guide vanes 2 regulate the direction of the inlet airflow; the compression rotor 3 pressurizes the airflow, and the first outlet stator vane 4 diffuses and guides the compressed airflow; the combustion chamber 5 organizes fuel combustion, and the guide vane 6 adjusts the speed and direction of the high-temperature combustion gas; the expansion rotor 7 utilizes the expansion of the combustion gas to do work and is coaxially connected to the compression rotor 3; the second outlet stator vane 8 rectifies the exhaust gas, which is finally discharged through the exhaust section 9. Air enters the compression rotor after pre-swirl via the adjustable guide vanes, where it is pressurized through oblique shock waves and diffusion within the rotating flow channel; it then enters the vortex combustion chamber, mixes with the fuel, and undergoes stable combustion. The high-temperature, high-pressure combustion gas enters the expansion rotor via the guide vane 6, where it expands and accelerates within the convergent, throat, and expansion flow channels, driving the rotor to do work and simultaneously providing driving force for the compression rotor. This structure features a continuous air path, simple transmission, small axial dimension, few parts, and high power density.

[0026] The one-dimensional design process of a compressor includes four stages: calculation of the adjustable guide vanes before the compressor rotor, calculation from the rotor inlet to the throat, calculation from the throat to the outlet, and calculation of the rear stationary vanes. For example... Figure 2 As shown, in the calculation stage of the adjustable guide vane in front of the compression rotor, a velocity triangle is established based on the inlet boundary conditions and the target airflow angle to obtain the rotor inlet circumferential velocity, rotor inlet absolute velocity axial component, rotor inlet absolute velocity, rotor inlet total temperature, rotor inlet total pressure, rotor inlet static temperature, rotor inlet static pressure, inlet cross-sectional area of ​​the adjustable guide vane in front of the compression rotor, and upper and lower end wall radii.

[0027] Based on this, the present invention provides a one-dimensional design method for an axial-flow rotating wave baffle engine, such as... Figure 1 As shown, the specific steps include: Step 1: Establish the overall design input parameters. Input parameters include the inlet air mass flow rate (m) and inlet total temperature of the rotary ram compressor. T 1 * Imported total pressure P 1 * Rotor speed n, and the speed loss coefficient of the adjustable guide vanes before the compressor rotor. φ 1 , velocity loss coefficient of stationary blades after compressor rotor outlet φ 2 Velocity loss coefficient of the inlet guide vane cascade of the expansion rotor φ 6 Combustion chamber total pressure recovery coefficient σ b Rotor inlet average radius R midRotor flow coefficient ϕ Absolute airflow angle at the compressor rotor inlet Absolute airflow angle at the inlet of the expansion rotor Adiabatic index k, gas constant R, and inlet / outlet area ratio of the compressor rotor Length-to-diameter ratio of the compression rotor throat absolute airflow angle at compressor outlet and the absolute speed Mach number at the compressor outlet .

[0028] Step 2: One-dimensional design of the compressor.

[0029] (1) Circumferential velocity of the adjustable guide vane outlet before the compression rotor: ; Axial component of absolute velocity at the outlet of the adjustable guide vane before the compression rotor: Absolute velocity at the outlet of the adjustable guide vane before the compressor rotor: Total outlet temperature of the adjustable guide vanes before the compressor rotor: ; Velocity coefficient at the outlet of the adjustable guide vane before the compressor rotor: The lossless theoretical speed coefficient at the outlet of the adjustable guide vane before the compressor rotor is: Total pressure recovery coefficient of the adjustable guide vanes before the compressor rotor: Total outlet pressure of the adjustable guide vanes before the compressor rotor: Adjustable guide vane outlet static temperature before compressor rotor: The static pressure at the outlet of the adjustable guide vane before the compressor rotor is: Adjustable guide vane inlet speed before the compressor rotor (axial intake): ;Stationary blade inlet velocity coefficient: ; Static temperature at the inlet of the leaf: Static pressure at the inlet of the stationary vane: ; Cross-sectional area of ​​the stationary blade inlet: The upper wall radius of the adjustable guide vane inlet before the compressor rotor: The lower end wall radius of the adjustable guide vane inlet before the compressor rotor: .

[0030] in The average radius of the adjustable guide vane outlet before the compression rotor. The rotor speed, To adjust the total inlet temperature of the guide vanes before the compressor rotor, To compress the total pressure at the inlet of the adjustable guide vane before the rotor, The rotor flow coefficient, The absolute airflow angle at the rotor inlet. The adiabatic index, The gas constant is For airflow, The variable guide vane velocity loss coefficient is used to measure the speed loss of the compressor rotor.

[0031] (2) During the calculation stage from the rotor inlet to the throat, combined with Figure 5 The velocity triangle is used to obtain the relative total temperature, relative total pressure, relative Mach number, relative velocity coefficient, relative velocity, and shock wave cumulative relative total pressure recovery coefficient after the normal shock wave in the throat. Then, the initial throat contraction ratio is determined by combining the flow balance relationship and the adiabatic relationship, and the actual throat contraction ratio is output. The throat area, average throat radius, throat static temperature, throat static pressure, throat total temperature, and throat total pressure are further obtained.

[0032] Rotor inlet absolute speed: ; Axial component of absolute velocity at the inlet of the rotary stamping compressor rotor: Rotary stamping compression rotor inlet cross-sectional area: Radius of the upper end wall of the rotary stamping compressor rotor inlet: Radius of the lower end wall of the rotary stamping compressor rotor inlet: Relative airflow angle at the inlet of the rotary press compressor rotor: ; Partition installation angle: = Relative velocity at the inlet of the rotary stamping compressor rotor: ; Relative Mach number at the entrance: Inlet relative velocity factor: ; Relative total temperature at the inlet: Inlet relative total pressure: ; by flow balancing adiabatic process The initial laryngeal contraction ratio was obtained: The actual throat contraction ratio amplified by supercritical treatment was obtained: Throat area: Radius of the lower end wall of the throat: Radius of the upper wall of the throat: = Average radius of the throat: ; Let the relative airflow angle at the throat be: The angle between the relative velocity of the throat and the circumferential velocity is: Circumferential velocity of the throat: ; Axial component of absolute velocity at the throat: Throat temperature: ;Laryngeal static pressure: Total absolute temperature of the throat: = Total absolute pressure in the larynx: = .

[0033] (3) In the throat-to-exit calculation stage, combined with Figure 6The velocity triangle introduces the total pressure recovery coefficient of the diffuser section of the compressor rotor, and obtains the outlet relative total pressure, outlet relative velocity coefficient, outlet relative velocity, outlet static temperature, outlet static pressure, outlet upper and lower end wall radii, outlet average radius, outlet absolute velocity, outlet total temperature, outlet total pressure, outlet absolute velocity coefficient, and outlet absolute airflow angle based on the flow balance and adiabatic flow relationship.

[0034] Relative total pressure at rotor outlet: ; By flow balancing And it is an adiabatic process. = ; ; Derive the rotor outlet relative velocity coefficient Rotor outlet relative velocity: = Rotor outlet static temperature: Outlet static pressure: ;Outlet lower end wall radius: ;Outlet upper wall radius: = Average export radius: Let the relative airflow angle at the outlet be: The angle between the exit relative velocity and the circumferential velocity is: Export circumferential speed: Absolute export velocity: Total temperature at the exit: Total export pressure: Export absolute speed coefficient: Exit absolute airflow angle: .

[0035] (4) In the calculation stage of the rear stationary blade, the compressor rotor outlet parameters are used as the inlet conditions of the rear stationary blade. Combined with the rear stationary blade velocity loss coefficient, the compressor rear stationary blade outlet velocity, the rear stationary blade total pressure recovery coefficient, the compressor outlet total temperature, the compressor outlet total pressure, the compressor outlet static temperature, the compressor outlet static pressure, the compressor outlet area, and the corresponding upper and lower end wall radii are obtained, thereby completing the one-dimensional design of the compressor.

[0036] Compressor outlet total temperature: ; Radius of the lower end wall of the rear stationary blade inlet: ; Radius of the upper wall of the rear stator inlet: ; Rear stationary blade exit velocity coefficient: ; Rear stationary blade exit velocity: Theoretical zero-loss velocity coefficient at the compressor outlet: ; Total pressure recovery coefficient of the rear stationary vane: Total compressor outlet pressure: Compressor outlet static temperature: Compressor outlet static pressure: ; Balanced by flow: Calculate the compressor outlet area: Compressor outlet upper wall radius: Compressor outlet lower end wall radius: .

[0037] Step 3: One-dimensional design of the combustion chamber. Utilizing the compressor's post-stationary vane outlet parameters, the compressor outlet total temperature is used as the combustion chamber inlet total temperature, and the compressor outlet total pressure is used as the combustion chamber inlet total pressure. Simultaneously, the compressor total pressure ratio, air mass flow rate, combustion chamber inlet airflow angle, and combustion chamber outlet airflow angle are read. Combustion efficiency and the combustion chamber total pressure recovery coefficient are set in the design. Fuel flow rate is determined by air flow rate, actual air-fuel ratio, stoichiometric air-fuel ratio, and equivalence ratio. Gas flow rate is determined by the sum of air flow rate and fuel flow rate. The combustion chamber outlet total temperature is obtained based on the combustion chamber energy conservation relationship using the following formula:

[0038] ; in, For air quality flow rate, For fuel mass flow rate, For the compressor outlet total temperature, For the total temperature at the combustion chamber outlet, The specific heat capacity of air at constant pressure, The specific heat at constant pressure of the combustion gas is used. The total pressure at the combustion chamber outlet is obtained based on the total pressure recovery relationship, which is the total pressure at the turbine inlet. The total temperature at the combustion chamber outlet is the total temperature at the inlet of the diaphragm turbine section.

[0039] Step 4: One-dimensional design of the diaphragm turbine section. Utilizing the combustion chamber outlet parameters, the total temperature and pressure at the combustion chamber outlet, and the gas mass flow rate are used as the inlet boundary conditions for the diaphragm turbine section. Calculations are then performed in conjunction with the average rim radius, rotational speed, absolute inlet flow angle, and relative inlet flow angle. The one-dimensional design of the diaphragm turbine section sequentially includes calculations of the pre-expansion stator and rotor inlet, the diaphragm turbine rotor outlet, and the post-expansion stator.

[0040] (1) In the calculation stage of the stator blade and rotor inlet before expansion, combined with Figure 7 The velocity triangle is used to obtain the rotor inlet circumferential velocity, rotor inlet absolute velocity axial component, rotor inlet absolute velocity, rotor inlet total temperature, rotor inlet total pressure, rotor inlet static temperature, and rotor inlet static pressure. At the same time, the inlet cross-sectional area, inlet outer diameter, inlet inner diameter, inlet relative velocity, inlet relative airflow angle, inlet relative Mach number, inlet relative velocity factor, inlet relative total temperature, and inlet relative total pressure are determined based on the flow balance relationship.

[0041] The inlet parameters of the front stator vane are derived from the geometry and aerodynamic parameters of the combustion chamber outlet. The circumferential velocity at the front stator vane outlet is: ; Axial component of absolute velocity at the front stator exit: Absolute velocity at the front stator exit: Total temperature at the outlet of the front static blade: ; Velocity coefficient at the front stator exit: The lossless theoretical velocity coefficient at the front stator exit is: The total pressure recovery coefficient of the front static vane is: Total pressure at the front stationary vane outlet: Static temperature at the outlet of the front static blade: Static pressure at the front stator outlet: Rotor inlet cross-sectional area: Rotor inlet outer diameter: ;Inlet inner diameter: Rotor inlet relative velocity: Inlet relative airflow angle: ;Entrance relative Mach number: Inlet relative velocity factor: ; Relative total temperature at the inlet: Inlet relative total pressure: .

[0042] (2) In the calculation stage of the turbine rotor outlet of the baffle, it is assumed that the airflow in the flow channel satisfies the flow balance relationship and is approximately adiabatic flow. After introducing the total pressure recovery coefficient, the outlet relative velocity factor, outlet relative velocity, outlet absolute velocity, outlet static temperature, outlet static pressure, outlet absolute Mach number, outlet absolute airflow angle, outlet absolute velocity factor, outlet absolute total temperature and outlet absolute total pressure are obtained.

[0043] The outlet formula uses the principles of flow balance and adiabatic flow. The airflow within the channel is an adiabatic flow. Total pressure recovery coefficient: ; Calculate the relative velocity factor at the exit. Rotor outlet static temperature: Rotor outlet static pressure: Rotor outlet relative velocity: Rotor outlet absolute velocity: Rotor outlet absolute Mach number: Rotor outlet absolute airflow angle: Rotor outlet absolute speed factor: Rotor outlet absolute total temperature: Rotor outlet absolute total pressure: .

[0044] (3) In the calculation stage of the rear stationary blade after expansion, the outlet parameters of the diaphragm turbine rotor are used as the inlet parameters of the rear stationary blade. The absolute Mach number, static temperature, absolute velocity, static pressure, and total pressure at the outlet of the rear stationary blade are further obtained. The inlet parameters of the rear stationary blade are taken from the rotor outlet parameters. Total temperature at the outlet of the rear stationary blade: Absolute Mach number at the exit of the rear stationary blade: Static temperature at the outlet of the rear leaf: Static pressure at the rear stationary vane outlet: Total pressure at the rear stationary vane outlet: .in, T i * The absolute total temperature of the i-th cross section P i * Let be the absolute total pressure at section i. Complete the one-dimensional design of the entire engine, from the compressor to the combustion chamber and then to the diaphragm turbine. Output the full process parameters as the one-dimensional design result of the entire engine.

[0045] Taking a certain axial-flow rotating wave baffle engine as an example, given a converted speed of 2906.19 ( ), equivalent to a flow rate of 0.277 ( The adjustable guide vane outlet Mach number is controlled between 0.7 and 0.9, stabilizing the rotor inlet relative Mach number in the range of 2 to 2.7. The absolute airflow angle at the inlet of the rotary ram compressor rotor ranges from 50° to 70°, and the relative airflow angle ranges from 7° to 15°.

[0046] This invention also provides a one-dimensional design system for an axial-flow rotating wave deflector engine, specifically comprising: The input module is used to obtain the global design parameters of the axial-flow rotating wave baffle engine.

[0047] The closed-loop calculation module is used to calculate the parameters of the adjustable guide vanes before the compressor rotor, the parameters from the rotor inlet to the throat, the parameters from the throat to the outlet, and the parameters of the rear stationary vanes of the rotary ram compressor according to the actual airflow channel sequence based on global design parameters, thereby obtaining the aerodynamic parameter set of the compressor outlet. The parameter set of the compressor outlet is used as the inlet boundary condition of the annular central evaporative vortex combustor. Combined with the preset combustion process parameter set, the module solves the problem according to the energy conservation relationship of the combustor, and outputs the thermodynamic parameter set and gas parameter set of the annular central evaporative vortex combustor outlet. The thermodynamic parameter set and gas parameter set are used as the inlet boundary condition of the diaphragm turbine. The module calculates the parameters of the guide vane cascade before expansion, the rotor parameters, and the rear stationary vane parameters in sequence, and outputs the thermodynamic, aerodynamic, and geometric parameter sets of key sections in the diaphragm turbine. The set of parameters sequentially transferred between the rotary ram compressor, the annular central vortex combustion chamber, and the diaphragm turbine is taken as the one-dimensional design result of the whole machine.

[0048] The modules in the aforementioned one-dimensional design system for an axial-flow rotating wave baffle engine can be implemented entirely or partially through software, hardware, or a combination thereof. These modules can be embedded in or independent of the processor in a computer device, or stored in the memory of a computer device as software, so that the processor can call and execute the corresponding operations of each module.

[0049] It should be noted that the specific embodiments described above enable those skilled in the art to more fully understand the present invention, but do not limit the present invention in any way. Therefore, although the present invention has been described in detail in this specification and embodiments, those skilled in the art should understand that modifications or equivalent substitutions can still be made to the present invention; and all technical solutions and improvements that do not depart from the spirit and scope of the present invention are covered within the protection scope of the present invention patent. No reference numerals in the claims should be construed as limiting the scope of the claims. Any simple variations or equivalent substitutions of technical solutions that can be readily obtained by those skilled in the art within the scope of the technology disclosed in the present invention are within the protection scope of the present invention.

Claims

1. A one-dimensional design method for an axial-flow rotating wave baffle engine, the axial-flow rotating wave baffle engine comprising a rotating ram compressor, an annular central vortex combustion chamber, and a baffle turbine arranged sequentially along the airflow direction, characterized in that, The method includes the following steps: Obtain the global design parameters of the axial-flow rotating wave baffle engine; Based on global design parameters, the rotary ram compressor performs parameter calculations for the adjustable guide vanes before the compressor rotor, the rotor inlet to throat, the throat to outlet, and the rear stationary vane, according to the actual airflow channel sequence, to obtain the aerodynamic parameter set at the compressor outlet. This parameter set at the compressor outlet is then used as the inlet boundary condition for the annular central evaporative vortex combustor. Combined with a preset combustion process parameter set, the energy conservation relationship of the combustor is solved to output the thermodynamic parameter set and gas parameter set at the outlet of the annular central evaporative vortex combustor. Finally, this thermodynamic and gas parameter set is used as the inlet boundary condition for the diaphragm turbine. The parameters for the guide vane cascade before expansion, the rotor parameters, and the rear stationary vane parameters are calculated sequentially, outputting the thermodynamic, aerodynamic, and geometric parameter sets for key sections in the diaphragm turbine. The set of parameters sequentially transferred between the rotary ram compressor, the annular central vortex combustion chamber, and the diaphragm turbine is taken as the one-dimensional design result of the whole machine.

2. The one-dimensional design method for an axial-flow rotating wave baffle engine according to claim 1, characterized in that, The rotary ram compressor calculates the parameters of the adjustable guide vanes before the compressor rotor, the parameters from the rotor inlet to the throat, the parameters from the throat to the outlet, and the parameters of the rear stationary vanes according to the actual airflow channel sequence, to obtain the set of aerodynamic parameters at the compressor outlet. This specifically includes the following steps: Import the global design parameters, construct a velocity triangle based on the inlet boundary conditions and the target airflow angle, calculate and output the aerodynamic parameter set at the guide vane outlet; Based on the aforementioned guide vane outlet parameter set, calculate the throat shock wave parameters, and output the throat characteristic parameter set by combining the flow balance and adiabatic relationship. Based on the throat characteristic parameter set, a total pressure recovery coefficient for the diffuser section is introduced. The rotor outlet parameter set is calculated and output using the flow balance and adiabatic flow relationship. The total pressure recovery coefficient of the adjustable guide vane before the compression rotor is determined according to the speed loss coefficient of the adjustable guide vane. The total pressure at the outlet of the adjustable guide vane before the compression rotor is equal to the total pressure at the inlet of the adjustable guide vane before the compression rotor multiplied by the total pressure recovery coefficient. Using the rotor outlet parameter set as the inlet boundary condition of the rear stator, and combining it with the preset rear stator velocity loss coefficient, the aerodynamic parameter set of the compressor outlet is calculated.

3. The one-dimensional design method for an axial-flow rotating wave baffle engine according to claim 2, characterized in that, The parameter set at the compressor outlet is used as the inlet boundary condition of the annular central stagnant vortex combustor. Specifically, it takes the outlet parameters of the rotary ram compressor's stator vanes, uses the total temperature at the rotary ram compressor outlet as the total temperature at the combustor inlet, and uses the total pressure at the rotary ram compressor outlet as the total pressure at the combustor inlet.

4. The one-dimensional design method for an axial-flow rotating wave baffle engine according to claim 1, characterized in that, Based on the energy conservation relationship of the combustion chamber, the thermodynamic parameter set and gas parameter set of the outlet of the annular central evaporative vortex combustion chamber are output. The specific processing steps include the following: Read the preset combustion efficiency and total pressure recovery coefficient, calculate the fuel flow rate based on the air mass flow rate, actual air-fuel ratio, stoichiometric air-fuel ratio and equivalence ratio, and superimpose to obtain the gas mass flow rate; based on the energy conservation equation, calculate and output the total outlet temperature of the annular central evaporative vortex combustor by combining the specific heat capacity of air at constant pressure and the specific heat capacity of gas at constant pressure. Based on the total pressure recovery relationship, the total pressure at the outlet of the annular central evaporative vortex combustor is calculated and output in conjunction with the inlet total pressure. The thermodynamic parameter set and gas parameter set at the outlet of the annular central evaporative vortex combustor are also output. Among them, the fuel flow rate is derived from the relationship between the air flow rate, stoichiometric fuel-air ratio and equivalence ratio, and the gas flow rate is determined by the sum of the air flow rate and the fuel flow rate.

5. The one-dimensional design method for an axial-flow rotating wave baffle engine according to claim 1, characterized in that, Using the thermodynamic parameter set and gas parameter set as the inlet boundary conditions of the diaphragm turbine specifically means using the total outlet temperature and total outlet pressure of the annular central evaporative vortex combustion chamber as the total inlet temperature and total inlet pressure of the one-dimensional design of the diaphragm turbine.

6. The one-dimensional design method for an axial-flow rotating wave baffle engine according to claim 1, characterized in that, The specific global design parameters include: inlet air mass flow rate, inlet total temperature, inlet total pressure, rotor speed, velocity loss coefficient of the adjustable guide vanes at the front of the compression rotor and the inlet guide vanes of the expansion rotor, velocity loss coefficient of the rear stationary vanes, total pressure recovery coefficient of the combustion chamber, average rotor inlet radius, rotor flow coefficient, absolute airflow angle at the rotor inlet, adiabatic index, gas constant, rotor inlet-outlet area ratio, rotor throat length-to-diameter ratio, absolute airflow angle at the compressor outlet, and absolute speed Mach number at the compressor outlet.

7. The one-dimensional design method for an axial-flow rotating wave baffle engine according to claim 1, characterized in that, It also includes verifying the one-dimensional design results of the whole machine by calculating whether the mass conservation, energy conservation, power matching and back pressure matching are satisfied. If satisfied, the design is completed; if not satisfied, the design parameters are changed and the calculation is re-executed until the one-dimensional design results of the whole machine are self-consistent and closed.

8. A one-dimensional design system for an axial-flow rotating wave baffle engine, characterized in that, include: The input module is used to obtain the global design parameters of the axial-flow rotating wave baffle engine; A closed-loop calculation module is used to calculate the parameters of the adjustable guide vanes before the compressor rotor, the parameters from the rotor inlet to the throat, the parameters from the throat to the outlet, and the parameters of the rear stationary vanes, based on global design parameters and in the actual airflow channel sequence, to obtain the aerodynamic parameter set at the compressor outlet. This parameter set at the compressor outlet is then used as the inlet boundary condition for the annular central evaporative vortex combustor. Combined with a preset combustion process parameter set, the module solves the energy conservation relationship of the combustor to output the thermodynamic parameter set and gas parameter set at the outlet of the annular central evaporative vortex combustor. Finally, this thermodynamic and gas parameter set is used as the inlet boundary condition for the diaphragm turbine. The module then sequentially calculates the parameters of the guide vane cascade before expansion, the rotor parameters, and the rear stationary vane parameters, outputting the thermodynamic, aerodynamic, and geometric parameter set for key sections in the diaphragm turbine. The set of parameters sequentially transferred between the rotary ram compressor, the annular central vortex combustion chamber, and the diaphragm turbine is taken as the one-dimensional design result of the whole machine.

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