TBCC air inlet duct external pressure section air inlet duct design method and system based on optimal wave system design theory

Abstract

The invention discloses a TBCC air inlet channel external pressure section air inlet channel design method and system based on the optimal wave system design theory, and belongs to the technical field of turbine-based combined cycle air inlet channels. For the external pressure section of the binary stamping air inlet channel, the optimal wave system design theory is utilized to meet the requirement for compression efficiency, the requirement for low total pressure loss and the requirement for flow of the air inlet channel; zero-dimensional design is adopted, the design of an external pressure section is carried out by a non-stick shock wave relational expression, and correction of a boundary layer is assisted. The method is used for solving the problems that in the prior art, at a non-design point, a shock wave system structure may deteriorate, so that the total pressure of an air inlet channel is recovered and suddenly reduced, flow capture is insufficient, and even starting failure is caused, and the problem that when the Mach number is high, the performance is poor due to insufficient compression or too large shock wave loss is possibly solved.

Description

Technical Field

[0001] This invention belongs to the field of turbine-based combined cycle inlet technology, specifically relating to a design method and system for the external pressure section of a TBCC inlet based on the optimal wave system design theory. Background Technology

[0002] Turbine-Based Combined Cycle (TBCC) engines, as the core power plant for future hypersonic vehicles, need to operate efficiently and reliably across a wide range of flight Mach numbers. Their air intakes, as the primary component capturing incoming air and providing a stable, high-quality airflow to the subsequent combustion chamber, directly impact the efficiency and stability of the entire propulsion system. The design of the external pressure section is particularly critical, as it undertakes the core task of initially decelerating and pressurizing the incoming airflow during supersonic / hypersonic flight.

[0003] Traditional external pressure section design methods often achieve good results at specific design points, but they present significant challenges when facing the stringent requirements of TBCC engines operating across a wide speed range: at non-design points, the shock wave structure may deteriorate, leading to a sharp drop in total pressure recovery in the intake manifold, insufficient flow capture, or even start-up failure; while at high Mach numbers, performance may be poor due to insufficient compression or excessive shock wave losses. Therefore, there is an urgent need for a design theory and method that can seek the optimal overall performance across the entire operating envelope. Summary of the Invention

[0004] This invention provides a design method and system for the external pressure section of the TBCC inlet based on the optimal wave system design theory. This method addresses the problems in the prior art where, at non-design points, the shock system structure may deteriorate, leading to a sudden drop in total pressure recovery, insufficient flow capture, or even failure to start. It also addresses the problem that at high Mach numbers, performance may be poor due to insufficient compression or excessive shock loss.

[0005] This invention is achieved through the following technical solution: A design method for the external pressure section of the TBCC inlet based on the optimal wave system design theory, wherein the design method is as follows: The design of the external pressure section of the two-dimensional ramjet inlet utilizes the optimal wave system design theory to meet the requirements of compression efficiency, low total pressure loss, and inlet flow rate. A zero-dimensional design was adopted, and the external pressure section was designed based on the inviscid shock wave relation, supplemented by boundary layer correction.

[0006] Furthermore, the design method includes the following steps: Step 1: Inviscid design based on the external pressure section of the two-dimensional ramjet intake; Step 2: Based on the non-viscous design in Step 1, perform viscous correction to adjust the boundary layer thickness of the outer compression section of the intake duct.

[0007] Furthermore, step 1 specifically involves designing the Mach number to be considered as the incoming Mach number. Ma 1, and assume the shock wave angle is... β 1; First turn δ 1. Total pressure recovery coefficient σ 1 and the Mach number following the first shock wave Ma 2 can be calculated using the corresponding airflow parameter relationship before and after the shock wave; The second shock angle is solved using formula (1). β 2; (1) According to the Mach number before the second shock wave Ma 2. Shock angle of the second shock wave β 2. Calculated from the relationship between airflow parameters before and after the shock wave. δ 2. Total pressure recovery coefficient σ 2 and post-wave Mach number Ma 3; The final total compression angle and total pressure recovery coefficient are calculated using equations (2) and (3); (2) (3) Repeat the iterative process until... δ t The solution and the given compression angle δ t0 The error between them is within the allowable error range; thus, the optimal compression angle allocation method is obtained.

[0008] Furthermore, step 2 specifically involves correcting the position of the lip mask, which requires adjusting the geometric position of the lip mask at the designed Mach number based on the actual CFD numerical simulation results. Furthermore, the correction method also includes slightly reducing the design Mach number during the design of the external pressure section geometry to achieve shock wave sealing.

[0009] A TBCC inlet external pressure section inlet design system based on optimal wave system design theory, the system using the TBCC inlet external pressure section inlet design method based on optimal wave system design theory as described above, the system comprising: Non-stick design unit: Non-stick design based on the external pressure section of the two-dimensional ram air intake; Viscous correction unit: Based on the non-viscous design unit, viscous correction is performed to correct the boundary layer thickness of the outer compression section of the intake duct.

[0010] Furthermore, the working process of the non-adhesive design unit specifically involves considering the design Mach number as the incoming flow Mach number. Ma 1, and assume the shock wave angle is... β 1; First turn δ 1. Total pressure recovery coefficient σ 1 and the Mach number following the first shock wave Ma 2 can be calculated using the corresponding airflow parameter relationship before and after the shock wave; The second shock angle is solved using formula (1). β 2; (1) According to the Mach number before the second shock wave Ma 2. Shock angle of the second shock wave β 2. Calculated from the relationship between airflow parameters before and after the shock wave. δ 2. Total pressure recovery coefficient σ 2 and post-wave Mach number Ma 3; The final total compression angle and total pressure recovery coefficient are calculated using equations (2) and (3); (2) (3) Repeat the iterative process until... δ t The solution and the given compression angle δ t0 The error between them is within the allowable error range. This ultimately yields the optimal compression angle allocation.

[0011] Furthermore, the correction method of the adhesive correction unit includes correcting the position of the lip mask, which requires adjusting the geometric position of the lip mask at the designed Mach number in combination with the actual CFD numerical simulation results. This also includes slightly lowering the design Mach number during the non-adhesive design of the external pressure section to design the geometry of the external pressure section, thereby achieving shock wave sealing.

[0012] A computer device includes a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor, when executing the computer program, implements the method described above.

[0013] A computer-readable storage medium storing a computer program that, when executed by a processor, implements the method described above.

[0014] The beneficial effects of this invention are: This invention transcends the limitations of a single design point and aims to provide a stable and efficient airflow supply for TBCC engines under complex and variable flight conditions.

[0015] This invention represents a cutting-edge approach to addressing the design challenges of wide-range, high-performance supersonic inlets. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the TBCC inlet external pressure section inlet design method based on the optimal wave system design theory of the present invention. Detailed Implementation

[0017] In the following description, specific details such as particular system architectures and techniques are set forth for illustrative purposes and not for limitation, in order to provide a thorough understanding of the embodiments of this application. However, those skilled in the art will understand that this application may also be implemented in other embodiments without these specific details. In other instances, detailed descriptions of well-known systems, apparatuses, circuits, and methods are omitted so as not to obscure the description of this application with unnecessary detail.

[0018] It should be understood that, when used in this specification and the appended claims, the term "comprising" indicates the presence of the described features, integrals, steps, operations, elements and / or components, but does not exclude the presence or addition of one or more other features, integrals, steps, operations, elements, components and / or collections thereof.

[0019] It should also be understood that the terminology used in this application specification is for the purpose of describing particular embodiments only and is not intended to limit the application. As used in this application specification and the appended claims, the singular forms “a,” “an,” and “the” are intended to include the plural forms unless the context clearly indicates otherwise.

[0020] The technical solutions in the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of the embodiments. Based on the embodiments of this application, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of this application.

[0021] Many specific details are set forth in the following description in order to provide a full understanding of this application. However, this application may also be implemented in other ways different from those described herein. Those skilled in the art can make similar extensions without departing from the spirit of this application. Therefore, this application is not limited to the specific embodiments disclosed below.

[0022] Implementation Method 1 This embodiment provides a design method for the external pressure section of a TBCC inlet based on the optimal wave system design theory. The design method specifically includes: The design of the external pressure section of the two-dimensional ramjet inlet utilizes the optimal wave system design theory to meet the requirements of compression efficiency, low total pressure loss, and inlet flow rate. A zero-dimensional design was adopted, and the external pressure section was designed based on the inviscid shock wave relation, supplemented by boundary layer correction.

[0023] Figure 1 This is a schematic diagram of the TBCC inlet external pressure section design method based on the optimal wave system design theory. The external pressure section of the two-dimensional ramjet inlet adopts the forward design method of the inlet, that is, under the conditions of known incoming flow conditions, design requirements and total compression angle of the external compression surface (selected according to relevant design experience), the design work of the external pressure section of the inlet is carried out.

[0024] Furthermore, the design method includes the following steps: Step 1: Inviscid design based on the external pressure section of the two-dimensional ramjet intake; Step 2: Based on the non-viscous design in Step 1, perform viscous modification to adjust the boundary layer thickness of the outer compression section of the intake manifold so that it can better reflect actual conditions in practical applications.

[0025] Furthermore, step 1 specifically involves designing the Mach number to be considered as the incoming Mach number. Ma 1, and assume the shock wave angle is... β 1; First turn δ 1. Total pressure recovery coefficient σ 1 and the Mach number following the first shock wave Ma 2 can be calculated using the corresponding airflow parameter relationship before and after the shock wave; The second shock angle is solved using formula (1). β 2; (1) According to the Mach number before the second shock wave Ma 2. Shock angle of the second shock wave β 2. Calculated from the relationship between airflow parameters before and after the shock wave. δ 2. Total pressure recovery coefficient σ 2 and post-wave Mach number Ma 3; The final total compression angle and total pressure recovery coefficient are calculated using equations (2) and (3); (2) (3) Repeat the iterative process until... δ t The solution and the given compression angle δ t0 The error between them is within the allowable error range; thus, the optimal compression angle allocation method is obtained.

[0026] Furthermore, step 2 specifically involves correcting the position of the lip mask, which requires adjusting the geometric position of the lip mask at the designed Mach number based on the actual CFD numerical simulation results. Furthermore, the correction method also includes slightly reducing the design Mach number during the design of the external pressure section geometry to achieve shock wave sealing.

[0027] Table 1. Comparison of Inlet External Pressure Section Performance under Different Compression Angle Assignments and Wavelength Configurations

[0028] Assuming the following design conditions: design Mach number is 5.0, and the intake width is... W = 100 mm, capture area is A c = 0.027 m 2 The height of the isolation section is H t = 40 mm, the total external compression angle of the external pressure section of the intake is 14°, and the optimal distribution of the compression angle of the external pressure section is basically determined according to the optimal wave system theory. Table 1 shows the performance comparison of the external pressure section of the intake with different compression angle distributions and different wave system configurations.

[0029] Taking into account the total pressure recovery coefficient, flow capture coefficient, and pressure rise, it was found that the external pressure section using the wave system configuration of oblique shock wave + isentropic compression wave has good performance. However, considering the structural strength of the mode conversion device of the TBCC inlet and the working performance of the turbine channel, it was decided to use oblique shock wave compression in the last stage. Therefore, the total compression angle of the external compression section of the inlet is 14°, and a three-stage compression (4.8°, 5.2°, and 4° respectively) wave system configuration of oblique shock wave + isentropic compression wave + oblique shock wave is adopted. This method has good overall performance and is suitable for the external compression section of the TBCC inlet.

[0030] Implementation Method 2 A TBCC inlet external pressure section inlet design system based on optimal wave system design theory, the system using the TBCC inlet external pressure section inlet design method based on optimal wave system design theory as described in Embodiment 1, the system comprising: Non-stick design unit: Non-stick design based on the external pressure section of the two-dimensional ram air intake; Viscous correction unit: Based on the non-viscous design unit, viscous correction is performed to correct the boundary layer thickness of the outer compression section of the intake duct.

[0031] Furthermore, the working process of the non-adhesive design unit specifically involves considering the design Mach number as the incoming flow Mach number. Ma 1, and assume the shock wave angle is... β 1; First turn δ 1. Total pressure recovery coefficient σ 1 and the Mach number following the first shock wave Ma 2 can be calculated using the corresponding airflow parameter relationship before and after the shock wave; The second shock angle is solved using formula (1). β 2; (1) According to the Mach number before the second shock wave Ma 2. Shock angle of the second shock wave β 2. Calculated from the relationship between airflow parameters before and after the shock wave. δ 2. Total pressure recovery coefficient σ 2 and post-wave Mach number Ma 3; The final total compression angle and total pressure recovery coefficient are calculated using equations (2) and (3); (2) (3) Repeat the iterative process until... δ t The solution and the given compression angle δ t0 The error between them is within the allowable error range. This ultimately yields the optimal compression angle allocation.

[0032] Furthermore, the correction method of the adhesive correction unit includes correcting the position of the lip mask, which requires adjusting the geometric position of the lip mask at the designed Mach number in combination with the actual CFD numerical simulation results. This also includes slightly lowering the design Mach number during the non-adhesive design of the external pressure section to design the geometry of the external pressure section, thereby achieving shock wave sealing.

[0033] Implementation Method 3 This invention provides an electronic device including a memory, a processor, and a computer program stored in the memory and executable on the processor. The memory stores software programs and modules, and the processor executes various functional applications and data processing by running the software programs and modules stored in the memory. The memory and processor are connected via a bus. Specifically, the processor implements any step in Embodiment 1 by running the computer program stored in the memory.

[0034] It should be understood that, in the embodiments of the present invention, the processor may be a Central Processing Unit (CPU), but it may also be other general-purpose processors, digital signal processors (DSPs), application-specific integrated circuits (ASICs), field-programmable gate arrays (FPGAs), or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. A general-purpose processor may be a microprocessor or any conventional processor.

[0035] Memory may include read-only memory, flash memory, and random access memory, and provides instructions and data to the processor. Some or all of the memory may also include non-volatile random access memory.

[0036] As can be seen from the above, the electronic device provided in the embodiments of the present invention can implement the TBCC inlet external pressure section inlet design method based on the optimal wave system design theory as described in Embodiment 1 by running a computer program. By carefully constructing a series of controllable shock waves, the maximum total pressure recovery coefficient can be obtained when the intensity of each oblique shock wave is equal. This allows the entire compression process to achieve overall or trade-off optimality of key performance indicators within the target velocity range while satisfying aerodynamic constraints. The TBCC inlet external pressure section design method based on the optimal wave system design theory represents the cutting-edge direction for addressing the challenges of wide-velocity, high-performance supersonic inlet design. It transcends the limitations of a single design point and is committed to providing a stable and efficient airflow supply for TBCC engines under complex and variable flight conditions. It is one of the key technological foundations for realizing the practical application of TBCC power systems.

[0037] It should be understood that if the integrated modules / units described above are implemented as software functional units and sold or used as independent products, they can be stored in a computer-readable storage medium. Based on this understanding, all or part of the processes in the methods described above can also be implemented by a computer program instructing related hardware. This computer program can be stored in a computer-readable storage medium, and when executed by a processor, it can implement the steps of the various method embodiments described above. The computer program includes computer program code, which can be in the form of source code, object code, executable files, or certain intermediate forms. The computer-readable medium can include: any entity or device capable of carrying the computer program code, recording media, USB flash drives, portable hard drives, magnetic disks, optical disks, computer memory, read-only memory (ROM), random access memory (RAM), electrical carrier signals, telecommunication signals, and software distribution media, etc. It should be noted that the content contained in the computer-readable storage medium can be appropriately increased or decreased according to the requirements of legislation and patent practice in the jurisdiction.

[0038] The above description of the disclosed embodiments enables those skilled in the art to make or use the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the invention. Therefore, the invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

[0039] Those skilled in the art will clearly understand that, for the sake of convenience and brevity, the above-described division of functional units and modules is merely an example. In practical applications, the above functions can be assigned to different functional units and modules as needed, that is, the internal structure of the above device can be divided into different functional units or modules to complete all or part of the functions described above. The functional units and modules in the embodiments can be integrated into one processing unit, or each unit can exist physically separately, or two or more units can be integrated into one unit. The integrated unit can be implemented in hardware or as a software functional unit. Furthermore, the specific names of the functional units and modules are only for easy differentiation and are not intended to limit the scope of protection of this invention. The specific working process of the units and modules in the above system can be referred to the corresponding process in the foregoing method embodiments, and will not be repeated here.

[0040] It should be noted that the methods and detailed examples provided in the above embodiments can be incorporated into the apparatus and devices provided in the embodiments for mutual reference, and will not be repeated here.

[0041] Those skilled in the art will recognize that the units and algorithm steps of the various examples described in conjunction with the embodiments disclosed herein can be implemented in electronic hardware, or a combination of computer software and electronic hardware. Whether these functions are implemented in hardware or software depends on the specific application and design constraints of the technical solution. Those skilled in the art can use different methods to implement the described functions for each specific application, but such implementations should not be considered beyond the scope of this invention.

[0042] In the embodiments provided by this invention, it should be understood that the disclosed apparatus / terminal devices and methods can be implemented in other ways. For example, the apparatus / device embodiments described above are merely illustrative. For instance, the division of modules or units described above is merely a logical functional division, and in actual implementation, it can be divided in other ways. For example, multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed.

[0043] The above embodiments are only used to illustrate the technical solutions of the present invention, and are not intended to limit them. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention, and should all be included within the protection scope of the present invention.

Claims

1. A design method for the external pressure section of a TBCC inlet based on optimal wave system design theory, characterized in that, The design method is specifically as follows: The design of the external pressure section of the two-dimensional ramjet inlet utilizes the optimal wave system design theory to meet the requirements of compression efficiency, low total pressure loss, and inlet flow rate. A zero-dimensional design was adopted, and the external pressure section was designed based on the inviscid shock wave relation, supplemented by boundary layer correction.

2. The method according to claim 1, characterized in that, The design method includes the following steps: Step 1: Inviscid design based on the external pressure section of the two-dimensional ramjet intake; Step 2: Based on the non-viscous design in Step 1, perform viscous correction to adjust the boundary layer thickness of the outer compression section of the intake duct.

3. The method according to claim 1, characterized in that, Specifically, step 1 involves designing the Mach number to be considered as the incoming Mach number. Ma 1, and assume the shock wave angle is... β 1; First turn δ 1. Total pressure recovery coefficient σ 1 and the Mach number following the first shock wave Ma 2 can be calculated using the corresponding airflow parameter relationship before and after the shock wave; The second shock angle is solved using formula (1). β 2; (1) According to the Mach number before the second shock wave Ma 2. Shock angle of the second shock wave β 2. Calculated from the relationship between airflow parameters before and after the shock wave. δ 2. Total pressure recovery coefficient σ 2 and post-wave Mach number Ma 3; The final total compression angle and total pressure recovery coefficient are calculated using equations (2) and (3); (2) (3) Repeat the iterative process until... δ t The solution and the given compression angle δ t0 The error between them is within the allowable error range; thus, the optimal compression angle allocation method is obtained.

4. The method according to claim 2, characterized in that, Step 2 specifically involves correcting the position of the lip cover. This method requires adjusting the geometric position of the lip cover at the designed Mach number based on the actual CFD numerical simulation results.

5. The method according to claim 4, characterized in that, The correction method also includes slightly reducing the design Mach number during the design of the external pressure section geometry to achieve shock wave sealing.

6. A TBCC inlet external pressure section inlet design system based on optimal wave system design theory, characterized in that, The system uses the TBCC inlet external pressure section inlet design method based on the optimal wave system design theory as described in any one of claims 1-5, and the system includes: Non-stick design unit: Non-stick design based on the external pressure section of the two-dimensional ram air intake; Viscous correction unit: Based on the non-viscous design unit, viscous correction is performed to correct the boundary layer thickness of the outer compression section of the intake duct.

7. The system according to claim 6, characterized in that, The specific working process of the non-adhesive design unit is as follows: the design Mach number is considered to be the incoming Mach number. Ma 1, and assume the shock wave angle is... β 1; First turn δ 1. Total pressure recovery coefficient σ 1 and the Mach number following the first shock wave Ma 2 can be calculated using the corresponding airflow parameter relationship before and after the shock wave; The second shock angle is solved using formula (1). β 2; (1) According to the Mach number before the second shock wave Ma 2. Shock angle of the second shock wave β 2. Calculated from the relationship between airflow parameters before and after the shock wave. δ 2. Total pressure recovery coefficient σ 2 and post-wave Mach number Ma 3; The final total compression angle and total pressure recovery coefficient are calculated using equations (2) and (3); (2) (3) Repeat the iterative process until... δ t The solution and the given compression angle δ t0 The error between them is within the allowable error range. This ultimately yields the optimal compression angle allocation.

8. The system according to claim 6, characterized in that, The correction method of the adhesive correction unit includes correcting the position of the lip cover. This method requires adjusting the geometric position of the lip cover at the designed Mach number in combination with the actual CFD numerical simulation results. This also includes slightly lowering the design Mach number during the non-adhesive design of the external pressure section to design the geometry of the external pressure section, thereby achieving shock wave sealing.

9. A computer device, characterized in that, It includes a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein when the processor executes the computer program, it implements the method as described in any one of claims 6-8.

10. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores a computer program that, when executed by a processor, implements the method as described in any one of claims 6-8.

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