Nest compact BLI propulsion system layout, method, apparatus, medium and product

Abstract

The invention relates to the technical field of aerospace, and particularly provides a nested compact BLI propulsion system layout, a method, equipment, a medium and a product. The propelling system comprises a nested air inlet channel, an inner duct blower device and an outer duct blower device, a nested inner cylinder sucks main flow and inputs the sucked main flow into the inner duct blower device, and a nested outer cylinder sucks boundary layer fluid and inputs the sucked boundary layer fluid into the outer duct blower device. The nested inner cylinder sucks in a mainstream fluid, the uniformity of the mainstream fluid can greatly reduce the flow separation of the inner cylinder in the nested layout, the outer cylinder sucks in a boundary layer fluid and a small part of mainstream fluid, and the particularity of the structure can enable the separation of the flow separation in the outer cylinder to be smaller than that in a push layout in the related technology. The outer cylinder not only retains the advantage that the traditional layout is not easy to separate, but also retains the advantage that the BLI layout sucks low-energy fluid so as to reduce power consumption.

Description

Technical Field

[0001] The present disclosure relates to the field of aerospace technology, and in particular, to a nested compact BLI propulsion system layout, method, device, medium, and product. Background Art

[0002] With the development of the aviation industry, people have been constantly pursuing the passenger capacity of aircraft. Such a demand has led to the pursuit of a larger bypass ratio and larger engine size for traditional pylon-mounted engines. However, due to the limitation of the aircraft size, the engine size has also approached its limit. Under such requirements, the benefits of the traditional pylon-mounted propulsion system layout have approached their limit.

[0003] Therefore, a new Boundary Layer Ingestion (BLI) propulsion system layout has been proposed. In the traditional layout, the boundary layer causes kinetic energy loss and wake drag, while the BLI layout allows the boundary layer fluid of the fuselage or wing to enter the intake duct as the working fluid of the engine, flow through the fan, and participate in work to generate thrust. Currently, it is widely used. For example, distributed propulsion aircraft such as N3-X and ONEARA NOVA have adopted the BLI distributed propulsion layout. Compared with the traditional propulsion system, the BLI propulsion system can reduce the power consumed by the engine to achieve the same thrust, improve the flight efficiency of the aircraft, and reduce the fuel consumption rate.

[0004] However, in the BLI propulsion system layout, the boundary layer ingestion will lead to poor aerodynamic performance of components, resulting in excessive power consumption. Summary of the Invention

[0005] In view of the above problems, the present disclosure is proposed. The present disclosure provides a nested compact BLI propulsion system layout, method, device, medium, and product.

[0006] According to a first aspect of the present disclosure, a propulsion system is provided, including: A nested intake duct and an inner and outer double-duct blower device; The nested intake duct includes a nested inner cylinder and a nested outer cylinder, and the inner and outer double-duct blower device includes an inner-duct blower device and an outer-duct blower device; The nested inner cylinder sucks in the mainstream and inputs the sucked mainstream into the inner-duct blower device, and the nested outer cylinder sucks in the boundary layer fluid and inputs the sucked boundary layer fluid into the outer-duct blower device.

[0007] In addition, for the propulsion system according to the first aspect of the present disclosure, the nested intake duct is a nested S-shaped intake duct.

[0008] According to a second aspect of the present disclosure, there is provided a method for calculating power consumption, which is applied to the propulsion system described in the first aspect. The method includes: Based on the target inference requirement of the propulsion system, the static pressure of the inlet environment of the propulsion system, and the flow rates through the nested inner cylinder and the nested outer cylinder, calculate the pressure ratio and design efficiency of the core duct blower device and the bypass duct blower device; Based on the static pressure of the inlet environment of the propulsion system, the flight Mach number, the pressure ratio and the design efficiency of the inner and outer double-layer duct blower devices, calculate the total temperature at the outlet section of the core duct blower device, the total temperature at the inlet section of the core duct blower device, the total temperature at the outlet section of the bypass duct blower device, and the total temperature at the inlet section of the bypass duct blower device; Based on the total temperature at the outlet section of the core duct blower device, the total temperature at the inlet section of the core duct blower device, the total temperature at the outlet section of the bypass duct blower device, the total temperature at the inlet section of the bypass duct blower device, and the flow rates through the nested inner cylinder and the nested outer cylinder, calculate the power that the propulsion system needs to consume when meeting the target inference requirement.

[0009] In addition, according to the method for calculating power consumption described in the second aspect of the present disclosure, based on the total temperature at the outlet section of the core duct blower device, the total temperature at the inlet section of the core duct blower device, the total temperature at the outlet section of the bypass duct blower device, the total temperature at the inlet section of the bypass duct blower device, and the flow rates through the nested inner cylinder and the nested outer cylinder, calculating the power that the propulsion system needs to consume when meeting the target inference requirement includes: Calculate a first temperature difference between the total temperature at the outlet section of the core duct blower device and the total temperature at the inlet section of the core duct blower device, and calculate a second temperature difference between the total temperature at the outlet section of the bypass duct blower device and the total temperature at the inlet section of the bypass duct blower device; Calculate a first product of the first temperature difference and the flow rate through the nested inner cylinder, and calculate a second product of the second temperature difference and the flow rate through the nested outer cylinder; Calculate the sum of the first product and the second product to obtain the power that the propulsion system needs to consume when meeting the target inference requirement.

[0010] In addition, according to the method for calculating power consumption described in the second aspect of the present disclosure, the method further includes: When the power that the propulsion system needs to consume when meeting the target inference requirement is obtained, calculate the energy-saving coefficient of the propulsion system based on the power; Evaluate the power benefit of the propulsion system based on the energy-saving coefficient.

[0011] In addition, according to the method for calculating power consumption described in the second aspect of the present disclosure, based on the inlet ambient static pressure of the propulsion system, the flight Mach number, the pressure ratio and the design efficiency of the inner and outer double-duct blower device, calculate the total temperature at the outlet section of the inner-duct blower device, the total temperature at the inlet section of the inner-duct blower device, the total temperature at the outlet section of the outer-duct blower device, and the total temperature at the inlet section of the outer-duct blower device, including: Calculate the temperature at the inlet section of the intake duct according to the inlet ambient static pressure and the inner cylinder Mach number obtained based on the flight Mach number; and calculate the temperature at the outlet section of the intake duct according to the inlet ambient static pressure and the outer cylinder Mach number obtained based on the inner cylinder Mach number; Take the temperature at the inlet section of the intake duct as the total temperature at the inlet section of the inner-duct blower device, and take the temperature at the outlet section of the intake duct as the total temperature at the inlet section of the outer-duct blower device; Based on the temperature at the inlet section of the intake duct, the pressure ratio and the design efficiency, calculate the total temperature at the outlet section of the inner-duct blower device; and based on the temperature at the outlet section of the intake duct, the pressure ratio and the design efficiency, calculate the total temperature at the outlet section of the outer-duct blower device.

[0012] According to the third aspect of the present disclosure, there is provided a power consumption calculation device, which is applied to the propulsion system described in the first aspect. The device includes: A first calculation module, configured to calculate the pressure ratio and the design efficiency of the inner-duct blower device and the outer-duct blower device based on the target inference requirement of the propulsion system, the inlet ambient static pressure of the propulsion system, and the flow rates flowing through the nested inner cylinder and the nested outer cylinder; A second calculation module, configured to calculate the total temperature at the outlet section of the inner-duct blower device, the total temperature at the inlet section of the inner-duct blower device, the total temperature at the outlet section of the outer-duct blower device, and the total temperature at the inlet section of the outer-duct blower device based on the inlet ambient static pressure of the propulsion system, the flight Mach number, the pressure ratio of the inner and outer double-duct blower device, and the design efficiency; A third calculation module, configured to calculate the power consumption required by the propulsion system to meet the target inference requirement based on the total temperature at the outlet section of the inner-duct blower device, the total temperature at the inlet section of the inner-duct blower device, the total temperature at the outlet section of the outer-duct blower device, the total temperature at the inlet section of the outer-duct blower device, and the flow rates flowing through the nested inner cylinder and the nested outer cylinder.

[0013] According to the fourth aspect of the present disclosure, there is provided an electronic device, including a memory, a processor, and a computer program stored on the memory. The processor executes the computer program to implement the steps of the method described in the first aspect. According to a fifth aspect of the present disclosure, there is provided a computer-readable storage medium having stored thereon a computer program / instruction, which when executed by a processor, implements the steps of the method described in the first aspect. According to a sixth aspect of the present disclosure, there is provided a computer program product including a computer program / instruction, which when executed by a processor, implements the steps of the method described in the first aspect.

[0014] As will be described in detail below, the propulsion system provided in this embodiment includes a nested intake duct and an inner and outer double-duct blower device. The nested inner cylinder sucks in the mainstream and inputs the sucked mainstream into the core duct blower device. The nested outer cylinder sucks in the boundary layer fluid and inputs the sucked boundary layer fluid into the bypass duct blower device. The nested inner cylinder sucks in the mainstream fluid, and the uniformity of the mainstream fluid can significantly reduce the flow separation of the inner cylinder in the nested layout. The outer cylinder sucks in the boundary layer fluid and a small part of the mainstream fluid, and the special structure thereof can make the flow separation on the outer cylinder smaller than that in the propulsive layout in the related art. The outer cylinder retains both the advantage of the traditional layout that is not easy to separate and the advantage of the BLI layout that sucks in low-energy fluid in total to reduce power consumption.

[0015] It is to be understood that both the foregoing general description and the following detailed description are exemplary and are intended to provide further explanation of the claimed technology. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] By describing the embodiments of the present disclosure in more detail in conjunction with the drawings, the above and other objects, features, and advantages of the present disclosure will become more apparent. The drawings are used to provide a further understanding of the embodiments of the present disclosure and constitute a part of the specification. Together with the embodiments of the present disclosure, they are used to explain the present disclosure and do not constitute a limitation to the present disclosure. In the drawings, the same reference numerals generally represent the same components or steps.

[0017] Figure 1 is a schematic diagram illustrating the principle of airflow inhalation according to an embodiment of the present disclosure.

[0018] Figure 2 is a schematic diagram illustrating a propulsion system according to an embodiment of the present disclosure.

[0019] Figure 3 is a flowchart illustrating a method for calculating power consumption according to an embodiment of the present disclosure.

[0020] Figure 4 is a structural diagram illustrating a device for calculating power consumption according to an embodiment of the present disclosure.

[0021] Figure 5It is a hardware block diagram of an electronic device according to an embodiment of the present disclosure.

[0022] Figure 6 It is a schematic diagram of a computer-readable storage medium according to an embodiment of the present disclosure. Detailed implementation manners

[0023] To make the objectives, technical solutions and advantages of the embodiments of the present disclosure clearer, the technical solutions in the embodiments of the present disclosure will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present disclosure. Apparently, the described embodiments are only some, but not all, of the embodiments of the present disclosure. Components of the embodiments of the present disclosure generally described and illustrated in the figures herein may be arranged and designed in a variety of different configurations. Therefore, the detailed description of the embodiments of the present disclosure provided herein is not intended to limit the scope of the claimed present disclosure, but is merely representative of selected embodiments of the present disclosure. All other embodiments obtained by those skilled in the art based on the embodiments of the present disclosure without creative efforts shall fall within the protection scope of the present disclosure.

[0024] It should be noted that like reference numerals and letters denote like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.

[0025] The term "and / or" in this document merely describes an associated relationship and means that three relationships may exist. For example, A and / or B may mean: A exists alone, A and B exist simultaneously, or B exists alone. In addition, the term "at least one" in this document means any one of a plurality or any combination of at least two of a plurality. For example, including at least one of A, B, and C may mean including any one or more elements selected from the set composed of A, B, and C.

[0026] In the related art, in the layout of the BLI propulsion system, the propulsion system includes a single intake duct and a fan connected to the single intake duct. The aircraft obtains thrust by accelerating the airflow flowing through the propulsion system so that the outlet flow velocity of the airflow is greater than the inlet flow velocity. The BLI layout sucks in the boundary layer flow, and there will be mixing of the mainstream and the low-speed boundary layer flow at the inlet, and the average outlet flow velocity is small. However, the suction of the boundary layer flow will cause very poor aerodynamic performance of the component characteristics, thereby resulting in excessive power consumption.

[0027] Specifically, in the state where the airflow at the inlet and outlet of the propulsion system is fully expanded, its thrust formula can be simplified as: (1) Where is the gas flow rate flowing through the propulsion system, is the outlet flow velocity of the airflow, is the inlet flow velocity of the air flow. In order to enable the propulsion system to accelerate the air flow, it is necessary to consume fuel to obtain energy and then transfer the energy to the propulsion system. The ability of the propulsion system to do work on the air flow per unit time to accelerate the air flow can be expressed as: (2) In the above formula, represents the amount of energy input to the propulsion system per unit time to accelerate the air flow and obtain thrust. The energy input to the propulsion system comes from the combustion of fuel. Therefore, in the case of obtaining the same thrust, if the of the propulsion system is smaller, it means that its fuel consumption rate is lower. It can be seen from the above formula that in the case of the same target thrust, the ability of the propulsion system to do work on the air flow per unit time depends on the flow rate and the inlet and outlet flow velocities. If the flow rate through the propulsion system is the same, the square difference of the inlet and outlet flow velocities becomes the key factor affecting its magnitude. Combining the above two formulas, we have: (3) This formula is a monotonically increasing function when the inlet flow velocity is always greater than 0. It can be seen that if the inlet flow velocity is smaller, the power consumed is smaller, and the requirement for fuel consumption is lower. In the traditional back-mounted layout, since the propulsion system is far from the fuselage and wings, the inlet air flow is uniform, the average inlet flow velocity is large, and the average outlet flow velocity is also large. In the BLI layout, the boundary layer is inhaled, and there is mixing of the mainstream and the low-speed boundary layer flow at the inlet, and the average outlet flow velocity is small, as Figure 1 shown.

[0028] The BLI layout inhales low-energy fluid, which reduces the average inlet flow velocity and power consumption. Compared with the traditional back-mounted layout, it has greater advantages in power consumption. However, in fact, in the real flow process, the air flow in each component of the propulsion system must not be in an ideal state, that is, there are flow losses in each component, and this loss will cause a part of the power input to the propulsion system to be converted into heat energy and cannot do work to accelerate the air flow. Therefore, considering this part of the loss, to make the propulsion system reach the target thrust, the actual input power should be expressed as:

[0029] In the formula, P represents the total power that needs to be input to the propulsion system to meet a certain thrust F, is the mechanical power consumed by the propulsion system to accelerate the air flow to meet the target thrust, is the power consumed due to the aerodynamic loss of the components of the propulsion system, is the flow rate flowing into the propulsion system, is the flow velocity of the air flow at the outlet of the propulsion system, The flow velocity of the inlet air of the propulsion system.

[0030] A part of the power input to the propulsion system is converted into mechanical energy to accelerate the air flow and ultimately used to generate thrust. Another part is converted into heat energy due to the irreversible processes when the air flow passes through the inlet duct, fan, and nozzle components. This part of the energy cannot be converted into thrust. Considering the inlet and outlet air flows as fully expanded, given the total inlet temperature and pressure and the incoming Mach number, the inlet air velocity can be calculated. The outlet flow velocity of the air can be obtained from the thrust requirement. Therefore, the mechanical energy consumption power required to meet the target thrust of the propulsion system Can be obtained therefrom.

[0031] And the lost power Consists of three parts: (5) In the formula Is the total inlet temperature of each component, Is the entropy increase of the air flow when passing through each component. The magnitude of the entropy increase generated by the irreversible process represents the amount of mechanical energy loss. The greater the entropy increase, the more mechanical energy is lost. This part of the energy is converted into heat and absorbed by the air flow. Represents the total inlet temperature at the inlet of the inlet duct, Represents the entropy increase of the air flow generated in the inlet duct. The process of the air flow passing through the inlet duct is usually regarded as an adiabatic and irreversible process, that is, the total temperature remains unchanged and the total pressure decreases. Represents the total inlet temperature at the inlet of the fan, Represents the entropy increase of the air flow generated in the fan. The process of passing through the fan is non-adiabatic and irreversible, Represents the total inlet temperature at the inlet of the nozzle, Represents the entropy increase of the air flow passing through the nozzle. Usually, the process of passing through the nozzle is regarded as an adiabatic and isentropic process. Therefore, for the nozzle This term is 0. Therefore, when calculating Only the inlet duct and fan components need to be considered.

[0032] + (6) (7) (8) (9) (10) In the formula 、 、 And Are the total inlet temperature, outlet temperature, total inlet temperature, and outlet temperature at the inlet of the inlet duct, fan, respectively. , , , are the total pressure at the inlet of the intake duct, the total pressure at the outlet, the total pressure at the inlet of the fan, and the total pressure at the outlet, respectively. Cp is the specific heat capacity at constant pressure of air, Rg is the gas constant, and k is the adiabatic index of air. is the total pressure recovery coefficient in the intake duct. is the pressure ratio of the fan. is the efficiency of the fan. Since the flow in the intake duct is considered an isentropic flow, the total temperature at the inlet and outlet is the same. From the above, the functional expression of the power loss caused by irreversible processes in the propulsion system and the component characteristics can be obtained.

[0033] (11)

[0034] Therefore, given the component characteristics and the flow velocities at the inlet and outlet of the propulsion system, the power required for the propulsion system to meet a certain thrust can be calculated.

[0035] Under the traditional layout, the large flow velocities at the inlet and outlet result in being too large, causing high power consumption. Therefore, it is hoped to obtain higher fuel consumption benefits through the low inlet flow velocity of the BLI layout. However, due to boundary layer ingestion, the aerodynamic performance of the component characteristics is very poor, resulting in being too large.

[0036] To alleviate the technical problems in the related art, an embodiment of the present disclosure provides a nested compact BLI propulsion system layout, method, device, medium, and product.

[0037] For ease of understanding of this embodiment, a propulsion system disclosed in an embodiment of the present disclosure will be introduced in detail first.

[0038] Referring to Figure 2 shown, which is a structural diagram of the propulsion system provided by an embodiment of the present disclosure. The propulsion system includes: a nested intake duct 21 and an inner and outer double-duct blower device 22; The nested intake duct 21 includes a nested inner cylinder and a nested outer cylinder. The inner and outer double-duct blower device 22 includes an inner-duct blower device and an outer-duct blower device; The nested inner cylinder sucks in the mainstream and inputs the sucked mainstream into the inner-duct blower device. The nested outer cylinder sucks in the boundary layer fluid and inputs the sucked boundary layer fluid into the outer-duct blower device.

[0039] In some embodiments, the inner and outer double-duct blower device can be an inner and outer double-duct fan.

[0040] In some embodiments, the nested air intakes are nested S-shaped air intakes.

[0041] The propulsion system consists of two important components, a nested S-shaped inlet and an inner-outer double-layer duct fan. The inlet guides the airflow to achieve initial pressurization of the airflow and introduces the rear fan to achieve further compression of the airflow. The nested S-shaped nested inner barrel inhales a uniform mainstream and inputs this part of the fluid into the inner duct of the rear fan. The outer barrel of the inlet inhales a small part of the mainstream and all boundary layer fluids, and inputs this part of the fluid into the outer duct of the rear fan. The airflow at the inlet of the inner barrel is uniform, and there will be no large-scale flow separation inside, causing excessive flow loss and affecting the overall benefit of BLI. The outer barrel inhales the boundary layer and a small part of the mainstream. Due to the uneven intake conditions, the flow of the outer barrel is not as uniform as that of the inner barrel. It is accompanied by airflow lift and the formation of tail vortices. These flow conditions will lead to a decrease in the total pressure recovery coefficient of the nested outer barrel and a decrease in fan efficiency, but due to the small flow entering the outer barrel, the impact on the overall benefit is not obvious. In addition, the rear inner-outer double duct fan can also reduce the overflow resistance of the inlet.

[0042] The propulsion system provided in this embodiment includes a nested air intake duct and an inner and outer double-layer duct blowing device. The nested inner cylinder sucks in the mainstream and inputs the sucked mainstream into the inner duct blowing device, and the nested outer cylinder sucks in the boundary layer fluid and inputs the sucked boundary layer fluid into the outer duct blowing device. The nested inner cylinder sucks in the mainstream fluid, and the uniformity of the mainstream fluid can greatly reduce the flow separation of the inner cylinder of the nested layout, while the outer cylinder sucks in the boundary layer fluid and a small part of the mainstream fluid. The special structure can make the flow separation in the outer cylinder smaller than that in the propulsion layout in the related technology. The outer cylinder retains the advantage of the traditional layout that is not easy to separate, and also retains the advantage of the BLI layout that sucks in low-energy fluids to reduce power consumption.

[0043] The present application also provides a method for calculating power consumption, which can be applied to calculate the power consumption of the recommended system in the above embodiment. Figure 3 As shown, the method may include the following steps: Step 301, based on the target reasoning requirements of the propulsion system, the inlet ambient static pressure of the propulsion system, and the flow rate flowing through the nested inner cylinder and the nested outer cylinder, calculate the boost ratio and design efficiency of the inner duct blower and the outer duct blower.

[0044] In the application, the target reasoning requirement of the propulsion system includes but is not limited to being expressed in terms of target thrust, that is, the target reasoning requirement defines the thrust that the propulsion system needs to provide.

[0045] When the component design indicators are determined (total pressure recovery coefficient of the inlet duct, fan pressure ratio, fan efficiency), the parameters of each section are known, and the target thrust requirement satisfies the following formula: (13) where F is the target thrust requirement, and respectively represent the mass flow rates through the inner and outer channels, is the mass flow rate velocity at the outlet of the core duct blower device, is the mass flow rate velocity at the outlet of the bypass duct blower device, is the mass flow rate velocity at the inlet of the nested inner cylinder, is the mass flow rate velocity at the outlet of the nested outer cylinder.

[0046] Among them, 、 、 、 can be obtained through the following conversion formula: Given the ambient static pressure 、static temperature at the inlet of the propulsion system and the flight Mach number, the airflow expands completely at the inlet section. The subscripts 1, 2, 3, and 4 in the formula respectively represent the inlet section of the inlet duct, the outlet section of the inlet duct (fan inlet section), and the outlet section of the fan.

[0047] Then the total temperature and total pressure of the inner and outer cylinders at section 1 can be respectively expressed as: (14) (15) (16) (17) (18) (19) (20) (21) where k is the adiabatic index, is the thermodynamics constant. and respectively represent the total pressure at the inlets of the inner and outer cylinders of the inlet duct, and respectively represent the total temperature at the inlets of the inner and outer cylinders of the inlet duct, and respectively represent the average Ma of the airflow at the inlets of the inner and outer cylinders. Since the outer cylinder sucks in low-energy fluid in the boundary layer, so is slightly lower than . and respectively represent the static pressure and static temperature of the environment. Under the condition of complete expansion of the inlet airflow, the static pressure and static temperature of the airflow at the inlet section are the same as those of the environment static pressure and static temperature. After flowing through the nested S-shaped inlet duct, the aerodynamic parameters at the inner and outer cylinder outlets of the inlet duct are expressed as: (22) (23) (24) (25) In the formula and respectively represent the total pressure recovery coefficients of the inner and outer cylinders of the inlet duct. The aerodynamic parameters at the inner and outer bypass outlets of the fan can be expressed as (26) (27) (28) (29) In the formula and respectively represent the design pressure ratios of the core fan and the bypass fan, and respectively represent the design efficiencies of the core fan and the bypass fan. After passing through the adiabatic and isentropic nozzle, the outlet airflow is completely expanded, and its aerodynamic parameters can be expressed as: (30) (31) (32) (33) (34) The outlet velocity of the nozzle can be expressed as (35) (36) (37) (38) (39) (40) Step 302: Calculate the total temperature at the outlet section of the inner duct blower, the total temperature at the inlet section of the inner duct blower, the total temperature at the outlet section of the outer duct blower, and the total temperature at the inlet section of the outer duct blower based on the static pressure of the inlet environment of the propulsion system, the flight Mach number, the pressure ratio and design efficiency of the inner duct blower and the outer duct blower.

[0048] In some alternative embodiments, step 302 may include the following steps: Calculate the temperature at the inlet section of the inlet duct according to the static pressure of the inlet environment and the inner barrel Mach number obtained based on the flight Mach number; and calculate the temperature at the outlet section of the inlet duct according to the static pressure of the inlet environment and the outer barrel Mach number obtained based on the inner barrel Mach number; Take the temperature at the inlet section of the inlet duct as the total temperature at the inlet section of the inner duct blower, and take the temperature at the outlet section of the inlet duct as the total temperature at the inlet section of the outer duct blower; Calculate the total temperature at the outlet section of the inner duct blower based on the temperature at the inlet section of the inlet duct, the pressure ratio and the design efficiency; and calculate the total temperature at the outlet section of the outer duct blower based on the temperature at the outlet section of the inlet duct, the pressure ratio and the design efficiency.

[0049] Among them, the formula for calculating the temperature at the inlet section of the inlet duct can be referred to the foregoing formula (16), where in formula (16) is the temperature at the inlet section of the inlet duct. The calculation formula for the temperature at the outlet section of the inlet duct can be referred to the foregoing formula (17), where in formula (17) is the temperature at the outlet section of the inlet duct.

[0050] The calculation of the total temperature at the inlet section of the inner duct blower can be referred to formula (24), and in formula (24) is the total temperature at the inlet section of the inner duct blower. The calculation of the total temperature at the inlet section of the outer duct blower can be referred to formula (25), and in formula (25) is the total temperature at the inlet section of the outer duct blower.

[0051] The calculation formula for the total temperature at the outlet section of the inner duct blower can be referred to the foregoing formula (28), and in formula (28) is the total temperature at the outlet section of the inner duct blower. The total temperature at the outlet section of the outer duct blower can be referred to the foregoing formula (29), and in formula (29) is the total temperature at the outlet section of the outer duct blower.

[0052] Step 303: Calculate the power that the propulsion system needs to consume when meeting the target inference requirements based on the total temperature at the outlet section of the inner duct blower, the total temperature at the inlet section of the inner duct blower, the total temperature at the outlet section of the outer duct blower, the total temperature at the inlet section of the outer duct blower, and the flow rates flowing through the nested inner barrel and the nested outer barrel.

[0053] In some embodiments, step 303 may include the following steps: Calculate a first temperature difference between the total temperature at the outlet cross-section of the core blower device and the total temperature at the inlet cross-section of the core blower device, and calculate a second temperature difference between the total temperature at the outlet cross-section of the bypass blower device and the total temperature at the inlet cross-section of the bypass blower device; Calculate a first product of the first temperature difference and the flow rate through the nested inner cylinder, and calculate a second product of the second temperature difference and the flow rate through the nested outer cylinder; Calculate the sum of the first product and the second product to obtain the power that the propulsion system needs to consume when meeting the target reasoning requirement.

[0054] To meet the target reasoning requirement, energy needs to be input from the outside into the propulsion system. For the propulsion system, the energy input from the outside per unit time (i.e., the power consumed by the propulsion system) only acts on the fan component, and drives the air flow to flow and increase pressure by transmitting the energy to the fan. Since the total temperature magnitude represents the total energy magnitude, the total energy input from the outside is reflected in the increase in the total temperature. Therefore, to achieve the target thrust requirement, the power consumed by the propulsion system can also be expressed by the following formula:

[0055] Where, is the outlet cross-section of the core blower device, is the total temperature at the inlet cross-section of the core blower device, is the total temperature at the outlet cross-section of the bypass blower device, is the total temperature at the inlet cross-section of the bypass blower device.

[0056] In some embodiments, the method may further include: Based on the power consumed by the propulsion system when meeting the target reasoning requirement, calculate the energy-saving coefficient of the propulsion system; Evaluate the power benefit of the propulsion system based on the energy-saving coefficient.

[0057] As described above, the power benefit of the traditional BLI relative to the traditional back-support layout is that due to the relatively low inlet air flow velocity, the total temperature difference between the fan outlet and the inlet is smaller, so the consumed power P is smaller; however, due to the flow separation phenomenon in the inlet duct of the traditional BLI components, the total pressure loss coefficient of the inlet duct is relatively large, so the power benefit is not obvious. The nested layout proposed by the present invention ensures a relatively low inlet air flow velocity, and its structure can ensure that there is no separation phenomenon in both the inner and outer channels, and the component performance parameters are relatively high, so that the power consumption P is smaller.

[0058] To comprehensively evaluate the layout advantages and specific benefits of the nested layout compared with the back-support layout and the traditional BLI layout, this embodiment introduces the Power-saving coefficient (PSC). Under the traditional engine / fuselage layout, the air flow velocity at the inlet of the propulsion system intake is relatively high, and more power is consumed to obtain a certain thrust, that is, the fuel consumption rate is higher. In the wing-body fusion layout, low-speed boundary layer fluid is inhaled, and less power is consumed to obtain the same thrust as in the traditional layout, and the fuel consumption rate is lower. However, the intake flow separation and vortex caused by the low-energy fluid greatly affect the aerodynamic and fuel consumption benefits of the BLI layout. The nested layout proposed by the present invention can suck the mainstream uniform fluid and the low-energy boundary layer fluid separately.

[0059] Taking PSC as the power benefit of the BLI propulsion system compared with the traditional propulsion system layout, where P represents the power consumed by the traditional back-support propulsion system layout under a certain thrust F, and represents the power consumed by the propulsion system under the BLI layout when meeting the same thrust F. The higher the PSC, the greater the layout benefit and the smaller the fuel consumption rate.

[0060] From the above, to achieve the goal of consuming less power under the same thrust, the mechanical energy consumption power and component loss power can be reduced. Under the traditional back-support layout, although the uniform intake air can reduce the flow separation degree in the intake duct of the propulsion system, resulting in a high total pressure recovery coefficient of the intake duct and a high fan efficiency, due to the high intake air velocity, the outlet flow velocity will also be high to meet the thrust requirement. The large square difference between the two will cause excessive mechanical energy consumption power. In the BLI layout, due to the inhalation of the low-energy fluid of the fuselage, the air flow in the intake duct of the propulsion system in the BLI layout is prone to flow separation, resulting in a large total pressure loss, and the efficiency of the subsequent fan will also be reduced. These factors will lead to a large component loss power in the BLI layout. Due to the special nature of its layout, the intake air velocity is low, so the outlet flow velocity is low under the same thrust target, and the square difference between the two is small, so the mechanical energy consumption power of the BLI layout is small, which makes the overall power consumption smaller than that of the traditional back-support layout, thus bringing fuel consumption benefits. However, the nested layout proposed by the present invention divides the oncoming flow into the mainstream and the boundary layer flow. The nested inner cylinder sucks the mainstream fluid, and the uniformity of the mainstream fluid can greatly reduce the flow separation in the inner cylinder of the nested layout. The outer cylinder sucks the boundary layer fluid and a small part of the mainstream fluid, and its special structure can make the flow separation in the outer cylinder smaller than that in the previous two layouts. The outer cylinder retains the advantages of the traditional layout that are not easy to separate, and also retains the advantage of the BLI layout that sucks the low-energy fluid to reduce the power consumption.

[0061] An embodiment of the present disclosure also provides a computing device for power consumption. As Figure 4 shown, the device includes: A first calculation module 41, configured to calculate the pressure ratio and design efficiency of the core duct blower and the bypass duct blower based on the target inference requirement of the propulsion system, the inlet ambient static pressure of the propulsion system, and the flow rate through the nested inner cylinder and the nested outer cylinder; A second calculation module 42, configured to calculate the total temperature at the outlet section of the core duct blower, the total temperature at the inlet section of the core duct blower, the total temperature at the outlet section of the bypass duct blower, and the total temperature at the inlet section of the bypass duct blower based on the inlet ambient static pressure of the propulsion system, the flight Mach number, the pressure ratio and the design efficiency of the inner and outer double-layer duct blowers; A third calculation module 43, configured to calculate the power consumed by the propulsion system to meet the target inference requirement based on the total temperature at the outlet section of the core duct blower, the total temperature at the inlet section of the core duct blower, the total temperature at the outlet section of the bypass duct blower, the total temperature at the inlet section of the bypass duct blower, and the flow rate through the nested inner cylinder and the nested outer cylinder.

[0062] In some embodiments, the third calculation module 43 is configured to: Calculate a first temperature difference between the total temperature at the outlet section of the core duct blower and the total temperature at the inlet section of the core duct blower, and calculate a second temperature difference between the total temperature at the outlet section of the bypass duct blower and the total temperature at the inlet section of the bypass duct blower; Calculate a first product of the first temperature difference and the flow rate through the nested inner cylinder, and calculate a second product of the second temperature difference and the flow rate through the nested outer cylinder; Calculate the sum of the first product and the second product to obtain the power consumed by the propulsion system to meet the target inference requirement.

[0063] In some embodiments, the device is further configured to: Based on the power consumed by the propulsion system to meet the target inference requirement, calculate the energy-saving coefficient of the propulsion system; Evaluate the power benefit of the propulsion system based on the energy-saving coefficient.

[0064] In some embodiments, the second calculation module 42 is configured to: Calculate the inlet section temperature of the intake duct according to the inlet ambient static pressure and the inner cylinder Mach number obtained based on the flight Mach number; and calculate the outlet section temperature of the intake duct according to the inlet ambient static pressure and the outer cylinder Mach number obtained based on the inner cylinder Mach number. Take the inlet cross-section temperature of the inlet duct as the total temperature at the inlet cross-section of the core blower device, and take the outlet cross-section temperature of the inlet duct as the total temperature at the inlet cross-section of the bypass blower device; Based on the inlet cross-section temperature of the inlet duct, the pressure ratio, and the design efficiency, calculate the total temperature at the outlet cross-section of the core blower device; and, based on the outlet cross-section temperature of the inlet duct, the pressure ratio, and the design efficiency, calculate the total temperature at the outlet cross-section of the bypass blower device.

[0065] The power consumption calculation device provided by the embodiments of the present disclosure and the power consumption calculation method provided by the embodiments of the present disclosure are based on the same inventive concept and have the same beneficial effects as the method adopted, run, or implemented by it.

[0066] The embodiments of the present disclosure also provide an electronic device to execute the above-mentioned power consumption calculation method. Please refer to Figure 5 It shows a schematic diagram of an electronic device provided by some embodiments of the present disclosure. As Figure 5 shown, the electronic device 8 includes: a processor 800, a memory 801, a bus 802, and a communication interface 803. The processor 800, the communication interface 803, and the memory 801 are connected through the bus 802; a computer program that can run on the processor 800 is stored in the memory 801, and when the processor 800 runs the computer program, it executes the power consumption calculation method provided by any one of the foregoing embodiments of the present disclosure.

[0067] Among them, the memory 801 may include a high-speed random access memory (RAM: Random Access Memory), and may also include a non-volatile memory, such as at least one disk memory. Through at least one communication interface 803 (which can be wired or wireless), a communication connection between the device network element and at least one other network element is realized, and the Internet, wide area network, local area network, metropolitan area network, etc. can be used.

[0068] The bus 802 may be an ISA bus, a PCI bus, an EISA bus, etc. The bus can be divided into an address bus, a data bus, a control bus, etc. Among them, the memory 801 is used to store a program, and after the processor 800 receives an execution instruction, it executes the program. The power consumption calculation method disclosed in any one of the foregoing embodiments of the present disclosure can be applied to the processor 800 or implemented by the processor 800.

[0069] The processor 800 may be an integrated circuit chip with signal processing capabilities. In the implementation process, the steps of the above method can be completed by the integrated logic circuit of the hardware in the processor 800 or the instructions in the form of software. The above-mentioned processor 800 may be a general-purpose processor, including a central processing unit (CPU for short), a network processor (NP for short), etc.; it may also be a digital signal processor (DSP), an application-specific integrated circuit (ASIC), a field-programmable gate array (FPGA) or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components. It can implement or execute the various methods, steps and logic block diagrams disclosed in the embodiments of the present disclosure. The general-purpose processor may be a microprocessor or the processor may also be any conventional processor, etc. The steps of the method disclosed in combination with the embodiments of the present disclosure can be directly embodied as being executed and completed by a hardware decoding processor, or executed and completed by a combination of the hardware and software modules in the decoding processor. The software module may be located in a mature storage medium in the art such as a random access memory, a flash memory, a read-only memory, a programmable read-only memory or an electrically erasable programmable memory, a register, etc. This storage medium is located in the memory 801, and the processor 800 reads the information in the memory 801 and combines its hardware to complete the steps of the above method.

[0070] The electronic device provided by the embodiments of the present disclosure and the power consumption calculation method provided by the embodiments of the present disclosure are based on the same inventive concept and have the same beneficial effects as the methods adopted, run or implemented by them.

[0071] The embodiments of the present disclosure also provide a computer-readable storage medium corresponding to the power consumption calculation method provided in the foregoing embodiments. Please refer to Figure 6 , which shows that the computer-readable storage medium is an optical disc 30, on which a computer program (i.e., a program product) is stored. When the computer program is run by a processor, it will execute the power consumption calculation method provided in any of the foregoing embodiments.

[0072] It should be noted that examples of the computer-readable storage medium may also include, but are not limited to, phase change memory (PRAM), static random access memory (SRAM), dynamic random access memory (DRAM), other types of random access memory (RAM), read-only memory (ROM), electrically erasable programmable read-only memory (EEPROM), flash memory or other optical and magnetic storage media, which will not be elaborated here one by one.

[0073] The computer-readable storage medium provided by the above embodiments of the present disclosure and the power consumption calculation method provided by the embodiments of the present disclosure are based on the same inventive concept and have the same beneficial effects as the methods adopted, run, or implemented by the application programs stored therein.

[0074] It should be noted that: In the specification provided here, a large number of specific details are described. However, it can be understood that the embodiments of the present disclosure can be practiced without these specific details. In some instances, well-known structures and technologies are not shown in detail so as not to obscure the understanding of this specification.

[0075] Similarly, it should be understood that, in order to streamline the present disclosure and assist in understanding one or more of the various inventive aspects, in the above description of the exemplary embodiments of the present disclosure, the various features of the present disclosure are sometimes grouped together into a single embodiment, figure, or description thereof. However, the disclosed method should not be construed as reflecting the following schematic: that the claimed present disclosure requires more features than those expressly recited in each claim. Rather, as reflected in the following claims, the inventive aspects lie in less than all the features of the single embodiments disclosed previously. Thus, the claims following the detailed description are hereby expressly incorporated into the detailed description, where each claim itself serves as a separate embodiment of the present disclosure.

[0076] In addition, those skilled in the art can understand that, although some of the embodiments described herein include certain features included in other embodiments rather than other features, the combination of features of different embodiments means that it is within the scope of the present disclosure and forms different embodiments. For example, in the following claims, any one of the claimed embodiments can be used in any combination.

[0077] As described above, the above are only the preferred specific embodiments of the present disclosure, but the protection scope of the present disclosure is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed by the present disclosure should be covered by the protection scope of the present disclosure. Therefore, the protection scope of the present disclosure should be subject to the protection scope of the claims.

Claims

1. A propulsion system, characterized in that, Comprising: A nested inlet and an inner and outer double-duct blower device; The nested inlet includes a nested inner cylinder and a nested outer cylinder, and the inner and outer double-duct blower device includes an inner-duct blower device and an outer-duct blower device; The nested inner cylinder sucks in the mainstream and inputs the sucked mainstream to the inner-duct blower device, and the nested outer cylinder sucks in the boundary layer fluid and inputs the sucked boundary layer fluid to the outer-duct blower device.

2. The propulsion system according to claim 1, characterized in that, The nested inlet is a nested S-shaped inlet.

3. A method for calculating power consumption, characterized in that, Applied to the propulsion system according to claim 1 or 2, the method includes: Based on the target inference requirements of the propulsion system, the static pressure of the inlet environment of the propulsion system, and the flow rates through the nested inner cylinder and the nested outer cylinder, calculate the pressure ratio and design efficiency of the inner-duct blower device and the outer-duct blower device; Based on the static pressure of the inlet environment of the propulsion system, the flight Mach number, the pressure ratio and the design efficiency of the inner and outer double-duct blower device, calculate the total temperature at the outlet section of the inner-duct blower device, the total temperature at the inlet section of the inner-duct blower device, the total temperature at the outlet section of the outer-duct blower device, and the total temperature at the inlet section of the outer-duct blower device; Based on the total temperature at the outlet section of the inner-duct blower device, the total temperature at the inlet section of the inner-duct blower device, the total temperature at the outlet section of the outer-duct blower device, the total temperature at the inlet section of the outer-duct blower device, and the flow rates through the nested inner cylinder and the nested outer cylinder, calculate the power consumed by the propulsion system when meeting the target inference requirements.

4. The method according to claim 3, wherein Based on the total temperature at the outlet section of the inner-duct blower device, the total temperature at the inlet section of the inner-duct blower device, the total temperature at the outlet section of the outer-duct blower device, the total temperature at the inlet section of the outer-duct blower device, and the flow rates through the nested inner cylinder and the nested outer cylinder, calculating the power consumed by the propulsion system when meeting the target inference requirements includes: Calculating a first temperature difference between the total temperature at the outlet section of the inner-duct blower device and the total temperature at the inlet section of the inner-duct blower device, and calculating a second temperature difference between the total temperature at the outlet section of the outer-duct blower device and the total temperature at the inlet section of the outer-duct blower device; Calculating a first product of the first temperature difference and the flow rate through the nested inner cylinder, and calculating a second product of the second temperature difference and the flow rate through the nested outer cylinder; Calculating the sum of the first product and the second product to obtain the power consumed by the propulsion system when meeting the target inference requirements.

5. The method according to claim 3, wherein The method further includes: When obtaining the power consumed by the propulsion system when meeting the target inference requirements, calculating the energy-saving coefficient of the propulsion system based on the power; Evaluating the power benefit of the propulsion system based on the energy-saving coefficient.

6. The method according to claim 3, wherein Based on the static pressure of the inlet environment of the propulsion system, the flight Mach number, the pressure ratio and the design efficiency of the inner and outer double-duct blower device, calculating the total temperature at the outlet section of the inner-duct blower device, the total temperature at the inlet section of the inner-duct blower device, the total temperature at the outlet section of the outer-duct blower device, and the total temperature at the inlet section of the outer-duct blower device includes: Calculate the inlet cross-section temperature of the inlet duct based on the static pressure of the inlet environment and the Mach number of the inner barrel obtained based on the flight Mach number; and calculate the outlet cross-section temperature of the inlet duct based on the static pressure of the inlet environment and the Mach number of the outer barrel obtained based on the Mach number of the inner barrel. Use the inlet cross-section temperature of the inlet duct as the total temperature of the inlet cross-section of the core duct blower device, and use the outlet cross-section temperature of the inlet duct as the total temperature of the inlet cross-section of the bypass duct blower device. Calculate the total temperature of the outlet cross-section of the core duct blower device based on the inlet cross-section temperature of the inlet duct, the pressure ratio, and the design efficiency; and calculate the total temperature of the outlet cross-section of the bypass duct blower device based on the outlet cross-section temperature of the inlet duct, the pressure ratio, and the design efficiency.

7. A power consumption calculation device, characterized in that, Applied to the propulsion system according to claim 1 or 2, the device includes: A first calculation module for calculating the pressure ratio and design efficiency of the core duct blower device and the bypass duct blower device based on the target inference requirements of the propulsion system, the static pressure of the inlet environment of the propulsion system, and the flow rates flowing through the nested inner barrel and the nested outer barrel. A second calculation module for calculating the total temperature of the outlet cross-section of the core duct blower device, the total temperature of the inlet cross-section of the core duct blower device, the total temperature of the outlet cross-section of the bypass duct blower device, and the total temperature of the inlet cross-section of the bypass duct blower device based on the static pressure of the inlet environment of the propulsion system, the flight Mach number, the pressure ratio of the double-layer duct blower device, and the design efficiency. A third calculation module for calculating the power required for the propulsion system to consume under the condition of meeting the target inference requirements based on the total temperature of the outlet cross-section of the core duct blower device, the total temperature of the inlet cross-section of the core duct blower device, the total temperature of the outlet cross-section of the bypass duct blower device, the total temperature of the inlet cross-section of the bypass duct blower device, and the flow rates flowing through the nested inner barrel and the nested outer barrel.

8. An electronic device, comprising a memory, a processor, and a computer program stored on the memory, characterized in that, The processor executes the computer program to implement the steps of the method according to any one of claims 3-6.

9. A computer-readable storage medium having computer programs / instructions stored thereon, characterized in that, When the computer program / instructions are executed by the processor, the steps of the method according to any one of claims 3-6 are implemented.

10. A computer program product, comprising a computer program / instructions, characterized in that, When the computer program / instructions are executed by the processor, the steps of the method according to any one of claims 3-6 are implemented.

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