CN111412066B - Three-dimensional inward rotation air inlet channel with annular self-adaptive drainage tube and design method - Google Patents
Three-dimensional inward rotation air inlet channel with annular self-adaptive drainage tube and design method Download PDFInfo
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Abstract
The invention relates to a three-dimensional inward-turning air inlet with a circumferential self-adaptive drainage tube, which comprises a three-dimensional inward-turning air inlet isentropic compression profile, a three-dimensional inward-turning air inlet reflected shock wave post-isolation section and a circumferential self-adaptive drainage device, wherein the three-dimensional inward-turning air inlet isentropic compression profile is connected with the three-dimensional inward-turning air inlet reflected shock wave post-isolation section, and the circumferential self-adaptive drainage device is arranged at the connection position. According to the invention, while the advantages of the three-dimensional internal rotation air inlet channel are maintained, the annular self-adaptive drainage tube is adopted to introduce high-pressure airflow into low-speed low-energy boundary layer airflow, so that the total energy of the airflow in the boundary layer is increased, the boundary layer separation in the air inlet channel is inhibited, and the effect of widening the working Mach number of the three-dimensional internal rotation air inlet channel is achieved.
Description
Technical Field
The invention relates to the technical field of boundary layer control of a three-dimensional inward-rotation air inlet channel, in particular to a three-dimensional inward-rotation air inlet channel with a circumferential self-adaptive drainage tube and a design method.
Background
The research of hypersonic flight vehicles is the highest point of aerospace technical strategy competitive in all aviation strong countries. All the strong countries in the world are tightening the development plan for propelling hypersonic flight. For a hypersonic aircraft, the key technology of a propulsion system of the hypersonic aircraft is a scramjet engine technology, and the hypersonic ramjet engine is different from a traditional turbojet engine in an air compression part. The traditional turbojet engine needs to reduce and pressurize incoming flow by means of the blades of the gas compressor so as to meet the requirement of a combustion chamber on the state of the incoming flow, and the scramjet engine compresses supersonic/hypersonic incoming flow by means of a shock wave system in an air inlet channel part under the supersonic condition so as to reduce and pressurize the supersonic/hypersonic incoming flow, so that the combustion requirement of the combustion chamber of the scramjet engine is met, and therefore, the design of a hypersonic air inlet channel is also the important factor of the scramjet engine technology.
After long-term research, scholars at home and abroad propose a series of design methods of hypersonic inlet channels, wherein the representative configurations comprise a binary inlet channel, an axisymmetric inlet channel and a lateral pressure inlet channel. In addition to these configurations, researchers at home and abroad have conducted intensive research on a three-dimensional inward-contraction air intake duct with a high flow capture coefficient and excellent aerodynamic performance, which is called a three-dimensional inward-rotation air intake duct. The streamline tracking Busemann inlet [1] proposed by Billg et al, john Hopkins university, USA, the Funnel inlet [2] proposed by Ajay et al, astrox, USA, the three-dimensional inward-turning inlet which turns a rectangular inlet into an elliptical outlet [3] proposed by Smart et al, US aerospace research center, and the like. In China, you Yancheng and the like propose a three-dimensional inward turning air inlet design method called an inner waverider. Although such an intake duct has certain advantages in aerodynamic performance, the high flow capture capability also increases the burden of low mach number starting, which has a great influence on the operating speed range of the hypersonic aircraft. Therefore, how to widen the working range of the three-dimensional internal rotation air inlet and reduce the starting Mach number of the three-dimensional internal rotation air inlet is researched, and the method has extremely important significance for the development of the air inlet.
In order to widen the working range of the three-dimensional inward turning air inlet and reduce the starting Mach number of the three-dimensional inward turning air inlet, the two types of flow control including a variable geometry method and a fixed geometry condition are adopted by scholars at home and abroad at present. The variable geometry method is to adjust the compression profile of the air inlet according to the incoming flow Mach number so as to adjust the internal contraction ratio of the air inlet. The method is widely applied to the field of binary air inlets with simple structures, but the starting capability of the air inlet cannot be effectively improved due to the fact that the molded surface of the three-dimensional inward-turning air inlet is too complex.
Flow control under fixed geometry conditions is more common with boundary layer aspiration bleed flow. The low-speed low-energy flow in the air inlet channel can be eliminated under the working condition of low Mach number, so that the normal operation of the air inlet channel under the low Mach number is realized. However, aspiration drainage presents some problems: on one hand, the eliminated boundary layer airflow needs to be eliminated through the leakage flow channel, so that the leakage flow channel needs to penetrate through the interior of the fuselage to realize the connection of the wall surface of the air inlet channel and the external flow field of the aircraft, which inevitably has adverse effect on the internal layout of the fuselage; on the other hand, due to the existence of the leakage flow, the flow rate of the airflow flowing into the combustion chamber at the downstream of the air inlet channel is reduced, the combustion efficiency is influenced, and the thrust of the whole propulsion system is further influenced. Therefore, the effective boundary layer control technology provided under the condition of not reducing the flow rate has important significance on improving the thrust of the scramjet and widening the working range of the scramjet.
Disclosure of Invention
Aiming at the defects of the prior art, the invention aims to provide a three-dimensional inward turning air inlet with a hoop self-adaptive drainage tube and a design method, which are used for introducing high-pressure airflow into low-speed and low-energy boundary layer airflow by adopting the hoop self-adaptive drainage tube while keeping the advantages of the three-dimensional inward turning air inlet, so that the total energy of the airflow in the boundary layer is increased, the boundary layer separation in the air inlet is restrained, and the effect of widening the working Mach number of the three-dimensional inward turning air inlet is achieved.
The invention is realized by the following technical scheme.
A three-dimensional inward-turning air inlet passage with an annular self-adaptive drainage tube comprises a three-dimensional inward-turning air inlet passage isentropic compression profile, a three-dimensional inward-turning air inlet passage reflection shock wave post-isolation section and an annular self-adaptive drainage device, wherein the three-dimensional inward-turning air inlet passage isentropic compression profile is connected with the three-dimensional inward-turning air inlet passage reflection shock wave post-isolation section, and the annular self-adaptive drainage device is arranged at the connection position; the three-dimensional inner-rotation air inlet channel isentropic compression molded surface is provided with a waist-shaped three-dimensional inner-rotation air inlet channel inlet molded line and a three-dimensional inner-rotation air inlet channel shoulder molded line; the three-dimensional inward-rotation air inlet channel reflection laser rear isolation section is a circular pipe with the same diameter and is provided with a circular three-dimensional inward-rotation air inlet channel outlet molded line; the annular self-adaptive drainage device is in an annular layout and comprises a hollow annular self-adaptive drainage tube, a cylindrical high-pressure area airflow inflow tube, a cylindrical low-pressure area airflow outlet tube, a circular high-pressure area airflow inflow port and a circular low-pressure area airflow outflow port, the two ends of the high-pressure area airflow inflow tube are respectively connected with the annular self-adaptive drainage tube and the high-pressure area airflow inflow port, the two ends of the low-pressure area airflow outlet tube are respectively connected with the annular self-adaptive drainage tube and the low-pressure area airflow outflow port, the high-pressure area airflow inflow port is positioned in a three-dimensional inward turning air inlet channel reflection shock wave back isolation section at the lower part of a three-dimensional inward turning inlet channel shoulder profile, the low-pressure area airflow outflow port is positioned in a three-dimensional inward turning inlet channel equal entropy compression profile at the upper part of the three-dimensional inward turning inlet channel shoulder profile, and the high-pressure area airflow inflow port is communicated with the low-pressure area airflow outflow port through the high-pressure area airflow inflow tube, the annular self-adaptive drainage tube and the low-pressure area airflow outlet tube. When hypersonic incoming flow enters the isentropic compression profile area of the three-dimensional inward-turning air inlet channel, the boundary layer is generated on the wall surface, and the air flow can be guided to the low-pressure area from the high-pressure area through the annular self-adaptive drainage device according to the distribution rule of the high-pressure area and the low-pressure area in the three-dimensional inward-turning air inlet channel, so that the influence of the boundary layer on the performance of the three-dimensional inward-turning air inlet channel is weakened.
Preferably, the included angle between the airflow inflow pipe of the high-pressure area and the horizontal direction is less than 45 degrees, and the airflow inflow of the high-pressure airflow is facilitated by adopting a forward arrangement mode.
Preferably, the included angle between the airflow outlet pipe of the low-pressure area and the horizontal direction is more than 135 degrees, and the airflow inflow in the isentropic compression profile of the three-dimensional inward-turning air inlet channel can be inhibited by adopting the arrangement mode of the reverse flow direction, and the outflow efficiency of the airflow is improved.
A design method of a three-dimensional inward-turning air inlet channel with a circumferential self-adaptive drainage tube comprises the following steps:
(1) Generating a three-dimensional inward-turning air inlet channel;
(2) Selecting a relative high-pressure area as an airflow inlet position;
(3) Selecting a relatively low-pressure area as an airflow outlet position;
(4) And (4) designing an annular self-adaptive drainage tube to be connected with the inflow port and the outflow port according to the inflow and outflow positions obtained in the steps (2) and (3), and completing the design of the three-dimensional inward-turning air inlet channel with the annular self-adaptive drainage tube.
Preferably, in the step (1), a streamline tracing method is adopted in the three-dimensional inward-turning air inlet channel in the three-dimensional axisymmetric inward-contraction basic flow field, and the streamline generated according to the discrete point of the inlet profile of the three-dimensional inward-turning air inlet channel is distributed in the circumferential direction. The three-dimensional axisymmetric internally-contracted air inlet channel comprises an incident shock wave front uniform area, a reflected shock wave front isentropic supercharging area and a reflected shock wave rear high-pressure area. In the subsequent design of the annular drainage tube, high-pressure airflow is guided into the isentropic compression region by virtue of a high-pressure region after the shock wave is reflected.
Preferably, the air inlet position in the step (2) is arranged after the high-pressure area of the three-dimensional inward-turning air inlet, namely the reflected shock wave, and the position is located at the downstream of the shoulder molded line of the three-dimensional inward-turning air inlet; after the position of the airflow inlet is selected, the airflow inflow pipe is arranged in a forward flow mode, the included angle between the airflow inflow pipe and the horizontal direction is smaller than 45 degrees, and the forward flow arrangement mode is favorable for the inflow of high-pressure airflow.
Preferably, the air outflow port in the step (3) is arranged in a low-pressure area of the three-dimensional inward-turning air inlet channel, namely before the shock wave is reflected after the shock wave is incident, and the position is located at the upstream of the shoulder molded line of the three-dimensional inward-turning air inlet channel; after the position of the airflow outlet is selected, the airflow outflow pipe is arranged in a counter-flow mode, the included angle between the outflow pipe and the horizontal direction is larger than 135 degrees, the airflow inflow of the isentropic compression section of the three-dimensional inward-rotation air inlet channel can be restrained by adopting the counter-flow arrangement mode, and the outflow efficiency of the airflow is improved.
Preferably, the circumferential self-adaptive drainage tube in the step (4) adopts a circular-ring-shaped circular tube structure, is arranged outside the three-dimensional inward-rotation air inlet channel in a surrounding manner, and is connected with the inflow flow tube and the airflow outlet tube in parallel, so that the drainage purpose is achieved.
Compared with the prior art, the invention has the advantages that: the three-dimensional inward-turning air inlet channel with the annular self-adaptive drainage tube, which is generated by the design method, can remarkably widen the working range of the three-dimensional inward-turning air inlet channel; the annular self-adaptive flow guiding device obtained through the calculation design of the internal pressure difference of the three-dimensional inward-turning air inlet channel can guide the air flow in the air inlet channel from a high-pressure area to a low-pressure area so as to control the boundary layer in the equal entropy compression area and inhibit the flow separation of the shoulder position of the air inlet channel; in addition, the form of this adoption drainage tube can not additionally produce flow loss, when reducing the intake duct and starting mach number to the high thrust demand of whole propulsion system has been guaranteed.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention and not to limit the invention.
FIG. 1 is a three-dimensional axisymmetrically-adducted fundamental flow field;
FIG. 2 is a schematic diagram of a three-dimensional internal-rotation air inlet duct with an annular self-adaptive drainage tube;
FIG. 3 is a three-dimensional cross-sectional view of a three-dimensional inward-turning air inlet duct with an annular self-adaptive drainage tube;
FIG. 4 is a half-sectional view of a three-dimensional internal-rotation air inlet with an axially adaptive draft tube;
FIG. 5 is a bottom view of a three-dimensional inward turning air intake with an axially adaptive draft tube;
the labels in the figure are: 1 represents hypersonic inflow, 2 represents a three-dimensional axisymmetric internal contracted basic flow field revolution generatrix, 3 represents a three-dimensional axisymmetric basic flow field revolution axis, 4 represents a three-dimensional internal contracted basic flow field incident shock wave, 5 represents a three-dimensional internal turning intake channel internal contracted basic flow field reflected shock wave, 6 represents a uniform inflow region, 7 represents an isentropic compression region, 8 represents a high-pressure region after shock wave reflection, 9 represents a streamline for generating a three-dimensional internal turning intake channel, 10 represents a three-dimensional internal turning intake channel inlet profile, 11 represents a three-dimensional internal turning intake channel isentropic compression profile, 12 represents a three-dimensional internal turning intake channel shoulder profile, 13 represents a three-dimensional internal turning intake channel reflected post-isolation section, 14 represents a three-dimensional internal turning intake channel outlet profile, 15 represents a hoop adaptive draft tube, 16 represents a high-pressure region airflow inflow tube, 17 represents a low-pressure region airflow outlet tube, 18 represents a high-pressure region airflow inlet, 19 represents a low-pressure region airflow outlet, 20 represents a low-pressure region airflow outlet layer, 21 represents a low-pressure region outflow, 22 represents a high-pressure region inflow, and 23 represents a three-dimensional internal turning shoulder position.
Detailed Description
The following detailed description of the embodiments of the present invention will be provided with reference to the accompanying drawings and examples, so that how to implement the technical means for solving the technical problems and achieving the technical effects of the present invention can be fully understood and implemented, but the present invention is not limited thereto.
As shown in fig. 1-5;
a three-dimensional inward-turning air inlet channel with a circumferential self-adaptive drainage tube comprises a three-dimensional inward-turning air inlet channel isentropic compression molded surface 11, a three-dimensional inward-turning air inlet channel reflected shock wave post-isolation section 13 and a circumferential self-adaptive drainage device, wherein the three-dimensional inward-turning air inlet channel isentropic compression molded surface 11 is connected with the three-dimensional inward-turning air inlet channel reflected shock wave post-isolation section 13, and the circumferential self-adaptive drainage device is arranged at the connection position; the three-dimensional inner-turning air inlet isentropic compression molded surface 11 is provided with a waist-shaped three-dimensional inner-turning air inlet molded line 10 and a three-dimensional inner-turning air inlet shoulder molded line 12; the three-dimensional inward-turning air inlet channel reflection laser rear isolation section 13 is a circular pipe with the same diameter and is provided with a circular three-dimensional inward-turning air inlet channel outlet molded line 14; the annular self-adaptive drainage device is in an annular layout and comprises a hollow annular self-adaptive drainage tube 15, a cylindrical high-pressure area airflow inflow tube 16, a cylindrical low-pressure area airflow outlet tube 17, a circular high-pressure area airflow inflow port 18 and a circular low-pressure area airflow outflow port 19, wherein two ends of the high-pressure area airflow inflow tube 16 are respectively connected with the annular self-adaptive drainage tube 15 and the high-pressure area airflow inflow port 18, two ends of the low-pressure area airflow outlet tube 17 are respectively connected with the annular self-adaptive drainage tube 15 and the low-pressure area airflow outflow port 19, the high-pressure area airflow inflow port 18 is located in a three-dimensional inward turning air inlet channel reflection shock wave rear isolation section 13 at the downstream of a three-dimensional inward turning inlet channel shoulder profile 12, the low-pressure area airflow outflow port 19 is located in a three-dimensional inward turning inlet channel isentropic compression profile 11 at the upstream of the three-dimensional inward turning inlet channel shoulder profile 12, and the high-pressure area airflow inflow port 18 is communicated with the low-pressure area airflow outflow port 19 through the annular self-adaptive drainage tube 16, the annular self-adaptive drainage tube 15 and the high-pressure area airflow outlet tube 17. After hypersonic incoming flow enters the region of the isentropic compression molded surface 11 of the three-dimensional inward-turning air inlet, the boundary layer is generated on the wall surface, and the air flow can be guided to the low-pressure region from the high-pressure region through the annular self-adaptive drainage device according to the distribution rule of the high-pressure region and the low-pressure region in the three-dimensional inward-turning air inlet, so that the influence of the boundary layer on the performance of the three-dimensional inward-turning air inlet is weakened.
In a preferred embodiment, the included angle between the airflow inflow pipe of the high-pressure area and the horizontal direction is less than 45 degrees, and the airflow in the high-pressure area is facilitated by adopting a forward arrangement mode.
As a preferable embodiment, the included angle between the air flow outlet pipe of the low-pressure area and the horizontal direction is more than 135 degrees, the arrangement form of the reverse flow direction can inhibit the air flow inflow in the isentropic compression profile of the three-dimensional inward-turning air inlet channel, and the outflow efficiency of the air flow is improved.
The three-dimensional inward-rotation air inlet channel with the annular self-adaptive drainage tube can remarkably widen the working range of the three-dimensional inward-rotation air inlet channel. The annular self-adaptive drainage device obtained by calculating and designing the internal pressure difference of the three-dimensional inward-turning air inlet channel can drain the air flow in the air inlet channel from a high-pressure area to a low-pressure area so as to control the boundary layer in the equal entropy compression area and inhibit the flow separation of the shoulder position of the air inlet channel. In addition, the form of the draft tube can not additionally generate flow loss, and the high thrust requirement of the whole propulsion system is ensured while the starting Mach number of the air inlet channel is reduced.
A design method of a three-dimensional inward-turning air inlet channel with a circumferential self-adaptive drainage tube comprises the following steps:
(1) Generating a three-dimensional inward-turning air inlet channel, wherein the three-dimensional inward-turning air inlet channel consists of a three-dimensional inward-turning air inlet channel isentropic compression molded surface 11 and a three-dimensional inward-turning air inlet channel reflected laser post-isolation section 13, and the three-dimensional inward-turning air inlet channel isentropic compression molded surface 11 is generated in a three-dimensional axisymmetric inward-shrinkage basic flow field shown in the figure 1 by adopting a streamline tracing method; the generation mode is that the three-dimensional inward turning air inlet molded line 12 is dispersed, streamline tracing is carried out on the downstream direction according to the discrete point by taking the three-dimensional inward shrinkage basic flow field incident shock wave 4 as a starting point in a basic flow field, the streamline is stopped at the position of the three-dimensional inward turning air inlet in the shrinkage basic flow field reflected shock wave 5, and a series of obtained streamlines 9 for generating the three-dimensional inward turning air inlet are arranged in the circumferential direction to finally obtain the three-dimensional inward turning air inlet isentropic compression molded surface 11; the three-dimensional inward turning air inlet channel reflection shock wave rear isolation section 13 is obtained by stretching the shoulder molded line 12 of the three-dimensional inward turning air inlet channel backwards in an equal straight direction; the three-dimensional axisymmetric internally-contracted basic flow field comprises a uniform inflow region 6, an isentropic compression region 7 and a shock wave reflected high-pressure region 8, and the corresponding three-dimensional internally-rotated air inlet channel generated by the basic flow field also has the same regional distribution; in the subsequent design of the annular drainage tube, high-pressure airflow is introduced into the isentropic compression region 7 by the high-pressure region 8 after shock wave reflection, so that the effect of inhibiting boundary layer separation is achieved;
(2) Selecting a relative high-pressure area as an air flow inlet position, wherein the three-dimensional axisymmetric internally-contracted basic flow field shown in fig. 1 comprises a uniform inflow area 6, an isentropic compression area 7 and a shock wave reflected high-pressure area 8, and the corresponding three-dimensional inward-turning air inlet channels generated by the basic flow field also have the same area distribution; therefore, in the design of the inflow opening and the outflow opening of the annular drainage tube, high-pressure airflow is introduced into the isentropic compression zone 7 by the high-pressure zone 8 after shock wave reflection, so that the effect of inhibiting boundary layer separation is achieved; according to the distribution rule of the internal flow field pressure of the air inlet channel, the air inflow opening 18 of the high-pressure area is arranged in the high-pressure area of the three-dimensional inward-turning air inlet channel, namely the three-dimensional inward-turning air inlet channel reflection shock wave rear isolation section 13, and the position is located at the downstream of the shoulder molded line 12 of the three-dimensional inward-turning air inlet channel; after the high-pressure area air inflow opening 18 is selected, the high-pressure area air inflow pipe 16 is designed in a forward flow mode, the included angle between the high-pressure area air inflow pipe 16 and the horizontal direction is less than 45 degrees, and the forward flow arrangement mode is adopted to be beneficial to the inflow of high-pressure air;
(3) Selecting a relatively low-pressure area as an airflow outlet position, and arranging a low-pressure area outlet 19 in the isentropic compression molded surface 11 of the three-dimensional inward-turning air inlet according to the pressure distribution rule of the internal flow field of the air inlet, wherein the position is positioned at the upstream of the shoulder molded line 12 of the three-dimensional inward-turning air inlet; after the position of the low-pressure area outflow port 19 is selected, the low-pressure area airflow outlet pipe 17 is arranged in a reverse flow direction mode, the included angle between the low-pressure area airflow outlet pipe 17 and the horizontal direction is larger than 135 degrees, the airflow inflow in the three-dimensional inner-turning air inlet channel isentropic compression molded surface 11 can be inhibited by adopting the reverse flow direction arrangement mode, and the airflow outflow efficiency is improved;
(4) Designing an annular self-adaptive drainage tube 15 to communicate the high-pressure area gas inflow opening 18 and the low-pressure area outflow opening 19 according to the positions of the high-pressure area gas inflow opening 18 and the low-pressure area outflow opening 19 obtained in the steps (2) and (3), and completing the design of a three-dimensional inward-turning air inlet channel with the annular self-adaptive drainage tube; the annular self-adaptive drainage tube 15 is of an annular round tube structure, is arranged outside the three-dimensional inward turning air inlet channel in a surrounding mode, and is communicated with a high-pressure area air inflow port 18 and a low-pressure area outflow port 19 in parallel, so that high-pressure air flow of the isolation section 13 is introduced into a low-energy boundary layer 20 of the three-dimensional inward turning air inlet channel isentropic compression molded surface 11 after the three-dimensional inward turning air inlet channel reflects shock, and the effect of restraining the boundary layer 20 from being separated from the shoulder position 23 of the three-dimensional inward turning air inlet channel is achieved.
The design method of the three-dimensional inward-turning air inlet with the annular self-adaptive drainage tube has the advantages that the three-dimensional inward-turning air inlet is kept, meanwhile, the generation of boundary layer separation is restrained by adopting an annular self-adaptive drainage mode, and the working Mach number range of the three-dimensional inward-turning air inlet is widened.
The invention has the beneficial effects that: the three-dimensional inward-turning air inlet channel with the annular self-adaptive drainage tube, which is generated by the design method, can remarkably widen the working range of the three-dimensional inward-turning air inlet channel. The separation effect of the three-dimensional circumferential boundary layer of the compression profile of the air inlet channel can be effectively inhibited by utilizing the self-adaptive adjustment of the fluid between the high-pressure area and the low-pressure area in the three-dimensional inward turning air inlet channel, in addition, the method can not cause extra flow loss, and therefore, the pneumatic performance of the three-dimensional inward turning air inlet channel can be ensured while the starting Mach number of the air inlet channel is reduced.
While the invention has been described with reference to a preferred embodiment, it will be understood by those skilled in the art that various changes in form and detail may be made therein without departing from the spirit and scope of the invention.
Claims (2)
1. The three-dimensional inward-rotating air inlet with the annular self-adaptive drainage tube is characterized by comprising a three-dimensional inward-rotating air inlet isentropic compression profile, a three-dimensional inward-rotating air inlet reflection laser post-isolation section and an annular self-adaptive drainage device, wherein the three-dimensional inward-rotating air inlet isentropic compression profile is connected with the three-dimensional inward-rotating air inlet reflection laser post-isolation section, and the annular self-adaptive drainage device is arranged at the connection position; the three-dimensional inward-turning air inlet isentropic compression profile is provided with a waist-shaped three-dimensional inward-turning air inlet molded line and a three-dimensional inward-turning air inlet shoulder molded line; the three-dimensional inward-rotation air inlet channel reflection laser rear isolation section is a circular pipe with the same diameter and is provided with a circular three-dimensional inward-rotation air inlet channel outlet molded line; the annular self-adaptive drainage device is in an annular layout and comprises a hollow annular self-adaptive drainage tube, a cylindrical high-pressure area airflow inflow tube, a cylindrical low-pressure area airflow outlet tube, a circular high-pressure area airflow inflow port and a circular low-pressure area airflow outflow port, wherein two ends of the high-pressure area airflow inflow tube are respectively connected with the annular self-adaptive drainage tube and the high-pressure area airflow inflow port, two ends of the low-pressure area airflow outlet tube are respectively connected with the annular self-adaptive drainage tube and the low-pressure area airflow outflow port, the high-pressure area airflow inflow port is positioned in a three-dimensional inward turning air inlet channel reflection shock wave back isolation section at the downstream of a three-dimensional inward turning inlet channel shoulder profile, the low-pressure area airflow outflow port is positioned in a three-dimensional inward turning inlet channel isentropic compression profile at the upstream of the three-dimensional inward turning inlet channel shoulder profile, and the high-pressure area airflow inflow port is communicated with the low-pressure area airflow outflow port through the high-pressure area airflow inflow tube, the annular self-adaptive drainage tube and the low-pressure area airflow outlet tube;
the included angle between the high-pressure area airflow inflow pipe and the horizontal direction is less than 45 degrees, and the inflow of high-pressure airflow is facilitated by adopting a forward arrangement mode;
the included angle between the airflow outlet pipe of the low-pressure area and the horizontal direction is larger than 135 degrees, the airflow inflow in an isentropic compression profile of the three-dimensional inward-rotation air inlet channel can be restrained by adopting a reverse-flow arrangement mode, and the outflow efficiency of the airflow is improved.
2. The design method of the three-dimensional inward turning air inlet channel with the annular self-adaptive drainage tube is characterized by comprising the following steps of:
(1) Generating a three-dimensional inward-turning air inlet channel; in the step (1), a streamline tracking method is adopted in the three-dimensional inward-turning air inlet channel in the three-dimensional axisymmetric inward-contraction basic flow field, and streamlines generated by the three-dimensional inward-turning air inlet channel inlet profile discrete points are distributed in the circumferential direction to obtain the three-dimensional inward-turning air inlet channel; the three-dimensional axisymmetric internally-contracted air inlet channel comprises an incident shock wave front uniform area, a reflected shock wave front isentropic supercharging area and a reflected shock wave rear high-pressure area; in the subsequent design of the annular drainage tube, high-pressure airflow is introduced into an isentropic compression region by depending on a high-pressure region after the shock wave is reflected;
(2) Selecting a relatively high-pressure area as an airflow inlet position; the position of the air inlet in the step (2) is arranged after a high-pressure area of the three-dimensional inward-turning air inlet, namely reflected shock waves, and the position is positioned at the downstream of the shoulder molded line of the three-dimensional inward-turning air inlet; after the position of the airflow inlet is selected, the airflow inflow pipe is arranged in a downstream mode, the included angle between the airflow inflow pipe and the horizontal direction is less than 45 degrees, and the downstream arrangement mode is favorable for the inflow of high-pressure airflow
(3) Selecting a relatively low-pressure area as an airflow outlet position; the airflow outflow port is arranged in a low-pressure area of the three-dimensional inward turning air inlet channel, namely before shock waves are reflected after the shock waves enter, and the position is located at the upstream of the shoulder molded line of the three-dimensional inward turning air inlet channel; after the position of the airflow outlet is selected, the airflow outflow pipe is arranged in a counter-flow mode, the included angle between the outflow pipe and the horizontal direction is larger than 135 degrees, the airflow inflow of the isentropic compression section of the three-dimensional inward-rotation air inlet channel can be inhibited by adopting the counter-flow arrangement mode, and the outflow efficiency of the airflow is improved
(4) Designing an annular self-adaptive drainage tube to connect an inflow port and an outflow port according to inflow and outflow positions obtained in the steps (2) and (3) to complete the design of a three-dimensional inner-rotation air inlet channel with the annular self-adaptive drainage tube; the annular self-adaptive drainage tube in the step (4) adopts an annular circular tube structure, is arranged outside the three-dimensional inward-rotation air inlet channel in a surrounding manner, and is connected with the inflow tube and the airflow outlet tube in parallel in a ventilation manner, so that the drainage purpose is achieved.
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE69715303D1 (en) * | 1996-05-28 | 2002-10-17 | Lockheed Corp | Deflection device of air boundary layers |
| CN105156212A (en) * | 2015-10-09 | 2015-12-16 | 西北工业大学 | Variable geometry side pressure type air inlet passage of rocket-based-combined-cycle (RBCC) engine |
| CN205823451U (en) * | 2016-07-26 | 2016-12-21 | 厦门大学 | A kind of band rotates into air flue in flowing to the three-dimensional of suction channel completely |
| CN106250597A (en) * | 2016-07-26 | 2016-12-21 | 厦门大学 | Air flue design method is rotated in a kind of three-dimensional flowing to suction completely |
| CN110175408A (en) * | 2019-05-24 | 2019-08-27 | 南昌航空大学 | Air flue design method is rotated into three-dimensional with boundary-layer isolation aerial drainage |
| CN211975175U (en) * | 2020-04-27 | 2020-11-20 | 南昌航空大学 | Three-dimensional inward rotation air inlet channel with annular self-adaptive drainage tube |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6527224B2 (en) * | 2001-03-23 | 2003-03-04 | The Boeing Company | Separate boundary layer engine inlet |
-
2020
- 2020-04-27 CN CN202010342894.8A patent/CN111412066B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE69715303D1 (en) * | 1996-05-28 | 2002-10-17 | Lockheed Corp | Deflection device of air boundary layers |
| CN105156212A (en) * | 2015-10-09 | 2015-12-16 | 西北工业大学 | Variable geometry side pressure type air inlet passage of rocket-based-combined-cycle (RBCC) engine |
| CN205823451U (en) * | 2016-07-26 | 2016-12-21 | 厦门大学 | A kind of band rotates into air flue in flowing to the three-dimensional of suction channel completely |
| CN106250597A (en) * | 2016-07-26 | 2016-12-21 | 厦门大学 | Air flue design method is rotated in a kind of three-dimensional flowing to suction completely |
| CN110175408A (en) * | 2019-05-24 | 2019-08-27 | 南昌航空大学 | Air flue design method is rotated into three-dimensional with boundary-layer isolation aerial drainage |
| CN211975175U (en) * | 2020-04-27 | 2020-11-20 | 南昌航空大学 | Three-dimensional inward rotation air inlet channel with annular self-adaptive drainage tube |
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