CN109733634B - Design method of three-dimensional inward-turning four-channel hypersonic combined air inlet channel - Google Patents
Design method of three-dimensional inward-turning four-channel hypersonic combined air inlet channel Download PDFInfo
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Abstract
A design method of a three-dimensional inward turning four-channel hypersonic combined air inlet channel is disclosed. Designing a stamping channel with the working Mach number range of Ma being 4-6; designing an ejection rocket channel splitter plate and a turbine channel splitter plate, wherein airflow entering the ejection rocket channel and the turbine channel is adjusted by rotating the splitter plate, and the splitter plate is designed by combining the layout of the ejection rocket channel and the turbine channel; designing a turbine channel expansion section with the working Mach number range Ma being 0-2; and designing an ejection rocket channel expansion section with the working Mach number range of Ma being 2-4. The three-dimensional inner-rotation four-channel hypersonic combined air inlet comprises a three-dimensional inner-rotation air inlet compression molded surface, a stamping channel expansion isolation section, a turbine channel flow distribution section, a turbine channel type rectangular adjustable expansion section, a turbine channel type adjustable non-adjustable expansion section, an ejection rocket channel flow distribution section, an ejection rocket channel type rectangular adjustable expansion section and an ejection rocket channel type non-adjustable expansion section.
Description
Technical Field
The invention relates to a hypersonic inlet channel of a wide-speed-range aircraft, in particular to a design method of a three-dimensional inner-turning four-channel hypersonic combined inlet channel.
Background
Since the birth of the aerocraft, the aerocraft is always the object of the development of countries in the world, and the status of the aerocraft is very important no matter the aerocraft is used as transportation or national defense equipment. The pursuit of human beings for aircraft performance and speed is endless, and a great deal of scientific research and innovation makes aircraft rapidly develop from subsonic flight to transonic, supersonic and hypersonic flight that is vigorously developed in many countries at present. The hypersonic aircraft has a wider flight speed range, and the engine in a single mode cannot meet the requirements of the hypersonic aircraft in the past, so a combined power device appears, and aims to provide reliable power for the hypersonic aircraft (1 Zhang Huajun, Guo Rong Wei, Libo TBCC air inlet research status and the key technology thereof [ J ] aerodynamic report, 2010, 28 (05): 613 + 620).
The development of hypersonic aircrafts is greatly promoted by the appearance of the combined power device, and the conventional single-mode air inlet duct cannot provide stable high-quality air flow for the multi-mode combined power device. The air inlet channel is an important component in a hypersonic propulsion system, and the combined engine can only work with high performance if the air inlet channel provides stable high-quality incoming flow. (2) Penwavelet combined power aircraft technology develops [ J ] missile and space transport technology, 2016 (5): 1-6) along with the development of a TBCC combined engine (combination of a turbine and a ramjet), the dual-channel air inlet channels which are relatively simple in structure and are connected in parallel inside and outside have relatively more development, and the dual-channel air inlet channels realize the conversion of the modes of the air inlet channels by controlling the rotation of a splitter plate. However, since the starting mach number of the ramjet engine is high, the turbine engine needs to work to a high mach number to perform mode conversion, and the conventional turbine engine cannot meet the requirement, so that insufficient thrust occurs when the mode conversion is performed on the air inlet duct of the type. In order to make up for the defect, the Trijet combined engine (combination of a turbine, an ejector rocket and a ramjet engine) develops the air inlet into a three-channel combined air inlet, increases an ejector rocket mode on the basis of a dual mode, forms transition from the turbine mode to the punching mode, and makes up for insufficient thrust in the process of converting the aircraft from the turbine to the punching mode, wherein a typical section is a hypersonic three-channel air inlet with an upper type, a middle type and a lower type (the upper type, the middle type and the lower type are respectively a turbine channel, an ejector rocket channel and a punching channel). Although the combined power of the type improves the situation of insufficient thrust in the mode conversion process to a certain extent, new problems are brought to the same time, such as local excessive expansion of airflow caused by an excessive rotation angle of a flow distribution plate of an air inlet in the mode conversion process, insufficient flow caused by an excessively small area of an inlet of a turbine channel and the like. Due to the fact that the design of the air inlet channel is insufficient, combined power cannot work in a high-performance mode, and therefore the high-performance air inlet channel can promote the development of the hypersonic aircraft to a certain extent.
Considering the design defects of the double-channel air inlet channel and the three-channel air inlet channel, the combination of three power devices including a turbine, an injection rocket and a ramjet is also adopted, a new air inlet channel layout mode is selected, and the hypersonic air inlet channel is optimally designed into a four-channel combined air inlet channel. Two sides of the four-channel air inlet channel are turbine channels, namely two turbine engines work simultaneously, so that sufficient thrust is provided for the aircraft; the upper side of the middle part is provided with an ejection rocket channel, and ejection rocket boosting is adopted, so that the stable transition from a turbine to a stamping mode is realized, and the smooth operation of the stage-changing process of the engine is ensured; the lower side of the middle part is provided with a stamping channel, and a high-performance stamping engine is adopted to provide sufficient thrust for the aircraft in a high-speed state. The splitter plates of the four-channel combined air inlet channel are respectively arranged on the upper side and the left side and the right side of the stamping channel, so that the problems of expansion and the like caused by overlarge rotation angle of a single splitter plate are avoided, and the design defect of the three-channel air inlet channel can be effectively improved. The four-channel air inlet in the layout form has the advantages of compact structure, stable and reliable mode conversion process and good working performance, promotes the research on the mode conversion of the air inlet, and has important significance for the development of combined power technology and hypersonic aircrafts.
Disclosure of Invention
The invention aims to provide a design method of a three-dimensional internal-rotation four-channel hypersonic combined air inlet passage, which can improve the stability of a mode conversion process, has a more compact layout form and higher working performance under each mode.
The invention comprises the following steps:
1) designing a stamping channel with the working Mach number range of Ma being 4-6;
in step 1), the specific method for designing the stamping channel with the operating mach number of Ma being 4-6 may be as follows:
(1) designing a three-dimensional inner-rotation rectangular compression molded surface: the design of the stamping channel takes an ICFD flow field as a design basis, the design Mach number of the stamping channel is taken as an incoming flow condition, a wall molded line of an internally contracted basic flow field is obtained in the ICFD flow field according to the required incoming flow Mach number, throat Mach number and an initial wedge angle at the front end of a compression molded surface, and an effective part of a flow line of the basic flow field is selected according to the design requirement; then solving an axisymmetric internally contracted basic flow field by using a characteristic line method to obtain an incident shock wave of an internally waverider-derived air inlet and a reflected shock wave of the axisymmetric internally contracted basic flow field, wherein the intersection point of the incident shock wave and the rotation center line of the basic flow field is designed as the lip of the air inlet, the intersection point of the incident shock wave and the effective part of the flow line of the basic flow field is designed as the position of the front edge point of the air inlet, and the intersection point of the reflected shock wave and the effective part of the flow line of the basic flow field is the effective terminal point of; then according to the design of a shoulder of the three-dimensional inner-rotation-like rectangular compression molded surface, a streamline traced out by using a reverse streamline tracing method in the obtained basic flow field is dispersed into a point set through an effective part of the basic streamline to form the three-dimensional inner-rotation-like rectangular compression molded surface with the inlet and outlet sections being similar to rectangles;
(2) stamping a channel isolation section: the stamping through isolation section is designed into an expansion profile, the stamping channel isolation section is designed according to the expansion ratio of the stamping channel isolation section and the requirement of the oval outlet of the stamping channel isolation section, and the profile is generated by adopting area uniform transition between the shoulder of the three-dimensional inner-rotation rectangular compression profile and the oval outlet of the stamping channel isolation section.
2) Designing an ejection rocket channel splitter plate and a turbine channel splitter plate, wherein airflow entering the ejection rocket channel and the turbine channel is adjusted by rotating the splitter plate, and the splitter plate is designed by combining the layout of the ejection rocket channel and the turbine channel;
in step 2), the splitter plate for the ejector rocket passage and the splitter plate for the turbine passage are designed, the airflow entering the ejector rocket passage and the turbine passage is adjusted by rotating the splitter plate, and the specific method for designing by combining the layout of the ejector rocket passage and the turbine passage when the splitter plate is designed can be divided into the following steps:
(1) designing a splitter plate of an ejection rocket channel and a splitter plate of a turbine channel: the rocket ejector channel and the turbine channel do not share the same splitter plate, the rocket ejector channel splitter plate is arranged on the upper wall surface of the three-dimensional inner-rotation type rectangular compression profile, and the two turbine channel splitter plates are arranged on the left side and the right side of the three-dimensional inner-rotation type rectangular compression profile; the compression ratio of the vertical cross-sectional area where the molded line at the tail end of the diversion plate of the ejection rocket channel and the shoulder area of the compression profile of the three-dimensional inward-turning air inlet channel is controlled to be below 1.1, the tail end of the diversion plate of the ejection rocket channel is selected according to design requirements, the rotation angle of the diversion plate of the ejection rocket channel is ensured not to be too large according to the preset area of an outlet of the diversion section of the ejection rocket channel, the diversion plate extends forwards from the rotated tail end to intersect with the three-dimensional inward-turning rectangular compression profile, and the intersection line is designed to be the rotation shaft of the diversion plate of the ejection rocket channel; the rotating shaft of the turbine channel splitter plate and the rotating shaft of the ejector rocket channel splitter plate are controlled to be on the same section, and the tail end of the turbine channel splitter plate is determined according to the preset outlet area of the turbine channel splitter section and the requirement that the rotating angle of the turbine channel splitter plate is not too large;
(2) designing the rotating angle of the splitter plate of the channel of the ejector rocket and the rotating angle of the splitter plate of the channel of the turbine: the rotation angle depends on the length of the diversion plate of the ejection rocket channel, the tail end of the turbine channel and the inlet area requirements of the expansion section of the ejection rocket channel and the expansion section of the turbine channel, and is controlled not to exceed 10 degrees in order to reduce the influence of expansion, and the rotation angle of the diversion plate of the ejection rocket channel and the rotation angle of the diversion plate of the turbine channel are determined according to the rotation shaft of the diversion plate of the ejection rocket channel and the rotation shaft of the diversion plate of the turbine channel designed in the step (1);
(3) designing a rotating mode of the flow distribution plate: the rotation of the ejector rocket channel splitter plate and the turbine channel splitter plate in the mode conversion process can affect the passing air flow and generate a local expansion phenomenon, and in order to reduce the influence, the incoming flow flows into the turbine channel, the ejector rocket channel and the stamping channel as stably as possible, and the splitter plate is adjusted by selecting a uniform rotation mode.
3) Designing a turbine channel expansion section with the working Mach number range Ma being 0-2;
in step 3), the specific method for designing the turbine channel expansion section with the operating mach number of Ma being 0-2 may be as follows:
(1) designing a turbine channel rectangular-like adjustable expansion section: the rotating molded surface of the turbine channel quasi-rectangular adjustable expansion section can be adjusted in rotation in the mode conversion, so that the adjustment synchronization of the turbine channel quasi-rectangular adjustable expansion section and the adjustment of the turbine channel splitter plate is controlled, and the sealing performance in the mode conversion process is improved; the rotating molded surface of the turbine channel quasi-rectangular adjustable expansion section rotates in the mode conversion process, and the expansion section is designed to be quasi-rectangular; determining the length of the adjustable expansion section of the turbine channel and a rotating shaft of the rotating profile of the rectangular-like adjustable expansion section of the turbine channel by combining the outlet section of the flow dividing section of the turbine channel according to the designed expansion ratio of the expansion section and the rotating angle within 15 degrees; generating the rest molded surfaces of the turbine channel quasi-rectangular adjustable expansion section between the outlet of the turbine channel quasi-rectangular adjustable expansion section and the outlet of the turbine channel flow dividing section in a form of uniform and excessive area according to the determined shape of the outlet of the turbine channel quasi-rectangular adjustable expansion section;
(2) designing a non-adjustable expansion section of a turbine channel: the outlet of the turbine channel quasi-rectangular adjustable expansion section is quasi-rectangular, the cross section of the outlet of the turbine channel is circular, and a cubic curve is used for ensuring smooth transition of the molded surface of the turbine channel non-adjustable expansion section; and generating a cubic curve connecting the inlet and the outlet of the non-adjustable expansion section of the turbine channel by using the slope of the end point arranged by tangency of the two ends of the slope with the outlet of the turbine channel quasi-rectangular adjustable expansion section and the outlet of the turbine channel, and then generating the molded surface of the non-adjustable expansion section of the turbine channel in a form of uniform area transition.
4) And designing an ejection rocket channel expansion section with the working Mach number range of Ma being 2-4.
In the step 4), the specific method for designing the ejector rocket channel expansion section with the working mach number range of Ma being 2-4 may be as follows:
(1) designing an ejection rocket channel type rectangular adjustable expansion section: the rotating profile of the rectangular adjustable expansion section of the ejection rocket channel is adjustable in rotation in mode conversion, so that the adjustment synchronization of the rotating profile and the ejection rocket channel splitter plate is controlled, and the sealing property in the mode conversion process is improved; the rotating molded surface of the rectangular-like adjustable expansion section of the rocket ejecting channel rotates in the mode conversion process, and the expansion section is designed into a rectangular-like shape; determining the length of the adjustable expansion section of the rocket ejector channel and a rotating shaft of a rotating profile of the rectangular adjustable expansion section of the rocket ejector channel by combining the section of an outlet of the diversion section of the rocket ejector channel according to the designed expansion ratio of the expansion section and the rotating angle within 20 degrees; generating other molded surfaces of the ejection rocket channel type rectangular adjustable expansion section between the form of uniform and transitional area and the exit of the ejection rocket channel diversion section according to the determined exit shape of the ejection rocket channel type rectangular adjustable expansion section;
(2) designing an unadjustable expansion section of an ejection rocket channel: the section of an outlet of the rectangular adjustable expansion section of the ejector rocket channel is rectangular, the section of an outlet of the ejector rocket channel is circular, and a cubic curve is used for ensuring smooth transition of the molded surface of the non-adjustable expansion section of the ejector rocket channel. And generating a cubic curve connecting the inlet and the outlet of the non-adjustable expansion section of the ejector rocket channel by using the slope of the end point arranged at the two ends of the slope tangent to the outlet section of the rectangular adjustable expansion section of the ejector rocket channel and the outlet section of the ejector rocket channel, and then generating the molded surface of the non-adjustable expansion section of the ejector rocket channel by adopting a form of uniform area transition.
The invention provides a design method of a three-dimensional inward-turning four-channel hypersonic combined air inlet channel, which has novel layout, compact structure and reasonable design, on the basis of considering the defects of an inward-parallel double-channel hypersonic air inlet channel and a three-channel hypersonic combined air inlet channel.
The invention designs a three-dimensional inner-turning four-channel hypersonic combined air inlet channel, which structurally comprises: the three-dimensional internal rotation type rocket engine comprises a three-dimensional internal rotation air inlet compression profile, a stamping channel expansion isolation section, a turbine channel flow distribution section, a turbine channel type rectangular adjustable expansion section, a turbine channel type non-adjustable expansion section, an injection rocket channel flow distribution section, an injection rocket channel type rectangular adjustable expansion section and an injection rocket channel type non-adjustable expansion section. Wherein three-dimensional adversion intake duct compression profile adopts characteristic line method and the technical generation of reverse flow line tracking, and reposition of redundant personnel section profile is through rotatory generation, and other profiles are according to the even transition generation of area.
The invention has the following advantages: the hypersonic combined air inlet passage with the three-dimensional inward rotation four channels is designed into a double-turbine channel, more reliable thrust guarantee can be provided for the aircraft at low speed, and the combined power device of the turbine, the stamping and the ejection rocket enables the aircraft to have a wider flight speed range. Each flow distribution plate controls the flow distribution of a single channel, the rotation angle of the flow distribution plate is small, and the problems of expansion caused by overlarge rotation angle of the three-channel flow distribution plate and insufficient flow of a turbine channel and an ejection rocket channel are solved. The isolation section of the stamping channel is an expansion profile, so that the back pressure resistance of the stamping channel is improved to a certain extent; the expansion sections of the turbine channel and the ejection rocket channel are both designed to be a combination of an adjustable rectangular expansion section and an unadjustable rectangular-to-circular expansion section, and the adjustable expansion section and the splitter plate rotate synchronously in the mode conversion process, so that the compactness of the structure and the tightness in the mode conversion process are improved, and the mode conversion performance of the air inlet channel is improved to a certain extent. The four-channel air inlet channel is compact in channel layout, reduces the windward area and the external resistance, and is more in line with the requirements of future aircrafts in structural form.
Drawings
Fig. 1 is a basic flow field schematic diagram of a three-dimensional inward turning four-channel hypersonic combined air inlet.
FIG. 2 is a two-dimensional projection of the three-dimensional inward-turning rectangular compression profile inlet and shoulder of the three-dimensional inward-turning four-channel hypersonic combined intake.
FIG. 3 is a schematic diagram of a stamped channel design for a three-dimensional internal-turning four-channel hypersonic combined intake.
FIG. 4 is a schematic diagram of the design of an ejector rocket passage and a turbine passage of a three-dimensional inward-turning four-passage hypersonic combined air inlet passage.
FIG. 5 is a schematic diagram of the rotation of the splitter plate and the rotating wall of the adjustable expansion section of the three-dimensional inward turning four-channel hypersonic combined intake duct.
FIG. 6 is a front view of the inlet of a three-dimensional internal-turn four-channel hypersonic combined intake.
FIG. 7 is a full mode view of a three-dimensional internal-turn four-channel hypersonic combined inlet.
In FIGS. 1 to 7, the symbols are: 1 represents an initial wedge angle of the front end of a compression profile, 2 represents a wall profile of an inner contraction basic flow field, 3 represents an effective part of a flow line of the basic flow field, 4 represents an effective terminal point of the inner contraction basic flow field, 5 represents a reflection shock wave, 6 represents a lip of an air inlet, 7 represents an incident shock wave, 8 represents a gyration central line of the basic flow field, 9 represents a position of a front edge of the air inlet, 10 represents a two-dimensional projection of a capture profile of the front edge of the air inlet, 11 represents a two-dimensional projection of a shoulder of a three-dimensional inner rotation type rectangular compression profile, 12 represents a flow line tracked by a reverse flow line tracing method, 13 represents a point set into which an effective part of the basic flow line is scattered, 14 represents an axisymmetric inner contraction basic flow field, 15 represents a flow line projection on an initial cone surface of the air inlet, 16 represents a two-dimensional projection of a three-dimensional inner rotation, 19 denotes a stamping channel of an air inlet, 20 denotes an oval outlet of a stamping channel isolation section, 21 denotes a stamping channel isolation section, 22 denotes a shoulder of a three-dimensional inner-rotation-type rectangular compression profile, 23 denotes a tail end of a turbine channel splitter plate, 24 denotes a turbine channel splitter plate, 25 denotes a rotating shaft of a turbine channel splitter plate, 26 denotes a rotating shaft of an ejection rocket channel splitter plate, 27 denotes a rotating angle of the ejection rocket channel splitter plate, 28 denotes an outlet cross section of the ejection rocket channel splitter section, 29 denotes a rotating profile of a rectangular adjustable expansion section of an ejection rocket channel, 30 denotes an ejection rocket channel rectangular adjustable expansion section, 31 denotes a rotating shaft of a rotating profile of a rectangular adjustable expansion section of an ejection rocket channel, 32 denotes an outlet cross section of a rectangular adjustable expansion section of an ejection rocket channel, 33 denotes an unadjustable expansion section of an ejection rocket channel, 34 denotes an outlet cross section of an ejection rocket channel, and, 35 represents an outlet cross section of a turbine channel, 36 represents a non-adjustable expansion section of the turbine channel, 37 represents an outlet of a quasi-rectangular adjustable expansion section of the turbine channel, 38 represents a rotating shaft of a rotating profile of the quasi-rectangular adjustable expansion section of the turbine channel, 39 represents a rotating profile of the quasi-rectangular adjustable expansion section of the turbine channel, 40 represents a quasi-rectangular adjustable expansion section of the turbine channel, 41 represents an outlet cross section of a flow dividing section of the turbine channel, 42 represents a rotating angle of a flow dividing plate of the turbine channel, 43 represents a front end compression profile of a four-channel air inlet channel, 44 represents a position schematic of a flow dividing plate of an ejector rocket channel in a mode conversion process, 45 represents a gap formed by the flow dividing plate of the ejector rocket channel and the rotating profile of the adjustable expansion section of the ejector rocket channel in the mode conversion process, 46 represents a position schematic of a rotating plate of the adjustable expansion section of the ejector rocket channel in the mode conversion process, 47 represents a position, 48 represents a gap formed between the turbine channel splitter plate and the rotating profile of the turbine channel adjustable expansion section in the mode conversion process, 49 represents a position schematic of the turbine channel splitter plate in the mode conversion process, 50 represents an ejection rocket channel splitter section, 51 represents an ejection rocket channel, 52 represents an ejection rocket channel expansion section, 53 represents a turbine channel expansion section, 54 represents a turbine channel, and 55 represents a turbine channel splitter section.
Detailed Description
The following examples will further illustrate the present invention with reference to the accompanying drawings.
Referring to fig. 1 to 7, an embodiment of the present invention includes the following steps:
1) the stamping channel 19 with the work Mach number range of Ma 4-6 is designed, and mainly comprises the following components:
(1) designing a three-dimensional inner-rotation-like rectangular compression molded surface 17: the design of the stamping channel 19 is based on an ICFD flow field, the design Mach number of the stamping channel 19 is taken as an incoming flow condition, a wall molded line 2 of an inner shrinkage basic flow field is obtained in the ICFD flow field according to the required incoming flow Mach number, throat Mach number and an initial wedge angle 1 at the front end of a compression molded surface, and an effective part 3 of a flow line of the basic flow field is selected according to the design requirement; then solving an axisymmetric internally contracted basic flow field 14 by using a characteristic line method to obtain an incident shock wave 7 of an internally waverider-derived air inlet and a reflected shock wave 5 of the axisymmetric internally contracted basic flow field 14, wherein the intersection point of the incident shock wave 7 and a rotation central line 8 of the basic flow field is designed as a lip 6 of the air inlet, the intersection point of the incident shock wave 7 and an effective part 3 of a flow line of the basic flow field is designed as an air inlet front edge point position 9, and the intersection point of the reflected shock wave 5 and the effective part 3 of the flow line of the basic flow field is an internally contracted basic flow field effective terminal point 4; then, according to the design of the shoulder 22 of the three-dimensional inward-turning rectangular compression profile, a streamline 12 traced out by using a reverse streamline tracing method in the obtained basic flow field forms a three-dimensional inward-turning rectangular compression profile 17 with the inlet and outlet sections being similar to rectangles through a point set 13 formed by dispersing the effective part of the basic streamline, and a streamline projection 15 on the initial conical section of the air inlet channel, a two-dimensional projection 10 of the capture profile of the front edge of the air inlet channel, a two-dimensional projection 11 of the shoulder of the three-dimensional inward-turning rectangular compression profile and a two-dimensional projection 16 of the three-dimensional inward-turning rectangular compression profile in the structure are shown in.
(2) Designing the stamping channel isolation section 21: the stamping through isolation section 21 is designed into an expansion profile, the stamping channel isolation section 21 is designed according to the expansion ratio of the stamping channel isolation section 21 and the requirement of the stamping channel isolation section oval outlet 20, and the profile is generated by adopting uniform area transition between the three-dimensional inner-rotation type rectangular compression profile shoulder 22 and the stamping channel isolation section oval outlet 20.
2) The design of the splitter plate 18 and the splitter plate 24 of the ejector rocket passage is that the airflow entering the ejector rocket passage 51 and the turbine passage 54 is adjusted by the rotation of the splitter plate, and the design of the splitter plate is carried out by combining the layout of the ejector rocket passage 51 and the layout of the turbine passage 54, and the design mainly comprises the following steps:
(1) designing the ejector rocket channel splitter plate 18 and the turbine channel splitter plate 24: the rocket ejector passage 51 and the turbine passage 54 do not share the same splitter plate, the rocket ejector passage splitter plate 18 is arranged on the upper wall surface of the three-dimensional inner-rotation-type rectangular compression profile 17, and the two turbine passage splitter plates 24 are arranged on the left side and the right side of the three-dimensional inner-rotation-type rectangular compression profile 17. The compression ratio of the vertical cross section area where the molded line at the tail end of the ejector rocket channel splitter plate 18 is located and the area of the shoulder 22 of the three-dimensional inward-turning air inlet compression molded surface is controlled to be below 1.1, the tail end of the ejector rocket channel splitter plate 18 is selected according to design requirements, the rotating angle of the ejector rocket channel splitter plate 18 is ensured not to be too large according to the preset area of an outlet of the ejector rocket channel splitter section 50, the rotating tail end extends forwards to intersect with the three-dimensional inward-turning rectangular compression molded surface 17, and the intersecting line is designed to be the rotating shaft 26 of the ejector rocket channel splitter plate; the rotating shaft 25 of the turbine channel splitter plate and the rotating shaft 26 of the ejector rocket channel splitter plate are controlled to be on the same cross section, and the tail end 23 of the turbine channel splitter plate is determined according to the preset outlet area of the turbine channel splitter section 55 and the requirement that the rotating angle of the turbine channel splitter plate 24 is not too large.
(2) Designing the rotation angle 27 of the splitter plate of the ejector rocket passage and the rotation angle 42 of the splitter plate of the turbine passage: the rotation angle depends on the inlet areas of the rocket ejector passage expanding section 52 and the turbine passage expanding section 53, the rotation angle is controlled not to exceed 10 degrees in order to reduce the influence of expansion, and the rotation angle 27 of the rocket ejector passage splitter plate and the rotation angle 42 of the turbine passage splitter plate are determined according to the rotation shaft 26 of the rocket ejector passage splitter plate and the rotation shaft 25 of the turbine passage splitter plate designed in the step (1).
(3) Designing a rotating mode of the flow distribution plate: the rotation of the splitter plate 18 and the splitter plate 24 during the mode conversion affects the passing airflow to cause local expansion of the airflow, so that the incoming flow flows as smoothly as possible into the turbine passage 54, the ejector rocket passage 51 and the ram passage 19, and the splitter plates are adjusted by selecting a uniform rotation mode in order to reduce the influence.
3) The turbine channel expanding section 53 with the designed working Mach number range of Ma being 0-2 mainly comprises:
(1) designing the turbine channel quasi-rectangular adjustable expansion section 40: the rotating molded surface 39 of the turbine channel rectangular-like adjustable expansion section can rotate and be adjusted in the mode conversion process, so that the adjustment synchronization of the rotating molded surface 39 and the adjustment of the turbine channel splitter plate 24 is controlled, and the sealing performance in the mode conversion process is improved. Since the rotating profile 39 of the turbine channel rectangular-like adjustable expansion segment rotates during the mode conversion process, the segment is designed to be rectangular-like. The length of the turbine channel adjustable expansion section 40 and the rotating shaft 38 of the turbine channel rectangular-like adjustable expansion section rotating profile are determined by combining the outlet section 41 of the turbine channel flow dividing section according to the designed expansion ratio of the section and the rotating angle within 15 degrees. The remaining profile of the turbine channel rectangular-like adjustable expansion section 40 is generated between the outlet cross section 41 of the turbine channel flow dividing section and the form of a uniform area transition according to the determined shape of the outlet 37 of the turbine channel rectangular-like adjustable expansion section.
(2) Design of turbine channel non-adjustable expansion section 36: the outlet 37 of the turbine channel quasi-rectangular adjustable expansion section is quasi-rectangular, the outlet section 35 of the turbine channel is circular, and a cubic curve is used for ensuring smooth transition of the profile of the turbine channel non-adjustable expansion section 36. And generating a cubic curve connecting the inlet and the outlet of the non-adjustable expansion section 36 of the turbine channel by using the slope of the end point arranged at the two ends of the slope tangent to the outlet 37 of the turbine channel rectangular-like adjustable expansion section and the outlet section 35 of the turbine channel, and then generating the molded surface of the non-adjustable expansion section 36 of the turbine channel in a form of uniform area transition.
4) The design work Mach number range is 2 ~ 4 draw and penetrate rocket passageway expansion section 52 for Ma, mainly includes:
(1) designing an ejection rocket passage type rectangular adjustable expansion section 30: the rotating molded surface 29 of the rectangular adjustable expansion section of the rocket channel is adjustable in rotation in mode conversion, so that the adjustment of the rotating molded surface is controlled to be synchronous with the adjustment of the splitter plate 18 of the rocket channel, and the sealing performance in the mode conversion process is improved. As the rotating molded surface 29 of the rectangular-like adjustable expansion section of the rocket channel is rotated in the mode conversion process, the section is designed to be rectangular-like. According to the designed expansion ratio of the section and the rotation angle within 20 degrees, the length of the adjustable expansion section 30 of the ejector rocket channel and the rotation axis 31 of the rotation profile of the rectangular adjustable expansion section of the ejector rocket channel are determined by combining the outlet section 28 of the splitter section of the ejector rocket channel. And generating the rest molded surfaces of the ejection rocket channel type rectangular adjustable expansion section 30 between the determined shape of the outlet section 32 of the ejection rocket channel type rectangular adjustable expansion section and the outlet section 28 of the ejection rocket channel diversion section in a form of uniform and excessive area.
(2) Designing an unadjustable expansion section 33 of the rocket ejection channel: the outlet section 32 of the rectangular-like adjustable expansion section of the ejector rocket channel is rectangular-like, the outlet section 34 of the ejector rocket channel is circular, and a cubic curve is used for ensuring smooth transition of the section surface of the non-adjustable expansion section 33 of the ejector rocket channel. The slope of the end point is arranged at the two ends of the ejection rocket channel tangent to the outlet section 32 of the rectangular adjustable expansion section of the ejection rocket channel and the outlet section 34 of the ejection rocket channel to generate a cubic curve connecting the inlet and the outlet of the ejection rocket channel non-adjustable expansion section 33, and then the molded surface of the ejection rocket channel non-adjustable expansion section 33 is generated in a mode of uniform area transition.
In the process of converting the turbine mode into the rocket mode, the turbine channel splitter plate 24 and the rotating profile 39 of the turbine channel rectangular-shaped adjustable expansion section rotate simultaneously, the position indication 49 of the turbine channel splitter plate in the process of converting the mode and the position indication 47 of the rotating plate of the turbine channel rectangular-shaped adjustable expansion section in the process of converting the mode are both shown in fig. 5, and a gap 48 formed by the turbine channel splitter plate and the rotating profile of the turbine channel rectangular-shaped adjustable expansion section in the process of converting the mode can appear because the rotating profile 39 of the turbine channel rectangular-shaped adjustable expansion section cannot stretch; in the process of converting the rocket mode to the stamping mode, the ejector rocket channel splitter plate 18 and the rotating profile 29 of the ejector rocket channel rectangular adjustable expansion section rotate simultaneously, the position indication 44 of the ejector rocket channel splitter plate in the mode conversion process and the position indication 46 of the ejector rocket channel rectangular adjustable expansion section rotating plate in the mode conversion process are shown in fig. 5, and a gap 45 formed by the turbine channel splitter plate and the rotating profile of the turbine channel adjustable expansion section can appear in the mode conversion process because the rotating profile 29 of the ejector rocket channel rectangular adjustable expansion section cannot stretch.
Specific examples are given below.
Referring to the design method of the three-dimensional inner-turning four-channel hypersonic combined air inlet, in the embodiment, a design mach number Ma is 5 as an incoming flow mach number, an initial wedge angle is 7 degrees, and an inner contraction ratio is 6, and a combined power inner-turning four-channel air inlet with a working range of Ma being 0-6 (wherein the operating mach number of a turbine mode is 0-2, the operating mach number of an ejector rocket mode is Ma 2-4, and the operating mach number of a stamping mode is Ma 4-6) as shown in fig. 7 is designed, and the air inlet is composed of a high-speed stamping channel 19, an ejector rocket channel 51 and two low-speed turbine channels 54. Through CFD numerical simulation calculation, the air inlet channel can realize three-dimensional shock wave patch and full flow capture under the condition that the Mach number is designed as an incoming flow condition, and has high performance.
Claims (1)
1. The design method of the three-dimensional inward turning four-channel hypersonic combined air inlet channel is characterized by comprising the following steps of:
1) designing a stamping channel with the working Mach number range of Ma being 4-6, wherein the specific method comprises the following steps:
1.1 designing a three-dimensional inner-rotation-like rectangular compression molded surface: the design of the stamping channel takes an ICFD flow field as a design basis, the design Mach number of the stamping channel is taken as an incoming flow condition, a wall molded line of an internally contracted basic flow field is obtained in the ICFD flow field according to the required incoming flow Mach number, throat Mach number and an initial wedge angle at the front end of a compression molded surface, and an effective part of a flow line of the basic flow field is selected according to the design requirement; then solving an axisymmetric internally contracted basic flow field by using a characteristic line method to obtain an incident shock wave of an internally waverider-derived air inlet and a reflected shock wave of the axisymmetric internally contracted basic flow field, wherein the intersection point of the incident shock wave and the rotation center line of the basic flow field is designed as the lip of the air inlet, the intersection point of the incident shock wave and the effective part of the flow line of the basic flow field is designed as the position of the front edge point of the air inlet, and the intersection point of the reflected shock wave and the effective part of the flow line of the basic flow field is the effective terminal point of; then according to the design of a shoulder of the three-dimensional inner-rotation-like rectangular compression molded surface, a streamline traced out by using a reverse streamline tracing method in the obtained basic flow field is dispersed into a point set through an effective part of the basic streamline to form the three-dimensional inner-rotation-like rectangular compression molded surface with the inlet and outlet sections being similar to rectangles;
1.2 stamping a channel isolation section: designing the stamping through isolation section as an expansion profile, designing the stamping channel isolation section according to the expansion ratio of the stamping channel isolation section and the requirement of an oval outlet of the stamping channel isolation section, and generating a profile by adopting uniform area transition between the shoulder of the three-dimensional inner-rotation-type rectangular compression profile and the oval outlet of the stamping channel isolation section;
2) the design is drawn and is penetrated rocket passageway flow distribution plate and turbine passageway flow distribution plate, and the air current that gets into and draw and penetrate rocket passageway and turbine passageway rotates through the flow distribution plate and adjusts, and the overall arrangement that will combine to draw rocket passageway, turbine passageway when designing the flow distribution plate designs, and concrete method divide into:
2.1 designing a splitter plate of an injection rocket channel and a splitter plate of a turbine channel: the rocket ejector channel and the turbine channel do not share the same splitter plate, the rocket ejector channel splitter plate is arranged on the upper wall surface of the three-dimensional inner-rotation type rectangular compression profile, and the two turbine channel splitter plates are arranged on the left side and the right side of the three-dimensional inner-rotation type rectangular compression profile; the compression ratio of the vertical cross-sectional area where the molded line at the tail end of the diversion plate of the ejection rocket channel and the shoulder area of the compression profile of the three-dimensional inward-turning air inlet channel is controlled to be below 1.1, the tail end of the diversion plate of the ejection rocket channel is selected according to design requirements, the rotation angle of the diversion plate of the ejection rocket channel is ensured not to be too large according to the preset area of an outlet of the diversion section of the ejection rocket channel, the diversion plate extends forwards from the rotated tail end to intersect with the three-dimensional inward-turning rectangular compression profile, and the intersection line is designed to be the rotation shaft of the diversion plate of the ejection rocket channel; the rotating shaft of the turbine channel splitter plate and the rotating shaft of the ejector rocket channel splitter plate are controlled to be on the same section, and the tail end of the turbine channel splitter plate is determined according to the preset outlet area of the turbine channel splitter section and the requirement that the rotating angle of the turbine channel splitter plate is not too large;
2.2 designing the rotating angle of the splitter plate of the ejector rocket channel and the rotating angle of the splitter plate of the turbine channel: the rotation angle depends on the length of the diversion plate of the ejection rocket channel, the tail end of the turbine channel and the inlet area requirements of the expansion section of the ejection rocket channel and the expansion section of the turbine channel, and is controlled not to exceed 10 degrees in order to reduce the influence of expansion, and the rotation angle of the diversion plate of the ejection rocket channel and the rotation angle of the diversion plate of the turbine channel are determined according to the rotation shaft of the diversion plate of the ejection rocket channel and the rotation shaft of the diversion plate of the turbine channel designed in the step (1);
2.3 design the rotating mode of the splitter plate: the rotation of the ejector rocket channel splitter plate and the turbine channel splitter plate in the mode conversion process can affect the passing airflow and generate a local expansion phenomenon, and in order to reduce the influence, the incoming flow can stably flow into the turbine channel, the ejector rocket channel and the stamping channel, and the splitter plate is adjusted by selecting a uniform rotation mode;
3) designing a turbine channel expansion section with a working Mach number range of Ma being 0-2, wherein the specific method comprises the following steps:
3.1 design turbine channel type rectangular adjustable expansion section: the rotating molded surface of the turbine channel quasi-rectangular adjustable expansion section can be adjusted in rotation in the mode conversion, so that the adjustment synchronization of the turbine channel quasi-rectangular adjustable expansion section and the adjustment of the turbine channel splitter plate is controlled, and the sealing performance in the mode conversion process is improved; the rotating molded surface of the turbine channel quasi-rectangular adjustable expansion section rotates in the mode conversion process, and the expansion section is designed to be quasi-rectangular; determining the length of the adjustable expansion section of the turbine channel and a rotating shaft of the rotating profile of the rectangular-like adjustable expansion section of the turbine channel by combining the outlet section of the flow dividing section of the turbine channel according to the designed expansion ratio of the expansion section and the rotating angle within 15 degrees; generating the rest molded surfaces of the turbine channel quasi-rectangular adjustable expansion section between the outlet of the turbine channel quasi-rectangular adjustable expansion section and the outlet of the turbine channel flow dividing section in a form of uniform and excessive area according to the determined shape of the outlet of the turbine channel quasi-rectangular adjustable expansion section;
3.2 design turbine channel non-adjustable expansion section: the outlet of the turbine channel quasi-rectangular adjustable expansion section is quasi-rectangular, the cross section of the outlet of the turbine channel is circular, and a cubic curve is used for ensuring smooth transition of the molded surface of the turbine channel non-adjustable expansion section; generating a cubic curve connecting the inlet and the outlet of the non-adjustable expansion section of the turbine channel by using the slope of the end point arranged by the two ends of the slope tangent to the outlet of the rectangular adjustable expansion section of the turbine channel and the outlet of the turbine channel, and then generating the molded surface of the non-adjustable expansion section of the turbine channel in a form of uniform area transition;
4) designing an ejection rocket channel expansion section with the working Mach number range of Ma being 2-4, wherein the specific method comprises the following steps:
4.1 designing an ejection rocket channel type rectangular adjustable expansion section: the rotating profile of the rectangular adjustable expansion section of the ejection rocket channel is adjustable in rotation in mode conversion, so that the adjustment synchronization of the rotating profile and the ejection rocket channel splitter plate is controlled, and the sealing property in the mode conversion process is improved; the rotating molded surface of the rectangular-like adjustable expansion section of the rocket ejecting channel rotates in the mode conversion process, and the expansion section is designed into a rectangular-like shape; determining the length of the adjustable expansion section of the rocket ejector channel and a rotating shaft of a rotating profile of the rectangular adjustable expansion section of the rocket ejector channel by combining the section of an outlet of the diversion section of the rocket ejector channel according to the designed expansion ratio of the expansion section and the rotating angle within 20 degrees; generating other molded surfaces of the ejection rocket channel type rectangular adjustable expansion section between the form of uniform and transitional area and the exit of the ejection rocket channel diversion section according to the determined exit shape of the ejection rocket channel type rectangular adjustable expansion section;
4.2 designing an unadjustable expansion section of the rocket channel for injection: the section of an outlet of the rectangular adjustable expansion section of the ejector rocket channel is rectangular-like, the section of the outlet of the ejector rocket channel is circular, in order to ensure smooth transition of the section of the non-adjustable expansion section of the ejector rocket channel, a cubic curve is used, the slope of the end point is arranged at the position, at which the two ends of the cubic curve are tangent to the section of the outlet of the rectangular adjustable expansion section of the ejector rocket channel and the section of the outlet of the ejector rocket channel, so that the cubic curve connecting the inlet and the outlet of the non-adjustable expansion section of the ejector rocket channel is generated, and then the section of the non-adjustable expansion section of the ejector rocket channel is generated in a mode of uniform.
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