CN104632411B - Binary is used to become the interior rider type turbine base assembly power air intake duct of geometric ways - Google Patents
Binary is used to become the interior rider type turbine base assembly power air intake duct of geometric ways Download PDFInfo
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Abstract
The present invention is a kind of interior rider type turbine base assembly power air intake duct using binary to become geometric ways, its structure is: include rider compression section 1 in air intake duct, venturi section 2, expansion shunting section 3, punching press passage 4, turbine channel 5, represent and determine rider compression section 6 in geometry three-dimensional, represent adjustable interior rider compression section 7, represent the change Geometric compression face 8 of adjustable interior rider compression section, represent adjustable expansion segment 9, 1 indicates without wedge angle shunting section 10, represent the movable upper wall 11 by body side, represent the movable upper wall of driving is servo action cylinder 12, represent flow distribution plate 13, in representing, rider formula determines geometry profile 14, represent shunting cross section 15.Air intake duct of the present invention has the advantages such as extrernal resistance is little, discharge coefficient is high, flow quality is good, and its profile deformation and flow distribution plate that only just can control to compress in rider mode in three-dimensional by two regulation parameters deflects, deformation is easy to be reliable, and the requirement to start servomechanism installation is easier to realize.
Description
Technical field
A kind of interior rider type turbine base assembly power (the Turbine Based Combined that the present invention relates to
Cycles, TBCC) air intake duct and binary curved surface become geometric design method, belongs to supersonic inlet technical field.
Background technology
Along with the fast development of airbreather, hypersonic aircraft has become the main strategic developing direction of future aircraft, and its flight range is the broadest, flight Mach number from subsonic speed, transonic speed, supersonic speed extend down to hypersonic.Owing to different types of engine has respective advantage in different flight range, the most many countries once conducted a research, attempt to integrate different engines in respective advantage section, form combination circulation propulsion system, enable aircraft performance in whole working range to reach optimum.At present research is more RBCC(rocket based combined cycle) and the combination of TBCC(turbine base circulate) two kinds.TBCC is to take into account at a high speed and air suction type thrust power that low-speed operations needs, have that flight envelope is broad, specific thrust is big, than leaping high, launch and landing place flexibly, can Horizontal Take-off and Landing, reusable, low cost, reliability and durability advantages of higher.All having great application prospect at cruise missile, high-altitude high speed bomber and the aspect such as reconnaissance plane, sky and space plane, TBCC assembly power is increasingly subject to attention and the concern of scholars in the industry.
According to the layout type of TBCC engine, series and parallel two class can be divided into.Tandem TBCC turbogenerator and punching engine use front/rear arrangement architecture, and its air intake duct and jet pipe reality are all single-flow-path designs, advantage compact conformation, but need engine itself is done more transformation.And parallel TBCC turbogenerator and punching engine use up/down arrangement architecture, need technological transformation own to engine less, the engine technology used is the most ripe, however it is necessary that air intake duct and the jet pipe using dual flow path, and technical difficulty is more is embodied in air inlet system and exhaust system aspect.
TBCC is as the at a relatively high novel airbreathing propulsion system of a kind of complexity, and the air intake duct technology matched therewith also wants complexity more than general Supersonic Inlet.TBCC assembly power, either uses turbogenerator operation mode or uses punching engine mode, and its gas handling system works at the higher speeds mostly, and therefore the impact on advancing usefulness is bigger than the gas handling system under conventional speeds.As Mach number from 1.8 increase to 4.5 time, the come energy of flow and the engine fuel of air intake duct conversion add the ratio of energy and increase to 0.7 from 0.1.Thus the applicability improved under the aeroperformance of air intake duct and different flight state is defined as one of key technology developing TBCC engine in the world.
Existing most of parallel TBCC air intake ducts use conventional dualistic formula air intake duct, and dualistic formula air intake duct is under design (cruise) Mach number, inlet characteristic parameter (discharge coefficient, pressure ratio, exit Mach number, temperature rise ratio, stagnation pressure recovery factor etc.) is the most general.In recent years, three-dimensional contract formula air intake duct receives much concern in recent years as a kind of supersonic inlet with unique advantage, and current advanced high-speed aircraft/power scheme all begins with three-dimensional contract air intake duct.This type of air intake duct has all been carried out and has been studied widely by foreign scholar, has developed multiple three-dimensional contract formula air intake duct, such as: Busemann air intake duct, the REST air intake duct of NASA Langley, Jaws air intake duct etc..At home, the Huang Guoping of Nanjing Aero-Space University, Liang Dewang, especially prolong tomahawk equal within 2004, proposing the novel three-dimensional contract formula air intake duct of a named interior inner wave rider type air inlet channel taking of class first, this air intake duct air intake duct has design point substantially without overflow, three-dimensional compressed capability is strong, compression efficiency advantages of higher.
Make a general survey of any of the above type air intake duct, although they all have design advantage and the feature of some uniquenesses, but yet suffer from some design defect and performance deficiency.As a example by typical REST air intake duct, due to its be only accomplished that in profile smoothly transit rather than be pneumatic on smoothly transit, cause its still can not realize under design point full flow capture, discharge coefficient only has 95%.And in hypersonic propulsion system, the flow loss of 5% the is corresponding thrust loss of at least 5%.Although interior inner wave rider type air inlet channel taking with direct streamlined impeller as technical characterstic confirm can with the traffic capture of 100%, but existing interior inner wave rider type air inlet channel taking is primarily directed to determine geometric format at a high speed, it is impossible to meet the work range of Mach numbers of broadness.In order to realize the application on TBCC assembly power of the interior inner wave rider type air inlet channel taking, need the research carrying out interior rider air intake duct about variable geometry formula badly.
Summary of the invention
What the present invention proposed is a kind of interior rider type turbine base assembly power air intake duct using binary to become geometric ways and binary curved surface change geometric design method thereof, its purpose is intended under maximum functional Mach number, venturi height is minimum, now air intake duct has the feature of interior inner wave rider type air inlet channel taking, i.e. oral area three-dimensional incident shock sealing, substantially without overflow, there is discharge coefficient high, the advantages such as resistance is little.Use rider air intake duct in osculating axisymmetry stream Theoretical Design so that the Field Characteristics in each osculating face keeps consistent with basic flow field.When deviateing design maximum Mach number, along with the reduction of Mach number, incident shock angle increases, and air intake duct passes through V-type overflow window automatic overflow, by regulating main compressing surface, the most reasonably arranges the internal wave system of air intake duct and amplifies venturi, increasing the negotiability of venturi.Along with Mach number reduces further, venturi is amplified to maximum position, increases venturi through-current capability further.
The technical solution of the present invention: a kind of interior rider formula turbine base assembly power air intake duct realizing the compression of interior rider, its structure includes rider compression section (1) in air intake duct, venturi section (2), expansion shunting section (3), punching press passage (4) and turbine channel (5)；
The binary curved surface of its internal flow channel becomes geometric design method, including
1. when the highest flight Mach number, the three-dimensional compression curved surface of rider compression in the profile of rider compression section (1) keeps in air intake duct, air-flow is compressed flow to venturi section (2) after, continue to slow down by the expansion shunting section (3) and punching press passage (4) deflecting into single-pass punching press pattern, provide required air-flow for punching engine；
2. when relatively low flight Mach number, the adjustable interior rider compression section (7) in rider compression section (1) in air intake duct deflect into less compression position and carry out air-flow compression, and amplify venturi section (2) and flow adapting to low mach；
3. the expansion shunting section (3) after venturi, by the needs according to dynamical system at transition Mach number MTRWhen being 2 ~ 3, to flow slowing down and shunting, and when flight Mach number is less than transition Mach number, air flow deflector to turbine channel (5) is provided for turbogenerator the air-flow of deceleration supercharging.
Advantages of the present invention: when the highest flight Mach number, the three-dimensional compression curved surface of rider compression in the profile of rider compression section keeps in air intake duct, air-flow is compressed flow to venturi section after, continue to slow down by the expansion shunting section and punching press passage deflecting into single-pass punching press pattern, provide required air-flow for punching engine；When relatively low flight Mach number, the adjustable interior rider compression section in rider compression section in air intake duct deflect into less compression position and carry out air-flow compression, and amplify venturi section and flow to adapt to low mach；Expansion shunting section after venturi, by the needs according to dynamical system when transition Mach number, to flow slowing down and shunting, and when flight Mach number is less than transition Mach number, provides the air-flow of deceleration supercharging by air flow deflector to turbine channel for turbogenerator.Air intake duct of the present invention has the advantages such as extrernal resistance is little, discharge coefficient is high, flow quality is good, and it only just can control the deformation of adjustable compression profile and the deflection of flow distribution plate by two regulation parameters, and deformation is easy to be reliable, and the requirement to start servomechanism installation is easier to realize.
Accompanying drawing explanation
Accompanying drawing 1 is that TBCC air intake duct three-dimensional based on interior rider concept becomes geometrized structure graph.
Accompanying drawing 2 is that the TBCC air intake duct of interior rider formula compression becomes geometry schematic diagram.
Accompanying drawing 3 is ICFC basic flow field schematic diagram.
Accompanying drawing 4 is inner wave rider type air inlet channel taking import and export schematic shapes in direct streamlined impeller.
Accompanying drawing 5 is inner wave rider type air inlet channel taking import and export schematic shapes in the direct streamlined impeller improved.
The hinge arrangement schematic diagram that accompanying drawing 6 is adjustable interior rider compression section 7 and adjustable expansion segment 11 is used.
nullIn figure 1 is to represent the compression section becoming geometry air intake duct based on interior rider concept、2 is to represent venturi section、3 is to represent expansion shunting section、4 is to represent punching press passage、5 is to represent turbine channel、6 is to represent to determine rider compression section in geometry three-dimensional、7 is to represent adjustable interior rider compression section、8 is the change Geometric compression face representing adjustable interior rider compression section、9 is to represent adjustable expansion segment、10 is to indicate without wedge angle shunting section、11 is to represent the movable upper wall by body side、12 be represent drive movable upper wall be servo action cylinder、13 is to represent flow distribution plate、14 is to represent that interior rider formula determines geometry profile、15 is to represent shunting cross section、16 is to represent hypersonic to flow、17 is to represent ICFA axial symmetry contract revolution wall in ICFC flow field、18 is to represent Busemann axial symmetry contract revolution wall in ICFC flow field、19 is to represent ICFA incident straight shock wave、20 is to represent Busemann incident shock、21 is to represent ICFC flow field reflected shock wave、22 is to represent basic flow field centre of gyration line、23 is the rectangular inlet profile representing interior inner wave rider type air inlet channel taking、24 is to represent that streamlined impeller obtains exporting rectangular profile、25 is to represent the basic flow field centre of gyration、26 is to represent point discrete in import、27 is to represent each osculating face、28 is to represent original incident circular arc shock wave、29 is the flow field central point of the interior inner wave rider type air inlet channel taking of the direct streamlined impeller representing improvement、30 is to represent import outline line、31 is to represent outlet outline line、32 is to represent preferable profile of shock wave，33 expressions are the middle binary compression sections spliced、34 expressions are the binary compression section length in entrance width direction.
Detailed description of the invention
A kind of interior rider formula turbine base assembly power air intake duct realizing the compression of interior rider, its structure includes rider compression section 1 in air intake duct, venturi section 2, expansion shunting section 3, punching press passage 4 and turbine channel 5；
Its binary curved surface becomes geometric design method, including:
1. when the highest flight Mach number, the three-dimensional compression curved surface of rider compression in the profile of rider compression section 1 keeps in air intake duct, air-flow is compressed flow to venturi section 2 after, continue to slow down by deflecting into the expansion shunting section 3 of single-pass punching press pattern and punching press passage 4, provide required air-flow for punching engine；
2. when relatively low flight Mach number, the adjustable interior rider compression section 7 in rider compression section 1 in air intake duct deflect into less compression position and carry out air-flow compression, and amplify venturi section 2 and flow to adapt to low mach；
3. the expansion shunting section 3 after venturi, by the needs according to dynamical system at transition Mach number (MTRGenerally 2 ~ 3) time, to flow slowing down and shunting, and when flight Mach number is less than transition Mach number, air flow deflector to turbine channel 5 is provided for turbogenerator the air-flow of deceleration supercharging.Air intake duct of the present invention has the advantages such as extrernal resistance is little, discharge coefficient is high, flow quality is good；And it only just can control the deformation of adjustable compression profile and the deflection of flow distribution plate by two regulation parameters, deformation is easy to be reliable, and the requirement to start servomechanism installation is easier to realize.
In described air intake duct, rider compression section 1 is formed by determining rider compression section 6 and adjustable interior rider compression section 7 in geometry three-dimensional, its design is with the highest flight Mach 2 ship reference design state, the profile of air intake duct compression section is obtained in this case, to inherit interior rider air intake duct advantage, to realize high efficiency air flow rate being compressed and reducing outflow resistance by rider Design of Inlet technology in the outer pressure ratio three-dimensional of height；At flight Mach number M < MTRTime, by the one piece of binary curved surface being partitioned in the middle part of the three-dimensional interior rider compression curved surface of reference design state, it is designed as the change geometry regulation compressing surface 8 of adjustable interior rider compression section 7, the shrinkage degree of this adjustable interior rider compression section is regulated, it is thus achieved that wide range of Mach numbers ability to work when different flight Mach number.
Described venturi section 2 is by the movable upper wall 11 by body side, fixing lower wall and two side by lip are constituted, and the most above wall energy moves along a rail plate to upper right or lower-left, drive movable upper wall is a servo action cylinder 12, and it is also rider compression section 1 and the driving source of expansion shunting section 3 deformation adjustment in air intake duct；When the movable upper wall that pressurized strut drives venturi section moves to certain position, front is become geometry regulation wall position with it by hinged expansion shunting section by hinged change geometry regulation compressing surface 8 position and rear with it and is all determined；Additionally, select to apply driving force at venturi section upper wall surface, be conducive to more effectively supporting the aerodynamic loading of each adjustable wall, thus be prone to reduce the size of servo drive, weight and the power consumption realizing becoming geometry.
Described expansion shunting section 3,1. by adjustable expansion segment 9 and form without wedge angle shunting section 10, in upstream in air intake duct the compression of rider compression section, the air-flow slightly larger than velocity of sound of venturi section rectification, will by adjustable expansion segment 9 first the most a little speed be decelerated to subcritical flow by terminal shock wave again and be supplied to shunting section 10 after deceleration further in expanding channel；2. without wedge angle shunting section at (M > M at a high speedTR) time, an independent acting device drive the flow distribution plate 13 rotated around hinge to deflect into upper extreme position, flow into and all flow to punching press passage by the air-flow of shunting section 10；3. without wedge angle shunting section at low speed (M < MTR) time, flow distribution plate 13 turns to lower limit position around hinge, and the air-flow flowing into shunting section 10 all flows to turbine channel；4. without wedge angle shunting section (M=M under power transition patternTR), flow distribution plate 13 deflects between upper and lower two limit positions, gradually realizes throughput in the distribution of two passages and regulation change.
Described interior rider compression section 1, 1. in the interior rider compression section 1 compressing surface moulding in reference design state (the highest flight Mach number) uses high outer pressure ratio three-dimensional, rider Design of Inlet technology obtains, the characteristic curve of the isentropic Compression ripple after i.e. making incident shock by adjustment basic flow field molded line converges in the incident shock position after a while near center of compression end, to guarantee that this moulding has the biggest low mach automatic overflow ability, thus reduce the length of adjustable interior rider compression section 7, reduce the load becoming geometry servo drive, and the previous section that this profile is in addition to adjustable interior rider compression section is as determining rider compression section 6 in geometry three-dimensional；Interior rider compression section employs a kind of new departure in terms of transverse compression mode configuration: importing and exporting square three-dimensional profile based on what direct streamlined impeller obtained, profile being cutd open along Central Symmetry one is two, in indirect one section of rectangle compression plate 8；The new approaches that the method proposes, i.e. three-dimensional contract flow field and the splicing in binary flow field, it is possible to make the flow field structure of compression section end be more easy to become geometry designs with binary and mate；Additionally, from air angle, rectangle compression plate not only increases the ratio of width to height of air intake duct, is conducive to low mach automatic overflow ability.
Described adjustable interior rider compression section 7,1. determined geometry profile 14 by interior rider formula and change geometry regulation compressing surface 8 forms, and binary configuration become geometry regulation compressing surface 8 be the upside compressing surface of rider compressing surface in reference design state as prototype, select one can ensure before lip position that low mach air-flow passes through is as becoming the section start of geometry regulation compressing surface 8 and arranging A hinge；The junction becoming geometry regulation compressing surface 8 downstream end and venturi section arranges another C hinge, B hinge is set between A hinge and C hinge, the governor motion free degree of whole change geometry regulation compressing surface 8 is 1, is only driven C hinge to control deformation along slide by venturi section；2. become the concave up isentropic Compression curved surface that geometry regulation compressing surface 8 is interior rider formula between A hinge and B hinge, be the shoulder fairing profile of interior rider formula compressing surface between B hinge and C hinge, protrude gradually downward；3. when flight Mach number reduces, venturi section drives C hinge to slide along guide rail to upper right, then BC segment type face is also moved to upper right and AB segment type face is rotated up, and has the most both been exaggerated throat area, also makes the regulation compressing surface 8 after deformation remain to keep airflow smooth.
The deformable upper wall surface of described adjustable expansion segment 11 is made up of rotor plate DE and sliding extension plate EF, wherein: rotor plate DE is connected to venturi section 2 by hinge D, it is connected to sliding extension plate EF by hinge E, sliding extension plate EF except with DE by chain connection in addition to, the other end can slide in the chute of turbine channel upper wall surface；The aisle spare expansion design feature of the most adjustable expansion segment 11 is to ensure that is down to 0.3 ~ 0.6 in shunting cross section 15 by gasflow mach number；For slowing down the flowed energy loss that turbine pattern stream inflection causes, the center line of adjustable expansion segment 11 can be designed to upper deflecting the most to the right.
Described shunting section without wedge angle, 1. for reducing flowed energy loss in shunting section 10, this section of channel cross-section is designed as replacing wedge angle with fillet；2. the leading edge of the flow distribution plate 13 in shunting section two jiaos is trimmed to the ellipse mated with filleted section passage, is being to coordinate filleted section to the deflection of upper and lower extreme position.
Described adjustable interior rider compression section 7, adjustable expansion segment 11, the hinge arrangement feature that it is used is: hinge centres O is not in its each section of pneumatic profile connected, but above profile with profile distance R at, and one section of circular arc end face having around the enough arc length of hinge centres O in hinged two sections of plates；When two sections of plates of needs relatively rotate around hinge, circular arc end face can make the profile of two sections of plates after turning to any position all keep continuously, not have sharp corner, so that it is guaranteed that gas flow smooth is smooth and easy.
Further describe technical scheme below in conjunction with the accompanying drawings:
According to design, ICFC basic flow field as shown in Figure 3, requires that design determines the design parameter of ICFC basic flow field, obtains initial ICFC flow field.Then geometry regulation is used to improve the more excellent ICFC flow field obtaining performance.Choosing the ratio of width to height of import rectangle as shown in Figure 4, obtain the basic profile as change geometry designs of the air intake duct profile under maximum functional Mach number by direct streamlined impeller technology and osculating stream theory, basis profile is as shown in Figure 5.The basic profile obtained being cutd open along the plane of symmetry one is two, in indirect one section of binary compression section, import/export the ratio of width to height can be adjusted the most flexibly, main for basis profile compressing surface is blocked and is divided into two, a part is as determining Geometric compression face, and another part all have employed segmental arc transition as adjustable compressing surface, adjustable compression plate and the connection determined between geometry and venturi level board, when can reduce change geometry, the discontinuous impact on performance of profile local.According to the hinge design technology shown in geometry and Fig. 6 that becomes shown in accompanying drawing 2, and then obtain the TBCC air intake duct that the interior rider formula shown in accompanying drawing 1 is compressed, thus the geometric air intake duct of change based on interior rider concept can be used to interior parallel TBCC assembly power.
Embodiment
Devise and be applicable to work range of Mach numbers 0-4, the geometric air intake duct of change of the interior parallel TBCC assembly power of transition Mach number 2.5.Due to maximum functional Mach number 4.0, have employed the combining form of sub-burning ramjet and turbogenerator.Use air intake duct profile during interior inner wave rider type air inlet channel taking method design maximum functional Mach number 4.0.The design parameter of the ICFC basic flow field therefore chosen: M1=4.0, M3=1.4, initial contract angle are 10 °.The design requirement of air intake duct shape is: air intake port is the regular rectangular shape of length to height ratio 1.6, and the flow field central point of air intake duct is arranged in the center that rectangular inlet is following.Basic profile based on M4 devises simple adjustable change geometrical solution.Accompanying drawing 1 provides the schematic three dimensional views of whole interior parallel TBCC air intake duct.When maximum functional Mach number 4.0, air intake duct oral area Three-Dimensional Shock Wave face patch mouth, substantially without overflow, discharge coefficient is up to 0.988, exit Mach number 0.38, and total pressure recovery 0.38 exports average pressure ratio 42.1.
It addition, the present invention may also apply to tandem TBCC air intake duct.Additionally, the outlet shapes of punching press passage is not specified by.Above-described embodiment is only intended to explanation of the invention, and cannot function as limitation of the present invention.The embodiment that the most every and mentality of designing of the present invention is identical is the most within the scope of the present invention.
Claims (9)
1. use binary to become an interior rider type turbine base assembly power air intake duct for geometric ways, it is characterized in that: include rider compression section (1) in air intake duct, venturi section (2), expansion shunting section (3), punching press passage (4) and turbine channel (5)；
The binary curved surface of its internal flow channel becomes geometric design method, including
1. when the highest flight Mach number, the three-dimensional compression curved surface of rider compression in the profile of rider compression section (1) keeps in air intake duct, air-flow is compressed flow to venturi section (2) after, continue to slow down by the expansion shunting section (3) and punching press passage (4) deflecting into single-pass punching press pattern, provide required air-flow for punching engine；
2. when relatively low flight Mach number, the adjustable interior rider compression section (7) in rider compression section (1) in air intake duct deflect into less compression position and carry out air-flow compression, and amplify venturi section (2) and flow adapting to low mach；
3. the expansion shunting section (3) after venturi, by the needs according to dynamical system at transition Mach number MTRWhen being 2 ~ 3, to flow slowing down and shunting, and when flight Mach number is less than transition Mach number, air flow deflector to turbine channel (5) is provided for turbogenerator the air-flow of deceleration supercharging.
A kind of interior rider type turbine base assembly power air intake duct using binary to become geometric ways the most according to claim 1, it is characterized in that: in described air intake duct, rider compression section (1) is formed by determining rider compression section (6) and adjustable interior rider compression section (7) in geometry three-dimensional, its design is with the highest flight Mach 2 ship reference design state, the profile of air intake duct compression section is obtained in this case, to inherit interior rider air intake duct advantage, to realize high efficiency air flow rate being compressed and reducing outflow resistance by rider Design of Inlet technology in the outer pressure ratio three-dimensional of height；At flight Mach number M < MTRTime, by the one piece of binary curved surface being partitioned in the middle part of the three-dimensional interior rider compression curved surface of reference design state, it is designed as change geometry regulation compressing surface (8) of adjustable interior rider compression section (7), the shrinkage degree of this adjustable interior rider compression section is regulated, it is thus achieved that wide range of Mach numbers ability to work when different flight Mach number.
A kind of interior rider type turbine base assembly power air intake duct using binary to become geometric ways the most according to claim 1, is characterized in that: described venturi section (2) is by by body sideMovable upper wall (11)Fixing lower wall and two side by lip are constituted, and the most above wall energy moves along a rail plate to upper right or lower-left, drive movable upper wall is a servo action cylinder (12), and it is also rider compression section (1) and the driving source of expansion shunting section (3) deformation adjustment in air intake duct；When the movable upper wall that pressurized strut drives venturi section moves to certain position, front is become geometry regulation wall position with it by hinged expansion shunting section by hinged change geometry regulation compressing surface (8) position and rear with it and is all determined；Additionally, select to apply driving force at venturi section upper wall surface, be conducive to more effectively supporting the aerodynamic loading of each adjustable wall.
A kind of interior rider type turbine base assembly power air intake duct using binary to become geometric ways the most according to claim 1, is characterized in that described expansion shunting section (3), and its method for designing is:
1. form by adjustable expansion segment (9) with without wedge angle shunting section (10), in upstream in air intake duct the compression of rider compression section, the air-flow slightly larger than velocity of sound of venturi section rectification, will by adjustable expansion segment (9) first the most a little speed be decelerated to subcritical flow by terminal shock wave again and be supplied to shunting section (10) after deceleration further in expanding channel；
2. without wedge angle shunting section in high speed M > MTRTime, an independent acting device drive the flow distribution plate (13) rotated around hinge to deflect into upper extreme position, flow into and all flow to punching press passage by the air-flow of shunting section (10)；
3. without wedge angle shunting section at low speed M < MTRTime, flow distribution plate (13) turns to lower limit position around hinge, and the air-flow flowing into shunting section (10) all flows to turbine channel；
4. without wedge angle shunting section M=M under power transition patternTR, flow distribution plate (13) deflects between upper and lower two limit positions, gradually realizes throughput in the distribution of two passages and regulation change.
A kind of interior rider type turbine base assembly power air intake duct using binary to become geometric ways the most according to claim 2, is characterized in that described interior rider compression section (1), and its method for designing is:
1. in reference design state, in interior rider compression section (1) the compressing surface moulding of the highest flight Mach number uses high outer pressure ratio three-dimensional, rider Design of Inlet technology obtains, the characteristic curve of the isentropic Compression ripple after i.e. making incident shock by adjustment basic flow field molded line converges in the incident shock position after a while near center of compression end, to guarantee that this moulding has the biggest low mach automatic overflow ability, thus reduce the length of adjustable interior rider compression section (7), reduce the load becoming geometry servo drive, and the previous section that this profile is in addition to adjustable interior rider compression section is as determining rider compression section (6) in geometry three-dimensional；
Interior rider compression section using method in terms of transverse compression mode configuration is: importing and exporting square three-dimensional profile based on what direct streamlined impeller obtained, profile being cutd open along Central Symmetry one is two, in indirect one section become geometry regulation compressing surface (8)；This method propose the splicing in three-dimensional contract flow field and binary flow field, it is possible to make the flow field structure of compression section end be more easy to become geometry designs with binary and mate；Additionally, from air angle, rectangle compression plate not only increases the ratio of width to height of air intake duct, is conducive to low mach automatic overflow ability.
A kind of interior rider type turbine base assembly power air intake duct using binary to become geometric ways the most according to claim 2, is characterized in that described adjustable interior rider compression section (7):
1. determined geometry profile (14) by interior rider formula and change geometry regulation compressing surface (8) forms, and change geometry regulation compressing surface (8) of binary configuration be the upside compressing surface of rider compressing surface in reference design state as prototype, select one can ensure before lip position that low mach air-flow passes through is as becoming the section start of geometry regulation compressing surface (8) and arranging A hinge；The junction becoming geometry regulation compressing surface (8) downstream end and venturi section arranges another C hinge, B hinge is set between A hinge and C hinge, the governor motion free degree of whole change geometry regulation compressing surface (8) is 1, is only driven C hinge to control deformation along slide by venturi section；
2. become the concave up isentropic Compression curved surface that geometry regulation compressing surface (8) is interior rider formula between A hinge and B hinge, be the shoulder fairing profile of interior rider formula compressing surface between B hinge and C hinge, protrude gradually downward；
3. when flight Mach number reduces, venturi section drives C hinge to slide along guide rail to upper right, then BC segment type face is also moved to upper right and AB segment type face is rotated up, and has the most both been exaggerated throat area, also makes the regulation compressing surface (8) after deformation remain to keep airflow smooth.
A kind of interior rider type turbine base assembly power air intake duct using binary to become geometric ways the most according to claim 4, it is characterized in that the deformable upper wall surface of described adjustable expansion segment (9) is made up of rotor plate DE and sliding extension plate EF, wherein: rotor plate DE is connected to venturi section (2) by hinge D, it is connected to sliding extension plate EF by hinge E, sliding extension plate EF except with DE by chain connection in addition to, the other end can slide in the chute of turbine channel upper wall surface；The aisle spare expansion design feature of the most adjustable expansion segment (9) is to ensure that is down to 0.3 ~ 0.6 in shunting cross section (15) by gasflow mach number；For slowing down the flowed energy loss that turbine pattern stream inflection causes, adjustable expansion segment (9) center line be designed to upper deflecting the most to the right.
A kind of interior rider type turbine base assembly power air intake duct using binary to become geometric ways the most according to claim 4, it is characterized in that described shunting section without wedge angle: 1. for reducing flowed energy loss in shunting section (10), this section of channel cross-section is designed as replacing wedge angle with fillet；2. the leading edge of the flow distribution plate in shunting section (13) two jiaos is trimmed to the ellipse mated with filleted section passage, is being to coordinate filleted section to the deflection of upper and lower extreme position.
9. according to a kind of interior rider type turbine base assembly power air intake duct using binary to become geometric ways described in claim 6 or 7, it is characterized in that described adjustable interior rider compression section (7), adjustable expansion segment (9), the hinge arrangement feature that it is used is: hinge centres O is not in its each section of pneumatic profile connected, but above profile with profile distance R at, and one section of circular arc end face having around the enough arc length of hinge centres O in hinged two sections of plates；When two sections of plates of needs relatively rotate around hinge, circular arc end face can make the profile of two sections of plates after turning to any position all keep continuously, not have sharp corner, so that it is guaranteed that gas flow smooth is smooth and easy.
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