CN104632411A - Internal waverider-derived turbine base combined dynamic gas inlet adopting binary variable-geometry manner - Google Patents
Internal waverider-derived turbine base combined dynamic gas inlet adopting binary variable-geometry manner Download PDFInfo
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Abstract
The invention discloses an internal waverider-derived turbine base combined dynamic gas inlet adopting a binary variable-geometry manner. The internal waverider-derived turbine base combined dynamic gas inlet structurally comprises a gas inlet internal waverider compression section 1, a throat section 2, an expansion and distribution section 3, a punching channel 4, a turbine channel 5, a fixed-geometry three-dimensional internal waverider compression representing section 6, an adjustable internal waverider compression representing section 7, an adjustable internal waverider compression section representing variable-geometry compression surface 8, an adjustable expansion representing section 9, a sharp point-free distribution representing section 10, a machine body proximity representing movable upper arm 11, a movable upper arm driving representing servo action cylinder 12, a distribution representing plate 13, an internal waverider-derived fixed-geometry representing profile 14 and a distribution representing cross section 15. The internal waverider-derived turbine base combined dynamic gas inlet has the advantages of small outer resistance, high flow coefficient, good airflow quality and the like; meanwhile, profile deformation and distribution plate deflection caused by compression in a three-dimensional internal waverider manner can be controlled by only two regulating parameters, the deformation is convenient and reliable, and the requirement on an acting servo device is relatively easily met.
Description
Technical field
In the one that the present invention relates to, rider type turbine base assembly power (Turbine Based Combined Cycles, TBCC) intake duct and binary curved surface become geometric design method, belong to supersonic inlet technical field.
Background technique
Along with the fast development of airbreather, hypersonic aircraft has become the main strategic developing direction of future aircraft, and its flight range is very broad, and flight Mach number is from subsonic velocity, transonic speed, ultrasound velocity expands to hypersonic always.Because dissimilar motor has respective advantage in different flight range, therefore many countries once conducted a research in the world, different motors is attempted to integrate in respective advantage section, form combination circulation propulsion system, enable aircraft performance in whole operating range reach optimum.Current research is more RBCC(rocket based combined cycle) and TBCC(turbine base combination circulation) two kinds.TBCC can take into account at a high speed and air-inlet type thrust power that low-speed operations needs, have flight envelope broadness, specific thrust large, than leaping high, launch and landing place is flexible, can Horizontal Take-off and Landing, reusable, cost is low, reliability and durability advantages of higher.All have great application prospect in cruise missile, high-altitude high speed bomber and reconnaissance plane, sky and space plane etc., TBCC assembly power receives attention and the concern of scholars in the industry day by day.
According to the layout type of TBCC motor, tandem and parallel two classes can be divided into.Tandem TBCC turbogenerator and pressed engine adopt front/rear arranging structure, and its intake duct and jet pipe reality are all single-flow-path designs, advantage compact structure, but need to do more transformation to motor itself.And parallel TBCC turbogenerator and pressed engine adopt up/down arranging structure, need the technical innovation of motor own less, the engine technology used is all comparatively ripe, but needs the intake duct and the jet pipe that adopt dual flow path, and technical difficulty is embodied in air inlet system and exhaust system aspect.
TBCC is as the quite high novel airbreathing propulsion system of a kind of complexity, and the intake duct technology matched with it also wants complicated more than general Supersonic Inlet.TBCC assembly power, no matter be use turbogenerator operation mode or use pressed engine mode, its gas handling system works at the higher speeds mostly, therefore larger than the gas handling system under conventional speeds on advancing the impact of usefulness.As Mach number be increased to 4.5 from 1.8 time, the ratio that the energy of flow and engine fuel add energy that comes of intake duct conversion is increased to 0.7 from 0.1.Thus the applicability improved under the aeroperformance of intake duct and different flight state is defined as one of key technology developing TBCC motor in the world.
Existing most of parallel TBCC intake duct adopts conventional dualistic formula intake duct, and dualistic formula intake duct is under design (cruising) Mach number, inlet characteristic parameter (flow coefficient, pressure ratio, exit Mach number, temperature rise ratio, stagnation pressure recovery factor etc.) is comparatively general.In recent years, in three-dimensional, telescopic type intake duct received much concern in recent years as a kind of supersonic inlet with unique advantage, and current advanced high-speed aircraft/power scheme all starts to adopt three-dimensional adduction indentation air flue.Foreign scholar has carried out this type of intake duct and has studied widely, has developed telescopic type intake duct in multiple three-dimensional, such as: the REST intake duct, Jaws intake duct etc. of Busemann intake duct, NASA Langley.At home, Huang Guoping, the Liang Dewang of Nanjing Aero-Space University, especially prolong telescopic type intake duct in novel three-dimensional that tomahawk equals to propose first for 2004 inner wave rider type air inlet channel taking in a class called after, this intake duct intake duct has design point substantially without overflow, three-dimensional compressed capability is strong, compression efficiency advantages of higher.
Make a general survey of above all kinds intake duct, although they all have design advantage and the feature of some uniquenesses, still there is some design deficiency and performance deficiency.For typical REST intake duct, due to its only realize be smooth transition in profile but not pneumatic on smooth transition, cause it under design point, still can not realize full flow and catch, flow coefficient only has 95%.And in hypersonic propulsion system, the flow loss of 5% the is corresponding thrust loss of at least 5%.Although with direct streamlined impeller for inner wave rider type air inlet channel taking in technical characterstic confirm can 100% traffic capture, existing interior inner wave rider type air inlet channel taking mainly at a high speed determining geometric format, cannot meet the work range of Mach numbers of broadness.In order to realize the application of interior inner wave rider type air inlet channel taking on TBCC assembly power, needing badly and carrying out the research of interior rider intake duct about variable geometry formula.
Summary of the invention
What the present invention proposed is that a kind of interior rider type turbine base assembly power intake duct of binary change geometric ways and binary curved surface thereof of adopting becomes geometric design method, under its object is intended to maximum functional Mach number, venturi height is minimum, now intake duct has the feature of interior inner wave rider type air inlet channel taking, the i.e. three-dimensional incident shock sealing of oral area, substantially without overflow, there is flow coefficient high, the advantages such as resistance is little.Adopt rider intake duct in osculating axisymmetry stream Theoretical Design, the Field Characteristics in each osculating face and basic flow field are consistent.When departing from design maximum Mach number, along with the reduction of Mach number, incident shock angle increases, intake duct is by V-type overflow window automatic overflow, by regulating main compressing surface, again reasonably arranging the inner wave system of intake duct and amplifying venturi, increasing the negotiability of venturi.Along with Mach number reduces further, venturi is amplified to maximum position, increases venturi through-current capability further.
Technical solution of the present invention: a kind of interior rider formula turbine base assembly power intake duct realizing the compression of interior rider, its structure comprises rider compressing section (1) in 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, comprises
1. when the highest flight Mach number, in intake duct, the profile of rider compressing section (1) keeps the three-dimensional compression curved surface of interior rider compression, air-flow is compressed flow to venturi section (2) after, continue to slow down, for pressed engine provides required air-flow by the expansion shunting section (3) and punching press passage (4) that deflect into single-pass punching press pattern;
2., when lower flight Mach number, deflect into less compression position by the adjustable interior rider compressing section (7) in rider compressing section (1) in intake duct and carry out air-flow compression, and amplify venturi section (2) to adapt to low mach incoming flow;
3. the expansion shunting section (3) after venturi, by according to the needs of power system at transition Mach number M
tRwhen being 2 ~ 3, to flow slowing down and shunting, and when flight Mach number is less than transition Mach number, by air flow deflector to turbine channel (5) for turbogenerator provides the air-flow of deceleration supercharging.
Advantage of the present invention: when the highest flight Mach number, in intake duct, the profile of rider compressing section keeps the three-dimensional compression curved surface of interior rider compression, air-flow is compressed flow to venturi section after, continue to slow down, for pressed engine provides required air-flow by the expansion shunting section and punching press passage that deflect into single-pass punching press pattern; When lower flight Mach number, deflect into less compression position by the adjustable interior rider compressing section in rider compressing section in intake duct and carry out air-flow compression, and amplify venturi section to adapt to low mach incoming flow; Expansion shunting section after venturi, by according to the needs of power system when transition Mach number, to flow slowing down and shunting, and when flight Mach number is less than transition Mach number, by air flow deflector to turbine channel for turbogenerator provides the air-flow of deceleration supercharging.Intake duct of the present invention has the advantages such as extrernal resistance is little, flow coefficient is high, flow quality is good, and it only just can control the distortion of adjustable compression profile and the deflection of flow distribution plate with two regulating parameter, is out of shape reliably easy, more easily realizes the requirement of start servomechanism installation.
Accompanying drawing explanation
Accompanying drawing 1 is the TBCC intake duct three-dimensional change geometrized structure graph based on interior rider concept.
Accompanying drawing 2 is that the TBCC intake duct of interior rider formula compression becomes geometrical construction schematic diagram.
Accompanying drawing 3 is ICFC basic flow field schematic diagram.
Accompanying drawing 4 is that in direct streamlined impeller, inner wave rider type air inlet channel taking imports and exports schematic shapes.
Accompanying drawing 5 be improve direct streamlined impeller in inner wave rider type air inlet channel taking import and export schematic shapes.
Accompanying drawing 6 is hinge structure schematic diagram that adjustable interior rider compressing section 7 and adjustable extending section 11 adopt.
In figure 1 is the compressing section of the change geometry intake duct represented based on interior rider concept, 2 is represent venturi section, 3 is represent expansion shunting section, 4 is represent punching press passage, 5 is represent turbine channel, 6 is represent to determine rider compressing section in geometry three-dimensional, 7 is represent adjustable interior rider compressing section, 8 is the change Geometric compression faces representing adjustable interior rider compressing section, 9 is represent adjustable extending section, 10 is indicate without wedge angle shunting section, 11 is represent the movable upper wall by body side, 12 be represent drive movable upper wall be servo action cylinder, 13 is represent flow distribution plate, 14 is represent that interior rider formula determines geometry profile, 15 is represent a point flow section, 16 is represent hypersonic incoming flow, 17 is represent in ICFC flow field to shrink back in ICFA axisymmetric to turn wall, 18 is represent in ICFC flow field to shrink back in Busemann axisymmetric to turn wall, 19 is represent ICFA incident straight shock wave, 20 is represent Busemann incident shock, 21 is represent ICFC flow field reflected shock wave, 22 is represent basic flow field gyration center line, 23 is the rectangular inlet profiles representing interior inner wave rider type air inlet channel taking, 24 is represent that streamlined impeller obtains exporting rectangular profile, 25 is represent basic flow field gyration center, 26 is represent point discrete in import, 27 is represent each osculating face, 28 is represent original incident circular arc shock wave, 29 is flow field central points of the interior inner wave rider type air inlet channel taking of the direct streamlined impeller representing improvement, 30 is represent import profile line, 31 is represent outlet profile line, 32 is represent desirable profile of shock wave, and 33 what represent is the binary compression member of middle splicing, 34 represent be the length of binary compression member in entrance width direction.
Embodiment
Realize an interior rider formula turbine base assembly power intake duct for interior rider compression, its structure comprises rider compressing section 1 in 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, comprising:
1. when the highest flight Mach number, in intake duct, the profile of rider compressing section 1 keeps the three-dimensional compression curved surface of interior rider compression, air-flow is compressed flow to venturi section 2 after, continue to slow down, for pressed engine provides required air-flow by the expansion shunting section 3 and punching press passage 4 that deflect into single-pass punching press pattern;
2. when lower flight Mach number, deflect into less compression position by the adjustable interior rider compressing section 7 in rider compressing section 1 in intake duct and carry out air-flow compression, and amplify venturi section 2 to adapt to low mach incoming flow;
3. the expansion shunting section 3 after venturi, by according to the needs of power system at transition Mach number (M
tRbe generally 2 ~ 3) time, to flow slowing down and shunting, and when flight Mach number is less than transition Mach number, by air flow deflector to turbine channel 5 for turbogenerator provides the air-flow of deceleration supercharging.Intake duct of the present invention has the advantages such as extrernal resistance is little, flow coefficient is high, flow quality is good; And it only just can control the distortion of adjustable compression profile and the deflection of flow distribution plate with two regulating parameter, is out of shape reliably easy, more easily realizes the requirement of start servomechanism installation.
In described intake duct, rider compressing section 1 forms by determining rider compressing section 6 and adjustable interior rider compressing section 7 in geometry three-dimensional, its design is with the highest flight Mach 2 ship reference design state, the profile of intake duct compressing section is obtained, to inherit interior rider intake duct advantage, to realize compressing high efficiency air flow rate and reducing outflow resistance in this case by rider Design of Inlet technology in the outer pressure ratio three-dimensional of height; At flight Mach number M<M
tRtime, the one piece of binary curved surface be partitioned in the middle part of curved surface is compressed by rider in the three-dimensional of reference design state, the change geometry it being designed to adjustable interior rider compressing section 7 regulates compressing surface 8, regulate the shrinkage degree of this adjustable interior rider compressing section when different flight Mach number, obtain wide range of Mach numbers ability to work.
Described venturi section 2 is by the movable upper wall 11 by body side, by fixing lower wall and the two side formation of lip, and movable upper wall energy moves along a slide guide to upper right or lower-left, what drive movable upper wall is a servo action cylinder 12, and it is also the driving source of rider compressing section 1 and expansion shunting section 3 deformation adjustment in intake duct; When pressurized strut drives the movable upper wall of venturi section to move to certain position, front and its regulate compressing surface 8 position and rear and its to become geometry by hinged expansion shunting section by hinged change geometry to regulate wall position all to be determined; In addition, select to apply driving force at venturi section upper wall surface, be conducive to the aerodynamic loading more effectively supporting each adjustable wall, thus be easy to the size of servo drive, weight and the power consumption that reduce to realize becoming geometry.
Described expansion shunting section 3,1. by adjustable extending section 9 with form without wedge angle shunting section 10, the air-flow slightly larger than velocity of sound of the compression of rider compressing section, the rectification of venturi section in intake duct in upstream, will be decelerated to subcritical flow by terminal shock wave again by the first speed a little of adjustable extending section 9 and be supplied to shunting section 10 after further deceleration in expanding channel; 2. without wedge angle shunting section at a high speed (M>M
tR) time, drive the flow distribution plate 13 rotated around hinge to deflect into upper extreme position by an independent actuator, 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<M
tR) 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 pattern
tR), flow distribution plate 13 deflects between upper and lower two limit positions, realizes throughput gradually in the distribution of two passages and adjustment change.
Described interior rider compressing section 1, 1. rider Design of Inlet technology in high outer pressure ratio three-dimensional is adopted to obtain in the interior rider compressing section 1 compressing surface moulding of reference design state (the highest flight Mach number), namely the characteristic line of the isentropic Compression ripple after incident shock is made to converge in the after a while position of incident shock near center of compression end by adjustment basic flow field molded line, to guarantee that this moulding has as far as possible large low mach automatic overflow ability, thus reduce the length of adjustable interior rider compressing section 7, reduce the load to becoming geometry servo drive, and the previous section of this profile except adjustable interior rider compressing section is as determining rider compressing section 6 in geometry three-dimensional, 2. interior rider compressing section employs a kind of new departure in the configuration of transverse compression mode: the three-dimensional profile that the import and export obtained based on direct streamlined impeller are square, and by profile, centrally symmetrical one to cut open be two, in indirect one section of rectangle compressed board 8, the new approaches that the method proposes, namely the splicing in three-dimensional interior contractive set field and binary flow field, can make the flow field structure of compressing section end more easily become geometry designs with binary and mate, in addition, from air angle, rectangle compressed board not only increase intake duct Aspect Ratio, be conducive to low mach automatic overflow ability.
Described adjustable interior rider compressing section 7,1. determine geometry profile 14 by interior rider formula and become geometry to regulate compressing surface 8 to form, and the change geometry of binary configuration regulates compressing surface 8 to be with the upside compressing surface of rider compressing surface in reference design state into prototype, before lip, a position that can ensure that low mach air-flow passes through is selected to regulate the section start of compressing surface 8 as becoming geometry and A hinge is set; Becoming geometry regulates the joint of compressing surface 8 downstream end and venturi section to arrange another C hinge, B hinge is set between A hinge and C hinge, whole change geometry regulates the controlling mechanism degrees of freedom of compressing surface 8 to be 1, only moves C hinge along slide controlling distortion by venturi length of tape; 2. become the isentropic Compression curved surface to fovea superior that geometry adjustment 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 downwards gradually; 3. when flight Mach number reduces, venturi length of tape is moved C hinge and is slided to upper right along guide rail, then BC segment type face also to upper right move and AB segment type towards upper rotation, be both exaggerated throat area like this, also make be out of shape after adjustment compressing surface 8 still can keep airflow smooth.
The deformable upper wall surface of described adjustable extending section 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, sliding extension plate EF is connected to by hinge E, sliding extension plate EF except with DE by except chain connection, the other end can slide in the chute of turbine channel upper wall surface; The aisle spare expansion DESIGNED FEATURE of adjustable extending section 11 ensures, at a point flow section 15, gasflow mach number is down to 0.3 ~ 0.6 in addition; For slowing down the flowed energy loss that the inflection of turbine pattern stream causes, can the center line of adjustable extending section 11 be designed deflect slightly toward upper right.
Described without wedge angle shunting section, 1. in shunting section 10 for reducing flowed energy loss, this section of channel cross-section is designed to replace wedge angle with fillet; The leading edge two jiaos of the flow distribution plate 13 2. in shunting section is trimmed to the ellipse mated with filleted section passage, is to coordinate filleted section upwards below limit position deflects.
Described adjustable interior rider compressing section 7, adjustable extending section 11, the hinge structure feature that it adopts is: hinge centres O is not positioned in its each section of pneumatic profile connected, but above profile with profile distance R place, and one section of circular arc end face had around the enough arc length of hinge centres O in hinged two sections of plates; When needs two sections of plates 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, thus guarantees that gas flow smooth is smooth and easy.
Technological scheme of the present invention is further described below in conjunction with accompanying drawing:
ICFC basic flow field as shown in Figure 3, determines the design parameter of ICFC basic flow field, obtains initial ICFC flow field according to designing requirement design.Then geometry is adopted to regulate the more excellent ICFC flow field of improving and obtaining performance.Choose Aspect Ratio of import rectangle as shown in Figure 4, obtain the basic profile of the intake duct profile under maximum functional Mach number as change geometry designs by direct streamlined impeller technology and osculating stream theory, basic type face as shown in Figure 5.The basic profile obtained being cutd open along symmetry plane one is two, in indirect one section of binary compression member, import/export Aspect Ratio can be adjusted comparatively flexibly, main for basic profile compressing surface is blocked and is divided into two, a part is as determining Geometric compression face, and another part is as adjustable compressing surface, and adjustable compressed board and the connection determined between geometry and venturi level board all have employed arcuate segment transition, when can reduce to become geometry, the discontinuous impact on performance of profile local.According to the hinge design technology shown in the change geometrical construction shown in accompanying drawing 2 and Fig. 6, and then obtain the TBCC intake duct of the interior rider formula compression shown in accompanying drawing 1, thus the geometric 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 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.Intake duct profile in adopting during 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 interior angle of throat are 10 °.Intake duct profile design requires: air intake port is the regular rectangular shape of length to height ratio 1.6, and the flow field central point of intake duct is arranged in the following center of rectangular inlet.Basic profile based on M4 devises simply adjustable change geometrical solution.Accompanying drawing 1 provides the schematic three dimensional views of whole interior parallel TBCC intake duct.When maximum functional Mach number 4.0, mouth is pasted in intake duct oral area Three-Dimensional Shock Wave face, and substantially without overflow, flow coefficient is up to 0.988, and exit Mach number 0.38, total pressure recovery 0.38, exports average pressure ratio 42.1.
In addition, the present invention is also applicable to tandem TBCC intake duct.In addition, the outlet shapes of punching press passage does not specify.Above-described embodiment is for explanation of the invention, and can not as limitation of the present invention.Therefore every mode of execution identical with mentality of designing of the present invention is all in protection scope of the present invention.
Claims (9)
1. adopt binary to become an interior rider type turbine base assembly power intake duct for geometric ways, it is characterized in that: comprise rider compressing section (1) in 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, comprises
1. when the highest flight Mach number, in intake duct, the profile of rider compressing section (1) keeps the three-dimensional compression curved surface of interior rider compression, air-flow is compressed flow to venturi section (2) after, continue to slow down, for pressed engine provides required air-flow by the expansion shunting section (3) and punching press passage (4) that deflect into single-pass punching press pattern;
2., when lower flight Mach number, deflect into less compression position by the adjustable interior rider compressing section (7) in rider compressing section (1) in intake duct and carry out air-flow compression, and amplify venturi section (2) to adapt to low mach incoming flow;
3. the expansion shunting section (3) after venturi, by according to the needs of power system at transition Mach number M
tRwhen being 2 ~ 3, to flow slowing down and shunting, and when flight Mach number is less than transition Mach number, by air flow deflector to turbine channel (5) for turbogenerator provides the air-flow of deceleration supercharging.
2. a kind of interior rider type turbine base assembly power intake duct adopting binary to become geometric ways according to claim 1, it is characterized in that: in described intake duct, rider compressing section (1) forms by determining rider compressing section (6) and adjustable interior rider compressing section (7) in geometry three-dimensional, its design is with the highest flight Mach 2 ship reference design state, the profile of intake duct compressing section is obtained, to inherit interior rider intake duct advantage, to realize compressing high efficiency air flow rate and reducing outflow resistance in this case by rider Design of Inlet technology in the outer pressure ratio three-dimensional of height; At flight Mach number M<M
tRtime, the one piece of binary curved surface be partitioned in the middle part of curved surface is compressed by rider in the three-dimensional of reference design state, the change geometry it being designed to adjustable interior rider compressing section (7) regulates compressing surface (8), regulate the shrinkage degree of this adjustable interior rider compressing section when different flight Mach number, obtain wide range of Mach numbers ability to work.
3. a kind of interior rider type turbine base assembly power intake duct adopting binary to become geometric ways according to claim 1, it is characterized in that: described venturi section (2) is by the movable upper wall (11) by body side, by fixing lower wall and the two side formation of lip, and movable upper wall energy moves along a slide guide to upper right or lower-left, what drive movable upper wall is a servo action cylinder (12), and it is also the driving source of rider compressing section (1) and expansion shunting section (3) deformation adjustment in intake duct; When pressurized strut drives the movable upper wall of venturi section to move to certain position, front and its regulate compressing surface (8) position and rear and its to become geometry by hinged expansion shunting section by hinged change geometry to regulate wall position all to be determined; In addition, select to apply driving force at venturi section upper wall surface, be conducive to the aerodynamic loading more effectively supporting each adjustable wall.
4. a kind of interior rider type turbine base assembly power intake duct adopting binary to become geometric ways according to claim 1, it is characterized in that described expansion shunting section (3), its design method is:
1. form by adjustable extending section (9) with without wedge angle shunting section (10), the air-flow slightly larger than velocity of sound of the compression of rider compressing section, the rectification of venturi section in intake duct in upstream, will be decelerated to subcritical flow by terminal shock wave again by the first speed a little of adjustable extending section (9) and be supplied to shunting section (10) after further deceleration in expanding channel;
2. without wedge angle shunting section at high speed M>M
tRtime, drive the flow distribution plate (13) rotated around hinge to deflect into upper extreme position by an independent actuator, 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<M
tRtime, 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 pattern
tR, flow distribution plate (13) deflects between upper and lower two limit positions, realizes throughput gradually in the distribution of two passages and adjustment change.
5. a kind of binary that adopts according to claim 2 becomes the interior rider type turbine base assembly power intake duct of geometric ways, and it is characterized in that described interior rider compressing section (1), its design method is:
1. in reference design state, interior rider compressing section (1) the compressing surface moulding of the highest flight Mach number adopts rider Design of Inlet technology in high outer pressure ratio three-dimensional to obtain, namely the characteristic line of the isentropic Compression ripple after incident shock is made to converge in the after a while position of incident shock near center of compression end by adjustment basic flow field molded line, to guarantee that this moulding has as far as possible large low mach automatic overflow ability, thus reduce the length of adjustable interior rider compressing section (7), reduce the load to becoming geometry servo drive, and the previous section of this profile except adjustable interior rider compressing section is as determining rider compressing section (6) in geometry three-dimensional,
2. interior rider compressing section using method in the configuration of transverse compression mode is: the three-dimensional profile that the import and export obtained based on direct streamlined impeller are square, and by profile, centrally symmetrical one to cut open be two, in indirect one section of rectangle compressed board (8); This method propose the splicing in three-dimensional interior contractive set field and binary flow field, the flow field structure of compressing section end can be made more easily to become geometry designs with binary and mate; In addition, from air angle, rectangle compressed board not only increase intake duct Aspect Ratio, be conducive to low mach automatic overflow ability.
6. a kind of interior rider type turbine base assembly power intake duct adopting binary to become geometric ways according to claim 2, is characterized in that described adjustable interior rider compressing section (7):
1. determine geometry profile (14) by interior rider formula and become geometry to regulate compressing surface (8) to form, and the change geometry of binary configuration regulates compressing surface (8) to be with the upside compressing surface of rider compressing surface in reference design state into prototype, before lip, a position that can ensure that low mach air-flow passes through is selected to regulate the section start of compressing surface (8) as becoming geometry and A hinge is set; Becoming geometry regulates the joint of compressing surface (8) downstream end and venturi section to arrange another C hinge, B hinge is set between A hinge and C hinge, whole change geometry regulates the controlling mechanism degrees of freedom of compressing surface (8) to be 1, only moves C hinge along slide controlling distortion by venturi length of tape;
2. become the isentropic Compression curved surface to fovea superior that geometry adjustment 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 downwards gradually;
3. when flight Mach number reduces, venturi length of tape is moved C hinge and is slided to upper right along guide rail, then BC segment type face also to upper right move and AB segment type towards upper rotation, be both exaggerated throat area like this, also make be out of shape after adjustment compressing surface (8) still can keep airflow smooth.
7. a kind of interior rider type turbine base assembly power intake duct adopting binary to become geometric ways according to claim 3, it is characterized in that the deformable upper wall surface of described adjustable extending section (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, sliding extension plate EF is connected to by hinge E, sliding extension plate EF except with DE by except chain connection, the other end can slide in the chute of turbine channel upper wall surface; The aisle spare expansion DESIGNED FEATURE of adjustable extending section (11) ensures, at a point flow section (15), gasflow mach number is down to 0.3 ~ 0.6 in addition; For slowing down the flowed energy loss that the inflection of turbine pattern stream causes, can the center line of adjustable extending section (11) be designed deflect slightly toward upper right.
8. a kind of interior rider type turbine base assembly power intake duct adopting binary to become geometric ways according to claim 4, it is characterized in that described without wedge angle shunting section: 1. in shunting section (10) for reducing flowed energy loss, this section of channel cross-section is designed to replace wedge angle with fillet; The leading edge two jiaos of the flow distribution plate (13) 2. in shunting section is trimmed to the ellipse mated with filleted section passage, is to coordinate filleted section upwards below limit position deflects.
9. a kind of binary that adopts according to claim 6 or 7 becomes rider type turbine base assembly power intake duct in geometric ways, it is characterized in that described adjustable interior rider compressing section (7), adjustable extending section (11), the hinge structure feature that it adopts is: hinge centres O is not positioned in its each section of pneumatic profile connected, but above profile with profile distance R place, and one section of circular arc end face had around the enough arc length of hinge centres O in hinged two sections of plates; When needs two sections of plates 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, thus guarantees that gas flow smooth is smooth and easy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510042709.2A CN104632411B (en) | 2015-01-28 | 2015-01-28 | Binary is used to become the interior rider type turbine base assembly power air intake duct of geometric ways |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510042709.2A CN104632411B (en) | 2015-01-28 | 2015-01-28 | Binary is used to become the interior rider type turbine base assembly power air intake duct of geometric ways |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104632411A true CN104632411A (en) | 2015-05-20 |
| CN104632411B CN104632411B (en) | 2016-08-24 |
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| CN105156212A (en) * | 2015-10-09 | 2015-12-16 | 西北工业大学 | Variable geometry side pressure type air inlet passage of rocket-based-combined-cycle (RBCC) engine |
| CN105971733A (en) * | 2016-06-30 | 2016-09-28 | 西北工业大学 | Two-dimensional supersonic inlet of enclosed variable structure |
| CN106285946A (en) * | 2016-08-01 | 2017-01-04 | 南京航空航天大学 | The passage of double-axle rotation deformation becomes geometry air intake duct without rider formula in wedge angle |
| CN106650173A (en) * | 2017-01-12 | 2017-05-10 | 西南科技大学 | Design method for internal rotation air inlet basic flow field with controllable outlet section flow field parameters |
| CN106837549A (en) * | 2017-02-06 | 2017-06-13 | 厦门大学 | The method for designing of interior parallel hypersonic binary channels air intake duct |
| CN106837550A (en) * | 2017-02-06 | 2017-06-13 | 厦门大学 | The method for designing of hypersonic triple channel air intake duct |
| CN107089340A (en) * | 2017-06-05 | 2017-08-25 | 南京航空航天大学 | The lower chin formula integrated with precursor be super/hypersonic inlet and design method |
| CN107191273A (en) * | 2017-06-15 | 2017-09-22 | 南京航空航天大学 | The continuously adjustabe air intake duct and control method of a kind of rigid/flexible combination regulation |
| CN107605601A (en) * | 2017-09-29 | 2018-01-19 | 南京航空航天大学 | A kind of Supersonic Inlet for capturing area and being adjusted in synchronism with throat area |
| CN108194224A (en) * | 2017-12-31 | 2018-06-22 | 厦门大学 | It is embedded to the TBCC parallel connection jet pipe regulating mechanism design methods of diaphragm internal |
| CN109458272A (en) * | 2018-11-20 | 2019-03-12 | 四川航天中天动力装备有限责任公司 | A kind of combination in series power mode regulating device |
| CN109488484A (en) * | 2018-12-21 | 2019-03-19 | 北京空天技术研究所 | Three-level is entered the orbit Reusable Launch Vehicles and its application method |
| CN110702415A (en) * | 2019-11-08 | 2020-01-17 | 北京动力机械研究所 | Testing device for verifying motion law of adjustable flow passage of air-breathing engine |
| CN111075570A (en) * | 2019-12-16 | 2020-04-28 | 北京动力机械研究所 | Geometric adjustable flow passage telescopic compensation and dynamic sealing structure |
| CN113153529A (en) * | 2021-04-21 | 2021-07-23 | 厦门大学 | Wide-speed-range air inlet channel design method based on double-incidence bending shock wave |
| CN113153531A (en) * | 2021-05-28 | 2021-07-23 | 西北工业大学 | Variable overflow groove adjusting mechanism, scramjet engine and hypersonic aircraft |
| CN113738511A (en) * | 2020-05-27 | 2021-12-03 | 厦门大学 | Splitter plate design method for improving modal transformation airtightness of TBCC (TBCC) air inlet channel |
| CN113945385A (en) * | 2021-09-21 | 2022-01-18 | 中国航空工业集团公司西安飞机设计研究所 | Model system for jet engine and air inlet channel ground rack combined test |
| RU2766238C1 (en) * | 2021-08-27 | 2022-02-10 | Федеральное Автономное Учреждение "Центральный институт авиационного моторостроения имени П.И. Баранова" | Variable geometry air intake for supersonic passenger aircraft |
| CN114412642A (en) * | 2022-01-17 | 2022-04-29 | 南京航空航天大学 | Combined power air inlet channel of single-variable control mode conversion device |
| CN117704077A (en) * | 2024-02-06 | 2024-03-15 | 中国空气动力研究与发展中心空天技术研究所 | Hard connection sealing position compensation structure |
| CN117823281A (en) * | 2024-03-06 | 2024-04-05 | 中国空气动力研究与发展中心空天技术研究所 | Multi-channel wide-speed-range adjustable air inlet channel in delta arrangement |
| CN117823281B (en) * | 2024-03-06 | 2024-06-04 | 中国空气动力研究与发展中心空天技术研究所 | Multi-channel wide-speed-range adjustable air inlet channel in delta arrangement |
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| CN105156212A (en) * | 2015-10-09 | 2015-12-16 | 西北工业大学 | Variable geometry side pressure type air inlet passage of rocket-based-combined-cycle (RBCC) engine |
| CN105971733B (en) * | 2016-06-30 | 2017-10-31 | 西北工业大学 | A kind of closed structure changes Two Dimensional Supersonic air intake duct |
| CN105971733A (en) * | 2016-06-30 | 2016-09-28 | 西北工业大学 | Two-dimensional supersonic inlet of enclosed variable structure |
| CN106285946A (en) * | 2016-08-01 | 2017-01-04 | 南京航空航天大学 | The passage of double-axle rotation deformation becomes geometry air intake duct without rider formula in wedge angle |
| CN106650173A (en) * | 2017-01-12 | 2017-05-10 | 西南科技大学 | Design method for internal rotation air inlet basic flow field with controllable outlet section flow field parameters |
| CN106650173B (en) * | 2017-01-12 | 2020-03-17 | 西南科技大学 | Design method for basic flow field of internal rotation type air inlet channel with controllable outlet section flow field parameters |
| CN106837549A (en) * | 2017-02-06 | 2017-06-13 | 厦门大学 | The method for designing of interior parallel hypersonic binary channels air intake duct |
| CN106837550B (en) * | 2017-02-06 | 2018-10-09 | 厦门大学 | The design method of hypersonic triple channel air intake duct |
| CN106837550A (en) * | 2017-02-06 | 2017-06-13 | 厦门大学 | The method for designing of hypersonic triple channel air intake duct |
| CN107089340A (en) * | 2017-06-05 | 2017-08-25 | 南京航空航天大学 | The lower chin formula integrated with precursor be super/hypersonic inlet and design method |
| CN107089340B (en) * | 2017-06-05 | 2018-07-27 | 南京航空航天大学 | With the integrated lower chin formula supersonic speed of precursor or hypersonic inlet and design method |
| CN107191273A (en) * | 2017-06-15 | 2017-09-22 | 南京航空航天大学 | The continuously adjustabe air intake duct and control method of a kind of rigid/flexible combination regulation |
| CN107191273B (en) * | 2017-06-15 | 2018-12-14 | 南京航空航天大学 | A kind of continuously adjustable air intake duct and control method of rigid/flexible combination adjusting |
| CN107605601A (en) * | 2017-09-29 | 2018-01-19 | 南京航空航天大学 | A kind of Supersonic Inlet for capturing area and being adjusted in synchronism with throat area |
| US11542867B2 (en) | 2017-09-29 | 2023-01-03 | Nanjing University Of Aeronautics And Astronautics | Supersonic air intake passage capable of achieving synchronous adjustment of capturing area and throat area |
| CN107605601B (en) * | 2017-09-29 | 2018-08-31 | 南京航空航天大学 | A kind of Supersonic Inlet and its control method and design method of capture area and throat area synchronous adjustment |
| CN108194224A (en) * | 2017-12-31 | 2018-06-22 | 厦门大学 | It is embedded to the TBCC parallel connection jet pipe regulating mechanism design methods of diaphragm internal |
| CN108194224B (en) * | 2017-12-31 | 2019-08-27 | 厦门大学 | It is embedded to the TBCC parallel connection jet pipe regulating mechanism design method of diaphragm internal |
| CN109458272A (en) * | 2018-11-20 | 2019-03-12 | 四川航天中天动力装备有限责任公司 | A kind of combination in series power mode regulating device |
| CN109488484A (en) * | 2018-12-21 | 2019-03-19 | 北京空天技术研究所 | Three-level is entered the orbit Reusable Launch Vehicles and its application method |
| CN110702415A (en) * | 2019-11-08 | 2020-01-17 | 北京动力机械研究所 | Testing device for verifying motion law of adjustable flow passage of air-breathing engine |
| CN110702415B (en) * | 2019-11-08 | 2021-04-06 | 北京动力机械研究所 | Testing device for verifying motion law of adjustable flow passage of air-breathing engine |
| CN111075570A (en) * | 2019-12-16 | 2020-04-28 | 北京动力机械研究所 | Geometric adjustable flow passage telescopic compensation and dynamic sealing structure |
| CN113738511A (en) * | 2020-05-27 | 2021-12-03 | 厦门大学 | Splitter plate design method for improving modal transformation airtightness of TBCC (TBCC) air inlet channel |
| CN113738511B (en) * | 2020-05-27 | 2024-05-14 | 厦门大学 | Splitter plate design method for improving TBCC air inlet channel mode conversion air tightness |
| CN113153529A (en) * | 2021-04-21 | 2021-07-23 | 厦门大学 | Wide-speed-range air inlet channel design method based on double-incidence bending shock wave |
| CN113153531A (en) * | 2021-05-28 | 2021-07-23 | 西北工业大学 | Variable overflow groove adjusting mechanism, scramjet engine and hypersonic aircraft |
| CN113153531B (en) * | 2021-05-28 | 2022-09-27 | 西北工业大学 | Variable overflow groove adjusting mechanism, scramjet engine and hypersonic aircraft |
| RU2766238C1 (en) * | 2021-08-27 | 2022-02-10 | Федеральное Автономное Учреждение "Центральный институт авиационного моторостроения имени П.И. Баранова" | Variable geometry air intake for supersonic passenger aircraft |
| CN113945385A (en) * | 2021-09-21 | 2022-01-18 | 中国航空工业集团公司西安飞机设计研究所 | Model system for jet engine and air inlet channel ground rack combined test |
| CN113945385B (en) * | 2021-09-21 | 2024-04-09 | 中国航空工业集团公司西安飞机设计研究所 | Model system for jet engine and air inlet channel ground bench combined test |
| CN114412642B (en) * | 2022-01-17 | 2023-03-17 | 南京航空航天大学 | Combined power air inlet channel of single-variable control mode state conversion device |
| CN114412642A (en) * | 2022-01-17 | 2022-04-29 | 南京航空航天大学 | Combined power air inlet channel of single-variable control mode conversion device |
| CN117704077A (en) * | 2024-02-06 | 2024-03-15 | 中国空气动力研究与发展中心空天技术研究所 | Hard connection sealing position compensation structure |
| CN117704077B (en) * | 2024-02-06 | 2024-04-12 | 中国空气动力研究与发展中心空天技术研究所 | Hard connection sealing position compensation structure |
| CN117823281A (en) * | 2024-03-06 | 2024-04-05 | 中国空气动力研究与发展中心空天技术研究所 | Multi-channel wide-speed-range adjustable air inlet channel in delta arrangement |
| CN117823281B (en) * | 2024-03-06 | 2024-06-04 | 中国空气动力研究与发展中心空天技术研究所 | Multi-channel wide-speed-range adjustable air inlet channel in delta arrangement |
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