CN101716995A - Waved wing and waved surface of object - Google Patents

Abstract

The invention relates to a waved wing belonging to a straight wing. The waved wing is different from the straight wing in that the front edge and the rear edge are in sinusoidal or triangular ruled convex-concave waves, look like saws and have great lifting force as the straight wing at a low speed and little wave resistance as a swept wing at a high speed. The waved surface of an object is a sinusoidal or triangular ruled convex-concave surface on the plane, the inclined plane, the cambered plane, the conical plane, and the like of the object; and fluid flowing by the surface has weak friction force without a boundary layer. The waved wing and the waved surface of the object are applied to aircrafts, missiles, air propellers, gas-turbine impellers, aquatic propellers, ships, submarines, torpedoes, and the like to remarkably improve the speeds and reduce the resistance thereof.

Description

The waved surface of Waved wing and object

The present invention relates to hydrodynamics, machinery, aerospace vehicle, navigation device and national defence for technical field.

The wing of the current aircraft of background technology has the classification such as the straight wing, swept-back wing, buzzard-type wing, dalta wing and tapered airfoil, relative to the straight wing, the characteristics of swept-back wing, dalta wing, tapered airfoil is leading edge of a wing sweepback, buzzard-type wing is leading edge of a wing sweepforward, can also be referred to as the wing of leading edge of a wing sweepforward or sweepback and plunder the wing；The low speed of the straight wing is good, but does not adapt at a high speed, and it is good to plunder wing high speed, but low-speed performance is poor；Though swing-wing can high low speed it is general, restricted that to state eliminated by present generation aircraft by its structure and weight.

The airborne vehicle flown in atmosphere, the propeller and impeller that rotate, the navigation device navigated by water in the water surface or water, the propeller rotated, its outer surface all has boundary layer；The presence and separation in boundary layer make airborne vehicle, propeller, impeller produce resistance and stall, make the problems such as navigation device produces resistance and hole.

The content of the invention will overcome straight wing not adapt at a high speed, plunder the problem of wing low-speed performance is poor, using not only adapting to low speed but also adapt at a high speed and the Novel aerofoil that is not limited by structure and weight is one of approach for solving the problems, such as, the boundary layer in-flight produced is eliminated simultaneously, the performance of airborne vehicle can be significantly improved, such a high low speed is general and wing configuration of boundless interlayer applies to propeller, impeller and navigation device and is equally remarkably improved its performance.

The present invention provides a kind of wing (see Fig. 1-a), it also belongs to the straight wing, difference with the straight wing is it on the basis of the straight wing, leading edge and trailing edge are in the wavy of sawtooth like, this " ripple " and the sine wave occurred on oscillograph, triangular wave is identical (see Fig. 1-b), nose of wing is crest to lordosis, trough is recessed backward, wing trailing edge is then that crest is recessed forward, trough is convex backward, the line on the summit of front and rear edge crest, the line of trough nadir is overlapped with wing chord, wing is blocked from the line between front and rear edge crest summit and obtains aerofoil profile, i.e. double airfoils (see Fig. 1-c), it can also be prismatic, the high speed aerofoil profile such as double prismatics.Here such a wing is referred to as Waved wing.

The upper and lower surface of Waved wing is also that wavy, the wavy form of expression has two kinds：It is a kind of be the exhibition that is linked to be in upper surface of the airfoil peak to straight line on have bar wave crest (see Fig. 1-d), wave height is parallel with wing chord and only less than the 1/8 of chord length, the line of the minimum point of trough is parallel with the line of upper surface of the airfoil peak, trough minimum point is overlapped with the vertical line of wing peak to wing chord again with the line of upper surface of the airfoil peak, the length of this coincidence line is the thickness of wave crest, this thickness is suitable with the boundary layer thickness of upper surface of the airfoil, it is gradually reduced and domatic smoothly connects with upper surface of the airfoil peak trailing edge formation initially towards the segment thickness of trailing edge from trough, this running surface is referred to as raised corrugated；Another corrugated is that have wavy depression in plane or cambered surface or inclined-plane (see Fig. 1-e, f, g, h, j, k), the summit of crest is overlapped with plane or cambered surface or inclined-plane, trough is then recessed into plane or cambered surface or inclined-plane, and this corrugated is referred to as the corrugated that is recessed；The ripple that corrugated is presented all is the equal sine wave or triangular wave of wave height, and convex corrugated and recessed corrugated are referred to as the waved surface of object.

The product that the waved surface of Waved wing and object is belonged to after the external shape of rule modification with ripple.

The good effect of Waved wing is that high low speed is general, the characteristics of existing straight wing low speed lift is big, wing critical Mach number is plunderred again high, break through the characteristics of resistance is small after sound barrier, and performance is than the straight wing and plunders that the wing is more superior, the complexity and weight of structure are suitable with the straight wing, and stability is good during transonic speed；The good effect of waved surface is to make airfoil outer surface without boundary-layer and significantly increase lift and reduce resistance.

Waved wing in atmosphere flight when, leading edge crest makes in front of the wing to slow down (see a in Fig. 2) on hypotenuse to vertical air-flow with the span with the hypotenuse that trough is formed, the principle of deceleration is identical with plunderring the wing, so as to improve critical Mach number, from plunderring air-flow unlike the wing on adjacent hypotenuse, towards trough component trough mutually converge and formed one it is parallel with wing chord, the sheet air-flow band vertical with aerofoil is (see Fig. 2-b, d), begin from trough, each one of wing upper and lower surface and positional symmetry, the similar wing fence of effect of gas band, but effect is more preferable than wing fence, the air-flow of wing upper and lower surface can be forced to flow to trailing edge from nose of wing, without flowing to wingtip and then greatly reducing induced drag；Because wing trailing edge is also waveform, the pressure drag produced by trailing edge tail produces the component of a deviation wing chord to greatly reduce pressure drag on the hypotenuse that trailing edge trough and crest are formed；(see Fig. 2-c, d) during the Waved wing generation angle of attack, due to the presence of leading edge trough, air-flow can supplement the air of wing upper surface through trough and suppress air-flow separation, when the angle of attack is maximum (see Fig. 2-e, f), air-flow can produce lift vortex without making wing stall on crest and the hypotenuse of trough formation, so the available angle of attack of Waved wing is up to more than 70 °；The straight wing is before velocity of sound is reached, because the raised acceleration to air-flow in upper surface makes that wing upper surface peak reaches velocity of sound in advance and producing shock wave increases resistance, in addition boundary-layer effect can also produce air-flow separation and then generation transonic speed is unstable, Waved wing has decelerating effect because of the raised corrugated in front of its upper surface peak summary to air-flow, the generation of wing upper surface peak shock wave is postponed, improving critical Mach number makes resistance reduce (see Fig. 2-g), and this drag reduction effect on raised corrugated is applied equally to transition position of the cone to cylinder (see Fig. 2-h)；The depression corrugated of wing is in low-speed wing flight, air-flow can do the curvilinear motion risen and fallen along the male and fomale(M＆F) of crest and trough formation (see Fig. 2-j), this allows for the path length for substantially exceeding lower surface air-flow from the path that leading edge flow to trailing edge in identical time inner wing upper surface air-flow, the upper and lower surface air velocity that upper and lower surface air velocity difference is noticeably greater than conventional aerofoil profile generation is poor, therefore the lift produced is also accordingly significantly increased than the conventional wing, because crest is very steep towards the slope of trough, air-flow is easy to occur air-flow separation when flowing to trough from crest, in addition the distance between crest is again nearer, slope from trough towards crest is also very steep, there is inhibition to air-flow, then air-flow separation just has the trend across depression, this causes the air pressure reduction in trough depression and then produces the suction towards trough to air-flow, air-flow from a crest flow through after it is recessed curved across next crest slightly to trough, but it is still low-pressure area in trough, this low-pressure area can produce the upward suction vertical with wing chord to trough and then show as profile lift, when airfoil flight speed further increases, air-flow is skimmed over (see Fig. 2-k) from each crest summit then straightly, the suction of high velocity air makes in trough depression close to vacuum, profile lift also further increases, the boundary-layer of wing upper surface also disappears therewith, to make the boundary-layer of wing lower surface disappear, wing lower surface is also wavy, but wave height is more much smaller than upper table face amount, the trough suction difference of upper and lower surface shows as powerful profile lift and without boundary-layer problem.Sufficiently large wing lift can make aircraft to be lifted off without producing the angle of attack, though the wing angle of attack can produce larger lift, but there is also aerodynamic drag simultaneously, the bigger aerodynamic drag of the angle of attack also there is also more greatly stall, aerodynamic drag and stall problem is then not present in wing lift, and aircraft can be made to be increased sharply speed and height with less thrust.

It its surface is lost boundary-layer (see Fig. 2-l, m, n) when the corrugated that is recessed applies to cone surface, damaged surface, curved surfaces, be substantially reduced frictional resistance.Because the high velocity air on depression corrugated only skims over the summit of crest, Waved wing speed reaches during thermal boundary that also only having crest summit is heated, and the heating degree of overall aerofoil is not serious, that is to say, that waveform sunk surface is improved the effect of thermal boundary and black barrier Mach number.Raised corrugated is to the low-pressure area in the decelerating effect of wing peak air-flow, the effect of depression corrugated elimination boundary-layer, corrugated trough to air-flow suction, the generation for making Waved wing postpone shock wave in transonic speed has no boundary-layer and separated with air-flow, and performance is stable when making Waved wing transonic speed.

Brief description of the drawings Fig. 1 is the configuration figure of the waved surface of Waved wing and object；Fig. 2 is the schematic diagram of the good effect of the waved surface of Waved wing and object；Fig. 3, Fig. 4 are that the waved surface of Waved wing and object applies to the embodiment of gas turbine；Fig. 5 is the embodiment that applies on turbofan jet engine and turboprop of waved surface of Waved wing and object；Fig. 6 is that the waved surface of Waved wing and object applies to reinforce the embodiment on turbofan/superpressure punching press/rocket composite rocket engine；Fig. 7-Figure 11 is the embodiment that applies on aerospace vehicle of waved surface of Waved wing and object；Figure 12 is the embodiment that applies on navigation device of waved surface of Waved wing and object.

The waved surface of embodiment Waved wing and object mainly applies to aerospace vehicle, navigation device, impeller, propeller (slurry) etc., and its use is different, and embodiment is also different, is further illustrated below in conjunction with accompanying drawing.

Ripple leaf gas turbine is the gas turbine that blade uses Waved wing configuration, as shown in Figure 3 and Figure 4.The front and rear edge of blade (Fig. 3-b, 1. with Fig. 4-g) is in wave shape, leaf basin and blade back surface are depression waved surfaces, compressor (Fig. 3-2.) casing inner surface, turbine surface at blade root, combustion chamber (Fig. 3-4.) inner surface, turbine surface is all depression corrugated at turbine (Fig. 3-9.) casing inner surface, turbine blade root, and the direction of ripple is consistent with airflow direction；There is bearing (Fig. 4-5.) at the hub disk center of compressor and turbine, wheel disc is fixed on arbor (Fig. 4-6.) by bearing, the two sides of wheel disc it is symmetrical radial pipeline (Fig. 4-2.), one end of pipeline at the vertical ring-type port of one mouth face arbor of Correspondent formation at wheel disc centre bearing (Fig. 4-4.), the other end is through the junction (Fig. 4-1.) of wheel disc and root of blade, the passage (figure being passed through in hollow blade

), passage in blade begins the blade root opposite side that turned back again to blade tip from blade root side, and the radiant tube with wheel disc two sides is communicated (see B-B, A-A in Fig. 4) respectively；Per have between two adjacent wheel discs one be fixed on it is on arbor, be in two-wheeled dish axle hold between annular bevel gear pedestal (Fig. 4-7.), the center of pedestal is the circular hole being placed on arbor, edge be 4-6 roots with pedestal diameter point-blank, vertical with edge surface bevel gear shaft (Fig. 4-

), it is that plane is parallel with pedestal diameter and pedestal thickness, dispersed arrangement equal sized multiple sheets every latticing (Fig. 4-9.) between pedestal margin and center hole, every latticing geometric center point on a circumference, space between latticing is the port of pedestal, the two ends of port connect with the ring-type port (Fig. 4-4.) at hub disk centre bearing respectively, and with Gask-O-Seal seal joint, bevel gear (Fig. 4-

) cone tooth be in the two ends of cylinder (4- is 10.), the big circumference diameter for boring tooth is equal with drum diameter, the small circumference diameter for boring tooth is equal with the two bearings internal diameter in cylinder, bevel gear shaft on pedestal penetrates in two bevel gear small circumference centre bores and cylinder the internal diameter of two bearings and bevel gear is fixed on pedestal, between two impeller disks, the cone tooth of ring-type bevel gear (Fig. 4-3.) wherein on the faster impeller disk of rotating speed and pedestal bevel gear (Fig. 4-10.) root is ratcheting, ring-type bevel gear (Fig. 4-8.) on the slower impeller disk of rotating speed and bevel gear at the top of pedestal bevel gear are ratcheting, the i.e. two adjacent impeller disks realize differential to turning by the Bevel Gear Transmission on pedestal therebetween, as bevel gear (Fig. 4-3. on two adjacent impeller disks, 8. when) diameter is equal, equal speed counter-rotating is then realized by bevel gear therebetween, as shown in Fig. 4-a；Every two row is referred to as one-level to the impeller turned, compressor and turbine are all to slow down step by step from front to back, as shown in Fig. 3-a, the impeller row of compressor is even number, turbine wheel row is odd number, and compressor impeller is that supersonic speed is rotated, and turbine wheel is that subsonic speed is rotated, prime counter rotating turbine (Fig. 3-7.), by be placed on tubular power transmission shaft on arbor, between turbine and compressor (Fig. 3-

) be driven to compressor, rear class counter rotating turbine (Fig. 3-8.) and most heel row impeller are free turbines, outside most heel row wheel disk of turbine on ring-type bore tooth (Fig. 3-

) and between the turbine rear stay plate bevel gear (Fig. 3-

) it is ratcheting, between fagging bevel gear again with penetrate arbor (Fig. 3-

) interior intracavitary power transmission shaft (Fig. 3-10.) on bevel gear (Fig. 3-

) ratcheting, power transmission shaft is in compressor front end (Fig. 3-10.) external power output；Part after the turbine of power transmission shaft (Fig. 3-10.) be sequentially arranged with steam turbine (Fig. 3-

), circulating pump (Fig. 3-

), condenser fan (Fig. 3-

), steam turbine import and turbine rear stay plate (Fig. 3-

) in cavity connect, fagging cavity is connected with the annular port (Fig. 4-4.) outside most heel row wheel disk of turbine at centre bearing again, connecting place has sealing gasket sealing, the outlet of steam turbine and condenser (Fig. 3-) import be connected, the outlet of condenser is connected with circulating pump；Circulation pump delivery line is divided into two-way, connect all the way with the heat exchanger in fuel gas exhaust pipe, the outlet of heat exchanger is connected to combustion chamber water jacket (Fig. 3-5.) by the pipeline that is distributed on gas turbine shell (Fig. 3-3.), fagging that another road is led at forcing press import (Fig. 3-

) in cavity, fagging cavity connects with the ring-type port (Fig. 4-4.) at compressor first row hub disk centre bearing again, and there is Gask-O-Seal sealing joint；Last row's hub disk of compressor communicated with combustion chamber water jacket towards the annular port at the wheel face centre bearing of combustion chamber (see Fig. 3-It is shown), combustion chamber (Fig. 3-4.) it is annular firing, shell of only having family is constituted, there is no the burner inner liner in conventional gas turbines combustion chamber, water jacket (Fig. 3-5.) outside the shell of room, close to arbor water jacket wall respectively have at compressor and at turbine a passage (Fig. 3-It is shown) the annular port that leads at its neighbouring hub disk centre bearing and to seal the guide vane in joint, combustion chamber inlet and outlet by Gask-O-Seal be all hollow, guide vane at import (Fig. 3-) inner chamber leads to the port of air compressor wheel disk center, the port at wheel disk of turbine center is led in exit guide vane (Fig. 3-6.) inner chamber；Whole gas turbine shows two passes, one be enter from compressor inlet, through compressor, combustion chamber, turbine, blast pipe gas channel, one be before compressor fagging inner chamber begin, through the compressor internal channel of pedestal port formation between gas compressor blade wheel face radiant tube and blade inner chamber and impeller, combustion chamber water jacket, turbine wheel card radiant tube and blade inner chamber (Fig. 4-) and impeller between turbine internal channel, turbine rear stay plate inner chamber, steam turbine, condenser, coolant recirculation pump, the heat exchanger in fuel gas exhaust pipe, the pipeline that is distributed on gas turbine shell of pedestal port formation be back to the coolant circulation passage of fagging inner chamber and combustion chamber water jacket before compressor.J is compressor blade section in Fig. 4, and k is turbo blade section, and l is compressor impeller, and m is turbine wheel.

When ripple leaf combustion turbine is started, gas compressor blade wheel speed is gradually increased to supersonic speed, finally it is operated in the maximum safe speed of rotation that impeller material and structure can bear, the rotating speed of first order Contra-rotating rotor is maximum, make air with supersonic speed axially into compressor, axial flow velocity is down to velocity of sound or so after being compressed through first order Contra-rotating rotor, the second level, the rotating speed of three-level Contra-rotating rotor is gradually reduced, air-flow axial velocity finally enters combustion chamber with low subsonic speed, the airflow inlet of every grade of Contra-rotating rotor and the direction exported are axial directions, to keep this axial direction, the heel row impeller of the first order and second level impeller is all more lower slightly than front-seat wheel speed, the speed triangle of three-level impeller is shown in Fig. 3-f, g, shown in h.Air and fuel in combustion chamber are that, with stoichiometric ratio mixed combustion, temperature is at 2200 DEG C or so, and turbine is only safe using subsonic speed to wheel turbine under conditions of this high temperature.The row of turbine wheel is slightly below the gyroscopic effect that front-seat impeller is produced for the heel row wheel speed that odd number can balance both stage impellers before compressor.

Compressor impeller is all transitioned into supersonic speed from starting to speed c, w, u during maximal rate from subsonic speed, and the critical Mach number of waveform blade inlet edge reaches as high as 2, both makes W₁M=3 when, the shock wave of waveform blade inlet edge also only with straight leading edge blade M=1.5 when Angle of Shock Waves it is suitable, and wave resistance is smaller, the minimum point of the peak of the crest of ripple leaf leading edge and the trough of adjacent ripple leaf leading edge is on a circumference when ripple leaf is installed on turbine, the sheet gas band that produces adjacent trough is non-intersect to converge, and the blade profile of ripple leaf farthest keeps equal thickness, and blade is wide and book, cascade solidity is larger, makes cascade flow field simply permanent.In speed w₁Increase to the shock wave produced when more than critical Mach number below critical Mach number to be pressurized leaf grating flow slowing down, the air-flow w of leaf grating outlet₂Direction can be more biased towards in the direction of rotation of impeller, the established angle of blade is installed by adapting to the deflection of this direction, and as shown in Fig. 3-d, e, this can make the high speed leaf grating speed w of compressor₁Leaf grating exit flow W when being in below critical Mach number₂Direction and subordinate leaf grating established angle it is inadaptable and the trend separated is produced in subordinate's leaf grating leaf basin, but the air-flow supplementary function of ripple leaf trough and the pressure of leaf basin are natively bigger than blade back, air-flow separation will not finally occur, in addition this phenomenon only can just occur in compressor start, time is also very short, on compressor substantially without influence, the stable operation range of compressor is in leaf grating relative velocity W₁Critical Mach number between compressor impeller maximum safe speed, this scope is more much greater than the stable operation range of straight leading edge supersonic cascade.The ultrasonic stable operation range of straight leading edge supersonic cascade is general in W₁M=1-1.5 between, can not be worked more than occurring cascade flow field complicated unsteady after M1.5, the critical Mach number of ripple leaf is higher, relative velocity W₁The more straight leading edge blade of the shock wave angular variable of ripple leaf leading edge is substantially slow during increase, so the speed change of ripple leaf grating and the scope of steady operation increase therewith.

When compressor is in stable operation range, that often arranges impeller adds the several times that work(amount is all subsonic compressor impeller, three-level is more than the pressure ratio of any subsonic compressor at present totally to turning the pressure ratio that 6 row's impellers are produced, weight and axial dimension are also substantially reduced, in addition the wave resistance of ripple leaf is small, gas channel is without boundary-layer, in the absence of surge problems, efficiency is higher, axial ultrasonic speed air inlet, the throughput of air for making ripple leaf compressor is also the several times of subsonic compressor, and the power output of combustion chamber and turbine is also made accordingly and increases several times.

Compressor, combustion chamber, the cooling of turbine and waste gas residual heat are reclaimed and all realized using the states of matter conversion cycle of steam and water.In figure 3, the normal-temperature water pressurizeed through water pump is divided into two-way, lead to compressor pipeline all the way into impeller disk radiant tube, blade inner flow passage, the compressor impeller internal channel of pedestal port formation flows to combustion chamber water jacket, the air for compressing heating to compressor blade and through compressor carries out cooling to improve compressor efficiency and reliability, another road flows to combustion chamber water jacket by being heated up after waste heat gas exchanger, two-way hot water is together vaporized in the water jacket of combustion chamber, moist steam then flows to wheel disk of turbine surface radiation shape flow tube, blade internal channel, the turbine wheel internal channel of pedestal port formation, at this moment turbine internal channel acts as superheater to the further heating of moist steam, steam turbine after entering turbine through high-pressure steam pipe promotes steam turbine acting, exhaust steam is cooled into normal-temperature water again within the condenser, the fan of arbor end is to strengthen condensation effect, circulated after normal-temperature water is pressurizeed through water circulating pump and into next cooling, this circulation is referred to as the cold interior circulation of liquid, this circulation makes a part of conversion in useless waste heat gas and heat generating components cooling dispersed heat for useful work, so as to improve the efficiency of gas turbine.Because the gas channel inner surface of ripple leaf combustion gas wheel and the outer surface of blade are all corrugateds, air-flow is skimmed over from the crest on corrugated in flow at high speed, therefore the ability that high temperature gas flow conducts heat to blade and gas channel can substantially weaken, this can significantly improve the heat resistance of combustion chamber and turbo blade, in addition the cooling effect of cooling water and steam in combustion chamber water jacket and turbine internal channel so that combustion chamber and turbine can bear the high temperature that air and fuel are produced with stoichiometric ratio mixed combustion.

Ripple leaf fanjet uses waveform blade, gas channel inner surface is the aerial turbo fan jet engine on corrugated, as shown in Fig. 5-a, it is identical that it is constituted with subsonic speed fanjet substantially, difference is that 1. its air intake duct is that the annular internal compressioninlet constituted in straight tube is placed in by cone governor, 2. the annulus area of air intake port rotates the ring area equation skimmed over fan blade, fan is one-level to turning ripple blade fan, 4. high-pressure compressor is two-stage ripple leaf counter-rotating compressor, 9. turbine is the i.e. 3 row's Contra-rotating rotors of one-level half, 5. turbine by being placed on arbor above in the tubular axle between compressor and turbine 6. to high-pressure compressor and fan transimission power, the arbor of engine is not rotated, the blade tip peripheral speed of fan and compressor is supersonic speed, turbine is subsonic speed counter rotating turbine, combustion chamber 8. interior air and fuel with stoichiometric ratio mixed combustion, by-pass air duct spout

It is the supersonic nozzle of no venturi, the spout of main duct

It is the receipts sword divergent channel for having venturi, coherent is not mixed the jet flow of provided with internal duct and external duct spout, compressor and turbine all have impeller internal channel, combustion chamber is the toroidal combustion chamber with water jacket, the quantity fin equal with fan blade quantity is uniform-distribution with engine by-pass air duct 7., cooling fin front end is close to fan, rear end is close to spout, two long sides respectively with by-pass air duct inwall, the outer wall of compressor and turbine casing connects, and be hollow flat board, its surface is plane rather than corrugated, thermal conductivity is stronger, cavity front end in fin and high pressure are calmed the anger, and 3. inner chamber is communicated for the fagging of phase front end, fagging inner chamber connects with annular port at the front-seat impeller central bearing of high-pressure compressor again, 10. cavity is communicated the cavity of fin rear end with turbine rear stay plate, turbine rear stay plate cavity connects with the annular port at turbine heel row impeller central bearing again, it is generator/motor in one section of isodiametric ring cavity between compressor and combustion chamber.

After engine start, because the supersonic speed of fan and compressor is rotated, fan inlet is that the axial admission speed of air inlet pipe outlet is also supersonic speed, maximum can be to M=2, powerful suction force is produced to Fighter Inlet and air inlet axial velocity is reached more than the velocity of sound, after engine takeoff air inlet almost non-resistance is reached in this period of the velocity of sound to flying speed, the air that supersonic speed enters axial velocity after fan compression is down to the velocity of sound or skips over the velocity of sound, then still accelerate to spray from divergentnozzle with supersonic speed through by-pass air duct, into main duct air through high-pressure compressor supercharging be decelerated to low subsonic speed, its speed triangle such as Fig. 3-f, g, shown in h, air promotes turbine after burning heating indoor with subsonic speed, sprayed after turbine after convergent divergent nozzle with supersonic speed, when engine flight speed reaches inlet charge speed, air intake duct starts to produce resistance, the interior shock wave produced in air intake duct makes air-flow be decelerated to subsonic speed in air intake duct again, because the astriction of runner and the swabbing action of fan are accelerated to supersonic speed again during fan is flowed to, with the increase of engine flight speed, the phenomenon that subsonic airflow in air intake duct is converted to supersonic speed again can disappear, become supersonic flow in air intake duct under excited wave retardation still with hypersonic flow to fan, engine flight speed when the axial intake velocity of air intake port air-flow axial velocity and fan is equal is the maximum flying speed of engine, this speed is maximum up to M=3.

In-engine liquid coolant enters compressor impeller internal channel from compressor front end fagging, through combustion chamber water jacket, turbine wheel internal channel, turbine rear stay plate enters fin inner chamber in by-pass air duct, finally it is returned to high-pressure compressor front end fagging, the heat that this circulating path sheds impeller in compressor and air cooling-down, the heat that combustion chamber and turbine cooling shed is transmitted to the air flowed in by-pass air duct by the fin in by-pass air duct, outer culvert air is heated to spray, core engine heating part is winding is effectively cooled again, the bad heat conductivility having due to Bo Ye and corrugated, the consumption of coolant is also fewer, it is little to the weight of engine.

Due to engine handle up air be all supersonic speed, stoichiometric ratio burning, axial dimension of the gas channel without boundary-layer, compressor and turbine be short, lightweight, coolant circulating cooling, the thrust and thrust-weight ratio that ripple leaf fanjet is produced are several times as much as subsonic speed fanjet, so as to ensure engine high-temperature, high pressure, supersonic flight.

Shown in ripple leaf turboprop as Fig. 5-b, 1. its air intake duct is also that the internal compressioninlet constituted in inlet cylinder is placed in by cone governor, 9. also 4. there is impeller internal channel with turbine to the compressor turned, 8. combustion chamber is also the cold toroidal combustion chamber of liquid, the channel inner surface that air-flow gulps down leaf is also corrugated, and two rows are to turning undulating helical oar

The arbor being placed in after gas generator turbine 5. end, the bevel gear on pedestal between propeller leaf dish

Transmission realizes that the blade number for often arranging turning propeller is 8 or so, train of reduction gears

Loaded on the arbor between propeller and turbine, the power of turbine is passed into rotating propeller, cylindric train of reduction gears outer cover

The diameter of one end is equal with last row's wheel disk of turbine diameter and is abutted with wheel disc, other end diameter is equal with airscrew diameter and is abutted with oar disk, change-speed gearing group is covered between arbor and gear train outer cover, gear train outer cover is fixed on the end face of the gear shaft vertical with arbor, the blast pipe after turbine

Axial length is equal with the axial length of gear train, between end inner surface and gear train outer cover in blast pipe fagging

It is fixedly connected, a plurality of hollow fin is uniform-distribution with gasifier shell 7., the length of fin is parallel with gas generator arbor, width is overlapped with the diameter of gas generator, 3. front end cavity communicates inner chamber with compressor front end fagging, 10. inner chamber is communicated rear end cavity with turbine rear stay plate, and compressor front end fagging inner chamber is communicated by compressor impeller internal channel, combustion chamber water jacket, turbine wheel internal channel with turbine rear stay plate inner chamber, the passage interior circulation that coolant is communicated herein.

When engine works, because the suction force that compressor supersonic speed rotates makes engine intake axial admission speed reach the velocity of sound, air inlet non-resistance in engine takeoff and accelerator, useless combustion gas after turbine in combustion gas blast pipe passes through from propeller root and blade root is done work, this can mitigate the transmission load of the gear train between turbine and propeller, because the bevel gear between wheel disk of turbine inherently makes prime impeller transmit power to rear class impeller, and make afterbody impeller deceleration, the peripheral speed of propeller blade tip is supersonic speed again, so the weight and degree of deceleration of train of reduction gears are smaller, coolant is in fin inner chamber, compressor impeller internal channel, combustion chamber water jacket, the heat to be shed in cooling down heat generating components is circulated in the passage that turbine wheel internal channel is connected to be transmitted to from the air for flowing fortune between fin, air and fuel in combustion chamber is with stoichiometric ratio mixed combustion, in addition engine is handled up air with the velocity of sound, engine just produces powerful power-weight ratio, as long as the centrifugal force collocation that the diameter and material of propeller can bear is proper, the speed of ripple leaf turbine propelling screw engine can break through the velocity of sound.

Ripple leaf reinforcing turbofan/ultra-combustion ramjet/rocket composite rocket engine is as shown in Figure 6,4. interior in straight-cylindrical casing, from air inlet 2. to exhaust outlet

Successively by air inlet adjustment cone 3., ripple leaf Turbofan with Afterburner 7., after-burnerRestrain diffused jet pipe

Coaxial line is formed by connecting, and inlet cone constitutes the pre-large post-small internal compressioninlet of annulus area with air inlet pipe, and air inlet has an angular cut from the air inlet center of circle to wall

, diameter and fan wheel disc diameter, the core engine of inlet cone butt end

Housing diameter is all equal, makes the fagging before the gas channel of the by-pass air duct formation uiform section product of fanjet, fan

Sectional area be adjustable, fagging is i.e. in regulation air intake port area, the main duct air intake duct after fan before regulation fanFrom fan trailing edge arbor direction reduced diameter backward, be uniform-distribution with the quantity dividing plate equal with fagging quantity before fan blade and fan in by-pass air duct, plate front end close to fan and with fagging before fan point-blank, rear end and core engine exhaust outlet

Concordantly, the length of dividing plate is parallel with arbor, highly parallel with fan diameter, and by-pass air duct is separated into multiple slypes to core engine exhaust port side before fan, this passage be both by-pass air duct gas channel simultaneously and super burn gas channel, along the straight line where the line at divider height midpoint, fagging foremost backward splits fagging and dividing plate before fan, fagging and dividing plate section point-blank

In elongated hexagon, front end

Air intake duct contraction section is collectively forming with air intake duct, the gas channel of middle equal thickness section is super burn air inlet distance piece

With uiform section super burn bringing-up section

, the divergent contour gas channel that the part that the thickness of rear end is gradually reduced is formed is to wait static temperature super burn bringing-up section

, there is depression on the crest top on the corrugated of two bringing-up sections

, depression in have fuel injection aperture, after-burner

It is exactly one section of isodiametric straight tube, no flameholder and igniter, the rectangular in cross-section of adjustable convergence diffused jet pipe, the two pieces of adjustable plates that can roll over

It is placed on two faces relative in rectangular tube, adjustable plate approximate venturi occurs when bending, adjustable plate abuts rectangular tube internal face during stretching, extension, it is parallel with internal face, sectional area is equal with after-burner sectional area, equipped with three triangle T tails, the two horizontal tail wings in spout outside wall surface

Symmetrically, a vertical fin wing

Vertical with the line of the two horizontal tail wings, three empennages are all hollow, and the side towards spout jet direction is to be open, and 90 ° of deflection of energy, referred to as deflect spout

, deflection spout communicated through empennage inner chamber with after-burner, at the front end of two horizontal tails on jet pipe shell respectively then one be folded to motor head forward direction conduction pipe

, the outlet of pipeline front endBe can do it is parallel with arbor or with arbor it is in 90 ° curve motion regurgitate/hang down the dual-purpose spout of spray, rear end of pipeline is communicated with after-burner.The combustion chamber of core engineOne section of annular air-flow path before entrance

Inside it is uniform-distribution with the height deflector parallel with arbor with compressor impeller diameter parallel, width

Part behind the midpoint of width dimensions can turn back 80 ° to the left or to the right to stop when up to being hindered by adjacent deflector midpoint and with axial flow sealing, blast pipe after core engine turbine is also rocket chamber, and nozzles with injector is constituted with rocket chamber when jet pipe adjustable plate stretches.From air inlet, every surface for having air-flow to flow through into the gas channel of nozzle is depression corrugated entirely to whole engine, 10. 7. fan be to have impeller internal channel to turning ripple leaf impeller with compressor, the blde pitch of fan is adjustable, when stopping fan rotation but when having the air-flow to flow through, fan bladeApproximate (see shown in b, c, d, the e in Fig. 4) parallel with arbor of chord of foil.Turbine

It is subsonic speed counter rotating turbine and with impeller internal channel, 6. arbor maintains static dynamic, and turbine is by being placed on arbor in the tubular axle between compressor and turbine

To high-pressure compressor and fan transimission power.There is the depression of small size on the crest summit on the depression corrugated that the high temperature gas flow of rocket chamber, after-burner and jet pipe passes through

, have low-temperature airflow jet apertures in depression.9. the fuel supply pipe of engine has three groups, first group 8. penetrated from engine housing after be passed through fan rear bulkheadInner chamber, from the crest of super burn combustion chamber corrugated small size depression

In aperture spray, second group

Penetrated from engine housing and be then passed through by-pass air duct dividing plate inner chamber and stretch into core engine combustion chamber from nozzle

Spray, the 3rd group

Penetrated from engine housing and be then passed through being divided into two, one after by-pass air duct dividing plate inner chamber enters core engine blast pipe

The nozzle on fagging terminal edge, Ling Yizhi are extended backward from turbine rear stay plateBlast pipe end nozzle is extended from exhaust wall inner chamber.The coolant circulation passage of engine be 1. begin from air inlet front edge, the cavity through air intake duct wall, the pipeline before fan before fagging inner chamber, inlet cone conical surface water jacket, inlet cone cone, cone and fan wheel disc between fagging 5., fan internal channel (Fig. 4-2.,

), between fan wheel disc and high pressure gas wheel disk be placed on arbor 6. on pipeline, high-pressure compressor impeller internal channel, combustion chamber water jacket, turbine wheel internal channel, turbine rear stay plate inner chamber, turbine rear exhaust tube wall inner chamber, by-pass air duct dividing plate end coolant channel

, afterbunring locular wall

Inner chamber to after-burner internal face crest summit is recessed

In aperture spray, cooling agent is also from by-pass air duct dividing plate end coolant channel

The outlet stretched out outside engine casing

Outflow, through with outlet

The pipeline connected is drained into outside engine.The liquid oxygen of engine is supplied through pipeline

From the end shell inner cavity of jet pipe

It is passed through, through afterbunring locular wall inner chamber, by-pass air duct dividing plate end coolant channel, turbine rear exhaust tube wall inner chamber to turbine rear stay plate end nozzle

.The valve at entrance that afterbunring wall inner chamber is communicated with aperture in the crest summit depression of internal faceWhen cooling agent flows from front to back, valve is opened by fluid forces, and coolant flow is to corrugated crest summit aperture

, when liquid oxygen is from rear end flow forward, valve is promoted and closed by liquid oxygen stream again, and liquid oxygen will not be leaked into afterbunring room.

After engine start, core engine drives fan supersonic speed to rotate, the powerful suction of fan makes the axial admission speed of Fighter Inlet and outlet all reach supersonic speed, air then enters by-pass air duct and main duct after fan compression with high subsonic speed, slow down through by-pass air duct runner and be pressurized, main duct core engine turbine rear exhaust pipe is also diffusion admittance, provided with internal duct and external duct air-flow is while after-burner is mixed, the fuel nozzle of turbine rear exhaust pipe end is also to mixed airflow spray fuel, because core engine combustion chamber is burnt with stoichiometric ratio, the gas flow temperature of turbine rear exhaust pipe discharge is higher, after-burner smooth ignition can be made, now jet pipe venturi shrinkage area, the high-temperature high-pressure air flow overwhelming majority that after-burner is produced enters preceding to mozzle, draft tube outlets make combustion gas stream is vertical slightly to spray earthward and backward, whole engine vertically lifts off, it can make engine pitching to the jet direction of mozzle spout and empennage spout before regulation, driftage, rolling, somersault etc., it is now the AB takeoff state of engine；Closed before when engine reach a certain height to mozzle, jet pipe venturi is expanded, after-burner stops spray fuel simultaneously, engine flight forward, but lift is undertaken by aircraft wing, regulation empennage spout jet direction makes engine vector motor-driven, during engine angle of attack increase, angular cut before air intake duct can increase air inflow, be now the cruising condition of engine；When flight forward speed is close to 3M, air intake duct has been started up, engine is again turned on reinforcing, fagging wears area expansion before fan simultaneously, reduce air intake port area, reduce fuel supply in core engine combustion chamber, main duct air intlet, which shrinks, reduces the tolerance into main duct, and turbine rear stay plate end nozzle starts spray fuel, so as to be formed, rotation speed of the fan reduces and the air-flow axial direction speed of air intake port is adapted, the hot combustion gas of turbine rear exhaust pipe discharge plays stable ignition to after-burner, now engine enters sub- combustion punching press state, because the rotation of fan can effectively prevent air-flow to the refluence at air inlet road junction, there is swabbing action to air intake port air-flow simultaneously, in addition before fan fagging sectional area cooperation regulation and empennage spout regulation, the job stability of engine and mobility in-flight are all more superior than conventional sub- burning ramjet；When engine flight speed reaches 6M, fan blade is all reversed to chord of foil and arbor less parallel, while main duct inlet close, core engine combustion chamber and turbine rear stay plate end nozzle stop fuel injection, the aperture that fuel changes in the depression of by-pass air duct fagging corrugated crest top sprays, venturi adjustable plate full extension in jet pipe, fagging sectional area is then gradually reduced before fan, air intake port air-flow is set to change to the velocity of sound and supersonic speed, after the distance piece between fagging after fan uiform section bringing-up section and etc. static temperature heating in fuel be diffused mixed combustion, sprayed from after-burner and jet pipe with the divergent channel that empennage spout is combined, now engine enters ultra-combustion ramjet state；When engine flight speed reaches 10-15M, the deflector in passage between core engine high-pressure compressor and combustion chamber, which is turned back, produces axial flow sealing, super burn combustion chamber stops supply fuel, the liquid oxygen passage of engine is opened, liquid oxygen is when flowing through passage because to jet pipe, after-burner and turbine rear exhaust tube wall are cooled down and heating of absorbing heat, gasify when reaching combustion chamber, burnt with the fuel mixing ignition that turbine rear stay plate end nozzle sprays, the nozzles with injector constituted from combustion chamber and after-burner and jet pipe sprays, engine enters rocket jet engine condition, engine is when further speeding up, fagging cross-sectional expansion to most ambassador's air intake port is blocked completely before fan, Fighter Inlet is also converted into taper under the cooperation of aircraft, engine finally accelerates to 25M and enters Earth's orbit；During engine returns to ground from Earth's orbit, State Transferring when State Transferring is with rising is opposite.

Engine fuel is mainly hydrogen fuel, hydrocarbon fuel can also be used in below 6M, the cooling agent of engine is mainly taken on by liquid hydrogen and ice, except carrying liquid hydrogen i.e. in engine flight, outside LOX tank, also one ice cube tank, engine flight speed is in below 6M, need the part mainly core engine of cooling, after-burner, to water conservancy diversion jet pipe and jet pipe before combustion gas, engine needs the part cooled down to include air intake duct during more than 6-10M, by-pass air duct dividing plate, the super burn jet pipe of after-burner and jet pipe composition, and engine be heated it is more serious, it is difficult that good cooling is carried out to engine to depend merely on for the liquid hydrogen for supplying burning, ice uses the ice of low temperature as far as possible, utilize the states of matter change heat absorption cooling of ice, Liquid Hydrogen fuel delivery pipe is also through just entering engine later out of ice cube tank.Ice tank has two pipelines to be connected with engine coolant fluid passage, one piece-root grafting is in engine charge tube wall leading edge inner chamber, another piece-root grafting is in the coolant channel inner chamber of by-pass air duct dividing plate end, water is in air intake duct wall, cone governor, fan, flowed from front to back in the coolant channel that core engine is communicated and engine is cooled down, after water heating ice cube tank is flow to from the pipeline for being connected to by-pass air duct dividing plate end coolant channel inner chamber, the liquid hydrogen in Liquid Hydrogen fuel supply pipe is set to gasify in cold piece of tank, ice cube is set gradually to melt simultaneously, and be further warming up to close to boiling point, such a type of cooling is used for the cruising condition of engine.After the closedown of pipeline that ice tank is connected with by-pass air duct dividing plate end coolant channel, reduce flow velocity of the cooling water in cooling channel of motor simultaneously, water can be vaporized when being cooled down to engine heating part, steam then flows into afterbunring locular wall inner chamber, sprayed from the aperture in after-burner and jet pipe internal face crest summit depression and air film is formed between crest and high-temperature fuel gas stream, sprayed with high temperature gas flow while internal wall cooling and increase the thrust of engine, such a type of cooling is used for the Afterburning condition and sub- combustion punching press state of engine.Cooling water enters from air inlet tube wall leading edge during super burn state, the rapid vaporization in coolant channel, aperture in the depression of the last super burn nozzle wall face crest summit constituted from after-burner and jet pipe of steam sprays, and had not only played cooling effect but also had increased the thrust of engine；Liquid hydrogen is only responsible for cooling down by-pass air duct dividing plate, and liquid hydrogen riddles the inner chamber of each dividing plate, and liquid hydrogen sprays from the aperture in dividing plate outer surface crest summit depression, hydrogen film is formed between high temperature gas flow and crest heat-insulated.Because the heat generating components of engine and the crest on corrugated are all that exotic material is constituted, in addition corrugated effectively can hinder high temperature to be conducted to wall, the consumption of cooling agent is seldom in real engine work, again because ice will absorb substantial amounts of heat from low temperature to melting to vaporizing to 700 DEG C of high temperature, a small amount of ice is with regard to that can aid in liquid hydrogen to carry out good cooling to engine, the final product of ice cooling agent is high-temperature steam and increases thrust after being sprayed with combustion gas, harmful effect of the ice tank to engine load can be reduced, cooling of the engine in rocket state is completed by liquid oxygen flows through cooling duct in supply process.

The characteristics of this engine is that internal compressioninlet intake efficiency is high, wide adaptation range, engine air handling capacity is big, turbine inlet temperature is high, and length and weight are suitable with Turbofan with Afterburner, and diameter is more smaller than Turbofan with Afterburner, thrust and thrust-weight ratio are several times of Turbofan with Afterburner, cost is more or less the same with Turbofan with Afterburner, can be vertically moved up or down, velocity adaptive 0-25M.

Ripple wing corrugated airborne vehicle

Ripple leaf whirlpool oar aircraft is as shown in fig. 7, airframe outer surface is all depression corrugated, and wing and empennage are all Waved wings, using ripple leaf turboprop.Such a aircraft takes off that ground run distance is shorter than common whirlpool oar, and loading capacity is bigger, and voyage is farther, and velocity of sound can be broken through during maximal rate.

Ripple oar helicopter is as shown in Figure 8, fuselage is supersonic speed fuselage, it is all depression corrugated that fuselage outer surface, which includes transparent part, 1. the crest on the corrugated of part especially makes of heat proof material when wherein saturating, wing is Waved wing, respectively there is a big hole in the middle of two aerofoil surfaces and circular hole occupies exhausted most area of wing, the multiple-blade propeller of ripple wing configuration is installed in wing circular hole, the diameter of propeller is parallel with wing chord, propeller rotational in two wings is in opposite direction, 2. wing circular hole face suitable for reading is provided with bending plate, bending plate is integral with upper surface of the airfoil when stretching, in upper surface of the airfoil one triangular-section gas channel from front to back of formation when bending plate is bent, engine uses ripple leaf fanjet, engine is placed in above afterbody, power transmission shaft of the front axle of engine through the propeller in clutch band motivation wing circular hole, the empennage jet pipe of engine rear end controls the posture of aircraft.

When taking off, engine afterbody tailplane spout downward bias is become a full member face over the ground, engine front axle drives the propeller in two wings simultaneously, bending plate is also at bending state, and the air-flow that propeller rotational is produced with engine empennage spout earthward sprays, and aircraft vertical takes off, while lifting height or rise to after certain altitude, the revolution of empennage spout makes jet flow backward, aircraft flight forward, and now aircraft flies as pure helicopter；Because aircraft is advanced with engine jet thrust, bending plate stretches when speed reaches certain value, drives the clutch of propeller to disconnect, engine pushing forward aircraft flight forward, and maximal rate is up to 3M.Because the rotating speed of propeller is high, diameter is smaller, lighter in weight, and aircraft is small without boundary layer drag in addition, and the lift of Waved wing is big, and influence of the heavy burden that propeller is produced in aircraft flight to voyage is also little.Alternative current armed helicopter and attack plane when such a aircraft is used for military, are mainly used as commercial special plane, carrying 3-5 people during for civil aviaton.

Ripple wing corrugated jet transport aircraft is as shown in Figure 9, the value of fuselage fineness ratio is larger, fuselage outer surface is all depression corrugated, the crest of the transparent part of outer surface is made using exotic material, manned in cabin can be by situation outside the gap observation machine of two crests, and wing and empennage are all Waved wings, and the wave height of wing front and rear edge is gradually reduced from wing root to wingtip, engine is used under ripple leaf turbofan/punching press combined engine, two wings each one at nearly wing root.The characteristics of this aircraft be can vertical/short distance lifting, no boundary-layer and resistance is small, loading capacity is big, and voyage is remote, using maximal rate 6M during hydrocarbon fuel, uses maximal rate 10M during hydrogen fuel.

Ripple wing corrugated high-performance cruise guided missile, jet-propelled war craft is as shown in Figure 10, guided missile a and aircraft b outer surface are all depression corrugateds, crest is made using exotic material, missile wing and wing are all Waved wings, wing front and rear edge wave height is gradually reduced from wing root to wingtip, empennage merges into a single whole with engine empennage spout, engine intake is below bomb body and fore-body, engine uses ripple leaf turbofan/ultra-combustion ramjet/rocket composite rocket engine, can vertical/short distance lifting, resistant to elevated temperatures crest can bear thermal boundary and greatly reduce the usage amount of exotic material and mitigate weight, it is extraordinary motor-driven, speed can reach 25M during high-speed flight.It is mainly used in space warfare bucket.

Ripple wing corrugated wing shaped airplane is as shown in Figure 11, the Waved wing and fuselage of aircraft combine together, whole aircraft is as leaf, leading edge has three crests, middle crest wave height value is maximum, the crest wave height value on both sides is smaller and equal, two crests of trailing edge and wave height is equal, two vertical fins are placed at trailing edge crest above fuselage, using three Tai Boye turbofans/ultra-combustion ramjet/rocket composite rocket engine, one is placed on the line of leading edge intermediate peak summit and trailing edge trough bottom point and close to leading edge intermediate peak, another two are placed on the line on the trough bottom point of leading edge two and the crest summit of trailing edge two and close to trailing edge crest, previous engine does not need empennage spout, the empennage spout of two engines combines together with the vertical fin of fuselage trailing edge and crest edge afterwards.Fuselage outer surface is all depression corrugated, and the crest on corrugated is made using exotic material.This aircraft has the aerodynamic lift of wing and the corrugated lift on corrugated; corrugated makes exotic material usage amount few again; resistance to elevated temperatures is good; the powerful thrust and vertical lift function of engine make aircraft vertical/short distance lifting; planeload is huge; in-flight because without boundary-layer, resistance is small, extraordinary mobility is good, maximal rate 25M.It is geloppy during for military and civil aviaton, black barrier effect can be postponed and slackened in corrugated when coming and going instrument as empty day, huge fuselage area and the vertical air injection function of engine make aircraft return to ground of being floatd go back to when ground gets through the earth's atmosphere, mitigate thermic load significantly.

Corrugated ripple slurry navigation device

Corrugated Bo Jiang naval vessels are as shown in Figure 12-a, the above water outer surface on naval vessel and underwater portion appearance are all depression corrugateds, ship navigation reclaimed water top wave-front division can reduce the frictional force with air, underwater portion corrugated can reduce the frictional force with water, the engine on naval vessel uses ripple leaf gas turbine, and the paddle of propeller uses the configuration of Waved wing to be ripple vane propeller, and such a ship sailing resistance is small, the speed of a ship or plane is fast, is substantially reduced consumption fuel quantity.

Shown in corrugated ripple slurry submarine, torpedo as Figure 12-b, c, submarine b and torpedo c outer surface are all depression corrugateds, the thickness junction of kayak body and thunder body is raised corrugated, propeller uses ripple vane propeller, when submarine and torpedo are navigated by water, pressure in the trough of corrugated can reduce and then produce water evaporation, steam and the alternate rubbing surface in crest summit are produced between outer surface and water, the resistance very little of this rubbing surface, in addition the rotating speed of ripple vane propeller is high and is not likely to produce hole, and the speed of a ship or plane is just significantly beyond conventional submarine and torpedo；When corrugated torpedo is promoted using rocket engine, as shown in Figure 12-d, the water evaporation phenomenon in the trough of corrugated is rapider, and corrugated torpedo can reach the speed of a ship or plane of supercavitating torpedo and can the alternately navigation of water sky.

Claims (7)

1. Waved wing also belongs to straight wing, difference with the straight wing be its on the basis of the straight wing, leading edge and trailing edge it is wavy in sawtooth like, this " ripple " is identical with the sine wave, the triangular wave that occur on oscillograph, nose of wing is that crest is recessed backward to lordosis, trough, wing trailing edge is then that crest is recessed forward, trough is convex backward, line, the line of trough nadir on the summit of front and rear edge crest are overlapped with wing chord, and aerofoil profile is high speed aerofoil profile；Object waveform surface exhibits form has two kinds：One kind is wave crest, wave height is parallel with body surface, the line of the minimum point of trough, the line of crest peak is parallel with surface, the thickness of wave crest is suitable with the boundary layer thickness on surface, the flow direction of fluid of the direction of ripple with being flowed through on surface is vertical, another corrugated is that have wavy depression in plane or cambered surface or inclined-plane, the summit of crest is overlapped with plane or cambered surface or inclined-plane, trough is then recessed into plane or cambered surface or inclined-plane, the flow direction of fluid of the direction of ripple with being flowed through on surface is consistent, this corrugated is referred to as the corrugated that is recessed, the ripple that corrugated is presented all is the equal sine wave or triangular wave of wave height；The product that the waved surface of Waved wing and object is belonged to after the external shape of rule modification with ripple.

2. claim 1 is applied into gas turbine, referred to as ripple leaf gas turbine, it is characterized in that：The front and rear edge of blade is in wave shape, and leaf basin and blade back surface are depression waved surfaces, compressor casing inner surface, turbine surface at blade root, and burn chamber internal surface, and turbine surface is all depression corrugated at turbine casing inner surface, turbine blade root；There is bearing at the hub disk center of compressor and turbine, wheel disc is fixed on arbor by bearing, the two sides of wheel disc it is symmetrical radial pipeline, one end of pipeline in the ring-type port vertical with arbor of one mouth face of Correspondent formation at wheel disc centre bearing, the other end is through the junction of wheel disc and root of blade, the passage being passed through in hollow blade, passage in blade begins the blade root opposite side that turned back again to blade tip from blade root side, and the radiant tube with wheel disc two sides is communicated respectively；There is one to be fixed on arbor between per two adjacent wheel discs, be in two-wheeled dish axle hold between annular bevel gear pedestal, the center of pedestal is the circular hole being placed on arbor, edge is 4-6 roots with pedestal diameter point-blank, the bevel gear shaft vertical with edge surface, it is that plane is parallel with pedestal diameter and pedestal thickness between pedestal margin and center hole, equal sized multiple sheets of dispersed arrangement every latticing, every latticing geometric center point on a circumference, space between latticing is the port of pedestal, the two ends of port connect with the ring-type port at hub disk centre bearing respectively, and seal joint with Gask-O-Seal, the cone tooth of bevel gear is in the two ends of cylinder, the big circumference diameter for boring tooth is equal with drum diameter, the small circumference diameter for boring tooth is equal with the two bearings internal diameter in cylinder, bevel gear shaft on pedestal penetrates in two bevel gear small circumference centre bores and cylinder the internal diameter of two bearings and bevel gear is fixed on pedestal, between two impeller disks, ring-type bevel gear and the cone tooth of pedestal bevel gear root wherein on the faster impeller disk of rotating speed is ratcheting, ring-type bevel gear on the slower impeller disk of rotating speed and bevel gear at the top of pedestal bevel gear are ratcheting, the i.e. two adjacent impeller disks realize differential to turning by the Bevel Gear Transmission on pedestal therebetween, when the bevel gear diameter on two adjacent impeller disks is equal, equal speed counter-rotating is then realized by bevel gear therebetween；Every two row is referred to as one-level to the impeller turned, compressor and turbine are all to slow down step by step from front to back, the impeller row of compressor is even number, turbine wheel row is odd number, compressor impeller is that supersonic speed is rotated, turbine wheel is that subsonic speed is rotated, prime counter rotating turbine is by being placed on arbor, the axial compressor transmission of tubular transmission between turbine and compressor, rear class counter rotating turbine and most heel row impeller are free turbines, ring-type cone tooth on outside most heel row wheel disk of turbine and the bevel gear between turbine rear stay plate are ratcheting, between fagging bevel gear again with to penetrate bevel gear in arbor on the power transmission shaft of intracavitary ratcheting, power transmission shaft is in the external power output in compressor front end；Part after the turbine of power transmission shaft is sequentially arranged with steam turbine, circulating pump, condenser fan, steam turbine import connects with the cavity in turbine rear stay plate, fagging cavity is connected with the annular port at centre bearing outside most heel row wheel disk of turbine again, connecting place has sealing gasket sealing, the outlet of steam turbine is connected with condenser inlet, and the outlet of condenser is connected with circulating pump；Circulation pump delivery line is divided into two-way, connect all the way with the heat exchanger in fuel gas exhaust pipe, the outlet of heat exchanger is connected to combustion chamber water jacket by the pipeline being distributed on gas turbine shell, another road is led in the fagging cavity at forcing press import, fagging cavity connects with the ring-type port at compressor first row hub disk centre bearing again, and there is Gask-O-Seal sealing joint；Last row's hub disk of compressor is communicated towards the annular port at the wheel face centre bearing of combustion chamber with combustion chamber water jacket, combustion chamber is annular firing, shell of only having family is constituted, there is no the burner inner liner in conventional gas turbines combustion chamber, it is water jacket outside the shell of room, water jacket wall close to arbor in the annular port for respectively having a passage to lead at its neighbouring hub disk centre bearing at compressor and at close turbine and seals joint by Gask-O-Seal, guide vane in the inlet and outlet of combustion chamber is all hollow, the port of air compressor wheel disk center is led in guide vane inner chamber at import, the port at wheel disk of turbine center is led in exit guide vane inner chamber；Whole gas turbine shows two passes, one is entered from compressor inlet, through compressor, combustion chamber, turbine, the gas channel of blast pipe, one is that fagging inner chamber is begun before compressor, compressor internal channel through pedestal port formation between gas compressor blade wheel face radiant tube and blade inner chamber and impeller, combustion chamber water jacket, the turbine internal channel of pedestal port formation between turbine wheel card radiant tube and blade inner chamber and impeller, turbine rear stay plate inner chamber, steam turbine, condenser, coolant recirculation pump, heat exchanger in fuel gas exhaust pipe, the pipeline being distributed on gas turbine shell is back to the coolant circulation passage of fagging inner chamber and combustion chamber water jacket before compressor.

3. claim 1 is applied into fanjet,Referred to as ripple leaf fanjet,It is identical that it is constituted with subsonic speed fanjet substantially,Difference is that its air intake duct is to be placed in straight tube to constitute annular internal compressioninlet by cone governor,The annulus area of air intake port rotates the ring area equation skimmed over fan blade,Fan is one-level to turning ripple blade fan,High-pressure compressor is two-stage ripple leaf counter-rotating compressor,Turbine is the i.e. 3 row's Contra-rotating rotors of one-level half,Turbine is by being placed on arbor in the tubular axial fan transimission power between compressor and turbine,The arbor of engine is not rotated,The blade tip peripheral speed of fan and compressor is supersonic speed,Turbine is subsonic speed counter rotating turbine,Burning room air is with fuel with stoichiometric ratio mixed combustion,By-pass air duct spout is the supersonic nozzle of no venturi,The spout of main duct is the receipts sword divergent channel for having venturi,Coherent is not mixed the jet flow of provided with internal duct and external duct spout,Compressor and turbine all have impeller internal channel,Combustion chamber is the toroidal combustion chamber with water jacket,The quantity fin equal with fan blade quantity is uniform-distribution with engine by-pass air duct,Cooling fin front end is close to fan,Rear end is close to spout,Two long sides respectively with by-pass air duct inwall,The outer wall of compressor and turbine casing connects,And be hollow flat board,Its surface is plane rather than corrugated,Thermal conductivity is stronger,Cavity front end in fin is communicated with the fagging inner chamber of high-pressure compressor front end,Fagging inner chamber connects with annular port at the front-seat impeller central bearing of high-pressure compressor again,The cavity of fin rear end is communicated with turbine rear stay plate cavity,Turbine rear stay plate cavity connects with the annular port at turbine heel row impeller central bearing again,It is generator/motor in one section of isodiametric ring cavity between compressor and combustion chamber.

4. claim 1 is applied into turboprop, referred to as ripple leaf turboprop, it is characterized in that：Air intake duct is placed in inlet cylinder by cone governor and constitutes internal compressioninlet, there is impeller internal channel to the compressor and turbine turned, combustion chamber is the cold toroidal combustion chamber of liquid, the channel inner surface that air-flow gulps down leaf is corrugated, two rows are to turning the arbor end that undulating helical oar is placed in after gas generator turbine, Bevel Gear Transmission on pedestal between propeller leaf dish is realized to turning, often the blade number of row's propeller is 8 or so, reduction gearing is assembled on the arbor between propeller and turbine, the power of turbine is passed into propeller, the diameter of cylindric train of reduction gears outer cover one end is equal with last row's wheel disk of turbine diameter and is abutted with wheel disc, other end diameter is equal with airscrew diameter and is abutted with oar disk, change-speed gearing group is covered between arbor and gear train outer cover, gear train outer cover is fixed on the end face of the gear shaft vertical with arbor, blast pipe axial length after turbine is equal with the axial length of gear train, fagging is fixedly connected in blast pipe between end inner surface and gear train outer cover, a plurality of hollow fin is uniform-distribution with gasifier shell, the length of fin is parallel with gas generator arbor, width is overlapped with the diameter of gas generator, cooling fin front end cavity is communicated with compressor front end fagging inner chamber, rear end cavity is communicated with turbine rear stay plate inner chamber, compressor front end fagging inner chamber passes through compressor impeller internal channel, combustion chamber water jacket, turbine wheel internal channel is communicated with turbine rear stay plate inner chamber, the passage interior circulation that coolant is communicated herein.

5. claim 1 is applied into Turbofan with Afterburner, scramjet engine and rocket and this three kinds of engines are combined, referred to as ripple leaf reinforcing turbofan/ultra-combustion ramjet/rocket composite rocket engine, it is characterized in that：In straight-cylindrical casing, bored successively by air inlet adjustment from air inlet to exhaust outlet, ripple leaf Turbofan with Afterburner, after-burner, convergence diffused jet pipe coaxial line be formed by connecting；Inlet cone constitutes the pre-large post-small internal compressioninlet of annulus area with air inlet pipe,Air inlet has an angular cut from the air inlet center of circle to wall,The diameter of inlet cone butt end and fan wheel disc diameter,Core engine housing diameter is all equal,Make the gas channel of the by-pass air duct formation uiform section product of fanjet,The sectional area of fagging before fan is adjustable,Adjust fagging before fan and adjust air intake port area,Main duct air intake duct after fan is from fan trailing edge,Arbor direction reduced diameter backward,The quantity dividing plate equal with fagging quantity before fan blade and fan is uniform-distribution with by-pass air duct,Plate front end close to fan and with fagging before fan point-blank,Rear end is concordant with core engine exhaust outlet,The length of dividing plate is parallel with arbor,Height is parallel with fan diameter,By-pass air duct is separated into multiple slypes to core engine exhaust port side before fan,This passage is both by-pass air duct gas channel while and super burn gas channel,Along the straight line where the line at divider height midpoint, fagging foremost backward splits fagging and dividing plate before fan,Fagging and dividing plate section point-blank is in elongated hexagon,Front end is collectively forming air intake duct contraction section with air intake duct,The gas channel of middle equal thickness section is super burn air inlet distance piece and uiform section super burn bringing-up section,The divergent contour gas channel for the part formation that the thickness of rear end is gradually reduced is to wait static temperature super burn bringing-up section,There is depression on the crest top on the corrugated of two bringing-up sections,There is fuel injection aperture in depression,After-burner is exactly one section of isodiametric straight tube,Without flameholder and igniter,The rectangular in cross-section of adjustable convergence diffused jet pipe,Two pieces of adjustable plates that can be rolled over are placed on two faces relative in rectangular tube,There is approximate venturi when bending in adjustable plate,Adjustable plate abuts rectangular tube internal face during stretching, extension,It is parallel with internal face,Sectional area is equal with after-burner sectional area,Equipped with three triangle T tails in spout outside wall surface,The two horizontal tail wings are symmetrical,The one vertical fin wing is vertical with the line of the two horizontal tail wings,Three empennages are all hollow,Side towards spout jet direction is opening,And can 90 ° of deflection,Referred to as deflect spout,Deflection spout is communicated through empennage inner chamber with after-burner,At the front end of two horizontal tails on jet pipe shell it is each then one be folded to motor head forward direction conduction pipe,The outlet of pipeline front end be can do it is parallel with arbor or with arbor it is in 90 ° curve motion regurgitate/hang down the dual-purpose spout of spray,Rear end of pipeline is communicated with after-burner；The part behind the height deflector parallel with arbor with compressor impeller diameter parallel, width, the midpoint of width dimensions is uniform-distribution with one section of annular air-flow path before the entry of combustion chamber of core engine can turn back 80 ° to the left or to the right to stop when up to being hindered by adjacent deflector midpoint and with axial flow sealing；Blast pipe after core engine turbine is also rocket chamber, and nozzles with injector is constituted with rocket chamber when jet pipe adjustable plate stretches；From air inlet, every surface for having air-flow to flow through into the gas channel of nozzle is depression corrugated entirely to whole engine, fan and compressor are that have impeller internal channel to turning ripple leaf impeller, the blde pitch of fan is adjustable, and when stopping fan rotation but when having the air-flow to flow through, that the chord of foil of fan blade is approximate is parallel with arbor；Turbine is subsonic speed counter rotating turbine and with impeller internal channel, and arbor maintains static dynamic, and turbine is by being placed on arbor in tubular axial high-pressure compressor and the fan transimission power between compressor and turbine；Having on the crest summit on the depression corrugated that the high temperature gas flow of rocket chamber, after-burner and jet pipe passes through in the depression of small size, depression has low-temperature airflow jet apertures；The fuel supply pipe of engine has three groups, first group penetrated from engine housing after be passed through the inner chamber of fan rear bulkhead, sprayed from the aperture in the small size depression on the crest of super burn combustion chamber corrugated, second group penetrated from engine housing be then passed through by-pass air duct dividing plate inner chamber stretch into core engine combustion chamber from nozzle spray, 3rd group penetrates from engine housing and is then passed through by-pass air duct dividing plate inner chamber into being divided into two after core engine blast pipe, one extends the nozzle on fagging terminal edge from turbine rear stay plate backward, and another extends blast pipe end nozzle from exhaust wall inner chamber；The coolant circulation passage of engine is begun from air inlet front edge, cavity through air intake duct wall, fagging inner chamber before fan, inlet cone conical surface water jacket, inlet cone cone, pipeline before cone and fan wheel disc between fagging, fan internal channel, the pipeline being placed on arbor between fan wheel disc and high-pressure compressor wheel disc, high-pressure compressor impeller internal channel, combustion chamber water jacket, turbine wheel internal channel, turbine rear stay plate inner chamber, turbine rear exhaust tube wall inner chamber, by-pass air duct dividing plate end coolant channel, aperture during afterbunring locular wall inner chamber is recessed to after-burner internal face crest summit sprays, the outlet outflow that cooling agent is also stretched out outside engine casing from by-pass air duct dividing plate end coolant channel, through being drained into exporting the pipeline connected outside engine；The liquid oxygen supply of engine is passed through through pipeline from the end shell inner cavity of jet pipe, through afterbunring locular wall inner chamber, by-pass air duct dividing plate end coolant channel, turbine rear exhaust tube wall inner chamber to turbine rear stay plate end nozzle；The valve at entrance that afterbunring wall inner chamber is communicated with aperture in internal face crest summit depression, when cooling agent flows from front to back, valve is opened by fluid forces, coolant flow is to corrugated crest summit aperture, when liquid oxygen is from rear end flow forward, valve is promoted and closed by liquid oxygen stream again, and liquid oxygen will not be leaked into afterbunring room.

6. claim 1 is applied into airborne vehicle, referred to as ripple wing corrugated airborne vehicle, including ripple leaf whirlpool oar aircraft, ripple oar helicopter, ripple wing corrugated jet transport aircraft, ripple wing corrugated high-performance cruise guided missile, the jet-propelled war craft in ripple wing corrugated, ripple wing corrugated aerofoil profile aircraft, its common trait is：Machine (bullet) body outer surface is all depression corrugated, and machine (bullet) wing and empennage are all Waved wings, and its respective feature is：Ripple leaf whirlpool oar aircraft uses ripple leaf turboprop；Ripple oar helicopter hull is supersonic speed fuselage, the crest on the corrugated of the transparent part in fuselage outer surface especially makes of heat proof material, respectively there is a big hole in the middle of two aerofoil surfaces and circular hole occupies exhausted most area of wing, the multiple-blade propeller of ripple wing configuration is installed in wing circular hole, the diameter of propeller is parallel with wing chord, propeller rotational in two wings is in opposite direction, wing circular hole face suitable for reading is provided with bending plate, bending plate is integral with upper surface of the airfoil when stretching, in upper surface of the airfoil one triangular-section gas channel from front to back of formation when bending plate is bent, engine uses ripple leaf fanjet, engine is placed in above afterbody, power transmission shaft of the front axle of engine through the propeller in clutch band motivation wing circular hole, the empennage jet pipe of engine rear end controls the posture of aircraft；The value of the fuselage fineness ratio of ripple wing corrugated jet transport aircraft is larger, the crest of the transparent part of outer surface is made using exotic material, manned in cabin can pass through situation outside the gap observation machine of two crests, the wave height of wing front and rear edge is gradually reduced from wing root to wingtip, engine is used under ripple leaf turbofan/punching press combined engine, two wings each one at nearly wing root；The outer surface crest of ripple wing corrugated high-performance cruise guided missile and jet-propelled war craft is made using exotic material, wing front and rear edge wave height is gradually reduced from wing root to wingtip, empennage merges into a single whole with engine empennage spout, engine intake is below bomb body and fore-body, and engine uses ripple leaf turbofan/ultra-combustion ramjet/rocket composite rocket engine；The Waved wing and fuselage of ripple wing corrugated wing shaped airplane combine together, whole aircraft is as leaf, leading edge has three crests, middle crest wave height value is maximum, the crest wave height value on both sides is smaller and equal, two crests of trailing edge and wave height is equal, two vertical fins are placed at trailing edge crest above fuselage, using three Tai Boye turbofans/ultra-combustion ramjet/rocket composite rocket engine, one is placed on the line of leading edge intermediate peak summit and trailing edge trough bottom point and close to leading edge intermediate peak, another two are placed on the line on the trough bottom point of leading edge two and the crest summit of trailing edge two and close to trailing edge crest, previous engine does not need empennage spout, the empennage spout of two engines combines together with the vertical fin of fuselage trailing edge and crest edge afterwards, the crest on corrugated is made using exotic material.

7. claim 1 is applied into navigation device, referred to as corrugated ripple slurry navigation device, including corrugated Bo Jiang naval vessels, corrugated ripple slurry submarine, corrugated ripple slurry torpedo, its common trait is：Outer surface is all depression corrugated, and propeller blade is ripple leaf propeller using Waved wing configuration, and its respective feature is：The engine on naval vessel uses ripple leaf gas turbine；The thickness junction of submarine and torpedo body is raised corrugated, and high-speed torpedo uses rocket engine.

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