CN101514656A - Turbine combined pulse detonation engine - Google Patents
Turbine combined pulse detonation engine Download PDFInfo
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- CN101514656A CN101514656A CNA2009100217811A CN200910021781A CN101514656A CN 101514656 A CN101514656 A CN 101514656A CN A2009100217811 A CNA2009100217811 A CN A2009100217811A CN 200910021781 A CN200910021781 A CN 200910021781A CN 101514656 A CN101514656 A CN 101514656A
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Abstract
The invention discloses a turbine combined pulse detonation engine (PDE). An air inlet device is positioned at the front tip of an engine shell; a gas compressor is positioned at the lower reaches of the air inlet device and is coaxial with the air inlet device; the gas compressor is coaxial with a radial turbine; a flow-guide casing is a smooth transition case between the gas compressor and the radial turbine; a guider is positioned between the flow-guide casing and the radial turbine; an inlet valve is positioned between the flow-guide casing and the inner wall of the engine shell; a diffusion cushion chamber ranges from the lower reaches of the gas compressor to the upper reaches of the inlet valve; a multi-tube detonation chamber is positioned at the lower reaches of the inlet valve; the outer annular wall surface of the multi-tube detonation chamber is part of the engine shell and the inner annular wall surface forms an inner annular wall; an inner flow passage is positioned at the lower reaches of the radial turbine; an ignition system is an ignition device of the multi-tube detonation chamber and the exit of the multi-tube detonation chamber is connected with a nozzle. The PDE is no longer than the length corresponding to the maximum external profile diameter of the gas compressor, thus greatly reducing coupling of detonation circulation and turbine operation, having high working frequency and conducing to power extraction.
Description
Technical field
The present invention relates to technical field of engines, especially a kind of pulse-knocking engine.
Background technique
The discovery of detonation wave can trace back to for 18 end of the centurys the earliest, than deflagration wave, the pinking velocity of wave propagation can reach a few km per seconds, produce high gaseous-pressure (greater than 15 to 55 barometric pressure) and fuel gas temperature (greater than 2800K) simultaneously, according to traditional C J theory, the CJ point of detonation is the smallest point that entropy increases, this means that the propulsion system based on knocking combustion will have advantage very much on the efficiency of cycle, therefore from last century the forties begin, detonation engine is competitively studied by each mechanism, in the exploratory development stage of six more than ten years, various types of detonation engines occurred, the focus of current this area research mainly concentrates on based on pulse-knocking circuit pulse-knocking engine.
For pure pulse-knocking engine, it does not contain any rotatable parts, thus simple in structure, in light weight, but identical with traditional pressed engine be that it must utilize the speed punching press to realize the inflow of air, so motor can't start on ground.Start problem for solving ground, further improve the pulse-knocking engine propulsive performance, realize taking of power simultaneously, the turbine rotation parts have been introduced in the pulse-knocking engine, i.e. gas turbine pulse-knocking combined engine.For this combined engine structure, automobile is received the detonation tube outlet with turbosupercharger early than people such as John hoke in 2002, drive turbine with the knocking combustion ripple, and and then realize from air-breathing; U.S. GE company had proposed two kinds of patent schemes in 2005, and its common feature is that detonation tube and gas turbine are designed to one, by tangential exhaust gas drive turbine since detonation tube length by DDT apart from decision, so that its maximum shortcoming is exactly its turbine size is very big; The focus of current American GE company, University of Cincinnati and the research of Tokyo Polytechnics all is the combined engine scheme that axial flow turbine is placed the detonation tube outlet.
It is the stable state combustion mode that replaces existing gas turbine engine with knocking combustion that the turbine rotation parts are placed the original intention of detonation chamber outlet, thereby make things convenient for the transplanting of new technology, it has brought new problem but then: (1) will be longer than the available engine firing chamber by DDT apart from the detonation tube length of decision, so the distance between shafts between turbine and gas compressor will extend; (2) because there are the turbine rotation parts in the detonation chamber outlet, knocking combustion is to its acting the time, than no turbine part situation, the pinking work cycle is influenced by turbine also can, increase along with secondary speed, the coupling of pinking circulation and turbine work is strengthened, thereby but increase the complexity of pinking loop control and then reduce the detonation chamber frequency of okperation; (3) because the strong non-permanent characteristic of knocking combustion process, make turbine inlet pressure minimum and pressure maximum differ from 18 times than at least, this differential pressure changes at several milliseconds simultaneously, current turbine design method is difficult to guarantee the taking of power efficient under the pressure pulse effect in short-term of this high strength, actual measured value is all lower, more than these all are the problems that the turbine rotation parts place detonation chamber outlet scheme to solve.
Summary of the invention
In order to overcome the coupling influence of prior art taking of power parts and pinking work cycle, the present invention proposes and a kind of turbine is placed the detonation chamber head, utilize the passback pinking to drive the turbine combined pulse detonation engine of turbine, can realize that ground starts, reduces the engine charge resistance and realizes the motor miniaturization.
The technical solution adopted for the present invention to solve the technical problems is: comprise air inlet system 1, gas compressor, diffusion buffer cavity 3, radial turbine 4, guider, flow-guide casing 6, suction valve 7, ignition system 8, multitube detonation chamber 9, jet pipe 10, inner flow passage 11, motor body 12 and internal ring wall 14, airflow direction along motor, air inlet system 1 is positioned at motor body 12 foremost, gas compressor be positioned at motor body 12, air inlet system 1 downstream and with air inlet system 1 coaxial arrangement; Gas compressor and radial turbine 4 link to each other by common shaft, and the turbine disk of radial turbine 4 is in the upstream, and blade downstream; Flow-guide casing 6 is the housings that seamlessly transit of 4 of gas compressor and radial turbines, and bearing lubrication system, gear train assembly are packaged between gas compressor and the radial turbine 4; Guider is coaxial with radial turbine 4, between flow-guide casing 6 and radial turbine; Suction valve 7 is positioned at flow-guide casing 6 and motor body 12 inwalls surround the air flow path that forms, and between gas compressor and radial turbine 4 positions; Diffusion buffer cavity 3 starts from the gas compressor downstream, end at suction valve 7 upstreams, be the annular cavity that surrounds by flow-guide casing 6 and motor body 12, the minimum area of the airflow path that diffusion buffer cavity 3 discharge area should form greater than gas compressor and motor body 12 inwalls; Multitube detonation chamber 9 is in suction valve 7 downstreams, it is the knocking combustion zone of fuel/air mixture, constitute along the peripheral tubes annular spread by a plurality of independent detonation tubes, the outer shroud wall of this ring-type multitube detonation chamber 9 is a part motor body 12, its internal ring wall face constitutes internal ring wall 14, internal ring wall 14 should be greater than 1 times of born of the same parents' lattice size of the fuel/air mixture that adopts with the spacing of motor body 12, and internal ring wall 14 downstream end face and multitube detonation chamber 9 downstream end face are on same plane simultaneously; Ring-type multitube detonation chamber 9 is swum end face from it and is begun to have ring-like cavity at interior ring place, guider and radial turbine 4 are wrapped in this toroidal cavity, radial turbine 4 blades and internal ring wall 14 minimum separables are less than 1mm, and radial turbine 4 maximum external profile diameters are identical with internal ring wall 14 upstream face overall dimensionss; Radial turbine 4 downstreams are inner flow passage 11, and inner flow passage 11 is surrounded by internal ring wall 14 and forms, and insert in the guider internal ring wall 14 upstreams, and insertion depth is 0.2～0.6 times a guider axial length; Ignition system 8 is the ignition mechanism of multitube detonation chamber 9, the corresponding ignition system of detonation tube; 9 outlets of multitube detonation chamber connect jet pipe 10.
Gas compressor is a prior art, can adopt centrifugal-flow compressor 2a, also can be axial flow compressor 2b.
The annular cavity that diffusion buffer cavity 3 surrounds for gas compressor downstream, suction valve 7 upstreams, motor body 12 and flow-guide casing 6, can adopt that the design method of Diffuser designs before the existing aeroengine combustor buring chamber, it isolates the influence of downstream pressure pulsation to gas compressor simultaneously with the incoming flow pressurized air diffusion that further slows down.
Guider is the device that a kind of passback detonation wave that multitube detonation chamber 6 igniting backs are formed is introduced radial turbine 4, can adopt fixed guide or rotary steering device.Fixed guide 5a is made up of guide vane 5a1 and pedestal 5a2, and the rotary steering device is divided into two classes, and rotary steering device I type 5b is formed four annular cavities of balance runner in twos by four compartments, and has groove at its front-end face and interior ring; Rotary steering device II type 5c is made up of air inlet disk 5c1 and guide ring 5c2, and air inlet disk 5c1 is the hollow disk plate with slots, and guide ring 5c2 is the downstream that has the annulus of symmetrical guiding gutter and be positioned at guider 5c.
Flow-guide casing 6 is the housings that seamlessly transit of 4 of gas compressor and radial turbines, its upstream and gas compressor seamlessly transit, its downstream airflow runner minimum diameter was suitable when downstream end face size and detonation chamber 9 were in stowing operation, its smooth profile design can be gone into suction valve 7 with incoming flow pressurized air water conservancy diversion, reduces the air current flow loss.
After ignition system 8 igniting, in multitube detonation chamber 9, formed detonation wave of propagating to engine downstream and the passback detonation wave of upstream propagating, the detonation wave of propagates down stream is discharged motor through jet pipe 10; Upstream Hui Chuan detonation wave causes partial combustion product flow upstream, and introduces radial turbine 4 behind the guider water conservancy diversion, and drives radial turbine 4 rotations, and products of combustion enters inner flow passage 11 after flowing out radial turbine 4, and finally flows out motor; Radial turbine 4 is coaxial with gas compressor, the rotation of radial turbine 4 drive pressure mechanisms of qi, and further gas compressor compresses the incoming flow air, thus the ground of realizing pulse-knocking engine starts.
As first preferred version of the present invention, radial turbine 4 is connected with centrifugal-flow compressor 2a is coaxial, suction valve 7 places fixed guide 5a upstream face, guider 5a is made up of guide vane 5a1 and pedestal 5a2, pedestal 5a2 is fixed on flow-guide casing 6 downstream end face, guide vane 5a1 sweeps away trip, fixed guide 5a is coaxial with radial turbine 4, radial turbine 4 is wrapped in the fixed guide 5a, fixed guide 5a and radial turbine 4 are wrapped in the detonation chamber 9 upstream toroidal cavities simultaneously, fixed guide 5a upstream face and detonation chamber 9 upstream face are on same plane, and internal ring wall 14 inserts in the fixed guide 5a simultaneously.
As second preferred version of the present invention, radial turbine 4 is connected with centrifugal-flow compressor 2a is coaxial, remove the suction valve 7 in first preferred version, 5b places flow-guide casing 6 downstreams and coaxial with radial turbine 4 with rotary steering device I type, rotary steering device I type 5b forms an annular cavity by inside and outside ring, described cavity is formed four balance runners in twos by four compartments again, wherein shut with smooth guide face the upper-end surface of less two the symmetrical runners of area, and the whole arc section in downstream internal ring wall upper edge has the hole in its runner; The shaft driven gear transmission system 13 that connects radial turbine 4 and centrifugal-flow compressor 2a, and then rotary driving guider I type 5b; Diffusion buffer cavity 3 starts from the centrifugal-flow compressor downstream, ends at rotary steering device I type upstream.
As the 3rd preferred version of the present invention, rotary steering device I type 5b in second preferred version is replaced with rotary steering device II type 5c, rotary steering device II type 5c is made up of air inlet disk 5c1 and guide ring 5c2, air inlet disk 5c1 is a hollow disc, be positioned at the upstream of guider 5c, have symmetrical sector air inlet duct on it, guide ring 5c2 has the annulus of symmetrical guiding gutter for the air inlet disk downstream, and internal ring wall 14 inserts in the guide ring 5c.
As the 4th preferred version of the present invention, the centrifugal-flow compressor 2a in the above scheme can be replaced with axial-flow compressor 2b.
The invention has the beneficial effects as follows: because turbine part is placed the detonation chamber front end, distance between shafts between turbine and gas compressor is only determined by the bearing lubrication system of necessity and the bulk of gear train assembly, it far is shorter than the distance between shafts when placing detonation chamber between turbine and gas compressor no longer than the length of the maximum external profile diameter correspondence of gas compressor; On the other hand, when turbine part places the detonation chamber front end, the fresh turbine of can quick-fried mixing also not flowing through of filling, so the turbine high speed rotating is little to the influence of motor stowing operation, simultaneously behind the detonation chamber ignition and detonation, most of products of combustion is discharged through jet pipe 10 with the detonation wave of propagating to the detonation chamber afterbody, because the detonation chamber afterbody does not have turbine part, so the rotation of turbine is less to this exhaust process influence, so place detonation chamber afterbody scheme than turbine, this scheme can subtract the coupling of fall pinking circulation and turbine work greatly, has higher frequency of okperation, can be grafted directly among the present invention having pure pulse-knocking engine detonation chamber structure now, the performance characteristic of detonation chamber 9 and pure pulse-knocking engine detonation chamber structure are basic identical among the present invention who obtains like this; Theoretical and test shows, the detonation chamber head pressure peak value that the passback detonation wave produces is lower than detonation chamber outlet detonation wave pressure, but its pressure platform district head, so prolonged the time of combustion gas to the turbine effect, help the extraction of power, simultaneously if multitube detonation chamber 9 adopts the cross-ignition working method, when the total frequency of okperation of its multitube (equaling the single tube detonation frequency takes advantage of in the detonation tube number) when reaching 200Hz, turbine inlet can be realized the operating conditions of approximation steady state, the present invention simultaneously only utilizes part working medium to drive radial turbine 4, calculating shows, if radial turbine is realized blow down ratio 2, then only need 20%～30% of the total working medium of inflow engine is used for driving radial turbine 4, just can realize the pressure ratio of gas compressor 2～3.
The present invention is further described below in conjunction with drawings and Examples.
Description of drawings
Fig. 1 is a structural drawing of the present invention;
Among the figure, 1-air inlet system, 3-diffusion buffer cavity, 4-radial turbine, 6-flow-guide casing, 7-suction valve, 8-ignition system, 9-multitube detonation chamber, 10-jet pipe, 11-inner flow passage, 12-motor body, 14-internal ring wall.
Fig. 2 is the structural drawing and the fundamental diagram of the embodiment of the invention 1, wherein Fig. 2 (a) is the air flow path figure of multitube firing mode down-firing after-combustion simultaneously product, Fig. 2 (b) is the air flow path figure that multitube simultaneously can quick-fried mixture filling under the firing mode, Fig. 2 (c) is can quick-fried mixture filling under the multitube timesharing firing mode, the air flow path figure of products of combustion discharge process, Fig. 2 (d) is this structure A-A face sectional drawing, and Fig. 2 (e) is the structural drawing of fixed guide 5a;
Among the figure, 2a-centrifugal-flow compressor, 5a-fixed guide, 5a1-guide vane, 5a2-pedestal.
Fig. 3 is the structural drawing and the fundamental diagram of the embodiment of the invention 2, wherein Fig. 3 (a) is the air flow path figure that is in the detonation tube internal combustion product of igniting process in the multitube detonation chamber 9, Fig. 3 (b) be in the multitube detonation chamber 9 in the detonation tube of filling can quick-fried mixture air flow path figure, Fig. 3 (c) rotary steering device I type 5b structural drawing and air flow path figure;
Among the figure, 5b-rotary steering device I type, 13-gear train assembly.
Fig. 4 is the structural drawing and the fundamental diagram of the embodiment of the invention 3, wherein Fig. 4 (a) is the air flow path figure that this structure is in the detonation tube internal combustion product of igniting process, Fig. 4 (b) be this structure be in the detonation tube of filling can quick-fried mixture air flow path figure, Fig. 4 (c) rotary steering device II type 5c structural drawing and air flow path figure;
Among the figure, 5c-rotary steering device II type.
Fig. 5 is the structural drawing of the embodiment of the invention 4;
Among the figure, the 2b-axial flow compressor.
Embodiment
Embodiment 1:
As shown in Figure 2, comprise air inlet system 1, centrifugal-flow compressor 2a, diffusion buffer cavity 3, radial turbine 4, fixed guide 5a, flow-guide casing 6, suction valve 7, ignition system 8, multitube detonation chamber 9, jet pipe 10, inner flow passage 11, motor body 12 and internal ring wall 14.Along the airflow direction of motor, air inlet system 1 is positioned at motor body 12 foremost, centrifugal-flow compressor 2a be positioned at motor body 12, air inlet system 1 downstream and with air inlet system 1 coaxial arrangement; Centrifugal-flow compressor 2a and radial turbine 4 link to each other by common shaft, and the turbine disk of radial turbine 4 is in the upstream simultaneously, and its blade sweeps away trip; Flow-guide casing 6 is between centrifugal-flow compressor 2a and radial turbine 4, and its upstream face physical dimension is identical with centrifugal compressor 2a maximum outside dimension, and its downstream end face physical dimension is identical with the maximum physical dimension of fixed guide 5a; Fixed guide 5a is fixed in flow-guide casing 6 downstream end face and coaxial with radial turbine 4, radial turbine 4 is wrapped in the fixed guide 5a, Fig. 2 (e) is the structural drawing of fixed guide 5a, it is made up of 10 guide vane 5a1 and pedestal 5a2, guide vane 5a1 entrance face blade profile and detonation tube sidewall end face fit, promptly from the blast wave of one of them detonation tube forward pass only by the passage between two guide vane 5a1, guide vane 5a1 exit angle designs according to the exit angle of nozzle ring in the existing turbosupercharger, pedestal 5a2 outside dimension is greater than inner flow passage 11 upstream face internal diameters, determined to flow into the working medium flow of radial turbine 4, its parameter is determined according to the work design point of motor, fixed guide 5a is fixed on flow-guide casing 6 downstream end face by pedestal 5a2 with the screw link, and guide vane 5a1 sweeps away trip; Suction valve 7 is positioned at flow-guide casing 6 and motor body 12 inwalls surround the air flow path that forms, and between gas compressor and radial turbine 4 positions; Diffusion buffer cavity 3 starts from centrifugal-flow compressor 2a downstream, end at suction valve 7 upstreams, the annular cavity that surrounds by flow-guide casing 6 and motor body 12, and the minimum area of the airflow path that forms greater than gas compressor and motor body 12 inwalls of diffusion buffer cavity 3 discharge area; Multitube detonation chamber 9 is in suction valve 7 downstreams, it is made of along the peripheral tubes annular spread a plurality of independent detonation tubes, Fig. 2 (d) is the sectional view in A-A cross section among Fig. 2 (b), radial turbine does not draw among the figure, can see that the multitube detonation chamber 9 among the embodiment 1 is made up of 10 covering of the fan detonation tubes, the outer shroud wall of this ring-type multitube detonation chamber 9 is a part motor body 12, and its internal ring wall face constitutes internal ring wall 14; Internal ring wall 14 and the 1 times born of the same parents lattice size of motor body 12 spacings greater than the fuel/air mixture that adopts, internal ring wall 14 downstream end face and multitube detonation chamber 9 downstream end face are on same plane simultaneously; Ring-type multitube detonation chamber 9 is swum end face from it and is begun to have ring-like cavity at interior ring place, fixed guide 5a and radial turbine 4 are wrapped in this toroidal cavity, fixed guide 5a upstream face and detonation chamber 9 upstream face are on same plane, internal ring wall 14 inserts in the fixed guide 5a simultaneously, the beeline of internal ring wall 14 to guide vane 5a1 is less than 1mm, the blade beeline of guide vane 5a1 and radial turbine 4 is less than 1cm, radial turbine 4 blades and internal ring wall 14 minimum separables are less than 1mm, and radial turbine 4 maximum external profile diameters are identical with internal ring wall 14 upstream face overall dimensionss; Ignition system 8 is a plug ignition, and the spark plug sparking electrode places in the multitube detonation chamber 9, the corresponding spark plug of detonation chamber; 9 outlets of multitube detonation chamber connect jet pipe 10; Spacing between fixed guide 5a outer rim and motor body 12 inwalls also should comprise one section multitube detonation chamber 9 greater than 1 times of born of the same parents' lattice size of the fuel/air mixture that adopts in this spacing, prolonging axial whole detonation chamber is uniform section or flaring.
Embodiment 2:
As shown in Figure 3, it is made up of air inlet system 1, centrifugal-flow compressor 2a, diffusion buffer cavity 3, radial turbine 4, rotary steering device I type 5b, flow-guide casing 6, ignition system 8, multitube detonation chamber 9, jet pipe 10, inner flow passage 11, motor body 12, gear train assembly 13.Along the airflow direction of motor, air inlet system 1 is positioned at motor body 12 foremost, centrifugal-flow compressor 2a be positioned at motor body 12, air inlet system 1 downstream and with air inlet system 1 coaxial arrangement; Centrifugal-flow compressor 2a and radial turbine 4 link to each other by common shaft, and the turbine disk of radial turbine 4 is in the upstream simultaneously, and its blade sweeps away trip; Flow-guide casing 6 is between centrifugal-flow compressor 2a and rotary steering device I type 5b, and its upstream face physical dimension is suitable with centrifugal compressor 2a maximum outside dimension, and its downstream end face physical dimension is suitable with radial turbine 4 maximum outside dimension; Rotary steering device I type 5b is positioned at flow-guide casing 6 downstreams and coaxial with radial turbine 4, radial turbine 4 is wrapped in rotary steering device I type 5b inside, the shaft driven gear transmission system 13 that connects radial turbine 4 and centrifugal-flow compressor 2a, and then driving guider 5b, guider 5b structure is shown in Fig. 3 (c), it forms an annular cavity by inside and outside ring, described cavity is formed four balance runners in twos by four compartments again, area between asymmetric runner is than between 0.1-0.5, wherein shut with smooth guide face the upper-end surface of less two the symmetrical runners of area, and the whole arc section in downstream internal ring wall upper edge has the hole in its runner, perforate length along axial direction is suitable with radial turbine 4 outer rim place length of blade, ring and internal ring wall 14 spacings are less than 1mm in the guider 5b downstream, internal ring wall 14 inserts in the guider 5b, guider 5b outer shroud and motor body 12 spacings are less than 1mm, and present embodiment motor outside dimension is less than embodiment 1; Diffusion buffer cavity 3 starts from centrifugal-flow compressor 2a downstream, end at rotary steering device 5b upstream, the annular cavity that surrounds by flow-guide casing 6 and motor body 12, and the minimum area of the airflow path that forms greater than gas compressor and motor body 12 inwalls of diffusion buffer cavity 3 discharge area; Multitube detonation chamber 9 is positioned at air inlet rotary steering device 5b downstream, and 9 outlets of multitube detonation chamber connect jet pipe 10; Ignition system 8 is a plug ignition, and the spark plug sparking electrode places in the multitube detonation chamber 9, the corresponding spark plug of detonation chamber; Inner flow passage 11 is surrounded by the internal ring wall 14 of the multitube detonation chamber 9 of annular distribution, and inner flow passage 11 upstreams are radial turbine 4, and radial turbine 4 blades and internal ring wall 14 minimum separables are less than 1mm, and radial turbine 4 maximum outside diameters are suitable with inner flow passage 11 maximum inner diameters.Compared to embodiment 1, this structure is complicated, it is two rotation systems (compressor wheel rotates with air inlet rotary steering device 5b and rotates), because the control of embodiment 2 work schedule realizes by rotation air inlet rotary steering device 5b, so at one time, part detonation tube in the multitube detonation chamber 9 is in the spark knock process, shown in Fig. 3 (a), and the part detonation tube is in the mixture stowing operation shown in Fig. 3 (b): for the detonation tube that is in the spark knock process (Fig. 3 (a)), because the effect of rotary steering device I type 5b, 3 obstructs of this detonation tube and diffusion buffer cavity, but be connected with radial turbine 4, so back, igniting back propagation of explosion seismic wave is discharged by engine jet pipe 10, the passback detonation wave is introduced radial turbine 4 through guider 5b, and and then drive radial turbine 4, the final inner flow passage 11 that flows into, radial turbine 4 drives centrifugal-flow compressor 2a, centrifugal-flow compressor 2a is with the incoming flow air compression, and then inflow diffusion buffer cavity 3, because the detonation tube that is in igniting is subjected to seal guider 5b with 3 of diffusion buffer cavitys and intercepts, other treat the filling detonation tube diffusion buffer cavity 3 inflows that the air that is intercepted will be by annular; For the detonation tube that is in the mixture stowing operation, guider 5b intercepts detonation tube and radial turbine 4, with detonation tube and 3 conductings of diffusion buffer cavity, can be quick-fried mixed air to open beginning filling detonation tube, and the products of combustion that motor inner flow passage 11 is still flowing and discharged through radial turbine 4 by the detonation tube that is in the spark knock process.
Embodiment 3:
As shown in Figure 4, it is made up of air inlet system 1, centrifugal-flow compressor 2a, diffusion buffer cavity 3, radial turbine 4, rotary steering device II type 5c, flow-guide casing 6, ignition system 8, multitube detonation chamber 9, jet pipe 10, inner flow passage 11, motor body 12, gear train assembly 13.Along the airflow direction of motor, air inlet system 1 is positioned at motor body 12 foremost, centrifugal-flow compressor 2a be positioned at motor body 12, air inlet system 1 downstream and with air inlet system 1 coaxial arrangement; Centrifugal-flow compressor 2a and radial turbine 4 link to each other by common shaft, and the turbine disk of radial turbine 4 is in the upstream simultaneously, and its blade sweeps away trip; Flow-guide casing 6 is between centrifugal-flow compressor 2a and rotary steering device I type 5b, and its upstream face physical dimension is suitable with centrifugal compressor 2a maximum outside dimension, and its downstream end face physical dimension is suitable with radial turbine 4 maximum outside dimension; Rotary steering device II type 5c is positioned at flow-guide casing 6 downstreams and coaxial with radial turbine 4, radial turbine 4 is wrapped in rotary steering device II type 5c inside, the shaft driven gear transmission system 13 that connects radial turbine 4 and centrifugal-flow compressor 2a, and then driving guider 5c, rotary steering device II type 5c structure is shown in Fig. 4 (c), it is made up of air inlet disk 5c1 and guide ring 5c2, air inlet disk 5c1 is a hollow disc, be positioned at the upstream of guider 5c, have symmetrical sector air inlet duct on it, to realize mixture filling to multitube detonation chamber 9, its fluting area and the area of not slotting are than between 2-10, guide ring 5c2 is the annulus that has symmetrical guiding gutter, with with multitube detonation chamber 9 and radial turbine 4 conductings, the guiding gutter along the circumferential direction angle of circumference of perforate sector correspondence is suitable with the not perforate sector corresponding circle round angle on the air inlet disk 5c1, phase difference between the not perforate sector circumferential phase of living on guiding gutter perforate sector circumferential phase of living in and the air inlet disk 5c1 is within positive and negative 10 degree, guide ring 5c2 and internal ring wall 14 spacings are less than 1mm, internal ring wall 14 inserts in the guide ring 5c2, and guide ring 5c2 outer rim and motor body 12 spacings are less than 1mm; Diffusion buffer cavity 3 starts from centrifugal-flow compressor 2a downstream, end at rotary steering device II type 5c upstream, the annular cavity that surrounds by flow-guide casing 6 and motor body 12, and the minimum area of the airflow path that forms greater than gas compressor and motor body 12 inwalls of diffusion buffer cavity 3 discharge area; Multitube detonation chamber 9 is positioned at air inlet disk 5c1 downstream end face, and its upstream head leaves ring-like cavity, is rotated so that bad 5c2 of water conservancy diversion inserts in multitube detonation chamber 9 heads, and 9 outlets of multitube detonation chamber connect jet pipe 10; Ignition system 8 is a plug ignition, and the spark plug sparking electrode places in the multitube detonation chamber 9, the corresponding spark plug of detonation chamber; Inner flow passage 11 is surrounded by the internal ring wall 14 of the multitube detonation chamber 9 of annular distribution, and inner flow passage 11 upstreams are radial turbine 4, and radial turbine 4 blades and internal ring wall 14 minimum separables are less than 1mm, and radial turbine 4 maximum outside diameters are suitable with inner flow passage 11 maximum inner diameters.
Embodiment 4:
As shown in Figure 5, comprise air inlet system 1, axial flow compressor 2b, diffusion buffer cavity 3, radial turbine 4, fixed guide 5a, flow-guide casing 6, suction valve 7, ignition system 8, multitube detonation chamber 9, jet pipe 10, inner flow passage 11, motor body 12 and internal ring wall 14.Along the airflow direction of motor, air inlet system 1 is positioned at motor body 12 foremost, axial flow compressor 2b be positioned at motor body 12, air inlet system 1 downstream and with air inlet system 1 coaxial arrangement; Axial flow compressor 2b and radial turbine 4 link to each other by common shaft, and the turbine disk of radial turbine 4 is in the upstream simultaneously, and its blade sweeps away trip; Flow-guide casing 6 is between axial flow compressor 2b and radial turbine 4, and the blade root of its upstream face physical dimension and axial flow compressor 2a blade place circumferential size is suitable, and the maximum physical dimension of its downstream end face physical dimension and fixed guide 5a is suitable; Fixed guide 5a is fixed in flow-guide casing 6 downstream end face, coaxial with radial turbine 4, Fig. 2 (e) is the structural drawing of fixed guide 5a, and suction valve 7 is positioned at flow-guide casing 6 and motor body 12 inwalls surround the air flow path that forms, and between gas compressor and radial turbine 4 positions; Diffusion buffer cavity 3 starts from centrifugal-flow compressor 2a downstream, end at suction valve 7 upstreams, the annular cavity that surrounds by flow-guide casing 6 and motor body 12, and the minimum area of the airflow path that forms greater than gas compressor and motor body 12 inwalls of diffusion buffer cavity 3 discharge area; Multitube detonation chamber 9 is made of along the peripheral tubes annular spread a plurality of independent detonation tubes in suction valve 7 downstreams, and the outer shroud wall of this ring-type multitube detonation chamber 9 is a part motor body 12, and its internal ring wall face constitutes internal ring wall 14; Ring-type multitube detonation chamber 9 is swum end face from it and is begun to have ring-like cavity at interior ring place, fixed guide 5a and radial turbine 4 are wrapped in this toroidal cavity, fixed guide 5a upstream face and detonation chamber 9 upstream face are on same plane, and internal ring wall 14 inserts in the fixed guide 5a simultaneously; Ignition system 8 is a plug ignition, and the spark plug sparking electrode places in the multitube detonation chamber 9, the corresponding spark plug of detonation chamber; 9 outlets of multitube detonation chamber connect jet pipe 10.
Claims (5)
1, a kind of turbine combined pulse detonation engine, comprise air inlet system, gas compressor, diffusion buffer cavity, radial turbine, guider, flow-guide casing, suction valve, ignition system, multitube detonation chamber, jet pipe, inner flow passage, motor body and internal ring wall, it is characterized in that: along the airflow direction of motor, air inlet system is positioned at motor body foremost, gas compressor be positioned at motor body, air inlet system downstream and with the air inlet system coaxial arrangement; Gas compressor links to each other by common shaft with radial turbine, and the turbine disk of radial turbine is in the upstream, and blade downstream; Flow-guide casing is the housing that seamlessly transits between gas compressor and radial turbine; Guider is coaxial with radial turbine, between flow-guide casing and radial turbine; Suction valve is positioned at flow-guide casing and the motor body inwall surrounds the air flow path that forms, and between gas compressor and radial turbine position; The diffusion buffer cavity starts from the gas compressor downstream, ends at the suction valve upstream, is the annular cavity that is surrounded by flow-guide casing and motor body, the minimum area of the airflow path that diffusion buffer cavity discharge area should form greater than gas compressor and motor body inwall; The multitube detonation chamber is in the suction valve downstream, constitute along the peripheral tubes annular spread by a plurality of independent detonation tubes, the outer shroud wall of this ring-type multitube detonation chamber is the part motor body, its internal ring wall face constitutes internal ring wall, the spacing of internal ring wall and motor body should be greater than 1 times of born of the same parents' lattice size of the fuel/air mixture that adopts, and internal ring wall downstream end face and multitube detonation chamber downstream end face are on same plane simultaneously; Ring-type multitube detonation chamber is swum end face from it and is begun to have ring-like cavity at interior ring place, guider and radial turbine are wrapped in this toroidal cavity, radial turbine blade and internal ring wall minimum separable are less than 1mm, and the maximum external profile diameter of radial turbine is identical with internal ring wall upstream face overall dimensions; The radial turbine downstream is an inner flow passage, and inner flow passage is surrounded by internal ring wall and forms, and insert in the guider internal ring wall upstream, and insertion depth is 0.2～0.6 times a guider axial length; Ignition system is the ignition mechanism of multitube detonation chamber, the corresponding ignition system of detonation tube; The outlet of multitube detonation chamber connects jet pipe.
2, a kind of turbine combined pulse detonation engine according to claim 1, it is characterized in that: described gas compressor adopts centrifugal-flow compressor, guider adopts fixed guide, fixed guide is made up of guide vane and pedestal, pedestal is fixed on the flow-guide casing downstream end face, and guide vane sweeps away trip.
3, a kind of turbine combined pulse detonation engine according to claim 1, it is characterized in that: described gas compressor adopts centrifugal-flow compressor, remove suction valve, guider adopts rotary steering device I type, rotary steering device I type is to form an annular cavity by inside and outside ring, described cavity is formed four balance runners in twos by four compartments again, wherein shut with smooth guide face the upper-end surface of less two the symmetrical runners of area, and the whole arc section in downstream internal ring wall upper edge has the hole in its runner; The shaft driven gear transmission system that connects radial turbine and centrifugal-flow compressor, and then rotary driving guider I type; Diffusion buffer cavity 3 starts from the centrifugal-flow compressor downstream, ends at rotary steering device I type upstream.
4, a kind of turbine combined pulse detonation engine according to claim 3, it is characterized in that: described guider adopts rotary steering device II type, rotary steering device II type is made up of air inlet disk and guide ring, air inlet disk is a hollow disc, be positioned at the upstream of guider, have symmetrical sector air inlet duct on it, guide ring has the annulus of symmetrical guiding gutter for the air inlet disk downstream, and internal ring wall inserts in the guide ring.
5, according to any described a kind of turbine combined pulse detonation engine in the claim 1～4, it is characterized in that: described gas compressor adopts axial-flow compressor.
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| CN110207801A (en) * | 2019-05-14 | 2019-09-06 | 西北工业大学 | Detonation wave three-dimensional structure reconstructing system based on Shadow Techniques |
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