CN104153884B - A kind of rotation pinking gas turbine - Google Patents
A kind of rotation pinking gas turbine Download PDFInfo
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- CN104153884B CN104153884B CN201410384377.1A CN201410384377A CN104153884B CN 104153884 B CN104153884 B CN 104153884B CN 201410384377 A CN201410384377 A CN 201410384377A CN 104153884 B CN104153884 B CN 104153884B
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Abstract
The invention discloses a kind of rotation pinking gas turbine, comprise the intake duct, diffuser and the gas storage chamber that connect successively from left to right, gas compressor is arranged on the downstream of intake duct; Rotate the right-hand member that detonation combustor is positioned at gas storage chamber, the right-hand member rotating detonation combustor is connected with blending room, turbine and outlet pipe in turn, rotate detonation combustor left side annular spaced set and have multiple nozzle, be evenly arranged six spark plugs in the circumference rotating detonation combustor; Single-nozzle is equipped with air passageways and fuel channel, gas storage chamber is connected with rotation detonation combustor by the air passageways of supply air line and some nozzles successively, and blending room is connected by venting bypass and gas storage chamber; Rotor is arranged at the center of gas compressor and turbine, and be connected with turbine and gas turbine static load parts casing by turbine turns parts gas compressor by two bearings, one end of rotor is drawn from outlet pipe.During use, the Outlet of rotor is connected with generator assembly by speed changer.
Description
[technical field]
The present invention relates to a kind of gas turbine, particularly a kind of naval vessel and industrial rotation pinking gas turbine.
[background technique]
Burning is the requisite key link of fuel energy release in gas turbine, and burning has various ways, and the characteristic propagated voluntarily by flame and mode can be divided into deflagration and knocking combustion two class.Deflagration burning makes unburned mixture temperature raise (or due to thermodiffusion and thermal radiation effect free atom, free radicals are delivered in unburned mixture and produce chain reaction) by heat transfer and the reaction that causes is accelerated, thus flame front is constantly advanced in unburned mixture body, deflagration flame of combustion face is commonly called deflagration ripple, due to the restriction by deflagration combustion temperature transfer mode, deflagration velocity of wave propagation is lower, is generally about several meters to tens metre per second (m/s)s.Different from deflagration combustion process, knocking combustion process is very fast, can produce supersonic combustion ripple, i.e. detonation wave.Pinking wave propagation by shock wave to can pinking mixture successively intense impact compression make its occur high-speed chemical reaction realize, therefore can think that detonation wave is the strong shock of Coupled with Chemical Reaction.Pinking velocity of wave propagation is far longer than deflagration velocity of wave propagation, generally 10
3m/s magnitude.Compared with burning with deflagration, knocking combustion has from supercharging, flame propagation speed, the advantage such as combustion efficiency is high, pollutant emission is low.
Pulse detonation combustion is knocking combustion technology the most ripe at present, but from present Research, because pulse detonation combustion adopts step working method, need repeatedly ignition and detonation, and frequency of okperation is difficult to significantly improve, the average energy discharge of rate of power plant is less, causes engineer applied to be obstructed.Compared with pulse detonation combustion, rotating knocking combustion only needs once detonation, and propellant agent just can knocking combustion continuously, solves the difficult problem that high frequency repeats to detonate.In addition compared with the frequency of okperation of pulse detonation combustion, rotate knocking combustion very high at burner's working frequency of power plant inside, firing chamber is similar to quasi-steady operation state, be more conducive to, based on the turbomachinery taking of power of stable state incoming flow assumed condition design, make power system output power more stable.
Current naval vessel and industrial gas turbine all adopt the mode of deflagration isobaric combustion to discharge fuel heat, and temperature before the raising need continuous increase turbine of its thermal efficiency of cycle, suitably improves compressor pressure ratio simultaneously.Gas turbine based on isobaric combustion now mainly faces following problem: 1) adopt lean combustion premix combustion with reduced pollutants technology to cause combustion chambers burn region of stability narrow, easily stop working; 2) firing chamber control system is complicated, and frequently need carry out firing optimization; 3) on existing basis, improve compressor pressure ratio further, the design difficulty of gas compressor is very large; 4) in order to fully extract the energy in high temperature, high-pressure gas, high pressure ratio gas turbine needs when not increasing turbine progression to adopt large enthalpy drop turbine blade designing technique, but the energy loss problem of large enthalpy drop turbine blade fails to be well solved always.
[summary of the invention]
The object of the invention is to solve combustion chambers burn region of stability existing for existing naval vessel and industrial gas turbine narrow, easily flame-out, combustion control system is complicated and frequently need carry out the problems such as firing optimization, propose a kind ofly to rotate pinking gas turbine.Its firing chamber adopted is a kind of new combustion chamber based on knocking combustion, and structure is simple, and combustion flame is with Supersonic transport, fuel energy rate of release is fast, combustion efficiency is high, there is not combustion stability and flame-out problem, does not need to carry out combustion adjustment test to firing chamber.And knocking combustion process has from supercharging feature, avoiding high pressure ratio gas compressor design challenges, gas compressor progression can be reduced simultaneously, reduce power input to compressor, increasing the air horsepower output quantity of gas turbine for generating electricity or drive, improve effective utilization rate of energy.In addition because knocking combustion is similar to isochoric combustion, from thermodynamic cycle angle analysis, more isobaric circulation is advantageously in performance for pinking cycle power device.
For achieving the above object, the present invention adopts following technological scheme:
A kind of rotation pinking gas turbine, comprise the intake duct, diffuser and the gas storage chamber that connect successively from left to right, gas compressor is arranged on the downstream of intake duct; Rotate the right-hand member that detonation combustor is positioned at gas storage chamber, the right-hand member rotating detonation combustor is connected with blending room, turbine and outlet pipe in turn, rotate detonation combustor left side annular spaced set and have multiple nozzle, be evenly arranged six spark plugs in the circumference rotating detonation combustor; Single-nozzle is equipped with air passageways and fuel channel, gas storage chamber is connected with rotation detonation combustor by the air passageways of supply air line and some nozzles successively, and blending room is connected by venting bypass and gas storage chamber; Rotor is arranged at the center of gas compressor and turbine, and be connected with turbine and gas turbine static load parts casing by turbine turns parts gas compressor by two bearings, one end of rotor is drawn from outlet pipe.
The present invention improves further and is, the Outlet of rotor is connected with generator assembly by speed changer.
The present invention improves further and is, is provided with guide vane in the ingress of gas storage chamber, and the current path between guide vane is expansion shape passage.
The present invention improves further and is, diffuser is an expansion annular pass, and the subsonic flow of blower outlet slows down supercharging behind expansion annular pass.
The present invention improves further and is, gas storage chamber is first-class cross sectional annular cavity, and its slenderness ratio is 0.1 ~ 0.2, and volume is 8 ~ 10 times that rotate detonation combustor; Blending room is a convergence annular pass, and cooling-air and High Temperature High Pressure pinking combustion gas are in the indoor evenly blending of blending and speedup step-down.
The present invention improves further and is, the end of supply air line is a hemispherical dome structure, and on this hemispherical dome structure, be evenly provided with multiple points of gas manifolds, and a point gas manifold is connected with the air passageways of nozzle; Air flow meter and air flow rate adjustment valve is provided with in supply air line.
The present invention improves further and is, is provided with the solenoid valve controlling its switch in venting bypass.
The present invention improves further and is, nozzle comprises nozzle body and is arranged at the nozzle outer shroud of nozzle body circumference, nozzle outer shroud is a hollow right circular cylinder structure, nozzle body is a cylindrical structure, its end is half spherical cambered surface, and nozzle outer shroud circumferentially can rotate around nozzle center's axle, nozzle body is equidistantly respectively provided with three row's nozzle body air holes and nozzle outer shroud air hole with the corresponding position of the circumference of nozzle outer shroud becoming four of 90 degree of spacing regions; Fuel channel is positioned at the center of nozzle body, and some air passagewayss circumferentially in the left side of nozzle body, and are connected with the annular housing air flow path of nozzle body inside.
The present invention improves further and is, rotating detonation combustor is first-class cross sectional annular firing chamber, it combustion chamber flame drum comprising combustion box and set within it, combustion chamber flame drum is divided into premixing chamber and detonation chamber by annular spray structure, and six spark plug circumferences are evenly arranged in detonation chamber one end near annular spray structure, No. I baffle chamber that detonates, No. II baffle chamber that detonates, No. III baffle chamber that detonates, No. IV baffle chamber that detonates, No. V detonate baffle chamber and No. VI baffle chamber that detonates circumferentially evenly are arranged between combustion box and combustion chamber flame drum, telescopic No. I dividing plate that detonates, No. II dividing plate that detonates, No. III dividing plate that detonates, No. IV dividing plate that detonates, detonation chamber is evenly divided between six annuluses by No. V detonate dividing plate and No. VI dividing plate that detonates, wherein, No. I dividing plate that detonates, No. II dividing plate that detonates, No. III dividing plate that detonates, No. IV dividing plate that detonates, No. V detonate dividing plate and No. VI detonate dividing plate respectively with No. I baffle chamber that detonates, No. II baffle chamber that detonates, No. III baffle chamber that detonates, No. IV baffle chamber that detonates, No. V detonate baffle chamber and No. VI baffle chamber that detonates corresponding,
Multiple nozzle is circumferentially evenly arranged in premixing chamber's head, by nozzle, combustion chamber flame drum is fixed on combustion box, between combustion box and combustion chamber flame drum, form annular cooling channel simultaneously, wherein, annular spray structure is an intensive fine-porous toroidal membrane, and its aperture is less than 2mm.
The present invention improves further and is, turbine comprises the first order turbine, second level turbine and the third level turbine that set gradually from left to right, and wherein, first order turbine adopts impulse turbine, and without turbine stator blade, second level turbine and third level turbine all adopt anti-force type turbine.
Compare with industrial gas turbine with existing naval vessel, the present invention rotates detonation combustor, and its structure is simple, is first-class cross sectional annular firing chamber, without the need to the gaseous film control structure of complexity; Because rotation knocking combustion has the advantage from supercharging, after the present invention adopts rotation detonation combustor to replace traditional constant-pressure combustion chamber, gas turbine can reduce gas compressor progression, avoid the design challenges of high pressure ratio gas compressor, gas compressor compression work can be reduced simultaneously, increase for generating electricity or driving the ratio of acting in turbine output shaft power, and then improve the thermal efficiency of cycle of gas turbine; Rotate knocking combustion flame propagation speed, generally 10 simultaneously
3m/s magnitude, in firing chamber, ignition mixture burns instantaneously heat release under the effect of knocking combustion ripple, combustion efficiency is high and there is not combustion stability and easily flame-out problem, therefore the problems such as combustion with reduced pollutants technology after-burner flameholding regions such as adopting lean fuel premixed combustion narrows and easily stops working can be solved in existing gas turbine, and then the combustion control system of gas turbine can be reduced, and the test procedure of in existing gas turbine, firing chamber being carried out to firing optimization can be saved; This external cause knocking combustion is similar to isochoric combustion, and more isobaric circulation is advantageously in performance for pinking cycle power device.
[accompanying drawing explanation]
Fig. 1 is that the present invention rotates the overall pie graph of pinking gas turbine;
Fig. 2 a is the structure diagram of the rotation detonation combustor of the gas turbine shown in Fig. 1, and Fig. 2 b is the A-A direction view of Fig. 2 a;
Fig. 3 a is the nozzle arrangements sketch of the gas turbine shown in Fig. 1, and Fig. 3 b is the A-A direction view of Fig. 3 a;
Fig. 4 is the nozzle three-dimensional views shown in Fig. 3;
Fig. 5 is that the present invention rotates detonation combustor combustion mode one and starts schematic diagram;
Fig. 6 is that the present invention rotates detonation combustor combustion mode two and starts schematic diagram;
Fig. 7 is that the present invention rotates detonation combustor combustion mode three and starts schematic diagram.
Wherein: 1, intake duct; 2, gas compressor; 3, diffuser; 4, gas storage chamber; 5, supply air line; 6, solenoid valve; 7, venting bypass; 8, detonation combustor is rotated; 9, blending room; 10, turbine; 11, outlet pipe; 12, gas working medium stream; 13, speed changer; 14, generator assembly; 15, bearing; 16, gas manifold is divided; 17, Air flow meter; 18, nozzle; 19, air flow rate adjustment valve; 20, guide vane; 21, rotor; 22, No. I baffle chamber that detonates; 23, No. I dividing plate that detonates; 24, No. II baffle chamber that detonates; 25, No. II dividing plate that detonates; 26, spark plug; 27, No. III baffle chamber that detonates; 28, No. III dividing plate that detonates; 29, No. IV dividing plate that detonates; 30, No. IV baffle chamber that detonates; 31, No. V dividing plate that detonates; 32, No. V baffle chamber that detonates; 33, annular spray structure; 34, No. VI baffle chamber that detonates; 35, No. VI dividing plate that detonates; 36, combustion box; 37, combustion chamber flame drum; 38, cooling channel; 39, detonation chamber; 40, premixing chamber; 41, nozzle outer shroud; 42, nozzle outer shroud air hole; 43, nozzle body air hole; 44, nozzle body; 45, fuel orifice; 46, oxidation air spray-hole; 47, air passageways; 48, fuel channel.
[embodiment]
Below in conjunction with accompanying drawing, the present invention is described in further detail.
See Fig. 1, the present invention's one rotates pinking gas turbine, and comprise the intake duct 1, diffuser 3 and the gas storage chamber 4 that connect successively from left to right, gas compressor 2 is arranged on the downstream of intake duct 1; Rotate the right-hand member that detonation combustor 8 is positioned at gas storage chamber 4, the right-hand member rotating detonation combustor 8 is connected with blending room 9, turbine 10 and outlet pipe 11 in turn, rotate detonation combustor 8 left side annular spaced set and have multiple nozzle 18, be evenly arranged six spark plugs 26 in the circumference rotating detonation combustor 8; Single-nozzle is equipped with air passageways 47 and fuel channel 48, gas storage chamber 4 is connected with rotation detonation combustor 8 by the air passageways 47 of supply air line 5 and some nozzles 18 successively, and blending room 9 is connected with gas storage chamber 4 by venting bypass 7; Rotor 21 is arranged at the center of gas compressor 2 and turbine 10, and be connected with turbine 10 and gas turbine static load parts casing by turbine turns parts gas compressor 2 by two bearings 15, one end of rotor 21 is drawn from outlet pipe 11.The Outlet of rotor 21 is connected with generator assembly 14 by speed changer 13.The present invention is formed as shown by the arrows in Figure 1 by their gas working medium stream 12.
Further, have from supercharging advantage owing to rotating knocking combustion, in the present invention, the progression of gas compressor 2 is few compared with conventional gas turbine, is 2 to 3 grades; Diffuser 3 is positioned at gas compressor 2 downstream, and it to slow down supercharging for expansion shape annular pass, the subsonic flow that gas compressor 2 exports behind expansion annular pass; Gas storage chamber 4 is positioned at the downstream of diffuser 3, its volume is 8 ~ 10 times that rotate detonation combustor, for shortening the length dimension of gas turbine complete machine, gas storage chamber 4 is designed to the short annular housing that slenderness ratio is 0.1 ~ 0.2, for reducing compressed-air actuated flow losses, be provided with guide vane 20 at the entrance of gas storage chamber 4, the current path between guide vane 20 is designed to expansion shape passage; The end of supply air line 5 is half spherical cambered surface structure, and be designed with multiple points of gas manifolds 16 thereon, each point of gas manifold 16 is connected with the air passageways 47 on nozzle 18, Air flow meter 17 and air flow rate adjustment valve 19 are installed on supply air line simultaneously, can accurately control air mass flow size and realize compressed-air actuated real-time distribution, to meet the air flow demand of the various mode of operation of gas turbine under different load; Keep to the side in gas storage chamber 4 right circular space position circumferentially uniform Design have venting bypass 7, venting bypass 7 is directly communicated with gas storage chamber 4 and blending room 9, to be exitted the switch of bypass by solenoid valve 6 control in venting bypass 7.
Ring rotation detonation combustor 8 is positioned at the downstream of gas turbine gas storage chamber 4, Fig. 2 a and Fig. 2 b is the structure diagram rotating knocking combustion 8 Room, it is first-class cross sectional annular firing chamber, the combustion chamber flame drum 37 comprising combustion box 36 and set within it, combustion chamber flame drum 37 is divided into premixing chamber 40 and detonation chamber 39, six spark plug 26 circumferences to be evenly arranged in detonation chamber 39 one end near annular spray structure 33 by annular spray structure 33, No. I baffle chamber 22 that detonates, No. II baffle chamber 24 that detonates, No. III baffle chamber 27 that detonates, No. IV baffle chamber 30 that detonates, No. V detonate baffle chamber 32 and No. VI baffle chamber 34 that detonates circumferentially evenly are arranged between combustion box 36 and combustion chamber flame drum 37, telescopic No. I dividing plate 23 that detonates, No. II dividing plate 25 that detonates, No. III dividing plate 28 that detonates, No. IV dividing plate 29 that detonates, detonation chamber 39 is evenly divided between six annuluses by No. V detonate dividing plate 31 and No. VI dividing plate 35 that detonates, wherein, No. I dividing plate 23 that detonates, No. II dividing plate 25 that detonates, No. III dividing plate 28 that detonates, No. IV dividing plate 29 that detonates, No. V detonate dividing plate 31 and No. VI dividing plate 35 that detonates detonate with No. I baffle chamber 22 respectively, No. II baffle chamber 24 that detonates, No. III baffle chamber 27 that detonates, No. IV baffle chamber 30 that detonates, No. V detonate baffle chamber 32 and No. VI baffle chamber 34 that detonates corresponding, multiple nozzle 18 is circumferentially evenly arranged in premixing chamber 40 head, by nozzle 18, combustion chamber flame drum 37 is fixed on combustion box 36, between combustion box 36 and combustion chamber flame drum 37, form annular cooling channel 38 simultaneously, wherein, annular spray structure 33 is an intensive fine-porous toroidal membrane, and its aperture is less than 2mm.During work, cooling-air enters 38 pairs, cooling channel combustion chamber flame drum 37 through nozzle 18 and cools, fuel and oxidation air first spray into detonation chamber at a high speed by annular spray structure 33 again behind premixing chamber 40 fully mixing, can prevent knocking combustion pressure wave from returning into fuel supply nozzle 18.
Wherein, rotate detonation combustor 8 and can have four kinds of combustion modes.
Fig. 5 is that combustion chambers burn pattern one starts schematic diagram, during startup combustor, No. II dividing plate 25 that detonates is inserted in detonation chamber 39 by actuation mechanism from No. II baffle chamber 24 that detonates, flammable reactant by head of combustion chamber multiple nozzles 18 circumferentially to spray into behind premixing chamber again through annular spray structure 33 spray to annular detonation chamber 39, lighted a fire by the spark plug 26 on the left of No. II baffle chamber 24 that detonates, combustion wave is formed on the left of detonate dividing plate 25 at No. II, combustion wave annularly room circumference is propagated and develops into detonation wave gradually, detonation wave annularly detonation chamber is propagated counterclockwise, until detonation wave first time be about to by No. II detonate dividing plate 25 time, sent back to No. II detonated in baffle chamber 24 by actuation mechanism No. II is detonated dividing plate 25, prevent detonation wave detonated dividing plate stop.In detonation wave propagation process, because the pressure at pinking crest face place is higher, higher than the spray stagnation pressure of reactant, face place, pinking peak is made not have new fuel to spray into, but one section of annular space after detonation wave is due to the carrying out of exhaust process, pressure has dropped to below propellant spray stagnation pressure, fresh reactant starts again to be injected to annular detonation chamber, complete fuel make up of next circulation of detonation wave, form the stable knocking combustion ripple of a High Rotation Speed in the counterclockwise direction like this at detonation chamber 39 head.
Fig. 6 is that combustion chambers burn pattern two starts schematic diagram, during startup combustor, No. II detonate dividing plate 25 and No. V dividing plate 31 that detonates is inserted in detonation chamber 39 from No. II detonate baffle chamber 24 and No. V baffle chamber 32 that detonates by actuation mechanism respectively, by the plug ignition on the left of No. II detonate baffle chamber 24 and No. V baffle chamber 32 that detonates, twice combustion wave is formed on the left of detonate dividing plate 25 and No. V dividing plate 31 that detonates at No. II, then propagate in the counterclockwise direction and develop into twice detonation wave gradually, until detonation wave first time will by No. II detonate dividing plate 25 and No. V detonate dividing plate 31 time, No. II detonate baffle chamber 24 and No. V baffle chamber 32 that detonates is sent back to by detonate No. II in advance dividing plate 25 and No. V dividing plate 31 that detonates of actuation mechanism, the stable knocking combustion ripple of twice High Rotation Speed in the counterclockwise direction is finally formed at detonation chamber 39 head.
Fig. 7 is that combustion chambers burn pattern three starts schematic diagram, during startup combustor, No. II, No. IV and No. VI dividing plate that detonates by actuation mechanism respectively from No. II, No. IV and No. VI baffle chamber that detonates are inserted in detonation chamber 39, by No. II, plug ignition on the left of No. IV and No. VI baffle chamber that detonates, at No. II, three road combustion waves are formed on the left of No. IV and No. VI dividing plate that detonates, then propagate in the counterclockwise direction and develop into three road detonation waves gradually, treat that detonation wave first time will by No. II, No. IV and No. VI detonate dividing plate time, by actuation mechanism in advance by No. II, No. IV and No. VI dividing plate that detonates sends No. II respectively back to, No. IV and No. VI baffle chamber that detonates, the stable knocking combustion ripple of three roads High Rotation Speed in the counterclockwise direction is finally formed at detonation chamber 39 head.
Combustion chambers burn pattern four is shown in Fig. 2 a and Fig. 2 b, during startup combustor, No. I ~ No. VI dividing plate that detonates all is placed in detonation chamber 39 by actuation mechanism, by the plug ignition on the left of No. I ~ No. VI baffle chamber that detonates, six road combustion waves are formed on the left of No. I ~ No. VI dividing plate that detonates, then propagate in the counterclockwise direction and develop into six road detonation waves gradually, until detonation wave first time will by No. I ~ No. VI detonate dividing plate time, No. I ~ No. VI dividing plate that detonates all is sent back to No. I ~ No. VI baffle chamber that detonates in advance by actuation mechanism, the stable knocking combustion ripple of six roads High Rotation Speed in the counterclockwise direction is finally formed at detonation chamber 39 head.
Fig. 3 a and Fig. 3 b is the structure diagram of nozzle of the present invention, and Fig. 4 is the nozzle three-dimensional views shown in Fig. 3, and nozzle comprises nozzle outer shroud 41 and nozzle body 44.Nozzle outer shroud 41 is a hollow right circular cylinder structure, and nozzle body 44 is cylindrical structures, and its tip designs becomes half spherical cambered surface, half spherical cambered surface offers fuel orifice 45 and oxidation air spray-hole 46.Nozzle outer shroud 41 is directly enclosed within nozzle body 44, and nozzle outer shroud 41 can circumferentially rotate freely.Four regions of 90 degree of spacing are become equidistantly respectively to be provided with three row's nozzle outer shroud air hole 42 and nozzle body air holes 43 at nozzle outer shroud 41 with nozzle body 44 tube wall circumference respectively, fuel channel 48 is had at the Center of nozzle body 44, equidistantly be designed with air passageways 47 in the head circumference of nozzle body 44, air passageways 47 is an annular pass in nozzle body 44.In gas turbine working procedure, regulate the degree of misalignment of nozzle outer shroud air hole 41 and nozzle body air hole 43 by swivel nozzle outer shroud 41, and then the AIR Proportional of real-time accurately control and participate in firing chamber cooling and oxidizing fire.
Blending room 9 is positioned at and rotates detonation combustor downstream, and it is a convergence type annular pass, and the high-temperature fuel gas sprayed from detonation chamber 39 and the Cryogenic air of discharging from cooling channel, firing chamber 38 and venting bypass 7 carry out blending, and are accelerated gradually by convergence type annular pass.Turbine 10 is positioned at downstream, blending room 9, turbine 10 comprises the first order turbine, second level turbine and the third level turbine that set gradually from left to right, wherein, first order turbine adopts impulse turbine, and without turbine stator blade, flow direction only by changing High Rotation Speed combustion gas extracts combustion gas kinetic energy, and second level turbine and third level turbine all adopt anti-force type turbine, and it is identical with existing gas turbine turbine structure.During work, from the high-temperature high-pressure fuel gas rotating detonation combustor discharge, there is the higher speed that rotates in a circumferential direction, the first order adopts impulse turbine to be designed with the energy extraction being beneficial to combustion gas, combustion gas only changes its flow direction and acceleration of not expanding after impulse turbine, and then in second, third grade of anti-force type turbine further expansion work, the capacity usage ratio rotating pinking combustion gas can be improved.
Outlet pipe 11 is placed in turbine 10 downstream, identical with existing combustion turbine exhaustion tubular construction; Generator assembly 14 is connected with gas turbine rotor 21 by speed changer 13, and speed changer 13 is identical with conventional art with generator assembly 14.
In order to understand further the present invention, now an explanation is done to its working procedure:
First gas compressor 2 is driven to rotate by Starter, ambient air enters gas turbine through intake duct 1, gas storage chamber 4 is flowed into through diffuser 3 after being compressed boosting by gas compressor 2, because diffuser 3 is expanding passage, pressurized air speed after diffuser 3 reduces pressure and raises, guide vane 20 pairs of air of gas storage chamber 4 entrance have guide functions, can prevent air from producing eddy current at turning and producing extra flow losses, channels designs between guide vane 20 becomes expanding, and the air that diffuser 3 exports will slow down further supercharging after guide vane 20.Pressurized air in gas storage chamber 4 enters the air passageways 47 of nozzle 18 through the gas manifold 16 that divides of supply air line 5 end, firing chamber cooling-air enters the annular cooling channel 38 formed by combustion box 36 and combustion chamber flame drum 37 after nozzle body air hole 43 and nozzle outer shroud air hole 42, the oxidation air hole 46 of combustion oxidation air on nozzle end half spherical cambered surface sprays into premixing chamber 40, when gas turbine is at different load MODE of operation, by the air mass flow of the accurate control combustion room of the air flow rate adjustment valve 19 on supply air line 5 and Air flow meter 17, can the degree of misalignment of Control Nozzle outer shroud air hole 42 and nozzle body air hole 43 by swivel nozzle outer shroud 41, realize the allocation proportion requirement of different working modes lower combustion chamber to cooling-air and oxidation air.By the fuel around spark plug 26 light up plug of detonation chamber 39 head, and form the circumferential detonation wave of High Rotation Speed, fuel in detonation chamber 39 to rotate knocking combustion mode rapid combustion heat release, and discharge at a high speed from combustor exit, then the cooling-air flowed out with cooling channel 38 in blending room 9 carries out blending, because blending room 9 is designed to convergence type, combination gas flow velocity behind blending room 9 increases pressure drop.Blending fuel gas high-speed after acceleration sprays into turbine 10, because combustion gas has the larger speed that rotates in a circumferential direction, therefore the turbine first order is without the need to flow-guiding stator blade, combustion gas directly enters first order impulse turbine movable vane, after impulse turbine movable vane, fuel gas flow direction is changed, energy is exported to turbine with the form of air horsepower simultaneously, the mode of combustion gas again by expanding in second and third level anti-force type turbine of discharging from impulse turbine movable vane is done work, the total energy that turbine extracts the most at last from combustion gas exports to gas compressor 2 and generator assembly 14 with the form of air horsepower, the combustion gas of having done work is discharged through outlet pipe 11.When gas compressor 2 is greater than gas compressor pressurized air power demand from the air horsepower that turbine 10 obtains, Starter and gas compressor are thrown off, realize gas turbine to rotate the generating of knocking combustion pattern, in the course of the work, when gas storage chamber 4 pressure reaches blow off pressure, switching mode solenoid valve 6 in venting bypass 7 will be opened automatically, and pressurized air can directly be expelled to blending room 9 by venting bypass 7.
Claims (8)
1. one kind rotates pinking gas turbine, it is characterized in that, comprise the intake duct (1), diffuser (3) and the gas storage chamber (4) that connect successively from left to right, gas compressor (2) is arranged on the downstream of intake duct (1); Rotate the right-hand member that detonation combustor (8) is positioned at gas storage chamber (4), the right-hand member rotating detonation combustor (8) is connected with blending room (9), turbine (10) and outlet pipe (11) in turn, rotate detonation combustor (8) left side annular spaced set and have multiple nozzle (18), be evenly arranged six spark plugs (26) in the circumference rotating detonation combustor (8); Single-nozzle is equipped with air passageways (47) and fuel channel (48), gas storage chamber (4) is connected with rotation detonation combustor (8) by the air passageways (47) of supply air line (5) and some nozzles (18) successively, and blending room (9) are connected by venting bypass (7) and gas storage chamber (4); Rotor (21) is arranged at the center of gas compressor (2) and turbine (10), be connected with gas turbine static load parts casing with turbine (10) by turbine turns parts gas compressor (2) by two bearings (15), one end of rotor (21) is drawn from outlet pipe (11);
The Outlet of rotor (21) is connected with generator assembly (14) by speed changer (13);
Be provided with guide vane (20) in the ingress of gas storage chamber (4), the current path between guide vane (20) is expansion shape passage.
2. one according to claim 1 rotates pinking gas turbine, and it is characterized in that, diffuser (3) is an expansion annular pass, and the subsonic flow that gas compressor (2) exports slows down supercharging behind expansion annular pass.
3. one according to claim 1 rotates pinking gas turbine, it is characterized in that, gas storage chamber (4) for first-class cross sectional annular cavity, its slenderness ratio be 0.1 ~ 0.2, volume be 8 ~ 10 times of rotation detonation combustor (8); Blending room (9) is a convergence annular pass, cooling-air and High Temperature High Pressure pinking combustion gas even blending speedup step-down in blending room (9).
4. one according to claim 1 rotates pinking gas turbine, it is characterized in that, the end of supply air line (5) is a hemispherical dome structure, and on this hemispherical dome structure, being evenly provided with multiple points of gas manifolds (16), a point gas manifold (16) is connected with the air passageways (47) of nozzle (18); Air flow meter (17) and air flow rate adjustment valve (19) is provided with in supply air line (5).
5. one according to claim 1 rotates pinking gas turbine, it is characterized in that, is provided with the solenoid valve (6) controlling its switch in venting bypass (7).
6. one according to claim 1 rotates pinking gas turbine, it is characterized in that, nozzle (18) comprises nozzle body (44) and is arranged at the nozzle outer shroud (41) of nozzle body (44) circumference, nozzle outer shroud (41) is a hollow right circular cylinder structure, nozzle body (44) is a cylindrical structure, its end is half spherical cambered surface, and nozzle outer shroud (41) circumferentially can rotate around nozzle center's axle, nozzle body (44) is equidistantly respectively provided with three row's nozzle body air holes (43) and nozzle outer shroud air hole (42) with the corresponding position of the circumference of nozzle outer shroud (41) becoming four of 90 degree of spacing regions, fuel channel (48) is positioned at the center of nozzle body (44), some air passagewayss (47) are circumferentially in the left side of nozzle body (44), and the annular housing air flow path inner with nozzle body (44) is connected.
7. one according to claim 1 rotates pinking gas turbine, it is characterized in that, rotating detonation combustor (8) is first-class cross sectional annular firing chamber, it combustion chamber flame drum (37) comprising combustion box (36) and set within it, combustion chamber flame drum (37) is divided into premixing chamber (40) and detonation chamber (39) by annular spray structure (33), and six spark plug (26) circumferences are evenly arranged in detonation chamber (39) one end near annular spray structure (33), No. I baffle chamber that detonates (22), No. II baffle chamber that detonates (24), No. III baffle chamber that detonates (27), No. IV baffle chamber that detonates (30), No. V baffle chamber that detonates (32) and No. VI baffle chamber that detonates (34) are circumferentially evenly arranged between combustion box (36) and combustion chamber flame drum (37), telescopic No. I dividing plate that detonates (23), No. II dividing plate that detonates (25), No. III dividing plate that detonates (28), No. IV dividing plate that detonates (29), detonation chamber (39) is evenly divided between six annuluses by No. V dividing plate that detonates (31) and No. VI dividing plate that detonates (35), wherein, and No. I dividing plate that detonates (23), No. II dividing plate that detonates (25), No. III dividing plate that detonates (28), No. IV dividing plate that detonates (29), No. V dividing plate that detonates (31) and No. VI dividing plate that detonates (35) respectively with No. I baffle chamber that detonates (22), No. II baffle chamber that detonates (24), No. III baffle chamber that detonates (27), No. IV baffle chamber that detonates (30), No. V baffle chamber that detonates (32) and No. VI baffle chamber that detonates (34) corresponding,
Multiple nozzle (18) is circumferentially evenly arranged in premixing chamber (40) head, by nozzle (18), combustion chamber flame drum (37) is fixed on combustion box (36), between combustion box (36) and combustion chamber flame drum (37), form annular cooling channel (38) simultaneously, wherein, annular spray structure (33) is an intensive fine-porous toroidal membrane, and its aperture is less than 2mm.
8. one according to claim 1 rotates pinking gas turbine, it is characterized in that, turbine (10) comprises the first order turbine, second level turbine and the third level turbine that set gradually from left to right, wherein, first order turbine adopts impulse turbine, and without turbine stator blade, second level turbine and third level turbine all adopt anti-force type turbine.
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1961142A (en) * | 2004-04-30 | 2007-05-09 | 威廉·安东尼·德纳 | Pulse jet engines |
| CN101285590A (en) * | 2007-04-12 | 2008-10-15 | 通用电气公司 | Electro-dynamic swirler, combustion apparatus and methods using the same |
| CN203730136U (en) * | 2014-02-27 | 2014-07-23 | 王庆 | Turbopulse detonation engine |
| CN204082338U (en) * | 2014-08-06 | 2015-01-07 | 西安热工研究院有限公司 | A kind of rotation pinking gas turbine |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7984614B2 (en) * | 2008-11-17 | 2011-07-26 | Honeywell International Inc. | Plasma flow controlled diffuser system |
-
2014
- 2014-08-06 CN CN201410384377.1A patent/CN104153884B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1961142A (en) * | 2004-04-30 | 2007-05-09 | 威廉·安东尼·德纳 | Pulse jet engines |
| CN101285590A (en) * | 2007-04-12 | 2008-10-15 | 通用电气公司 | Electro-dynamic swirler, combustion apparatus and methods using the same |
| CN203730136U (en) * | 2014-02-27 | 2014-07-23 | 王庆 | Turbopulse detonation engine |
| CN204082338U (en) * | 2014-08-06 | 2015-01-07 | 西安热工研究院有限公司 | A kind of rotation pinking gas turbine |
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