CN204042975U - A kind of rotation detonation combustor - Google Patents
A kind of rotation detonation combustor Download PDFInfo
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- CN204042975U CN204042975U CN201420441723.0U CN201420441723U CN204042975U CN 204042975 U CN204042975 U CN 204042975U CN 201420441723 U CN201420441723 U CN 201420441723U CN 204042975 U CN204042975 U CN 204042975U
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Abstract
The utility model one rotates detonation combustor, it is except equidistantly arranging some fuel nozzles in head of combustion chamber annular, also evenly be provided with multiple fuel nozzle at the axial and circumferential of combustor outer casing, annular detonation combustor is divided into multiple little space, each nozzle is responsible for the fuel supply in each little space, filling fuels efficiency can be improved, increase chamber fuel packing space, promote combustion chambers burn calorific intensity; The increase of chamber fuel packing space can extend the axial distance rotating detonating combustion ripple, makes rotation detonation wave through whole combustion chamber, can prevent from rotating detonation wave disappearance of degenerating because lacking fuel support in communication process simultaneously; Rotating the indoor spirality barrier be provided with circumferentially of detonating combustion, the distance that in startup combustor process, deflagration changes to detonating combustion can be shortened, strengthen and rotate pinking intensity of wave, improve the entirety of combustion chambers burn process from boosting capability, the stability rotated in detonation wave propagation process can be strengthened simultaneously.
Description
[technical field]
The utility model relates to a kind of combustion chamber of gas turbine, and particularly relate to a kind of rotation detonation combustor, it is for gas turbine power generation and power-equipment.
[background technology]
Deflagration and detonating combustion are two kinds of primary combustion modes of fuel energy release.Deflagration burning imports heat into non-burning mixt by heat transfer, thermal diffusion and heat radiation effect, successively heats, successively burns, and then realize deflagration wave propagation.Deflagration velocity of wave propagation is lower, is generally about several meters to tens metre per second (m/s)s.Detonating combustion by shock wave to can pinking mixture successively intense impact compression make it that high-speed chemical reaction occur to realize, can think that detonating combustion ripple is the intense shock wave of chemical reaction of being coupled.Detonation wave is all propagated, generally 10 with supersonic speed
3m/s magnitude.Deflagration burning is the combustion system extensively adopted in current industrial production, but detonating combustion has many deflagrations burns unrivaled advantage, as from supercharging, flame propagation speed, efficiency of combustion is high, pollutant emission is low.
Rotating detonation combustor is a kind of toroidal combustion chamber utilizing knocking combustion mode, and fuel is supplied jointly by multiple nozzles of head of combustion chamber.In one section of axial distance annular housing near head of combustion chamber, form one or more detonating combustion ripple rotated in a circumferential direction during combustion chamber operational, and deteriorate to a series of weak compressional wave at combustor tail detonation wave.Because detonating combustion spread speed is all 10
3m/s magnitude, and combustion chamber dimensions is all in m level, therefore the filling fuels time is all 10
-3s level.Within the so short time, fuel nozzle generally can only fill the very short annular housing of one section of axial dimension, and therefore detonating combustion ripple only can be formed at head, and deteriorates to a series of weak compressional wave at combustor tail detonation wave owing to losing fuel support.If fuel supply exists pressure fluctuation, then may to occur also not being able to do in time filling fuel and situation that detonation wave reaches again at the segment space of head of combustion chamber, this will cause detonating combustion ripple to extinguish disappearance because lacking fuel.
To sum up analyze, mainly there are the following problems to rotate detonation combustor at present: 1) rotate detonating combustion ripple and exist only in head of combustion chamber; 2) filling fuels limited space, is subject to the impact of feed system pressure fluctuation; 3) rotate detonating combustion ripple easily to degenerate disappearance.
[utility model content]
The purpose of this utility model is that the detonation wave solved existing for existing rotation detonation combustor is only formed at head of combustion chamber, filling fuels insufficient space, detonation wave easily degenerate the problems such as disappearance, provides a kind ofly to rotate detonation combustor.Its structure is simple, and fuel energy rate of release is fast, and efficiency of combustion is high; Head of combustion chamber and combustor outer casing have been evenly arranged multiple nozzle, improve filling fuels speed, can guarantee that chamber fuel is filled completely, make rotation detonating combustion wave energy through whole toroidal combustion chamber, add overall pressure ratio and the fault offset density of combustion chamber; In the annular housing of combustion chamber, install spirality barrier additional, the distance that deflagration wave direction detonation wave changes can have been shortened, simultaneously can strengthen and stablize and rotate detonating combustion ripple, prevent rotation detonation wave to degenerate in communication process disappearance.
For achieving the above object, the utility model adopts following technical scheme:
A kind of rotation detonation combustor, comprise the detonation combustor and fuel preheating room that set gradually from outside to inside, wherein, detonation combustor is the annular housing formed between combustor outer casing and combustion chamber inner casing, and it closes right-hand member open design for left end, fuel preheating room is the annular housing formed between the indoor shell of combustion chamber inner casing and fuel preheating, and its two ends, left and right are enclosed construction; The left side of detonation combustor and the circumference of combustor outer casing are evenly provided with some fuel nozzles, and in the circumference of combustor outer casing, being evenly provided with six groups of spark plugs, the outlet of detonation combustor left end fuel nozzle is connected with pinking forward pass pressure wave attenuating structure; Some spirality barriers are set in parallel in detonating combustion indoor, and some fuel inlet line are evenly arranged on the right side of fuel preheating room, and some fuel outlet pipelines are evenly arranged on the left side of fuel preheating room.
The utility model improves further and is: in the annular housing of detonation combustor, be evenly provided with No. I dividing plate that detonates successively along clockwise direction, 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 dividing plate that detonates, its respectively with No. I baffle chamber that detonates evenly being arranged on fuel preheating indoor along clockwise direction successively, 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, and each dividing plate that detonates can stretch in the quick-fried baffle chamber of its correspondence.
The utility model improves further and is: pinking forward pass pressure wave attenuating structure is a semicircular arc Rotational Symmetry shell structure, and it is fixed on the blind end of detonation combustor by the fuel nozzle of detonation combustor left end.
The utility model improves further and is: spirality barrier is arranged in the annular housing of detonation combustor in the mode of rotating in a circumferential direction.
The utility model improves further and is: the premixer that fuel nozzle comprises nozzle body and is connected with its right-hand member, the left end of nozzle body is enclosed construction, the left side of nozzle body is provided with fuel conduit and air pipe line, and the port of export of fuel conduit and air pipe line is all positioned at premixer, premixer evenly offers some fuel orifices.
The utility model improves further and is: the leading portion of fuel conduit and air pipe line is direct current channel, and rear end is spirality channel.
The utility model improves further and is: one end premixer offering some fuel orifices is hemispherical shell body structure.
Relative to prior art, the utility model one rotates detonation combustor, except equidistantly arranging some fuel nozzles in head of combustion chamber annular, also evenly be provided with multiple fuel nozzle at the axial and circumferential of combustor outer casing, annular detonation combustor is divided into multiple little space, and each nozzle is responsible for the fuel supply in each little space, can improve filling fuels efficiency, increase chamber fuel packing space, promote combustion chambers burn calorific intensity; The increase of chamber fuel packing space can extend the axial distance rotating detonating combustion ripple, makes rotation detonation wave through whole combustion chamber, can prevent from rotating detonation wave disappearance of degenerating because lacking fuel support in communication process simultaneously; Spirality barrier is circumferentially provided with in rotation detonation combustor annular housing, the distance that in startup combustor process, deflagration changes to detonating combustion can be shortened, strengthen and rotate pinking intensity of wave, improve the entirety of combustion chambers burn process from boosting capability, the stability rotated in detonation wave propagation process can be strengthened simultaneously.
[accompanying drawing explanation]
Fig. 1 is a kind of structural representation rotating detonation combustor of the utility model;
Fig. 2 is that the A-A of the rotation detonation combustor shown in Fig. 1 is to sectional view;
Fig. 3 is the normal axomometric drawing of the rotation detonation combustor shown in Fig. 1;
Fig. 4 is the structural representation of the utility model fuel nozzle;
Fig. 5 is that the utility model detonation combustor combustion mode one starts schematic diagram;
Fig. 6 is that the utility model detonation combustor combustion mode two starts schematic diagram;
Fig. 7 is that the utility model detonation combustor combustion mode three starts schematic diagram.
Wherein: 1, No. I baffle chamber that detonates; 2, No. I dividing plate that detonates; 3, spark plug; 4, No. II dividing plate that detonates; 5, No. II baffle chamber that detonates; 6, No. III baffle chamber that detonates; 7, No. III dividing plate that detonates; 8, No. IV baffle chamber that detonates; 9, No. IV dividing plate that detonates; 10, No. V baffle chamber that detonates; 11, No. V dividing plate that detonates; 12, No. VI dividing plate that detonates; 13, No. VI baffle chamber that detonates; 14, fuel outlet pipeline; 15, fuel nozzle; 16, combustor outer casing; 17, combustion chamber inner casing; 18, fuel inlet line; 19, the indoor shell of fuel preheating; 20, detonation combustor; 21, spirality barrier; 22, pinking forward pass pressure wave attenuating structure; 23, fuel preheating room; 24, fuel conduit; 25, nozzle body; 26, premixer; 27, fuel orifice; 28, air pipe line.
[detailed description of the invention]
Below in conjunction with drawings and Examples, the utility model is described in further detail.
See Fig. 1 to Fig. 3, the utility model one rotates detonation combustor, comprise the detonation combustor 20 and fuel preheating room 23 that set gradually from outside to inside, wherein, detonation combustor 20 is the annular housing formed between combustor outer casing 16 and combustion chamber inner casing 17, and it closes right-hand member open design for left end, fuel preheating room 23 is the annular housing formed between the indoor shell 19 of combustion chamber inner casing 17 and fuel preheating, and its two ends, left and right are enclosed construction; The circumference of the left side of detonation combustor 20 and combustor outer casing 16 is evenly provided with some fuel nozzles 15, and six groups of spark plugs 3 are evenly provided with in the circumference of combustor outer casing 16, the outlet of detonation combustor 20 left end fuel nozzle 15 is connected with pinking forward pass pressure wave attenuating structure 22; Some spirality barriers 21 are set in parallel in detonation combustor 20, some fuel inlet line 18 are evenly arranged on the right side of fuel preheating room 23, some fuel outlet pipelines 14 are evenly arranged on the left side of fuel preheating room 23, cold conditions fuel enters fuel preheating room 23 from the fuel inlet line 18 of combustor tail, because the head temperature of detonation combustor 20 is higher than afterbody, therefore fuel temperature when flowing through fuel preheating room 23 raises gradually, and finally flow out from fuel outlet pipeline 14.Fuel preheating room 23, except the effect had chamber fuel heating, also can cool detonation combustor 20 in real time.
See Fig. 1 and Fig. 5 to Fig. 7, No. I dividing plate 2 that detonates evenly is provided with along clockwise direction successively in the annular housing of detonation combustor 20, No. II dividing plate 4 that detonates, No. III dividing plate 7 that detonates, No. IV dividing plate 9 that detonates, No. V detonate dividing plate 11 and No. VI dividing plate 12 that detonates, its baffle chamber 1 that detonates with No. I of being evenly arranged on successively in fuel preheating room 23 along clockwise direction respectively, No. II baffle chamber 5 that detonates, No. III baffle chamber 6 that detonates, No. IV baffle chamber 8 that detonates, No. V detonate baffle chamber 10 and No. VI baffle chamber 13 that detonates corresponding, and each dividing plate that detonates can stretch in the quick-fried baffle chamber of its correspondence.Wherein, each dividing plate that detonates is rectangle, and the dividing plate that detonates is mainly used in startup combustor, and what change to detonating combustion as deflagration burning closes solid border, face, and after rotation detonation wave is formed, the dividing plate that detonates inserts by actuation mechanism the baffle chamber that detonates.
Further, pinking forward pass pressure wave attenuating structure 22 is a semicircular arc Rotational Symmetry shell structure, and it is fixed on the blind end of detonation combustor 20 by the fuel nozzle 15 of detonation combustor 20 left end.After in detonation combustor 20, igniting forms the detonation wave of High Rotation Speed, detonation wave, except propagating toward combustor tail, also can be propagated toward detonation combustor 20 head, be forwarded to fuel nozzle 15, affect the supply of fuel.Pinking forward pass decline of pressure structure 22 can make forward pass pressure wave first on semicircular arc openend and cambered surface, form reflected shock wave, reflected shock wave and pinking forward pass pressure wave interact, pinking forward pass pressure intensity of wave can be weakened gradually, and then reduce pinking forward pass pressure wave to the impact of fuel feed system.
Further, spirality barrier 21 is arranged in the annular housing of detonation combustor 20 in the mode of rotating in a circumferential direction, it can increase the turbulivity of burning mixture, improve the energy transferring between combustion gas and unburned gas, increase fuel heat release rate, thus the distance that the burning of deflagration in startup combustor process changes to detonating combustion can be shortened, simultaneously can enhanced detonation burning intensity of wave, improve pinking wave stability.
See Fig. 4, the premixer 26 that fuel nozzle 15 comprises nozzle body 25 and is connected with its right-hand member, the left end of nozzle body 25 is enclosed construction, the left side of nozzle body 25 is provided with fuel conduit 24 and air pipe line 28, and the port of export of fuel conduit 24 and air pipe line 28 is all positioned at premixer 26, premixer 26 evenly offers some fuel orifices 27.Wherein, the leading portion of fuel conduit 24 and air pipe line 28 is direct current channel, and rear end is spirality channel.Fuel and air enter premixer 26 by with the spiral fashion of High Rotation Speed after spirality channel, this can extend the blending distance of fuel and air, simultaneously under centrifugal action, the fuel being in center will gradually toward external diffusion, can ensure fuel and air blending even.One end premixer 26 offering some spray-holes 27 is hemispherical shell body structure.The static pressure of fuel and air can be converted into dynamic pressure by this hemispherical convergence structure, improves the flow velocity of blending gas, can guarantee that flammable mixture has stronger penetration power after fuel orifice 27.
Fuel nozzle 15 is arranged on outside detonation combustor 20 left side divided by the equidistant mode of annular, also on combustor outer casing 16, circumferential spaced set has multiple fuel nozzle, annular detonation combustor 20 can be divided into multiple little space by this, the fuel supply in each little space is only responsible for by each fuel nozzle, filling fuels efficiency can be improved, increase filling fuels space, can prevent rotating detonation wave and to degenerate because lacking fuel disappearance.
Embodiment:
See Fig. 1 and Fig. 2, the utility model one rotates detonation combustor, comprises detonation combustor 20, fuel preheating room 23, fuel nozzle 15, spirality barrier 21, pinking forward pass pressure wave attenuating structure 22, fuel inlet line 18, fuel outlet pipeline 14 and spark plug 3.In the present embodiment detonation combustor 20 and fuel preheating room 23 coaxially arranged; Detonation combustor external diameter 1400mm, internal diameter 1200mm, long 1100mm; Fuel preheating outdoor footpath 1190mm, internal diameter 890mm, long 1100mm.Pinking forward pass pressure wave attenuating structure 22 is arranged on the head of detonation combustor 20, is fixedly connected with detonation combustor 20 by fuel nozzle 15, and pinking forward pass pressure wave attenuating structure 22 is semicircular arc housing, radius 40mm.Spirality barrier 21 is square full circle helical spring structure, and circumferentially screw arrangement is in the annular housing of detonation combustor 20, spring diameter 8mm, pitch 100mm.The fuel nozzle 15 of detonation combustor 20 head arranges a circle in the equidistant mode of annular, and the fuel nozzle 15 on combustor outer casing 16 is evenly arranged in axial and circumferential; Air pipe line 28 diameter 6mm in fuel nozzle, spiral part central diameter 46mm, pitch 50mm; Fuel conduit 24 diameter 4mm, spiral part central diameter 25mm, pitch 50mm.Fuel inlet line 18 annular is equidistantly arranged in the right-hand member of fuel preheating room 23, diameter 16mm; Fuel outlet pipeline 14 annular is equidistantly arranged in the left end of fuel preheating room 23, diameter 16mm.
The present embodiment rotates detonation combustor four kinds of mode of operations.
Mode of operation one:
See Fig. 2 and Fig. 5, during startup combustor, No. II dividing plate 4 that detonates is inserted in detonation combustor 20 by actuation mechanism from No. II baffle chamber 5 that detonates, fuel flows into fuel preheating room 23 by fuel inlet line 18, multiple fuel nozzles 15 again on fuel outlet pipeline 14 flowing in combustion chamber head and combustor outer casing, through fuel orifice 27 at a high speed spray into annular detonation combustor 20 after fully mixing with oxidation air in fuel nozzle premixer 26; By the plug ignition on the left of No. II dividing plate 4 that detonates, combustion wave is formed on the left of detonate dividing plate 4 at No. II, combustion wave also changes detonation wave into gradually along combustion chamber circumferential development, detonation wave is counterclockwise to propagate at the indoor High Rotation Speed of annular detonating combustion, until detonation wave first time be about to by No. II detonate dividing plate 4 time, sent back to No. II detonated in baffle chamber 5 by actuation mechanism No. II is detonated dividing plate 4, prevent the detonation wave dividing plate that detonated from stoping.Rotate in communication process at detonation wave, because the pressure at pinking crest face place is higher, be greater than the spray stagnation pressure of flammable mixture, face place, pinking peak is made not have new fuel to spray into, but due to the carrying out of exhaust process in one section of annular housing after detonation wave, pressure has dropped to below propellant spray stagnation pressure, fresh flammable mixture starts again to be injected to annular detonation chamber, complete the fuel make up of next circulation of detonation wave, the stable detonating combustion ripple of a High Rotation Speed is in the counterclockwise direction formed like this in detonation combustor 20, high-temperature high-pressure fuel gas is finally discharged from the afterbody of detonation combustor 20.
Mode of operation two:
See Fig. 2 and Fig. 6, during startup combustor, No. II detonate dividing plate 4 and No. V dividing plate 11 that detonates is inserted in detonation combustor 20 from No. II detonate baffle chamber 5 and No. V baffle chamber 10 that detonates by actuation mechanism respectively, by the plug ignition on the left of No. II detonate dividing plate 4 and No. V dividing plate 11 that detonates, twice combustion wave is formed on the left of detonate dividing plate 4 and No. V dividing plate 11 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 4 and No. V detonate dividing plate 11 time, No. II detonate baffle chamber 5 and No. V baffle chamber 10 that detonates is sent back to by detonate No. II in advance dividing plate 4 and No. V dividing plate 11 that detonates of actuation mechanism, the final detonating combustion ripple forming twice High Rotation Speed in the counterclockwise direction in detonation combustor 20 annular housing.
Mode of operation three:
See Fig. 2 and Fig. 7, 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 combustor 20, by No. II, plug ignition on the left of No. IV and No. VI dividing plate 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 final detonating combustion ripple forming three roads High Rotation Speed in the counterclockwise direction in detonation combustor 20 annular housing.
Mode of operation four:
See Fig. 1 and Fig. 2, during startup combustor, No. I ~ No. VI dividing plate that detonates all is placed in detonation combustor 20 by actuation mechanism, by the plug ignition on the left of No. I ~ No. VI dividing plate 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 final stable detonating combustion ripple forming six roads High Rotation Speed in the counterclockwise direction in detonation combustor 20 annular housing.
Claims (7)
1. one kind rotates detonation combustor, it is characterized in that: comprise the detonation combustor (20) and fuel preheating room (23) that set gradually from outside to inside, wherein, the annular housing of detonation combustor (20) for being formed between combustor outer casing (16) and combustion chamber inner casing (17), and it closes right-hand member open design for left end, the annular housing of fuel preheating room (23) for being formed between combustion chamber inner casing (17) and the indoor shell (19) of fuel preheating, and its two ends, left and right are enclosed construction; The circumference of the left side of detonation combustor (20) and combustor outer casing (16) is evenly provided with some fuel nozzles (15), and in the circumference of combustor outer casing (16), being evenly provided with six groups of spark plugs (3), the outlet of detonation combustor (20) left end fuel nozzle (15) is connected with pinking forward pass pressure wave attenuating structure (22); Some spirality barriers (21) are set in parallel in detonation combustor (20), some fuel inlet line (18) are evenly arranged on the right side of fuel preheating room (23), and some fuel outlet pipelines (14) are evenly arranged on the left side of fuel preheating room (23).
2. one according to claim 1 rotates detonation combustor, it is characterized in that: in the annular housing of detonation combustor (20), be evenly provided with No. I dividing plate that detonates (2) along clockwise direction successively, No. II dividing plate that detonates (4), No. III dividing plate that detonates (7), No. IV dividing plate that detonates (9), No. V dividing plate that detonates (11) and No. VI dividing plate that detonates (12), its respectively with No. I baffle chamber that detonates (1) be evenly arranged on successively along clockwise direction in fuel preheating room (23), No. II baffle chamber that detonates (5), No. III baffle chamber that detonates (6), No. IV baffle chamber that detonates (8), No. V baffle chamber that detonates (10) and No. VI baffle chamber that detonates (13) corresponding, and each dividing plate that detonates can stretch in the quick-fried baffle chamber of its correspondence.
3. one according to claim 1 rotates detonation combustor, it is characterized in that: pinking forward pass pressure wave attenuating structure (22) is a semicircular arc Rotational Symmetry shell structure, it is fixed on the blind end of detonation combustor (20) by the fuel nozzle (15) of detonation combustor (20) left end.
4. one according to claim 1 rotates detonation combustor, it is characterized in that: spirality barrier (21) is arranged in the annular housing of detonation combustor (20) in the mode of rotating in a circumferential direction.
5. one according to claim 1 rotates detonation combustor, it is characterized in that: the premixer (26) that fuel nozzle (15) comprises nozzle body (25) and is connected with its right-hand member, the left end of nozzle body (25) is enclosed construction, the left side of nozzle body (25) is provided with fuel conduit (24) and air pipe line (28), and the port of export of fuel conduit (24) and air pipe line (28) is all positioned at premixer (26), premixer (26) evenly offer some fuel orifices (27).
6. one according to claim 5 rotates detonation combustor, it is characterized in that: the leading portion of fuel conduit (24) and air pipe line (28) is direct current channel, and rear end is spirality channel.
7. the one according to claim 5 or 6 rotates detonation combustor, it is characterized in that: one end premixer (26) offering some fuel orifices (27) is hemispherical shell body structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201420441723.0U CN204042975U (en) | 2014-08-06 | 2014-08-06 | A kind of rotation detonation combustor |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201420441723.0U CN204042975U (en) | 2014-08-06 | 2014-08-06 | A kind of rotation detonation combustor |
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| CN201420441723.0U Expired - Fee Related CN204042975U (en) | 2014-08-06 | 2014-08-06 | A kind of rotation detonation combustor |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104792534A (en) * | 2015-02-03 | 2015-07-22 | 北京理工大学 | Rotation detonation engine experimental device |
| CN105066175A (en) * | 2015-08-31 | 2015-11-18 | 华能国际电力股份有限公司 | Rotary constant-volume pressurizing combustion chamber |
| CN104154567B (en) * | 2014-08-06 | 2015-12-09 | 西安热工研究院有限公司 | A kind of rotation detonation combustor |
| CN109154441A (en) * | 2016-05-23 | 2019-01-04 | 赛峰集团 | Toroidal combustion chamber with continuous detonation wave |
| CN111197765A (en) * | 2019-12-18 | 2020-05-26 | 南京理工大学 | Rotary detonation combustion chamber |
| CN111322637A (en) * | 2018-12-14 | 2020-06-23 | 通用电气公司 | Rotary detonation propulsion system |
| US11149954B2 (en) | 2017-10-27 | 2021-10-19 | General Electric Company | Multi-can annular rotating detonation combustor |
| CN115371083A (en) * | 2021-05-18 | 2022-11-22 | 通用电气公司 | Passive fuel coupling dynamics mitigation device |
| US11536456B2 (en) | 2017-10-24 | 2022-12-27 | General Electric Company | Fuel and air injection handling system for a combustor of a rotating detonation engine |
-
2014
- 2014-08-06 CN CN201420441723.0U patent/CN204042975U/en not_active Expired - Fee Related
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104154567B (en) * | 2014-08-06 | 2015-12-09 | 西安热工研究院有限公司 | A kind of rotation detonation combustor |
| CN104792534A (en) * | 2015-02-03 | 2015-07-22 | 北京理工大学 | Rotation detonation engine experimental device |
| CN104792534B (en) * | 2015-02-03 | 2017-10-10 | 北京理工大学 | Rotate detonation engine experimental provision |
| CN105066175A (en) * | 2015-08-31 | 2015-11-18 | 华能国际电力股份有限公司 | Rotary constant-volume pressurizing combustion chamber |
| CN109154441A (en) * | 2016-05-23 | 2019-01-04 | 赛峰集团 | Toroidal combustion chamber with continuous detonation wave |
| US11536456B2 (en) | 2017-10-24 | 2022-12-27 | General Electric Company | Fuel and air injection handling system for a combustor of a rotating detonation engine |
| US11149954B2 (en) | 2017-10-27 | 2021-10-19 | General Electric Company | Multi-can annular rotating detonation combustor |
| CN111322637A (en) * | 2018-12-14 | 2020-06-23 | 通用电气公司 | Rotary detonation propulsion system |
| US11898757B2 (en) | 2018-12-14 | 2024-02-13 | General Electric Company | Rotating detonation propulsion system |
| CN111197765A (en) * | 2019-12-18 | 2020-05-26 | 南京理工大学 | Rotary detonation combustion chamber |
| CN111197765B (en) * | 2019-12-18 | 2021-08-03 | 南京理工大学 | Rotary detonation combustion chamber |
| CN115371083A (en) * | 2021-05-18 | 2022-11-22 | 通用电气公司 | Passive fuel coupling dynamics mitigation device |
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