CN113932252A - A multi-channel combustor combined with pulse detonation and rotary detonation - Google Patents
A multi-channel combustor combined with pulse detonation and rotary detonation Download PDFInfo
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- CN113932252A CN113932252A CN202111402143.1A CN202111402143A CN113932252A CN 113932252 A CN113932252 A CN 113932252A CN 202111402143 A CN202111402143 A CN 202111402143A CN 113932252 A CN113932252 A CN 113932252A
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- 238000005474 detonation Methods 0.000 title claims abstract description 72
- 238000002485 combustion reaction Methods 0.000 claims abstract description 268
- 239000000446 fuel Substances 0.000 claims abstract description 67
- 239000000112 cooling gas Substances 0.000 claims description 41
- 238000001816 cooling Methods 0.000 claims description 38
- 239000007789 gas Substances 0.000 claims description 10
- 230000000694 effects Effects 0.000 claims description 9
- 230000008602 contraction Effects 0.000 claims description 7
- 238000009434 installation Methods 0.000 claims description 4
- 239000007787 solid Substances 0.000 claims description 4
- 230000007704 transition Effects 0.000 claims description 2
- 230000006872 improvement Effects 0.000 description 7
- 230000001902 propagating effect Effects 0.000 description 6
- 238000000034 method Methods 0.000 description 5
- 230000008569 process Effects 0.000 description 5
- 238000006243 chemical reaction Methods 0.000 description 4
- 238000003466 welding Methods 0.000 description 4
- 230000000644 propagated effect Effects 0.000 description 3
- 230000035939 shock Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000004323 axial length Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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Abstract
The invention relates to a pulse detonation and rotation detonation combined type multi-channel combustion chamber which comprises a pulse detonation combustion chamber, a first-stage rotation detonation combustion chamber, a second-stage rotation detonation combustion chamber, a third-stage rotation detonation combustion chamber, an air and fuel injector and a combustion chamber exhaust chamber. The combined multi-channel detonation combustion chamber structure is formed by combining the structural characteristics of the pulse detonation combustion chamber and the rotary detonation combustion chamber, so that when the rotary detonation combustion chamber and the pulse detonation combustion chamber work simultaneously, the problem of reduction of the working stability of the combustion chamber caused by intermittent exhaust of the pulse detonation combustion chamber can be effectively solved; meanwhile, the flow area of the combustion chamber can be effectively increased, and the thrust-weight ratio of the combustion chamber is improved; the output power of the combustion chambers can be effectively adjusted by controlling whether different combustion chambers are ignited to work or not. The invention ensures the working stability of the combustion chamber, improves the space utilization rate of the combustion chamber, increases the output power of the combustion chamber and widens the adjusting range of the output power of the combustion chamber.
Description
Technical Field
The invention belongs to the technical field of detonation combustors, and particularly relates to a pulse detonation and rotary detonation combined type multi-channel combustor.
Background
Combustion is classified into slow combustion and knocking combustion according to the severity of chemical reaction. The existing aerospace engines comprise turbojet engines, conventional rocket engines, ramjet engines and other power devices, industrial gas turbines and other power devices, combustion chambers are based on a slow combustion mode of isobaric circulation, the technical maturity of the existing aerospace engines is high, and further improvement of thermal circulation efficiency is very difficult. The detonation combustion is characterized in that a shock wave structure exists in front of a chemical reaction zone, and the shock wave is coupled with the chemical reaction zone and propagates together. Due to the self-pressurization effect of the shock wave, compared with slow combustion, the detonation combustion has the characteristics of low entropy increase and high heat release rate theoretically. Therefore, the power plant based on the knocking combustion theoretically has the advantages of higher heat cycle efficiency, smaller combustion chamber volume and the like.
Many advantages of Detonation combustion attract extensive attention of researchers at home and abroad, and various Detonation combustion chamber structural forms are proposed, including a Pulse Detonation Combustor (PDC for short) and a rotary Detonation Combustor (RDC for short), and the like. The PDC is an intermittent operation mode, in which burned gas is discharged from the combustion chamber in an unsteady exhaust process, that is, the exhaust pressure of the burned gas is constantly changed. The PDC-form-based power device has the problems of poor working stability due to unsteady exhaust characteristics, difficult coupling with a gas compressor and a turbine part and the like. The RDC can work continuously in theory only through single ignition, the propagation frequency of the rotating detonation wave can reach thousands of hertz, and the influence of unsteady exhaust characteristics of the combustion chamber is small. However, because the RDC generally adopts an annular combustion chamber structure, the combustion chamber is composed of an outer ring and an inner column structure, and the inner space of the annular structure cannot be effectively utilized, the thrust-weight ratio of the combustion chamber is reduced, and space waste is caused.
Disclosure of Invention
The invention aims to provide a pulse detonation and rotation detonation combined type multi-channel combustion chamber, which aims to solve the problems of low working stability of the combustion chamber, poor matching with a turbine part of a gas compressor and insufficient utilization rate of RDC (radial fuel injection) space caused by intermittent exhaust of the conventional PDC. The invention can be applied to the fields of aircraft engines, gas turbines and the like.
In order to achieve the purpose, the invention adopts the technical scheme that:
a pulse detonation and rotary detonation combined type multi-channel combustion chamber comprises a PDC combustion chamber, a first-stage RDC combustion chamber, a second-stage RDC combustion chamber, a third-stage RDC combustion chamber, an air and fuel injector and a combustion chamber exhaust chamber:
the PDC combustion cavity is positioned in the center of the combustion chamber and is of a circular tubular structure consisting of a PDC cover plate and a PDC outer wall surface, and the contact surface of the PDC outer wall surface and the PDC cover plate fixes the PDC outer wall surface on the PDC cover plate;
the air and fuel injector of the PDC is positioned in the central position of the PDC cover plate, fuel is supplied to the PDC combustion cavity through the jet hole structure, and air is supplied to the PDC combustion cavity through the annular seam structure;
the PDC igniter is arranged on the outer wall surface of the PDC and is close to one side of the head part of the combustion cavity, the installation direction is vertical to the axial direction of the combustion cavity, the PDC cooling gas supply cavity and the cooling gas film hole are arranged in the outer wall surface of the PDC, and the included angle between the axial direction of the PDC cooling gas film hole and the axial direction of the combustion chamber is 20 degrees;
the turbulence device is positioned in the PDC combustion cavity, is close to one side of the head and is of a spiral structure, the axial direction of the spiral structure is consistent with the axial direction of the combustion cavity, and the turbulence device is fixed in the combustion cavity to prevent the turbulence device from moving along the axial direction;
the first-stage RDC combustion chamber is positioned outside the PDC combustion chamber and is of an annular cavity structure consisting of an RDC cover plate, a PDC outer wall surface and a first-stage RDC outer wall surface, and the axial positions of the outlet of the first-stage RDC combustion chamber and the outlet of the PDC combustion chamber are the same;
the second-stage RDC combustion chamber and the third-stage RDC combustion chamber are sequentially distributed on the outer side of the first-stage RDC combustion chamber and are all of annular cavity structures, and the axial positions of the inlet and the outlet of the first-stage RDC combustion chamber, the second-stage RDC combustion chamber and the third-stage RDC combustion chamber are completely the same; the air and fuel injectors and igniters of each stage of RDC are positioned on the RDC cover plate; RDC cooling air supply cavities and cooling air film holes are formed in the outer wall surfaces of the first-stage, the second-stage and the third-stage RDCs, and the axial included angle between the axial direction of each cooling air film hole and the axial direction of the combustion chamber is 20 degrees;
the combustion chamber exhaust cavity is positioned at one side of outlets of the PDC and the RDC, and the combustion chamber exhaust cavity is of a hollow shrinkage type circular truncated cone structure.
The invention has the further improvement that the air and fuel injector is of a double-channel cylindrical structure, the fuel supply cavity is arranged at the center and is of a cylindrical cavity structure, 4 fuel supply holes are uniformly distributed along the circumferential direction on the outlet end face of the fuel supply cavity, the fuel supply holes are of a straight circular hole structure, and the axial direction and the axial included angle of a combustion chamber are 45 degrees; the outer side of the fuel supply cavity is provided with an air supply annular cavity which is of an annular cavity-shaped structure, the outlet of the air supply cavity is provided with a contraction and expansion molded surface, the minimum flow area of the contraction molded surface is adjusted to control the supply flow of air, and the contraction molded surface and the expansion molded surface are in circular arc transition; in order to facilitate the installation and the disassembly of the air and fuel injector, taper pipe threads are arranged on the outer side of the injector.
The invention has the further improvement that the center of the PDC cover plate is provided with an injector mounting hole; the RDC cover plate is respectively provided with injector mounting holes at three radial positions, namely the central positions of the first-stage, second-stage and third-stage RDC combustion chambers; the number of air injectors and fuel injectors of each stage of RDC is 12, and the air injectors and the fuel injectors are uniformly distributed along the circumferential direction; the air and fuel injector mounting holes of the PDC and the RDC are both provided with taper pipe threads, and the thread types are the same as those of the taper pipe threads of the air and fuel injectors.
The invention has the further improvement that the flow disturbing device is of a spiral structure, and the outer diameter of the flow disturbing device is the same as the inner diameter of the PDC combustion cavity; in order to play a good turbulent flow effect, the ratio of the outer diameter of the spiral structure to the pitch of the spiral structure is about 5-8, the section of the spiral structure after being unfolded is a solid circle, and the ratio of the outer diameter of the spiral structure to the diameter of the solid circle is about 6: 1.
The further improvement of the invention is that the inner side of the outer wall surface of the PDC is provided with a cooling air film hole structure, 18 rows of cooling air film holes are uniformly distributed along the circumferential direction of the combustion chamber, 19 rows of cooling air film holes are uniformly distributed along the axial direction from the flow disturbing device to the outlet of the combustion chamber of the PDC, namely the number of the cooling air film holes is 342, the cooling air film holes are in a straight circular hole structure, and the included angle between the axial direction of the axis and the axial direction of the combustion chamber is 20 degrees.
The invention has the further improvement that the inner side and the outer side of the outer wall surfaces of the first-stage RDC and the second-stage RDC are respectively provided with a cooling air film hole structure, 18 rows are uniformly distributed along the circumferential direction of the combustion chamber, 5 rows are uniformly distributed along the axial direction, namely, the inner side and the outer side are respectively provided with 90 cooling air film holes, and the included angle between the axial direction of the cooling air film holes and the axial direction of the combustion chamber is 20 degrees.
The further improvement of the invention is that the inner side of the outer wall surface of the third stage RDC is provided with 90 cooling air film hole structures, 18 rows are uniformly distributed along the circumferential direction of the combustion chamber, 5 rows are uniformly distributed along the axial direction from the inlet of the combustion chamber of the third stage RDC to the outlet of the combustion chamber of the RDC, and the included angle between the axial direction of the cooling air film holes and the axial direction of the combustion chamber is 20 degrees.
The invention is further improved in that in order to prevent the airflow from forming a backflow area at the outlet of the combustion chamber and causing the flow loss of the burnt gas, the outer wall surface of the PDC and the outlets of the outer wall surfaces of the first-stage and the second-stage RDCs are all subjected to rounding treatment, and the thickness of the tail edge is close to 0.
The invention has at least the following beneficial technical effects:
according to the pulse detonation and rotation detonation combined type multi-channel combustion chamber, PDC and multi-stage RDC are combined, and a PDC combustion cavity, a first-stage RDC combustion cavity, a second-stage RDC combustion cavity and a third-stage RDC combustion cavity are formed in the center of the combustion chamber along the radius increasing direction. The beneficial technical effects are that firstly, the unsteady exhaust characteristic of the outlet of the detonation combustion chamber can be effectively weakened, and the exhaust pressure and the temperature spatial distribution are more uniform; secondly, the space utilization rate of the combustion chamber can be improved, and the volume of the combustion chamber is smaller under the condition of the same output power; finally, the total output power of the combustion chamber can be effectively controlled by adjusting whether the PDC and the RDC work or not, and the working flexibility of the combustion chamber is improved. Compared with the traditional PDC and RDC, the combustion chamber has the advantages that the structural form of the combustion chamber is optimized, the design is reasonable, the working stability of the combustion chamber can be improved, and the volume of the combustion chamber is reduced.
Drawings
FIG. 1 is a schematic structural diagram of a pulse detonation and rotation detonation combined multi-channel combustion chamber;
FIG. 2 is a sectional view of a pulse detonation and rotational detonation combined multi-channel combustion chamber A-A;
FIG. 3 is a schematic diagram of a pulse detonation combustor configuration;
FIG. 4 is a schematic view of a rotary detonation combustor;
fig. 5 is a structural view of an air and fuel injector, wherein fig. 5(b) is a sectional view of fig. 5 (a).
Description of reference numerals:
the combustion chamber comprises a PDC combustion chamber 1, a first-stage RDC combustion chamber 2, a second-stage RDC combustion chamber 3, a third-stage RDC combustion chamber 4, a PDC cover plate 5, a PDC outer wall surface 6, an RDC cover plate 7, a first-stage RDC outer wall surface 8, a second-stage RDC outer wall surface 9, a third-stage RDC outer wall surface 10, an air and fuel injector 11, an injector mounting hole 12, a PDC igniter 13, a turbulent flow device 14, a PDC cooling gas supply chamber 15, a PDC cooling gas film hole 16, an RDC igniter 17, an RDC cooling gas supply chamber 18, an RDC cooling gas film hole 19, a combustion chamber exhaust chamber 20, a fuel supply chamber 21, a fuel supply chamber 22, a fuel supply hole 23, an air supply chamber 24, an air supply annular seam 25 and taper pipe threads.
Detailed Description
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Referring to fig. 1 and 2, the pulse detonation and rotational detonation combined multi-channel combustion chamber provided by the invention comprises a PDC combustion chamber 1, a first-stage RDC combustion chamber 2, a second-stage RDC combustion chamber 3, a third-stage RDC combustion chamber 4, an air and fuel injector 11 and a combustion chamber exhaust chamber 20.
Referring to fig. 2, 3 and 5, the PDC combustion chamber 1 is located at the center of the multi-channel combustion chamber, and is a circular tube structure composed of a PDC cover plate 5 and a PDC outer wall surface 6, and the PDC cover plate 5 and the PDC outer wall surface 6 are fixedly connected at a contact surface by welding. The PDC cover plate 5 is positioned at the head of the PDC combustion chamber 1, is of a cylindrical structure, is provided with an injector mounting hole 12 at the center, and is of a straight round hole with conical threads. The air and fuel injectors 11 of the PDC are threadedly mounted in the injector mounting holes 12, and air and fuel are supplied into the PDC combustion chamber 1 through air supply annular slits 24 and fuel supply holes 22 inside the air and fuel injectors 11, respectively. The PDC igniter 13 is arranged in a mounting hole reserved on the outer wall surface 6 of the PDC, and the axial position of the PDC igniter is close to one side of the head of the PDC combustion cavity 1; the PDC igniter 13 is used for igniting the PDC combustion chamber 1 by filling fuel and air therein to form a slow-burning wave having a low reaction strength and a slow propagation speed, and the operating frequency of the PDC is controlled by the ignition frequency of the PDC igniter 13. The flow disturbing device 14 is arranged in the PDC combustion cavity 1, the axial position of the flow disturbing device is located on the left side of the PDC igniter 13, and in order to prevent the flow disturbing device 14 from moving axially in the working process of the combustion chamber, the flow burning device 14 is fixedly connected with the outer wall surface 6 of the PDC in a multipoint welding mode; the effect of vortex device 14 lies in, and the slow burning ripples that the combustion chamber head formed, when the vortex device, flow area constantly changes, and then becomes strong disturbance to the slow burning ripples wave, promotes the slow burning ripples at the short distance internal transfer to the detonation wave. Inside 6 outer wall surfaces of PDC, and axial position is located the 14 left sides of vortex device, has evenly distributed 18 rows of PDC cooling film holes 16 along circular combustion chamber circumference, and every row of cooling film holes has 19 rows along combustion chamber axial equipartition, and the axis direction and the axial contained angle of combustion chamber of cooling film holes are 20. The PDC cooling gas supply chamber 15 supplies the cooling gas required by the PDC cooling gas film hole 16, and the annular chamber-shaped PDC cooling gas supply chamber 15 is positioned inside the PDC outer wall surface 6.
Referring to fig. 2 and 4, the first-stage RDC combustion chamber 2 is located outside the PDC combustion chamber 1, and is an annular chamber structure composed of an RDC cover plate 7, a PDC outer wall surface 6, and a first-stage RDC outer wall surface 8, and the axial positions of the outlet sections of the first-stage RDC combustion chamber 2 and the PDC combustion chamber 1 are the same. The RDC cover plate 7 is located at the head of the first-stage RDC combustion chamber 2 and is of a circular ring structure, and the inner side of the RDC cover plate 7 is fixedly connected with the outer wall surface 6 of the PDC in a welding mode. RDC cooling air film holes 19 are arranged on the inner side and the outer side of the first-stage RDC outer wall surface 8, the number of the cooling air film holes on the inner side and the outer side is 90, 18 rows of cooling air film holes are uniformly distributed in the circumferential direction of the outer wall surface, 5 rows of cooling air film holes are uniformly distributed in the axial direction, and the included angle between the axial direction of each cooling air film hole and the axial direction of the combustion chamber is 20 degrees. The cooling gas required by the RDC cooling gas film hole 19 is supplied by an RDC cooling gas supply cavity 18 distributed in the inner part of the outer wall surface of the first-stage RDC, and the structure of the RDC cooling gas supply cavity is a circular ring cavity.
The second-stage RDC combustion chamber 3 is located on the outer side of the first-stage RDC combustion chamber 2, and is of an annular cavity structure consisting of an RDC cover plate 7, a first-stage RDC outer wall surface 8 and a second-stage RDC outer wall surface 9, and the axial positions of an inlet and an outlet of the first-stage RDC combustion chamber 2 and the second-stage RDC combustion chamber 3 are completely the same. The inner part of the outer wall surface 9 of the second-stage RDC is also provided with an annular RDC cooling air supply cavity 18, and the inner side and the outer side of the outer wall surface are both provided with 90 RDC cooling air film holes 19.
The third-stage RDC combustion chamber 4 is located on the outer side of the second-stage RDC combustion chamber 3, is of an annular cavity structure consisting of an RDC cover plate 7, a second-stage RDC outer wall surface 9 and a third-stage RDC outer wall surface 10, and the axial positions of an inlet and an outlet of the combustion chamber are completely the same as those of the first-stage RDC combustion chamber 2 and the second-stage RDC combustion chamber 3. An annular cavity-shaped RDC cooling gas supply cavity 18 is arranged inside the outer wall surface 10 of the third stage RDC, and 90 RDC cooling gas film holes are arranged on the inner side. The axial length of the third-stage RDC outer wall surface 10 is larger than that of the first-stage outer wall surface 8 and the second-stage RDC outer wall surface 9, and a contraction type circular truncated cone structure is adopted on one side close to the outlet of the combustion chamber, so that the third-stage RDC outer wall surface can play a good role in rectifying the burnt gas exhausted by each stage of detonation combustion chambers. The contact surfaces of the first-stage RDC outer wall surface 8, the second-stage RDC outer wall surface 9 and the third-stage RDC outer wall surface 10 and the RDC cover plate 7 are fixedly connected in a welding mode.
The RDC cover plate 7 is respectively arranged at three radial positions corresponding to the central positions of the first-stage, second-stage and third-stage RDC combustion chambers, 12 injector mounting holes 12 are uniformly distributed at each radial position along the circumferential direction, each injector mounting hole 12 is correspondingly provided with an air injector 11 and a fuel injector 11, the air injector and the fuel injector are connected through taper pipe threads, and air and fuel required by the RDC combustion chambers are supplied through annular gaps and jet hole structures of the air injector 11 and the fuel injectors 11. In addition, one RDC igniter 17 is disposed at each radial position, and since RDC requires only a single ignition to form a stably propagating rotating detonation wave, the RDC igniter ignites at the start of operation and does not require continuous ignition for stable operation.
The working cycle process of the invention is as follows:
the invention relates to a pulse detonation and rotation detonation combined type multi-channel combustion chamber, which obtains four different working modes by controlling whether different combustion chambers are ignited to work, wherein the combustion chamber of each working mode has different output powers and is respectively a low power mode, a medium power mode, a high power mode and a full load mode.
When the combustor works in a low-power mode, only air and fuel source supply valves corresponding to the first-stage RDC combustion chamber 2 are opened, and air and fuel are respectively supplied to the first-stage RDC combustion chamber 2 through an air injector 11 and a fuel injector 11; simultaneously supplying cooling gas to a PDC cooling gas supply cavity 15 and an RDC cooling gas supply cavity 18 inside the PDC outer wall surface 6 and the first-stage RDC outer wall surface 8, wherein the cooling gas enters the first-stage RDC combustion cavity 2 through an RDC cooling gas film hole 19 for cooling; when the first-stage RDC combustion cavity 2 is filled with sufficient fuel and air, the RDC igniter 17 corresponding to the first-stage RDC is started, the combustion cavity forms a stably-propagated slow combustion wave, and the RDC igniter 17 is closed; in the circumferential propagation process of the slow combustion wave along the combustion chamber, the slow combustion wave gradually develops into a stably propagated rotary detonation wave under the turbulent flow effect of the wall surface of the combustion chamber, and the stable work of a low-power mode is realized.
When the low-power mode work of the combustion chamber is finished, air and fuel supply of the first-stage RDC combustion cavity 2 is cut off, due to the fact that combustible mixtures are lacked to maintain continuous propagation of the rotary detonation wave, the rotary detonation wave is decoupled and becomes a slow combustion wave, then flames are gradually extinguished, meanwhile, the supply of cooling gas is turned off, and the low-power mode work of the combustion chamber is finished.
When the combustion chamber works in a medium-power mode, firstly, air and fuel source supply valves corresponding to a first-stage RDC combustion chamber 2 and a second-stage RDC combustion chamber 3 are opened, and fuel and air are filled into the first-stage RDC combustion chamber and the second-stage RDC combustion chamber; simultaneously, cooling gas is supplied to a PDC cooling gas supply cavity 15 inside the outer wall surface 6 of the PDC and an RDC cooling gas supply cavity 18 inside the outer wall surfaces 8 and 9 of the first-stage RDC and enters the first-stage RDC combustion cavity 2 and the second-stage RDC combustion cavity 3 through RDC cooling gas film holes 19 for cooling; after sufficient fuel and air are filled, 2 RDC igniters 17 corresponding to the first-stage and second-stage RDCs are simultaneously started, slow combustion waves propagating along the circumferential direction are formed in combustion chambers of the first-stage and second-stage RDCs, and the 2 RDC igniters 17 are closed; the slow combustion wave is gradually converted into rotary detonation wave through the disturbance of the wall surface of the combustion chamber, the rotary detonation wave which is stably propagated is respectively generated in the first-stage RDC combustion cavity 2 and the second-stage RDC combustion cavity 3, and the stable work of a medium-power mode is realized in the combustion chamber.
When the power mode operation in the combustor is finished, the air and fuel supply of the first stage RDC combustion chamber 2 and the second stage RDC combustion chamber 3 is cut off simultaneously, then the flame is gradually extinguished, the supply of cooling gas is cut off simultaneously, and the middle power mode operation in the combustor is finished.
When the combustion chamber works in a high-power mode, firstly, air and fuel air source supply valves corresponding to the first-stage RDC combustion chamber 2, the second-stage RDC combustion chamber 3 and the third-stage RDC combustion chamber 4 are opened, and fuel and air are respectively filled into the first-stage RDC combustion chamber, the second-stage RDC combustion chamber and the third-stage RDC combustion chamber; meanwhile, cooling gas is supplied to a PDC cooling gas supply cavity 15 inside the outer wall surface 6 of the PDC and RDC cooling gas supply cavities 18 inside the outer wall surfaces 8, 9 and 10 of the first stage RDC, and the second stage RDC and the third stage RDC enter the combustion cavity 2, 3 and 4 of the first stage RDC through RDC cooling gas film holes 19 for cooling; after sufficient fuel and air are filled, 3 RDC igniters 17 corresponding to the first-stage, second-stage and third-stage RDCs are simultaneously started, slow combustion waves propagating along the circumferential direction are formed in the combustion cavities of the three-stage RDCs, and the RDC igniters 17 are closed; and then, through the turbulent flow effect of the wall surface of the combustion chamber, the slow combustion wave is gradually converted into the rotary detonation wave, the rotary detonation waves which are stably propagated are respectively generated in the three-level RDC combustion chamber, and the combustion chamber realizes the stable work of a high-power mode.
When the high-power mode operation of the combustor is finished, air and fuel supply of the first-stage, second-stage and third-stage RDC combustion chambers is cut off simultaneously, then the flame is gradually extinguished, meanwhile, the supply of cooling gas is closed, and the high-power mode operation of the combustor is finished.
When the combustion chamber works in a full-load mode, firstly, air and fuel gas source supply valves corresponding to a PDC combustion chamber 1, a first-stage RDC combustion chamber 2, a second-stage RDC combustion chamber 3 and a third-stage RDC combustion chamber 4 are opened; meanwhile, cooling gas is supplied to a PDC cooling gas supply cavity 15 inside the outer wall surface 6 of the PDC and an RDC cooling gas supply cavity 18 inside the outer wall surfaces 8, 9 and 10 of the first-stage RDC, and enters the PDC combustion cavity 1, the first-stage RDC combustion cavity 2, the second-stage RDC combustion cavity 3 and the third-stage RDC combustion cavity 4 for cooling through PDC cooling gas film holes 16 and 19; after sufficient fuel and air are charged, simultaneously starting 3 RDC igniters 17 and PDC igniters 13 corresponding to the first, second and third stage RDCs; the slow-burning wave propagating along the circumferential direction is formed in the RDC combustion cavity, the RDC igniter 17 is closed, then the slow-burning wave in the three-stage RDC combustion cavity is gradually changed into the rotary detonation wave propagating stably through the wall surface turbulence effect, and the three-stage RDC combustion cavity realizes stable work.
After the PDC igniter 13 is ignited, a slow combustion wave propagating along the axial direction is also formed in the PDC combustion cavity 1, and the PDC igniter 13 is closed; when the slow combustion wave is transmitted to the turbulence device, the slow combustion wave is strongly disturbed by the turbulence device and can be quickly converted into an explosion wave transmitted along the axial direction, the pressure of the combustion chamber rapidly exceeds the supply pressure of air and fuel, and the supply of the air and the fuel is stopped; the detonation wave then propagates to the combustion chamber outlet, with most of the detonation wave burned gases also exiting the combustion chamber, the combustion chamber pressure gradually falls below the supply pressure of air and fuel, and the 1 PDC duty cycle ends. When the combustion chamber pressure is reduced, the air and fuel are then refilled, and after sufficient fuel and air are refilled in the PDC combustion chamber 1, the PDC igniter 13 is turned on again, and the work cycle of the previous PDC is repeated. When the RDC is operating in a steady state process, the PDC repeats the pulse-like duty cycle continuously, and the operating frequency of the PDC can be controlled by controlling the firing frequency of the PDC igniter 13. At this time, the combustion chamber achieves a stable operation in a full load mode.
When the full-load mode work of the combustion chamber is finished, air and fuel supply of the first-stage RDC combustion chamber, the second-stage RDC combustion chamber, the third-stage RDC combustion chamber and the PDC combustion chamber is cut off simultaneously, then the flame is gradually extinguished, meanwhile, the supply of cooling gas is closed, and the full-load mode work of the combustion chamber is finished.
It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Claims (8)
1. The utility model provides a pulse detonation and rotatory detonation combination formula multichannel combustion chamber which characterized in that, includes PDC combustion chamber, first order RDC combustion chamber, second level RDC combustion chamber, third level RDC combustion chamber, air and fuel injector and combustion chamber exhaust chamber:
the PDC combustion cavity is positioned in the center of the combustion chamber and is of a circular tubular structure consisting of a PDC cover plate and a PDC outer wall surface, and the contact surface of the PDC outer wall surface and the PDC cover plate fixes the PDC outer wall surface on the PDC cover plate;
the air and fuel injector of the PDC is positioned in the central position of the PDC cover plate, fuel is supplied to the PDC combustion cavity through the jet hole structure, and air is supplied to the PDC combustion cavity through the annular seam structure;
the PDC igniter is arranged on the outer wall surface of the PDC and is close to one side of the head part of the combustion cavity, the installation direction is vertical to the axial direction of the combustion cavity, the PDC cooling gas supply cavity and the cooling gas film hole are arranged in the outer wall surface of the PDC, and the included angle between the axial direction of the PDC cooling gas film hole and the axial direction of the combustion chamber is 20 degrees;
the turbulence device is positioned in the PDC combustion cavity, is close to one side of the head and is of a spiral structure, the axial direction of the spiral structure is consistent with the axial direction of the combustion cavity, and the turbulence device is fixed in the combustion cavity to prevent the turbulence device from moving along the axial direction;
the first-stage RDC combustion chamber is positioned outside the PDC combustion chamber and is of an annular cavity structure consisting of an RDC cover plate, a PDC outer wall surface and a first-stage RDC outer wall surface, and the axial positions of the outlet of the first-stage RDC combustion chamber and the outlet of the PDC combustion chamber are the same;
the second-stage RDC combustion chamber and the third-stage RDC combustion chamber are sequentially distributed on the outer side of the first-stage RDC combustion chamber and are all of annular cavity structures, and the axial positions of the inlet and the outlet of the first-stage RDC combustion chamber, the second-stage RDC combustion chamber and the third-stage RDC combustion chamber are completely the same; the air and fuel injectors and igniters of each stage of RDC are positioned on the RDC cover plate; RDC cooling air supply cavities and cooling air film holes are formed in the outer wall surfaces of the first-stage, the second-stage and the third-stage RDCs, and the axial included angle between the axial direction of each cooling air film hole and the axial direction of the combustion chamber is 20 degrees;
the combustion chamber exhaust cavity is positioned at one side of outlets of the PDC and the RDC, and the combustion chamber exhaust cavity is of a hollow shrinkage type circular truncated cone structure.
2. The pulse detonation and rotary detonation combined multi-channel combustion chamber as claimed in claim 1, wherein the air and fuel injector is of a dual-channel cylindrical structure, the fuel supply cavity is centrally located and of a cylindrical cavity structure, 4 fuel supply holes are formed in the outlet end face of the fuel supply cavity and are uniformly distributed along the circumferential direction, the fuel supply holes are of a straight circular hole structure, and an included angle between the axial direction and the axial direction of the combustion chamber is 45 degrees; the outer side of the fuel supply cavity is provided with an air supply annular cavity which is of an annular cavity-shaped structure, the outlet of the air supply cavity is provided with a contraction and expansion molded surface, the minimum flow area of the contraction molded surface is adjusted to control the supply flow of air, and the contraction molded surface and the expansion molded surface are in circular arc transition; in order to facilitate the installation and the disassembly of the air and fuel injector, taper pipe threads are arranged on the outer side of the injector.
3. The combined pulse detonation and rotary detonation multi-channel combustion chamber of claim 2, wherein a PDC cover plate is centered on an injector mounting hole; the RDC cover plate is respectively provided with injector mounting holes at three radial positions, namely the central positions of the first-stage, second-stage and third-stage RDC combustion chambers; the number of air injectors and fuel injectors of each stage of RDC is 12, and the air injectors and the fuel injectors are uniformly distributed along the circumferential direction; the air and fuel injector mounting holes of the PDC and the RDC are both provided with taper pipe threads, and the thread types are the same as those of the taper pipe threads of the air and fuel injectors.
4. The combined pulse detonation and rotary detonation multi-channel combustion chamber of claim 1, wherein the flow perturbation device is of a spiral structure, and the outer diameter of the flow perturbation device is the same as the inner diameter of the PDC combustion cavity; in order to play a good turbulent flow effect, the ratio of the outer diameter of the spiral structure to the pitch of the spiral structure is about 5-8, the section of the spiral structure after being unfolded is a solid circle, and the ratio of the outer diameter of the spiral structure to the diameter of the solid circle is about 6: 1.
5. The pulse detonation and rotary detonation combined multi-channel combustion chamber as claimed in claim 1, wherein cooling film hole structures are arranged on the inner side of the outer wall surface of the PDC, 18 rows are uniformly distributed along the circumferential direction of the combustion chamber, 19 rows are uniformly distributed from the flow disturbing device to the outlet of the combustion chamber of the PDC along the axial direction, that is, the number of the cooling film holes is 342, the cooling film holes are of straight circular hole structures, and the included angle between the axial direction and the axial direction of the combustion chamber is 20 °.
6. The pulse detonation and rotary detonation combined multi-channel combustion chamber as claimed in claim 1, wherein cooling film hole structures are arranged on the inner and outer sides of the outer wall surfaces of the first stage and the second stage RDCs, 18 rows are uniformly distributed along the circumferential direction of the combustion chamber, 5 rows are uniformly distributed along the axial direction, that is, 90 cooling film holes are respectively arranged on the inner and outer sides, and the included angle between the axial direction of the cooling film holes and the axial direction of the combustion chamber is 20 °.
7. The pulse detonation and rotary detonation combined multi-channel combustion chamber as claimed in claim 1, wherein 90 cooling film hole structures are arranged on the inner side of the outer wall surface of the third-stage RDC, 18 rows are uniformly distributed along the circumferential direction of the combustion chamber, 5 rows are uniformly distributed from the inlet of the third-stage RDC combustion chamber to the outlet of the RDC combustion chamber along the axial direction, and the included angle between the axial direction of the cooling film holes and the axial direction of the combustion chamber is 20 degrees.
8. The combined pulse detonation and rotational detonation multi-channel combustor of claim 1, wherein the outer wall of the PDC and the outer wall of the first and second stage RDCs are rounded at the outlets to prevent backflow at the combustion chamber outlet and thereby to prevent flow losses of combusted gases, and the thickness of the trailing edge is approximately 0.
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114811654A (en) * | 2022-06-15 | 2022-07-29 | 清航空天(北京)科技有限公司 | Pressure-stabilizing flow-equalizing self-cooling continuous rotation detonation ramjet engine with radial oil supply |
| CN114963239A (en) * | 2022-05-12 | 2022-08-30 | 西北工业大学 | Rotary detonation combustion device for staged combustion |
| CN115342381A (en) * | 2022-07-26 | 2022-11-15 | 清航空天(北京)科技有限公司 | Detonation combustion chamber module and detonation combustion chamber |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2721530A1 (en) * | 2009-11-30 | 2011-05-30 | General Electric Company | Thrust modulation in a multiple combustor pulse detonation engine using cross-combustor detonation initiation |
| CN104153884A (en) * | 2014-08-06 | 2014-11-19 | 西安热工研究院有限公司 | Rotary knocking gas turbine |
| CN203962199U (en) * | 2014-06-04 | 2014-11-26 | 西安热工研究院有限公司 | A kind of high-frequency pulse pinking combustion-powered apparatus |
| CN109154441A (en) * | 2016-05-23 | 2019-01-04 | 赛峰集团 | Toroidal combustion chamber with continuous detonation wave |
| CN111520746A (en) * | 2019-02-05 | 2020-08-11 | 通用电气公司 | Rotary detonation combustor with discrete detonation annulus |
-
2021
- 2021-11-19 CN CN202111402143.1A patent/CN113932252B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2721530A1 (en) * | 2009-11-30 | 2011-05-30 | General Electric Company | Thrust modulation in a multiple combustor pulse detonation engine using cross-combustor detonation initiation |
| CN203962199U (en) * | 2014-06-04 | 2014-11-26 | 西安热工研究院有限公司 | A kind of high-frequency pulse pinking combustion-powered apparatus |
| CN104153884A (en) * | 2014-08-06 | 2014-11-19 | 西安热工研究院有限公司 | Rotary knocking gas turbine |
| CN109154441A (en) * | 2016-05-23 | 2019-01-04 | 赛峰集团 | Toroidal combustion chamber with continuous detonation wave |
| CN111520746A (en) * | 2019-02-05 | 2020-08-11 | 通用电气公司 | Rotary detonation combustor with discrete detonation annulus |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114963239A (en) * | 2022-05-12 | 2022-08-30 | 西北工业大学 | Rotary detonation combustion device for staged combustion |
| CN114811654A (en) * | 2022-06-15 | 2022-07-29 | 清航空天(北京)科技有限公司 | Pressure-stabilizing flow-equalizing self-cooling continuous rotation detonation ramjet engine with radial oil supply |
| CN114811654B (en) * | 2022-06-15 | 2022-09-23 | 清航空天(北京)科技有限公司 | Pressure-stabilizing flow-equalizing self-cooling continuous rotation detonation ramjet engine with radial oil supply |
| CN115342381A (en) * | 2022-07-26 | 2022-11-15 | 清航空天(北京)科技有限公司 | Detonation combustion chamber module and detonation combustion chamber |
| CN115342382A (en) * | 2022-07-26 | 2022-11-15 | 清航空天(北京)科技有限公司 | Single-channel oxygen supply detonation combustion chamber module and detonation combustion chamber |
| CN115355543A (en) * | 2022-08-19 | 2022-11-18 | 西北工业大学 | A composite rotary detonation combustion device |
| CN115355543B (en) * | 2022-08-19 | 2023-10-10 | 西北工业大学 | A composite rotating detonation combustion device |
| CN115628449A (en) * | 2022-12-20 | 2023-01-20 | 中国空气动力研究与发展中心超高速空气动力研究所 | Gas-liquid coaxial centrifugal nozzle in assembly structure |
| CN115628449B (en) * | 2022-12-20 | 2023-03-10 | 中国空气动力研究与发展中心超高速空气动力研究所 | Gas-liquid coaxial centrifugal nozzle in assembly structure |
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