CN115218224B - Cooling structure suitable for pulse detonation combustor - Google Patents
Cooling structure suitable for pulse detonation combustor Download PDFInfo
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- CN115218224B CN115218224B CN202210910139.4A CN202210910139A CN115218224B CN 115218224 B CN115218224 B CN 115218224B CN 202210910139 A CN202210910139 A CN 202210910139A CN 115218224 B CN115218224 B CN 115218224B
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- detonation
- combustion chamber
- heat exchange
- cooling medium
- detonation combustion
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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
- F23R7/00—Intermittent or explosive combustion chambers
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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
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03043—Convection cooled combustion chamber walls with means for guiding the cooling air flow
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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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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
Abstract
The invention discloses a cooling structure suitable for a pulse detonation combustion chamber, which comprises a detonation combustion chamber, a high-efficiency heat exchange cavity and a common heat exchange cavity. The detonation combustion chamber is a sealed straight circular tube with one end closed and the other end open, and is internally provided with a Shchelkin spiral explosion-increasing barrier with a cooling channel, and the detonation combustion chamber has the function of reducing the time and distance from detonation to detonation transition (DDT for short). DDT section heat transfer is strong, and wall temperature is higher, therefore adopts high-efficient heat transfer chamber to carry out sectional type forced convection cooling to it. Taking the wall temperature distribution of the detonation combustor into consideration, the common heat exchange cavity is adopted to perform forced convection cooling on other hot end components of the detonation combustor. The invention can obviously reduce the temperature of the hot end component of the detonation combustor and the Shchelkin spiral explosion-increasing barrier, prolong the service life of the detonation combustor, avoid continuous combustion phenomenon caused by overhigh wall temperature of the combustor and effectively improve the detonation combustion stability.
Description
Technical Field
The invention relates to the field of detonation combustion, in particular to a cooling structure suitable for a pulse detonation combustion chamber.
Background
Pulse detonation combustion is an unsteady combustion mode that utilizes intermittent detonation waves to generate thrust. Research shows that compared with common slow combustion, detonation combustion has the advantages of strong chemical reaction, high thermal cycle efficiency and the like, and is particularly suitable for the power source of aviation, aerospace and navigation devices and the field of thermal spraying. However, each field of application places severe restrictions on the highest temperatures that can be tolerated by the materials, excessive temperatures tend to cause continuous combustion of the fuel, even with safety hazards during operation of the device, and therefore effective cooling of the device is critical. At present, the cooling means for pulse detonation combustion are not sufficient, limiting their further application.
Along with the development of the industrial field, the pulse detonation combustion technology is expected to be applied to various energy industries in the future, meanwhile, a detonation combustion device with high performance (such as high-frequency detonation combustion) tends to put a stricter limit on the wall surface temperature, and the traditional cooling mode is difficult to meet the performance requirement of the device, so that an efficient cooling mode is needed to reduce the wall surface temperature of the device.
Disclosure of Invention
The invention aims to provide a cooling structure suitable for a pulse detonation combustor.
The invention is realized by adopting the following technical scheme:
a cooling structure suitable for pulse detonation combustor comprises a detonation combustor, a high-efficiency heat exchange cavity and a common heat exchange cavity;
the detonation combustion chamber is a sealed straight circular pipe with one end closed and the other end open, a Shchelkin spiral explosion-increasing barrier with a cooling channel is arranged in the detonation combustion chamber, the detonation combustion chamber is used for reducing the time and distance from detonation to detonation transition DDT, the internal cooling channel of the Shchelkin spiral explosion-increasing barrier is used for reducing the wall surface temperature of the detonation combustion chamber, the high-efficiency heat exchange cavity is coaxially welded on the outer wall surface of the detonation combustion chamber, the axial length and the axial position are the same as those of the Shchelkin spiral explosion-increasing barrier, the high-efficiency heat exchange cavity is used for reducing the wall surface temperature of the DDT section of the detonation combustion chamber, and the common heat exchange cavity is coaxially welded on the other outer wall surfaces of the detonation combustion chamber and used for reducing the temperature of other hot end parts of the detonation combustion chamber.
The invention further improves that the DDT section of the detonation combustion chamber and the Shchelkin spiral explosion-increasing barrier are integrally manufactured and formed by adopting a casting process or an additive manufacturing technology.
The invention is further improved in that the outer diameter of the Shchelkin spiral explosion-increasing barrier is equal to the inner diameter of the detonation combustion chamber, the linear diameter is 0.15-0.25 times of the inner diameter of the detonation combustion chamber, the diameter of the internal cooling channel is 1-2 mm, and the internal cooling channel is provided with longitudinal micro fins to strengthen heat transfer and improve the structural strength of the internal cooling channel.
The invention is further improved in that the head end and the tail end of the Shchelkin spiral explosion-increasing barrier are in seamless connection with the inner wall surface of the detonation combustion chamber, the external contour of the section of the Shchelkin spiral explosion-increasing barrier is square and fan-shaped, a space is reserved for the cooling medium supply hole and the cooling medium discharge hole, and the external contour of the section of the rest part is round.
According to the invention, the cooling medium supply hole is positioned in the last section of the efficient heat exchange cavity far away from the closed end of the detonation combustion chamber and is close to one side of the cooling medium inlet, and the cooling medium discharge hole is positioned in the first section of the efficient heat exchange cavity close to the closed end of the detonation combustion chamber and is close to one side of the cooling medium outlet, so that fresh cooling medium can be ensured to be stably supplied into the Shchelkin spiral explosion increasing barrier and discharged.
The invention is further improved in that the high-efficiency heat exchange cavity is internally provided with a combined fin formed by annular fins and longitudinal fins, which is used for increasing the convection heat exchange area and reducing the wall temperature of the DDT section of the detonation combustion chamber.
The invention is further improved in that the annular fins are connected to the outer wall surface of the detonation combustion chamber and the inner wall surface of the efficient heat exchange cavity in a spiral manner, the cooling medium is forced to flow in a specified direction, the longitudinal fins are distributed on two sides of the annular fins in a staggered manner, the corners of the longitudinal fins are rounded, the flow loss of the cooling medium is reduced, the pitch of the annular fins is used for ensuring that the longitudinal fins on two adjacent annular fins are not contacted, and the space is increased for the flow of the cooling medium.
The invention is further improved in that the efficient heat exchange cavity is of a sectional cooling structure, a plurality of efficient heat exchange cavities are uniformly distributed along the axial direction of the DDT section of the detonation combustion chamber, and cooling media flow independently, so that the cooling effect is enhanced.
The invention is further improved in that a plurality of longitudinal wavy fins are arranged in the common heat exchange cavity and are uniformly distributed along the circumferential direction of the outer wall surface of the detonation combustion chamber, and the surfaces of the longitudinal wavy fins are continuously and uniformly distributed so as to reduce the flow loss of cooling medium.
The invention has at least the following beneficial technical effects:
the invention adopts a sectional forced convection cooling mode to efficiently cool the DDT section with strong heat exchange in the detonation combustion chamber. The cooling mediums are mutually independent when flowing in different efficient heat exchange cavities, so that the heat exchange effect is enhanced; annular fins and longitudinal fins in the efficient heat exchange cavity are arranged in a combined mode, the convection heat exchange area can be remarkably increased, and the wall temperature of the DDT section of the detonation combustion chamber is effectively reduced.
The microchelkin spiral explosion-increasing barrier is internally provided with the miniature cooling channel, so that heat exchange can be enhanced by utilizing a microscale effect, and meanwhile, the inside of the barrier is provided with the longitudinal fins, so that the structural strength is improved, the convection heat exchange area is increased, and the surface temperature of the barrier is effectively reduced.
In consideration of uniformity of temperature distribution of the detonation combustor wall surface, the rest hot end components of the detonation combustor are cooled by adopting a forced convection cooling mode. The wave-shaped fins uniformly distributed along the circumferential direction are arranged in the common heat exchange cavity, so that the heat exchange area is increased, and the heat exchange effect is improved.
The invention adopts a high-efficiency cooling scheme, can effectively reduce the wall temperature of the hot end part, prolongs the service life of the hot end part, and simultaneously avoids continuous combustion phenomenon and potential safety hazard caused by over-temperature of the wall.
In summary, the invention respectively sets a reasonable and effective cooling structure for different hot end components of the detonation combustion chamber, can reduce the wall temperature, prolong the service life, avoid continuous combustion phenomenon and obviously improve the detonation combustion stability.
Drawings
FIG. 1 is an isometric schematic diagram of a cooling scheme suitable for use with a pulse detonation combustor;
FIG. 2 is an axial cross-sectional view of a cooling scheme suitable for use with a pulse detonation combustor;
FIG. 3 is a schematic cross-sectional view of a Shchelkin spiral explosion-enhancing barrier;
FIG. 4 is a schematic cross-sectional view of a modular fin.
Reference numerals illustrate:
1 is a detonation combustion chamber, 2 is a Shchelkin spiral explosion-increasing barrier, 3 is a high-efficiency heat exchange cavity, 4 is a common heat exchange cavity, 5 is a micro fin, 6 is a combined fin, 7 is a wave-shaped fin, 8 is a fuel supply cavity, 9 is an igniter, 12 is a cooling medium supply hole, 13 is a cooling medium discharge hole, 6-1 is an annular fin, 6-2 is a longitudinal fin, 10-1 is a first cooling medium inlet, 10-2 is a second cooling medium inlet, 10-3 is a third cooling medium inlet, 10-4 is a fourth cooling medium inlet, 11-1 is a first cooling medium outlet, 11-2 is a second cooling medium outlet, 11-3 is a third cooling medium outlet, and 11-4 is a fourth cooling medium outlet.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art. It should be noted that, without conflict, the embodiments of the present invention and features of the embodiments may be combined with each other. The invention will be described in detail below with reference to the drawings in connection with embodiments.
As shown in fig. 1 and 2, the invention provides a cooling structure suitable for a pulse detonation combustion chamber, which mainly comprises a detonation combustion chamber 1, a high-efficiency heat exchange cavity 3 and a common heat exchange cavity 4. The detonation combustion chamber 1 is a sealed straight circular tube with one end closed and the other end open, and is internally provided with a Shchelkin spiral explosion-increasing barrier 2 with a cooling channel, and the function of the explosion-increasing barrier is to reduce the time and distance from detonation to detonation transition DDT. The internal cooling channel of the Shchelkin spiral explosion-increasing barrier 2 is used for reducing the surface temperature of the barrier. The high-efficiency heat exchange cavity 3 is coaxially welded on the outer wall surface of the detonation combustion chamber 1, the axial length and the axial position of the high-efficiency heat exchange cavity are the same as those of the Shchelkin spiral explosion-increasing barrier 2, and the high-efficiency heat exchange cavity is used for reducing the temperature of the wall surface of the DDT section of the detonation combustion chamber 1. The common heat exchange cavity 4 is coaxially welded on the other outer wall surfaces of the detonation combustion chamber 1 and is used for reducing the temperature of the other hot end components of the detonation combustion chamber 1.
The high-efficiency heat exchange cavity 3 is divided into a plurality of sections, the number of the sections is properly regulated by the length of the Shchelkin spiral explosion-increasing barrier 2 and the detonation combustion frequency, each section is provided with a cooling medium inlet and a cooling medium outlet which are independent, the axial speed of the cooling medium flowing in the high-efficiency heat exchange cavity 3 is opposite to the discharging direction of burnt gas, the heat exchange effect is enhanced, the cooling medium inlet comprises a first cooling medium inlet 10-1, a second cooling medium inlet 10-2, a third cooling medium inlet 10-3 and a fourth cooling medium inlet 10-4, and the cooling medium outlet comprises a first cooling medium outlet 11-1, a second cooling medium outlet 11-2, a third cooling medium outlet 11-3 and a fourth cooling medium outlet 11-4. A cooling medium supply hole 12 and a cooling medium discharge hole 13 are reserved on the wall surface of the detonation combustion chamber 1, wherein the cooling medium supply hole 12 is positioned in the last section of the high-efficiency heat exchange cavity 3 far away from the closed end of the detonation combustion chamber 1 and is close to one side of the cooling medium inlet; the cooling medium discharge hole 13 is positioned in the first section of the high-efficiency heat exchange cavity 3 near the closed end of the detonation combustor 1 and near the side of the cooling medium outlet. The cooling medium supply hole 12 is used for supplying cooling medium to the internal cooling channel of the Shchelkin spiral explosion-increasing barrier 2, the axial speed of the cooling medium flowing in the channel is opposite to the discharging direction of burnt gas, so that the heat exchange with the wall surface of the Shchelkin spiral explosion-increasing barrier 2 can be enhanced, the heat of the wall surface is taken away, the cooling medium flows into the efficient heat exchange cavity 3 through the cooling medium discharge hole 13, and finally the cooling medium and the cooling medium in the efficient heat exchange cavity 3 are discharged together.
The combined fins 6 consisting of the annular fins 6-1 and the longitudinal fins 6-2 in the efficient heat exchange cavity 3 can be independently processed and then welded and installed on the outer wall surface of the detonation combustion chamber 1, and can also be integrally manufactured and formed with the DDT section of the detonation combustion chamber 1 and the Shchelkin spiral explosion-increasing barrier 2 based on a casting process or an additive manufacturing technology, and the combined fins have high enough strength to ensure that the Shchelkin spiral explosion-increasing barrier 2 cannot be deformed and damaged during detonation combustion.
The number of the longitudinal micro fins 5 in the internal channel of the Shchelkin spiral explosion-increasing barrier 2 is properly adjusted by the detonation combustion frequency, so that the wall temperature of the Shchelkin spiral explosion-increasing barrier 2 is ensured to meet the working requirement.
The common heat exchange cavity 4 is provided with the cooling medium inlet and the cooling medium outlet, and the axial speed of the cooling medium flowing in the common heat exchange cavity 4 is opposite to the discharging direction of the burnt gas, so that the heat exchange effect is enhanced. The number of the longitudinal wavy fins 7 is appropriately adjusted by the knocking combustion frequency.
As shown in fig. 1 and 2, fuel required for detonation combustion is supplied to a detonation combustion chamber 1 from a fuel supply cavity 8, is ignited by an igniter 9 to generate slow combustion, and is converted into detonation combustion under the action of a Shchelkin spiral explosion-increasing barrier 2, so that detonation is formed and then discharged from an outlet together with burnt gas. As detonation combustion duration increases, so does the heat build up by the hot side components. In the process, the Shchelkin spiral explosion-increasing barrier 2 has strong heat exchange and higher temperature rise, and the cooling medium flowing in the Shchelkin spiral explosion-increasing barrier continuously exchanges heat with the wall surface of the Shchelkin spiral explosion-increasing barrier, so that the heat of the wall surface of the Shchelkin spiral explosion-increasing barrier is continuously taken away, and the temperature of the wall surface of the Shchelkin spiral explosion-increasing barrier is maintained in a normal range. Furthermore, the Shchelkin spiral explosion-increasing barrier 2 is located in the DDT section of the detonation combustor 1, which section has a similarly high wall temperature rise. The cooling mediums in the high-efficiency heat exchange cavities 3 of the sections are mutually independent, and are continuously in heat exchange with the wall surface of the detonation combustion chamber 1 and the combined fins 6 in the respective heat exchange cavities, so that the DDT sections are subjected to sectional cooling, the heat exchange effect is enhanced, and the wall surface temperature of the DDT sections is effectively reduced. The common heat exchange cavity 4 cools the hot end parts with lower temperature rise, reduces the wall temperature, ensures that the temperature distribution of the wall surface of the detonation combustion chamber 1 is in a reasonable range, and prolongs the service life of materials. The cooling medium may be a fluid such as air or liquid water.
The invention is based on a high-efficiency cooling scheme, can effectively reduce the temperature of the hot end part of the pulse detonation combustion chamber, prolongs the service life of the hot end part, and simultaneously avoids continuous combustion phenomenon and potential safety hazard caused by wall surface overtemperature.
While the invention has been described in detail in the foregoing general description and with reference to specific embodiments thereof, it will be apparent to one skilled in the art that modifications and improvements can be made thereto. Accordingly, such modifications or improvements may be made without departing from the spirit of the invention and are intended to be within the scope of the invention as claimed.
Claims (3)
1. The cooling structure suitable for the pulse detonation combustion chamber is characterized by comprising a detonation combustion chamber (1), a high-efficiency heat exchange cavity (3) and a common heat exchange cavity (4);
the detonation combustion chamber (1) is a sealed straight circular tube with one end closed and the other end open, a Shchelkin spiral explosion-increasing barrier (2) with a cooling channel is arranged in the detonation combustion chamber, the detonation combustion chamber is used for reducing the time and distance from detonation to the detonation transition DDT, the internal cooling channel of the Shchelkin spiral explosion-increasing barrier (2) is used for reducing the wall surface temperature of the detonation combustion chamber, the high-efficiency heat exchange cavity (3) is coaxially welded on the outer wall surface of the detonation combustion chamber (1), the axial length and the axial position are the same as those of the Shchelkin spiral explosion-increasing barrier (2), the Shchelkin spiral explosion-increasing barrier is used for reducing the wall surface temperature of the DDT section of the detonation combustion chamber (1), and the common heat exchange cavity (4) is coaxially welded on the other outer wall surfaces of the detonation combustion chamber (1) and is used for reducing the temperature of other hot end parts of the detonation combustion chamber (1).
The outer diameter of the Shchelkin spiral explosion-increasing barrier (2) is equal to the inner diameter of the detonation combustion chamber (1), the linear diameter is 0.15-0.25 times of the inner diameter of the detonation combustion chamber (1), the diameter of the internal cooling channel is 1-2 mm, and the internal cooling channel is provided with longitudinal micro fins (5) for enhancing heat transfer and improving the structural strength of the internal cooling channel;
the head end and the tail end of the Shchelkin spiral explosion-increasing barrier (2) are in seamless connection with the inner wall surface of the detonation combustion chamber (1), the external profile of the section of the barrier is square and fan-shaped, a space is reserved for the cooling medium supply hole (12) and the cooling medium discharge hole (13), and the external profile of the section of the rest part is circular;
the efficient heat exchange cavity (3) is internally provided with a combined fin (6) formed by annular fins (6-1) and longitudinal fins (6-2) for increasing the convection heat exchange area and reducing the wall temperature of the DDT section of the detonation combustion chamber (1);
the annular fins (6-1) are spirally connected to the outer wall surface of the detonation combustion chamber (1) and the inner wall surface of the efficient heat exchange cavity (3), a cooling medium is forced to flow in a specified direction, the longitudinal fins (6-2) are distributed on two sides of the annular fins (6-1) in a staggered mode, round corner rounding treatment is carried out on corners of the longitudinal fins (6-2), flow loss of the cooling medium is reduced, the pitch of the annular fins (6-1) is used for ensuring that the longitudinal fins (6-2) on two adjacent annular fins (6-1) are not contacted, and a space is increased for the flow of the cooling medium;
the efficient heat exchange cavities (3) are of a sectional cooling structure, the efficient heat exchange cavities (3) are uniformly distributed along the DDT section of the detonation combustion chamber (1) in the axial direction, each section is provided with an independent cooling medium inlet and a cooling medium outlet, the axial speed of the cooling medium flowing in the efficient heat exchange cavities (3) is opposite to the discharging direction of the burnt gas, and the cooling effect is enhanced;
the cooling medium supply hole (12) is positioned in the last section of the efficient heat exchange cavity (3) far away from the closed end of the detonation combustion chamber (1) and is close to one side of the cooling medium inlet, the cooling medium discharge hole (13) is positioned in the first section of the efficient heat exchange cavity (3) close to the closed end of the detonation combustion chamber (1) and is close to one side of the cooling medium outlet, and fresh cooling medium can be ensured to be stably supplied to the inside of the Shchelkin spiral explosion increasing barrier (2) and discharged.
2. A cooling structure suitable for pulse detonation combustor according to claim 1, characterized in that DDT section of said detonation combustor (1) is integrally formed with said Shchelkin spiral detonation disorder (2) by casting process or additive manufacturing technology.
3. The cooling structure for the pulse detonation combustor according to claim 1, wherein a plurality of longitudinal wavy fins (7) are arranged in the common heat exchange cavity (4), the longitudinal wavy fins are uniformly distributed along the circumferential direction of the outer wall surface of the detonation combustor (1), and the surfaces of the longitudinal wavy fins (7) are continuously and uniformly distributed so as to reduce the flow loss of cooling medium.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210910139.4A CN115218224B (en) | 2022-07-29 | 2022-07-29 | Cooling structure suitable for pulse detonation combustor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210910139.4A CN115218224B (en) | 2022-07-29 | 2022-07-29 | Cooling structure suitable for pulse detonation combustor |
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| Publication Number | Publication Date |
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| CN115218224A CN115218224A (en) | 2022-10-21 |
| CN115218224B true CN115218224B (en) | 2023-06-20 |
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| CN202210910139.4A Active CN115218224B (en) | 2022-07-29 | 2022-07-29 | Cooling structure suitable for pulse detonation combustor |
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Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110047962A1 (en) * | 2009-08-28 | 2011-03-03 | General Electric Company | Pulse detonation combustor configuration for deflagration to detonation transition enhancement |
| WO2011035444A1 (en) * | 2009-09-25 | 2011-03-31 | Exponential Technologies, Inc | Pressure gain combustion heat generator |
| US20130139486A1 (en) * | 2011-12-01 | 2013-06-06 | General Electric Company | Variable initiation location system for pulse detonation combustor |
| CN108895849A (en) * | 2018-08-30 | 2018-11-27 | 中冶长天国际工程有限责任公司 | Ring cold machine and its heat dissipation recycling component and method, oxide pellet Preparation equipment |
| CN109915281B (en) * | 2019-03-06 | 2021-03-19 | 西北工业大学 | Pulse detonation rocket engine oil supply scheme beneficial to wall cooling and detonation |
| CN214196484U (en) * | 2021-01-26 | 2021-09-14 | 厦门大学 | Interstage rotary detonation variable-circulation turboshaft engine |
| CN113028454B (en) * | 2021-04-09 | 2022-08-19 | 西北工业大学 | High-frequency detonation combustion scheme based on regenerative cooling |
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