CN115218224A - Cooling structure suitable for pulse detonation combustion chamber - Google Patents
Cooling structure suitable for pulse detonation combustion chamber Download PDFInfo
- Publication number
- CN115218224A CN115218224A CN202210910139.4A CN202210910139A CN115218224A CN 115218224 A CN115218224 A CN 115218224A CN 202210910139 A CN202210910139 A CN 202210910139A CN 115218224 A CN115218224 A CN 115218224A
- Authority
- CN
- China
- Prior art keywords
- detonation
- heat exchange
- combustion chamber
- cooling
- cooling medium
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- 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
-
- 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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- 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 combustor. The detonation combustion chamber is a sealed straight circular tube with one end closed and the other end open, and is internally provided with an Shchelkin spiral explosion-increasing barrier with a cooling channel, and the detonation combustion chamber has the function of reducing the time and distance for transition from detonation to detonation (DDT for short). The DDT section has strong heat exchange and higher wall surface temperature, so that the DDT section is cooled by a sectional forced convection by adopting a high-efficiency heat exchange cavity. And in consideration of the wall surface temperature distribution of the detonation combustion chamber, a common heat exchange cavity is adopted to carry out forced convection cooling on other hot end components of the detonation combustion chamber. The invention can obviously reduce the temperature of the hot end part of the detonation combustion chamber and the Shchelkin spiral explosion-increasing barrier, prolong the service life of the detonation combustion chamber, simultaneously avoid the continuous combustion phenomenon caused by overhigh temperature of the combustion chamber wall 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 uses an intermittent detonation wave to generate thrust. Research shows that compared with common slow combustion, the detonation combustion has the advantages of strong chemical reaction, high thermal cycle efficiency and the like, and is particularly suitable for power sources of aviation, aerospace and navigation devices and the field of thermal spraying. However, each application area imposes a strict limit on the maximum temperature resistance of the material, and an overtemperature is liable to cause continuous combustion of the fuel and even to create a safety hazard when the equipment is in operation, so that effective cooling of the equipment is of utmost importance. At present, cooling means related to pulse detonation combustion is not sufficient, and further application of the cooling means is limited.
With the development of the industrial field, the pulse detonation combustion technology is expected to be applied to various energy industries in the future, and meanwhile, a high-performance detonation combustion device (such as high-frequency detonation combustion) will certainly provide a stricter limit on the wall temperature, and the traditional cooling mode is difficult to meet the performance requirement of the device, so that an efficient cooling mode is urgently needed to reduce the wall temperature of the device.
Disclosure of Invention
The invention aims to provide a cooling structure suitable for a pulse detonation combustion chamber.
The invention is realized by adopting the following technical scheme:
a cooling structure suitable for a pulse detonation combustor comprises the detonation combustor, a high-efficiency heat exchange cavity and a common heat exchange cavity;
the detonation combustion chamber is a sealed straight circular tube with one closed end and an open other end, an Shchelkin spiral explosion-increasing barrier with a cooling channel is arranged inside the detonation combustion chamber, the time and the distance of DDT (spark discharge) transition from detonation to detonation are reduced, the internal cooling channel of the Shchelkin spiral explosion-increasing barrier is used for reducing the temperature of the wall surface of the Shchelkin spiral explosion-increasing barrier, the efficient heat exchange cavity is coaxially welded on the outer wall surface of the detonation combustion chamber, the axial length and the axial position of the efficient heat exchange cavity are the same as those of the Shchelkin spiral explosion-increasing barrier and used for reducing the temperature of the wall surface of a 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 detonation-increasing barrier are integrally manufactured and formed by adopting a casting process or an additive manufacturing technology.
The further improvement of the invention is that the outer diameter of the Shchelkin spiral detonation-enhanced barrier is equal to the inner diameter of the detonation combustion chamber, the wire 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 Shchelkin spiral detonation-enhanced barrier is provided with longitudinal micro fins to enhance heat transfer and improve the structural strength of the Shchelkin spiral detonation-enhanced barrier.
The further improvement of the invention is that the head end and the tail end of the Shchelkin spiral detonation increasing barrier are seamlessly connected with the inner wall surface of the detonation combustion chamber, the external outline of the cross section of the Shchelkin spiral detonation increasing barrier is in a shape formed by a square and a sector, a space is reserved for a cooling medium supply hole and a cooling medium discharge hole, and the external outline of the cross section of the other part of the Shchelkin spiral detonation increasing barrier is in a circular shape.
The invention further improves that the cooling medium supply hole is positioned in the last section of the high-efficiency heat exchange cavity far away from the closed end of the detonation combustion chamber and close to the side of the cooling medium inlet, and the cooling medium exhaust hole is positioned in the first section of the high-efficiency heat exchange cavity close to the closed end of the detonation combustion chamber and close to the side of the cooling medium outlet, so that fresh cooling medium can be stably supplied to the interior of the Shchelkin spiral detonation barrier and exhausted.
The invention has the further improvement that the high-efficiency heat exchange cavity is internally provided with combined fins formed by annular fins and longitudinal fins and used for increasing the convection heat exchange area and reducing the wall temperature of the DDT section of the detonation combustion chamber.
The invention has the further improvement that the annular fins are spirally connected with the outer wall surface of the detonation combustion chamber and the inner wall surface of the high-efficiency heat exchange cavity to force a cooling medium to flow in a specified direction, the longitudinal fins are distributed on two sides of the annular fins in a staggered mode, and the corners of the longitudinal fins are subjected to fillet treatment, so that the flow loss of the cooling medium is reduced, the screw pitch of the annular fins is ensured to ensure that the longitudinal fins on two adjacent annular fins are not in contact, and a space is increased for the flow of the cooling medium.
The invention has the further improvement that the high-efficiency heat exchange cavity is of a sectional type cooling structure, a plurality of high-efficiency heat exchange cavities are uniformly distributed along the axial direction of the DDT section of the detonation combustor, cooling media flow independently, and the cooling effect is enhanced.
The invention has the further improvement that a plurality of longitudinal wave-shaped 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 wave-shaped fins are continuous and uniform so as to reduce the flow loss of a cooling medium.
The invention has at least the following beneficial technical effects:
the invention adopts a sectional forced convection cooling mode to carry out high-efficiency cooling on the DDT section with strong heat exchange in the detonation combustion chamber. The cooling media flow in different high-efficiency heat exchange cavities independently, so that the heat exchange effect is enhanced; the annular fins and the longitudinal fins in the efficient heat exchange cavity are combined and arranged, so that the convection heat exchange area can be obviously increased, and the wall surface temperature of a DDT section of the detonation combustion chamber is effectively reduced.
The Shchelkin spiral explosion-increasing barrier is internally provided with a miniature cooling channel, heat exchange can be enhanced by utilizing a microscale effect, and meanwhile, the longitudinal fins are arranged in the Shchelkin spiral explosion-increasing barrier, so that the structural strength is improved, the convective heat exchange area is increased, and the surface temperature of the Shchelkin spiral explosion-increasing barrier is effectively reduced.
And in consideration of the uniformity of the temperature distribution of the wall surface of the detonation combustion chamber, cooling the rest hot end parts of the detonation combustion chamber by adopting a forced convection cooling mode. The wave type fins which are 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 an efficient cooling scheme, can effectively reduce the wall temperature of the hot end component, prolongs the service life of the hot end component, and simultaneously avoids continuous combustion phenomenon and potential safety hazard caused by overtemperature of the wall.
In conclusion, the invention respectively arranges the reasonable and effective cooling structures for different hot end components of the detonation combustion chamber, can reduce the wall temperature, prolong the service life, avoid the continuous combustion phenomenon and obviously improve the detonation combustion stability.
Drawings
FIG. 1 is a schematic axial view of a pulse detonation combustor cooling scheme;
FIG. 2 is an axial cross-sectional view of a cooling scheme suitable for use in a pulse detonation combustor;
FIG. 3 is a schematic cross-sectional view of a Shchelkin spiral booster barrier;
FIG. 4 is a cross-sectional schematic view of a sectional fin.
Description of the reference numerals:
the detonation combustor is characterized in that 1 is a detonation combustor, 2 is an Shchelkin spiral detonation-boosting barrier, 3 is a high-efficiency heat exchange cavity, 4 is a common heat exchange cavity, 5 is a micro 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 by 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 the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
As shown in fig. 1 and fig. 2, the present invention provides a cooling structure suitable for a pulse detonation combustor, which mainly comprises a detonation combustor 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 pipe with one end closed and the other end open, and is internally provided with an Shchelkin spiral explosion-increasing barrier 2 with a cooling channel, and the detonation combustion chamber has the function of reducing the time and distance for transition from detonation to detonation, namely DDT. The internal cooling channels of the Shchelkin spiral booster barrier 2 serve to reduce its surface temperature. The efficient heat exchange cavity 3 is coaxially welded on the outer wall surface of the detonation combustion chamber 1, the axial length and the position of the efficient heat exchange cavity are the same as those of the Shchelkin spiral detonation barrier 2, and the efficient heat exchange cavity has the function of reducing the wall surface temperature 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 combustor 1 and used for reducing the temperature of other hot end parts of the detonation combustor 1.
The high-efficiency heat exchange cavity 3 is divided into a plurality of sections, the number of the sections is properly adjusted according to the length of the Shchelkin spiral detonation increasing barrier 2 and the detonation combustion frequency, each section is provided with a cooling medium inlet and a cooling medium outlet, the axial speed of a cooling medium flowing in the high-efficiency heat exchange cavity 3 is opposite to the discharge direction of burnt gas, the heat exchange effect is enhanced, the cooling medium inlets comprise 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 outlets comprise 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 close to the closed end of the detonation combustion chamber 1 and close to one side of the cooling medium outlet. The cooling medium supply hole 12 is used for supplying a cooling medium into the internal cooling channel of the Shchelkin spiral detonation barrier 2, the axial speed of the cooling medium flowing in the channel is opposite to the discharging direction of combusted gas, so that the heat exchange between the cooling medium and the wall surface of the Shchelkin spiral detonation barrier 2 can be enhanced, the wall surface heat is taken away, the cooling medium flows into the high-efficiency heat exchange cavity 3 through the cooling medium discharge hole 13, and finally the cooling medium is discharged together with the cooling medium in the high-efficiency heat exchange cavity 3.
The combined fin formed by the annular fin 6-1 and the longitudinal fin 6-2 in the efficient heat exchange cavity 3 can be separately processed and then welded and installed on the outer wall surface of the detonation combustion chamber 1, and can also be integrally manufactured and molded 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 fin has high strength enough to ensure that the Shchelkin spiral explosion-increasing barrier 2 cannot deform or be damaged during detonation combustion.
The number of the longitudinal micro fins 5 in the internal channel of the Shchelkin spiral detonation barrier 2 is properly adjusted according to the detonation combustion frequency, and the wall surface temperature of the Shchelkin spiral detonation 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 exhausting 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.
In the embodiment, as shown in fig. 1 and fig. 2, fuel required by detonation combustion is supplied into a detonation combustion chamber 1 from a fuel supply cavity 8, is ignited by an igniter 9 to generate slow combustion, and transitions to detonation combustion under the action of a Shchelkin spiral explosion-increasing barrier 2, and is discharged from an outlet together with combusted gas after the detonation wave is formed. As the detonation combustion duration increases, the heat accumulated by the hot end component also continues to increase. In the process, the Shchelkin spiral explosion-increasing barrier 2 has strong heat exchange and higher temperature rise, and the cooling medium flowing inside the Shchelkin spiral explosion-increasing barrier continuously exchanges heat with the wall surface of the Shchelkin spiral explosion-increasing barrier to continuously take away the heat of the wall surface of the Shchelkin spiral explosion-increasing barrier so as to keep the temperature of the wall surface within a normal range. In addition, the Shchelkin spiral detonation barrier 2 is positioned in a DDT section of the detonation combustion chamber 1, and the temperature rise of the wall surface of the DDT section is also higher. The cooling media in the high-efficiency heat exchange cavities 3 of the sections are mutually independent, and continuously exchange heat with the wall surface of the detonation combustor 1 and the combined fins in the respective heat exchange cavities, so that the DDT sections are cooled in sections, the heat exchange effect is enhanced, and the wall surface temperature is effectively reduced. The common heat exchange cavity 4 cools other hot end parts with lower temperature rise, so that the temperature of the wall surface is reduced, the temperature distribution of the wall surface of the detonation combustion chamber 1 is in a reasonable range, and the service life of materials is prolonged. The cooling medium may be air, liquid water, or other fluid.
Based on an efficient cooling scheme, the invention can effectively reduce the temperature of the hot end part of the pulse detonation combustor, prolong the service life of the pulse detonation combustor and simultaneously avoid continuous combustion phenomenon and potential safety hazard caused by overtemperature of the wall surface.
Although the invention has been described in detail hereinabove with respect to a general description and specific embodiments thereof, it will be apparent to those skilled in the art that modifications or improvements may be made thereto based on the invention. Accordingly, it is intended that all such modifications and alterations be included within the scope of this invention as defined in the appended claims.
Claims (9)
1. A cooling structure suitable for a pulse detonation combustor is characterized by comprising a detonation combustor (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 closed end and an open other end, the Shchelkin spiral explosion-increasing barrier (2) with a cooling channel is arranged inside the sealed straight circular tube, the time and the distance of transition from detonation to DDT are reduced, the internal cooling channel of the Shchelkin spiral explosion-increasing barrier (2) is used for reducing the temperature of the wall surface of the Shchelkin spiral explosion-increasing barrier, the efficient 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 efficient heat exchange cavity are the same as those of the Shchelkin spiral explosion-increasing barrier (2), the temperature of the wall surface of the DDT section of the detonation combustion chamber (1) is reduced, 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).
2. A cooling structure suitable for a pulse detonation combustor according to claim 1, characterised in that the DDT section of the detonation combustor (1) and the Shchelkin spiral booster barrier (2) are integrally formed by a casting process or an additive manufacturing technology.
3. A cooling structure suitable for a pulse detonation combustor according to claim 1, characterized in that the Shchelkin spiral detonation obstacle (2) has an outer diameter equal to the inner diameter of the detonation combustor (1), a wire diameter 0.15-0.25 times the inner diameter of the detonation combustor (1), an inner cooling channel diameter 1-2 mm, and longitudinal micro fins (5) are provided to enhance heat transfer and improve structural strength.
4. The cooling structure suitable for the pulse detonation combustor according to claim 1, wherein the head end and the tail end of the Shchelkin spiral detonation obstacle (2) are seamlessly connected with the inner wall surface of the detonation combustor (1), the external contour of the cross section of the Shchelkin spiral detonation obstacle is in a shape formed by a square and a sector, a space is reserved for a cooling medium supply hole (12) and a cooling medium discharge hole (13), and the external contour of the cross section of the rest part is in a circular shape.
5. A cooling structure suitable for a pulse detonation combustor according to claim 1, characterized in that the cooling medium supply hole (12) is located in the last section of the high efficiency heat exchange cavity (3) far away from the closed end of the detonation combustor (1) and close to the side of the cooling medium inlet, and the cooling medium exhaust hole (13) is located in the first section of the high efficiency heat exchange cavity (3) close to the closed end of the detonation combustor (1) and close to the side of the cooling medium outlet, so that fresh cooling medium can be stably supplied to the inside of the Shchelkin spiral detonation obstacle (2) and exhausted.
6. The cooling structure suitable for the pulse detonation combustor according to claim 1, wherein combined fins formed by annular fins (6-1) and longitudinal fins (6-2) are arranged in the efficient heat exchange cavity (3) and used for increasing a convection heat exchange area and reducing a wall temperature of a DDT section of the detonation combustor (1).
7. The cooling structure suitable for the pulse detonation combustor according to claim 6, wherein the annular fins (6-1) are spirally connected to the outer wall surface of the detonation combustor (1) and the inner wall surface of the efficient heat exchange cavity (3) to force the cooling medium 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, and the corners of the longitudinal fins (6-2) are rounded to reduce the flow loss of the cooling medium, and the pitch of the annular fins (6-1) is ensured to ensure that the longitudinal fins (6-2) on two adjacent annular fins (6-1) are not in contact, so that space is added for the flow of the cooling medium.
8. The cooling structure suitable for the pulse detonation combustor according to the claim 1, characterized in that the high-efficiency heat exchange cavity (3) is a sectional type cooling structure, a plurality of high-efficiency heat exchange cavities (3) are uniformly distributed along the DDT section of the detonation combustor (1) in the axial direction, the flows of cooling media are independent from each other, and the cooling effect is enhanced.
9. The cooling structure suitable for the pulse detonation combustor according to the claim 1, characterized in that a plurality of longitudinal wavy fins (7) are arranged in the common heat exchange cavity (4) and are evenly 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 continuous and even so as to reduce the flow loss of a 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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115218224A true CN115218224A (en) | 2022-10-21 |
| CN115218224B CN115218224B (en) | 2023-06-20 |
Family
ID=83616532
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210910139.4A Active CN115218224B (en) | 2022-07-29 | 2022-07-29 | Cooling structure suitable for pulse detonation combustor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115218224B (en) |
Citations (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 |
| US20110073048A1 (en) * | 2009-09-25 | 2011-03-31 | Alejandro Juan | Pressure gain combustion heat generator |
| CN103134081A (en) * | 2011-12-01 | 2013-06-05 | 通用电气公司 | 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 |
| CN109915281A (en) * | 2019-03-06 | 2019-06-21 | 西北工业大学 | A kind of pulse detonation rocket engines fuel feeding scheme being beneficial to wall cooling and detonation |
| CN113028454A (en) * | 2021-04-09 | 2021-06-25 | 西北工业大学 | High-frequency detonation combustion scheme based on regenerative cooling |
| CN214196484U (en) * | 2021-01-26 | 2021-09-14 | 厦门大学 | Interstage rotary detonation variable-circulation turboshaft engine |
-
2022
- 2022-07-29 CN CN202210910139.4A patent/CN115218224B/en active Active
Patent Citations (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 |
| US20110073048A1 (en) * | 2009-09-25 | 2011-03-31 | Alejandro Juan | Pressure gain combustion heat generator |
| CN103134081A (en) * | 2011-12-01 | 2013-06-05 | 通用电气公司 | 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 |
| CN109915281A (en) * | 2019-03-06 | 2019-06-21 | 西北工业大学 | A kind of pulse detonation rocket engines fuel feeding scheme being 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 |
| CN113028454A (en) * | 2021-04-09 | 2021-06-25 | 西北工业大学 | High-frequency detonation combustion scheme based on regenerative cooling |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115218224B (en) | 2023-06-20 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10230287B2 (en) | Electric machine heat sink with incorporated pin fin arrangement | |
| CN102619648A (en) | Plate-fin EGR (Exhaust Gas Recirculation) cooler with heat insulation function | |
| JP2017122435A (en) | Methods of cooling fluid using annular heat exchanger | |
| CN109269756B (en) | A kind of water-cooled jet pipe | |
| JP2004518060A (en) | Rocket engine member and method of manufacturing rocket engine member | |
| JP2005283095A (en) | Efficient heat exchanger, and engine using the same | |
| CN115218224B (en) | Cooling structure suitable for pulse detonation combustor | |
| RU2671669C1 (en) | Heat exchanger | |
| CN105786045A (en) | Externally-arranged surrounding type temperature control device and method for high-energy system | |
| KR101772837B1 (en) | Gas turbine combustor and gas turbine provided with said combustor | |
| KR20130053756A (en) | Exhaust gas pipe structure of engine | |
| CN104566458A (en) | Gas turbine combustor transition section with cooling structure | |
| CN104578977A (en) | Automobile exhaust thermoelectricity generating set | |
| CN211781967U (en) | Fin heat exchange type mold temperature controller | |
| CN204404235U (en) | A kind of gas-turbine combustion chamber changeover portion with cooling structure | |
| CN202611933U (en) | Plate-fin type exhaust gas recirculation (EGR) cooler with heat insulation function | |
| RU2204773C2 (en) | Tube-in-tube heat exchanger | |
| CN109612307B (en) | Structure optimization method for shell-and-tube heat exchanger of liquid medicine for fumigation | |
| RU2686357C1 (en) | Gaseous medium heater | |
| CN113237097A (en) | Heat exchanger for gas turbine | |
| CN215444243U (en) | Engine tail nozzle | |
| CN203844579U (en) | Heating heat exchanger with denoising function | |
| CN112937880B (en) | Jet nozzle of auxiliary power device of airplane | |
| CN209212506U (en) | A kind of water-cooled cooler of compressor | |
| RU2755759C1 (en) | Recuperative heat exchanger and method for its operation |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |