CN115539986A - Hydrogen fuel honeycomb bionic combustion chamber head structure - Google Patents
Hydrogen fuel honeycomb bionic combustion chamber head structure Download PDFInfo
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- CN115539986A CN115539986A CN202211159910.5A CN202211159910A CN115539986A CN 115539986 A CN115539986 A CN 115539986A CN 202211159910 A CN202211159910 A CN 202211159910A CN 115539986 A CN115539986 A CN 115539986A
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- hexagonal
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 85
- 239000000446 fuel Substances 0.000 title claims abstract description 68
- 239000001257 hydrogen Substances 0.000 title claims abstract description 56
- 229910052739 hydrogen Inorganic materials 0.000 title claims abstract description 56
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 title claims abstract description 54
- 239000011664 nicotinic acid Substances 0.000 title claims description 13
- 230000003592 biomimetic effect Effects 0.000 claims description 5
- 230000008520 organization Effects 0.000 claims description 5
- 238000002347 injection Methods 0.000 claims description 4
- 239000007924 injection Substances 0.000 claims description 4
- 230000007704 transition Effects 0.000 claims description 2
- 150000002431 hydrogen Chemical class 0.000 claims 1
- 239000003350 kerosene Substances 0.000 description 3
- 239000000243 solution Substances 0.000 description 3
- 241000610716 Balduina Species 0.000 description 2
- 239000004215 Carbon black (E152) Substances 0.000 description 2
- 206010016754 Flashback Diseases 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 229930195733 hydrocarbon Natural products 0.000 description 2
- 150000002430 hydrocarbons Chemical class 0.000 description 2
- 235000001968 nicotinic acid Nutrition 0.000 description 2
- 230000003014 reinforcing effect Effects 0.000 description 2
- 239000000654 additive Substances 0.000 description 1
- 230000000996 additive effect Effects 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000004323 axial length Effects 0.000 description 1
- 230000033228 biological regulation Effects 0.000 description 1
- 239000006227 byproduct Substances 0.000 description 1
- 239000000112 cooling gas Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 239000003344 environmental pollutant Substances 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 231100000719 pollutant Toxicity 0.000 description 1
- 230000002269 spontaneous effect Effects 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
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
- 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
-
- 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
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
The application provides a bionical combustion chamber head structure of hydrogen fuel honeycomb includes: the head comprises an annular head body, wherein the end surface of the head body facing to airflow incoming flow is at least provided with a circle of hexagonal holes, each circle of hexagonal holes comprises a plurality of hexagonal holes, the non-airflow incoming flow end surface of the head body is provided with an annular groove, and a rectangular hole matched with the hexagonal hole is arranged between the hexagonal hole and the annular groove in the head body; the bluff body is arranged in the hexagonal hole and provided with an on-duty jet flow channel which faces backwards in the axial direction and a jet flow channel which is arranged in the circumferential direction and is communicated with the on-duty jet flow channel, and the jet flow channel and an annular channel in the head body form an on-duty main pipe which is used for supplying fuel to the on-duty jet flow channel; the radial side wall of the rectangular hole is provided with a main fuel jet hole which emits towards the rectangular hole, a main fuel channel is arranged at the position, matched with the main fuel jet hole, of the head body, and a main fuel main pipe is formed through the main fuel channel and used for supplying fuel to the main fuel jet hole.
Description
Technical Field
The application belongs to the technical field of aeroengines, and in particular relates to a hydrogen fuel honeycomb bionic combustion chamber head structure.
Background
The hydrogen is used as a novel green energy source, the reaction by-product of the hydrogen and oxygen is water or steam, the heat value of the hydrogen fuel is about 2.78 times of that of aviation kerosene, and compared with the traditional hydrocarbon aviation kerosene fuel, the reaction rate and the flame propagation speed of the hydrogen fuel in the combustion process are higher, the combustion speed is higher, the axial length of a combustion chamber can be shortened, and the thrust-weight ratio of an engine can be improved.
However, because the combustion speed of the hydrogen fuel is too high, the hydrogen fuel is easy to flash back in the combustion process by adopting the traditional aviation kerosene injection mode, and further the fuel is spontaneous combustion or even explosion. Meanwhile, hydrogen fuel is directly used in the existing burner, a stoichiometric condition is formed on a large flame diffusion surface, local high temperature points are formed, a large amount of NOx gas which is obviously higher than that of the traditional hydrocarbon fuel is generated near the high temperature points, and the pollutant discharge amount is increased.
In the prior art, a premixed combustion mode is mainly adopted to reduce NOx after hydrogen fuel is combusted, hot spots in combustion flame can be avoided by the method, and a special structure needs to be additionally designed to avoid a hydrogen flash-back phenomenon. However, under the complex environment of high turbulence and high rotational flow in the combustion chamber of a real aero-engine, the long-term stable and safe operation of the pre-combustion structure in the prior art is difficult to guarantee by adopting the pre-combustion structure, and the pre-mixing combustion needs to be provided with a mixer, so that the length of the combustion chamber is greatly increased, and the thrust-weight ratio of the aero-engine is remarkably reduced.
Therefore, a hydrogen fuel combustion chamber head structure suitable for the field of ground combustion engines and aircraft engines is needed.
Disclosure of Invention
It is an object of the present application to provide a hydrogen-fueled honeycomb biomimetic combustor head structure to solve or mitigate at least one of the problems in the background.
The technical scheme of the application is as follows: a hydrogen fuel honeycomb bionic combustion chamber head structure comprises:
the end face, facing the airflow incoming flow, of the head body is provided with at least one circle of hexagonal holes, each circle of hexagonal holes comprises a plurality of hexagonal holes, the end face, not facing the airflow incoming flow, of the head body is provided with an annular groove, and rectangular holes matched with the hexagonal holes are formed between the hexagonal holes and the annular groove in the head body;
the blunt body is arranged in the hexagonal hole and provided with an on-duty jet flow channel which faces backwards in the axial direction and a jet flow channel which is arranged in the circumferential direction and is communicated with the on-duty jet flow channel, and the jet flow channel and an annular channel in the head body form an on-duty main pipe which is used for supplying fuel to the on-duty jet flow channel;
the radial side wall of the rectangular hole is provided with a main fuel hole which emits towards the rectangular hole, a main fuel channel is arranged at the position, matched with the main fuel hole, of the head body, and a main fuel main pipe is formed through the main fuel channel and used for supplying fuel to the main fuel hole.
Furthermore, the number of turns of the hexagonal hole is 2-3.
Further, the hexagonal hole is a regular hexagon, and the length and width of the rectangular hole are configured to be not less than the opposite side distance or the opposite side distance of the hexagonal hole which is a regular hexagon, so that the rectangular hole can cover the hexagonal hole.
Further, the radial width of the annular groove is larger than the distance between the outer side wall surface of the rectangular hole of one circle and the inner side wall surface or the distance between the outer side wall surface of the rectangular hole of the outer ring and the inner side wall surface of the rectangular hole of the inner ring when more than two circles are formed.
Furthermore, the blunt body is in a triangular structure, two oblique edges or oblique planes of the triangular structure are separated in the radial direction, and the inclination angles of the two oblique edges or oblique planes are adjusted according to the flow field organization form.
Furthermore, two oblique edges or oblique surfaces separated in the radial direction are transited through a fillet transition.
Further, an axis of the main fuel hole is perpendicular to an axis of the head body.
Further, the aperture of the main fuel jet hole is smaller than 1mm.
Furthermore, the jet flow channel is communicated with a total hydrogen fuel inlet through a duty round pipe radially arranged in the head body, so that the supply of the hydrogen fuel is realized.
Furthermore, the main combustion channel is communicated with the hydrogen fuel main inlet through a main combustion round pipe radially arranged in the head body, so that the supply of the hydrogen fuel is realized.
The application provides a bionical combustion chamber head structure of hydrogen fuel honeycomb passes through the honeycomb head structural design based on bionics, in limited size range, when reinforcing combustion chamber head structural strength, promotes combustion reaction's space utilization, and then realizes light, compact, efficient and fires hydrogen combustion scheme.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
FIG. 1 is a general schematic view of a combustor head configuration of the present application.
Fig. 2 is a partially enlarged view of a head structure of a combustion chamber according to the present invention.
FIG. 3 is a front view of a hexagonal hole and a blunt body in a combustor head configuration of the present application.
Fig. 4 isbase:Sub>A sectional view taken alongbase:Sub>A-base:Sub>A in fig. 2.
Fig. 5 is a sectional view taken along line B-B in fig. 2.
Reference numerals are as follows:
1-head body
2-hexagonal hole
3-bluff body, 31-jet channel, 32-hydrogen jet hole
4-rectangular hole
5-main combustion channel
6-main combustion jet hole
7-ring groove
8-main combustion round pipe
9-duty round tube
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
As shown in fig. 1 to 5, the hydrogen fuel honeycomb bionic combustion chamber head structure provided by the present application mainly includes a head body 1.
The head body 1 is a circular structure. At least one circle of hexagonal holes 2 is arranged on the left side surface (namely the surface facing the airflow) of the head body 1, and the number of hexagonal holes 2 in each circle is multiple. In the illustrated embodiment of the present application, the hexagonal holes 2 are two circles, that is, an inner hexagonal hole and an outer hexagonal hole, and the shapes and sizes of the hexagonal holes 2 in the inner hexagonal hole and the outer hexagonal hole are the same, so that the number of the outer hexagonal holes 2 is 24, and the number of the inner hexagonal holes 2 is 20. The hexagonal holes 2 resemble hexagonal cells closely arranged in a honeycomb, and the entire combustion chamber head structure is formed in a honeycomb-like configuration by a hexagonal arrangement called honeycomb structure.
The rear side of the airflow flow in the hexagonal hole 2 in the head body 1 is provided with a rectangular hole 4 matched with the hexagonal hole 2, the rectangular hole 4 extends backwards for a certain distance and does not extend to the right end face, the number of rectangular holes 4 in each circle is also matched with the number of hexagonal holes 2 in each circle, and the position of the rectangular hole 4 is also matched with the position of the hexagonal hole 2. For example, in the illustrated embodiment of the present application, the number of the rectangular holes 4 is two, the number of the rectangular holes 4 in the outer ring is 24, the number of the rectangular holes 4 in the inner ring is 20, and the center of the rectangular hole 4 is adapted to the center of the hexagonal hole 2.
In the preferred embodiment of the present application, hexagonal hole 2 is a regular hexagon, and the width of rectangular hole 4 is not less than the width W of hexagonal hole, and the length of rectangular hole 4 is not less than the distance L between two fixed points of hexagonal hole, so that rectangular hole 4 can completely cover or wrap hexagonal hole 2.
A blunt body 3 is provided inside each hexagonal hole 2 to enhance flame holding. The bluff body 3 has the same width W as the hexagonal hole 2, is arranged in the hexagonal hole 2, and is perpendicular to a connecting line of two radial fixed points of the hexagonal hole 2. A plurality of blunt bodies 3 may be arranged in the hexagonal holes 2 to form a substantially circular shape.
The bluff body 3 is in a triangular structure facing the airflow direction, two oblique edges or oblique planes of the bluff body are separated in the radial direction, the two oblique edges or oblique planes are transitionally connected through a fillet, and the inclination angles of the two oblique edges or oblique planes can be adjusted according to the flow field organization form.
Each bluff body 3 is internally provided with 1 on-duty jet hole 32 extending along the axis of the head structure (namely, in the horizontal direction in fig. 2), and the aperture of the on-duty jet hole 32 can be adjusted according to the combustion chamber point and the flameout boundary. Annular jet flow channels 31 are arranged in the blunt body 3 and the head body 1, the jet flow channels 31 form a jet flow main pipe, and a hydrogen jet circular hole 32 in each blunt body 3 supplies hydrogen fuel through the jet flow channels 31. The hydrogen fuel jetted out through the hydrogen jet circular holes 32 is combusted to form on-duty flame of the combustion chamber, and through the on-duty flame, flame stabilization regulation and control are facilitated, and the stable working boundary of the combustion chamber can be further widened.
A pair of (i.e., two) main fuel holes 6 are oppositely arranged on the side wall of each rectangular hole 4, and the main fuel holes 6 are distributed in the radial direction. Meanwhile, a circular main combustion channel 5 is arranged in the head body 1, and the main combustion channel 5 forms a main combustion main pipe. The main combustion channel 5 is communicated with the main combustion jet holes 6, and hydrogen fuel is introduced into the main combustion channel 5 and can be uniformly injected into the rectangular holes 4 from the main combustion jet holes 6 which are circumferentially distributed, so that the combustion of main combustion stage flame is completed.
In the preferred embodiment of this application, main fuel orifice 6 is perpendicular to main gas flow direction, and the aperture of main fuel orifice 6 is less than 1mm in order to strengthen the transverse jet intensity, and then helps steady flame and abundant burning.
As shown in the schematic layout of the main combustion stage flow path in fig. 4, the main combustion stage flow path has two circles of rectangular holes 4, for each circle of rectangular holes 4, a pair of main combustion hole 6 is provided on the side walls of the upper and lower sides in the radial direction for supplying hydrogen into the rectangular holes 4, and the main combustion hole 6 on the two side walls supplies hydrogen through the annular main combustion channel 5. Wherein, set up three main passageway 5 that fires in the head body 1 outside rectangular hole 4, fire the main passageway 5 through two liang of main setting and carry out hydrogen to the main jet hole 6 that fires of its UNICOM. The three main combustion channels 5 are equivalent to a hydrogen main pipe and finally converge in a main combustion round pipe 8, and the main combustion round pipe 8 penetrates through the head body 1 and then is connected with a hydrogen main inlet.
As shown in the schematic diagram of the flow path layout on duty shown in fig. 5, the flow path on duty has two circles of hexagonal holes 2, for each circle of hexagonal hole 2, a blunt body 3 is arranged therein, an on duty jet hole 32 is axially backward arranged in the blunt body 3, the jet hole 32 on duty supplies hydrogen through an annular on duty channel 31, meanwhile, an annular channel is arranged on the head body 1 at a position matching the on duty channel 31, the annular channel and the on duty channel 31 together form an on duty header pipe, the two on duty header pipes are collected to an on duty round pipe 9, and the on duty round pipe 9 passes through the head body 1 and then is connected with a total hydrogen inlet.
The air flow direction rear side of the rectangular hole 4 on the head body 1 is provided with an annular groove 7, the annular groove 7 extends to the right end face of the head body 1, and the width of the annular groove 7 is larger than the distance of the circles of the rectangular holes 6 in the radial direction. For the illustrated embodiment of the present application, the width of the annular groove 7 is greater than the distance between the radially innermost and outermost edges of the two turns of the rectangular aperture 6, so that the annular groove 7 may contain or cover two turns of the rectangular aperture 6.
In the application, the internal flow path of the head structure of the hydrogen-fueled honeycomb bionic combustion chamber is complex, and in order to realize the processing of the structure, the processing can be carried out in a 3D additive manufacturing mode.
During operation, main flow air enters through the hexagonal holes 2 of the head body 1, and is fully mixed with hydrogen in the pair of main combustion jet holes 6 in the rectangular holes 4 at the downstream of the bluff body 3 in each hexagonal hole 2 to form a pair of tiny backflow regions, so that a tiny flame group is formed, and main combustion level flame is formed; meanwhile, hydrogen in the on-duty jet hole 32 also participates in combustion, but the hydrogen flow is less than that of the main jet hole 6, and the formed flame is used as an on-duty stage, so that the ignition and flameout boundary of the combustion chamber can be remarkably widened.
The utility model provides a combustor head structure can make and form hundreds of small flame group in the combustor, and hydrogen combustion rate is high, and required flame tube length is short, has saved a large amount of flame tube cooling gas. The air and hydrogen in each tiny flame group can realize lean oil non-premixed combustion, the combustion is sufficient, the efficiency is high, and local hot spots in the flame are greatly reduced, so that the NOx emission is remarkably reduced, and the pollution combustion potential is low. The non-premixed combustion organization mode also solves the problem that the hydrogen is high in combustion speed and easy to temper.
In the bionic combustion chamber head structure of hydrogen fuel honeycomb provided by the application, the number in hexagonal hole 2 is more, can reach dozens of or even hundreds usually, and hydrogen flow path overall arrangement is complicated, and for simplifying the technology, combustion chamber head structure accessible 3D vibration material disk technology integrated into one piece to realize the inside hydrogen fuel efflux overall arrangement of head structure, realize the non-premixed burning of microscale. Because the combustion rate of the hydrogen is high, the micro-scale non-premixed combustion organization mode can realize high-efficiency combustion in a short range, so that the length of a flame tube can be shortened, the weight of a combustion chamber can be reduced, the lean flameout boundary of the combustion chamber can be widened, and the thrust-weight ratio of an engine can be improved.
The application provides a bionical combustion chamber head structure of hydrogen fuel honeycomb passes through the honeycomb head structural design based on bionics, in limited size scope, when reinforcing combustion chamber head structural strength, promotes combustion reaction's space utilization, and then realizes light, compact, efficient hydrogen combustion scheme.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. The utility model provides a hydrogen fuel honeycomb bionic combustion chamber head structure which characterized in that includes:
the air flow inlet end face of the head body (1) is provided with at least one circle of hexagonal holes (2), each circle of hexagonal holes (2) comprises a plurality of holes, the non-air flow inlet end face of the head body (1) is provided with an annular groove (7), and a rectangular hole (4) matched with the hexagonal hole (2) is formed between the hexagonal hole (2) and the annular groove (7) in the head body (1);
the blunt body (3) is arranged in the hexagonal hole (2), the blunt body (3) is provided with an on-duty jet flow channel (32) which faces backwards in the axial direction and a jet flow channel (31) which is circumferentially arranged and communicated with the on-duty jet flow channel (32), and the jet flow channel (31) and an annular channel in the head body (1) form an on-duty main pipe and are used for supplying fuel to the on-duty jet flow channel (32);
the radial side wall of the rectangular hole (4) is provided with a main fuel injection hole (6) which emits to the rectangular hole (4), a main fuel channel (5) is arranged at the position, matched with the main fuel injection hole (6), of the head body (1), and a main fuel main pipe is formed through the main fuel channel (5) and used for supplying fuel to the main fuel injection hole (6).
2. The head structure of the hydrogen fuel honeycomb bionic combustion chamber as claimed in claim 1, wherein the number of turns of the hexagonal hole (2) is 2-3.
3. The hydrogen-fueled honeycomb biomimetic combustor head structure according to claim 1 or 2, characterized in that the hexagonal holes (2) are regular hexagons, and the length and width of the rectangular holes (4) are configured to be not less than the opposite side distance or the diagonal distance of the hexagonal holes (2) being regular hexagons, so that the rectangular holes (4) can cover the hexagonal holes (2).
4. The head structure of a hydrogen fuel honeycomb bionic combustion chamber as claimed in claim 3, wherein the radial width of the annular groove (7) is larger than the distance between the outer side wall surface and the inner side wall surface of one circle of rectangular hole (4) or the distance between the outer side wall surface of the rectangular hole (4) of the outer ring and the inner side wall surface of the rectangular hole of the inner ring when more than two circles are carried out.
5. The head structure of a hydrogen-fueled honeycomb bionic combustion chamber according to claim 1, wherein the blunt body (3) is in a triangular structure having two inclined sides or inclined planes separated in a radial direction, and the inclination angles of the two inclined sides or inclined planes are adjusted according to the flow field organization.
6. A head structure of a hydrogen-fueled honeycomb biomimetic combustion chamber as in claim 5, wherein the two radially spaced beveled edges or bevels meet through a rounded transition.
7. A hydrogen-fueled honeycomb biomimetic combustion head structure according to claim 1, characterized in that the axis of the primary fuel holes (6) is perpendicular to the axis of the head body (1).
8. The hydrogen-fueled honeycomb biomimetic combustion chamber head structure according to claim 7, wherein the aperture diameter of the primary fuel holes (6) is less than 1mm.
9. The head structure of the hydrogen fuel honeycomb bionic combustion chamber as claimed in claim 1, wherein the jet flow channel (31) is communicated with a hydrogen fuel main inlet through a duty round pipe (9) which is radially arranged in the head body (1) to realize the supply of the hydrogen fuel.
10. The head structure of the hydrogen fuel honeycomb bionic combustion chamber as claimed in claim 1, wherein the main combustion channel (5) is communicated with a main hydrogen fuel inlet through a main combustion circular tube (8) radially arranged in the head body (1) to realize the supply of hydrogen fuel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211159910.5A CN115539986B (en) | 2022-09-22 | 2022-09-22 | Hydrogen fuel honeycomb bionic combustion chamber head structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211159910.5A CN115539986B (en) | 2022-09-22 | 2022-09-22 | Hydrogen fuel honeycomb bionic combustion chamber head structure |
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| CN115539986A true CN115539986A (en) | 2022-12-30 |
| CN115539986B CN115539986B (en) | 2024-03-19 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116293800A (en) * | 2023-02-24 | 2023-06-23 | 北京航空航天大学 | Micro-mixing head of combustion chamber, combustion chamber of gas turbine and gas turbine |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2500762A1 (en) * | 2004-04-15 | 2005-10-15 | Snecma Moteurs | Ring-shaped turbine engine combustion chamber with improved internal attachment clamp |
| CN111396927A (en) * | 2020-03-27 | 2020-07-10 | 中国科学院工程热物理研究所 | Two-dimensional array low-pollution combustion device without traditional swirler |
| CN114688559A (en) * | 2022-02-17 | 2022-07-01 | 中国航发沈阳发动机研究所 | High-efficiency mixing head structure of low-emission hydrogen fuel combustion chamber |
-
2022
- 2022-09-22 CN CN202211159910.5A patent/CN115539986B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2500762A1 (en) * | 2004-04-15 | 2005-10-15 | Snecma Moteurs | Ring-shaped turbine engine combustion chamber with improved internal attachment clamp |
| CN111396927A (en) * | 2020-03-27 | 2020-07-10 | 中国科学院工程热物理研究所 | Two-dimensional array low-pollution combustion device without traditional swirler |
| CN114688559A (en) * | 2022-02-17 | 2022-07-01 | 中国航发沈阳发动机研究所 | High-efficiency mixing head structure of low-emission hydrogen fuel combustion chamber |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116293800A (en) * | 2023-02-24 | 2023-06-23 | 北京航空航天大学 | Micro-mixing head of combustion chamber, combustion chamber of gas turbine and gas turbine |
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| CN115539986B (en) | 2024-03-19 |
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