CN115539986B - Hydrogen fuel honeycomb bionic combustion chamber head structure - Google Patents
Hydrogen fuel honeycomb bionic combustion chamber head structure Download PDFInfo
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- CN115539986B CN115539986B CN202211159910.5A CN202211159910A CN115539986B CN 115539986 B CN115539986 B CN 115539986B CN 202211159910 A CN202211159910 A CN 202211159910A CN 115539986 B CN115539986 B CN 115539986B
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- fuel
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- channel
- hexagonal
- head body
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- 239000000446 fuel Substances 0.000 title claims abstract description 79
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 77
- 239000001257 hydrogen Substances 0.000 title claims abstract description 57
- 229910052739 hydrogen Inorganic materials 0.000 title claims abstract description 57
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 title claims abstract description 56
- 239000011664 nicotinic acid Substances 0.000 title claims description 12
- 230000008520 organization Effects 0.000 claims description 5
- 230000003592 biomimetic effect Effects 0.000 claims 1
- 239000003350 kerosene Substances 0.000 description 3
- 238000000034 method Methods 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
- 239000000654 additive Substances 0.000 description 2
- 230000000996 additive effect Effects 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 229930195733 hydrocarbon Natural products 0.000 description 2
- 150000002430 hydrocarbons Chemical class 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000003014 reinforcing effect Effects 0.000 description 2
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000004323 axial length Effects 0.000 description 1
- 239000006227 byproduct Substances 0.000 description 1
- 239000000112 cooling gas Substances 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 239000003344 environmental pollutant Substances 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 230000007774 longterm Effects 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
- 238000004904 shortening Methods 0.000 description 1
- 230000002269 spontaneous effect Effects 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
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
Landscapes
- 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, include: an annular head body, wherein the end face of the head body facing the airflow incoming flow is provided with at least one circle of hexagonal holes, each circle of hexagonal holes comprises a plurality of hexagonal holes, the non-airflow incoming flow end face 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 blunt body is arranged in the hexagonal hole, the blunt body is provided with an axial rearward duty jet channel and a jet channel which is circumferentially arranged and communicated with the duty jet channel, and the jet channel forms a duty main pipe with an annular channel in the head body and is used for supplying fuel to the duty jet channel; the radial side wall of the rectangular hole is provided with a main fuel hole which is shot to the rectangular hole, a main fuel channel is arranged at the position of the head body matched with the main fuel hole, and a main fuel main pipe is formed by the main fuel channel and is used for supplying fuel to the main fuel hole.
Description
Technical Field
The application belongs to the technical field of aero-engines, and particularly relates to a hydrogen fuel honeycomb bionic combustion chamber head structure.
Background
The hydrogen is used as a novel green energy, the reaction byproduct 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 hydrogen fuel has higher reaction rate and flame propagation speed in the combustion process, the combustion speed is faster, the axial length of a combustion chamber can be shortened, and the thrust-weight ratio of an engine can be further improved.
However, because the burning speed of the hydrogen fuel is too high, the traditional aviation kerosene injection mode is extremely easy to cause the 'flash back' of the hydrogen fuel in the burning process, thereby causing the spontaneous combustion and even explosion of the fuel. Meanwhile, the direct use of hydrogen fuel in the existing burner can form stoichiometric conditions in a large flame diffusion surface and generate local high temperature points, and a large amount of NOx gas which is obviously higher than that of the traditional hydrocarbon fuel can be generated near the high temperature points, so that the pollutant emission is improved.
In the prior art, a premixed combustion mode is mainly adopted to reduce NOx after hydrogen fuel combustion, and the method can avoid hot spots in combustion flame, but a special structure is required to be additionally designed to avoid a hydrogen flashback phenomenon. However, under the complex environment of high turbulence and high swirl 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 ensure, and the pre-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 obviously reduced.
Accordingly, there is a need for a hydrogen fuel combustor head structure suitable for use in the field of ground-based engines and aircraft engines.
Disclosure of Invention
The invention aims to provide a hydrogen fuel honeycomb bionic combustion chamber head structure which solves or reduces at least one problem in the background art.
The technical scheme of the application is as follows: a hydrogen fuel honeycomb bionic combustion chamber head structure comprising:
an annular head body, wherein the end face of the head body facing the airflow incoming flow is provided with at least one circle of hexagonal holes, each circle of hexagonal holes comprises a plurality of hexagonal holes, the non-airflow incoming flow end face 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 blunt body is arranged in the hexagonal hole, the blunt body is provided with an axial rearward duty jet channel and a jet channel which is circumferentially arranged and communicated with the duty jet channel, and the jet channel forms a duty main pipe with an annular channel in the head body and is used for supplying fuel to the duty jet channel;
the radial side wall of the rectangular hole is provided with a main fuel hole which is shot to the rectangular hole, a main fuel channel is arranged at the position of the head body matched with the main fuel hole, and a main fuel main pipe is formed by the main fuel channel and is used for supplying fuel to the main fuel hole.
Further, 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 diagonal distance of the 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 and the inner side wall surface of the rectangular hole of one circle 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.
Further, the blunt body is in a triangular structure, two inclined strip edges or inclined planes of the triangular structure are separated in the radial direction, and the inclination angles of the two inclined edges or inclined planes are adjusted according to the flow field organization form.
Further, two radially separated beveled edges or slopes are transitionally connected by a rounded corner.
Further, the axis of the primary fuel bore is perpendicular to the axis of the head body.
Further, the aperture of the main fuel orifice is less than 1mm.
Furthermore, the jet flow channel is communicated with the hydrogen fuel total inlet through a duty round pipe arranged in the head body in the radial direction, so that the supply of the hydrogen fuel is realized.
Furthermore, the main combustion channel is communicated with the main combustion circular pipe arranged in the head body in a radial direction to realize the supply of the hydrogen fuel.
The application provides a bionical combustion chamber head structure of hydrogen fuel honeycomb is through bionical honeycomb head structural design, in limited size scope, when reinforcing combustion chamber head structural strength, promotes the space utilization of combustion reaction, and then realizes light, compact, efficient hydrogen combustion scheme.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following description will briefly refer to the accompanying drawings. It will be apparent that the figures described below are only some embodiments of the present application.
FIG. 1 is a general schematic view of a combustion chamber head structure of the present application.
FIG. 2 is an enlarged view of a portion of the combustion chamber head structure of the present application.
FIG. 3 is a front view of a hex hole and bluff body in the combustion chamber head configuration of the present application.
Fig. 4 is a sectional view taken along line A-A in fig. 2.
Fig. 5 is a sectional view taken along the direction B-B in fig. 2.
Reference numerals:
1-head body
2-Hexagon hole
3-blunt body, 31-jet channel, 32-hydrogen jet hole
4-rectangular hole
5-main combustion channel
6-primary fuel flow holes
7-annular groove
8-main combustion round tube
9-round tube on duty
Detailed Description
In order to make the purposes, technical solutions and advantages of the implementation of the present application more clear, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application.
As shown in fig. 1 to 5, the head structure of the hydrogen fuel honeycomb bionic combustion chamber provided by the application mainly comprises a head body 1.
The head body 1 has a circular ring structure. At least one circle of hexagonal holes 2 is provided on the left side surface (i.e., the surface facing the air flow) of the head body 1, and the number of hexagonal holes 2 per circle is plural. In the illustrated embodiment of the present application, the hexagonal holes 2 are two circles, that is, an inner ring hexagonal hole and an outer ring hexagonal hole, and the shape and the size of the hexagonal holes 2 in the inner ring hexagonal hole and the outer ring hexagonal hole are identical, so that the number of the outer ring hexagonal holes 2 is 24, and the number of the inner ring hexagonal holes 2 is 20. The hexagonal cells 2 resemble closely packed hexagonal cells within a honeycomb, and the overall combustion chamber head structure forms a honeycomb-like configuration by virtue of the hexagonal arrangement of the structure known as the honeycomb structure.
The hexagonal holes 2 on the head body 1 are provided with rectangular holes 4 matched with the hexagonal holes 2 on the rear side, the rectangular holes 4 extend backwards for a certain distance and do not extend to the right end face, the number of the rectangular holes 4 in each circle is also matched with the number of the hexagonal holes 2 in each circle, and the positions of the rectangular holes 4 are also matched with the positions of the hexagonal holes 2. For example, in the illustrated embodiment of the present application, the rectangular holes 4 are also two circles, the number of rectangular holes 4 of the outer ring is 24, the number of rectangular holes 4 of the inner ring is 20, and the center of the rectangular holes 4 is adapted to the center of the hexagonal holes 2.
In the preferred embodiment of the present application, the hexagonal hole 2 is a regular hexagon, and the width of the rectangular hole 4 is not smaller than the width W of the hexagonal hole, and the length of the rectangular hole 4 is not smaller than the distance L between two opposite points of the hexagonal hole, so that the rectangular hole 4 can completely cover or wrap the hexagonal hole 2.
A blunt body 3 is provided inside each hexagonal hole 2 for enhancing flame holding. The blunt body 3 has the same width W as the hexagonal hole 2 and is disposed in the hexagonal hole 2 perpendicular to the line connecting the two radial points of the hexagonal hole 2. After a plurality of blunt bodies 3 are disposed in the hexagonal hole 2, a circular shape may be formed substantially.
The blunt body 3 is in a triangular structure in the direction facing the air flow, two inclined strip edges or inclined planes are separated in the radial direction, the two inclined strip edges or inclined planes are transitionally connected through a round angle, and the inclination angles of the two inclined edges or inclined planes can be adjusted according to the flow field organization form.
Each blunt 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 point and flameout boundary of the combustion chamber. Annular jet channels 31 are arranged in the blunt body 3 and the head body 1, the jet channels 31 form a jet manifold, and a hydrogen jet circular hole 32 in each blunt body 3 is used for supplying hydrogen fuel through the jet channels 31. The hydrogen fuel injected through the hydrogen jet circular holes 32 burns to form the duty-level flame of the combustion chamber, and the stable working boundary of the combustion chamber can be further widened through the duty-level flame, so that the stable flame is convenient to regulate and control.
A pair of (i.e., two) main fuel holes 6 are provided in opposition to each other on the side wall of each rectangular hole 4, the main fuel holes 6 being 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 flow holes 6, and hydrogen fuel is introduced into the main combustion channel 5, so that the hydrogen fuel can uniformly jet fuel into the rectangular holes 4 from the main combustion flow holes 6 distributed in the circumferential direction, and the combustion of the main combustion stage flame is completed.
In the preferred embodiment of the present application, the primary fuel flow holes 6 are perpendicular to the primary fuel flow direction, and the primary fuel flow holes 6 have a diameter of less than 1mm to enhance the transverse jet strength, thereby facilitating flame holding and adequate combustion.
As shown in the schematic layout of the main fuel stage flow path shown in fig. 4, the main fuel stage flow path has two circles of rectangular holes 4, and for each circle of rectangular holes 4, a pair of main fuel holes 6 are provided on the side walls on the upper and lower sides in the radial direction for supplying hydrogen into the rectangular holes 4, and the main fuel holes 6 on the two side walls supply hydrogen through the annular main fuel passage 5. Wherein, three main combustion channels 5 are arranged in the head body 1 outside the rectangular hole 4, and hydrogen is supplied to the main combustion flow holes 6 communicated with the main combustion channels 5 in pairs. The three main combustion channels 5 are equivalent to a hydrogen main pipe and finally are converged on the main combustion circular pipe 8, and the main combustion circular pipe 8 passes through the head body 1 and then is connected with a hydrogen main inlet.
As shown in the schematic layout of the on-duty flow path shown in fig. 5, the on-duty flow path has two circles of hexagonal holes 2, for each circle of hexagonal holes 2, a blunt body 3 is arranged in the hexagonal holes 2, the blunt body 3 is internally provided with an axial backward on-duty jet hole 32, the on-duty jet hole 32 supplies hydrogen through an annular on-duty channel 31, and meanwhile, an annular channel is arranged on the head body 1 at a position matched with the on-duty channel 31, the annular channel and the on-duty channel 31 together form an on-duty manifold, the two on-duty manifolds are gathered in an on-duty circular tube 9, and the on-duty circular tube 9 passes through the head body 1 and then is connected with a hydrogen total inlet.
The airflow of the rectangular hole 4 on the head body 1 flows to the rear side 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 a plurality of circles of 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 the two turns of the rectangular aperture 6.
In the application, the internal flow path of the head structure of the hydrogen fuel honeycomb bionic combustion chamber is complex, and in order to realize the processing of the structure, the processing can be performed by adopting a 3D additive manufacturing mode.
In operation, mainstream air is admitted through the hexagonal holes 2 of the head body 1, downstream of the bluff body 3 in each hexagonal hole 2, and thoroughly mixed with hydrogen in a pair of main fuel holes 6 in the rectangular hole 4 to form a pair of tiny recirculation zones, thereby forming a tiny flame mass to form a main fuel stage flame; meanwhile, the 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 a value class, so that the flameout boundary of the combustion chamber can be remarkably widened.
The combustion chamber head structure can enable hundreds of thousands of tiny flame groups to be formed in the combustion chamber, the hydrogen combustion rate is high, the required flame tube length is short, and a large amount of flame tube cooling gas is saved. The air and hydrogen in each micro flame group can realize lean oil non-premixed combustion, the combustion is sufficient, the efficiency is high, and the local hot spots in the flame are greatly reduced, so that the NOx emission is obviously reduced, and the 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 hydrogen fuel honeycomb bionic combustion chamber head structure provided by the application, the number of the hexagonal holes 2 is more, tens or hundreds of the hexagonal holes can be usually achieved, the hydrogen flow path is complex in layout, and the combustion chamber head structure can be integrally formed through a 3D additive manufacturing technology for simplifying the process, so that the hydrogen fuel jet layout inside the head structure is realized, and micro-scale non-premixed combustion is realized. As the hydrogen combustion rate is high, the micro-scale non-premixed combustion organization mode can burn in a short range with high efficiency, thereby shortening the length of the flame tube, reducing the weight of the combustion chamber, widening the lean oil flameout boundary of the combustion chamber and improving the thrust-weight ratio of the engine.
The application provides a bionical combustion chamber head structure of hydrogen fuel honeycomb is through bionical honeycomb head structural design, in limited size scope, when reinforcing combustion chamber head structural strength, promotes the space utilization of combustion reaction, and then realizes light, compact, efficient hydrogen combustion scheme.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in 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 (5)
1. A hydrogen fuel honeycomb bionic combustion chamber head structure, comprising:
an annular head body (1), wherein the end face of the head body (1) facing the airflow inflow is provided with at least one circle of hexagonal holes (2), each circle of hexagonal holes (2) comprises a plurality of annular grooves (7), the distance between the outer side wall surface of the hexagonal holes (4) and the inner side wall surface of the annular grooves (7) when the head body (1) is not in airflow inflow is larger than the distance between the outer side wall surface of the hexagonal holes (4) when the annular grooves (7) are in one circle or the distance between the outer side wall surface of the rectangular holes (4) of the outer ring and the inner side wall surface of the rectangular holes of the inner ring when the annular grooves (7) are in more than two circles, the length and the width of the rectangular holes (4) are configured to be not smaller than the opposite side distance or the diagonal distance between the hexagonal holes (2) of the regular hexagon, and thus the rectangular holes (4) can cover the hexagonal holes (2);
the blunt body (3) is arranged in the hexagonal hole (2), the blunt body (3) is in a triangular structure, two oblique sides or inclined planes of the triangular structure are separated in the radial direction and are transitionally connected through a round angle, the inclination angles of the two oblique sides or inclined planes are adjusted according to a flow field organization form, the blunt body (3) is provided with an axially backward duty jet channel (32) and a jet channel (31) which is circumferentially arranged and communicated with the duty jet channel (32), and the jet channel (31) forms a duty manifold through an annular channel in the head body (1) and is used for supplying fuel to the duty jet channel (32);
the radial side wall of the rectangular hole (4) is provided with a main fuel hole (6) which shoots the rectangular hole (4), the axis of the main fuel hole (6) is perpendicular to the axis of the head body (1), a main fuel channel (5) is arranged at the position of the head body (1) matched with the main fuel hole (6), and a main fuel manifold is formed by the main fuel channel (5) and is used for supplying fuel to the main fuel hole (6).
2. The hydrogen fuel honeycomb bionic combustion chamber head structure according to claim 1, wherein the number of turns of the hexagonal hole (2) is 2-3.
3. A hydrogen-fuelled honeycomb biomimetic combustor head structure as claimed in claim 1, wherein the aperture of the primary fuel flow aperture (6) is less than 1mm.
4. The head structure of the hydrogen fuel honeycomb bionic combustion chamber according to claim 1, wherein the jet flow channel (31) is communicated with a hydrogen fuel total inlet through a duty round pipe (9) which is arranged in the inner diameter of the head body (1) to realize the supply of the hydrogen fuel.
5. The head structure of the hydrogen fuel honeycomb bionic combustion chamber according to claim 1, wherein the main combustion channel (5) is communicated with a hydrogen fuel total inlet through a main combustion circular pipe (8) which is arranged in the inner diameter of the head body (1) to realize the supply of the 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 |
Applications Claiming Priority (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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| Publication Number | Publication Date |
|---|---|
| CN115539986A CN115539986A (en) | 2022-12-30 |
| CN115539986B true CN115539986B (en) | 2024-03-19 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202211159910.5A Active CN115539986B (en) | 2022-09-22 | 2022-09-22 | Hydrogen fuel honeycomb bionic combustion chamber head structure |
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| 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 |
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| CN115539986A (en) | 2022-12-30 |
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