CN116592397A - Hydrogen fuel combustion chamber head structure - Google Patents
Hydrogen fuel combustion chamber head structure Download PDFInfo
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- CN116592397A CN116592397A CN202310552053.3A CN202310552053A CN116592397A CN 116592397 A CN116592397 A CN 116592397A CN 202310552053 A CN202310552053 A CN 202310552053A CN 116592397 A CN116592397 A CN 116592397A
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- Prior art keywords
- stage
- nozzle
- cyclone
- primary
- blade
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 77
- 239000001257 hydrogen Substances 0.000 title claims abstract description 66
- 229910052739 hydrogen Inorganic materials 0.000 title claims abstract description 66
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 title claims abstract description 62
- 239000000446 fuel Substances 0.000 title claims abstract description 42
- 239000007921 spray Substances 0.000 claims description 41
- 238000003466 welding Methods 0.000 claims description 9
- 238000010146 3D printing Methods 0.000 claims description 8
- JTJMJGYZQZDUJJ-UHFFFAOYSA-N phencyclidine Chemical class C1CCCCN1C1(C=2C=CC=CC=2)CCCCC1 JTJMJGYZQZDUJJ-UHFFFAOYSA-N 0.000 claims description 6
- 239000007789 gas Substances 0.000 claims description 4
- 150000002431 hydrogen Chemical class 0.000 claims description 4
- 230000006641 stabilisation Effects 0.000 abstract description 4
- 238000011105 stabilization Methods 0.000 abstract description 4
- 238000002156 mixing Methods 0.000 description 8
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 6
- 230000009286 beneficial effect Effects 0.000 description 5
- 230000000694 effects Effects 0.000 description 3
- 230000008520 organization Effects 0.000 description 3
- 239000002803 fossil fuel Substances 0.000 description 2
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000008033 biological extinction Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000003245 coal Substances 0.000 description 1
- 238000003912 environmental pollution Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
- 239000003208 petroleum Substances 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 238000005496 tempering 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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/58—Cyclone or vortex type 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
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
-
- 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 invention discloses a hydrogen fuel combustion chamber head structure, which comprises a multi-stage nozzle, a multi-stage cyclone, an outer cover and a plurality of air inlet pipes, wherein the multi-stage nozzle, the multi-stage cyclone and the outer cover are sequentially connected into a whole from inside to outside, and the multi-stage nozzle and the multi-stage cyclone are alternately distributed; the air inlet pipes are respectively communicated with the multi-stage nozzles. The hydrogen is sprayed from the multi-stage nozzle in a multi-layer and multi-point mode, and meanwhile, the multi-stage air cyclone is adopted, so that the air can be better mixed and combusted with the hydrogen jet, flame stabilization is realized, the requirement of a combustion chamber on a wide working range is met, and the combustion performance of hydrogen fuel is improved.
Description
Technical Field
The invention relates to the technical field of hydrogen fuel combustion chambers, such as combustion chambers of aero-engines, hydrogen fuel air rocket thrust chambers or combustion chambers of other hydrogen fuel aerospace engines, in particular to a head structure of a hydrogen fuel combustion chamber.
Background
Nowadays, fossil fuels such as coal, petroleum, natural gas and the like are gradually exhausted, and emissions generated by burning the fossil fuels cause serious environmental pollution. Finding alternative fuels in different energy application fields has become a problem to be solved. In the aerospace field, hydrogen is widely favored as an alternative fuel. Hydrogen is a very clean fuel, combustion products only contain water, in addition, hydrogen is the fuel with the highest heat value, which is 2.8 times that of common aviation fuel, the flammability boundary of hydrogen is wider than other fuels, the ignition time of hydrogen is short, the diffusivity is high, the hydrogen has the highest heat conductivity in gas, the high heat capacity and the low viscosity, and the hydrogen is suitable for the operation of high Mach number aircrafts and strong precooling high-temperature rise combustion chambers.
However, hydrogen fuel has some problems in its application to aero gas turbines and air rocket engines due to its special physicochemical properties. Under the condition that the hydrogen fuel is combusted in a close chemical proper ratio, a large amount of nitrogen oxides can be generated to endanger the atmosphere, in a low-emission gas turbine, the combustion mode of the hydrogen fuel is a micro-mixing mode, the structure is more complicated, so that the combustion is similar to premixed combustion, the emission of the nitrogen oxides is reduced, the hydrogen fuel is applied to a hypersonic aircraft, under the working condition of large Mach number, the hydrogen combustion with high equivalent ratio is unavoidable, and at the moment, the premixed combustion mode is not applicable any more; and because the flameout boundary of hydrogen is leaner than other fuels, the flame propagation speed of hydrogen is very fast, and the prevention of backfire becomes important, and although the backflow area generated by the rotational flow can stabilize flame, the backfire can be generated due to the too high hydrogen combustion speed and the too strong rotational flow, so that the head is burnt out, and the danger is further caused.
Therefore, providing a hydrogen fuel combustor head structure that is efficient and stable is a problem that one skilled in the art would be highly aware of.
Disclosure of Invention
In view of the above, the present invention provides a hydrogen fuel combustion chamber head structure capable of improving the combustion performance of hydrogen fuel in a combustion chamber, and realizing efficient and stable combustion of the combustion chamber in a wide working range.
In order to achieve the above purpose, the present invention adopts the following technical scheme:
the head structure of the hydrogen fuel combustion chamber comprises a multi-stage nozzle, a multi-stage cyclone, an outer cover and a plurality of air inlet pipes, wherein the multi-stage nozzle, the multi-stage cyclone and the outer cover are sequentially connected into a whole from inside to outside, and the multi-stage nozzle and the multi-stage cyclone are alternately distributed; and the air inlet pipes are respectively communicated with the multi-stage nozzles.
By adopting the technical scheme, the invention has the beneficial effects that:
the hydrogen is sprayed from multiple layers of multiple points of the multiple nozzles in a jet flow mode, and meanwhile, multiple air rotational flows are adopted, so that air can be better mixed and combusted with the hydrogen jet flow, flame stabilization is realized, the combustion performance of hydrogen fuel is improved, and the requirement of a combustion chamber for a wide working range is met.
Further, the number of the nozzles is 2-4, the number of the cyclones is 2-4, and correspondingly, the number of the air inlet pipes is 2-4.
Further, the nozzles are a first-stage nozzle, a second-stage nozzle and a third-stage nozzle respectively, the cyclones are a first-stage cyclone, a second-stage cyclone and a third-stage cyclone respectively, the air inlet pipes are a first air inlet pipe, a second air inlet pipe and a third air inlet pipe respectively, the first-stage nozzle, the first-stage cyclone, the second-stage nozzle, the second-stage cyclone, the third-stage nozzle, the third-stage cyclone and the outer cover are sequentially distributed from inside to outside, the first-stage nozzle and the first-stage cyclone are integrally formed through 3D printing, and the first-stage cyclone is in spot welding connection with the second-stage nozzle; the secondary nozzle and the secondary cyclone are integrally formed through 3D printing, and the secondary cyclone is in spot welding connection with the tertiary nozzle; the three-stage nozzle and the three-stage cyclone are integrally formed through 3D printing; the three-stage cyclone is in spot welding connection with the outer cover; the first air inlet pipe is communicated with the primary nozzle; the second air inlet pipe is communicated with the secondary nozzle; the third air inlet pipe is communicated with the three-stage nozzle.
Further, the conical surface of the extending end of the primary nozzle is provided with a plurality of primary spray holes which are uniformly distributed along the circumferential direction, the diameter of each primary spray hole is 1-2mm, the included angle between the central line of each primary spray hole and the axis of the primary nozzle is 40-50 degrees, and the length-diameter ratio of each primary spray hole is 2-3; the number of the primary blades of the primary cyclone is 8-15, each primary blade is a straight blade or a bent blade, the inclination angle between each primary blade and the axis of the primary cyclone is 15-36 degrees, the thickness of each primary blade is 0.8-1.2mm, the height of each primary blade is 6-16mm, the swirl number of the primary cyclone is 0.4-0.55, and the flow area of the primary cyclone accounts for 10-15% of the total flow area of the head of the combustion chamber.
Further, the secondary nozzle is of an annular structure, the diameter is 6-8mm, the wall thickness is 1-1.5mm, and the secondary nozzle is in clearance fit with the primary cyclone; the conical surface of the extending end of the secondary nozzle is provided with a plurality of secondary spray holes which are uniformly distributed along the circumferential direction, the diameter of each secondary spray hole is 2-3mm, the included angle between the central line of each secondary spray hole and the axis of the secondary nozzle is 35-50 degrees, and the length-diameter ratio of each secondary spray hole is 2-2.5; the number of the secondary blades of the secondary cyclone is 12-30, each secondary blade is a straight blade or a bent blade, the inclination angle between each secondary blade and the axis of the secondary cyclone is 15-30 degrees, the thickness of each secondary blade is 0.8-1.2mm, the height of each secondary blade is 6-20mm, the swirl number of the secondary cyclone is 0.4-0.55, and the flow area of the secondary cyclone accounts for 25-30% of the total flow area of the head of the combustion chamber.
Further, the three-stage nozzle is of an annular structure, the diameter is 6-8mm, the wall thickness is 1-1.5mm, and the three-stage nozzle is in clearance fit with the secondary cyclone; the conical surface of the extension end of the three-stage nozzle is provided with a plurality of three-stage spray holes which are uniformly distributed along the circumferential direction, the diameter of each three-stage spray hole is 2-3mm, the included angle between the central line of each three-stage spray hole and the axis of the three-stage nozzle is 35-50 degrees, and the length-diameter ratio of each three-stage spray hole is 2-2.5; the three-stage cyclone is characterized in that the number of three-stage blades of the three-stage cyclone is 20-36, each three-stage blade is a straight blade or a bent blade, the inclination angle between each three-stage blade and the axis of the three-stage cyclone is 15-30 degrees, the thickness of each three-stage blade is 0.8-1.2mm, the height of each three-stage blade is 10-30mm, the swirl number of the three-stage cyclone is 0.4-0.55, and the flow area of the three-stage cyclone accounts for 60-65% of the total flow area of the head of the combustion chamber.
Further, the area ratio of the first air inlet pipe to the second air inlet pipe to the area ratio of the third air inlet pipe are 1:4:8, and correspondingly, the area ratio of the primary nozzle to the secondary nozzle to the tertiary nozzle spray holes is 1:4:8.
Further, the inner side of the outlet of the outer cover is provided with a molded surface matched with the three-stage nozzle and the three-stage cyclone so as to form an airflow channel.
Further, the primary nozzle is internally trapped in the secondary nozzle, and the axial distance between the extending end face of the primary nozzle and the extending end face of the secondary nozzle is 8-12mm; the secondary nozzle is trapped in the tertiary nozzle, and the axial distance between the extending end face of the secondary nozzle and the extending end face of the tertiary nozzle is 10-12mm.
Therefore, compared with the prior art, the hydrogen fuel combustion chamber head structure has the following beneficial effects:
1) The multi-stage air swirling flow is matched with multi-layer multipoint hydrogen injection, the air and the hydrogen are uniformly mixed, central grading is adopted, the fuel is uniformly distributed, the heat energy generated by hydrogen combustion is completely released, the high-efficiency stable combustion in an ultra-wide working range equivalent ratio, such as 0.05-1.5, is realized, and the rapid change of working conditions is adapted;
2) The multistage air rotational flow design can adjust the air flow area of the head structure according to the actual parameter requirement of the combustion chamber, and the air flow area adjusting range is 2000-15000mm 2 To meet the design requirements of different air flow or different scale combustion chambers;
3) The application range is wide, and the burner can be used for different types of combustion chambers, such as a single-tube combustion chamber, an annular combustion chamber or an air and hydrogen rocket combustion chamber;
4) Short processing period and low cost.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required to be used in the embodiments or the description of the prior art will be briefly described below, and it is obvious that the drawings in the following description are only embodiments of the present invention, and that other drawings can be obtained according to the provided drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic perspective view of a hydrogen fuel combustion chamber head structure according to the present invention;
FIG. 2 is a schematic cross-sectional view of a hydrogen fuel combustor head structure in accordance with the present invention;
FIG. 3 is a schematic perspective view of a primary nozzle and a primary cyclone according to the present invention;
FIG. 4 is a side view of FIG. 3;
FIG. 5 is a cross-sectional view taken along line A-A of FIG. 4;
FIG. 6 is a schematic perspective view of a secondary nozzle and a secondary cyclone provided by the invention;
FIG. 7 is a side view of FIG. 6;
FIG. 8 is a cross-sectional view taken along line A-A of FIG. 7;
FIG. 9 is a schematic perspective view of a three-stage nozzle and three-stage swirler according to the present invention;
FIG. 10 is a side view of FIG. 9;
FIG. 11 is a cross-sectional view taken along line A-A of FIG. 10;
FIG. 12 is a schematic perspective view of the cover according to the present invention;
fig. 13 is a cross-sectional view of a housing provided by the present invention.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
1-13, the embodiment of the invention discloses a head structure of a hydrogen fuel combustion chamber, which aims at a combustion chamber with an ultra-wide working range, such as a combustion chamber with a chemical appropriate ratio of 0.05-1.5 and a combustion chamber temperature rise of 200-1800K, and comprises a multi-stage nozzle, a multi-stage cyclone, an outer cover 1 and a plurality of air inlet pipes, wherein the multi-stage nozzle, the multi-stage cyclone and the outer cover 1 are sequentially connected into a whole from inside to outside, and the multi-stage nozzle and the multi-stage cyclone are alternately distributed; the air inlet pipes are respectively communicated with the multi-stage nozzles. The hydrogen is sprayed from multiple stages of nozzles in multiple layers in a jet flow mode, and meanwhile, the multi-stage air rotational flow is adopted, so that air can be better mixed and combusted with the hydrogen jet flow, flame stabilization is realized, the combustion performance of hydrogen fuel in a combustion chamber is improved, and in a word, the hydrogen fuel is applied to the combustion chamber to meet the requirements of ultra-wide working range, stable working condition conversion, good fuel and air mixing effect, high combustion efficiency, difficult tempering, flameout, good stability and the like.
Specifically, the number of the nozzles is 2-4, the number of the cyclones is 2-4, correspondingly, the number of the air inlet pipes is 2-4, in the embodiment, the number of the nozzles is 3, the number of the cyclones is 3, the number of the air inlet pipes is also 3, specifically, the multi-stage nozzles are respectively a first-stage nozzle 2, a second-stage nozzle 3 and a third-stage nozzle 4, the first-stage nozzle 2 can work independently, the second-stage nozzle 3 and the third-stage nozzle 4 can work independently under the working condition of the equivalent ratio of 0.05, the multi-stage cyclones are respectively a first-stage cyclone 5, a second-stage cyclone 6 and a third-stage cyclone 7, the plurality of air inlet pipes are respectively a first air inlet pipe 8, a second air inlet pipe 9 and a third air inlet pipe 10, the first-stage nozzle 2, the first-stage cyclone 5, the second-stage nozzle 3, the second-stage cyclone 6, the third-stage nozzle 4, the third-stage cyclone 7 and the housing 1 are distributed sequentially from inside to outside, the first-stage nozzle 2 and the first-stage cyclone 5 are printed integrally, and the first-stage cyclone 5 and the second-stage nozzle 3 are connected by spot welding; the secondary nozzle 3 and the secondary cyclone 6 are integrally formed through 3D printing, and the secondary cyclone 6 is connected with the tertiary nozzle 4 through spot welding; the three-stage nozzle 4 and the three-stage cyclone 7 are integrally formed through 3D printing; the tertiary cyclone 7 is in spot welding connection with the outer cover 1; the first air inlet pipe 8 is communicated with the primary nozzle 2; the second air inlet pipe 9 is communicated with the secondary nozzle 3; the third air inlet pipe 10 is communicated with the three-stage nozzle 4.
Specifically, the conical surface of the extending end of the primary nozzle 2 is provided with a plurality of primary spray holes 21 which are uniformly distributed along the circumferential direction, so as to realize the purposes of grading and uniformly mixing the fuel center, in the embodiment, the number of the primary spray holes 21 is 6-10, the diameter of each primary spray hole 21 is 1-2mm, the included angle between the central line of each primary spray hole 21 and the axis of the primary nozzle 2 is 40-50 degrees, and the length-diameter ratio of each primary spray hole 21 is 2-3; the number of the first-stage blades 51 of the first-stage swirler 5 is 8-15, each first-stage blade 51 is a straight blade or a bent blade, the inclination angle between each first-stage blade 51 and the axis of the first-stage swirler 5 is 15-36 degrees, the thickness of each first-stage blade 51 is 0.8-1.2mm, the height is 6-16mm, the swirl number of the first-stage swirler 5 is 0.4-0.55, the flow area of the first-stage swirler 5 occupies 10-15% of the total flow area of the head of the combustion chamber, and the specific structural parameter selection depends on the air flow and the scale of the combustion chamber.
Specifically, the secondary nozzle 3 is in an annular structure, the diameter is 6-8mm, the wall thickness is 1-1.5mm, and the secondary nozzle 3 is in clearance fit with the primary cyclone 5; the conical surface of the extending end of the secondary nozzle 3 is provided with a plurality of secondary spray holes 31 which are uniformly distributed along the circumferential direction, the number of the secondary spray holes 31 is 20-30, the diameter of each secondary spray hole 31 is 2-3mm, the included angle between the central line of each secondary spray hole 31 and the axis of the secondary nozzle 3 is 35-50 degrees, and the length-diameter ratio of each secondary spray hole 31 is 2-2.5; the number of the secondary blades 61 of the secondary cyclone 6 is 12-30, each secondary blade 61 is a straight blade or a bent blade, the inclination angle between each secondary blade 61 and the axis of the secondary cyclone 6 is 15-30 degrees, the thickness of each secondary blade 61 is 0.8-1.2mm, the height is 6-20mm, the swirl number of the secondary cyclone 6 is 0.4-0.55, the flow area of the secondary cyclone 6 accounts for 25-30% of the total flow area of the head of the combustion chamber, and the specific structural parameter selection depends on the air flow and the scale of the combustion chamber.
Specifically, the three-stage nozzle 4 is in an annular structure, the diameter is 6-8mm, the wall thickness is 1-1.5mm, and the three-stage nozzle 4 is in clearance fit with the secondary cyclone 6; the conical surface of the extending end of the three-stage nozzle 4 is provided with a plurality of three-stage spray holes 41 which are uniformly distributed along the circumferential direction, the number of the three-stage spray holes 41 is 40-60, the diameter of each three-stage spray hole 41 is 2-3mm, the included angle between the central line of each three-stage spray hole 41 and the axis of the three-stage nozzle 4 is 35-50 degrees, and the length-diameter ratio of each three-stage spray hole 41 is 2-2.5; the number of the three-stage blades 71 of the three-stage cyclone 7 is 20-36, each three-stage blade 71 is a straight blade or a bent blade, the inclination angle between each three-stage blade 71 and the axis of the three-stage cyclone 7 is 15-30 degrees, the thickness of each three-stage blade 71 is 0.8-1.2mm, the height is 10-30mm, the swirl number of the three-stage cyclone 7 is 0.4-0.55, the flow area of the three-stage cyclone 7 occupies 60-65% of the total flow area of the head of the combustion chamber, and the specific structural parameter selection depends on the air flow and the scale of the combustion chamber.
Specifically, the area ratio of the first air inlet pipe 8, the second air inlet pipe 9 and the third air inlet pipe 10 is 1:4:8, and correspondingly, the area ratio of the spray holes of the primary nozzle 2, the secondary nozzle 3 and the tertiary nozzle 4 is 1:4:8.
Specifically, the inner side of the outlet of the outer cover 1 is provided with a molded surface 11 matched with the three-stage nozzle 4 and the three-stage cyclone 7 to form an airflow channel, thereby being beneficial to forming an optimal flow field and controlling the flame structure and the heat release distribution.
Specifically, the primary nozzle 2 is embedded in the secondary nozzle 3, and the axial distance between the extending end surface of the primary nozzle 2 and the extending end surface of the secondary nozzle 3 is 8-12mm; the secondary nozzle 3 is trapped in the tertiary nozzle 4, and the axial distance between the extending end surface of the secondary nozzle 3 and the extending end surface of the tertiary nozzle 4 is 10-12mm, so that the flames of the nozzles at all levels are mutually connected better, combined for combustion, and the flames are more rapidly propelled along the radial direction, thereby being beneficial to combustion.
The working principle of the invention is as follows:
the multi-stage rotational flow and hydrogen multi-layer multi-point jet combustion organization mode is adopted. The theoretical basis of the combustion organization mode is that a plurality of transverse jet flows and rotational flows interact to generate a complex flow structure and a flame structure, so that the uniform mixing of hydrogen fuel and air is achieved, and the requirement of large-scale combustion is met. From the microscopic view, the hydrogen jet transversely (or obliquely) enters into the swirling air, the track of the hydrogen jet is similar to a parabolic shape, the hydrogen jet is finally consistent with the axial movement direction of the swirling flow, a pair of counter-rotating vortex pairs are generated in the core area of the hydrogen jet, a vortex of a shear layer is generated on the windward side along the track direction of the hydrogen jet, a horseshoe vortex is generated at the root of the jet, and a three-dimensional wake vortex is generated on the leeward side of the jet, so that the mixing and flame stabilization are facilitated. The hydrogen jet also has a strength and weakness, and is measured by a jet momentum ratio, the larger the jet momentum ratio is, the deeper penetration is, and the more obvious wake vortex is, and the jet momentum ratio of the jet generated by a single hydrogen jet hole at the head part of the combustion chamber is about 3-6. From a macroscopic point of view, this combustion organization is clearly reflected in the design of the combustion chamber. The local equivalent ratio of the hydrogen in the central primary nozzle 2 to the air passing through the primary cyclone 5 can meet the minimum requirement of hydrogen ignition (namely, lean flame extinction boundary) and the requirement of the combustion chamber at the minimum working point, and can work independently. In addition, in order to stabilize the flame, the area is designed to be rich in fuel, when the outer ring nozzle works, the ignition of the secondary nozzle 3 and the tertiary nozzle 4 is supported, the effect of 'duty flame' is achieved, the effect of hierarchical relay combustion is achieved, and meanwhile the requirement of a wide working range is met. That is, the following is true. The multi-stage nozzles may be operated individually or in combination. When the combustion chamber is in the maximum working state, all the nozzles are used for combustion, the multi-layer multipoint injection is utilized to strengthen the mixing of air and hydrogen by utilizing the microcosmic working principle, the uniform mixing is achieved, the oxygen is fully utilized, the combustion efficiency is improved, and the uniformity of the outlet temperature of the combustion chamber is improved. In addition, the two-level and three-level jet hydrogen jet flows and the two-level air package are beneficial to uniform blending and combustion.
In the present specification, each embodiment is described in a progressive manner, and each embodiment is mainly described in a different point from other embodiments, and identical and similar parts between the embodiments are all enough to refer to each other. For the device disclosed in the embodiment, since it corresponds to the method disclosed in the embodiment, the description is relatively simple, and the relevant points refer to the description of the method section.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (9)
1. The head structure of the hydrogen fuel combustion chamber is characterized by comprising a multi-stage nozzle, a multi-stage cyclone, an outer cover and a plurality of air inlet pipes, wherein the multi-stage nozzle, the multi-stage cyclone and the outer cover are sequentially connected into a whole from inside to outside, and the multi-stage nozzle and the multi-stage cyclone are alternately distributed; and the air inlet pipes are respectively communicated with the multi-stage nozzles.
2. A hydrogen combustion chamber head structure according to claim 1, wherein the number of the nozzles is 2 to 4, the number of the swirlers is 2 to 4, and accordingly, the number of the intake pipes is 2 to 4.
3. The head structure of a hydrogen fuel combustion chamber according to claim 2, wherein the nozzles are a first-stage nozzle, a second-stage nozzle and a third-stage nozzle, the cyclones are a first-stage cyclone, a second-stage cyclone and a third-stage cyclone, the air inlet pipes are a first air inlet pipe, a second air inlet pipe and a third air inlet pipe, the first-stage nozzle, the second-stage cyclone, the third-stage nozzle, the third-stage cyclone and the outer cover are distributed in sequence from inside to outside, the first-stage nozzle and the first-stage cyclone are integrally formed through 3D printing, and the first-stage cyclone is in spot welding connection with the second-stage nozzle; the secondary nozzle and the secondary cyclone are integrally formed through 3D printing, and the secondary cyclone is in spot welding connection with the tertiary nozzle; the three-stage nozzle and the three-stage cyclone are integrally formed through 3D printing; the three-stage cyclone is in spot welding connection with the outer cover; the first air inlet pipe is communicated with the primary nozzle; the second air inlet pipe is communicated with the secondary nozzle; the third air inlet pipe is communicated with the three-stage nozzle.
4. A hydrogen fuel combustion chamber head structure according to claim 3, wherein the conical surface of the extension end of the primary nozzle is provided with a plurality of primary spray holes uniformly distributed along the circumferential direction, the diameter of each primary spray hole is 1-2mm, the included angle between the central line of each primary spray hole and the axis of the primary nozzle is 40-50 degrees, and the length-diameter ratio of each primary spray hole is 2-3; the number of the primary blades of the primary cyclone is 8-15, each primary blade is a straight blade or a bent blade, the inclination angle between each primary blade and the axis of the primary cyclone is 15-36 degrees, the thickness of each primary blade is 0.8-1.2mm, the height of each primary blade is 6-16mm, the swirl number of the primary cyclone is 0.4-0.55, and the flow area of the primary cyclone accounts for 10-15% of the total flow area of the head of the combustion chamber.
5. A hydrogen fuel combustion chamber head structure as claimed in claim 3, wherein said secondary nozzle is of annular configuration having a diameter of 6-8mm and a wall thickness of 1-1.5mm, said secondary nozzle being in clearance fit with said primary swirler; the conical surface of the extending end of the secondary nozzle is provided with a plurality of secondary spray holes which are uniformly distributed along the circumferential direction, the diameter of each secondary spray hole is 2-3mm, the included angle between the central line of each secondary spray hole and the axis of the secondary nozzle is 35-50 degrees, and the length-diameter ratio of each secondary spray hole is 2-2.5; the number of the secondary blades of the secondary cyclone is 12-30, each secondary blade is a straight blade or a bent blade, the inclination angle between each secondary blade and the axis of the secondary cyclone is 15-30 degrees, the thickness of each secondary blade is 0.8-1.2mm, the height of each secondary blade is 6-20mm, the swirl number of the secondary cyclone is 0.4-0.55, and the flow area of the secondary cyclone accounts for 25-30% of the total flow area of the head of the combustion chamber.
6. A hydrogen fuel combustion chamber head structure as claimed in claim 3, wherein said tertiary nozzle is of annular configuration having a diameter of 6-8mm and a wall thickness of 1-1.5mm, said tertiary nozzle being in clearance fit with said secondary swirler; the conical surface of the extension end of the three-stage nozzle is provided with a plurality of three-stage spray holes which are uniformly distributed along the circumferential direction, the diameter of each three-stage spray hole is 2-3mm, the included angle between the central line of each three-stage spray hole and the axis of the three-stage nozzle is 35-50 degrees, and the length-diameter ratio of each three-stage spray hole is 2-2.5; the three-stage cyclone is characterized in that the number of three-stage blades of the three-stage cyclone is 20-36, each three-stage blade is a straight blade or a bent blade, the inclination angle between each three-stage blade and the axis of the three-stage cyclone is 15-30 degrees, the thickness of each three-stage blade is 0.8-1.2mm, the height of each three-stage blade is 10-30mm, the swirl number of the three-stage cyclone is 0.4-0.55, and the flow area of the three-stage cyclone accounts for 50-60% of the total flow area of the head of the combustion chamber.
7. A hydrogen fuel combustor head structure according to claim 3, wherein the area ratio of the primary nozzle, the secondary nozzle and the tertiary nozzle orifice is 1:4:8.
8. A hydrogen fuel combustor head structure according to claim 3, wherein the inner side of the housing outlet has a profile matching the three stage nozzle and the three stage swirler to form a gas flow passage.
9. A hydrogen fuel combustion chamber head structure as claimed in claim 3, wherein said primary nozzle is trapped in said secondary nozzle, and an axial distance between an extended end face of said primary nozzle and an extended end face of said secondary nozzle is 8-12mm; the secondary nozzle is trapped in the tertiary nozzle, and the axial distance between the extending end face of the secondary nozzle and the extending end face of the tertiary nozzle is 10-12mm.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310552053.3A CN116592397A (en) | 2023-05-16 | 2023-05-16 | Hydrogen fuel combustion chamber head structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310552053.3A CN116592397A (en) | 2023-05-16 | 2023-05-16 | Hydrogen fuel combustion chamber head structure |
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| CN116592397A true CN116592397A (en) | 2023-08-15 |
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| CN202310552053.3A Pending CN116592397A (en) | 2023-05-16 | 2023-05-16 | Hydrogen fuel combustion chamber head structure |
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- 2023-05-16 CN CN202310552053.3A patent/CN116592397A/en active Pending
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