CN112282969A - Vortex cold wall combustion chamber with central rotational flow - Google Patents
Vortex cold wall combustion chamber with central rotational flow Download PDFInfo
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- CN112282969A CN112282969A CN202011129388.7A CN202011129388A CN112282969A CN 112282969 A CN112282969 A CN 112282969A CN 202011129388 A CN202011129388 A CN 202011129388A CN 112282969 A CN112282969 A CN 112282969A
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- oxidant injection
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 88
- 239000007800 oxidant agent Substances 0.000 claims abstract description 138
- 230000001590 oxidative effect Effects 0.000 claims abstract description 138
- 238000002347 injection Methods 0.000 claims abstract description 117
- 239000007924 injection Substances 0.000 claims abstract description 117
- 239000000446 fuel Substances 0.000 claims abstract description 51
- 239000007921 spray Substances 0.000 claims abstract description 13
- 239000007789 gas Substances 0.000 claims description 15
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 12
- 238000000034 method Methods 0.000 claims description 9
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 6
- 239000001257 hydrogen Substances 0.000 claims description 6
- 229910052739 hydrogen Inorganic materials 0.000 claims description 6
- 239000001301 oxygen Substances 0.000 claims description 6
- 229910052760 oxygen Inorganic materials 0.000 claims description 6
- 238000011049 filling Methods 0.000 claims description 5
- 230000008602 contraction Effects 0.000 claims description 4
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims description 3
- 239000003795 chemical substances by application Substances 0.000 claims description 3
- 150000002431 hydrogen Chemical class 0.000 claims description 3
- 239000000203 mixture Substances 0.000 claims 1
- 239000002994 raw material Substances 0.000 claims 1
- 238000002156 mixing Methods 0.000 abstract description 7
- 239000000243 solution Substances 0.000 description 4
- 239000003344 environmental pollutant Substances 0.000 description 3
- 239000007788 liquid Substances 0.000 description 3
- 231100000719 pollutant Toxicity 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 239000002737 fuel gas Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000006641 stabilisation Effects 0.000 description 2
- 238000011105 stabilization Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
- F02K9/64—Combustion or thrust chambers having cooling arrangements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
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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 vortex cold wall combustion chamber with central rotational flow, which comprises a first body assembly and an injection assembly, wherein the injection assembly comprises a primary oxidant injection port, a secondary oxidant injection port and a fuel injection port which are communicated with the inner cavity of the combustion chamber, the primary oxidant injection port is arranged on the side wall of the body assembly along the tangential direction, the secondary oxidant injection port is arranged at the end part of the body assembly, a guide vane is arranged inside the secondary oxidant injection port, and the tangential direction of oxidant entering the inner cavity of the combustion chamber from the primary oxidant injection port is opposite to the tangential direction of oxidant entering from the secondary oxidant injection port. According to the invention, the oxidant of the vortex combustion chamber is sprayed in the tangential direction from the position near the connection part of the combustion chamber and the spray pipe, and the fuel is sprayed in the radial direction from the position near the end part of the combustion chamber, so that a stable double-vortex structure can be formed inside the combustion chamber, the cyclone is arranged by combining the vortex flow and the vortex flow to realize the sufficient mixing of the oxidant and the combustion, and the internal double-vortex structure is formed to increase the efficiency of the combustion chamber.
Description
Technical Field
The invention relates to the technical field of combustion chambers, in particular to a vortex cold wall combustion chamber with a central rotational flow.
Background
In the field of aerospace launch, liquid rocket engines are mainly adopted in all aerospace major countries in the world, and low cost, long service life and reusability of the liquid engines are always pursued targets. One of the main reasons that aerospace is expensive is that the engine is difficult to reuse and has a short life; for small rocket motors, expensive materials are often used. These problems, mainly caused by the temperature of the engine combustion chamber being too high, shorten the operation life and reduce the safety margin, the existing vortex cold wall combustion chamber oxidant enters tangentially from the bottom, and the fuel enters from the vicinity of the head along the radial direction, so that the oxidant and the fuel are not sufficiently mixed in the central area of the combustion chamber, and the combustion efficiency is low. Therefore, it would be of great interest to develop a new, low cost, reusable liquid fuel rocket engine.
Disclosure of Invention
This section is for the purpose of summarizing some aspects of embodiments of the invention and to briefly introduce some preferred embodiments. In this section, as well as in the abstract and the title of the invention of this application, simplifications or omissions may be made to avoid obscuring the purpose of the section, the abstract and the title, and such simplifications or omissions are not intended to limit the scope of the invention.
The present invention has been made in view of the above and/or other problems with the prior art vortex cooled wall combustors with a central swirl.
The problem to be solved by the present invention is therefore how to increase the efficiency of the combustion chamber.
In order to solve the technical problems, the invention provides the following technical scheme: a vortex cold wall combustion chamber with central rotational flow comprises,
the body assembly comprises a combustion chamber inner cavity, and one end of the combustion chamber inner cavity is provided with a combustion chamber outlet;
the injection assembly comprises a primary oxidant injection port, a secondary oxidant injection port and a fuel injection port which are communicated with the inner cavity of the combustion chamber, the primary oxidant injection port is arranged on the side wall of the body assembly along the tangential direction, the secondary oxidant injection port is arranged at the end part of the body assembly, and a guide vane is arranged inside the secondary oxidant injection port;
the tangential direction of oxidant entry into the combustion chamber interior from the primary oxidant injection port is opposite the tangential direction of oxidant entry from the secondary oxidant injection port.
As a preferable scheme of the vortex cold wall combustion chamber with the central rotational flow, the invention comprises the following steps: the injection component is cylindrical, the cross section of the injection component is circular, the fuel injection port is vertically arranged on the side wall of the body component and close to one side of the secondary oxidant injection port, and the primary oxidant injection port is arranged on the side wall of the body component in a tangential component of 0.8 and a radial component of 0.2.
As a preferable scheme of the vortex cold wall combustion chamber with the central rotational flow, the invention comprises the following steps: the primary oxidant injection port and the fuel injection port are respectively arranged at two ends of the outer side wall of the body assembly and are uniformly and circumferentially distributed along the outer side wall of the body assembly, and the secondary oxidant injection port is vertically arranged at the center of the end part of the body assembly.
As a preferable scheme of the vortex cold wall combustion chamber with the central rotational flow, the invention comprises the following steps: and the inner cavity of the combustion chamber is communicated with the outlet of the combustion chamber to form a spray pipe.
As a preferable scheme of the vortex cold wall combustion chamber with the central rotational flow, the invention comprises the following steps: the cross section of the outlet of the combustion chamber is circular, and the outlet of the combustion chamber and a spray pipe communicated with the body assembly are in a contraction and enlargement state.
As a preferable scheme of the vortex cold wall combustion chamber with the central rotational flow, the invention comprises the following steps: a fillet is arranged between the side wall and the end part of the body assembly.
As a preferable scheme of the vortex cold wall combustion chamber with the central rotational flow, the invention comprises the following steps: the inside support column that is equipped with of secondary oxidant sprue, guide vane slope in support column and axial set up in on the support column, it is a plurality of guide vane along circumference distribute in on the lateral wall of support column, form annular whirl inflow mouth.
The invention also provides a filling method of the vortex cold wall combustion chamber with the central rotational flow, which comprises the following steps:
simultaneously injecting an oxidant and a fuel into the primary oxidant injection port, the secondary oxidant injection port, and the fuel injection port, respectively;
the ratio of the oxidant injected from the primary oxidant injection port to the oxidant injected from the secondary oxidant injection port is 9: 1.
As a preferable scheme of the filling method of the vortex cold wall combustion chamber with the central rotational flow, the method comprises the following steps: the primary oxidant injection port injects an oxidant in a direct-current jet mode, and the secondary oxidant injection port injects an oxidant in a rotary jet mode.
As a preferable scheme of the filling method of the vortex cold wall combustion chamber with the central rotational flow, the method comprises the following steps: the fuel injected by the fuel injection port is gas fuel, the gas fuel is methane and hydrogen, the ratio of the hydrogen to the oxygen is 1:4, and the methane and the oxygen are configured according to the equivalent ratio of 1: 4.
The invention has the beneficial effects that: the invention relates to a vortex combustion chamber, wherein oxidant is injected from the position near the connection part of the combustion chamber and a nozzle in the tangential direction, fuel is injected from the position near the end part of the combustion chamber in the radial direction, the combination can form a stable double-vortex structure in the combustion chamber, high-temperature gas is confined in a core area, low-temperature gas plays a role in isolation between the high-temperature gas and the wall surface, a relatively cold propellant close to the wall surface not only isolates heat conduction, but also reduces the oxidation of the high-temperature gas to wall surface materials, the swirler is arranged by combining the vortex flow and the vortex flow to realize the full mixing of the oxidant and the combustion, the internal double-vortex structure is formed to increase the efficiency of the combustion chamber, the swirler is arranged at the central position of the end part, and the appropriate vortex flow number and the proportion of the secondary injection of the oxidant in the oxidant are arranged to improve the combustion, in order to achieve both a reduction in the temperature of the end of the combustion chamber and an improvement in the specific impulse of the engine, the specific impulse of the engine and the temperature of the wall surface of the head of the combustion chamber are increased by providing a head shape with a rounded corner.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without inventive exercise. Wherein:
FIG. 1 is a block diagram of a vortex cold wall combustor with a central vortex.
FIG. 2 is a cross-sectional internal view of a vortex cold wall combustor with a central swirl.
FIG. 3 is a view showing the internal structure of the secondary oxidant injection port of the vortex cold wall combustor with a central vortex.
FIG. 4 is a graph of the combustor efficiency for different radial components of the primary oxidant injection port and the sidewall of the body assembly for a vortex cold wall combustor with a central swirl in example 2.
FIG. 5 is the combustor efficiency at different ratios of the secondary oxidant injection for the vortex cooled wall combustor with center swirl in example 2.
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below.
In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention, but the present invention may be practiced in other ways than those specifically described and will be readily apparent to those of ordinary skill in the art without departing from the spirit of the present invention, and therefore the present invention is not limited to the specific embodiments disclosed below.
Furthermore, reference herein to "one embodiment" or "an embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least one implementation of the invention. The appearances of the phrase "in one embodiment" in various places in the specification are not necessarily all referring to the same embodiment, nor are separate or alternative embodiments mutually exclusive of other embodiments.
Example 1
Referring to fig. 1 to 2, a first embodiment of the present invention provides a vortex cold wall combustion chamber with a central cyclone, which includes a body assembly 100 and an injection agent assembly 200.
Wherein the body assembly 100 comprises a combustion chamber inner chamber 101, one end of which is provided with a combustion chamber outlet 102;
the injection assembly 200 comprises a primary oxidant injection port 201, a secondary oxidant injection port 202 and a fuel injection port 203 which are communicated with the inner cavity 101 of the combustion chamber, the primary oxidant injection port 201 is tangentially arranged on the side wall of the body assembly 100, the secondary oxidant injection port 202 is arranged at the end part of the body assembly 100, and a guide vane 202a is arranged inside the secondary oxidant injection port 202;
the tangential direction of oxidant entering the combustion chamber interior 101 from the primary oxidant injection port 201 is opposite to the tangential direction of oxidant entering from the secondary oxidant injection port 202.
Based on the above, the combustion chamber cavity 101 is communicated with the primary oxidant injection port 201, the secondary oxidant injection port 202 and the fuel injection port 203, wherein the number of the primary oxidant injection port 201 and the number of the fuel injection port 203 are preferably four, the number of the secondary oxidant injection port 202 is preferably one, the tangential direction of the oxidant entering the combustion chamber cavity 101 from the primary oxidant injection port 201 is opposite to the tangential direction of the oxidant entering from the secondary oxidant injection port 202, so that after the oxidant is injected from the primary oxidant injection port 201 and the secondary oxidant injection port 202, the oxidant forms strong vortex flow near the wall surface of the combustion chamber cavity 101, the rotating oxidant reversely flows to the end of the body assembly 100 from the back of the combustion chamber cavity 101 under the action of pressure difference, and then turns inwards to mix with the fuel injected from the fuel injection port 203, then the gas is turned to the direction of the jet pipe to flow, another vortex is formed in the thrust chamber, the gas is combusted in the vortex area, and high-temperature gas flows to the jet pipe.
Further, the injection member 200 is cylindrical and has a circular cross-section, wherein the fuel injection port 203 is vertically disposed on the sidewall of the body member 100 near the side of the secondary oxidant injection port 202, and the primary oxidant injection port 201 is disposed on the sidewall of the body member 100 with a tangential component of 0.8 and a radial component of 0.2.
In order to avoid the oxidant flowing out of the primary oxidant injection port 201, a certain radial component is required to be provided when the oxidant is injected into the primary oxidant injection port 201, if the tangential velocity is too large, the oxidant flows out, and if the tangential velocity is too small, the effect of forming a double vortex is not good, so that the tangential component is equivalently set to be 0.8, and the radial component is set to be 0.2, so that the tangential velocity is ensured, the airflow is prevented from flowing out, the efficiency is ensured, and the waste of the oxidant is avoided.
The primary oxidant injection port 201 and the fuel injection port 203 are respectively arranged at two ends of the outer side wall of the body assembly 100 and are uniformly distributed along the outer side wall of the body assembly 100 in the circumferential direction, so that when the oxidant is injected into the primary oxidant injection port 201 and the fuel is injected into the fuel injection port 203, the oxidant and the fuel form strong vortex flow near the wall surface of the combustion chamber inner cavity 101, in order to enhance the mixing and heat transfer degree of the oxidant and the fuel in the combustion chamber inner cavity 101, the secondary oxidant injection port 203 is vertically arranged at the center of the end part of the body assembly 100 to perform secondary injection of the oxidant, a backflow zone is formed at the central part of the combustion chamber inner cavity 101, flame stabilization is realized, high-temperature airflow near the wall surface is sucked, the efficiency of the combustion chamber is improved, the wall surface temperature of.
The combustion chamber inner chamber 101 and the combustion chamber export 102 are communicated with a spray pipe 103, the spray pipe 103 is a Laval spray pipe, oxidant and fuel are uniformly mixed in the combustion chamber inner chamber 101 and then are sprayed out to the combustion chamber export 102 through the spray pipe 103, the cross section of the combustion chamber export 102 is circular, the spray pipe 103 of the combustion chamber export 102 and the body component 100 is in a contraction and contraction state, then gas passes through the throat part of the spray pipe 103, the flow cross section is narrowed, the flow velocity is increased, and therefore the gas is sprayed out.
Preferably, rounded corners are provided between the side walls and the ends of the body assembly 100.
To both reduce the end temperature of the body assembly 100 and increase the specific impulse of the engine, the hemispherical shape and the frustoconical shape of the conventional combustion chamber are combined to form a truncated head with rounded corners.
In order to enhance the mixing and heat transfer degree of the oxidant and the fuel in the combustion chamber inner chamber 101, a support column 202b is disposed inside the secondary oxidant injection port 202 disposed at the center of the end portion of the body assembly 100, the guide vanes 202a are inclined to the support column 202b and axially disposed on the support column 202b, a plurality of guide vanes 202a are circumferentially distributed on the outer side wall of the support column 202b to form an annular swirl inlet, the swirl number is set to be S-0.3, the swirl number becomes 0.3 after the oxidant is introduced into the secondary oxidant injection port 202, the oxidant is secondarily injected to further enhance the mixing of the fuel and the oxidant, therefore, the combustion efficiency is improved, the wall surface temperature is reduced, the efficiency of the combustion chamber can be improved by more than 2%, the wall surface temperature can be reduced to 650K, the specific impulse efficiency of the engine can be improved to about 92%, and the emission of pollutants is further reduced.
Example 2
Referring to fig. 1 to 2 and 5, the present embodiment provides a filling method for a vortex cold wall combustion chamber with a central rotational flow, which includes the following steps:
simultaneously injecting an oxidant and a fuel into the primary oxidant injection port 201, the secondary oxidant injection port 202, and the fuel injection port 203, respectively;
the ratio of the oxidant injected from the primary oxidant injection port 201 to the oxidant injected from the secondary oxidant injection port 202 is 9: 1.
After an oxidant is injected into a primary oxidant injection port 201 and a fuel is injected into a fuel injection port 203, strong vortex flow is formed near the wall surface of a combustion chamber inner cavity 101, the rotating oxidant reversely flows to the end part of the combustion chamber inner cavity 101 from the tail part of the combustion chamber inner cavity 101 under the action of pressure difference, the rotating oxidant is turned inwards to be mixed with the fuel injected by the fuel injection port 203, then the rotating oxidant is turned to flow towards a spray pipe 103 to form another vortex, the high-temperature fuel gas is combusted in the vortex region, the high-temperature fuel gas flows towards the spray pipe 103, in order to enhance the mixing and heat transfer degree of the oxidant and the fuel in the combustion chamber inner cavity 101, the oxidant is injected into the secondary oxidant injection port 201 for secondary injection of the oxidant, the proportion of the oxidant in the secondary injection is about 10%, a backflow region is formed at the central part of the combustion chamber inner cavity 101, flame stabilization is realized, and high-temperature air flow near the wall surface, thereby realizing the functions of improving the efficiency, reducing the wall surface temperature of the inner cavity 101 of the combustion chamber and reducing the emission of pollutants.
The primary oxidant injection port 201 injects the oxidant in a direct-current jet mode, and the secondary oxidant injection port 202 injects the oxidant in a rotary jet mode, so that the mixing of the fuel and the oxidant is further enhanced, and the combustion efficiency is improved and the wall surface temperature is reduced.
The fuel injected by the fuel injection port 203 is gas fuel, and the gas fuel is methane and hydrogen, wherein the ratio of the hydrogen to the oxygen is 1:4, and the ratio of the methane to the oxygen is 1: 4.
Based on the above, the efficiency of the combustion chamber can be improved by more than 2%, the wall surface temperature can be reduced to 650K, and the specific impulse efficiency of the engine can be improved to more than 92%. Thereby further reducing the emission of pollutants.
It should be noted that the above-mentioned embodiments are only for illustrating the technical solutions of the present invention and not for limiting, and although the present invention has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that modifications or equivalent substitutions may be made on the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, which should be covered by the claims of the present invention.
Claims (10)
1. The utility model provides a take vortex cold wall combustion chamber of center whirl which characterized in that: comprises the steps of (a) preparing a mixture of a plurality of raw materials,
the body assembly (100) comprises a combustion chamber inner cavity (101), and one end of the combustion chamber inner cavity is provided with a combustion chamber outlet (102);
the injection assembly (200) comprises a primary oxidant injection port (201), a secondary oxidant injection port (202) and a fuel injection port (203), wherein the primary oxidant injection port (201), the secondary oxidant injection port (202) and the fuel injection port are communicated with the inner cavity (101) of the combustion chamber, the primary oxidant injection port (201) is arranged on the side wall of the body assembly (100) along the tangential direction, the secondary oxidant injection port (202) is arranged at the end part of the body assembly (100), and a guide vane (202a) is arranged inside the secondary oxidant injection port (202);
the tangential direction of oxidant entry into the combustor chamber (101) from the primary oxidant injection port (201) is opposite to the tangential direction of oxidant entry from the secondary oxidant injection port (202).
2. A vortex cooled wall combustor with central swirl as in claim 1 wherein: the injection agent component (200) is cylindrical, the cross section of the injection agent component is circular, the fuel injection port (203) is vertically arranged on the side wall of the body component (100) and close to one side of the secondary oxidant injection port (202), and the primary oxidant injection port (202) is arranged on the side wall of the body component (100) in a tangential component of 0.8 and a radial component of 0.2.
3. A vortex cooled wall combustor with central swirl as claimed in claim 1 or 2 wherein: the primary oxidant injection port (201) and the fuel injection port (203) are respectively arranged at two ends of the outer side wall of the body assembly (100) and are uniformly and circumferentially distributed along the outer side wall of the body assembly (100), and the secondary oxidant injection port (203) is vertically arranged at the center of the end part of the body assembly (100).
4. A vortex cooled wall combustor with central swirl as in claim 3 wherein: and the combustion chamber inner cavity (101) and the combustion chamber outlet (102) are communicated with a spray pipe (103).
5. A vortex cooled wall combustion chamber with central vortex flow according to claim 1 or 4, characterised in that: the section of the combustion chamber outlet (102) is circular, and a spray pipe (103) of the combustion chamber outlet (102) communicated with the body assembly (100) is in a contraction and enlargement state.
6. A vortex cooled wall combustor with central swirl as in claim 1 wherein: a fillet is arranged between the side wall and the end part of the body assembly (100).
7. A vortex cooled wall combustor with central swirl as in claim 6 wherein: a supporting column (202b) is arranged inside the secondary oxidant injection port (202), the guide vanes (202a) are inclined to the supporting column (202b) and axially arranged on the supporting column (202b), and the guide vanes (202a) are circumferentially distributed on the outer side wall of the supporting column (202b) to form an annular swirl inlet.
8. A method of filling a vortex cold wall combustor with a central vortex flow according to any one of claims 1 to 7, comprising the steps of:
simultaneously injecting an oxidant and a fuel into the primary oxidant injection port (201), the secondary oxidant injection port (202), and the fuel injection port (203), respectively;
the ratio of the oxidant injected by the primary oxidant injection port (201) to the oxidant injected by the secondary oxidant injection port (202) is 9: 1.
9. A method of injecting a vortex cold wall combustor with central swirl as claimed in claim 8, wherein: the primary oxidant injection port (201) injects an oxidant by means of direct current jet, and the secondary oxidant injection port (202) injects an oxidant by means of rotary jet.
10. A method of injecting a vortex cold wall combustor with central swirl as claimed in claim 9, wherein: the fuel injected by the fuel injection port (203) is gas fuel, the gas fuel is methane and hydrogen, the ratio of the hydrogen to the oxygen is 1:4, and the methane and the oxygen are configured according to the equivalent ratio of 1: 4.
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| CN202011129388.7A CN112282969B (en) | 2020-10-21 | 2020-10-21 | Vortex cold wall combustion chamber with central rotational flow |
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| CN111288490A (en) * | 2020-03-23 | 2020-06-16 | 上海电力大学 | Combustion chamber device of high-temperature backflow zone at scattered boss |
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