CN114440261B - Supersonic part premixed combustion device with low turbulence - Google Patents
Supersonic part premixed combustion device with low turbulence Download PDFInfo
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- CN114440261B CN114440261B CN202210025670.3A CN202210025670A CN114440261B CN 114440261 B CN114440261 B CN 114440261B CN 202210025670 A CN202210025670 A CN 202210025670A CN 114440261 B CN114440261 B CN 114440261B
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- air
- electromagnetic valve
- premixer
- heater
- fuel
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Classifications
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- 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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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23N—REGULATING OR CONTROLLING COMBUSTION
- F23N1/00—Regulating fuel supply
- F23N1/02—Regulating fuel supply conjointly with air supply
- F23N1/025—Regulating fuel supply conjointly with air supply using electrical or electromechanical means
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- 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
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- 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
- F23R3/26—Controlling the air flow
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- 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
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E20/00—Combustion technologies with mitigation potential
- Y02E20/34—Indirect CO2mitigation, i.e. by acting on non CO2directly related matters of the process, e.g. pre-heating or heat recovery
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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 supersonic speed part premixing combustion device with low turbulence, wherein the output end of a first air cylinder is connected with the input end of a heater, the output end of a second air cylinder and the output end of a fuel cylinder are both connected with the input end of a premixing device, a coaxial injector comprises a nozzle and an annular injector arranged outside the nozzle, the output end of the premixing device is connected with the input end of the nozzle, the output end of the heater is connected with the input end of the annular injector, and a honeycomb rectifier is also arranged in the annular injector. According to the invention, the premixer is adopted, the proportion of fuel and air can be accurately controlled to ensure that the premixed gas is in a designed equivalent ratio, and the honeycomb rectifier is adopted, so that large-scale vortex can be broken into small characteristic scale after high-enthalpy airflow passes through the honeycomb rectifier, the turbulence intensity of the airflow can be obviously reduced, when the air jet flow is used, the high-enthalpy air jet flow is firstly opened, then the rich premixed combustible gas is opened, excessive fuel is prevented from being discharged into a laboratory, and the risk in the test process is reduced.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a supersonic speed partial premix combustion device with low turbulence.
Background
The reusable world shuttle aircraft is a great trend of the development of future near space vehicles, and rocket-based ramjet combined engines are widely focused at home and abroad with wide flight envelope and better overall performance. According to the actual flight state, the engine may undergo a rocket mode, a rocket ejection mode, a ram mode and the like; rocket and scramjet work simultaneously in injection mode: the outlet of the rocket nozzle is high-temperature fuel gas, air injected into the ramjet engine is mixed with fuel to form rich premixed combustible gas, and two airflows undergo severe chemical reaction at the downstream to generate thrust. The combustion mechanism in the combined cycle engine in the injection mode is extremely complex, shows very obvious partial premixing characteristics, and has strong interaction between high-intensity turbulence and chemical reaction. The turbulent combustion process and the flame stabilizing mechanism under the injection mode are deeply understood, and are very important for the design and performance optimization of the rocket-based ram combined cycle engine system. In consideration of the complex working process of an actual engine, the cost and the technical difficulty of developing test observation are great. In order to facilitate experimental observation and numerical simulation, the actual physical problem can be abstracted into a simplified physical model, namely a part of premixed flame in supersonic air flow, according to the basic characteristics of a reaction flow field, so that the design of the supersonic jet combustion device which has a simple structure and is easy to adjust has important scientific research value.
There is a lot of description of partially premixed flame devices at low speed and a lot of experimental work has been done. Limited by the difficulty of flame stabilization, supersonic jet burners are not very common, and one more mature solution is to use a low temperature fuel jet in the central region and a high enthalpy air jet in the outer annular jet to maintain flame stability. The fuel and air are mixed rapidly under the shearing action after being injected, the ignition delay of the fuel leads to a certain lifting height of the downstream flame, and finally, partial premixed flame is formed downstream. The combustion device has the advantages of relatively simple configuration, easiness in flame stabilization and the like, and the lifting height of the flame can be controlled by adjusting parameters such as the ratio of fuel to air, the temperature or the pressure of air jet flow and the like. The lifting jet flow flame forming process is subjected to various physical and chemical mechanisms such as initial blending, self-ignition, flame stabilization and the like, and has modes such as lean premixed flame, re-burned premixed flame and diffusion flame, and the like, and comprises all the processes existing in practical problems, and meanwhile, the flame structure is axisymmetric, so that an optical observation test is easier to develop.
Because the existing partially premixed burner mostly adopts an axisymmetric scheme, a rectifying device is not arranged at the upstream of the burner under the general condition, the turbulence degree of fuel and high-enthalpy air jet flow is very high, the influence of the turbulence intensity on the lifting height of flame is very remarkable, and the small-scale turbulence pulsation at the inlet position is difficult to accurately measure; in order to ensure safe operation of the device, the central jet adopts pure fuel, the fuel and the air are not premixed, and the mechanism of partial premixed combustion under the condition of different equivalence ratios cannot be studied.
Disclosure of Invention
The invention aims to provide a supersonic speed partial premix combustion device with low turbulence so as to overcome the defects in the prior art.
In order to achieve the above purpose, the technical scheme adopted by the invention is as follows:
the utility model provides a supersonic speed part premix burner of low turbulence, includes first air cylinder, fuel gas cylinder, second air cylinder, premixer, heater and coaxial injector, the output of first air cylinder is connected with the input of heater, the output of second air cylinder, fuel gas cylinder all is connected with the input of premixer, coaxial injector includes the nozzle and locates the annular injector in the nozzle outside, the output of premixer is connected with the input of nozzle, the output of heater is connected with the input of annular injector, still install cellular rectifier in the annular injector.
Further, a first pressure reducer and a first electromagnetic valve are sequentially arranged on a connecting pipeline of the first air cylinder and the heater, a second pressure reducer and a second electromagnetic valve are sequentially arranged on a connecting pipeline of the second air cylinder and the premixer, and a third pressure reducer and a third electromagnetic valve are sequentially arranged on a connecting pipeline of the gas cylinder and the premixer.
Further, the premixer comprises a premixer shell, a cyclone mixer and a venturi tube mixer which are sequentially arranged in the premixer shell, wherein the output end of the second air cylinder is connected with the air inlet of the cyclone mixer, and the output end of the fuel cylinder is connected with the fuel inlet of the cyclone mixer.
Further, the heater comprises a cylindrical shell, the cylindrical shell comprises an inner shell, a heat preservation layer and an outer shell, and a plurality of resistance heat ribs are arranged on the inner side of the inner shell.
Further, the annular injector comprises an inner section and an outer section, wherein the inner section is an equal-straight circular section pipeline, the outer section is a Laval nozzle molded surface annular channel which is contracted before expanded, and the honeycomb rectifier is arranged in the equal-straight circular section pipeline.
Further, an anti-backfire device made of a hot-melting material is arranged at the outlet position of the nozzle.
Further, the first electromagnetic valve, the second electromagnetic valve and the third electromagnetic valve are further connected with a controller, and the controller is connected with a computer terminal.
Compared with the prior art, the invention has the advantages that: according to the invention, the premixer is adopted, the proportion of fuel and air can be accurately controlled to ensure that the premixed gas is in a designed equivalent ratio, and the honeycomb rectifier is adopted, so that large-scale vortex can be broken into small characteristic scale after high-enthalpy airflow passes through the honeycomb rectifier, the turbulence intensity of the airflow can be obviously reduced, when the air jet flow is used, the high-enthalpy air jet flow is firstly opened, then the rich premixed combustible gas is opened, excessive fuel is prevented from being discharged into a laboratory, and the risk in the test process is reduced.
Drawings
In order to more clearly illustrate the embodiments of the invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic structural view of a low turbulence supersonic partially premixed combustion apparatus of the present invention.
FIG. 2 is a schematic diagram of the structure of the premixer of the present invention.
Fig. 3 is a schematic view of the structure of the heater according to the present invention.
Fig. 4 is a schematic view of the structure of the coaxial injector of the present invention.
Fig. 5 is a schematic view of the mounting structure of the honeycomb rectifier in the present invention.
Detailed Description
The preferred embodiments of the present invention will be described in detail below with reference to the accompanying drawings so that the advantages and features of the present invention can be more easily understood by those skilled in the art, thereby making clear and defining the scope of the present invention.
Referring to fig. 1, this embodiment discloses a supersonic partially premixed combustion device with low turbulence, which comprises a first air cylinder 1, a fuel cylinder 2, a second air cylinder 3, a premixer 4, a heater 5 and a coaxial injector 6, wherein the output end of the first air cylinder 1 is connected with the input end of the heater 5, the output end of the second air cylinder 3 and the output end of the fuel cylinder 2 are both connected with the input end of the premixer 4, the coaxial injector 6 comprises a nozzle 61 and an annular injector 62 arranged outside the nozzle 61, the output end of the premixer 4 is connected with the input end of the nozzle 61, the output end of the heater 5 is connected with the input end of the annular injector 62, and a honeycomb rectifier 63 is further installed in the annular injector 62.
In this embodiment, a connecting pipeline between the first air cylinder 1 and the heater 5 is sequentially provided with a first pressure reducer 7 and a first electromagnetic valve 8, a connecting pipeline between the second air cylinder 3 and the premixer 4 is sequentially provided with a second pressure reducer 9 and a second electromagnetic valve 10, and a connecting pipeline between the gas cylinder 2 and the premixer 4 is sequentially provided with a third pressure reducer 11 and a third electromagnetic valve 12.
In this embodiment, the first electromagnetic valve 8, the second electromagnetic valve 10 and the third electromagnetic valve 12 are further connected with a controller 13, and the controller is connected with a computer terminal, so as to control the operation of the electromagnetic valves.
In this embodiment, the honeycomb rectifier 63 is made of stainless steel, and the honeycomb rectifier 63 is provided with a frame outside and is fixedly mounted on the inner wall surface of the pipe with the equal straight circular section.
In this embodiment, a high temperature resistant insulating material is used between the nozzle 61 and the annular injector 62 to prevent heat transfer.
Referring to fig. 2, the premixer 4 includes a premixer housing 41, and a cyclone mixer 42 and a venturi mixer 43 sequentially disposed in the premixer housing 41, an output end of the second air cylinder 3 is connected with an air inlet of the cyclone mixer 42, and an output end of the fuel cylinder 2 is connected with a fuel inlet of the cyclone mixer 42, and is subjected to two-stage mixing by the cyclone mixer 42 and the venturi mixer 43, so as to ensure sufficient premixing and uniformity, which is obviously different from the previous pure fuel injection.
Referring to fig. 3, the heater 5 includes a cylindrical shell, the cylindrical shell includes an inner shell 51, a heat insulation layer 52 and an outer shell 53, a plurality of resistive heating ribs 54 are disposed on the inner side of the inner shell 51, and the resistive heating ribs 54 are driven by a high-power source 55 to heat by an electric heater, so that high-enthalpy air jet is generated and then enters the annular channel through a honeycomb rectifier 63.
Referring to fig. 4, the annular injector 62 includes an inner section 64 and an outer section 65, the inner section 64 is an equal straight circular section pipe, the outer section 65 is a laval nozzle profile annular channel which is contracted and then expanded, and the honeycomb rectifier 63 is installed in the equal straight circular section pipe.
In this embodiment, the outlet of the nozzle is provided with a backfire preventing device 66 made of a hot-melting material, so that once the flame is lifted and returned, the premixed fuel passage can be fused, and the backfire preventing device 66 prevents the flame from further entering an upstream pipeline to ensure safety.
The hot melt material (anti-flashback device 66) will plug the fuel orifices after flashback occurs, preventing the premixed fuel from continuing to be injected, thereby inhibiting the flame from continuing forward to the conduit.
The workflow of the invention comprises the following steps:
firstly, before a test, checking whether each gas cylinder has hidden dangers such as leakage, open fire and the like, and opening a ventilation kitchen switch; and opening the switches of all bottle mouths of the gas cylinders, and adjusting the downstream pressure reducer to the design pressure.
Step two, turning on a power switch of the electric heater, manually setting the power switch to rated power, and driving a first electromagnetic valve of an air channel to be opened through a computer and a controller; the air in the air bottle is quickly raised in temperature after passing through the resistive heating fins in the heater (shown in figure 3), and is injected into an open test section after passing through the honeycomb rectifier, so that high-enthalpy air jet with low turbulence intensity is formed.
And thirdly, controlling the second electromagnetic valve and the third electromagnetic valve to be opened, adjusting the pressure reducer to set the pressure of the hydrogen and the air, and enabling the low-temperature two gases to flow into the premixer from the high-pressure gas bottle respectively at the designed flow (as shown in figure 2), and performing two-stage mixing through the cyclone mixer and the venturi mixer to generate fully premixed rich-combustion gas. The premixer outlet was connected to an inlet of a straight circular section tube in the nozzle and was injected into the test section at sonic velocity.
And fourthly, after stable supersonic lifting jet flame is formed, measuring data such as flame lifting height, instantaneous flame structure, temperature, component distribution and the like by adopting a non-contact combustion diagnosis technology.
And fifthly, after the test is finished, closing the second electromagnetic valve and the third electromagnetic valve, closing the power supply of the first electromagnetic valve and the heater, and recording test data.
The invention is characterized in that a pressure reducer is respectively arranged at the downstream of an upstream fuel high-pressure gas cylinder and an air high-pressure gas cylinder, and is connected with a straight circular section flow passage at the center of an annular injector after a two-stage mixing premixer is adopted; the other high-pressure air cylinder is heated by an electric heater of the staggered ribs driven by a high-power supply after passing through the pressure reducer, and high-enthalpy air jet flow is generated and then enters the annular channel through the honeycomb rectifier.
The honeycomb rectifier 63 arranged in the high-enthalpy air flow passage at the upstream of the nozzle outlet can remarkably improve the uniformity of jet flow, reduce the influence of turbulence small-scale pulsation on lifting jet flow flame, and is beneficial to accurately analyzing the lifting height and propagation characteristics of part of premixed flame. The backfire preventing device 66 made of hot-melting materials is arranged at the outlet of the nozzle, once the flame is lifted back, the premixed fuel passage can be fused, and the flame is prevented from further entering an upstream pipeline, so that the safety is ensured.
The invention simulates high enthalpy air close to real working conditions based on an electric heating mode, on one hand, the temperature of air jet flow is easier to control, and meanwhile, other component polluted gas can not be generated like in the case of chemical heating.
According to the invention, the premixer of fuel and air is adopted, the fuel and the air are respectively injected into the gas collection cavity, the equivalence ratio radial distribution is uneven after shearing and mixing, the low-temperature fuel and the air are mixed in advance and then injected together with high-enthalpy air through the coaxial nozzle, and the pressure of the downstream of the fuel/air gas cylinder can be controlled, so that the equivalence ratio of the premixed fuel is controlled.
Although the embodiments of the present invention have been described with reference to the accompanying drawings, the patentees may make various modifications or alterations within the scope of the appended claims, and are intended to be within the scope of the invention as described in the claims.
Claims (1)
1. The supersonic speed part premixing combustion device with low turbulence is characterized by comprising a first air cylinder, a fuel cylinder, a second air cylinder, a premixer, a heater and a coaxial injector, wherein the output end of the first air cylinder is connected with the input end of the heater;
a first pressure reducer and a first electromagnetic valve are sequentially arranged on a connecting pipeline of the first air cylinder and the heater, a second pressure reducer and a second electromagnetic valve are sequentially arranged on a connecting pipeline of the second air cylinder and the premixer, and a third pressure reducer and a third electromagnetic valve are sequentially arranged on a connecting pipeline of the fuel cylinder and the premixer;
the premixer comprises a premixer shell, a cyclone mixer and a venturi tube mixer which are sequentially arranged in the premixer shell, the output end of the second air cylinder is connected with the air inlet of the cyclone mixer, and the output end of the fuel cylinder is connected with the fuel inlet of the cyclone mixer;
the heater comprises a cylindrical shell, wherein the cylindrical shell comprises an inner shell, a heat preservation layer and an outer shell, and a plurality of resistance heat ribs are arranged on the inner side of the inner shell;
the annular injector comprises an inner section and an outer section, wherein the inner section is an equal-straight circular section pipeline, the outer section is a Laval nozzle molded surface annular channel which is contracted and then expanded, and the honeycomb rectifier is arranged in the equal-straight circular section pipeline;
an anti-backfire device formed by hot-melting materials is arranged at the outlet position of the nozzle;
the first electromagnetic valve, the second electromagnetic valve and the third electromagnetic valve are also connected with a controller, and the controller is connected with a computer terminal;
the working flow of the low-turbulence supersonic speed part pre-mixing combustion device comprises the following steps:
firstly, checking whether each gas cylinder has leakage or not and hidden danger of open fire before a test, and opening a ventilation kitchen switch; opening the switches of all bottle mouths of the gas cylinders, and regulating the downstream pressure reducer to the design pressure;
step two, turning on a power switch of the electric heater, manually setting the power switch to rated power, and driving a first electromagnetic valve of an air channel to be opened through a computer and a controller; the temperature of the air in the air bottle rises rapidly after passing through the resistance heat fins in the heater, and the air is injected into an open test section after passing through the honeycomb rectifier, so that high-enthalpy air jet with low turbulence intensity is formed; the honeycomb rectifier arranged in the high-enthalpy air flow channel at the upstream of the nozzle outlet can remarkably improve the uniformity of jet flow, reduce the influence of turbulent small-scale pulsation on lifting jet flow flame, and is beneficial to accurately analyzing the lifting height and propagation characteristics of part of premixed flame;
step three, controlling the second electromagnetic valve and the third electromagnetic valve to be opened, regulating the pressure reducer to set the pressure of hydrogen and air, enabling low-temperature two gases to flow into the premixer from the high-pressure gas bottle respectively at a designed flow rate, performing two-stage mixing through the cyclone mixer and the venturi mixer to generate fully premixed rich gas, connecting an outlet of the premixer to an inlet of a straight circular section pipeline in a nozzle and injecting the rich gas into a test section at sound velocity;
fourthly, after stable supersonic lifting jet flame is formed, measuring flame lifting height, instantaneous flame structure, temperature and component distribution data by adopting a non-contact combustion diagnosis technology;
and fifthly, after the test is finished, closing the second electromagnetic valve and the third electromagnetic valve, closing the power supply of the first electromagnetic valve and the heater, and recording test data.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210025670.3A CN114440261B (en) | 2022-01-11 | 2022-01-11 | Supersonic part premixed combustion device with low turbulence |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210025670.3A CN114440261B (en) | 2022-01-11 | 2022-01-11 | Supersonic part premixed combustion device with low turbulence |
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| Publication Number | Publication Date |
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| CN114440261A CN114440261A (en) | 2022-05-06 |
| CN114440261B true CN114440261B (en) | 2023-09-01 |
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| CN115751375B (en) * | 2022-10-09 | 2024-05-10 | 哈尔滨工业大学 | Supersonic steady combustion support plate for assisting enhanced combustion of electrolyzed water |
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| JPH08200678A (en) * | 1995-01-23 | 1996-08-06 | Hitachi Ltd | Combustion device |
| CN106996579A (en) * | 2017-05-16 | 2017-08-01 | 西北工业大学 | A kind of oil-poor direct jetstream whirl nozzle mould of low-pollution burning chamber of gas turbine |
| CN107143881A (en) * | 2017-05-16 | 2017-09-08 | 西北工业大学 | A kind of direct injection nozzle structure of multiple spot for low-pollution burning chamber of gas turbine |
| CN110226026A (en) * | 2017-01-31 | 2019-09-10 | 株式会社Ihi | Burner and gas turbine |
| CN214307199U (en) * | 2021-01-20 | 2021-09-28 | 浙江浙能技术研究院有限公司 | Head structure of combustion chamber |
-
2022
- 2022-01-11 CN CN202210025670.3A patent/CN114440261B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08200678A (en) * | 1995-01-23 | 1996-08-06 | Hitachi Ltd | Combustion device |
| CN110226026A (en) * | 2017-01-31 | 2019-09-10 | 株式会社Ihi | Burner and gas turbine |
| CN106996579A (en) * | 2017-05-16 | 2017-08-01 | 西北工业大学 | A kind of oil-poor direct jetstream whirl nozzle mould of low-pollution burning chamber of gas turbine |
| CN107143881A (en) * | 2017-05-16 | 2017-09-08 | 西北工业大学 | A kind of direct injection nozzle structure of multiple spot for low-pollution burning chamber of gas turbine |
| CN214307199U (en) * | 2021-01-20 | 2021-09-28 | 浙江浙能技术研究院有限公司 | Head structure of combustion chamber |
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| CN114440261A (en) | 2022-05-06 |
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