CN109654536B - Autonomous backflow type combustion chamber - Google Patents
Autonomous backflow type combustion chamber Download PDFInfo
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- CN109654536B CN109654536B CN201811538081.5A CN201811538081A CN109654536B CN 109654536 B CN109654536 B CN 109654536B CN 201811538081 A CN201811538081 A CN 201811538081A CN 109654536 B CN109654536 B CN 109654536B
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- flame tube
- combustion chamber
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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
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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
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
- F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
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- Engineering & Computer Science (AREA)
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- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
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Abstract
The application discloses from independent backward flow formula combustion chamber belongs to aeroengine combustion chamber design technical field, and this combustion chamber includes flame tube (1), fuel line and air pipeline (4), wherein, the one end of flame tube (1) is uncovered, and the other end is sealed, the export part setting of fuel line and air pipeline (4) is in the opening end of flame tube (1), and the orientation inside flame tube (1), the encirclement of the opening end of flame tube (1) the export part of fuel line and air pipeline (4) is as the gas outlet, the combustion area of flame tube sets up the export part of fuel line and air pipeline (4) with between the flame tube blind end. This application has realized the autonomic backward flow of flue gas through structural design, has reduced the oxygen content of participating in combustion gas, has promoted combustion air's temperature, is reducing NOxIn the case of emissions, combustion stability is simultaneously enhanced.
Description
Technical Field
The application belongs to the technical field of aero-engine combustion chamber design, and particularly relates to an autonomous backflow type combustion chamber.
Background
National Standard and International civil aviation organization for NOxThe strict requirements of emissions are the prerequisites for gas turbines to enter the market, and the current research on the technology of nitrogen oxide control is mainly focused on organizing the combustion mode and the structural design of the combustion chamber. NOxTo generate mainly thermal NOxFuel type NOxFast NOxAnd NNH type NOxNO of fuel typexNO reduction by controlling nitrogen content in fuelxEmission of (2), NO produced by the remaining three mechanismsxFor total NOxThe contribution of which varies greatly in composition with the operating conditions of the combustion chamber. From NOxAnalysis of the mechanisms of production affecting NOxThe emission factors are mainly: the flame temperature, the residence time of a high-temperature area, the mole fraction of combustion reactants, the pressure of a combustion chamber and other factors, tens of combustion chamber structures such as a classification combustion chamber, a variable geometry combustion chamber, a catalysis combustion chamber, a lean oil premixing and pre-evaporation combustion chamber, an oil-rich combustion chamber/quenching combustion chamber/lean oil combustion chamber, a double-ring premixing cyclone combustion chamber, a lean oil single-stage combustion chamber and an axial classification combustion chamber are researched at home and abroad, but part of the combustion chambers also have the defects of narrow working range, easy tempering, unstable combustion and the like, and mainly comprise
The lean oil premixing and pre-evaporating combustor has the main defects that the premixing and pre-evaporating mode is difficult to control, the fuel oil is easy to coke, the working range is small, and the tempering is easy;
the variable geometry combustion chamber has a complex structure and is easy to generate faults;
the control of the combustion chamber of the staged combustion is complex, and the working range is narrow;
the catalytic combustion mode needs to consume a catalyst, and the intake air temperature is easy to cause the failure of the catalyst.
RQL combustion chamber divides combustion into two stages, which results in side length of combustion chamber, and the deviation of the injection process of secondary air from ideal state is large, so that NO can not be effectively reducedxAnd (4) discharging.
Therefore, the fuel can be stably combusted under the conditions of premixing and non-premixing, has higher combustion strength and can reach NOxThe ultra-low emission combustor is urgently expected by developers.
Disclosure of Invention
It is an object of the present application to provide an autonomous reverse flow combustor to address at least one of the above-mentioned problems.
This application is from STREAMING combustion chamber that flows back, including flame tube, fuel line and air pipeline, wherein, the one end of flame tube is uncovered, and the other end is sealed, the exit portion of fuel line and air pipeline sets up the opening end of flame tube, and orientation inside the flame tube, the encirclement of the opening end of flame tube the exit portion of fuel line and air pipeline is as the gas outlet, the combustion area of flame tube sets up the exit portion of fuel line and air pipeline with between the flame tube closed end.
Preferably, the fuel lines include a fuel line in a premixed mode and a fuel line in a non-premixed mode.
Preferably, the outer part of the flame tube is sleeved with a combustion chamber outer casing, the inner wall of the combustion chamber outer casing and the flame tube outer arm are supported by a support frame, and fluid or cooling gas is arranged in the combustion chamber outer casing.
Preferably, the wall of the flame tube is made of high-temperature alloy.
Preferably, the closed end of the flame tube is made of high-temperature ceramic, or the closed end in the flame tube is additionally provided with the high-temperature ceramic.
The key point of the invention is that the structure design realizes the autonomous reflux of the fuel gas, reduces the oxygen content of the gas participating in combustion, improves the temperature of the combustion air, and enhances the combustion stability under the condition of reducing the NOx emission.
The invention has the advantages that:
1) the high-temperature backflow gas automatically flows back to be mixed with the inlet fuel, so that the temperature of the inflow gas is increased, and the combustion stability is improved;
2) the mixing of the reflux gas and the inlet gas reduces the oxygen content of the inflow gas and can greatly reduce NOxDischarging of (3);
3) the ceramic plate arranged at the bottom of the flame tube realizes automatic backflow of fuel gas;
4) the combustion chamber can be stably combusted under the conditions of lower inflow temperature and lower oil-gas ratio, and the working stability of the combustion chamber under low working conditions is improved.
Drawings
FIG. 1 is a schematic structural diagram of a preferred embodiment of the self-recirculating combustor of the present application.
The fuel injection device comprises a flame tube 1, a fuel pipeline in a 2-premixing mode, a fuel pipeline in a 3-non-premixing mode, an air pipeline 4, a combustion chamber outer casing 5, a combustion mixture 6 and a backflow fuel gas 7; 8-combustion zone, 9-reflux zone, 10-ceramic cylinder bottom and 11-cooling gas.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The utility model designs a can both stabilize the novel gas turbine low discharge combustor of work under the diffusion mode in advance, this combustor can independently produce the gas backward flow, and high temperature backward flow gas mixes with imported fuel, reduces reaction mixture's oxygen content when increasing fuel import temperature, improves combustion stability, has reduced the degree of difficulty of igniting, mixes in advance with the non-condition in advance at the fuel under, and the homoenergetic realizes nitrogen oxide's minimum emission.
As shown in fig. 1, the present application relates to an autonomous reverse-flow type combustion chamber, which mainly includes a flame tube 1, a fuel line, and an air line 4, wherein one end of the flame tube 1 is open, and the other end is closed, an outlet portion of the fuel line and the air line 4 is disposed at the open end of the flame tube 1 and faces the interior of the flame tube 1, an outlet portion of the open end of the flame tube 1 surrounding the fuel line and the air line 4 is used as a gas outlet, and a combustion area of the flame tube is disposed between the outlet portion of the fuel line and the air line 4 and the closed end of the flame tube.
In this embodiment, the flame tube 1 is open at only one end, the fuel inlet and the gas outlet (return gas 7) are located at the same side, and the gas is received at the bottom of the flame tubeThe fuel gas can be prevented from forming automatic backflow, and can generate mass transfer and heat transfer with fuel and air when flowing through a combustion zone, so that the temperature of inlet air is increased, the stable combustion of flame is facilitated, and simultaneously, the content of oxygen participating in combustion air is reduced due to the backflow of fuel gas, and NO can be effectively reducedxAnd (4) discharging.
This application fuel inlet and gas outlet are located the homonymy, fuel and gaseous open end central zone at the flame tube mix, form combustion mixture 6, and receive the carminative promotion of pipeline, get into combustion zone 8, the mixture is after the combustion zone burning, continue to the bobbin base flow, and form the backward flow at the bobbin base, as shown in the figure, because combustion mixture 6 and combustion zone 8 are located near flame tube central axis basically, the gas after the burning is after touching the bobbin base center, to week side diffusion, form backward flow district 9, and flow to the open end along the section of thick bamboo wall of flame tube, discharge at the open end of flame tube finally, form backward flow gas 7, in the figure, backward flow gas 7 cladding has improved the temperature of inlet air in the outside of combustion mixture 6.
In some alternative embodiments, the fuel lines include fuel line 2 in the premix mode and fuel line 3 in the non-premix mode. The switching between the two fuel pipelines can realize the switching of premixed and non-premixed modes of fuel and air.
In some alternative embodiments, the outer portion of the flame tube 1 is sleeved with a combustion chamber outer casing 5, the inner wall of the combustion chamber outer casing 5 and the outer arm of the flame tube 1 are supported by a support frame, and a fluid or cooling air 11 is disposed in the combustion chamber outer casing 5.
In some alternative embodiments, the wall of the flame tube 1 is made of high temperature alloy.
In some alternative embodiments, the closed end of the flame tube 1 is made of high temperature ceramics, or the high temperature ceramics is added at the closed end of the inner part of the flame tube 1.
The flame tube wall of the high-temperature alloy and the high-temperature ceramic flame tube bottom (ceramic tube bottom 10) are welded to form a closed structure or are integrally designed, and a cooling gas is introduced between the outer casing 5 of the combustion chamber and the flame tube wall to cool the flame tube.
The invention has the advantages that:
1) the high-temperature backflow gas automatically flows back to be mixed with the inlet fuel, so that the temperature of the inflow gas is increased, and the combustion stability is improved;
2) the mixing of the reflux gas and the inlet gas reduces the oxygen content of the inflow gas and can greatly reduce NOxDischarging of (3);
3) the ceramic plate arranged at the bottom of the flame tube realizes automatic backflow of fuel gas;
4) the combustion chamber can be stably combusted under the conditions of lower inflow temperature and lower oil-gas ratio, and the working stability of the combustion chamber under low working conditions is improved.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (5)
1. From the backward flow formula combustion chamber of deciding oneself, its characterized in that includes: the flame tube comprises a flame tube (1), a fuel pipeline and an air pipeline (4), wherein one end of the flame tube (1) is open, the other end of the flame tube is closed, the outlet part of the fuel pipeline and the air pipeline (4) is arranged at the open end of the flame tube (1) and faces the interior of the flame tube (1), the outlet part of the open end of the flame tube (1) surrounding the fuel pipeline and the air pipeline (4) is used as a gas outlet, and the combustion area of the flame tube is arranged between the outlet part of the fuel pipeline and the air pipeline (4) and the closed end of the flame tube.
2. The autonomous reverse-flow combustor according to claim 1, characterized in that the fuel lines comprise a fuel line (2) in premixed mode and a fuel line (3) in non-premixed mode.
3. The self-circulation-back type combustion chamber as claimed in claim 1, wherein the outer portion of the flame tube (1) is sleeved with a combustion chamber outer casing (5), the inner wall of the combustion chamber outer casing (5) and the outer arm of the flame tube (1) are supported by a support frame, and cooling air is arranged in the combustion chamber.
4. The self-contained reverse flow type combustion chamber according to claim 1, characterized in that the wall of the flame tube (1) is made of high temperature alloy.
5. The self-contained reverse flow combustor according to claim 4, wherein the closed end of the liner (1) is made of high temperature ceramic or the high temperature ceramic is added at the closed end inside the liner (1).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811538081.5A CN109654536B (en) | 2018-12-16 | 2018-12-16 | Autonomous backflow type combustion chamber |
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| CN201811538081.5A CN109654536B (en) | 2018-12-16 | 2018-12-16 | Autonomous backflow type combustion chamber |
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| CN109654536A CN109654536A (en) | 2019-04-19 |
| CN109654536B true CN109654536B (en) | 2021-01-08 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110081462B (en) * | 2019-04-29 | 2021-04-02 | 天津天成智造科技有限公司 | Low-pollution combustion chamber |
| CN110107402B (en) * | 2019-04-29 | 2021-06-08 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Ceramic turbine engine |
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| JP2011163626A (en) * | 2010-02-08 | 2011-08-25 | Niigata Power Systems Co Ltd | Gas turbine combustor and method of supplying combustion air in the gas turbine combustor |
| CN203605215U (en) * | 2013-11-25 | 2014-05-21 | 常伟 | Stamping combustion chamber |
| CN104359127A (en) * | 2014-10-31 | 2015-02-18 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Channel type cooling structure of flame tube in combustion chamber of gas turbine |
| CN105371299A (en) * | 2015-09-24 | 2016-03-02 | 北京动力机械研究所 | Flame stabilizers for backflow combustor |
| CN107120689A (en) * | 2017-04-28 | 2017-09-01 | 中国航发湖南动力机械研究所 | Bend pipe structure and reverse flow type combustor, gas-turbine unit in reflowed combustion room |
| CN107620961A (en) * | 2017-11-02 | 2018-01-23 | 上海华之邦科技股份有限公司 | The novel super-low nitrogen combustion apparatus that a kind of non-premixed combustion and premixed combustion are combined |
| EP3301371A1 (en) * | 2016-09-30 | 2018-04-04 | Deutsches Zentrum Für Luft- Und Raumfahrt E.V. (DLR) | Combustion chamber system, use of a combustion chamber system with a connected turbine and method for performing a combustion process |
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2018
- 2018-12-16 CN CN201811538081.5A patent/CN109654536B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2011163626A (en) * | 2010-02-08 | 2011-08-25 | Niigata Power Systems Co Ltd | Gas turbine combustor and method of supplying combustion air in the gas turbine combustor |
| CN203605215U (en) * | 2013-11-25 | 2014-05-21 | 常伟 | Stamping combustion chamber |
| CN104359127A (en) * | 2014-10-31 | 2015-02-18 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Channel type cooling structure of flame tube in combustion chamber of gas turbine |
| CN105371299A (en) * | 2015-09-24 | 2016-03-02 | 北京动力机械研究所 | Flame stabilizers for backflow combustor |
| EP3301371A1 (en) * | 2016-09-30 | 2018-04-04 | Deutsches Zentrum Für Luft- Und Raumfahrt E.V. (DLR) | Combustion chamber system, use of a combustion chamber system with a connected turbine and method for performing a combustion process |
| CN107120689A (en) * | 2017-04-28 | 2017-09-01 | 中国航发湖南动力机械研究所 | Bend pipe structure and reverse flow type combustor, gas-turbine unit in reflowed combustion room |
| CN107620961A (en) * | 2017-11-02 | 2018-01-23 | 上海华之邦科技股份有限公司 | The novel super-low nitrogen combustion apparatus that a kind of non-premixed combustion and premixed combustion are combined |
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| CN109654536A (en) | 2019-04-19 |
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