CN109282307B - Standing vortex cavity rotational flow atomization device for flame tube head - Google Patents
Standing vortex cavity rotational flow atomization device for flame tube head Download PDFInfo
- Publication number
- CN109282307B CN109282307B CN201810904365.5A CN201810904365A CN109282307B CN 109282307 B CN109282307 B CN 109282307B CN 201810904365 A CN201810904365 A CN 201810904365A CN 109282307 B CN109282307 B CN 109282307B
- Authority
- CN
- China
- Prior art keywords
- cylinder
- cavity
- vortex cavity
- main
- swirler
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
-
- 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
Abstract
The invention relates to the field of design of main combustion chambers of aircraft engines, in particular to a standing vortex cavity rotational flow atomization device for a flame tube head, which comprises an outer swirler; a nozzle housing comprising: an outer cylinder; a middle cylinder; and, an inner barrel; a strut; a trapped vortex cavity; an inner swirler; a main oil pipe; an auxiliary oil pipe; and, a fuel pipe; wherein, the wall surface of the outer cylinder is provided with a main nozzle; a cooling through hole is formed in the wall surface of the standing vortex cavity; a middle hollow flow passage is formed between the outer cylinder and the outer cyclone; a main oil cavity is formed between the outer cylinder and the middle cylinder; an auxiliary oil cavity is formed between the middle cylinder body and the inner cylinder; an air inlet channel is formed between the inner cylinder and the trapped vortex cavity. The device has simple structure, can realize the staged combustion in the main combustion chamber of the aircraft engine, and solves the defects of the prior art.
Description
Technical Field
The invention relates to the field of design of main combustion chambers of aircraft engines, in particular to a standing vortex cavity rotational flow atomization device for a flame tube head.
Background
At present, along with the development of aeroengine technology, the design of aeroengine main combustion chamber gradually tends to high temperature rise, low pollution, wherein, traditional main combustion chamber flame tube head whirl atomizing device has not can satisfy present design requirement owing to have a great deal of problems such as smoking, carbon deposit, low combustion efficiency, high exhaust pollution.
In order to meet the requirements, the swirl atomizing device at the head of the flame tube of the main combustion chamber is improved and designed by the technical personnel in the field so as to realize a classified and zoned combustion organization mode and meet the current requirements.
At present, a swirl atomization device at the head of a flame tube of a main combustion chamber mainly comprises a fuel nozzle, a main swirler and an auxiliary swirler. The swirler is used for generating a backflow area in the flame tube, stable and efficient combustion is guaranteed, and fuel atomization is mainly realized by the aid of pressure difference at a nozzle and shearing action of airflow of the main swirler and the auxiliary swirler. It has the following disadvantages:
1. when the engine is in a large working condition, the pressure in the main combustion chamber is high, and fuel oil near a nozzle is concentrated, so that the problems of smoke generation, carbon deposition, reduction of combustion efficiency and the like are caused;
2. when the engine is in a small working condition, the oil supply amount of the main combustion chamber is low, the atomization level of a nozzle is poor, the combustion stability is poor, and flameout is easy to occur;
3. can not realize good atomizing and oil gas matching under the full operating mode, exhaust pollution is high.
Disclosure of Invention
It is an object of the present invention to provide a trapped vortex chamber swirl atomizing apparatus for a combustor basket head which alleviates or overcomes at least one of the problems mentioned above.
The technical scheme of the invention is as follows: a trapped vortex cavity swirl atomizing apparatus for a flame tube head, comprising:
the inlet end of the outer swirler is communicated with the air inlet, and the end surface of the outer wall of the outlet end of the outer swirler is connected with the end surface of the inlet of the flame tube;
a nozzle housing comprising:
the outer cylinder is coaxially arranged at the inner side of the outer swirler, an intermediate air flow passage is formed between the outer cylinder and the inner wall surface of the outer swirler, and a main nozzle is formed on the wall surface of the outer cylinder;
the middle cylinder is coaxially arranged on the inner side of the outer cylinder, and a closed main oil cavity is formed between the middle cylinder and the outer cylinder; and the number of the first and second groups,
the inner cylinder is coaxially arranged at the inner side of the middle cylinder body, and a closed auxiliary oil cavity is formed between the inner cylinder and the middle cylinder body;
the support rod is positioned in the middle air flow channel, one end of the support rod is fixedly connected with the inner wall of the outer cyclone, and the other end of the support rod is fixedly connected with the wall of the outer cylinder;
the trapped vortex cavity is coaxially arranged on the inner side of the inner cylinder, the concave cavity faces the flame tube, a cooling through hole and a fuel oil through hole are formed in the wall surface of the trapped vortex cavity, an air inlet channel is formed between the trapped vortex cavity and the inner cylinder, and the air inlet channel is communicated with the middle air flow channel;
the inner swirler is arranged at one end of the air inlet channel close to the middle air flow channel;
the main oil pipe is communicated with the main oil cavity;
the auxiliary oil pipe is communicated with the auxiliary oil cavity; and the number of the first and second groups,
and the fuel pipe is arranged between the inner cylinder and the trapped vortex cavity, one end of the fuel pipe is communicated with the auxiliary oil cavity, and the other end of the fuel pipe is communicated with the fuel through hole.
Preferably, the secondary oil pipe is disposed coaxially inside the primary oil pipe.
Preferably, the outer swirler has an opposite swirling direction to the gas flow of the inner swirler.
Preferably, the opening angle of the concave cavity for arranging the trapped vortex cavity is between 30 and 90 degrees.
Preferably, the number of the main nozzles is 4-12 and is evenly distributed in the circumferential direction.
Preferably, the number of the fuel pipes is 1-4, and the fuel pipes are uniformly arranged in the circumferential direction.
The invention has the advantages that the standing vortex cavity rotational flow atomization device for the head part of the flame tube is simple in structure, staged combustion in a main combustion chamber of an aero-engine can be realized, the standing vortex cavity structure can reduce the local air flow rate, so that the combustion stability of the main combustion chamber under a small working condition is solved, the main combustion stage backflow area is lean oil premixed combustion by arranging the outer swirler and the inner swirler, so that the problems of smoke emission, carbon deposition, low combustion efficiency and the like of the combustion chamber under a large working condition are solved, meanwhile, the problems of spontaneous combustion, backfire, unstable combustion and the like are effectively avoided, and exhaust pollution is reduced.
Drawings
FIG. 1 is a structural section view of a standing vortex cavity swirl atomizing device for a flame tube head.
Fig. 2 is a schematic diagram of the trapped vortex cavity structure in fig. 1.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. 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 only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. 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 invention. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present invention and for simplifying the description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be taken as limiting the scope of the present invention.
The present invention is described in further detail below with reference to fig. 1.
The invention provides a standing vortex cavity rotational flow atomization device for a flame tube head, which comprises:
the inlet end of the outer swirler 1 is communicated with the air inlet, and the end surface of the outer wall of the outlet end is connected with the end surface of the inlet of the flame tube;
a nozzle housing 3, comprising:
the outer cylinder is coaxially arranged at the inner side of the outer swirler 1, an intermediate air flow channel C is formed between the outer cylinder and the inner wall surface of the outer swirler 1, and a main nozzle 8 is formed in the side wall of the outer cylinder;
the middle cylinder is coaxially arranged on the inner side of the outer cylinder, and a closed main oil cavity D is formed between the middle cylinder and the outer cylinder; and the number of the first and second groups,
the inner cylinder is coaxially arranged at the inner side of the middle cylinder body, and a closed auxiliary oil cavity E is formed between the inner cylinder and the middle cylinder body;
the strut 6 is positioned in the middle air flow channel, one end of the strut is fixedly connected with the inner wall of the outer cyclone, and the other end of the strut is fixedly connected with the wall of the outer cylinder;
the trapped vortex cavity 4 is coaxially arranged on the inner side of the inner cylinder, the cavity of the trapped vortex cavity faces the flame tube, the wall surface of the trapped vortex cavity is provided with a cooling through hole 5 and a fuel oil through hole, an air inlet channel is formed between the trapped vortex cavity 4 and the inner cylinder and is communicated with the middle air flow channel C;
the inner swirler 2 is arranged at one end of the air inlet channel close to the middle air flow channel C;
the main oil pipe 10 is communicated with the main oil cavity D;
the auxiliary oil pipe 9 is communicated with the auxiliary oil cavity E; and the number of the first and second groups,
and the fuel pipe 7 is arranged between the inner cylinder and the trapped vortex cavity, one end of the fuel pipe is communicated with the auxiliary oil cavity E, and the other end of the fuel pipe is communicated with the fuel through hole.
When the swirl atomization device works, a pre-combustion stage backflow area A and a main-combustion stage backflow area B can be formed in the combustion area in the flame tube. Wherein, the pre-combustion stage reflux area A is formed by depending on a concave cavity of the standing vortex cavity 4; the main combustion stage backflow area B is mainly formed by the swirling flow generated by the outer swirler 1. Incoming air flows into the flame tube through the outer swirler 1, the middle airflow channel C, the inner swirler 2 and the cooling holes 5 respectively, wherein the air flowing in through the outer swirler 1 enters the main combustion stage backflow area B; the air flowing in through the middle air flow channel C is mixed with the air flowing in through the inner cyclone 2, then the majority of the air enters the main combustion stage backflow area B, and the minority of the air is sucked into the pre-combustion stage backflow area A; the air flowing through the cooling holes 5 cools the trapped vortex cavity 4 and then enters the pre-combustion stage return area A.
Under a small working condition, fuel oil flows into the auxiliary oil cavity E from the auxiliary oil pipe 9 and then is directly sprayed into the pre-combustion stage backflow area A through the fuel oil pipe 7, the fuel oil is diffused and combusted at the position, the fuel-air ratio is high, an oil-rich combustion area is formed, the air flow rate in the cavity of the trapped vortex cavity 4 is low, flame is not easy to extinguish, starting and flame stabilization are facilitated, and unburned oil-gas mixture at the position can be mixed with air in the main combustion stage backflow area B at the downstream for further combustion, so that pollution emission under a small working condition can be reduced.
In a large working condition, except that fuel oil is directly sprayed into the pre-combustion stage backflow area A through the fuel oil pipe 7, the fuel oil flows into the main oil cavity D from the main oil pipe 10, and is sprayed into the middle air flow passage C at the main nozzle 8 to be mixed with air in the middle air flow passage C, so that the atomization quality of the fuel oil and the uniformity of oil-gas mixing are improved, the problems of spontaneous combustion, tempering, unstable combustion and the like are not easy to occur in the middle air flow passage due to high oil-gas ratio, the mixed oil-gas is further mixed with the air flowing in from the inner swirler 2 before entering the main combustion stage backflow area B, the mixing effect can be effectively enhanced, the oil-gas ratio is quickly reduced, rich oil is changed into lean oil, the lean oil is premixed and combusted after entering the main combustion stage backflow area B, the problems of smoke generation, carbon deposition and the like are avoided, and high combustion efficiency and low pollution emission are ensured.
No matter big operating mode or little operating mode, vice oil pipe 9 need be the oil feed for vice oil pocket E all the time, can be here with vice oil pipe 9 coaxial setting inside main oil pipe 10, and the during operation vice oil pipe 9 can cool off main oil pipe, need not additionally to set up complicated oil pipe cooling structure.
The air flow rotating directions of the outer cyclone 1 and the inner cyclone 2 are set to be opposite, so that the oil-gas mixing effect can be effectively improved.
Further, the opening angle of the cavity of the trapped vortex cavity 4 is set to be between 30 and 90 degrees according to engineering design experience.
Further, the number of the main nozzles 8 is set to 4 to 12 and is evenly distributed in the circumferential direction.
Further, the number of the fuel pipes 7 is 1-4, and the fuel pipes are circumferentially and uniformly arranged.
The above description is only for the specific embodiment of the present invention, but the scope of the present invention 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 invention should be covered within the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (6)
1. A trapped vortex cavity swirl atomizing device for a flame tube head, comprising:
the inlet end of the outer swirler (1) is communicated with the air inlet, and the end surface of the outer wall of the outlet end is connected with the end surface of the inlet of the flame tube;
a nozzle housing (3) comprising:
the outer cylinder is coaxially arranged on the inner side of the outer swirler (1), an intermediate air flow channel (C) is formed between the outer cylinder and the inner wall of the outer swirler (1), and a main nozzle (8) is formed in the side wall of the outer cylinder;
the middle cylinder is coaxially arranged on the inner side of the outer cylinder, and a closed main oil cavity (D) is formed between the middle cylinder and the outer cylinder; and the number of the first and second groups,
the inner cylinder is coaxially arranged at the inner side of the middle cylinder body, and a closed auxiliary oil cavity (E) is formed between the inner cylinder and the middle cylinder body;
the support rod (6) is positioned in the middle air flow channel, one end of the support rod is fixedly connected with the inner wall of the outer cyclone, and the other end of the support rod is fixedly connected with the outer cylinder wall;
the trapped vortex cavity (4) is coaxially arranged on the inner side of the inner cylinder, the cavity of the trapped vortex cavity faces the flame tube, the wall surface of the trapped vortex cavity is provided with a cooling through hole (5) and a fuel oil through hole, an air inlet channel is formed between the trapped vortex cavity (4) and the inner cylinder, and the air inlet channel is communicated with the intermediate air flow channel (C);
an inner swirler (2) arranged at one end of the air inlet channel close to the middle air flow channel (C);
a main oil pipe (10) communicating with the main oil chamber (D);
an auxiliary oil pipe (9) communicated with the auxiliary oil chamber (E); and the number of the first and second groups,
and the fuel pipe (7) is arranged between the inner cylinder and the trapped vortex cavity, one end of the fuel pipe is communicated with the auxiliary oil cavity (E), and the other end of the fuel pipe is communicated with the fuel through hole.
2. The cyclonic atomizing apparatus of claim 1, wherein: the auxiliary oil pipe (9) is coaxially arranged inside the main oil pipe (10).
3. The cyclonic atomizing apparatus of claim 1, wherein: the air flow rotating directions of the outer swirler (1) and the inner swirler (2) are opposite.
4. The cyclonic atomizing apparatus of claim 1, wherein: the opening angle of the concave cavity of the trapped vortex cavity (4) is between 30 and 90 degrees.
5. The cyclonic atomizing apparatus of claim 1, wherein: the number of the main nozzles 8 is 4-12, and the main nozzles are uniformly distributed in the circumferential direction.
6. The cyclonic atomizing apparatus of claim 1, wherein: the number of the fuel pipes (7) is 1-4, and the fuel pipes are uniformly arranged in the circumferential direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810904365.5A CN109282307B (en) | 2018-08-09 | 2018-08-09 | Standing vortex cavity rotational flow atomization device for flame tube head |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810904365.5A CN109282307B (en) | 2018-08-09 | 2018-08-09 | Standing vortex cavity rotational flow atomization device for flame tube head |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109282307A CN109282307A (en) | 2019-01-29 |
| CN109282307B true CN109282307B (en) | 2020-04-21 |
Family
ID=65182751
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810904365.5A Active CN109282307B (en) | 2018-08-09 | 2018-08-09 | Standing vortex cavity rotational flow atomization device for flame tube head |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109282307B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111735077B (en) * | 2019-03-25 | 2021-10-12 | 中国航发湖南动力机械研究所 | Flame tube device, combustion chamber and engine |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2211596A (en) * | 1985-08-23 | 1989-07-05 | Gen Electric | Gas turbine engine carburetor |
| EP1186832A2 (en) * | 2000-09-08 | 2002-03-13 | General Electric Company | Fuel nozzle assembly for reduced exhaust emissions |
| CN101169252A (en) * | 2007-11-29 | 2008-04-30 | 北京航空航天大学 | Aerial engine lean premixed preevaporated low contamination combustion chamber |
| WO2008133695A1 (en) * | 2007-05-01 | 2008-11-06 | Ingersoll-Rand Energy Systems | Trapped vortex combustion chamber |
| CN103196159A (en) * | 2013-03-18 | 2013-07-10 | 哈尔滨工程大学 | Annular grading trapped vortex combustor |
| JP2013253767A (en) * | 2012-06-05 | 2013-12-19 | General Electric Co <Ge> | Combustor with brief severe quench zone |
| CN104456627A (en) * | 2014-10-27 | 2015-03-25 | 北京航空航天大学 | Lean oil premixing and pre-evaporating combustion chamber head structure with cyclone/pre-film plate integrated primary combustion stage |
-
2018
- 2018-08-09 CN CN201810904365.5A patent/CN109282307B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2211596A (en) * | 1985-08-23 | 1989-07-05 | Gen Electric | Gas turbine engine carburetor |
| EP1186832A2 (en) * | 2000-09-08 | 2002-03-13 | General Electric Company | Fuel nozzle assembly for reduced exhaust emissions |
| WO2008133695A1 (en) * | 2007-05-01 | 2008-11-06 | Ingersoll-Rand Energy Systems | Trapped vortex combustion chamber |
| CN101169252A (en) * | 2007-11-29 | 2008-04-30 | 北京航空航天大学 | Aerial engine lean premixed preevaporated low contamination combustion chamber |
| JP2013253767A (en) * | 2012-06-05 | 2013-12-19 | General Electric Co <Ge> | Combustor with brief severe quench zone |
| CN103196159A (en) * | 2013-03-18 | 2013-07-10 | 哈尔滨工程大学 | Annular grading trapped vortex combustor |
| CN104456627A (en) * | 2014-10-27 | 2015-03-25 | 北京航空航天大学 | Lean oil premixing and pre-evaporating combustion chamber head structure with cyclone/pre-film plate integrated primary combustion stage |
Non-Patent Citations (1)
| Title |
|---|
| 燃气轮机燃烧室专利分析与研究;赵传亮等;《航空发动机》;20150815(第04期);第77-83页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109282307A (en) | 2019-01-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108561897B (en) | Partial premixing and pre-evaporating ultralow emission combustion chamber for enhancing oil-gas mixing | |
| CN109595589B (en) | Integrated afterburner with two-stage cyclone | |
| CN107543201B (en) | One kind is oil-poor directly to spray and mixes low pollution combustor | |
| CN203757766U (en) | Rich oil direct-mixing partitioning combustion chamber | |
| CN106678868B (en) | A kind of integrated after-burner of deflection rectification supporting plate flameholder | |
| CN102200291B (en) | Pneumatic primary level graded low-pollution combustion chamber | |
| CN108072053B (en) | Rotational flow atomization device | |
| CN106091013B (en) | A kind of high temperature rise combustor structure of three-level stratified combustion | |
| CN110686275B (en) | Combustion chamber flame stabilizing structure for reinforcing mixing and flame propagation | |
| CN105953265A (en) | Combination combustion chamber | |
| CN107525095B (en) | A kind of axially staged can burner of gas turbine | |
| CN103047683B (en) | Partial premixing and pre-evaporation combustion chamber with three-level oil passages | |
| CN108253455B (en) | Premixing and pre-evaporating ultra-low emission combustion chamber head and combustion chamber thereof | |
| CN206001524U (en) | A kind of combustor radial direction two-stage swirl nozzle | |
| CN108916912A (en) | A kind of pre-combustion grade uses the low emission combustor head of cooling anti-carbon deposition structure | |
| CN108758693A (en) | A kind of integrated after-burner with double oil circuits and butt center wimble structure | |
| CN108954388A (en) | A kind of multiple spot unit directly sprays fractional combustion room | |
| CN109539309A (en) | A kind of cavity standing vortex and rectification supporting plate combined integral after-burner | |
| CN103411236B (en) | Opening side skirt plate type on-duty flame stabilizer | |
| CN109654533A (en) | A kind of trailing edge blowing formula stabilizer adapting to incoming flow distortion | |
| CN103486617A (en) | Dual-fuel low-emission burner for gas turbine | |
| CN114608032B (en) | Combustor with widened stability boundary | |
| CN110925794A (en) | Discrete multi-point rotational flow pressure atomizing nozzle, combustion chamber head and combustion chamber | |
| CN107228362B (en) | A kind of oil-poor direct-injection low pollution combustor of multiple spot with precombustion chamber | |
| CN109282307B (en) | Standing vortex cavity rotational flow atomization device for flame tube head |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |