CN109210573A - A kind of Novel variable-section aeroengine combustor buring room - Google Patents
A kind of Novel variable-section aeroengine combustor buring room Download PDFInfo
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- CN109210573A CN109210573A CN201810909112.7A CN201810909112A CN109210573A CN 109210573 A CN109210573 A CN 109210573A CN 201810909112 A CN201810909112 A CN 201810909112A CN 109210573 A CN109210573 A CN 109210573A
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- Prior art keywords
- bluff body
- combustion chamber
- section
- dog
- ear
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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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/58—Cyclone or vortex type combustion chambers
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Combustion Methods Of Internal-Combustion Engines (AREA)
Abstract
The invention discloses a kind of Novel variable-section aeroengine combustor buring rooms, and including the preceding bluff body, cavity and rear bluff body being arranged in the combustion chamber, the preceding bluff body and rear bluff body are in the location of combustion chamber respectively preceding combustion chamber and after-burner；The cavity between preceding bluff body and rear bluff body by forming, dog-ear is set on gas passage, bluff body is parallel to the jet hole that cyclone is provided on the side of chamber passage after described, can optimize existing combustion chamber there are the problem of, and realize efficient burning, low emission and low pitot loss.
Description
Technical field
The invention belongs to aeroengine combustor buring room field more particularly to a kind of Novel variable-section aeroengine combustor burings
Room.
Background technique
In recent years, Civil Aviation Industry is developed rapidly, the research and development of aero-engine are towards high thrust, low emission
Direction effort.Currently, the research of low emission combustor is concentrated mainly on standing vortex burning chamber (TVC), TVC have efficiency of combustion compared with
Advantage high, pollutant emission is lower, the indoor temperature rise of burning is lower and pitot loss is smaller.But if more than realizing
Advantage it is necessary to meeting ideal state when TVC work, such as make the mixing of oil gas Quick uniform, formed in cavity it is ideal double
Vortex structure etc..
In order to realize ideal double vortex structure, there is scholar to propose to spray gas mixture using on cavity front face top,
Air is sprayed in the middle part of rear surface, but the jet velocity of air and oil gas is difficult to control in a preferable level.In addition there is scholar
It is proposed to use the TVC of flow deflector and rear bluff body more to manage using flow deflector by a part of oil gas importing cavity of mainstream to be formed
The double vortex structure thought, the flow-disturbing effect of bluff body after recycling, so that air-fuel mixture is more uniform, but cavity is that a comparison is multiple
Miscellaneous component, its size have a significant impact to combustibility, especially for the TVC of front and rear wall oil spout gas and air, realize
Get up more difficult.In addition, also having the combustion chamber without using cavity, although can still make like that with flow deflector and rear bluff body
It is low to obtain oil gas mixability in flow process, causes efficiency of combustion low, while combustion zone temperature being be easy to cause to be unevenly distributed
It is even, it is unfavorable for reducing discharge.
Summary of the invention
The present invention is insufficient according to prior art and defect, proposes a kind of Novel variable-section aeroengine combustor buring room,
Purpose is to avoid to optimize problem existing for combuster using complicated cavity, and realize efficient burning,
Low emission and low pitot loss.
A kind of Novel variable-section aeroengine combustor buring room, including preceding bluff body, the cavity and rear blunt being arranged in the combustion chamber
Body, the preceding bluff body and rear bluff body are respectively preceding combustion chamber and after-burner in the location of combustion chamber；The cavity is by preceding
It is formed between bluff body and rear bluff body, dog-ear is set on gas passage, the rear bluff body, which is parallel on the side of chamber passage, to be set
Set the jet hole with cyclone；
Further, the rear bluff body is equipped with 2 discharge discharge orifices, and every row is arranged 4, and the bore dia of each jet hole is 4mm；
Further, the cyclone is vane type axial swirler；
Further, the dog-ear is symmetricly set on gas passage, for connecting preceding combustion chamber and after-burner, so that after
The width of chamber passage is narrower than preceding combustion chamber, and the angle of dog-ear 3 is 30 °；
Further, it is the folding at 0.4 times of entire chamber length that the length apart from inlet, which is arranged in, in the dog-ear
The height at angle is 0.5 times of air inlet of combustion chamber channel width, and the air inlet of combustion chamber channel width is the upper of preceding combustion chamber
Width between surface and the upper surface of preceding bluff body；
Further, the front end face of dog-ear bottom end and the channel attached position of after-burner and rear bluff body is in the same vertical plane
On.
Further, the preheating device of the arc-shaped front face of preceding bluff body preheats air-flow；Preheating device is set to
Inside preceding bluff body, preheating method is inside preceding bluff body arc surface, is close to front face using heater element, such as iron aluminium closes
The nonmetallic materials such as the metal materials such as gold, nichrome and silicon carbide, molybdenum disilicide, the galvanization on heater element and make element
Fever achievees the effect that preheat mainstream so that bluff body front face is heated before making.
Beneficial effects of the present invention:
A kind of Novel variable-section aeroengine combustor buring room of the present invention, using dog-ear and with the jet stream of cyclone
Hole, so that incoming flow preferably turbulization, and temperature of incoming flow is increased using preheating device, to improve fuel availability, improve
Combustor exit temperature distribution, so that the generation of NO is maintained at a lower level, while can significantly improve combustion chamber and go out
Mouth flow velocity, to improve the performance of gas turbine.
Detailed description of the invention
Fig. 1 is a kind of Novel variable-section aeroengine combustor buring of the invention room perspective view；
Fig. 2 is combustion chamber top view of the present invention；
Fig. 3 is swirler blades schematic diagram of the present invention；
Fig. 4 is hydrocyclone structure schematic diagram of the present invention.
In figure, 1, be entry of combustion chamber, 2, preheating face, 3, preceding bluff body, 4, dog-ear, 5, rear bluff body, 6, combustor exit, 7,
Chamber passage, 8, jet hole, 9, cavity.
Specific embodiment
In order to make the objectives, technical solutions, and advantages of the present invention clearer, with reference to the accompanying drawings and embodiments, right
The present invention is further elaborated.It should be appreciated that described herein, the specific embodiments are only for explaining the present invention, not
For limiting the present invention.
As shown in Figure 1, 2, it is logical to be included in combustion chamber for a kind of Novel variable-section aeroengine combustor buring of embodiment of the present invention room
Preceding bluff body 3, cavity 9 and the rear bluff body 5 being arranged in road, the preheating device of preceding bluff body front face, preheating device are set to preceding bluff body
Inside, preheating method is inside preceding bluff body arc surface, is close to front face using heater element, such as ferroaluminium, nickel chromium triangle
The nonmetallic materials such as the metal materials such as alloy and silicon carbide, molybdenum disilicide, the galvanization on heater element and make element heating, from
And bluff body front face is heated before making, and be can be realized and is preheated to the air-flow for entering combustion chamber；It is parallel in chamber passage
It is respectively preceding combustion chamber and after-combustion that preceding bluff body 3 and rear bluff body 5, preceding bluff body 3 and rear bluff body 5, which is arranged, in the location of combustion chamber
Room forms cavity 9 between preceding bluff body 3 and rear bluff body 5, dog-ear 3 is symmetricly set on gas passage, and dog-ear 3 connects preceding combustion chamber
And after-burner, so that the width in after-burner channel is narrower than preceding combustion chamber, and the angle of dog-ear 4 is 30 °, at this time in combustion chamber
Combustion case it is best, although ignition temperature is higher, Temperature Distribution more evenly, can make the generation of NO be maintained in this way
One lower level；Dog-ear 4 is arranged at 0.4 times that the length apart from inlet is entire chamber length, so that mainstream
Preferably turbulization, in combustion chamber, back segment more fully burns, to improve efficiency of combustion；The height of the dog-ear 4 is burning
0.5 times of room air inlet total height, height is too high to will affect air-flow flowing, causes pitot loss excessive, height is too low to be will cause
Flow-disturbing effect is unobvious；The position of 3 bottom end of dog-ear and the front end face of rear bluff body 5 are on a vertical plane, so that dog-ear water conservancy diversion is made
Gas after can guarantee that dog-ear 4 and jet stream can play optimal disturb simultaneously close to the position of rear about 5 two sides of bluff body in this way
Stream effect, becomes apparent from perturbation action.
Such as Fig. 1, rear bluff body 5 is parallel to the jet hole 8 that cyclone is provided on the side of chamber passage；Bluff body 5 afterwards
On jet hole 8 be equipped with 2 rows, every row is arranged 4, and the bore dia of each jet hole is 4mm；Cyclone as shown in Figure 3,4 is leaf
Chip axial swirler；It is mounted in jet hole 8.
It is further explained below with reference to the course of work of the invention:
Primary air is from flow into combustor from entry of combustion chamber 1, pre- by the preheating face 2 at the circular arc wall surface of preceding bluff body 3
After heat, air inlet of combustion chamber channel flowing in combustion chamber primary zone of the air-flow from preceding 3 two sides of bluff body.Before entering primary zone,
The dog-ear 4 at 30 ° of angle can be met in air-flow flow process, after encountering dog-ear 4, flow direction can change air-flow, stream
Dynamic to be also disturbed, disorder degree can be got higher, and the air-flow being disturbed can be met during toward movement in the middle part of combustion chamber
To the jet stream of rear about 5 two side walls of bluff body, the turbulization degree of air-flow is further enhanced, makes the more abundant of fuel combustion, combustion
Efficiency is burnt to improve.Since combustion chamber wall surface narrows, air-flow velocity is accelerated, and combustor exit flow velocity correspondinglys increase, and combustion can be improved
Gas turbine performance.
The height of bluff body 5 and thickness can cause various sizes of whirlpool afterwards, thus to the indoor air flow condition of burning, burned
Journey can have a major impact, should be in the actual process according to the ruler of entire combustion chamber because the size selection of hereafter bluff body 5 is particularly significant
The requirement of very little, burning and discharge is determined.
In the description of this specification, reference term " one embodiment ", " some embodiments ", " illustrative examples ",
The description of " example ", " specific example " or " some examples " etc. means specific features described in conjunction with this embodiment or example, knot
Structure, material or feature are included at least one embodiment or example of the invention.In the present specification, to above-mentioned term
Schematic representation may not refer to the same embodiment or example.Moreover, specific features, structure, material or the spy of description
Point can be combined in any suitable manner in any one or more of the embodiments or examples.
Above embodiments are merely to illustrate design philosophy and feature of the invention, and its object is to make technology in the art
Personnel can understand the content of the present invention and implement it accordingly, and protection scope of the present invention is not limited to the above embodiments.So it is all according to
It is within the scope of the present invention according to equivalent variations made by disclosed principle, mentality of designing or modification.
Claims (7)
1. a kind of Novel variable-section aeroengine combustor buring room, which is characterized in that including the preceding bluff body being arranged in the combustion chamber
(3), the burning before the location of combustion chamber is respectively of cavity (9) and rear bluff body (5), the preceding bluff body (3) and rear bluff body (5)
Room and after-burner；Dog-ear (4) are arranged on gas passage by being formed between preceding bluff body (3) and rear bluff body (5) in the cavity (9),
Bluff body (5) is parallel to the jet hole (8) that cyclone is provided on the side of chamber passage after described.
2. a kind of Novel variable-section aeroengine combustor buring room according to claim 1, which is characterized in that bluff body after described
(5) 2 discharge discharge orifices are equipped with, every row is arranged 4, and the bore dia of each jet hole is 4mm.
3. a kind of Novel variable-section aeroengine combustor buring room according to claim 1, which is characterized in that the cyclone
For vane type axial swirler.
4. a kind of Novel variable-section aeroengine combustor buring room according to claim 1, which is characterized in that the dog-ear
(4) it is symmetricly set on gas passage, for connecting preceding combustion chamber and after-burner, so that before the width ratio in after-burner channel
Combustion chamber is narrow, and the angle of dog-ear (4) is 30 °.
5. a kind of Novel variable-section aeroengine combustor buring room according to claim 4, which is characterized in that the dog-ear
(4) it is 0.4 times of entire chamber length place that the length apart from inlet, which is arranged in, and the height of the dog-ear (4) is combustion chamber
0.5 times of air intake passage width, the air inlet of combustion chamber channel width are the upper of upper surface and the preceding bluff body of preceding combustion chamber
Width between surface.
6. a kind of according to claim 1, Novel variable-section aeroengine combustor buring room described in 4 or 5, which is characterized in that dog-ear
(4) front end face of bottom end and the channel attached position of after-burner and rear bluff body is on the same vertical plane.
7. a kind of Novel variable-section aeroengine combustor buring room according to claim 4, which is characterized in that the preceding bluff body
(3) preheating device of arc-shaped front face preheats air-flow.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810909112.7A CN109210573B (en) | 2018-08-10 | 2018-08-10 | Novel variable cross-section aeroengine combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810909112.7A CN109210573B (en) | 2018-08-10 | 2018-08-10 | Novel variable cross-section aeroengine combustion chamber |
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| Publication Number | Publication Date |
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| CN109210573A true CN109210573A (en) | 2019-01-15 |
| CN109210573B CN109210573B (en) | 2023-08-18 |
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| CN201810909112.7A Active CN109210573B (en) | 2018-08-10 | 2018-08-10 | Novel variable cross-section aeroengine combustion chamber |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114777158A (en) * | 2022-05-13 | 2022-07-22 | 哈尔滨工程大学 | Combustion chamber mixing structure based on blunt body group |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114777158A (en) * | 2022-05-13 | 2022-07-22 | 哈尔滨工程大学 | Combustion chamber mixing structure based on blunt body group |
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| CN109210573B (en) | 2023-08-18 |
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