CN107906560B - A kind of standing vortex declines type gas turbine combustors - Google Patents
A kind of standing vortex declines type gas turbine combustors Download PDFInfo
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- CN107906560B CN107906560B CN201711097957.2A CN201711097957A CN107906560B CN 107906560 B CN107906560 B CN 107906560B CN 201711097957 A CN201711097957 A CN 201711097957A CN 107906560 B CN107906560 B CN 107906560B
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- inner liner
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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
- F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
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- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gas Burners (AREA)
Abstract
It declines type gas turbine combustors the invention discloses a kind of standing vortex, including burner inner liner and casing, burner inner liner includes flame drum outer wall, burner inner liner antetheca and burner inner liner inner wall, flame drum outer wall, burner inner liner antetheca and burner inner liner inner wall seal to form burner inner liner airstream compartment A, and annular housing B is formed between burner inner liner and casing；Flame drum outer wall is provided with the second jet hole, and flame drum outer wall is provided with third jet hole far from burner inner liner antetheca one end；The first jet hole is provided on burner inner liner antetheca；It is provided with the 4th jet hole on burner inner liner inner wall, first group of cooling hole is provided on flame drum outer wall, second group of cooling hole is provided on burner inner liner inner wall.The invention enables the strong inverse flow areas at center can make the residence time increase of air-flow in the combustion chamber, and the periphery low speed region of recirculating zone increases, and is conducive to flame transmission, so that head zone be made to stablize burning.
Description
Technical field
The present invention relates to micro gas turbine engine combustion chamber field more particularly to a kind of standing vortex formula micro gas turbines
Engine chamber.
Background technique
Miniature turbine jet engines (Micro-turbine en-gine, MTE) are with light-weight, power is big, thrust ratio
The advantages that high.For small-sized and miniature unmanned vehicle in execution such as aerial reconnaissance, training of practicing shooting, electronic interferences, communication
After, environmental monitoring, nuclear radiation sampling and air-to-ground attack etc., more and more important role will be played the part of from now on.With close
To the demand of unmanned vehicle development over year, miniature turbine class engine has also been correspondingly made available very big development.The U.S. is generation
Carry out the country of small-sized and miniature turbine class engine technology research in boundary at first and model kind is most and technology is most advanced
Country.Nineteen sixty, the miniature whirlpool eruption that Williams international corporation, the U.S. has developed 265N thrust earliest in the world are dynamic
Machine WR2-1, it is also pioneer's type of nowadays American Tomahawk cruise missile fanjet F107-WR-100.
It is continuously improved by decades, in the world the small-sized and microjet technology of aeronautical technology developed country
Obtain the development advanced by leaps and bounds.This kind of engine has that size is small, light-weight, structure is simple, the at low cost, service life in design
The features such as short and working service facilitates, the fuel system of combustion chamber mainly use pressure atomization formula, air atomizing formula and evaporation
Tubular type, and combustion chamber is mostly based on reflux and direct current ring structure.Currently, each state is all stepping up design and research to MTE.And
As the combustion chamber of one of MTE key technology, due to the micromation (grade to Centimeter Level) of size, so that its surface to volume ratio is big,
Heat transfer loss greatly increases.Combustion residence time is short, it may appear that the case where fuel burn incompletely.Therefore, improving its burning
Adequacy, improving its efficiency of combustion etc., there are also very big rooms for promotion.
Summary of the invention
Place in view of the shortcomings of the prior art, the purpose of the present invention is to provide a kind of standing vortex formula micro gas turbines
Engine chamber enables the strong inverse flow area at center to increase the residence time of air-flow in the combustion chamber, and recirculating zone
Periphery low speed region increase, be conducive to flame transmission, thus make head zone stablize burning.
The purpose of the invention is achieved by the following technical solution:
A kind of standing vortex declines type gas turbine combustors, including burner inner liner and casing, and the burner inner liner includes fire
Flame drum outer wall, burner inner liner antetheca and burner inner liner inner wall, the flame drum outer wall are sealedly and fixedly connected with burner inner liner antetheca, the fire
Flame cylinder inner wall is located inside flame drum outer wall, and the burner inner liner inner wall is sealedly and fixedly connected with burner inner liner antetheca；The burner inner liner
Outer wall, burner inner liner antetheca and burner inner liner inner wall seal to form burner inner liner airstream compartment A, form ring between the burner inner liner and casing
Shape cavity B；The flame drum outer wall is provided with several for being connected to the second jet stream of burner inner liner airstream compartment A Yu annular housing B
Hole, the flame drum outer wall are provided with for being connected to burner inner liner airstream compartment A and annular housing B far from burner inner liner antetheca one end
Three jet holes；The first jet hole for being connected to burner inner liner airstream compartment A Yu annular housing B is provided on the burner inner liner antetheca；
The 4th jet hole for being connected to burner inner liner airstream compartment A Yu annular housing B, the burner inner liner are provided on the burner inner liner inner wall
It is provided with first group of cooling hole for being connected to burner inner liner airstream compartment A Yu annular housing B on outer wall, is opened on the burner inner liner inner wall
There is second group of cooling hole for being connected to burner inner liner airstream compartment A Yu annular housing B.
In order to which the present invention is better achieved, the burner inner liner is flame tube head primary zone close to burner inner liner antetheca one end,
The flame tube head primary zone uses sudden expansion structure, and the flame tube head primary zone is standing vortex form structure.
Preferably, the flame drum outer wall and burner inner liner inner wall are all made of variable cross-section design.
Preferably, first group of cooling hole is made of several cooling holes, second group of cooling hole is by several coolings
Hole is constituted；The cooling hole of first group of cooling hole, the cooling hole of second group of cooling hole are oblique annulus hole, oblique annulus hole it is interior
Circular diameter is 3~8mm, and the depth in hole is 0.5~1.5mm.
Preferably, the cooling hole of first cooling hole and flame drum outer wall central axis are at 20 °~45 ° angles, institute
The cooling hole and burner inner liner inner wall central axis for stating the second cooling hole are at 20 °~45 ° angles.
Preferably, first jet hole forms diversion edges to burner inner liner airstream compartment A direction flange, diversion edges are high
Degree is 1~3mm；Second jet hole forms diversion edges to burner inner liner airstream compartment A direction flange, and diversion edges height is 1
~3mm.
Preferably, the third jet hole forms diversion edges to burner inner liner airstream compartment A direction flange, diversion edges are high
Degree is 1~3mm；4th jet hole forms diversion edges to burner inner liner airstream compartment A direction flange, and diversion edges height is 1
~3mm
Preferably, the bore dia of first jet hole, the second jet hole, third jet hole, the 4th jet hole be 5~
10mm。
The present invention compared with the prior art, have the following advantages that and the utility model has the advantages that
(1) head primary zone of the present invention uses sudden expansion structure, passes through the position of each jet hole of reasonable Arrangement burner inner liner, size
And Jet Penetration Depth, so that the jet stream of third jet hole outflow is mutually connected with the jet stream that the second jet hole flows out, through the second jet stream
Hole outflow jet stream be mutually connected with the jet stream that the first jet hole flow out, and so on formed individually be relatively large in diameter and with centainly
The recirculating zone of intensity.Using the resident effect of recirculating zone, increase air-flow in the flame tube head region residence time, increases oil gas
Blending, burning time, improve combustion stability and efficiency of combustion；Burning sufficiently can also improve combustor exit profiling-quality,
Improve combustion chamber integrated performance index.
(2) outer wall of burner inner liner of the present invention and interior wall construction form are expansion type, in contrast burner inner liner primary zone space
Greatly, be conducive to improve the ignition performance of combustion chamber.
(3) the miniature standing vortex burning chamber of the present invention considers cooling structure, multiple rows of in flame drum outer wall and burner inner liner inner wall arrangement
Cooling hole carries out gaseous film control to burner inner liner wall surface, prevents part from stoichiometric ratio region occur, avoid to burner inner liner wall surface
Ablation, effectively reduce wall surface temperature and temperature gradient.The principle of trapped vortex combustion technology is applied to micro combustions by the present invention
On room, thinking is novel, structure type is simple, easy to process.
Detailed description of the invention
Fig. 1 is structure sectional view of the invention；
Fig. 2 is the structural schematic diagram of core component burner inner liner of the present invention；
Fig. 3 is the structural schematic diagram of flame drum outer wall；
Fig. 4 is the structural schematic diagram of burner inner liner antetheca；
The structural schematic diagram of Fig. 5 burner inner liner inner wall.
Wherein, title corresponding to the appended drawing reference in attached drawing are as follows:
1- burner inner liner antetheca, the first jet hole of 2-, 3- flame drum outer wall, the second jet hole of 4-, 5- third jet stream
Hole, the first cooling hole of 6-, 7- burner inner liner inner wall, the 4th jet hole of 8-, the second cooling hole of 9-, 10- have certain pressure
Air, 11- high-temperature fuel gas, 12- casing, 13- annular housing B, 14- burner inner liner airstream compartment A.
Specific embodiment
The present invention is described in further detail below with reference to embodiment:
Embodiment
As shown in fig. 1~fig. 5, a kind of standing vortex declines type gas turbine combustors, including burner inner liner and casing 12,
Burner inner liner includes flame drum outer wall 3, burner inner liner antetheca 1 and burner inner liner inner wall 7；Burner inner liner is fire close to 1 one end of burner inner liner antetheca
Flame cylinder head primary zone, flame tube head primary zone use sudden expansion structure, and flame tube head primary zone is standing vortex form structure.Fire
Flame drum outer wall 3 is sealedly and fixedly connected with burner inner liner antetheca 1, and burner inner liner inner wall 7 is located inside flame drum outer wall 3, burner inner liner inner wall 7
It is sealedly and fixedly connected with burner inner liner antetheca 1.Flame drum outer wall 3 and burner inner liner inner wall 7 of the invention is all made of variable cross-section design.Fire
Flame drum outer wall 3, burner inner liner antetheca 1 and the sealing of burner inner liner inner wall 7 form burner inner liner airstream compartment A14, flame drum outer wall 3 and flame
Cylinder inner wall 7 has airstream compartment A, also has airstream compartment B, burner inner liner airstream compartment A14 of the invention inside burner inner liner inner wall 7
Including airstream compartment A, airstream compartment B.Annular housing B13 is formed between burner inner liner and casing 12.Flame drum outer wall 3 is provided with several
A the second jet hole 4 for being used to be connected to burner inner liner airstream compartment A14 Yu annular housing B13, before flame drum outer wall 3 is far from burner inner liner
1 one end of wall is provided with the third jet hole 5 for being connected to burner inner liner airstream compartment A14 Yu annular housing B13.On burner inner liner antetheca 1
It is provided with the first jet hole 2 for being connected to burner inner liner airstream compartment A14 Yu annular housing B13.It is provided with and is used on burner inner liner inner wall 7
It is connected to the 4th jet hole 8 of burner inner liner airstream compartment A14 and annular housing B13, is provided on flame drum outer wall 3 for being connected to flame
First group of cooling hole 6 of cylinder airstream compartment A14 and annular housing B13, are provided with for being connected to burner inner liner air-flow on burner inner liner inner wall 7
Second group of cooling hole 9 of cavity A14 and annular housing B13.
Flame tube head primary zone of the present invention uses standing vortex form, is sudden expansion structure, and reasonably arrange four jet holes
Position, head air-flow forms stable recirculating zone in burner inner liner, and the resident effect of recirculating zone makes head air-flow in burner inner liner
The head zone residence time increases, and then increases fuel oil in the burning time of head zone, while the intensity of recirculating zone increases, head
The combustion stability in portion region is reinforced, and the igniting reliability and stability of combustion chamber improves.Recirculating zone intensity is obtained with range
To raising, the efficiency of combustion of the raising of residence time and burning time, head of combustion chamber region is improved, and high-temperature region is close to header area
Domain, Combustion outlet temperature distribution evenness is preferable, and the chamber performance of combustion chamber entirety is highly improved.
As shown in fig. 1~fig. 5, first group of cooling hole 6 is made of several cooling holes, and second group of cooling hole 9 is by several
Cooling hole is constituted；The cooling hole of first group of cooling hole 6, the cooling hole of second group of cooling hole 9 are oblique annulus hole, oblique annulus
The interior circular diameter in hole is 3~8mm, and the depth in hole is 0.5~1.5mm.In the cooling hole and flame drum outer wall 3 of first cooling hole 6
Mandrel line is at 20 °~45 ° angles, and the cooling hole and 7 central axis of burner inner liner inner wall of the second cooling hole 9 are at 20 °~45 ° angles.
As shown in fig. 1~fig. 5, the first jet hole 2 forms diversion edges to burner inner liner airstream compartment A14 direction flange, leads
Stream side height is 1~3mm；Second jet hole 4 forms diversion edges, water conservancy diversion to burner inner liner airstream compartment A14 direction flange
Side height is 1~3mm.Third jet hole 5 forms diversion edges, diversion edges height to burner inner liner airstream compartment A14 direction flange
For 1~3mm；4th jet hole 8 to burner inner liner airstream compartment A14 direction flange formed diversion edges, diversion edges height be 1~
3mm.First jet hole 2, the second jet hole 4, third jet hole 5, the 4th jet hole 8 bore dia be 5~10mm.
Working principle of the present invention is as follows:
As shown in fig. 1~fig. 5, enter in casing 12 with the air 10 of certain pressure from left side, be divided into two strands of air-flows, one
Stock air-flow flows through flame drum outer wall 3, from second jet hole 4 in 3 primary zone of flame drum outer wall, 3 sudden expansion position of flame drum outer wall
First group of cooling hole 6 of third jet hole 5 and flame drum outer wall 3 enters in burner inner liner；Another strand of air-flow flows through burner inner liner antetheca
1, second group from the first jet hole 2 of burner inner liner antetheca 1, the 4th jet hole 8 of burner inner liner inner wall 7 and flame drum outer wall 3 is cold
But hole 9 enters in burner inner liner.The jet direction of second jet hole 4 in 3 primary zone of flame drum outer wall is to 7 side of burner inner liner inner wall
To the jet direction of the third jet hole 5 of 3 sudden expansion position of flame drum outer wall is the first jet hole 2 of burner inner liner antetheca 1 to the left
Jet direction be that the right, the jet direction of the 4th jet hole 8 of burner inner liner inner wall 7 is to 3 wall direction of flame drum outer wall four
The convolution direction of the Gas Jet in a direction is reflux jet stream counterclockwise, powerful, and head zone is made to form stronger shear layer
With biggish adverse pressure gradient, thus central area formed reinforce recirculating zone.The strong inverse flow area at center can be such that air-flow is firing
Indoor residence time increase is burnt, and the periphery low speed region of recirculating zone increases, and is conducive to flame transmission, to make head
Regional stability burning, the high-temperature fuel gas 11 after burning are smoothly discharged.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all in essence of the invention
Made any modifications, equivalent replacements, and improvements etc., should all be included in the protection scope of the present invention within mind and principle.
Claims (6)
- The type gas turbine combustors 1. a kind of standing vortex declines, including burner inner liner and casing (12), it is characterised in that: described Burner inner liner includes flame drum outer wall (3), burner inner liner antetheca (1) and burner inner liner inner wall (7), the flame drum outer wall (3) and flame Cylinder antetheca (1) is sealedly and fixedly connected, and the burner inner liner inner wall (7) is located at flame drum outer wall (3) inside, the burner inner liner inner wall (7) it is sealedly and fixedly connected with burner inner liner antetheca (1)；The flame drum outer wall (3), burner inner liner antetheca (1) and burner inner liner inner wall (7) Sealing forms burner inner liner airstream compartment A(14), annular housing B(13 is formed between the burner inner liner and casing (12))；The fire Flame drum outer wall (3) is provided with several for being connected to burner inner liner airstream compartment A(14) the second jet hole with annular housing B(13) (4), the flame drum outer wall (3) is provided with far from burner inner liner antetheca (1) one end for being connected to burner inner liner airstream compartment A(14) and ring Shape cavity B(13) third jet hole (5)；It is provided on the burner inner liner antetheca (1) for being connected to burner inner liner airstream compartment A(14) With the first jet hole (2) of annular housing B(13)；It is provided on the burner inner liner inner wall (7) for being connected to burner inner liner airstream compartment A (14) it with the 4th jet hole (8) of annular housing B(13), is provided with for being connected to burner inner liner air-flow on the flame drum outer wall (3) Cavity A(14) first group of cooling hole (6) with annular housing B(13), it is provided with for being connected to flame on the burner inner liner inner wall (7) Cylinder airstream compartment A(14) with annular housing B(13) second group of cooling hole (9)；The burner inner liner is close to burner inner liner antetheca (1) one End is flame tube head primary zone, and the flame tube head primary zone uses sudden expansion structure, and the flame tube head primary zone is Standing vortex form structure；First group of cooling hole (6) is made of several cooling holes, and second group of cooling hole (9) is cold by several But hole is constituted；The cooling hole of first group of cooling hole (6), the cooling hole of second group of cooling hole (9) are oblique annulus hole, tiltedly circle The interior circular diameter of annular distance is 3~8mm, and the depth in hole is 0.5~1.5mm.
- The type gas turbine combustors 2. a kind of standing vortex described in accordance with the claim 1 declines, it is characterised in that: the fire Flame drum outer wall (3) and burner inner liner inner wall (7) are all made of variable cross-section design.
- The type gas turbine combustors 3. a kind of standing vortex described in accordance with the claim 1 declines, it is characterised in that: described The cooling hole and flame drum outer wall (3) central axis of one group of cooling hole (6) are at 20 °~45 ° angles, second group of cooling hole (9) cooling hole and burner inner liner inner wall (7) central axis is at 20 °~45 ° angles.
- The type gas turbine combustors 4. a kind of standing vortex described in accordance with the claim 1 declines, it is characterised in that: described One jet hole (2) forms diversion edges to burner inner liner airstream compartment A(14) direction flange, and diversion edges height is 1~3mm；It is described Second jet hole (4) forms diversion edges to burner inner liner airstream compartment A(14) direction flange, and diversion edges height is 1~3mm.
- 5. a kind of standing vortex declines type gas turbine combustors according to claim 4, it is characterised in that: described Three jet holes (5) form diversion edges to burner inner liner airstream compartment A(14) direction flange, and diversion edges height is 1~3mm；It is described 4th jet hole (8) forms diversion edges to burner inner liner airstream compartment A(14) direction flange, and diversion edges height is 1~3mm.
- 6. a kind of standing vortex declines type gas turbine combustors according to claim 5, it is characterised in that: described One jet hole (2), the second jet hole (4), third jet hole (5), the 4th jet hole (8) bore dia be 5~10mm.
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| CN201711097957.2A CN107906560B (en) | 2017-11-09 | 2017-11-09 | A kind of standing vortex declines type gas turbine combustors |
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|---|---|---|---|
| CN201711097957.2A CN107906560B (en) | 2017-11-09 | 2017-11-09 | A kind of standing vortex declines type gas turbine combustors |
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| CN107906560B true CN107906560B (en) | 2019-11-26 |
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| CN109737454A (en) * | 2019-01-02 | 2019-05-10 | 西北工业大学 | A kind of variable cross-section annular evaporation tube |
| CN111780161B (en) * | 2019-04-04 | 2022-03-25 | 中国航发湖南动力机械研究所 | Turbine engine combustion chamber |
| CN113237096B (en) * | 2021-04-28 | 2024-09-06 | 华电（北京）热电有限公司 | Combustion chamber structure with heat exchanger |
| CN114110657B (en) * | 2021-11-11 | 2022-11-08 | 中国航发贵阳发动机设计研究所 | Cooling structure for head of flame tube of combustion chamber of middle-thrust aircraft engine |
| CN114608032B (en) * | 2022-03-01 | 2023-04-07 | 中国航发四川燃气涡轮研究院 | Combustor with widened stability boundary |
| CN115405950B (en) * | 2022-07-19 | 2024-03-29 | 南京航空航天大学 | Novel combustion chamber with full-ring pneumatic backflow and unilateral air inlet concave cavity coupling |
| CN115751378B (en) * | 2022-11-10 | 2024-10-18 | 南昌航空大学 | Support plate flame stabilizer with trapezoidal ribs and triangular convex blocks |
| CN116136307A (en) * | 2023-03-27 | 2023-05-19 | 西北工业大学 | Combustion chamber evaporation tube structure with perforated rib and expansion variable-section outlet |
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| JP2015059695A (en) * | 2013-09-19 | 2015-03-30 | 三菱日立パワーシステムズ株式会社 | Gas turbine combustor, and gas turbine system |
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