CN104879782A - Novel asymmetric flame stabilizer - Google Patents
Novel asymmetric flame stabilizer Download PDFInfo
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- CN104879782A CN104879782A CN201510266400.1A CN201510266400A CN104879782A CN 104879782 A CN104879782 A CN 104879782A CN 201510266400 A CN201510266400 A CN 201510266400A CN 104879782 A CN104879782 A CN 104879782A
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- flameholder
- novel asymmetric
- flame stabilizer
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- combustion
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Abstract
The invention provides a novel asymmetric flame stabilizer which has low pressure losses and can significantly improve the combustion efficiency. The shape of the section of the novel asymmetric flame stabilizer is composed of a straight line and two curves and is similar to the geometrical shape of a low-speed wing. By using the novel asymmetric flame stabilizer with the geometrical section, the windward area of the flame stabilizer can be reduced, and pressure losses are effectively reduced. When the novel asymmetric flame stabilizer formed in a planimetry mode is used on a combustion gas turbine, the combustion efficiency can be effectively improved, and the energy utilization rate is improved; by reasonably arranging the position of the flame stabilizer on a ground gas turbine, energy is absorbed, vibration combustion can be avoided, and the working margin is improved.
Description
Technical field
The invention belongs to gas turbine field, be specifically related to a kind of Novel asymmetric flameholder and comprise ground gas turbine combustion chamber and the aeroengine thrust augmentation combustion chamber of this flameholder.
Background technology
If gas turbine is the imperial crown of modern industry circle, so combustion chamber is exactly a jewel on modern industry imperial crown, and the existence of combustion chamber is just made the chemical energy of fuel be heat energy just.For gas-turbine combustion chamber, flame stabilization is one of its most basic requirement.Require that combustion chamber is once after catching fire, and can make the propagation that flame remains stable under different operating conditions.Flameholding, refers to that combustion chamber will at suitable, wide as far as possible oil-gas ratio operated within range on the one hand; Refer in combustion on the other hand, under certain inlet air flow speed conditions, the primary condition of flame stabilization be met.Because thermal capacitance intensity is large, inlet air flow speed is high, brings larger difficulty to stabilizing the flame.Therefore, flameholder is provided with bar none.
Flameholder is generally bluff body barrier.Head-on incoming flow flows to bluff body trailing edge along bluff body surface, generation boundary-layer is separated, tail vortex is produced because of viscosity, form recirculating zone, in recirculating zone, some local velocity is equal to or less than turbulent-flame spread speed, so just possess the necessary requirement of flame stabilization, once there be the incendiary source that power is enough large, flammable mixed gas just can have been made to light.High-temperature combustion product returns to upstream by recirculating zone, forms the incendiary source of steady and continuous.Recirculating zone plays a part thermal storage device, with the form of turbulent flow heat transfer and heat exchange, is flammable mixed gas transmission heat and active material, makes flame be able to bamboo telegraph in a combustion chamber.
In the heavy duty gas turbine of ground, combustion zone is very large, therefore occur that some areas burning is insufficient unavoidably, the situation that efficiency of combustion is lower, this phenomenon especially appears at the part that ground combustion machine combustion chamber changeover portion is connected with burner inner liner, this zone gas speed is lower, but ignition temperature and efficiency of combustion are lower, the existence of this non symmetric flame stabilizer can address this problem well, stablizes the flame in this region, strengthen the blending of fuel and air, improve the efficiency of combustion in this region.The after-burner speed of incoming flow of the empty engine of aviation forces down greatly, always, stagnation temperature is high, and owing to having consumed the part of oxygen in air in main chamber, so oxygen content is low, these are all unfavorable to combustion chemistry reflection, solve the stability problems of after-burner, will flameholder be used.The application of this Novel asymmetric flameholder, for conventional flameholder, expands the stable operation range of combustion engine, improves efficiency of combustion, have good flame holding, can adapt to worse combustion conditions.
Summary of the invention
Technical problem to be solved by this invention proposes a kind of stable operation range, the Novel asymmetric flameholder that improves its efficiency of combustion, maintain smooth combustion that significantly can expand ground combustion machine and aeroengine thrust augmentation combustion chamber.Compared with prior art, advantage of the present invention is relative to other flameholders, and this flameholder can effectively stabilize the flame, under identical pitot loss, have higher efficiency of combustion, and its structure is simple; For ground combustion machine and aeroengine thrust augmentation combustion chamber, it can be made to burn more abundant, the utilization rate of fuel is higher.
Technical scheme
The object of the present invention is to provide a kind of Novel asymmetric flameholder.
The object of the present invention is achieved like this:
For improving the Novel asymmetric flameholder of chamber performance, it is characterized in that: its sectional view is made up of straight line and two curves, three its transverse surfaces of the end to end formation of line.
Above-mentioned Novel asymmetric flameholder, relation between its characteristic size is: the cross section straight length L1 of non symmetric flame stabilizer is 8 ~ 14 times of cross section straight line height H 1, the length L2 of the cross section curve 2 of non symmetric flame stabilizer is 1 ~ 2 times of its height H 2, and the length L3 of the cross section curve 3 of non symmetric flame stabilizer is 2 ~ 5 times of its height H 3.L1 and H1 is used for positioning linear 1; L2 and H2 is for locating circular arc 2, and this arc radius excursion is 2 ~ 3H2; L3 and H3 is for locating the vertex position of SPL, and the position of all the other several points can obtain at random under this SPL of guarantee only has the condition of an extreme vertex.
Above-mentioned Novel asymmetric flameholder, is characterized in that: the point of intersection of straight line 1 and circular arc 2 in addition circular sliding slopes, the radius R excursion of this fillet is 0 ~ 10mm.
Above-mentioned Novel asymmetric flameholder, its position relationship in ground combustion machine is: the distance H of this Novel asymmetric flameholder and burner inner liner chamber exit is 5 ~ 15mm, and the minimum distance L of non symmetric flame stabilizer and burner inner liner outer wall is 5 ~ 40mm.After position is determined, this non symmetric flame stabilizer to be rotated a circle around burner inner liner axis by above-mentioned plane geometry and is formed.
Above-mentioned Novel asymmetric flameholder, its position relationship in afterbunring indoor is: this Novel asymmetric flameholder is arranged on the cross section at 150mm ~ 350mm place after the center cone of aeroengine thrust augmentation combustion chamber.Determine with 1 ~ 3 this asymmetric annular flame stabilizer according to practical flow field, be connected on the Shockproof heat insulation screen of after-burner with radial connection flame groove between flameholder.
The maximum benefit of this Novel asymmetric flameholder is, employ the Cross section Design of similar low speed wing, upper surface camber is larger, lower surface camber is less, there is pressure reduction in that therefore goes up lower wall surface, mutually converges again at end, therefore causes the long bubble separation that similar thin wing is separated the inside, whirlpool is formed, i.e. recirculating zone after stabilizer.And stabilizer rear surface adopts single summit SPL to contribute to staying the formation in whirlpool, recirculating zone is stable at herein.Its application can reduce the pitot loss flowing through flameholder, improves the efficiency of combustion of gas turbine, and makes combustion engine can rapid fire, and reliability improves.
Accompanying drawing explanation
Fig. 1: the ground combustion machine burner inner liner having Novel asymmetric flameholder
Fig. 2: Novel asymmetric flameholder sectional view
Fig. 3: Novel asymmetric flameholder schematic cross-section
Fig. 4: Novel asymmetric flameholder cross section rounded corner schematic diagram
Fig. 5: the ground combustion machine burner inner liner sectional view having Novel asymmetric flameholder
Fig. 6: Novel asymmetric flameholder relative position schematic diagram
Fig. 7: the after-burner half sectional view having Novel asymmetric flameholder
Fig. 8: the after-burner left view having Novel asymmetric flameholder
1-Novel asymmetric flameholder cross section straight line 1 in figure; 2-Novel asymmetric flameholder cross-sectional curve 2; 3-Novel asymmetric flameholder cross section SPL 3; 4-Novel asymmetric flameholder; 5-burner inner liner inner chamber; 6-burner inner liner outer wall; 7-after-burner center cone; 8-joins flame groove; 9-New Ring-like Type non symmetric flame stabilizer; 10-after-burner Shockproof heat insulation shields.
Detailed description of the invention
Now the invention will be further described by reference to the accompanying drawings:
Composition graphs 2, Fig. 3, Fig. 4, the invention provides a kind of Novel asymmetric flameholder structure.Fig. 3 is the schematic cross-section of this Novel asymmetric flameholder, is used for illustrating the position constraint relation of this cross section profile; Fig. 4 is this Novel asymmetric flameholder schematic cross-section of band rounded corner, for showing fillet position and the size of this Novel asymmetric flameholder windward side; Novel asymmetric flameholder to rotate a circle formation around burner inner liner central shaft for figure shown in Fig. 3 or 4; Fig. 2 is the sectional view of this Novel asymmetric flameholder.Fig. 1, Fig. 5 are used for the position relationship of this Novel asymmetric flameholder in ground combustion machine burner inner liner is described.Fig. 1 is the ground combustion machine burner inner liner schematic diagram that this Novel asymmetric flameholder is housed; Fig. 5, Fig. 6 are the burner inner liner sectional view for this Novel asymmetric flameholder and burner inner liner position relationship are described.Fig. 7, Fig. 8 are after-burner half sectional view for this Novel asymmetric flameholder and aeroengine thrust augmentation combustion chamber position relationship are described and left view.
Conventional flameholder structure is simple, and use experience is enriched, as long as reasonable employment just can meet job requirement, but its pitot loss is comparatively large, and this novel flame stabilizer uses the Cross section Design of similar low speed wing, and upper surface camber is larger, lower surface camber is less, and the benefit of design is like this
Front stationary point is positioned at stabilizer front end, and the streamline flowing through stationary point is divided into two parts, a part from stationary point, walk around leading edge point through stabilizer upper wall surface along wall diffluence, another part from stationary point through stabilizer lower wall surface along wall diffluence.At upper wall surface place, because wall angle changes greatly, this place's fluid particle speed is accelerated quickly; At lower wall surface place, wall angle change is less, and this place's fluid particle accelerates slowly.According to Bernoulli equation, pressure distribution is that maximal rate point place pressure is minimum.There is pressure reduction in that therefore goes up lower wall surface, mutually converges again at end, therefore causes the long bubble separation that similar thin wing is separated the inside, form whirlpool, i.e. recirculating zone after stabilizer.And stabilizer rear surface adopts single summit SPL to contribute to staying the formation in whirlpool, recirculating zone is stable at herein.The summit of this SPL and curve form are determined by the distribution of velocity field after analyzing gas turbine flameholder.
Analyze from operation principle, this Novel asymmetric flameholder has following advantages:
(1) this Novel asymmetric flameholder head have employed the design of similar wing, relative Novel asymmetric flameholder upper surface, lower surface height is less, therefore relatively carrys out flow path direction, cross-sectional area is less, because this reducing the pitot loss flowing through flameholder.
(2) backflow formed enhances the exchange with the heat of main flow, momentum, quality, adds the time of staying of main flow on border, recirculating zone simultaneously, therefore improves the efficiency of combustion of gas turbine.
(3) in stabilizer, again set up point of safes burning things which may cause a fire disaster, be subject to the protection of stabilizer wall, directly acceptor drains off the impact of disturbing, and this pilot flame is very fast to main flow diffusion, and therefore make combustion engine light a fire rapidly, reliability improves.
The low-frequency oscillation burning of combustion chamber is often fluctuated by the combustion process in combustion chamber and internal system acoustic pressure and is intercoupled and the self-oscillation that produces.If do not suppressed acoustic pressure pulsation, then rough burning can be caused, this is very dangerous concerning ground gas turbine, install flameholder additional after burner inner liner inner chamber after, owing to having certain radial distance between flameholder and burner inner liner outer wall, between flameholder and burner inner liner outer wall, the existence of annular flow field can the absorption pressure oscillation energy of pulsing, and can suppress the generation of hugging to a certain extent, improve the margin of operation of ground combustion machine.
Ground combustion machine burner inner liner chamber exit place temperature is lower, burn very insufficient, and herein relative to burner inner liner inner chamber, oxygen and fuel concentration are all lower, be not easy tissue stabilization burning, flameholder is placed in the efficiency of combustion that this place can improve ground combustion machine significantly, makes burning more fully and more stable.This flameholder is used for after-burner, flame can be made more stable, burning is more easily organized, and improves efficiency of combustion.
Claims (5)
1. a Novel asymmetric flameholder, is characterized in that: its sectional view is made up of straight line and two curves, three its transverse surfaces of the end to end formation of line.
2. a kind of Novel asymmetric flameholder according to claim 1, it is characterized in that: the relation between its characteristic size is for the cross section straight length L1 of non symmetric flame stabilizer is 8 ~ 14 times of cross section straight line height H 1, the length L2 of the cross section curve 2 of non symmetric flame stabilizer is 1 ~ 2 times of its height H 2, and the length L3 of the cross section curve 3 of non symmetric flame stabilizer is 2 ~ 5 times of its height H 3.L1 and H1 is used for positioning linear 1; L2 and H2 is for locating circular arc 2, and this arc radius excursion is 2 ~ 3H2; L3 and H3 is for locating the vertex position of SPL, and the position of all the other several points can obtain at random under this SPL of guarantee only has the condition of an extreme vertex.
3. a kind of Novel asymmetric flameholder according to claim 1 and 2, is characterized in that: the point of intersection of straight line 1 and circular arc 2 in addition circular sliding slopes, the radius R excursion of this fillet is 0 ~ 10mm.
4. a kind of Novel asymmetric flameholder according to claim 1 or 2 or 3, it is characterized in that: when it is positioned at ground combustion machine combustion chamber, the distance H of this Novel asymmetric flameholder and burner inner liner chamber exit is 5 ~ 15mm, and the minimum distance L of non symmetric flame stabilizer and burner inner liner outer wall is 5 ~ 40mm.After position is determined, this non symmetric flame stabilizer to be rotated a circle around burner inner liner axis by above-mentioned plane geometry and is formed.
5. a kind of Novel asymmetric flameholder according to claim 1 or 2 or 3, it is characterized in that: when it is positioned at aeroengine thrust augmentation combustion chamber, this Novel asymmetric flameholder is arranged on the cross section at 150mm ~ 350mm place after the center cone of aeroengine thrust augmentation combustion chamber.Determine with 1 ~ 3 this asymmetric annular flame stabilizer according to practical flow field, be connected on the Shockproof heat insulation screen of after-burner with radial connection flame groove between flameholder.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510266400.1A CN104879782A (en) | 2015-05-18 | 2015-05-18 | Novel asymmetric flame stabilizer |
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| CN201510266400.1A CN104879782A (en) | 2015-05-18 | 2015-05-18 | Novel asymmetric flame stabilizer |
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| CN104879782A true CN104879782A (en) | 2015-09-02 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105841191A (en) * | 2016-03-30 | 2016-08-10 | 中国科学院工程热物理研究所 | Tail edge structure of V-shaped flame stabilizer |
Citations (7)
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| CN1031890A (en) * | 1985-12-26 | 1989-03-22 | 北京航空学院 | Dune-shaped stationary-eddy flameholder |
| US5095696A (en) * | 1990-01-02 | 1992-03-17 | General Electric Company | Asymmetric flameholder for gas turbine engine afterburner |
| CN1211310A (en) * | 1995-11-07 | 1999-03-17 | 西屋电气公司 | Gas turbing combustor with enhanced mixing fuel injectors |
| CN2791488Y (en) * | 2005-02-03 | 2006-06-28 | 李淑琴 | Blast furnace and converter gas flame stabilizer |
| CN101514815A (en) * | 2008-02-21 | 2009-08-26 | 通用电气公司 | Gas turbine combustor flame stabilizer |
| EP2472090A2 (en) * | 2010-12-30 | 2012-07-04 | Rolls-Royce North American Technologies, Inc. | A gas engine turbine comprising a thrust augmentation system |
| CN102748775A (en) * | 2012-07-23 | 2012-10-24 | 集美大学 | Streamline flame stabilizer with built-in ignition sources |
-
2015
- 2015-05-18 CN CN201510266400.1A patent/CN104879782A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1031890A (en) * | 1985-12-26 | 1989-03-22 | 北京航空学院 | Dune-shaped stationary-eddy flameholder |
| US5095696A (en) * | 1990-01-02 | 1992-03-17 | General Electric Company | Asymmetric flameholder for gas turbine engine afterburner |
| CN1211310A (en) * | 1995-11-07 | 1999-03-17 | 西屋电气公司 | Gas turbing combustor with enhanced mixing fuel injectors |
| CN2791488Y (en) * | 2005-02-03 | 2006-06-28 | 李淑琴 | Blast furnace and converter gas flame stabilizer |
| CN101514815A (en) * | 2008-02-21 | 2009-08-26 | 通用电气公司 | Gas turbine combustor flame stabilizer |
| EP2472090A2 (en) * | 2010-12-30 | 2012-07-04 | Rolls-Royce North American Technologies, Inc. | A gas engine turbine comprising a thrust augmentation system |
| EP2472090A3 (en) * | 2010-12-30 | 2014-03-05 | Rolls-Royce North American Technologies, Inc. | A gas engine turbine comprising a thrust augmentation system |
| CN102748775A (en) * | 2012-07-23 | 2012-10-24 | 集美大学 | Streamline flame stabilizer with built-in ignition sources |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105841191A (en) * | 2016-03-30 | 2016-08-10 | 中国科学院工程热物理研究所 | Tail edge structure of V-shaped flame stabilizer |
| CN105841191B (en) * | 2016-03-30 | 2018-07-06 | 中国科学院工程热物理研究所 | A kind of V-flame stabilizer trailing edge structures |
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Application publication date: 20150902 |