CN101737802A - Central cavity stable fire tangential combustion chamber - Google Patents
Central cavity stable fire tangential combustion chamber Download PDFInfo
- Publication number
- CN101737802A CN101737802A CN 200910241247 CN200910241247A CN101737802A CN 101737802 A CN101737802 A CN 101737802A CN 200910241247 CN200910241247 CN 200910241247 CN 200910241247 A CN200910241247 A CN 200910241247A CN 101737802 A CN101737802 A CN 101737802A
- Authority
- CN
- China
- Prior art keywords
- tangential
- bluff body
- combustion
- outer shroud
- ring
- 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.)
- Granted
Links
Images
Abstract
The invention discloses a central cavity stable fire tangential combustion chamber, which consists of a shunting type diffuser, a combustion chamber external cartridge receiver, a central cavity rear step pre-combustion stage, an outer ring blunt body flame stabilizer main combustion stage, an inner ring blunt body flame stabilizer main combustion stage, a fuel supply system, an inner flame tube, an outer flame tube and an outlet supporting plate. An air flow with a deflection angle is diffused into the combustion chamber by the shunting type diffuser; the central cavity pre-combustion stage consists of a rear step, a top plate, a nozzle, a tangential slot inner ring and a tangential slot outer ring, and in the pre-combustion stage, the flame is stabilized by a low-speed recirculation zone generated by the rear step; the inner ring and the outer ring blunt body flame stabilizer main combustion stages consist of the inner ring, the outer ring and blunt body stabilizers with deflection angles, the high temperature and high pressure fuel jetted out of the inner ring and outer ring blunt body flame stabilizers is mixed with air, is ignited by the pre-combustion stage, and is burnt stably in a low-speed zone after a blunt body; and the outlet supporting plate is arranged between the inner flame tube and the outer flame tube and has an included angle with the axial line of the combustion chamber, and the outlet gas of the combustion chamber has an deflection angle. The central cavity stable fire tangential combustion chamber realizes tangential flow and tangential combustion while ensuring stable combustion for providing power; besides, the structure is simplified, and the weight of the combustion chamber is reduced.
Description
Technical field
The present invention is the gas-turbine combustion chamber of a kind of tangential admission, burning, exhaust, guaranteeing tangentially to flow, in the burning, making combustion chamber and even whole gas turbine contraction in length, and compact conformation, weight reduces.
Background technology
The key property of modern gas turbines combustion chamber and structure distribution have reached quite high level, but for the modern gas turbines combustion chamber, still have some difficult problems and challenge, the development and application of new material, new technology, new construction, new ideas is only and guarantees that it continues progressive source.
Its burning organizational form of conventional gas-turbine combustion chamber is to utilize the local low speed recirculating zone in primary zone to form the smooth combustion of continuity point burning things which may cause a fire disaster on the main basis of flowing vertically of air-flow, and adopt suitable fuel system atomized fuel, the air share split enters burner inner liner can guarantee the primary zone near appropriate oil-gas ratio, thereby guarantees the stability and high efficiency burning.This shows, it mainly is to make up on the basis of axial flow that burning in the conventional combustion chamber is organized, in order to obtain flow losses characteristic preferably, require it to import and export air-flow and all flow vertically, so the guide vane parts that for conventional combustion chamber, are absolutely necessary.
Traditional gas turbine, generally the turbine expansion system by annular compression system, combustion system and annular constitutes.The compressed system of air enters the combustion chamber and mixes the burning of formation gas mixture with fuel oil, and then enters the circular passage of turbine.Air is before entering the combustion chamber, compressed system is the compressor compression, under the effect of compressor rotor and stator, air in compressor with the gyration of certain tangential velocity, about 30 ° to 55 ° with respect to the axis of gas turbine of its air-flow angles, the size of this air-flow angle and the rotating speed of whole gas turbine have much relations.Compressed air is when entering the combustion chamber, and the blower outlet straightener(stator) blade can become straight with its rectification, and compressed air is 0 ° with respect to the angle of gas turbine axis, (being parallel and longitudinal axis gas turbine).Compressed air in the combustion chamber, mix with fuel oil form mixture burns after, combustion gas is still flowed along the gas turbine axis direction, then enters turbine.Before entering turbine, combustion gas changes flow direction under the effect of nozzle ring, forms the gyration that has certain tangential velocity once more, and general air-flow angle is about 70 ° with respect to the axis of gas turbine.
The fluid deflection degree will certainly form certain angle of attack, and this angle of attack is that to provide mechanical force to rotor blade needed so that give rotary driving force to turbine section first order rotor.But the distribution of this air-flow angle also be gas turbine especially the combustion chamber band many problems and defective.The air of blower outlet has certain angle, in 30 ° to 55 ° scopes, air constantly by rectification (angle is got back to 0 °), then enters into the combustion chamber and participates in burning before entering the combustion chamber, change direction when entering turbine afterwards once more, about 70 ° of the angle of formation.The continuous change at the mobile inclination angle of the air of this gas turbine of flowing through requires blower outlet straightener(stator) blade and turbine inlet guiding to produce powerful aerodynamic force, and this pneumatic side is harmful especially to the gas turbine overall efficiency.
In addition, the pressure that reduces under the pressure of the size and the weight of aero-gas turbine, the length of conventional combustion chamber also shortens thereupon greatly, and the atomizing of fuel oil, evaporation, blending and burning are all carried out vertically, and too short combustion chamber length will certainly have influence on efficiency of combustion and outlet temperature distributes.And the axial burning organizational form in the conventional combustion chamber well is not used the tangential momentum of blower outlet air-flow, and this will need in technology of advanced combustion chamber to consider in future.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the deficiencies in the prior art, a kind of center cavity stable fire tangential combustion chamber is provided, guarantee the smooth combustion of burning under tangential condition, the coupling of connection flame and pre-combustion grade and main combustion stage, to realize cramped construction, simplified structure reduces the purpose of combustion chamber and even whole gas turbine length and weight.
Technical solution of the present invention: the center cavity stable fire tangential combustion chamber is characterized in that: be made of casing (11), center cavity backward step pre-combustion grade (44), outer shroud bluff body flameholder main combustion stage (50), interior ring bluff body flameholder main combustion stage (51), fuel oil supply system (48), interior burner inner liner (20), outer burner inner liner (19) and outlet support plate (21) in shunting diffuser (10), outer combustion case (12), the combustion chamber; Described center cavity backward step pre-combustion grade (44) is by top board (24), backward step (16), nozzle (15), ring (17) and tangential slot outer shroud (14) constitute in the tangential slot, top board (24) is connected along the place circumference with backward step (16), nozzle (15) is placed on the radial end face of backward step (16), what ring (17) and tangential slot outer shroud (14) were placed in backward step (16) and top board (24) respectively in the tangential slot is the inside circumference and the outside of axle with the engine axis, ring (17) in the tangential slot, tangential slot outer shroud (14), backward step (16) and top board (24) four form the circumferential pre-combustion grade cavity (30) that section is semiclosed rectangle, air enters pre-combustion grade cavity (30) through tangential slot inner and outer ring tangential admission groove (25) and tangentially flows the low speed recirculating zone retention flame that utilizes backward step (16) to produce; Described outer shroud bluff body flameholder main combustion stage (50) and interior ring bluff body flameholder main combustion stage (51) are formed main combustion stage jointly, outer shroud bluff body flameholder main combustion stage (50) and interior ring bluff body flameholder main combustion stage (51) are made up of outer shroud bluff body flameholder (13) and interior ring bluff body flameholder (18) respectively, outer shroud bluff body flameholder main combustion stage (50) is identical with both structures of interior ring bluff body flameholder main combustion stage (51), outer shroud bluff body flameholder (13) is placed between the outer side surface and outer burner inner liner (20) internal face of tangential slot outer shroud (14), the leading edge of outer shroud bluff body flameholder (13) flushes with the leading edge of tangential slot outer shroud (14), interior ring bluff body flameholder (18) is placed between the interior sidewall surface and interior burner inner liner (19) outside wall surface of ring (17) in the tangential slot, in the leading edge of ring bluff body flameholder (18) flush with the leading edge of tangential slot outer shroud (17), during the installation of outer shroud bluff body flameholder (13) and interior ring bluff body flameholder (18) and engine axis deflection angle is arranged; Fuel oil supply system (48) is by nozzle mount pad (45), liquid fuel pipe (46) and HTHP fuel pipe (47) constitute, fuel oil supply system (48) links to each other with outer combustion case (12) by nozzle mount pad (45), the liquid fuel pipe is supplied with liquid fuel to nozzle (15), HTHP fuel pipe (47) is supplied with the HTHP fuel oil, be connected with top board (24), through top board (24), backward step (16), the HTHP oil supplying hole (52) of ring (14) is supplied with the HTHP fuel oil in tangential slot outer shroud (17) and the tangential slot in outer shroud bluff body flameholder (13) and interior ring bluff body flameholder (18), the main combustion stage HTHP fuel oil (34) that ejects in outer shroud bluff body flameholder (13) and the interior ring bluff body flameholder (18) mixes with air by center cavity backward step pre-combustion grade (44) and ignites, and the low regime smooth combustion behind bluff body; Described outlet support plate (21) is placed in the exit of interior burner inner liner (20) and outer burner inner liner (19), and outlet support plate (21) has angle with the combustion chamber axis, and burning after-burner outlet combustion gas has deflection angle.
The air distribution of described center cavity backward step pre-combustion grade (44) accounts for 5%～20% of whole burning tolerance, and the air distribution of outer shroud bluff body flameholder main combustion stage (50) and interior ring bluff body flameholder main combustion stage (51) accounts for 60%～90% of whole burning tolerance; Whole combustion chamber has 12～18 pre-combustion grade, 20 °～30 ° of single pre-combustion grade cycle segment angles.
Described shunting diffuser (10) is divided into three strands of air-flows by two splitters with air-flow, be central gas stream (2), outer shroud air-flow (54) and interior ring air-flow (55), make air-flow be uniformly scattered onto head of combustion chamber, three strands of exit flows of shunting diffuser (10) are upwards turned back.
Ring (17) and tangential slot outer shroud (14) have tangential slot inner and outer ring tangential admission groove (25) in the tangential slot of described center cavity backward step pre-combustion grade (44), tangential slot inner and outer ring tangential admission groove (25) and 15 °～30 ° of tangent to periphery angles, tangential slot inner and outer ring tangential slot width (38) is 1.0mm～1.5mm, tangential slot inner and outer ring tangential gas flow (4) enters the inner pre-combustion grade cavity (30) of center cavity backward step pre-combustion grade (44) through tangential slot inner and outer ring tangential admission groove (25) and forms tangential gas flow, tangential slot outer shroud (14) flow accounts for 20%～50% of center cavity backward step pre-combustion grade (44), and ring (17) flow accounts for 20%～50% of center cavity backward step pre-combustion grade (44) in the tangential slot.
The top board (24) of described center cavity backward step pre-combustion grade (44) has a plurality of top board tangential admissions holes (26) opposite with the tangential flow direction of the interior air-flow of pre-combustion grade cavity (30), top board tangential admission hole (26) and 15 °～30 ° of engine axis angles, top board tangential hole diameter (41) is 0.5mm～1.0mm, number of aperture 65～135, gas inlet hole strengthens the interior recirculating zone (32) of pre-combustion grade cavity behind the backward step (16), and flow is 10%～50% of center cavity backward step pre-combustion grade (a 44) flow.
The nozzle (15) of described center cavity backward step pre-combustion grade (44) is placed on backward step (16) radial end face, with place axial cross section angle be 5 °～60 °.
Ring (14) all has HTHP oil supplying hole (52), aperture 0.4mm～1mm in the top board (24) of described center cavity backward step pre-combustion grade (44), backward step (16), tangential slot outer shroud (17), the tangential slot; HTHP fuel pipe (47) is connected with backward step (16), and the HTHP oil supplying hole (52) of ring (14) is interconnected in backward step (16), top board (24), tangential slot outer shroud (17) and the tangential slot; Fuel oil supply system (48) is supplied with HTHP fuel oil (53) in the stabilizer through HTHP oil supplying hole (52) in outer shroud bluff body flameholder (13) and interior ring bluff body flameholder (18).
When described outer shroud bluff body flameholder (13) and interior ring bluff body flameholder (18) are installed and the deflection angle of engine axis be 10 °～60.
Described outer shroud bluff body flameholder (13) and interior ring bluff body flameholder (18) are hollow-core construction, outer shroud bluff body flameholder (13) and interior ring bluff body flameholder (18) wall are radially opened a plurality of bluff body flameholder of single row or multiple rows fuel jet (27), the aperture of described bluff body flameholder fuel jet (27) is 0.5mm～1mm, from the outwards ejection of outer shroud bluff body flameholder (13) and interior ring bluff body flameholder (18), perforate is chosen in 10%～20% the position that accounts for passage length apart from channel outlet to main combustion stage HTHP fuel oil (34) through bluff body flameholder fuel jet (27).
The interior burner inner liner (11) of described combustion chamber and the type of cooling of outer burner inner liner (12) adopt the air film cooling, disperse the cooling or the compound type of cooling, wall surface temperature is controlled the life-span that prolongs burner inner liner.
Described combustor exit support plate (21) is 5 °～70 ° with the angle of combustion chamber axis; Described outlet support plate (21) number is 24～48.
Principle of the present invention: center cavity stable fire tangential combustion chamber of the present invention is to be made of casing, center cavity backward step pre-combustion grade, outer shroud bluff body flameholder main combustion stage, interior ring bluff body flameholder main combustion stage, fuel oil supply system, interior burner inner liner, outer burner inner liner and outlet support plate in shunting diffuser, outer combustion case, the combustion chamber.The air-flow at belt deflector angle enters inside, combustion chamber through shunting diffuser diffusion; Described center cavity pre-combustion grade is made of ring and tangential slot outer shroud in backward step, top board, nozzle, the tangential slot, the low speed recirculating zone retention flame that utilizes backward step to produce in the pre-combustion grade; Described inner and outer rings bluff body flameholder main combustion stage is made of the bluff body stabilizer of inside and outside two endless belt deflection angles, the HTHP fuel oil that ejects in the inner and outer rings bluff body flameholder mixes with air by center cavity backward step pre-combustion grade to be lighted, and the low regime smooth combustion behind bluff body; Between the outlet of burner inner liner and outer burner inner liner, with the combustion chamber axis angle is arranged in described outlet support plate is installed in, the combustor exit combustion gas has deflection angle.Flow in the tangential of air-flow that utilization of the present invention enters center cavity backward step pre-combustion grade cavity, under the effect of backward step circumferentially forming a plurality of recirculating zones, in order to produce a plurality of stable burning things which may cause a fire disaster that makes progress in week.Fuel-air mixture after the inner and outer rings of igniting the again bluff body stabilizer main combustion stage, smooth combustion in the low regime behind bluff body.Tangential flow of utilization in the combustion chamber increases the residence time of air-flow in the combustion chamber, thereby can shorten combustion chamber length.Adopt tangential inlet and outlet can save compressor afterbody stator and turbine inlet guiding, and cancelled the head design of traditional combustion chamber, simplified the structure of inside, combustion chamber, make whole gas turbine structure compactness simultaneously, contraction in length, weight reduces.
The present invention's advantage compared with prior art is as follows:
(1) the present invention utilizes the backward step pre-combustion grade of the steady fire of center cavity, and inner and outer ring bluff body flameholder main combustion stage, adopt comparatively simple version, realized tangential flowing, tangential firing is under less combustion chamber length, realize the residence time of longer burning indoor air flow, make the gas turbine structure compactness, length reduces, and weight reduces;
(2) adopt the backward step pre-combustion grade of the steady fire of center cavity, cancelled the head design of gas-turbine combustion chamber eddy flow cup air inlet commonly used, when reaching identical flame holding, simplified the structure of combustion chamber;
(3) bluff body flameholder main combustion stage, perforate is sprayed on the single stabilizer, and the fuel that adapts to the different pressures temperature sprays, and multi-point injection has improved outlet temperature circumferentially distribution and radial distribution;
(4) burner inner liner does not adopt the blending hole design, has simplified the burner inner liner structure.
Description of drawings
Fig. 1 is the work schematic diagram of the present invention on gas turbine;
Fig. 2 is a structural representation of the present invention;
Fig. 3 is a combustion chamber internal structure schematic diagram
Fig. 4 is a pre-combustion grade internal structure top view;
Fig. 5 is the inside and outside tangential slot schematic diagram of pre-combustion grade
Fig. 6 is that pre-combustion grade top board master looks schematic diagram;
Fig. 7 is a pre-combustion grade top board schematic top plan view;
Fig. 8 is a bluff body flameholder schematic diagram;
Fig. 9 is a main combustion stage flameholder access diagram;
Figure 10 is an outlet support plate schematic diagram;
Figure 11 is a pre-combustion grade main combustion stage domain schematic diagram.
Among the figure: 1. combustion chamber inlet air flow, 2. central gas stream, 3. bluff body flameholder main combustion stage air-flow, 4. tangential slot inner and outer ring tangential gas flow, 5. pre-combustion grade fuel injected, 6. bluff body flameholder main combustion stage combustion zone, 7. center cavity backward step pre-combustion grade combustion zone, 8. burner inner liner internal gas flow, 9. combustor exit air-flow, 10. shunting diffuser, 11. casing in the combustion chamber, 12. outer combustion case, 13. outer shroud bluff body flameholders, 14. tangential slot outer shrouds, 15. nozzle, 16. ring in the backward step, 17. tangential slots, 18. interior ring bluff body flameholders, 19. outer burner inner liner, 20. interior burner inner liner, 21 outlet support plates, 22. combustor exits, 23. combustion chamber import, 24. top board, 25. tangential slot inner and outer ring tangential admission grooves, 26. top board tangential admission holes, 27. bluff body flameholder fuel jet, 30. circumferential air-flow in the pre-combustion grade cavity, 31. pre-combustion grade cavitys, recirculating zone in the 32. pre-combustion grade cavitys, 33. top board tangential admission, 34. main combustion stage HTHP fuel oil, 44. center cavity backward step pre-combustion grade, 45. nozzle mount pads, 46. liquid fuel pipe, 47. the HTHP fuel pipe, 48. fuel oil supply systems, 49. burner inner liners cooling hole, 50. outer shroud bluff body flameholder main combustion stage, ring bluff body flameholder main combustion stage in 51, HTHP fuel oil in the 52. HTHP oil supplying holes, 53. bluff body stabilizers, 54. outer shroud air-flow, 55. interior ring air-flow, 56. bluff body flameholder pressure faces, 57. bluff body flameholder suction surfaces.
Structure in the corresponding diagram, relate to following critical size: the single cycle segment angle of 28. center cavity pre-combustion grade, 29. bluff body flameholder established angles, 35. backward step height, 36. top board circumferential lengths, 37. the tangential angle of tangential slot inner and outer ring, 38. tangential slot inner and outer ring tangential slot width, 39 tangential slot inner and outer ring tangential slot cycle angles, 40. top board tangential hole angle, 41. top board tangential hole diameter, 42. bluff body flameholder exit widths, 43. bluff body flameholders outlet axial length.
The specific embodiment
As shown in Figure 1, 2, 3, combustion chamber of the present invention is made of casing 11, center cavity backward step pre-combustion grade 44, outer shroud bluff body flameholder main combustion stage 50, interior ring bluff body flameholder main combustion stage 51, fuel oil supply system 48, interior burner inner liner 19, outer burner inner liner 20 and outlet support plate 21 in shunting diffuser 10, outer combustion case 12, the combustion chamber.
The notion of fractional combustion is adopted in the combustion chamber of the present invention's design, and burning usefulness gas is all from center cavity backward step pre-combustion grade 44, and outer shroud bluff body flameholder main combustion stage 50 and interior ring bluff body flameholder main combustion stage 51 infeed, and do not adopt traditional blending hole.Center cavity backward step pre-combustion grade 44 adopts center cavity backward step loop configuration, utilize the stable diffusion flame burning organizational form in backward step recirculating zone, the low regime tissue burnt after main combustion stage HTHP fuel oil and air half premix utilized inside loop and outside loop bluff body flameholder, and cold gas is infeeded by burner inner liner.
This combustion chamber comprises two combustion zones---center cavity backward step pre-combustion grade combustion zone 7 and bluff body flameholder main combustion stage combustion zone 6, the external boundary of center cavity backward step pre-combustion grade combustion zone 7 is tangential slot outer shrouds 14, inner boundary is a ring 17 in the tangential slot, the external boundary of bluff body flameholder main combustion stage combustion zone 6 is outer burner inner liners 12, inner boundary is interior burner inner liner 11, and center cavity backward step pre-combustion grade combustion zone 7 extends back and intersect bluff body flameholder main combustion stage combustion zone 6 along the combustion chamber axis.Center cavity backward step pre-combustion grade 44 is between outer shroud bluff body flameholder main combustion stage 50 and interior ring bluff body flameholder main combustion stage 51, outer shroud bluff body flameholder main combustion stage 50 and interior ring bluff body flameholder main combustion stage 51 again outside between burner inner liner 19 and the interior burner inner liner 20, the combustion chamber outermost and the most inboard be casing 11 in outer combustion case 12 and the combustion chamber.Outer burner inner liner 19 and interior burner inner liner 20 also arrange to have cooling, the type of cooling can adopt the air film cooling, disperse the cooling or the compound type of cooling, are used to cool off the burner inner liner wall, guarantee the life-span of combustion chamber.In specific embodiments, the outer burner inner liner 19 and interior burner inner liner 20 types of cooling adopt disperses cooling, and burner inner liner 19 and interior burner inner liner 20 have diffusion cooling hole 49 outside, and diffusion cooling hole 49 signals as shown in Figure 1.
Center cavity backward step pre-combustion grade 44 comprises nozzle 15, top board 24, ring 17 in the backward step 16, tangential slot outer shroud 14 and tangential slot; Top board 24 is connected along the place circumference with backward step 16, can adopt welding or pass through the machining global formation, nozzle 15 directly is inserted in the tangential hole of radial end face of backward step 16, what ring 17 and tangential slot outer shroud 14 were placed in backward step 16 and top board 24 respectively in the tangential slot is the inside circumference and the outside of axle with the engine axis, can adopt welding or bolt to connect, four form the circumferential pre-combustion grade cavity 30 that section is semiclosed rectangle.
Outer shroud bluff body flameholder main combustion stage 50 and interior ring bluff body flameholder main combustion stage 51 constitute main combustion stage, outer shroud bluff body flameholder 13 connects by welding or bolt and is connected with the outer side surface of tangential slot outer shroud 14, be connected with outer burner inner liner 20 internal faces by the bolt connection again, guarantee that the leading edge of outer shroud bluff body flameholder 13 flushes with the leading edge of tangential slot outer shroud 14; Interior ring bluff body flameholder 18 connects with the interior sidewall surface of the interior ring 17 of tangential slot by welding or bolt and is connected, connect by bolt again and be connected with interior burner inner liner 19 outside wall surface, the leading edge of ring bluff body flameholder 18 flushes with the leading edge of tangential slot outer shroud 17 in guaranteeing, outer shroud bluff body flameholder 13 and interior ring bluff body flameholder 18 guarantee that its mean camber line and engine axis have deflection angle when installing.
Earlier with center cavity backward step pre-combustion grade 44 and outer shroud bluff body flameholder main combustion stage 50 and 51 integral installations of interior ring bluff body flameholder main combustion stage, push then in the burner inner liner and pass through bolting during installation with flame tube wall.Outlet support plate 21 and outer burner inner liner 19 and interior burner inner liner 20 are connected by bolt, guarantee that its mean camber line and engine axis have deflection angle.Fuel oil supply system 49 is done as a whole, stretch into the combustion chamber from the opening part of outer combustion case 12, by being threaded, HTHP fuel pipe 47 is connected with top board 24 by being threaded, thereby finishes the installation of combustion chamber with liquid fuel pipe 46 and nozzle 15.
In the gas turbine blower outlet, air-flow generally is with certain deflection angle, and the angle of typical gas turbine blower exit flow speed and engine axis is 30 °～55 °.Combustion chamber inlet air flow 1 enters the combustion chamber with certain tangential velocity, is divided into three strands through shunting diffuser air-flow, i.e. central gas stream 2, outer shroud air-flow 54 and interior ring air-flow 53.Two moment of momentum such as splitter employing design blade profiles of shunting diffuser 10 guarantee the diffusion deceleration and air-flow are separated.Air-flow part behind the diffusion enters pre-combustion grade cavity 30 through the tangential slot inner and outer ring tangential admission groove 25 on ring 14 and the tangential slot outer shroud 17 in the tangential slot, forms circumferential flow 31 in the stronger pre-combustion grade cavity.Through backward step 16,, form recirculating zone 32 in the pre-combustion grade cavity because air-flow entrainments effect.Pre-combustion grade fuel injected 5 is sprayed and is entered pre-combustion grade cavity 30, in the pre-combustion grade cavity in the recirculating zone 32 with air mixing diffusion combustion.Top board tangential hole 26 by center cavity backward step pre-combustion grade 44, top board tangential admission 33 enters pre-combustion grade cavity 30, strengthen flowing of pre-combustion grade cavity recirculating zone 32, appropriate low-speed conditions and oil-gas ratio have guaranteed the smooth combustion in the center cavity backward step pre-combustion grade combustion zone 7 in pre-combustion grade cavity recirculating zone 32, for the combustion chamber provides stable burning things which may cause a fire disaster.The distribution number of center cavity backward step pre-combustion grade 44 designs according to required duty, and tangential firing can improve the circumferential Temperature Distribution in the burner inner liner.Bluff body flameholder main combustion stage air-flow 3 with certain tangential angle by outer shroud bluff body flameholder 13, interior ring bluff body flameholder 18 passages enter burner inner liner inside, HTHP fuel oil 53 is confessed from flameholder inside in the bluff body stabilizer, fuel oil is through 27 ejections of bluff body flameholder spout, main combustion stage HTHP fuel oil 34 jets mix the formation gas mixture with bluff body flameholder main combustion stage main combustion stage air-flow 3, formed the smooth combustion in the bluff body flameholder main combustion stage combustion zone 6 at outer shroud bluff body flameholder 13 and interior ring bluff body flameholder 18 rear portions of main combustion stage flame by the pre-combustion grade flame ignition.The distribution number of outer shroud bluff body flameholder 13 and interior ring bluff body flameholder 18 designs according to required duty, guarantees combustor exit 23 Temperature Distribution requirements.Combustion gas is discharged the combustion chamber through outlet support plate 21 with certain tangential angle, and the number of outlet support plate 21 and angle are according to the air inlet angle and the decision of blade number of turbine.
The diffusion ratio of shunting diffuser 10 is 1～3, with moment of momentum principles such as air designs, make inlet air flow 1 behind diffuser still with tangential flows at angles, the flow of each several part need satisfy the requirement that air-flow evenly enters burner inner liner.
The distribution number of center cavity backward step pre-combustion grade 44 designs according to required duty, and center cavity single cycle segment angle 28 of backward step pre-combustion grade and top board circumferential lengths 36 are also determined by center cavity backward step pre-combustion grade 44 distribution numbers simultaneously.Backward step height 35 is by 36 decisions of top board circumferential lengths, and it is suitable with top board circumferential lengths 36 generally to design pre-combustion grade cavity recirculating zone 32 length, and pre-combustion grade cavity recirculating zone 32 length are 10 times of backward step height 35, and the obstruction ratio of backward step 16 is 0.3～0.4.
Center cavity backward step pre-combustion grade air mass flow accounts for 5%～20% of whole combustion chamber air mass flow, wherein tangential slot outer shroud 14 air inlets 2.8%～3.5%, ring 17 air inlets 2.1%～2.8% in the tangential slot, top board 24 air inlets 0.7%～1.4%.The required air mass flow of ring 17 and tangential slot outer shroud 14 is relevant in the distribution number of tangential slot inner and outer ring tangential slot 25 and tangential slot inner and outer ring tangential slot cycle angle 39 and the tangential slot, tangential slot inner and outer ring tangential slot width 38 is 1mm～1.5mm, and the tangential angle 37 of tangential slot inner and outer ring is 15 °～30 °.
In order to strengthen recirculating zone 32 in the pre-combustion grade cavity, top board 24 is opened top board tangential admission hole 26, and top board tangential hole diameter 41 is 1mm～1.2mm, and it 40 is 30 °～45 ° that the top board perforate cuts angle, and number of aperture is 65～135.Be the humidification that guarantees that 33 pairs of pre-combustion grade cavitys of top board tangential gas flow recirculating zone 32 is best, top board 24 perforate scopes from the whole top board circumferential lengths 36 of backward step 16 beginnings 60% in.
Center cavity backward step pre-combustion grade has enough spraying subtended angles to satisfy stable ignition performance, and the design point oil-gas ratio of nozzle 15 is 0.05.
Outer shroud bluff body flameholder main combustion stage 50 and interior ring bluff body flameholder main combustion stage 51 account for 80% of the total air mass flow in combustion chamber, 48% of outer shroud bluff body flameholder main combustion stage 50 air mass flows, and interior ring bluff body flameholder main combustion stage 51 accounts for 32%.Outer shroud bluff body flameholder 13 adopts the identical structure that waits the aisle spare blade profile with interior ring bluff body flameholder 18, inner hollow, HTHP fuel oil 53 sprays from bluff body flameholder inside through bluff body flameholder fuel jet 27 in the bluff body stabilizer, fuel oil according to different pressures, temperature requirement ejection can be liquid state, also can be gaseous state.Mix the formation gas mixture at main combustion stage HTHP fuel oil 34 and bluff body flameholder main combustion stage air-flow 3, well-mixed fuel oil and air are lighted by the flame heat of center cavity backward step pre-combustion grade combustion zone 7.Utilize the low speed recirculating zone that forms behind the bluff body, the burning that gas mixture is stable in the recirculating zone.This designs simplification the head of combustion chamber structure, and use gaseous fuel injection to get rid of the influence of fuel-oil atmozation to burning, improved the oil gas admixture simultaneously, optimized the combustor exit Temperature Distribution.
The distribution number of outer shroud bluff body flameholder main combustion stage 50 and interior ring bluff body flameholder main combustion stage 51 is according to required duty design, the interior ring bluff body of outer shroud bluff body flameholder 13 distribution numbers flameholder more than 18, its number is by the height decision of pre-combustion grade cavity 30.Bluff body flameholder exit width 42 is relevant with the distribution number of outer shroud bluff body flameholder 13 and interior ring bluff body flameholder 18, general main combustion stage channel width is suitable with bluff body flameholder width 42, because the periphery diameter that inner and outer ring bluff body flameholder is installed is different with inner and outer ring bluff body flameholder distribution number, the inner and outer ring channel width is slightly different.
Bluff body flame stabilization axial length 43 is relevant with the setting angle 29 of bluff body flameholder, blower outlet flow-deviation angle decision bluff body flameholder established angle 29, and bluff body flameholder established angle 29 scopes are 10 °～60 °.Because bluff body flameholder main combustion stage air-flow 3 has certain tangential angle, make interior the flowing of whole burner inner liner also have certain tangential angle, thereby under the situation of less burner inner liner length, increased the residence time of gas mixture in burner inner liner, satisfied the smooth combustion work of combustion chamber, reached the combustion chamber of knowing clearly and shorten the purpose that length reduces weight.
Bluff body flameholder fuel oil spray orifice 27 can be selected out at bluff body flameholder pressure face 56, also can be simultaneously in bluff body flameholder pressure face 56,57 perforates of bluff body flameholder suction surface, perforate can be selected single or many rows, single number of aperture should be greater than 5, opening diameter 0.5mm～1.0mm.The gentle amount of flow of fuel flow in the concrete working range and the ratio of momentum of fuel injected have determined perforate quantity and perforate apart from the axial location of channel outlet, should guarantee that the track center of main combustion stage HTHP fuel oil 34 reaches the center of channel width at least in channel outlet.
The cooling gas flow of interior burner inner liner 20 and outer burner inner liner 19 is 10%～20% of a combustion chamber total flow, adopt the air film cooling, impact and disperse cooling or other compound type of cooling, with control flame tube wall temperature, and prevent that combustion flame from entering in the cold gas, to reduce the generation of CO and UHC.
In a concrete case study on implementation, the gross gas-oil ratio of establishing Combustion chamber design point is 0.05, the about 194778mm of the total air inlet effective area in combustion chamber
2According to said method, the distribution tolerance of center cavity backward step pre-combustion grade accounts for the about 7% of whole combustion chamber air inlet, and center cavity backward step pre-combustion grade combustion zone equivalent proportion is 0.73, belongs to poor oil firing; Outer shroud bluff body flameholder main combustion stage distributes tolerance to account for the about 48% of whole combustion chamber air inlet, and interior ring bluff body flameholder main combustion stage distributes tolerance to account for about 32% of whole combustion chamber air inlet.The cold gas air inlet distributes tolerance to account for 13% of whole combustion chamber air inlet, in order to burner inner liner in cooling off and outer burner inner liner.According to proportioning, center cavity backward step pre-combustion grade air inlet effective area is 13634mm
2, outer shroud bluff body flameholder main combustion stage is 93493mm
2, interior ring bluff body flameholder main combustion stage is 62329mm
2Fire for center cavity backward step pre-combustion grade, the tangential angle of tangential slot inner and outer ring is 15 °, tangential slot inner and outer ring tangential slot width 1mm, 5 ° at tangential slot inner and outer ring tangential slot cycle angle, tangential slot outer shroud flow accounts for 40% of center cavity backward step pre-combustion grade, and circulation accounts for 40% of center cavity backward step pre-combustion grade in the tangential slot; 15 ° of top board tangential hole angles, top board tangential hole diameter 1mm, 135 of perforate numbers, top board tangential admission orifice flow amount accounts for 20% of center cavity backward step pre-combustion grade.Backward step height 13.5mm, pre-combustion grade channel height 42mm stops up than 0.32 top board circumferential lengths 120mm, HTHP oil supplying hole diameter 0.5mm.The combustion of center cavity backward step pre-combustion grade is along circumferentially evenly distributing 12, and center cavity backward step pre-combustion grade is fired 30 ° of single cycle segment angles.Bluff body flameholder exit width is 20mm, and bluff body flameholder axial length 20mm, outer shroud arrange 48 outer shroud bluff body flameholders, in be periphery and put ring bluff body flameholder in 36.Bluff body flameholder pressure face is opened single 5 bluff body flameholder fuel jets, bore dia 1mm, and position of opening is 10% of a whole passage length apart from the axial distance of channel outlet.The gaseous fuel of logical HTHP in the bluff body flameholder, bluff body flameholder thickness 1.2mm, outer shroud bluff body flameholder and interior ring bluff body flameholder established angle are 60 °.65 ° of outlet support plate setting angles, thickness 1.2mm, number is 36.
Claims (11)
1. the center cavity stable fire tangential combustion chamber is characterized in that: be made of casing (11), center cavity backward step pre-combustion grade (44), outer shroud bluff body flameholder main combustion stage (50), interior ring bluff body flameholder main combustion stage (51), fuel oil supply system (48), interior burner inner liner (20), outer burner inner liner (19) and outlet support plate (21) in shunting diffuser (10), outer combustion case (12), the combustion chamber; Described center cavity backward step pre-combustion grade (44) is by top board (24), backward step (16), nozzle (15), ring (17) and tangential slot outer shroud (14) constitute in the tangential slot, top board (24) is connected along the place circumference with backward step (16), nozzle (15) is placed on the radial end face of backward step (16), what ring (17) and tangential slot outer shroud (14) were placed in backward step (16) and top board (24) respectively in the tangential slot is the inside circumference and the outside of axle with the engine axis, ring (17) in the tangential slot, tangential slot outer shroud (14), backward step (16) and top board (24) four form the circumferential pre-combustion grade cavity (30) that section is semiclosed rectangle, air enters pre-combustion grade cavity (30) through tangential slot inner and outer ring tangential admission groove (25) and tangentially flows the low speed recirculating zone retention flame that utilizes backward step (16) to produce; Described outer shroud bluff body flameholder main combustion stage (50) and interior ring bluff body flameholder main combustion stage (51) are formed main combustion stage jointly, outer shroud bluff body flameholder main combustion stage (50) and interior ring bluff body flameholder main combustion stage (51) are made up of outer shroud bluff body flameholder (13) and interior ring bluff body flameholder (18) respectively, outer shroud bluff body flameholder main combustion stage (50) is identical with both structures of interior ring bluff body flameholder main combustion stage (51), outer shroud bluff body flameholder (13) is placed between the outer side surface and outer burner inner liner (20) internal face of tangential slot outer shroud (14), the leading edge of outer shroud bluff body flameholder (13) flushes with the leading edge of tangential slot outer shroud (14), interior ring bluff body flameholder (18) is placed between the interior sidewall surface and interior burner inner liner (19) outside wall surface of ring (17) in the tangential slot, in the leading edge of ring bluff body flameholder (18) flush with the leading edge of tangential slot outer shroud (17), during the installation of outer shroud bluff body flameholder (13) and interior ring bluff body flameholder (18) and engine axis deflection angle is arranged; Fuel oil supply system (48) is by nozzle mount pad (45), liquid fuel pipe (46) and HTHP fuel pipe (47) constitute, fuel oil supply system (48) links to each other with outer combustion case (12) by nozzle mount pad (45), the liquid fuel pipe is supplied with liquid fuel to nozzle (15), HTHP fuel pipe (47) is supplied with the HTHP fuel oil, be connected with top board (24), through top board (24), backward step (16), the HTHP oil supplying hole (52) of ring (14) is supplied with the HTHP fuel oil in tangential slot outer shroud (17) and the tangential slot in outer shroud bluff body flameholder (13) and interior ring bluff body flameholder (18), the main combustion stage HTHP fuel oil (34) that ejects in outer shroud bluff body flameholder (13) and the interior ring bluff body flameholder (18) mixes with air by center cavity backward step pre-combustion grade (44) and ignites, and the low regime smooth combustion behind bluff body; Described outlet support plate (21) is placed in the exit of interior burner inner liner (20) and outer burner inner liner (19), and outlet support plate (21) has angle with the combustion chamber axis, and burning after-burner outlet combustion gas has deflection angle.
2. center cavity stable fire tangential combustion chamber according to claim 1, it is characterized in that: the air distribution of described center cavity backward step pre-combustion grade (44) accounts for 5%～20% of whole burning tolerance, and the air distribution of outer shroud bluff body flameholder main combustion stage (50) and interior ring bluff body flameholder main combustion stage (51) accounts for 60%～90% of whole burning tolerance; Whole combustion chamber has 12～18 center cavity backward step pre-combustion grade (44), and the single cycle segment angle of center cavity pre-combustion grade (28) is 20 °～30 °.
3. center cavity stable fire tangential combustion chamber according to claim 1, it is characterized in that: described shunting diffuser (10) is divided into three strands of air-flows by two splitters with air-flow, be central gas stream (2), outer shroud air-flow (54) and interior ring air-flow (55), make air-flow be uniformly scattered onto head of combustion chamber, three strands of exit flows of shunting diffuser (10) are upwards turned back.
4. center cavity stable fire tangential combustion chamber according to claim 4, it is characterized in that: ring (17) and tangential slot outer shroud (14) have tangential slot inner and outer ring tangential admission groove (25) in the tangential slot of described center cavity backward step pre-combustion grade (44), tangential slot inner and outer ring tangential admission groove (25) and 15 °～30 ° of tangent to periphery angles, tangential slot inner and outer ring tangential slot width (38) is 1.0mm～1.5mm, tangential slot inner and outer ring tangential gas flow (4) enters the inner pre-combustion grade cavity (30) of center cavity backward step pre-combustion grade (44) through tangential slot inner and outer ring tangential admission groove (25) and forms tangential gas flow, tangential slot outer shroud (14) flow accounts for 20%～50% of center cavity backward step pre-combustion grade (44), and ring (17) flow accounts for 20%～50% of center cavity backward step pre-combustion grade (44) in the tangential slot.
5. center cavity stable fire tangential combustion chamber according to claim 2, it is characterized in that: the top board (24) of described center cavity backward step pre-combustion grade (44) has a plurality of top board tangential admissions holes (26) opposite with the tangential flow direction of the interior air-flow of pre-combustion grade cavity (30), top board tangential admission hole (26) and 15 °～30 ° of engine axis angles, top board tangential hole diameter (41) is 0.5mm～1.0mm, number of aperture 65～135, gas inlet hole strengthens the interior recirculating zone (32) of pre-combustion grade cavity behind the backward step (16), and flow is 10%～50% of center cavity backward step pre-combustion grade (a 44) flow.
6. center cavity stable fire tangential combustion chamber according to claim 1 is characterized in that: the nozzle (15) of described center cavity backward step pre-combustion grade (44) is placed on backward step (16) radial end face, with place axial cross section angle be 5 °～60 °.
7. center cavity stable fire tangential combustion chamber according to claim 1, it is characterized in that: ring (14) all has HTHP oil supplying hole (52), aperture 0.4mm～1mm in the top board (24) of described center cavity backward step pre-combustion grade (44), backward step (16), tangential slot outer shroud (17), the tangential slot; HTHP fuel pipe (47) is connected with backward step (16), and the HTHP oil supplying hole (52) of ring (14) is interconnected in backward step (16), top board (24), tangential slot outer shroud (17) and the tangential slot; Fuel oil supply system (48) is supplied with HTHP fuel oil (53) in the stabilizer through HTHP oil supplying hole (52) in outer shroud bluff body flameholder (13) and interior ring bluff body flameholder (18).
8. center cavity stable fire tangential combustion chamber according to claim 1 is characterized in that: when described outer shroud bluff body flameholder (13) and interior ring bluff body flameholder (18) are installed and the deflection angle of engine axis be 10 °～60.
9. center cavity stable fire tangential combustion chamber according to claim 8, it is characterized in that: described outer shroud bluff body flameholder (13) and interior ring bluff body flameholder (18) are hollow-core construction, outer shroud bluff body flameholder (13) and interior ring bluff body flameholder (18) wall are radially opened a plurality of bluff body flameholder of single row or multiple rows fuel jet (27), the aperture of described bluff body flameholder fuel jet (27) is 0.5mm～1mm, from the outwards ejection of outer shroud bluff body flameholder (13) and interior ring bluff body flameholder (18), perforate is chosen in 10%～20% the position that accounts for passage length apart from channel outlet to main combustion stage HTHP fuel oil (34) through bluff body flameholder fuel jet (27).
10. center cavity stable fire tangential combustion chamber according to claim 1, it is characterized in that: the interior burner inner liner (11) of described combustion chamber and the type of cooling of outer burner inner liner (12) adopt the air film cooling, disperse the cooling or the compound type of cooling, wall surface temperature is controlled the life-span that prolongs burner inner liner.
11. center cavity stable fire tangential combustion chamber according to claim 1 is characterized in that: described combustor exit support plate (21) is 5 °～70 ° with the angle of combustion chamber axis; Described outlet support plate (21) number is 24～48.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200910241247 CN101737802B (en) | 2009-11-27 | 2009-11-27 | Central cavity stable fire tangential combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200910241247 CN101737802B (en) | 2009-11-27 | 2009-11-27 | Central cavity stable fire tangential combustion chamber |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101737802A true CN101737802A (en) | 2010-06-16 |
| CN101737802B CN101737802B (en) | 2012-12-26 |
Family
ID=42461636
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200910241247 Expired - Fee Related CN101737802B (en) | 2009-11-27 | 2009-11-27 | Central cavity stable fire tangential combustion chamber |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101737802B (en) |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102200291A (en) * | 2011-03-29 | 2011-09-28 | 北京航空航天大学 | Pneumatic primary level graded low-pollution combustion chamber |
| CN102242940A (en) * | 2011-07-29 | 2011-11-16 | 北京航空航天大学 | Three-stage structured pre-mixing and pre-evaporating low-pollution combustor |
| CN102242939A (en) * | 2011-07-29 | 2011-11-16 | 北京航空航天大学 | Prefilming three-stage pre-mixing and pre-evaporating low-pollution combustor |
| CN102589007A (en) * | 2011-01-03 | 2012-07-18 | 通用电气公司 | Combustor with fuel staggering for flame holding mitigation |
| CN102748775A (en) * | 2012-07-23 | 2012-10-24 | 集美大学 | Streamline flame stabilizer with built-in ignition sources |
| CN104832949A (en) * | 2015-05-19 | 2015-08-12 | 北京航空航天大学 | Airflow induction backward step standing vortex flame stabilization grading combustion chamber |
| CN105114982A (en) * | 2015-09-15 | 2015-12-02 | 中国航空工业集团公司沈阳发动机设计研究所 | Diffuser with large expansion ratio |
| WO2016095157A1 (en) * | 2014-12-18 | 2016-06-23 | 深圳智慧能源技术有限公司 | Combustion chamber having porous flame tube |
| CN106907738A (en) * | 2017-02-16 | 2017-06-30 | 中国航发沈阳发动机研究所 | A kind of combustion chamber |
| CN109780571A (en) * | 2018-12-26 | 2019-05-21 | 南京航空航天大学 | A kind of vaporation-type combination flameholder |
| CN109899831A (en) * | 2019-03-11 | 2019-06-18 | 中国航发湖南动力机械研究所 | Combustion chamber |
| CN112969890A (en) * | 2018-10-05 | 2021-06-15 | 法孚皮拉德公司 | Burner and combustion method for a burner |
| CN112963273A (en) * | 2021-03-03 | 2021-06-15 | 中国人民解放军空军工程大学 | Self-air-entraining kerosene pre-combustion cracking activation device and method for concave cavity flame stabilizer |
| CN114777158A (en) * | 2022-05-13 | 2022-07-22 | 哈尔滨工程大学 | Combustion chamber mixing structure based on blunt body group |
| CN115095885A (en) * | 2022-06-06 | 2022-09-23 | 中国船舶集团有限公司系统工程研究院 | Combined multi-point LDI oblique-feeding combustion chamber |
| CN115264533A (en) * | 2022-07-24 | 2022-11-01 | 哈尔滨工程大学 | Natural gas coaxial staged combustion chamber adopting center ignition and combustion method |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113566237A (en) * | 2021-07-23 | 2021-10-29 | 中国航发贵阳发动机设计研究所 | High-energy large-penetration torch type igniter |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE59208831D1 (en) * | 1992-06-29 | 1997-10-02 | Abb Research Ltd | Combustion chamber of a gas turbine |
| US5687571A (en) * | 1995-02-20 | 1997-11-18 | Asea Brown Boveri Ag | Combustion chamber with two-stage combustion |
-
2009
- 2009-11-27 CN CN 200910241247 patent/CN101737802B/en not_active Expired - Fee Related
Cited By (26)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102589007B (en) * | 2011-01-03 | 2016-03-23 | 通用电气公司 | For alleviating the burner with fuel staggering that flame keeps |
| CN102589007A (en) * | 2011-01-03 | 2012-07-18 | 通用电气公司 | Combustor with fuel staggering for flame holding mitigation |
| US9416974B2 (en) | 2011-01-03 | 2016-08-16 | General Electric Company | Combustor with fuel staggering for flame holding mitigation |
| CN102200291B (en) | 2011-03-29 | 2013-12-11 | 北京航空航天大学 | Pneumatic primary level graded low-pollution combustion chamber |
| CN102200291A (en) * | 2011-03-29 | 2011-09-28 | 北京航空航天大学 | Pneumatic primary level graded low-pollution combustion chamber |
| CN102242940A (en) * | 2011-07-29 | 2011-11-16 | 北京航空航天大学 | Three-stage structured pre-mixing and pre-evaporating low-pollution combustor |
| CN102242939A (en) * | 2011-07-29 | 2011-11-16 | 北京航空航天大学 | Prefilming three-stage pre-mixing and pre-evaporating low-pollution combustor |
| CN102242939B (en) * | 2011-07-29 | 2013-12-11 | 北京航空航天大学 | Prefilming three-stage pre-mixing and pre-evaporating low-pollution combustor |
| CN102242940B (en) * | 2011-07-29 | 2014-02-12 | 北京航空航天大学 | Three-stage structured pre-mixing and pre-evaporating low-pollution combustor |
| CN102748775A (en) * | 2012-07-23 | 2012-10-24 | 集美大学 | Streamline flame stabilizer with built-in ignition sources |
| CN102748775B (en) * | 2012-07-23 | 2014-11-19 | 集美大学 | Streamline flame stabilizer with built-in ignition sources |
| WO2016095157A1 (en) * | 2014-12-18 | 2016-06-23 | 深圳智慧能源技术有限公司 | Combustion chamber having porous flame tube |
| CN104832949A (en) * | 2015-05-19 | 2015-08-12 | 北京航空航天大学 | Airflow induction backward step standing vortex flame stabilization grading combustion chamber |
| CN104832949B (en) * | 2015-05-19 | 2017-02-01 | 北京航空航天大学 | Airflow induction backward step standing vortex flame stabilization grading combustion chamber |
| CN105114982A (en) * | 2015-09-15 | 2015-12-02 | 中国航空工业集团公司沈阳发动机设计研究所 | Diffuser with large expansion ratio |
| CN106907738A (en) * | 2017-02-16 | 2017-06-30 | 中国航发沈阳发动机研究所 | A kind of combustion chamber |
| CN112969890A (en) * | 2018-10-05 | 2021-06-15 | 法孚皮拉德公司 | Burner and combustion method for a burner |
| CN109780571A (en) * | 2018-12-26 | 2019-05-21 | 南京航空航天大学 | A kind of vaporation-type combination flameholder |
| CN109899831B (en) * | 2019-03-11 | 2020-10-02 | 中国航发湖南动力机械研究所 | Combustion chamber |
| CN109899831A (en) * | 2019-03-11 | 2019-06-18 | 中国航发湖南动力机械研究所 | Combustion chamber |
| CN112963273A (en) * | 2021-03-03 | 2021-06-15 | 中国人民解放军空军工程大学 | Self-air-entraining kerosene pre-combustion cracking activation device and method for concave cavity flame stabilizer |
| CN112963273B (en) * | 2021-03-03 | 2022-07-01 | 中国人民解放军空军工程大学 | Self-air-entraining kerosene pre-combustion cracking activation device and method for concave cavity flame stabilizer |
| CN114777158A (en) * | 2022-05-13 | 2022-07-22 | 哈尔滨工程大学 | Combustion chamber mixing structure based on blunt body group |
| CN115095885A (en) * | 2022-06-06 | 2022-09-23 | 中国船舶集团有限公司系统工程研究院 | Combined multi-point LDI oblique-feeding combustion chamber |
| CN115095885B (en) * | 2022-06-06 | 2024-02-09 | 中国船舶集团有限公司系统工程研究院 | Combined multi-point LDI inclined combustion chamber |
| CN115264533A (en) * | 2022-07-24 | 2022-11-01 | 哈尔滨工程大学 | Natural gas coaxial staged combustion chamber adopting center ignition and combustion method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101737802B (en) | 2012-12-26 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101737802B (en) | Central cavity stable fire tangential combustion chamber | |
| CN110657452B (en) | Low-pollution combustion chamber and combustion control method thereof | |
| US10072848B2 (en) | Fuel injector with premix pilot nozzle | |
| CN101285591B (en) | Integral fuel jet radial swirler pre-mixing preevaporated low pollution combustion-chamber | |
| CN101275750B (en) | Radial swirler turning zone direct injection premixing and prevapourising low pollution burning chamber | |
| CN100557318C (en) | A kind of integral fuel jet axial swirler pre-mixing preevaporated low pollution combustion chamber | |
| CN102022753B (en) | Low-pollution combustion chamber with premixed and pre-evaporated precombustion part | |
| CN101029739B (en) | Combustion chamber of gas turbine engine and the gas turbine engine | |
| CN102032598B (en) | Circumferentially graded low-pollution combustion chamber with multiple middle spiral-flow flame stabilizing stages | |
| US20080078183A1 (en) | Liquid fuel enhancement for natural gas swirl stabilized nozzle and method | |
| CN109668171B (en) | Radial grading zoning high-temperature-rise combustion chamber head | |
| US8528338B2 (en) | Method for operating an air-staged diffusion nozzle | |
| CN106123033B (en) | A kind of low emission combustor of main combustion stage blade trepanning oil spout | |
| CN102889616B (en) | Multi-point direct spray combustion chamber based on venturi premixing double spiral nozzle | |
| CN102889618B (en) | Annular combustion chamber based on Venturi pre-mixing bispin nozzle | |
| CN105157062A (en) | Low-emission combustion chamber with double-layer axial hydrocyclone adopted at precombustion stage | |
| CN102889617B (en) | Premixing and pre-evaporation combustor for main combustion stage using radial film formation | |
| US20080168773A1 (en) | Device for injecting a mixture of air and fuel, and combustion chamber and turbomachine which are provided with such a device | |
| CN103017203A (en) | Fractional combustion chamber | |
| CN108954388A (en) | A kind of multiple spot unit directly sprays fractional combustion room | |
| CN107575891A (en) | A kind of dual-fuel gas turbine low pollution combustor head construction | |
| CN100543371C (en) | A kind of radial swirler turning zone liquid and mist injection premixing and prevapourising low pollution combustor | |
| CN109708148B (en) | Gas turbine combustor doublestage radial swirler | |
| EP2932155A1 (en) | Air directed fuel injection | |
| CN108844097B (en) | Low-pollution combustion chamber for multi-point lean oil direct injection |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20121226 Termination date: 20131127 |