CN103998867A - Combustor - Google Patents
Combustor Download PDFInfo
- Publication number
- CN103998867A CN103998867A CN201280050137.7A CN201280050137A CN103998867A CN 103998867 A CN103998867 A CN 103998867A CN 201280050137 A CN201280050137 A CN 201280050137A CN 103998867 A CN103998867 A CN 103998867A
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- China
- Prior art keywords
- combustion chamber
- air
- fuel
- passage
- compressor
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/06—Arrangement of apertures along the flame tube
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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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
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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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
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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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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/58—Cyclone or vortex type combustion chambers
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Abstract
A combustion method and combustor for use in a jet engine, the jet engine having a compressor portion and a turbine portion are provided. The combustor includes an outer tube having a central axis that extends longitudinally intermediate the compressor portion and turbine portion and is positioned to receive air discharged by the compressor portion. An inner tube is positioned within the outer tube that includes an associated outer surface spaced from the inner surface of the outer tube thereby defining a combustion chamber. The outer tube and inner tube include fluid directing structure for communicating at least some of the air discharged by the compressor portion to the combustion chamber. The fluid directing structure directs air into the combustion chamber in a direction offset from the central axis, thereby causing rotation or swirling of the air about the central axis.
Description
the cross reference of related application
The application requires the priority of U.S. Provisional Application No.61/522412 of submitting on August 11st, 2011, the full content of described U.S. Provisional Application at this by reference to being incorporated herein.
Technical field
The present invention relates to a kind of fuel burner, and relate more specifically to a kind of combustion chamber for gas-turbine engine or heater, it is based on combustion air or combustion air and fuel and transmit centrifugal force.
Background technology
Gas turbine (being also called jet engine) is the mobile rotating engine that draws energy from burning gases.They have the upstream compressor of the downstream turbine of being connected to, and between described upstream compressor and described downstream turbine, have combustion chamber.Gas turbine has many different modification, but they all use identical general principle.
Jet-propelled aircraft is driven by turbojet or fanjet conventionally.Turbojet is by the gas-turbine engine of following manner work: mix, make the mixture burns in combustion chamber by air compressing, by fuel with compressed air and make subsequently hot gases at high pressure through turbine and nozzle with entrance and compressor.Compressor is by turbo-driven, and described turbine draws energy from the expanding gas through it.The energy in fuel is changed into the kinetic energy in effluent by engine, thereby produce thrust.The all air that absorbed by entrance all pass compressor, combustion chamber and turbine.
Fanjet is very similar to turbo jet engine, except it is also included in compression section fan before.Just as compressor, fan is also to be driven by the turbine of engine.Unlike turbo jet engine, some that accelerated by fan flows bypass combustion chamber and discharges by nozzle.The speed of the stream of bypass is lower, but quality is higher, thereby makes the thrust that produced by fan more efficient than the thrust being produced by core.Turbofan machine is conventionally more efficient than turbo jet engine at subsonic, but they have larger front area, and described larger front area generates larger towing in fair speed.
Turboprop is to draw from hot discharge is jet the jet engine derivative that merit is rotated rotating shaft, thereby the merit of drawing is subsequently for making screw rotation produce other thrust.Turboprop has generally than the better performance of turbo jet engine or has other thrust.Turboprop has than turbo jet engine or the better performance of turbofan machine generally at low speed (now propeller efficiency is high), but noise is increasing and efficiency is more and more lower in the time of high speed.
Turboaxle motor is very similar to turboprop, and difference is that the nearly all energy in effluent is all extracted makes rotating shaft rotation.Turboaxle motor generates equipment and other application for fixing power.
The problem being associated with gas-turbine engine (especially in aircraft) is the possibility of fire extinguishing, and this occurs in the time that flame extinguishes in combustion chamber.One in the reason of fire extinguishing is, the anterior flame in combustion chamber unstable.Because engine failure is obviously problematic during flying, so construct a kind of gas-turbine engine, the possibility of fire extinguishing is reduced favourable.For fixing power generation system, need to reduce emission (is mainly NO
x), so that meet upgrade, severeer clean air demand.
Summary of the invention
The invention provides a kind of new and improved combustion method and a kind of combustion chamber or the burner that can in jet engine and other heating/burn application, use.In the illustrated embodiment, described combustion chamber is depicted as and will uses together with comprising the jet engine of compressor section and the type of turbine part.
According to one preferably and in the embodiment illustrating, described jet engine comprises compressor section and turbine part.In a this preferred embodiment with illustrating, described combustion chamber comprises the pipe extending longitudinally with central axis, and described pipe extending longitudinally is positioned to receive the air being loaded by described compressor section.Exterior tube has outer surface and inner surface.Inner tube is positioned in described exterior tube and comprises the outer surface being associated, and the inner surface of described outer surface and described exterior tube is spaced apart, can be the passage of combustion chamber thereby limit, and at described passage place, fuel mixture can burn at least partly.
In the illustrated embodiment, described exterior tube comprises direct fluid structure, described direct fluid structure for by the air being discharged by described compressor section at least some is communicated to combustion chamber passage, described combustion chamber passage is limited between the inner surface of described exterior tube and the outer surface of described inner tube.Described direct fluid structure leads air in the direction of setovering from the central axis of described exterior tube, thereby causes the rotation of air around described central axis.Fuel is directly or indirectly fed to described combustion chamber passage by least one fuel delivery member, to form fuel air mixture rotation or vortex in described combustion chamber passage.
According to the present invention, the described swirling fuel mixture in described combustion chamber passage can be burnt wholly or in part in described combustion chamber passage.
Preferably and in the embodiment illustrating, described inner tube also comprises the direct fluid structure being associated, described in the direct fluid structure that is associated for air communication that it is received from described compressor section to described combustion chamber passage.The described direct fluid structure being associated is being also that the direction of setovering from described central axis leads by air.
In one embodiment, described fuel component is directly communicated with described combustion chamber passage and directly supplies fuel to described chamber passage, thereby mixes with compressor air at described chamber passage place fuel that formation rotates/combustible fuel/air mixture of vortex.In alternative, described fuel component is by described fuel and some compressor air premixed and subsequently described premixed fuel and air are fed to described combustion chamber passage, states premixed fuel and air mix with the rotary compressor air (or fuel/air mixture) that is transported to described combustion chamber passage in described combustion chamber passage place.In another alternative, described fuel component by fuel draining in the air stream being discharged by described compressor section (along with described air stream is towards described Combustor Flows).In this alternative, the direct fluid structure that fuel and compressor air all flow through described outside and/or inner tube enters in described combustion chamber passage.
According to an embodiment who illustrates, described outside and inner tube are arranged such that their corresponding deads in line.According to the constructive alternative of this embodiment, the axis of described inside and outside pipe overlaps with the rotation being limited by described compressor section.
According to preferred embodiment, the guiding piece that described direct fluid structure comprises multiple openings and is associated with each opening, described guiding piece is angled with respect to the surface of pipe, to radial rotary is delivered to air around described central axis.In the illustrated embodiment, described guiding piece is arranged in a series of rows that extend around the periphery of described exterior tube.In a preferred embodiment, described inner tube has similar direct fluid structure.
In preferred embodiment, described direct fluid structure is included in a series of scalariform things that form in described exterior tube, described scalariform thing comprises opening, and described opening is for causing mixture to be directed to described combustion chamber passage in the rotation of described central axis or the direction of vortex air.According to the feature of this preferred embodiment, each scalariform thing has L shaped, described L shaped the first member and the second component of comprising, described second component comprises for by the opening of air guide, with the opening that makes a scalariform thing, air is rotated to described mixture across the scalariform thing guiding of adjacency to transmit.
According to exemplary embodiment, described direct fluid structure comprises multiple openings, the each outer surface from described exterior tube of described multiple opening extends to described inner surface, each opening to be angularly to extend through described exterior tube with respect to an axis, and a described axis extends and through described central axis in the normal direction of the outer surface of described inner tube.According to the feature of this embodiment, described exterior tube comprises multiple the second openings, and described multiple the second openings are each extends to described inner surface from the outer surface of described exterior tube in the direction that extends to described central axis.In preferred embodiment, described inner tube comprises similar direct fluid structure.
In embodiment preferred and that illustrate, described exterior tube is formed as limiting a series of overlapping cambered plate of described direct fluid structure, each plate has corrugated contours, and described corrugated contours has series of passages, and air is directed in described combustion chamber passage through described series of passages.In such an embodiment, described corrugated contours comprises multiple alternately cusp and recesses, and preferably, described overlapping plates is longitudinal and radial offset each other, and the cusp of a plate is positioned between the cusp of adjacent panels.In addition, in such an embodiment, each plate leads air to rotation is delivered to mixture in the direction that is arranged essentially parallel to adjacent plate extension.
In the preferable configuration of this embodiment, the inner tube of described combustion chamber comprises first end and the second end, described first end and the air communication of being discharged by described compressor section, described the second end there is end wall in case by the second end of described inner tube with air tight manner closure.By this structure, the direct fluid structure being associated with described inside and outside pipe provides unique fluid path of described combustion chamber passage.
According in the combustion chamber of the one or more structures in disclosed embodiment, described rotation mixture is radially layered in described combustion chamber passage.
According to still another embodiment of the invention, described combustion chamber comprises the pipe with central axis, and described pipe is positioned in the middle of described compressor section and described turbine part and has outer surface and inner surface.Direct fluid structure forms on described pipe, and described pipe comprises the passage that extends to described inner surface from described outer surface.The inner surface of described pipe limits combustion chamber.Passage is communicated with the air being discharged by described compressor section with the outer surface of described pipe.Described direct fluid structure is the angle guiding with the central axis biasing from described pipe by described compressor air, thereby causes compressor air to rotate in described combustion chamber.The mixture of fuel or fuel and air is directly or indirectly fed to described combustion chamber by fuel component.
In the shown burning of this alternative, a kind of isolated continuous wall is around described pipe, thus limit described passage at least a portion in case by air communication the outer surface to described pipe.In the more preferably structure of this embodiment, described jet engine comprises multiple this alternative combustion chambers, and described alternative combustion chamber is arranged around the rotation space being limited by described compressor section.
The object of this invention is to provide a kind of jet engine combustion chamber, in described combustion chamber, air or fuel and air are forced to through direct fluid structure, thereby cause vortex and/or the rotation of air/fuel mixture around the axis of described combustion chamber.
By the detailed description to preferred embodiments and drawings below, will obtain about other objects of the present invention and advantage and understand more fully.
Read in conjunction with the drawings detailed description below, other feature of the present invention and further understanding will become clear.
Brief description of the drawings
Fig. 1 is the schematic diagram of the combustion chamber for using at jet engine according to aspects of the present invention;
Fig. 2 A is the cutaway view intercepting along the line 2A-2A of Fig. 1;
Fig. 2 B is the cutaway view intercepting along the line 2B-2B of Fig. 1;
Fig. 3 A is the enlarged drawing of a part for the direct fluid structure of constructing according to a preferred embodiment of the invention;
Fig. 3 B is the cutaway view along Fig. 3 A of line 3B-3B intercepting;
Fig. 4 A-4D is according to the enlarged drawing of multiple parts of alternative fluid guide frame of the present invention;
Fig. 5 is the schematic diagram of the alternative combustion chamber for using at jet engine according to another aspect of the present invention;
Fig. 6 A is the cutaway view intercepting along the line 6A-6A of Fig. 5;
Fig. 7 is the schematic diagram of the alternative combustion chamber for using at jet engine according to another aspect of the present invention;
Fig. 8 A is the cutaway view intercepting along the line 8A-8A of Fig. 7;
Fig. 8 B is the cutaway view intercepting along the line 8B-8B of Fig. 7;
Fig. 9 is the schematic diagram of the alternative combustion chamber for using at jet engine according to another aspect of the present invention;
Figure 10 is the cutaway view intercepting along the line 10-10 of Fig. 9, and;
Figure 11 is the cutaway view intercepting along the line 11-11 of Figure 10.
Detailed description of the invention
The present invention relates to a kind of fuel burner, and relate in particular to a kind of combustion chamber for gas-turbine engine, centrifugal force is transmitted by the burning of combustion air or air and fuel in described combustion chamber.Although accompanying drawing has been described turbojet h type engine h generally and description has been described the use of the present invention in jet engine, but it will be appreciated by those skilled in the art that, in any engine variants that combustion chamber of the present invention described here is suitable for describing in the above, use.
Fig. 1-2 B shows the combustion chamber 240 using in jet engine 200 according to an embodiment of the invention.As shown in Figure 1, jet engine 200 extends and comprises housing 210 along axis 202, and described housing 210 extends to the second end 214 along described axis from first end 212.The wall 216 of housing 210 limits inner passage 218, the length of described inner passage 218 extensional shells.Turbine 220, compressor 230 and at least one combustion chamber 240 are positioned in the passage 218 of housing 210 and along axis 202.Compressor 230 comprises axle or connecting elements 232, and described axle or connecting elements 232 are connected to turbine 220 to described connecting elements is rotated together with described turbine by compressor.Combustion chamber 240 axial location are between turbine 220 and compressor 230.
As shown in Fig. 2 A-2B, combustion chamber 240 comprises outside and inner tube 242,244, and described outside and inner tube 242,244 around central axis 241 concentrically with respect to one another, and are fastened to each other and housing 210.The central axis 241 of combustion chamber 240 can be coaxial with the axis of engine 200 202, or can with the spaced apart (not shown) of the axis of engine.Connecting elements 232 extends through inner tube 244, and shaft seal 233 be arranged between connecting elements and inner tube so as to prevent fluid in described connecting elements and described inner tube through directly entering in turbine 220.
Space boundary fluid passage 274 between outside and inner tube 242,244 is to receive fuel and air.The periphery of exterior tube 242 comprises direct fluid structure 248 to fluid is radially inwardly directed to fluid passage 274.More specifically, direct fluid structure 248 is configured to fluid on the direction of setovering from the central axis 241 of combustion chamber 240 and along the angled route guidance of normal direction (not shown) of the inner surface with respect to exterior tube 242 to fluid passage 274.
The periphery of inner tube 244 comprises direct fluid structure 252 to fluid is radially outward directed to fluid passage 274 from the inside 250 of described inner tube.More specifically, direct fluid structure 252 be configured to fluid on the direction of setovering from the central axis 241 of combustion chamber 240 and along the angled route guidance of normal direction (not shown) of the outer surface with respect to inner tube 244 in fluid passage 274.Direct fluid structure 248,252 can lead their corresponding fluid on identical general direction.Direct fluid structure 248,252 can comprise a series of openings of being associated with fin or guiding piece in case by fluid with the mode of expecting lead (Fig. 3 A-4D).
Jet engine 200 also comprises one or more fuel tube delivery member 254, described member 254 extends in the fluid passage 274 of combustion chamber 240 or is otherwise communicated with the direct fluid in described fluid passage 274, and extend radially outwardly from described passage, pass the wall 216 of housing 210, and extend to the fuels sources (not shown) of described hull outside.Fuel delivery member 254 is delivered directly to fuel fluid passage 274(thus as indicated with arrow F1 generally).Although six fuel delivery member 254 equidistant intervals radially has each other been shown in Fig. 1-2 B, has will be appreciated that any amount of fuel delivery member that shows any spatial configuration can be set according to the present invention.
Annular wall 251 (seeing Fig. 2 B) is fastened to the end that more approaches compressor 230 of outside and inner tube 242,244, so that with one end of the fluid-encapsulated passage 274 of fluid leak-proof manner.Wall 251 is provided with the opening 253 of the end of receiving fuel delivery member 254, to set up direct fluid path between fuel delivery member and fluid passage 274.
Be in operation, air enters (using on the whole in the direction of arrow D2 (Fig. 2 A) sign) compressor 230 at first end 212 places of housing 210, and exits compressor as the air of compression.Exit (as indicated with arrow D3 generally) in the inside 250 that some in the compressed air of compressor 230 directly flow to inner tube 244 and through as described in the direct fluid structure 252 of inner tube 244 enter in fluid passage 274.Some in compressed air also flow to the circumferential annular space 277 between exterior tube 242 and the wall 216 of housing 212, flows through the direct fluid structure 248 in exterior tube and enters fluid passage 274 (as indicated with arrow D4 generally) at described circumferential annular space 277 place's compressed air.Wall 255 (its be fastened to the end that more approaches turbine 220 of outside and inner tube 242,244 and between exterior tube and the wall 216 of housing 210) prevents that compressed air D4 from entering turbine not first through combustion chamber 240 in the situation that.
Compressed air D3, D4 mix with fuel F1, and described fuel F1 is ejected in combustion chamber 240 via fuel delivery member 254.Because annular wall 251 is blocked the end of the contiguous compressor 230 of fluid passage 274, fuel F1 is directly directed in fluid passage 274 by fuel delivery member 254.Correspondingly, the direct fluid structure 248,252 of combustion chamber 240 is only controlled the flowing of compressed air D4, D3 that enters fluid passage 274, so that compressed air mixes in the mode of expectation in fluid passage 274 with fuel F1 from fuel delivery member 254.More specifically, along with ambient air D4 passes the direct fluid structure 248 in exterior tube 242 and enters fluid passage 274, air mixes with the fuel F1 that exits fuel delivery member 254.Due to the structure of direct fluid structure 248, compressed air D4 is along with it enters fluid passage 274 and transmits centrifugal force around the central axis 241 of combustion chamber 240.Vortex air D4 mixes with fuel F1, thereby forms vortex air/fuel mixture in fluid passage 274 and around the central axis 241 of combustion chamber 240.
Equally, compressed air D3 enters the inside 250 of inner tube 244 and passes the fuel guide frame 252 of inner tube 244 and enter fluid passage 274, thereby transmits centrifugal force by compressed air D3 around the central axis 241 of combustion chamber 240.Vortex air D3 mixes with fuel F1, thereby forms other vortex air/fuel mixture in fuel channel 274 and around the central axis 241 of combustion chamber 240.The mixture being formed with compressed air D3 by fuel F1 is with by fuel F1, in fluid passage 274, interior formed mixture mixes and can not distinguish with compressed air D4.
Because direct fluid structure 248,252 is extended around the whole periphery of exterior tube 242 and inner tube 244 respectively, so the total air/fuel mixture in fluid passage 274 is forced in, the single direction (Fig. 2 B) indicating with arrow R is upper to flow, and described single direction is horizontal with 241 one-tenth of the central axis of combustion chamber 240.Will be appreciated that direct fluid structure 248,252 can by corresponding air/fuel mixture for example, in identical (, clockwise with respect to central axis 241) direction in the interior guiding in fluid passage 274.Therefore, the air/fuel mixture in fluid passage 274 experiences with respect to the central axis 241 of combustion chamber 240 and rotation, helical effect in fluid passage 274.Rotation, spiral of air/fuel mixture lighted by any amount of igniter (not shown) to light combustion chamber 240, and the type of described igniter is that affiliated field is well-known and be positioned in any amount of appropriate location.For example, wall 251 can be provided with opening (not shown), and igniter extends through described opening.Flame verifying attachment (not shown) can be positioned at appropriate location so that the existing of flame detection with any quantity.
Due to from compressor 230 and fuel delivery member 254 air without interruption and fuel to combustion chamber 240, (before the previous air/fuel mixture completing combustion in passage) spiral of air/fuel mixture is in the interior formation in fluid passage 274, to make spiral of air/fuel mixture radially layered in fluid passage subsequently.The spiral of air fuel mixture or rotation provide fully mixing of fuel and air, thereby improve burning.The helicon mode that is delivered to fuel air mixture contributes to combustion stability, and therefore reduces the chance of fire extinguishing.
As shown in Fig. 2 A-2B, exit rotatably combustion chamber 240 from the combustion product of the air/fuel mixture of lighting around the central axis 241 of combustion chamber 240 and the axis 202 of jet engine 200.The combustion product of air/fuel mixture exits combustion chamber 240 and passes turbine 220 at the pressure promoting and speed, thereby by turbine transmission rotation (as indicated with arrow R3 generally).Turbine 220 then by the combustion product jet engine 200 that leads out in the direction by arrow T sign on the whole, to provide thrust to arrive aircraft.Because turbine 220 is connected to rotatably compressor 230 by connecting elements 232, so the turbine driven compressor of rotation.
According to the present invention, each in direct fluid structure 248,252 has and is suitable for transmitting respectively any structure that rotates to compressed air D4, D3, thereby with fuel F1 and in fluid passage 274 interior formation air/fuel mixture, described mixture is around central axis 241 vortexs of combustion chamber 240.Fig. 3 A-3B shows a structure of the direct fluid structure 252 of inner tube 244, and it will be appreciated by those skilled in the art that, the direct fluid structure 248 of exterior tube 242 can have with direct fluid structure 252 similarly constructs.Alternatively, direct fluid structure 248 and 252 can be not similar (not shown).In any case, direct fluid structure 248 is configured to fluid radially inwardly to lead, and direct fluid structure 252 is configured to fluid radially outward to lead.
As shown in Fig. 3 A-B, direct fluid structure 252 comprises the multiple openings 284 in inner tube 244, to allow compressed air D3 radially outward to walk fluid passage 274 from the central passage 250 of inner tube.Each in opening 284 extends fully through inner tube 244 from inner surface 282 to outer surface 280.Each opening 284 can have any shape, such as rectangle, square, circle, triangle etc.Opening 284 all can have same shape or difformity.Opening 284 along the periphery circumference of inner tube 244 (, around) thus formation Infinite Cyclic aligned with each other.One or more Infinite Cyclic of opening 284 can be positioned to the adjacent one another are or each interval of length along inner tube 244.Each circulation can have any amount of opening 284.Opening 284 in adjacent circulation can be aligned with each other or can be offset with respect to each.Size, shape, structure and the aligning of inner tube 244 split sheds 284 depend on the compressed air D3 that flows through opening expectation flow and Performance Characteristics.Although opening 284 is depicted as with preassigned pattern and arranges along inner tube 244, will be appreciated that opening can locate arbitrarily (not shown) along inner tube.
Each opening 284 comprises corresponding direct fluid projection or guiding piece 286 so that by the compressed air D3 of the opening through being associated radially outward and be directed in certain direction in fluid passage 274, described direction is from the central axis 241 of combustion chamber 240 setover (, by not with the direction of described central axis intersection).Guiding piece 286 forms on the inner surface 282 of inner tube 244 and/or outer surface 280 (not shown) or entirety is attached to described inner surface 282 and/or outer surface 280.Each guiding piece 286 extends with respect to the outer surface 280 of inner tube 244 is angled (shown in Fig. 3 b).Guiding piece 286 can extend with equal angular or different angles with respect to the outer surface of inner tube 244 280.Each guiding piece 286 extends with the angle indicating with α 2 with respect to axis 287, and described axis 287 is perpendicular to the outer surface 280 of inner tube 244.
Because the direct fluid structure 248 in exterior tube 242 can be formed as being similar to the direct fluid structure 252 in inner tube 244, what it will be appreciated by those skilled in the art that is, the guiding piece being associated with guide frame 248 (not shown) and opening are by through the compressed air D4 of exterior tube radially inwardly and lead towards central passage 274 in certain direction, and described direction is setovered from the central axis 241 of combustion chamber 240.Be similar to the direct fluid structure 252 in inner tube 244, in exterior tube 242, the guiding piece of fluid guide frame 248 can form or entirety is attached to described inner surface and/or outer surface in the inner surface of exterior tube (not shown) and/or outer surface.In the illustrated embodiment, direct fluid structure 248,252 leads enter compressed air D4, the D3 that are associated on identical general direction, the air/fuel mixture that makes combination in fluid passage 274 around central axis 241 vortex on described identical general direction of combustion chamber 240.
Fig. 4 A-D shows according to the constructive alternative of direct fluid structure 252 in inner tube 244 of the present invention.Direct fluid structure 252a-d by the compressed air D3 entering radially outward and in a kind of direction, be directed in fluid passage 274, described a kind of direction: 1) setover from central axis 241, and 2) angled with respect to the normal direction of the outer surface 280 of inner tube 244, so that compressed air is mixed with fuel F1, thereby at the interior formation air/fuel mixture of central passage 274, described air/fuel mixture has around the vortex of central axis, rotate path, simultaneously with respect to described central axis radially layered.Submit to flowing and performance standard of expectation, the opening in direct fluid structure can be located arbitrarily or can arrange with any preassigned pattern along inner tube 244.
Fig. 4 A-D shows the constructive alternative of direct fluid structure 252,248 (it can form on the inner and/or outer surface of corresponding pipe 244,242 according to the present invention or entirety is attached to described inner and/or outer surface).More specifically, each in direct fluid structure 248,252 has any structure shown in Fig. 4 A-D.In a preferred embodiment, direct fluid structure 248 by the compressed air D4 entering radially inwardly and be directed in fluid passage 274 along a kind of direction, described a kind of direction: 1) setover from central axis 241, and 2) angled with respect to the normal direction of the inner surface of exterior tube 242 (not shown), thereby compressed air is mixed form air/fuel mixture with fuel F1, described air/fuel mixture has in central passage 274 and around vortex, the rotate path of central axis.Equally, direct fluid structure 252 radially outward and along a kind of direction is directed to the compressed air D3 entering in fluid passage 274, described a kind of direction: 1) setover from central axis 241, and 2) angled with respect to the normal direction of the outer surface 280 of inner tube 244 (not shown), thereby compressed air is mixed form air/fuel mixture with fuel F1, described air/fuel mixture has in central passage 274 and around vortex, the rotate path of central axis.In every kind of situation, submit to flowing and performance standard of expectation, the opening in direct fluid structure 248,252 can be located arbitrarily or can arrange with any preassigned pattern along corresponding pipe 242,244.
In Fig. 4 A, direct fluid structure 252a comprises multiple guiding piece 286a, and described guiding piece 286a limits the opening 284a in inner tube 244a.Guiding piece 286a is arranged in a series of rows, and described a series of rows extend around the periphery of inner tube 244a.Annular row is positioned to closer to each other along the length of inner tube 244a.Adjacent row's guiding piece 286a radial offset or can radially aim at each other (not shown) each other.Guiding piece 286a in each row can be similar or not similar each other.Guiding piece 286a will lead through the compressed air D3 of opening 284a in radially inner direction, and described direction is setovered and with respect to the angled α 2 of axis 287a, described axis 287a extends vertically up to the outer surface 280a of inner tube 244a from central axis 241.If the guiding piece 286a in row aims at each other wholly or in part around the periphery of inner tube 244a, the compressed air D3 of the each guiding piece in the row of exiting is further led in the direction of setovering from central axis 241 by the adjacent guiding piece in same row so.
In Fig. 4 B, inner tube 244b is formed as a series of scalariform things, and each scalariform thing comprises the first member 283 and second component 285, thereby described second component 285 extends and forms L shaped scalariform thing perpendicular to described the first member substantially.The second component 285 of each scalariform thing comprises the multiple opening 284b for compressed air D3 is led in a kind of direction, and described a kind of direction is setovered and angled with respect to the axis (not shown) of outer surface 280b that extends vertically up to inner tube 244b from central axis 241.Especially, opening 284b in each second component 285 leads compressed air D3 to rotation is delivered to compressed air across the first member 283 in abutting connection with scalariform thing, and is therefore delivered to the air/fuel mixture in fluid passage 274 around central axis 241.
In Fig. 4 C, direct fluid structure 252c comprises multiple opening 284c, and described opening 284c extends to outer surface 280c from the inner surface 282c of inner tube 244c.Opening 284c is to extend through inner tube 244c with respect to the angle of axis 287c, and described axis 287c extends vertically up to the outer surface 280c of inner tube 244c and the central axis 241 through combustion chamber 240.Opening 284c in inner tube 244c by compressed air D3 and therefore by the air/fuel mixture in fluid passage 274 setover from central axis 241 and with respect to the angled direction of axis 287c guiding to rotation is delivered to the air/fuel mixture in fluid passage around central axis.
In Fig. 4 D, direct fluid structure 252d is formed by a series of arc, overlapping plates 330, and described plate 330 cooperatively interacts to form inner tube 244d.Each plate 330 has corrugated contours, and described corrugated contours comprises cusp 332 and recess 334.Plate 330 is longitudinal and radial offset each other, is spaced apart between the cusp of adjacent panels with the cusp 332 that makes a plate 330.In this structure, the cusp of plate and recess 334 form passage 336, and compressed air D3 is directed through described passage 336.Each plate 330 by compressed air D3 be parallel to substantially in abutting connection with cambered plate extend direction on guiding to rotation be delivered to compressed air and be therefore delivered to the air/fuel mixture in fluid passage 274 around central axis 241.Thereby the air/fuel mixture in fluid passage 274 leads in a kind of direction, described a kind of direction is setovered and angled with respect to the axis (not shown) that extends vertically up to plate 330 from the central axis 241 of combustion chamber 240.
Fig. 5-6A shows jet engine 200a according to another embodiment of the invention.Feature in Fig. 5-6A identical with feature in Fig. 1-2 B has the Reference numeral identical with Fig. 1-2 B, but the feature not being similar in Fig. 5-6A of the feature in Fig. 1-2 B has been given tail tag " a ".Fig. 5-6A shows jet engine 200a, and described jet engine 200a is similar to the jet engine 200 of Fig. 1-2 B.In the jet engine 200a of Fig. 5-6A, the fuel of carrying via fuel conductor 254a partly mixed with air before being injected in region 274.Partly premixed fuel indicates with reference character F3, and as being clear that in Fig. 6 A, fuel conductor 254a is through premixed chamber 254'.As being clear that in Fig. 6 A, premixed chamber 254' receives the compressor air being indicated by reference character D5 by port (not illustrating particularly), and described port forms in described premixed chamber 254'.Mix with the air stream entering (D5) and be injected into region 274 through the fuel of chamber, state fuel in 274 places, described region and mix with other air D4, the D3 that carry by port 252,248, described port 252,248 forms respectively (seeing equally Fig. 2 B) in member 244,242.
The operation of the jet engine burner shown in Fig. 6 A is substantially similar to the burner shown in Fig. 2 A, except fuel closed with some air pre-mixing before being injected into region 274.The Move Mode of the fuel shown in Fig. 2 B and air is same can be applicable to the burner shown in Fig. 6 A.But, in the jet engine 200a of Fig. 5-6A, the fuel of being carried by fuel delivery member 254a before being discharged in chamber 274 with partly-premixed the closing of compressed air D5 that enter.This part of fuel mixture also mixes with compressed air D3 and D4, described compressed air D3 and D4 are injected through corresponding direct fluid structure 252 and 248 and enter fluid passage/combustion chamber 274', and the fuel loading thing mixing completely at described fluid passage/combustion chamber 274' place is lighted and burns.
Direct fluid structure 252 allows the air D3 in passage 250 to be radially outward directed in fluid passage 274, and direct fluid structure 248 allows the air D4 in the region 277 of exterior tube 242 outsides to be radially inwardly directed in fluid passage 274.Any in direct fluid structure 248,252 or two can have any structure shown in Fig. 3 A-4D.
Compressed air D3, D4 mix with the mixing portion fuel mixture F3 from fuel delivery member 254a, thereby at the interior formation air/fuel mixture of flow guide channel 274, described mixture is around axis 241 vortexs of combustion chamber 240a.Due to the structure of direct fluid structure 248, compressed air D4 is along with it is walked in fluid passage 274 and transmits centrifugal force around the axis 241 of combustion chamber 240a.Equally, compressed air D3 enters the inside 250 of inner tube 244 and passes subsequently the guide frame 252 of inner tube 244 and enter in fluid passage 274, thereby transmits centrifugal force by air/fuel mixture around the axis 241 of combustion chamber 240a.
What it will be appreciated by those skilled in the art that is, the mixture of air and fuel forms and transmits centrifugal force in fluid passage, described centrifugal force causes the air/fuel mixture in fluid passage 274 to rotate or vortex around the central axis of combustion chamber, therefore makes combustion modifications and stable.
Fig. 7-8 show jet engine 200b according to another embodiment of the invention.Feature in Fig. 7-8 identical with feature in Fig. 1-2 B has and Fig. 1-2 B or the identical Reference numeral of Fig. 5-6A, but the feature not being similar in Fig. 7-8 of the feature in Fig. 1-2 B has been given tail tag " b ".Be similar to the jet engine 200 of Fig. 1-2 B, wall 251b is secured to the end closer to compressor 230 of combustion chamber 240b and wall 255b and is secured to the end closer to turbine 220 of burner.But in the jet engine 200b of Fig. 7-8, fuel F4 mixes with compressed air D4' completely in the injected upstream of combustion chamber and before entering combustion chamber 240b.
The jet engine 200b of Fig. 7-8 comprises the fluid hybrid element 290 that is fastened to housing 210, so as by compressed air D4' and exit fuel delivery member 254b fuel F4 premixed so that air mixed completely before entering combustion chamber 240b with fuel.Fluid hybrid element 290 is positioned between fuel delivery member 254b and combustion chamber 240b along the axis 202 of jet engine 200b, and comprises outer member 292 and inner member 294 (they are positioned to each other and are concentric with connecting elements 232).Outer member 292 be annular and there is frusto-conical configuration substantially, described in be configured in (, as Fig. 8 observes left) in the direction of extending towards combustion chamber 240b and radially taper inwardly.Inner member 294 is positioned at the inside of outer member 292 and is fastened to outer member or forms with described outer member entirety.Compressor/turbine connecting elements 232 extends through the opening (indicating with reference character 294a generally) in inner member 294.
Annular gap 296 is being extended between inner member 294 and outer member 292 and is tapering inwardly in the direction of extending towards combustion chamber 240b, that is, gap reduces in the direction towards combustion chamber along the cross-sectional area of axis 202.Fluid hybrid element 290 be constructed such that from the compressed air D4' of compressor and exit the fuel F4 of fuel delivery member 254b must be through the gap 296 in hybrid element to arrive combustion chamber 240b.Because the cross-sectional area in gap 296 reduces along the length of fluid hybrid element 290, so compressed air D4' and fuel F4 are along with air and fuel are through fluid hybrid element and start to mix.Air D4' and fuel F4 exit fuel mix element 290 (indicating with M generally in Fig. 8) as the fully premixed mixture closing.Although being depicted as, fluid hybrid element 290 there is particular configuration, but those skilled in the art will appreciate that, can use to be configured to compressed air D4' and fuel F4 to mix and to form any or various structures of fully premixed mixture M of closing (entering combustion chamber 240b to be lighted).
Mixture M enters combustion chamber 240b along two different paths.Some in mixture M flow to region 277, be the outside (between the wall 216 and exterior tube 242 of housing 210) of combustion chamber 240b, the direct fluid structure 248 that is passed exterior tube 242 in described region 277 place's mixture M is radially inwardly directed in fluid passage 274.The remainder of mixture M flow in the inside 250 of inner tube 244, and the direct fluid structure 252 that is passed inner tube in described inner 250 place's mixture M is radially outward directed in fluid passage 274.Direct fluid structure 248,252 cause total mixture M be similar to the mode shown in Fig. 2 B around the axis 241 of combustion chamber 240b at fluid passage 274 inside vortex.Mixture M is lighted a fire by incendiary source (not shown) subsequently in fluid passage 274, and the combustion product of the mixture of lighting from combustion chamber 240b towards turbine 220 with generally with arrow R2 indicate mode discharge so that with describe mode drive turbine.
Fig. 9-11 show jet engine 200c according to another aspect of the present invention.In the jet engine 200c of Fig. 9-11, multiple combustion chamber 240c arrange around the central axis 202 of jet engine.Each non-premixed combustion chamber 240, the partly-premixed combination burning chamber 240a of Fig. 5-6B or fully premixed combination burning chamber 240b or their remodeling of Fig. 7-8 that can pie graph 1-2B in the 240c of combustion chamber.Feature in Fig. 9-11 identical with feature in Fig. 1-8 has the Reference numeral identical with Fig. 1-8, but the feature being similar in Fig. 9-11 of the feature in Fig. 1-8 has been given tail tag " c ".
As shown in Figure 9, compressor 230 and turbine 220 are positioned on the opposite side of housing 210 240c of inner combustion chamber.Combustion chamber 240c is preferably aligned axially to each other and around axis 202 spaced radials (Fig. 9) of jet engine 200c.Although five combustion chamber 240c have been shown in Fig. 9-11, have will be appreciated that more or less combustion chamber can be set according to the present invention.In addition, combustion chamber 240c can be around central axis 202 symmetrically or asymmetricly spaced apart.Combustion chamber 240c can be parallel to substantially extend with axis 202 each other or can be relative to each other and/or described axis angularly extend.Wall 270 is arranged between the wall 212 of housing 210 and combustion chamber 240c and between described combustion chamber, to guarantee that fluid only flow in combustion chamber, not around combustion chamber or between combustion chamber and the wall of described housing.Other wall 272 is also preferably set to prevent air or fuel/air mixture bypass combustion chamber.Wall 270,272 also can be used as installing plate or the support member for combustion chamber 240c.
Combustion chamber 240c is different from the combustion chamber 240,240a, the 240b that wherein do not use inner tube.The exterior tube 242' of combustion chamber has direct fluid structure 248, enters inner 274' to the mixture of air and fuel is radially inwardly guided through to direct fluid structure from fluid passage 277'.In this structure, each combustion chamber 240c comprises firm outer wall 297, and described outer wall 297 has continuous surface to make there is no fluid radially through it.It is upper to fluidly seal the upstream extremity closer to the pipe 242 of turbine 200 that lid 251c is arranged on each combustion chamber 240c, so that air and/or fuel/air mixture can not axially enter the passage 274' of combustion chamber 240c, air and/or fuel mixture must be radially inwardly through direct fluid structure 248' and enter in the 274' of inner passage.The downstream of circular passage 277' is by lid 257a sealing, and this guarantees that all air (or fuel-air mixture) flow in burning gallery 274'.
The air that exits combustion chamber 230 is distributed among the 240c of combustion chamber.Air and the fuel mix of being carried by fuel conductor 254c and final vortex and burning in internal-combustion chamber 274'.Multiple method and apparatus for injecting fuel into burner 240c have been shown in Figure 10.Fuel conductor 254c illustrates with solid line, and in solid line structure, fuel is ejected into the upstream of combustion chamber 240c, mixes (as in conjunction with Fig. 7,8A and 8B description) at described upstream end fuel with the air of being carried by compressor 230 completely.This fuel/air mixture tote mixing completely enters subsequently region 277' and flow in burning gallery 274' via the port 248 forming in tubular element 242'.As explained above, port arrangements becomes to cause fuel/air mixture rotation in burning gallery 274'.
In alternative, each combustion chamber 240c has adopted the fuel/air mixture induction system in conjunction with Fig. 5 and 6A description.Fuel conductor 254c' comprises premixed chamber 254 ".In this structure, the fuel of being carried by fuel conductor 254c' is with by premixed chamber 254, " air receiving from compressor 230 partly mixes.This part of fuel mixture is passed and covers 251c and be ejected in chamber 274', state part of fuel mixture in described chamber 274' place and mix completely with compressed air D6, described compressed air D6 is via passage 277' and enter chamber 274' via the port 248 forming in tubular element 242' subsequently.
In yet another embodiment, combustion chamber 240c has adopted the fuel/air mixture induction system of describing in conjunction with Fig. 1 and 2 A.In this structure, fuel is directly injected in burning gallery 274' via fuel conductor 254c, and the downstream of described fuel conductor 254c extends through covers 251c.The fuel spraying mixes with the vortex air of carrying by tubular element 242'.
In all these embodiment, the igniter (not shown) in the inside 274' of the pipe component 242' of each combustion chamber 240c is lighted vortex air/fuel mixture.Eddy combustion product jointly exits combustion chamber 240c and passes turbine 220, thereby causes the rotation of turbine and combustion product to be discharged from jet engine 200c.
Due to multiple reasons, be favourable for the combustion chamber of the present invention using at jet engine than conventional combustion chamber or burner.Unlike conventional combustion chamber, (its Flame is mainly to propagate into reactant (by the molecular heat conduction from flame and molecule free radical (radical) diffusion, air/fuel mixture) approach in stream), combustion chamber of the present invention forces additional heat by transmitting from convection current and radiation overlapping with the air/fuel mixture entering and the mutual high speed flame envelope mixing.The preheated while flame region of air/fuel mixture entering is cooled, and this advantageously helps to reduce NO
x.Free radical is also by the flame envelope reaction logistics to entering forced to move overlapping and that mix.In the mixture of reactant, the existence of free radical reduces firing temperature and allows fuel to burn in subnormal temperature.It also helps significantly to increase flame speed (this is with regard to Reaction time shorten), thereby reduces in addition NO
xformation, improve flame holding/flame retentivity simultaneously significantly.Improved stability and flame retentivity have reduced the chance of fire extinguishing.
Due to the superior flame retentivity/stability of combustion chamber of the present invention, can be in very high combustion load operation.High capacity allows burner with stable " lifting flame " pattern (, flame and combustor surface are spaced apart) operation.Flame lifting is by this way that expectation combustor surface is not directly received heat, thereby makes described surface remain on lower temperature and the probable life of combustion chamber is increased.For given application, that high combustion load also allows to use is less, joint space-efficient and combustion chamber more cheaply.In addition, due to superior as described above flame retentivity, combustion chamber of the present invention can also be under very high-caliber excess air (low CO) operation cleanly, the NO of this generation
xlevel far below by conventional combustion chamber obtainable those.
The preferred embodiments of the present invention have been shown specifically and have described.But the present invention can not be considered to be limited to disclosed accurate structure.For example, will be appreciated that, by the described wall 251c (shown in Fig. 9) that is fastened to inside and outside pipe is configured to move along the axis of jet engine, above-described any combustion chamber all can comprise the combustion chamber of " variable volume ", for example fluid passage.This structure will be by making combustion chamber volume mate and allow best combustion performance with needed power stage.
The present invention describes in detail in conjunction with jet engine application.One of ordinary skill in the art will recognize that, principle of the present invention can be applied in the burner for example, using in heater (, boiler, stove and boiler).One of ordinary skill in the art will recognize that, disclosed burner configuration can be suitable for using in the heating application being equal to.For some application, burner will be constructed to dynamic combustion device (power burner), wherein air blast or suitable device will force air to enter burner, and in described burner, air will for example, for example, mix with suitable liquid fuel (fuel oil) or gaseous fuel (natural gas or propane).
Technical staff in the field the present invention relates to can expect various adjustment of the present invention, remodeling and use, and the present invention will cover all this adjustment, remodeling and the use in the spirit or scope that fall into claims thus.
Claims (27)
1. a jet engine, it comprises:
Housing, described housing has first end and the second end and extends to the inner passage of described the second end from described first end;
Compressor, described compressor is positioned in the first end of described inner passage;
Turbine, described turbine is positioned in the second end of described inner passage; And
Combustion chamber, described combustion chamber is positioned in described inner passage between described compressor and described turbine, and described combustion chamber is extended and comprises along central axis:
Exterior tube, described exterior tube has outer surface and limits the inner surface of passage;
Inner tube, described inner tube is positioned in the passage of described exterior tube and has outer surface and limit inner inner surface, wherein, fluid passage is limited between the outer surface of described inner tube and the inner surface of described exterior tube, described fluid passage is supplied the mixture with air and combustible fuel, described inner tube and described exterior tube there is direct fluid structure so as to make air in described fluid passage and the mixture of combustible fuel around described central axis radial rotary.
2. for a combustion chamber for jet engine, described jet engine has compressor section and turbine part, and described combustion chamber comprises:
A) have the exterior tube of central axis, described exterior tube is extending longitudinally and be positioned to receive air and the described exterior tube of being discharged by described compressor section and have outer surface and inner surface;
B) be positioned at the inner tube in described exterior tube, described inner tube has the isolated outer surface of described inner surface with described exterior tube, thereby is limited to the combustion chamber passage between it;
C) described exterior tube comprise direct fluid structure in case by discharged by described compressor section airborne at least some is communicated in described combustion chamber passage, described air is being directed to from the direction of described central axis biasing, thereby causes described air to rotate around described central axis;
D) at least one fuel delivery member, described at least one fuel delivery member forms the fuel air mixture rotating for supplying fuel to described combustion chamber passage so that at described combustion chamber passage.
3. combustion chamber as claimed in claim 2, wherein, described inner tube comprise the direct fluid structure that is associated in case by the air communication of being discharged by described compressor section to described combustion chamber passage, described in the direct fluid structure that is associated described air is being led from the direction of described central axis biasing.
4. combustion chamber as claimed in claim 1, wherein, described fuel component and described combustion chamber channel connection and directly supply fuel to described combustion chamber passage, thus mixes at described combustion chamber passage place fuel combustible fuel/air mixture that formation is rotated with described compressor air.
5. combustion chamber as claimed in claim 2, wherein, described fuel component is by described fuel and some compressor air premixed and subsequently described premixed fuel and air are fed to described combustion chamber passage, states premixed fuel and air mixes with the compressor air of the rotation in described combustion chamber passage in described combustion chamber passage place.
6. device as claimed in claim 2, wherein, described fuel component is by fuel draining to by described compressor discharge and in the mobile air stream of described exterior tube, and by fuel and compressor air, the two is all communicated to described combustion chamber passage to the described direct fluid structure of described exterior tube.
7. device as claimed in claim 1, wherein, the described central axes of the axis of described inner tube and described exterior tube.
8. device as claimed in claim 7, wherein, the described axis of described inside and outside pipe also overlaps with the rotation of described compressor section.
9. for a combustion chamber for jet engine, described jet engine has compressor section and turbine part, and described compressor comprises:
A) have the pipe of central axis, described pipe is positioned in the middle of described compressor section and described turbine part, and described pipe has outer surface and inner surface;
B) the direct fluid structure forming on described pipe, it comprises the passage that extends to described inner surface from described outer surface;
C) the described inner surface of described pipe limits combustion chamber;
D) passage, described passage is communicated with the air being discharged by described compressor section with the described outer surface of described pipe, to compressor air is transported to described combustion chamber by described direct fluid structure, described direct fluid structure is the angle guiding to setover from described central axis by described compressor air, thereby causes rotating at compressor air described in described combustion chamber;
E) fuel component, described fuel component is used for supplying fuel to described combustion chamber.
10. device as claimed in claim 9, wherein, isolated continuous wall is around described pipe, thereby limit described passage at least a portion in case by air communication the described outer surface to described pipe.
11. devices as claimed in claim 10, wherein, described jet engine comprises multiple described combustion chambers, multiple described combustion chambers are arranged around the rotation space being limited by described compressor section.
12. devices as claimed in claim 2, wherein, the completing combustion substantially in described combustion chamber passage of the fuel air mixture of described rotation.
13. combustion chambers as claimed in claim 2, wherein, the guiding piece that described direct fluid structure comprises multiple openings and is associated with each opening, described guiding piece is angled to make described mixture around described central axis radial rotary with respect to the surface of described pipe.
14. fuel burners as claimed in claim 13, wherein, described guiding piece is arranged in a series of row who extends around the periphery of described exterior tube.
15. combustion chambers as claimed in claim 2, wherein, described direct fluid structure comprises a series of scalariform things that are formed in described exterior tube, described scalariform thing comprises opening, and described opening is used for air guide to described combustion chamber passage to make described mixture radially around described central axis rotation.
16. combustion chambers as claimed in claim 15, wherein, each scalariform thing has L shaped, described L shaped the first member and the second component of comprising, described second component comprises opening, and described opening is for leading air air guide to rotation is delivered to described mixture across the scalariform thing of adjacency with the opening that makes a scalariform thing.
17. combustion chambers as claimed in claim 2, wherein, described direct fluid structure comprises multiple openings, the each outer surface from described exterior tube of described multiple opening extends to described inner surface, each opening angularly extends through described exterior tube with respect to an axis, and a described axis extends and through described central axis in the normal direction of the outer surface of described inner tube.
18. combustion chambers as claimed in claim 17, wherein, described exterior tube comprises multiple the second openings, described multiple the second openings are each extends to described inner surface from the outer surface of described exterior tube in the direction that extends to described central axis.
19. combustion chambers as claimed in claim 2, wherein, described exterior tube is formed as limiting a series of overlapping cambered plate of described direct fluid structure, each plate has corrugated contours, described corrugated contours has series of passages, and air is directed in described combustion chamber passage through described series of passages.
20. combustion chambers as claimed in claim 19, wherein, described corrugated contours comprises multiple cusps that replace and recess.
21. combustion chambers as claimed in claim 20, wherein, described overlapping plates is longitudinal and radial offset each other, so that the cusp of a plate is positioned between the cusp of adjacent panels.
22. combustion chambers as claimed in claim 19, wherein, in each plate extends air direction being arranged essentially parallel to adjacent plate, guiding is to be delivered to mixture by rotation.
23. combustion chambers as claimed in claim 3, wherein, described inner tube comprises first end and the second end, described first end and the air communication of being discharged by described compressor section, described the second end there is end wall in case by the second end of described inner tube with air tight manner closure, be provided to unique fluid path of described combustion chamber passage from the described air that described compressor section was received with the direct fluid structure being associated described in the making described inner tube of serving as reasons.
24. combustion chambers as claimed in claim 2, wherein, described rotation mixture is radially layered in described combustion chamber passage.
25. 1 kinds for making the method for fuel combustion of jet engine, and described jet engine has compressor section and turbine part, and described method comprises the steps:
A) provide the pipe with outer surface and inner surface, described outer surface and the air communication of being discharged by described compressor section, described inner surface limits combustion chamber at least in part;
B) in described and between outer surface, provide direct fluid structure, so that the central axis with respect to described pipe is angularly communicated to described combustion chamber by described compressor air from described outer surface, to cause described air to rotate in described combustion chamber;
C) supply fuel to described combustion chamber thereby the fuel/air mixture of vortex is provided;
D) the described fuel air mixture in described combustion chamber is burnt at least in part;
E) fuel/air mixture of described burning is fed to described turbine part.
26. methods as claimed in claim 25, are also included in the step that inner tube is provided in described exterior tube, so that described combustion chamber is limited between the outer surface of described inner tube and the inner surface of described exterior tube.
27. methods as claimed in claim 26, also comprise that the direct fluid structure by being associated is directed to compressor air the step of the outer surface of described inner tube from the inner surface of described inner tube, described direct fluid structure in described combustion chamber is delivered to rotation described compressor air along with described compressor air is sent to.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US201161522412P | 2011-08-11 | 2011-08-11 | |
| US61/522,412 | 2011-08-11 | ||
| PCT/US2012/050349 WO2013023147A1 (en) | 2011-08-11 | 2012-08-10 | Combustor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103998867A true CN103998867A (en) | 2014-08-20 |
Family
ID=47668992
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201280050137.7A Pending CN103998867A (en) | 2011-08-11 | 2012-08-10 | Combustor |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20140190178A1 (en) |
| EP (1) | EP2742292A4 (en) |
| CN (1) | CN103998867A (en) |
| CA (1) | CA2844693A1 (en) |
| WO (1) | WO2013023147A1 (en) |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104373962A (en) * | 2014-10-28 | 2015-02-25 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Blade type air inlet swirl nozzle for combustion chamber of gas turbine |
| CN110741205A (en) * | 2016-11-22 | 2020-01-31 | 贝克特瓦斯公司 | Burner with a burner head |
| KR20230106246A (en) * | 2022-01-06 | 2023-07-13 | 두산에너빌리티 주식회사 | Nozzle for combustor, combustor, and gas turbine including the same |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US10634354B2 (en) | 2011-08-11 | 2020-04-28 | Beckett Gas, Inc. | Combustor |
| US9541292B2 (en) | 2013-03-12 | 2017-01-10 | Pratt & Whitney Canada Corp. | Combustor for gas turbine engine |
| US9366187B2 (en) | 2013-03-12 | 2016-06-14 | Pratt & Whitney Canada Corp. | Slinger combustor |
| US9228747B2 (en) | 2013-03-12 | 2016-01-05 | Pratt & Whitney Canada Corp. | Combustor for gas turbine engine |
| US9127843B2 (en) | 2013-03-12 | 2015-09-08 | Pratt & Whitney Canada Corp. | Combustor for gas turbine engine |
| US9958161B2 (en) | 2013-03-12 | 2018-05-01 | Pratt & Whitney Canada Corp. | Combustor for gas turbine engine |
| CN110440290B (en) * | 2018-05-02 | 2024-03-29 | 中国联合重型燃气轮机技术有限公司 | Micro-mixing nozzle for gas turbine |
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| US20040148936A1 (en) * | 1999-12-15 | 2004-08-05 | Koji Moriya | Fluid distributor, burner apparatus, gas turbine engine and co-generation system |
| US20070028624A1 (en) * | 2005-07-25 | 2007-02-08 | General Electric Company | Mixer assembly for combustor of a gas turbine engine having a plurality of counter-rotating swirlers |
| CN101382297A (en) * | 2007-09-05 | 2009-03-11 | 斯奈克玛 | Gas turbine combustion chamber with helicoidal air circulation |
| US20110097189A1 (en) * | 2007-12-31 | 2011-04-28 | Aaron Sandoval | Boundary layer effect turbine |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104373962A (en) * | 2014-10-28 | 2015-02-25 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Blade type air inlet swirl nozzle for combustion chamber of gas turbine |
| CN104373962B (en) * | 2014-10-28 | 2016-08-24 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of gas-turbine combustion chamber blade Inlet Swirl nozzle |
| CN110741205A (en) * | 2016-11-22 | 2020-01-31 | 贝克特瓦斯公司 | Burner with a burner head |
| CN110741205B (en) * | 2016-11-22 | 2021-01-26 | 贝克特瓦斯公司 | Burner with a burner head |
| KR20230106246A (en) * | 2022-01-06 | 2023-07-13 | 두산에너빌리티 주식회사 | Nozzle for combustor, combustor, and gas turbine including the same |
| KR102583222B1 (en) | 2022-01-06 | 2023-09-25 | 두산에너빌리티 주식회사 | Nozzle for combustor, combustor, and gas turbine including the same |
| US11898754B2 (en) | 2022-01-06 | 2024-02-13 | Doosan Enerbility Co., Ltd. | Combustor nozzle, combustor, and gas turbine including the same |
Also Published As
| Publication number | Publication date |
|---|---|
| EP2742292A4 (en) | 2015-08-12 |
| EP2742292A1 (en) | 2014-06-18 |
| WO2013023147A1 (en) | 2013-02-14 |
| US20140190178A1 (en) | 2014-07-10 |
| CA2844693A1 (en) | 2013-02-14 |
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Application publication date: 20140820 |