US3788065A - Annular combustion chamber for dissimilar fluids in swirling flow relationship - Google Patents

Annular combustion chamber for dissimilar fluids in swirling flow relationship Download PDF

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US3788065A
US3788065A US00084086A US3788065DA US3788065A US 3788065 A US3788065 A US 3788065A US 00084086 A US00084086 A US 00084086A US 3788065D A US3788065D A US 3788065DA US 3788065 A US3788065 A US 3788065A
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annular passage
fluid
rho
duct
fluids
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S Markowski
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RTX Corp
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United Aircraft Corp
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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
    • F23R3/34—Feeding into different combustion zones
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/38—Introducing air inside the jet
    • F02K1/386—Introducing air inside the jet mixing devices in the jet pipe, e.g. for mixing primary and secondary flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02G—HOT GAS OR COMBUSTION-PRODUCT POSITIVE-DISPLACEMENT ENGINE PLANTS; USE OF WASTE HEAT OF COMBUSTION ENGINES; NOT OTHERWISE PROVIDED FOR
    • F02G2243/00—Stirling type engines having closed regenerative thermodynamic cycles with flow controlled by volume changes
    • F02G2243/30—Stirling type engines having closed regenerative thermodynamic cycles with flow controlled by volume changes having their pistons and displacers each in separate cylinders
    • F02G2243/50—Stirling type engines having closed regenerative thermodynamic cycles with flow controlled by volume changes having their pistons and displacers each in separate cylinders having resonance tubes
    • F02G2243/52—Stirling type engines having closed regenerative thermodynamic cycles with flow controlled by volume changes having their pistons and displacers each in separate cylinders having resonance tubes acoustic
    • 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

Definitions

  • FIG-37 Pmgmmmzsmm 3,788,065
  • This invention relates to the controlled mixing of two thermodynamically and aerodynamically dissimilar fluids and particularly to the use of swirling flow between two dissimilar fluids in annular combustion chambers, such as the burners and afterburners of turbine engines, to accelerate both the combustion process and the temperature reduction process of the products of combustion in the dilution zone of the burner.
  • This recirculation zone is formed because the angular momentum of the air is proportional to the tangential velocity V, thereof times the radius of the air particle involved from the burner central'axis, accordingly, any air which is at or near the burner axis is of minimal or zero radius so that the tangential velocity attempts to go to infinity with the result that nonswirling secondary air is brought in around the recirculation zone for mixing with the stagnated fuel-air mixture downstream ofthe recirculation zone and for cooling the walls of the combustion chamber, as typically shown in U.S. Pat. No. 3,498,055.
  • can burners because of their cylindrical shape, or can-annular burners, because they have a series of can-shaped inlet sections opening into an annular main section.
  • the momentum-velocity system of establishing a recirculation zone is used in the can portion of both.
  • the momentum-velocity system of establishing a recirculation zone does not work in an annular combustion chamber because all combustion stations are of substantial radius and therefore I utilize the interdigitation of the swirling sheets of dissimilar fluids to perform this function.
  • swirling flow is generally discouraged in conventional combustion chambers and straightening vanes are provided for this purpose.
  • a primary object of the present invention is to provide an improved annular combustion chamber by establishing, controlling and/or varying the product parameter pVF, where p is fluid density and V, is fluid tangential velocity, between two dissimilar swirling fluids to establish an unstable interface therebetween to accelerate mixing and hence combustion in the combustion zone and mixing and hence coolingin the dilution zone of the combustion chamber.
  • this product parameter is established, controlled and/or varied so that the product parameter of the fluid which is flowing at the lesser radius about the combustion chamber axis is greater than the product parameter of the fluid which is flowing at the greater radius, so that the mixing ratio in the combustion chamber is determined by the ratio pV, (inner flow) pV, (outer flow).
  • the interface between two dissimilar swirling combustion chamber fluids are established or controlled so that outside-inside burning occurs in the combustion chamber.
  • the invention permits accelerated mixing and combustion or accelerated mixing and dilution to occur in several annular combustion chamber configurations, for example, in the concentric flow mixer configuration, the barberpole mixer configuration, and the bent tube or folded combustion chamber mixer configuration.
  • a combustion chamber can be fabricated so as to consist of a combustion zone and a dilution zone with either or both of these zones utilizing a concentric mixer, a barberpole mixer, or a bent tube mixer and any of these mixers can be used with a conventional combustion zone or dilution zone.
  • combustion can take place utilizing either the premixed or diffusion principle.
  • hardware is provided to establish, control or vary the orientation of two concentric fluid streams of different thermodynamic and aerodynamic states in such a way that the product parameter density, p, of the inner stream times the tangential velocity V, of the inner stream is greater than the corresponding product parameter of the outer stream.
  • compound mixing in radial, parallel staging occurs both in the combustion zone and the dilution zone of an annular combustion chamber in which the combustion zone and the dilution zone are axially staged in series so as to reduce the overall length of the combustion chamber and hence the engine length and weight.
  • triggers are used to disturb the unstable interface between two swirling streams to accelerate mixing and either combustion or cooling therebetween.
  • a combination flameholder and/or trigger can be used in a swirling flow annular combustion chamber to accelerate mixing and burning of the products of combustion from the recirculation zone established downstream of the flameholder and the fuel-air mixture passing around the flameholder.
  • swirling fluid interface trigger mechanisms are provided in the form ofa corrugated and tapered rings,
  • combustion apparatus in which combustion or dilution zones are located in series in which mixing occurs in both zones at parallel radial stations.
  • the unstable interface between two swirling streams of fluid which are established by the product parameter criterion taught herein can be physically interrupted or disturbed by a variety of trigger mechanisms.
  • swirling flow in an annular combustion chamber invites the use of flameholders therein and the use of a substantial variety of fuel injecting devices to be used therewith.
  • FIG. 1 is a schematic representation of two dissimilar fluids flowing in swirling relationship in separated coannular passages and then joining and mixing in a single annular passage.
  • FIG. 2 is a schematic showing in cross-section of the FIG. 1 flow representation.
  • FIG. 3 is a vector diagram of the fluid flowing in swirling fashion in the FIG. 1 and 2 environment and the other environments disclosed herein.
  • FIG. 4 is a showing of the static pressure distribution across the outer and inner swirling fluid flows of the FIG. 1 and 2 environment.
  • FIG. 5 is a schematic representation of mixing occuring in two fluid streams flowing in side-by-side relationship and which are caused to swirl in passing through a bent tube.
  • FIG. 6 is a schematic cross-sectional showing of a barberpole swirl mixer.
  • FIG. 7 is an end view taken along line 7-7 of FIG. 6.
  • FIG. 8 is a showing of an annular combustion chamber concentric mixer utilizing the premixed burning principle.
  • FIG. 9 is similar to FIG. 8 but utilizing the diffusion burning principle.
  • FIG. 10 is a cross-sectional showing of an annular combustion chamber barberpole mixer used in the combustion zone and utilizing the premixed burning principle.
  • FIG. 11 is similar to FIG. 10 but utilizing the diffusion burning principle.
  • FIG. 12 is a showing of a premixed combustor employing bent tube mixing in a folded combustion chamber which is preferably of the annular type.
  • FIG. 13 is a showing of a modern turbine engine of the type used in the modern aircraft and shown utilizing my invention.
  • FIG. 14 is a cross-sectional showing of an annular combustion chamber using a concentric mixer in both the combustion zone and the dilution zones.
  • FIG. 15 is a showing of a vane of an annular vane cascade and its actuating mechanism to make the cascade variable angle so as to vary the angle at which the gases passing therethrough are discharged.
  • FIG. 16 is a cross-sectional showing of an annular combustion chamber using a barberpole mixer in both the combustion zone and dilution zones thereof.
  • FIG. 17 is taken along line 17l7 of FIG. 16.
  • FIG. 18 is an enlarged, unrolled showing of the combustion chamber outer liner of FIG. 16 to illustrate the orientation of the outer liner helical slots in the barberpole mixer of the dilution zone.
  • FIG. 19 is a cross-sectional showing of the vaned, helical slots use in the inner Wall of the dilution zone mixer of FIG. 16 and is taken along line l919 of FIG. 16.
  • FIG. 20 is a modification of the helical slots shown in FIG. 18 and can be used in the barberpole mixer either in the combustion zone or the dilution zone of an annular combustion chamber.
  • FIG. 21 is a cross-sectional showing of an annular combustion chamber having axially staged combustion and dilution zones and utilizing a concentric mixer in the combustion zone and a barberpole mixer in the dilution zone.
  • FIG. 22 is a cross-sectional showing of an annular combustion chamber having a conventional combustion zone and dilution zone of the folder burner or bent tube variety utilizing my invention.
  • FIG. 23 is a modification of the primary combustor portion of the combustion zone mixer shown in FIG. 14.
  • FIG. 24 is a modification of the concentric mixer used in the combustion zone of an annular combustion chamber which may be substituted for the type shown in FIG. 14.
  • FIG. 25 is an enlarged, partial, cross-sectional showing of the flameholder member taken along line 25-25 of FIG. 24.
  • FIG. 26 is a showing ofa modification of the combustor shown in FIG. 25.
  • FIG. 27 is an enlarged showing of the FIG. 26 construction taken along line 27 of FIG. 26.
  • FIG. 28 corresponds to FIG. 27 and shows the secondary flow patterns between the helical guide vanes.
  • FIG. 29 is still another modification for the primary combustion chamber shown in FIG. 14.
  • FIG. 30 is a schematic representation of two swirling fluids flowing through annular passages with a splitter duct therebetween and with a trigger mechanism attached to the downstream end of the splitter duct.
  • FIG. 31 is an end view of the FIG. 30 construction.
  • FIG. 32 is a cross-sectional showing of a trigger mechanism which may be substituted for the trigger mechanism shown in the splitter duct of FIG. 14.
  • FIG. 33 is a showing ofthe trigger mechanism of FIG. 32 shown with the splitter duct unrolled for purposes of better illustration.
  • FIG. 34 shows another modification of trigger mechanism of FIG. 14.
  • FIG. 35 is a showing of a further trigger mechanism modification utilizing plural rows or patterns of helical slots in or near the trailing edge of a splitter duct.
  • FIGS. 36 and 37 are plan and end views of still another trigger mechanism modification of the variety which utilizes both a helically slotted and helically corrugated downstream end on a splitter duct to perform their swirling fluid interface triggering function's.
  • FIG. 38 is a showing of still another trigger mechanism modification utilizing a combination of helical slots and scooped projections cooperating therewith at the downstream end of a splitter duct to accelerate mixing.
  • FIG. 39 is a representation of irregular trigger corrugation utilized for the purpose of noise suppression.
  • FIGS. 40 and 41 depict annular combustion chamber flow passage modifications which can be used because of the swirling flow therethrough to retard or prevent flow separation of the boundary layers along the diffuser walls.
  • FIGS. 42a and 4212 are showings of an annular combustion chamber utilizing swirl flow and further utilizing a compound vane cascade at the inlet thereof to control the amount of swirling at the various radial stations across the cascade so as to discourage boundary layer flow separation and permit the utilization of shortened diffuser section in the combustion chamber, thereby reducing the length of the combustion chamber.
  • FIGS. 43 and 44 are showings of the axial velocity profile and tangential velocity profile of the air immediately downstream of the cascade of compound vanes of FIG. 42.
  • FIG. 45 is a cross-sectional showing of a scoopedaperture which may be used with trigger mechanisms, such as those shown in FIG. 14.
  • FIGS. 46 thru 48 are showings of annular combustion chambers utilizing radially staged combustion for reduced combustion chamber and engine length and having provisions for engine power performance control.
  • dissimilar fluids means fluids which are thermodynamically and aerodynamically dissimilar. This phenomenon of interest and its characteristics will now be described by referring to FIGS. 1 and 2.
  • two dissimilar fluids are flowing in concentric swirling flow patterns and are isolated initially by a cylindrical separator wall 10, which is positioned between cylindrical ducts l2 and 14 so that walls 10, 12 and 14 are concentric about centerline or axis 16 and cooperate to define concentric annular passages 18 and 20. While the outer fluid will be described as the hot fluid and the inner fluid the cold fluid, this does not have to be the case.
  • interface 24 is established therebetween.
  • the velocity of each fluid may be represented by the flow vector diagram shown where V, is axial velocity, V, is tangential velocity and V is actual velocity in the indicated direction.
  • Fluid flowing in such a manner comes under the primary influence of two forces of significant magnitude, namely, centrifugal forces and forces due to the pressure gradient which exists in the duct through which the fluid is flowing.
  • centrifugal force, F is proportional to the mass of the fluid, and consequently the density, p, of the fluid, and the square of the tangential velocity or tangential velocity component V,, of the fluid.
  • the pressure gradient force, F,, is proportional to the radial pressure gradient and results from the radial difference in static pressure across the radially projected area of the fluid element.
  • the relative magnitude of the unbalanced forces just described may be assessed by considering the outer fluid as a combusted gas from a combustion chamber which typically would lower the density by a factor of perhaps four relative to the unvitiated innerstream. Since the tangential velocity of the gas in a typical combustor pilot will change relatively to a smaller magnitude, the unbalanced force is seen to be three-quarters or more of the maximum centrifugal force on the two fluids. This magnitude of the unbalanced force is decidedly first order and represents a large acceleration potential available to expedite the radial movement of the two concentric fluids into a helical sheet mode of flow.
  • My invention is the utilization of this phenomenon in accelerating mixing between two dissimilar swirling fluids in annular combustion chambers of the type used in turbine engines to both accelerate combustion and accelerate the dilution ofthe hot products of combustion with cooling air before passage through the turbine.
  • This accelerated mixing can also be established by use of the barberpole swirl mixer 80 shown in FIGS. 6 and 7.
  • the term barberpole is selected to describe this mixer because it causes the two dissimilar fluids to form into a series of interdigitated, swirling sheets or fingers.
  • This mixer consists of outer wall 82 and inner wall 84 which preferably diverge to form diverging passage 86 through which the swirling main fluids flow and which have selectively oriented helical slots 88 and 90 extending therethrough, respectively, through which the secondary fluids flow and are caused to enter parallel to the main stream flow.
  • the direction of helical slots 88 and 90 are such that they are locally parallel to the direction of the swirling main flow.
  • the product parameter flow criterion pV, inner secondary pV, main flow and pV, outer secondary pV, main flow are attained.
  • the sheets of secondary flow will penetrate rapidly across the main flow because the same mixing phenomenon previously described in connection with the FIGS. 1 and 2 construction occurs here between each swirling fluid sheet and the two swirling sheets of dissimilar fluids adjacent thereto. Accordingly, total required mixing will occur more rapidly.
  • the main flow is preferably hot air and the secondary flows are cooler air and the slots 88 and 90 are oriented to bring about not only helical flow but helical flow substantially parallel to the main flow direction.
  • any of these mixers that is, the concentric mixer, barberpole mixer and the bent tube mixer can be effectively utilized in the combustion zone of a combustor or burner to increase the rate of mixing and hence rate of combustion and effective flame speed so as to reduce overall burner length as illustrated in FIGS. 8-12.
  • the reference numerals of FIGS. 1, 2, 6 and 7 will be repeated in describing the FIGS. 8-12 constructions.
  • one of the swirling streams is used as a hot pilot to initiate combustion in the other swirling stream, which is a fuel-air mixture. Burning occurs when the two streams mix.
  • the pilot stream should be the outer stream because the density depression caused by heating helps in achieving the desired interfaced instability criteria pV, inner pV, outer.
  • the choice of which stream will act as the heated pilot is not as obvious.
  • the pilot stream should be one of the streams requiring a low pV, product parameter and hence the pilot stream should not be the secondary flow in inner passage 114.
  • the main stream 112 should be chosen as the pilot stream to avoid the severe wall cooling problems which would be caused by injecting a hot gas secondary stream from passage 112 along outer walls 82.
  • the product parameter pV, for the outer secondary fluid can be made smaller than the product parameter pV, of the pilot to obtain the desired rapid mixing by permitting little or no tangential velocity V, as it passes through slots 88.
  • the desired interface instability criteria between the pilot flow from passage 112 and inner secondary flow from the passage 114 is satisfied by the use of the required turning vanes or the like to adjust the tangential velocity (V,) level to satisfy the required criteria pV, inner pV, pilot.
  • the combustion process in the pilot decreases the density of this stream thereby assisting in satisfying this criteria.
  • FIG. 8 depicts a concentric mixer in a combustion chamber combustion zone where concentric passages 18 and are formed between concentric ducts 12, 10 and 14 and wherein splitter duct 10 terminates short of the outer ducts so that the outer ducts form combustion zone 30 downstream thereof.
  • Appropriately positioned inlet guide vanes or other mechanisms cause swirling fluid to pass through each of passages 18 and 20.
  • the flow in passage 20 serves as the pilot combustion stream in that pilot fuel is injected thereinto through pilot fuel nozzle mechanism 92 which sprays atomized fuel into the fluid passing therethrough just upstream of flameholder 94 to form pilot combustion zone 96 downstream thereof wherein the fuel-air mixture is burned and vitiated after appropriate ignition in combustion zone 96 so that the swirling fluid discharging from passage 20 becomes a pilot to ignite and sustain combustion in the swirling fluid passing through passage 18.
  • This fluid in passage 18 has fuel added thereto by secondary fuel injector 98 to form a fuel-air mixture of the characteristics that the product of its density and tangential velocity squared pV, is greater than the corresponding product parameter for the outer swirling pilot stream of passage 20 so that accelerated mixing and subsequent combustion takes place between the two fluids in combustion zone 30.
  • the burner shown in FIG. 8 utilizes the premixed burning principle in that fuel is sprayed into the secondary stream 18 prior to entering the mixing and combustion zone 30 and this stream becomes a combustible fuel-air mixture that is subsequently ignited and vitiated when it is mixed with the hot pilot gases or flame from stream 20.
  • FIG. 9 Such a concentric mixer used as a combustor utilizing the diffusion burning principle is shown in FIG. 9.
  • the diffusion burning technique works on a different principle than the premixed burning technique.
  • the pilot fuel from nozzle 92 is fully combusted and fully vitiated in pilot combustion zone 96 such that little or no oxygen remains therein and, accordingly, any fuel added thereto downstream of fully vitiated interface 100 can be vaporized only by the hot products of combustion from pilot zone 96.
  • This phenomenon is taken advantage of in the diffusion burning principle and secondary fuel is discharged into stream 20 by secondary fuel nozzles 101 but this secondary fuel cannot burn until it is mixed with the secondary air being passed in swirl fashion through in stream 18.
  • no fuel whatsoever is directed into stream 18 and that the pilot stream 20 carries not only the heat necessary to initiate combustion and mixing in mixing and combustion zone 20 but also carries the fuel to support this combustion process, when mixed with the air from passage 18.
  • FlGS. l0 and 11 depict barberpole mixers of the type shown in FIGS. 6 and 7 utilized to form combustion chambers of the premixed burning and diffusion burning variety.
  • ducts 102, 104, 106 and 108 are positioned concentrically about centerline 16 to form coannular passages 110, l 12 and 114 therebetween.
  • Guide vanes or the like are used to produce swirling flow in passages 110, 112, and 114 to achieve the desired tangential velocity V, or, as in all other configurations disclosed, this flow may be accepted directly from a compressor which does not have straightening vanes at its outlet.
  • Ducts 104 and 106 join walls 82 and 84 which define passage 86, which is preferably divergent and is the main combustion zone 60.
  • Fuel is sprayed through pilot nozzles 92 into annular passage 112 to be combusted in pilot combustion zone 96 downstream of flameholder 94 to serve as the pilot stream.
  • Secondary fuel is injected into passages and 114 through secondary fuel nozzles 98 in atomized form to be mixed with the air passing therethrough and to pass therefrom through opposed helical slots 88 and 90, respectively, to be discharged as a fuel-air mixture flow substantially parallel to the swirling pilot stream being directed from pilot combustion chamber 96 for accelerated mixing and subsequent combustion with the pilot stream in mixing and combustion zone 60.
  • the direction of flow of the secondary fuel-air mixture through slots 88 and 90 are adjusted by suitable guide vanes to satisfy the instability criteria pV, outer secondary pV, pilot and pVf" inner secondary pV, pilot.
  • the portion of the fuel-air mixture which passed through helical slots or hole patten 90 has a tangential velocity V, imparted thereto that is sufficiently high for pV, p ⁇ of the vitiated pilot gases. Therefore the admitted fuel-air mixture will form helical sheets which will interdigitate with the hot spinning air entering zone 60 from the pilot region 96 and be accelerated radially outward. While the density, p, of the locally burned surface layer of the swirling fuel-air mixture streams will decrease substantially during burning, it will retain the same tangential velocity, V,, since its angular momentum is unaffected by the change of thermodynamic state.
  • the local pV, product parameter of the sheets entering through the slots 90 will be substantially reduced and its acceleration due to the radial pressure gradient will also be reduced as the sheet burns.
  • the unburned portion of the helical layer will continue to be accelerated radially outward, thus continuing to stir the flame front until it is completely burned.
  • FIG. 11 we see the barberpole mixer used as a combustion chamber utilizing diffusion burning in which concentric, preferably cylindrical ducts 102, 104, 106 and 108 are positioned concentrically about centerline or axis 16 to form coannular passages 110, 112, and 114 therebetween, with ducts 104, 106 extending into preferably divergent walls 82 and 84 to form section 86 which defines the main combustion zone 60. Pilot fuel from nozzles 92 is admitted in atomized form to passage 112 upstream flameholder 94 to be fully combusted and vitiated in pilot combustion chamber 96 so that the products of combustion are fully vitiated upstream at interface 100.
  • Secondary fuel is admitted to annular passage 112 downstream of interface 100 through secondary fuel nozzle 101 to be heated and carried with swirling combustion products of the pilot combustion chamber 96 into combustion zone 60, secondary air is passed through annular ducts 110 and 114 and through opposed helical slots 88 and 90, respectively, into mixing and combustion chamber 60 to be mixed with, the hot, fuel rich, flow from pilot stream duct 112. As the mixing process proceeds the excess fuel in the pilot stream comes into contact with the sheets of secondary air entering through slots 88 and and combustion occurs at the multiplicity of interface between these flows.
  • FIG. 12 depicts a bent tube mixer in the form of a folded burner or combustor of the premixed burning variety.
  • the first fluid is passed through passage 74 to have atomized fuel added thereto from pilot fuel nozzle 92 and so that a pilot combustion zone is established at 96 so as to provide an outer pilot stream entering the curved section 70 of curved duct 66 to serve as a pilot to institute mixing with and subsequent combustion of the fuel-air mixture being introduced through passage 76 into mixing and combustion chamber 30.
  • the fuel-air mixture in passage 76 is generated by the passage of fluid therethrough and the introduction of atomized fuel thereinto through secondary fuel spray nozzles 98. It will accordingly be seen in the FIG.
  • a hot pilot stream is established as the outer swirling stream with respect to the inner colder fuel-air mixture stream, both of which are concentric about center of curvature 79 to cause accelerated mixing and combustion therein in view of the flow criteria pV, inner pV, outer.
  • FIG. 12 could be made of the diffusion variety by moving pilot fuel nozzle 92 and flameholders 94 farther upstream so that combustion in the pilot combustion zone 96 is completed and a fully vitiated interface corresponding to 100 of FIG.
  • trigger mechanism 166 positioned at the downstream end of splitter duct 246 which is of circular cross-section and positioned concentrically about axis 16 and cooperates with outer cylindrical duct 248 and inner cylindrical duct 250 to define outer annular gas passage 252 and inner annular gas passage 254.
  • a hot fluid which is to be the pilot fluid, is passed through passage 252.
  • This hot outer fluid has a density p,, and a tangential velocity V,,,.
  • a second fluid which is preferably a cold (high density) combustible mixture, is passed through inner annular passage 254 and has a density of p and a tangential velocity V
  • the mixing criteria p V,,, p, V exists to establish an unstable interface between two swirling fluids.
  • Trigger 166 which is shown to be a convoluted sheet metal ring member attached to the downstream end of splitter duct 246 further serves to accelerate mixing and combustion.
  • Trigger 166 defines convolutions which follow helical paths growing in amplitude in a downstream direction and as the fluids of passage 252 and 254 pass thereover, a regular pattern of radial fluid motion will be initiated outwardly and inwardly due to the change of flow direction imparted to the fluids by trigger mechanism 166. The motion thus initiated will grow because of the instability of the interface.
  • Such a trigger mixer has been successfully demonstrated using air at 200 Fahrenheit and 800 Fahrenheit as working media.
  • the amount of tangential mixing induced by fluid shearing at the helical sheet interface will depend upon the difference between the circulation per radian of the fluids in ducts 252 and 254.
  • trigger mechanisms provides the advantage of controlling the location, size and shape of the disturbance at the interface between the two fluids and it will be appreciated that in constructions where trigger mechanisms are not used the disturbance of the interface is caused by turbulence only and is therefore random in nature.
  • FIG. 31 is a showing of the combustion-pilot primary combustion zone downstream of trigger [66.
  • the flame front where active combustion occurs is located at the interface 255 and 253, respectively, of the triggered helical sheets of hot pilot flow from duct 252 and cold combustible mixture flow from duct 254. As shown in FIG.
  • the flame speed, F/S moves against the trigger helical current of the combustible mixture flowing radially outward and into the hot mass of pilot flow.
  • elements of air undergo an abrupt density change in a high centrifugal field with resultant release of the acceleration potential to magnify the local turbulence and effective flame speed.
  • This local stirring action i.e., increased turbulence, is superimposed upon the interface of the triggered mixing of the initial hot pilot and cold combustible mixture flows.
  • the triggered hot pilot gas from passage 252, which comprises a radially inward directed current has an interface flame speed that moves with the current, as well as laterally into the unburned mixture.
  • FIGS. 32 and 33 Another trigger mechanism, which could be used as a substitute for trigger 166 in the FIGS. 14 and 30 construction, is shown in FIGS. 32 and 33.
  • splitter duct 246 and ducts 248 and 250 are used in the same fashion as in the FIG. 30 construction. Hot products of combustion flow between ducts 246 and 248, while the cooler fluid, such as a fuel-air mixture, flows in the passage between ducts 246 and 250.
  • Trigger mechanism 258 is located at the downstream end of splitter duct 140 and consists of a series of oppositely oriented vane 260 and 262 pairs forming vortex generators which are spaced circumferentially about splitter duct and extending radially outwardly from the splitter duct and in any desired number of axially spaced rows.
  • trigger mechanism 258 to convolute the interface between the hot products of combustion flowing on one side of splitter duct and the cooling air or fuel-air mixture flowing in passage on the other side of the splitter duct so as to take advantage of the mixing criteria in that the pV, product parameter of the hot gases flowing at the greater radius is less than the pV, product parameter of the cold air or fuel-air mixture flowing at a lesser radian at the interface therebetween and any convolution will react with the respective pressure gradients in the hot and cold regions to cause radial mixing currents with cold air currents moving into the hot flow in helical sheets and the hot fluid currents moving into the cold region in helical sheets.
  • the flow at the interface downstream of the trigger plane is unstable and the trigger configuration establishes the helical sheet mixing patterns. This mixing occurs from the inside (minimum radial station) to the outside (maximum radial station) and shortens the length of the combustion chamber and engine by accelerating the mixing process.
  • the trigger of FIG. 34 consists of a series of helically oriented and circumferentially positioned slots 260 at the downstream end of splitter duct 140.
  • the slots are preferably oriented to be parallel to the direction of flow, V, of either the hot or cold gas streams and serves to trigger or disturb the unstable interface which exists between the swirling hot gas flow from the combustion chamber flowing outside splitter duct and the swirling colder air of the cooling gas stream flowing inside of the splitter duct 140 so as to accelerate intermixing.
  • FIG. 35 An additional trigger embodiment is shown in FIG. 35 wherein a plurality of helically extending and circumferentially positioned slots 262 are positioned forward or upstream of slots 260 of the type shown in FIG. 34. Thereby adding to the mixing advantage of the trigger device by utilizing plural slot rows arid/or patterns.
  • FIGS. 36 and 37 Still a further trigger configuration is shown in FIGS. 36 and 37 wherein slots comparable to slot 260 of FIG. 34 are fabricated so as to be elongated and are circumferentially positioned helical slots 264.
  • the after end of splitter duct 140 is fabricated, as shown in FIG. 37, to be corrugated in shape so that the FIGS. 36 and 37 trigger is a combination of the slotted trigger of FIG. 34 and the convoluted trigger of FIG. 30.
  • FIG. 38 Still another form of trigger is shown in FIG. 38 wherein scoops 266 are added to helical slots 268, which are comparable to slots 260 of FIGS. 34 and 35 and which serve to scoop the cold spinning air from a construction comparable to the FIG. 14 construction flowing on the outside of splitter 140 into the hot region radially inward of the splitter duct 140 where the products of combustion from combustion chamber 60 flow, thus triggering the mixing pattern downstream of the splitter duct plane.
  • This FIG. 38 construction will set up helical spinning layers of hot and cold air to mix downstream of the splitter duct. While but a single row of such scooped slots are shown in FIG. 38, it should be realized that more than one row or a pattern thereof could be used, as is shown in FIG. 35 without scoops.
  • trigger 166 be made of sheet metal with a series of small holes 257 therein and preferably, scoop member 259 (see FIG. 45) to be associated with holes 257 to force small jets from the cold side of the trigger to flow to the hot side to cool the trigger and to also introduce a fine scale of disturbance or turbulence to improve combustion.
  • acoustic benefit can be gained by utilizing perforations in the corrugated trigger of the type shown in FIG. 14 and this is important because large amplitude noise has been shown to affect combustion efficiency adversely.
  • Additional noise suppression can be achieved by varying the height and width (distance between) of the trigger corrugations or other trigger mechanisms, and also varying the cycle of the trigger pattern peripherally to achieve noise suppression, thus producing spiraling or helical sheets of hot and cold gases having different frequency responses.
  • FIG. 39 Such a configuration is depicted in FIG. 39 wherein It represents height or amplitude of the convolutions and l and m represent different corrugation widths.
  • turbine engine 40 which consists of a compressor section 42, a burner or combustion section 44, a turbine section 46, and may have an afterburner section 48, which terminates in a variable area nozzle 50.
  • Engine 40 is preferably of circular cross-section and concentric about axis 52.
  • Combustion section 44 includes outer casing 54 and and annular combustor combustion chamber or burner 56, which consists of diffuser inlet section 58, combustion zone 60 and dilution zone 62.
  • annular combustion chamber means a combustion chamber having an annular passage extending from the inlet, or upstream end, to the outlet, or downstream end thereof.
  • Fuel is supplied to combustor 56 by variable output fuel pump 64 which is either under pilot manual or pilot set automatic control, and is fed into the inlet of combustor 56 in a fashion to be described hereinafter, to be mixed therewith with a portion of the pressurized gas from compressor section 42 to form a combustible fuel-air mixture to be burned in combustion zone 60, from which the products of combustion pass into dilution zone 62 for mixing with diluent cooling air also from the compressor to lower the temperature thereof prior to entry into turbine section 46.
  • Engine 40 may be of the type more fully described in U.S. Pat. Nos. 2,747,367, 2,711,63l and 2,846,841.
  • a typical combustor system or section 44 of a turbine engine of the type shown in FIG; 13 may be considered to be composed of two components in series, namely, a combustion zone 60 in which fuel is burned in a portion of the total engine airflow from the compressor and a dilution zone 62 in which the balance of the airflow is mixed with the hot products ofcombustion from the combustion zone so that a substantially cooler mixture than the products of combustion is passed through the turbine 46.
  • Any combination of concentric mixtures, barberpole mixers, and bent tube mixers can be used to perform the combustion zone region mixing and combustion function and the dilution zone region mixing and cooling functions of such a combustion section 44.
  • annular combustion chamber 56 which comprises outer case 54 and inner case 1 13, which are preferably of circular cross-section and mounted concentrically about axis or centerline 16.
  • the air from the compressor section 42 of FIG. 13 enters annular inlet 114 in either swirling flow or nonswirling flow depending upon the discharge conditions from the compressor section 42, and portions thereof pass through pilot passage 124, main combustion zone fuel preparation passage 126 and the diluent air passage 130. Further quantities of airflow through passages 122 and 132 to provide for cooling the walls of the combustor chamber. Vanes 116, 118, and 128 are employed as required to swirl or straighten the flow in the respective passage so as to satisfy the previously defined mixing instability criteria.
  • Each of the passages 122, 124, 126, 130 and 132 are of annular shape since the outer burner liner 134, the inner burner liner 136 and splitter ducts 138 and 140 are of circular crosssection and concentric about axis 16.
  • Turning vanes 116 and 118, 120 and 128 may be fixed or any or all vanes could be of the variable angle type as shown, for example, in FIG. 15 wherein each of vanes 116 is pivotally connected to duct 134 and outer housing 54 by pivot pins 144 and 146, respectively.
  • Pivot pin 146 extends through outer case 54 and carries ring gear 148 at its outer end, which engages circumferentially rotatable ring or annular gear 150, which is pilot operated to rotate circumferentially about axis 16 by motion of pilot actuated lever 152 into and out of the plane of the paper, thereby causing vanes 116 to rotate in unison and thereby vary the tangential velocity V, of the gas or fluid passing thereby.
  • the swirling air which entered passage 124 has atomized fuel added thereto by fuel injection device 156 to form a fuel-air mixture which is ignited by ignitor 158 and vitiated in pilot combustion chamber 160 which is located downstream of aperturetype flameholder 161, which is a tilted and apertured plate extending between ducts 134 and 138.
  • the hot swirling stream emerging from passage 124 serves as a pilot stream for combustion chamber 60.
  • the swirling air entering passage 126 has atomized fuel added thereto by injection member 162 and the amount of fuel to be discharged into passage 124 and 126 can be regulated by the size and number of fuel nozzles, such as 162 located therein and by pilot controlled valves 163 and 165 located in the fuel line thereto.
  • the atomized fuel entering passage 126 mixes with the swirling gas passing therethrough to provide a combustible fuelair mixture to combustion chamber 60 for accelerated mixing pilot stream emerging from passage 124 and subsequent combustion of this flow. It will accordingly be seen that hot swirling pilot stream emerging from passageway 124 to mix with and sustain combustion in the fuel-air mixture emerging from passageway 126 and the thermodynamic and aerodynamic characteristics of these two streams are established so as to satisfy the

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  • Spray-Type Burners (AREA)
US00084086A 1970-10-26 1970-10-26 Annular combustion chamber for dissimilar fluids in swirling flow relationship Expired - Lifetime US3788065A (en)

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US3872664A (en) * 1973-10-15 1975-03-25 United Aircraft Corp Swirl combustor with vortex burning and mixing
US3931707A (en) * 1975-01-08 1976-01-13 General Electric Company Augmentor flameholding apparatus
US3934409A (en) * 1973-03-13 1976-01-27 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Gas turbine combustion chambers
US3937008A (en) * 1974-12-18 1976-02-10 United Technologies Corporation Low emission combustion chamber
US3973395A (en) * 1974-12-18 1976-08-10 United Technologies Corporation Low emission combustion chamber
US3973390A (en) * 1974-12-18 1976-08-10 United Technologies Corporation Combustor employing serially staged pilot combustion, fuel vaporization, and primary combustion zones
US3974646A (en) * 1974-06-11 1976-08-17 United Technologies Corporation Turbofan engine with augmented combustion chamber using vorbix principle
US3993449A (en) * 1975-04-07 1976-11-23 City Of North Olmsted Apparatus for pollution abatement
US3999378A (en) * 1974-01-02 1976-12-28 General Electric Company Bypass augmentation burner arrangement for a gas turbine engine
US4012904A (en) * 1975-07-17 1977-03-22 Chrysler Corporation Gas turbine burner
US4045956A (en) * 1974-12-18 1977-09-06 United Technologies Corporation Low emission combustion chamber
US4058977A (en) * 1974-12-18 1977-11-22 United Technologies Corporation Low emission combustion chamber
US4149373A (en) * 1977-08-29 1979-04-17 United Technologies Corporation Combustion chamber stress reducing means
FR2411968A1 (fr) * 1977-12-15 1979-07-13 Gen Electric Chambre de combustion annulaire double perfectionnee
DE2901098A1 (de) * 1978-01-19 1979-07-26 United Technologies Corp Brennkammer und verfahren zum betreiben derselben
US4204402A (en) * 1976-05-07 1980-05-27 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Reduction of nitric oxide emissions from a combustor
US4389848A (en) * 1981-01-12 1983-06-28 United Technologies Corporation Burner construction for gas turbines
US4928479A (en) * 1987-12-28 1990-05-29 Sundstrand Corporation Annular combustor with tangential cooling air injection
US5076053A (en) * 1989-08-10 1991-12-31 United Technologies Corporation Mechanism for accelerating heat release of combusting flows
US5197278A (en) * 1990-12-17 1993-03-30 General Electric Company Double dome combustor and method of operation
US5207064A (en) * 1990-11-21 1993-05-04 General Electric Company Staged, mixed combustor assembly having low emissions
US5335501A (en) * 1992-11-16 1994-08-09 General Electric Company Flow spreading diffuser
US5406799A (en) * 1992-06-12 1995-04-18 United Technologies Corporation Combustion chamber
US5407347A (en) * 1993-07-16 1995-04-18 Radian Corporation Apparatus and method for reducing NOx, CO and hydrocarbon emissions when burning gaseous fuels
US5470224A (en) * 1993-07-16 1995-11-28 Radian Corporation Apparatus and method for reducing NOx , CO and hydrocarbon emissions when burning gaseous fuels
US5865030A (en) * 1995-02-01 1999-02-02 Mitsubishi Jukogyo Kabushiki Kaisha Gas turbine combustor with liquid fuel wall cooling
US6058710A (en) * 1995-03-08 2000-05-09 Bmw Rolls-Royce Gmbh Axially staged annular combustion chamber of a gas turbine
US6390805B1 (en) * 1998-09-16 2002-05-21 Asea Brown Boveri Ag Method of preventing flow instabilities in a burner
US6668541B2 (en) * 1998-08-11 2003-12-30 Allison Advanced Development Company Method and apparatus for spraying fuel within a gas turbine engine
US20060154189A1 (en) * 2004-12-08 2006-07-13 Ramotowski Michael J Method and apparatus for conditioning liquid hydrocarbon fuels
US20070254966A1 (en) * 2006-05-01 2007-11-01 Lpp Combustion Llc Integrated system and method for production and vaporization of liquid hydrocarbon fuels for combustion
US20080053097A1 (en) * 2006-09-05 2008-03-06 Fei Han Injection assembly for a combustor
US20090214989A1 (en) * 2008-02-25 2009-08-27 Larry William Swanson Method and apparatus for staged combustion of air and fuel
US20100192583A1 (en) * 2007-06-21 2010-08-05 Mariano Cano Wolff Non-rotational stabilization of the flame of a premixing burner
US20100300103A1 (en) * 2002-10-10 2010-12-02 LLP Combustion, LLC System for vaporization of liquid fuels for combustion and method of use
US20110197591A1 (en) * 2010-02-16 2011-08-18 Almaz Valeev Axially staged premixed combustion chamber
US20120018543A1 (en) * 2009-02-05 2012-01-26 Snecma Diffuser/rectifier assembly for a turbine engine
WO2013023147A1 (en) * 2011-08-11 2013-02-14 Beckett Gas, Inc. Combustor
US20130104552A1 (en) * 2011-10-26 2013-05-02 Jong Ho Uhm Fuel nozzle assembly for use in turbine engines and methods of assembling same
US20140004469A1 (en) * 2011-03-16 2014-01-02 L'air Liquide, Societe Anonyme Pour L'etude Et L'exploitation Des Procedes Low NOx Combustion Process and Burner Therefor
US20150013339A1 (en) * 2012-03-26 2015-01-15 Alstom Technology Ltd Mixing arrangement for mixing a fuel with a stream of oxygen containing gas
WO2015022269A1 (de) * 2013-08-16 2015-02-19 Siemens Aktiengesellschaft Auslegung eines axialdiffusors unter berücksichtigung von einbauten
US9677766B2 (en) * 2012-11-28 2017-06-13 General Electric Company Fuel nozzle for use in a turbine engine and method of assembly
US10876407B2 (en) * 2017-02-16 2020-12-29 General Electric Company Thermal structure for outer diameter mounted turbine blades
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly

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FR2312653A2 (fr) * 1975-05-30 1976-12-24 Snecma Chambre de combustion anti-pollution pour turbine a gaz
FR2694624B1 (fr) * 1992-08-05 1994-09-23 Snecma Chambre de combustion à plusieurs injecteurs de carburant.
ES2488404T3 (es) * 2011-03-07 2014-08-27 Eads Construcciones Aeronáuticas, S.A. Sistema de evacuación de flujo para un motor de aeronave
CN112762435B (zh) * 2019-10-21 2025-03-28 王春明 一种燃烧器

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Cited By (58)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3934409A (en) * 1973-03-13 1976-01-27 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Gas turbine combustion chambers
US3872664A (en) * 1973-10-15 1975-03-25 United Aircraft Corp Swirl combustor with vortex burning and mixing
US3999378A (en) * 1974-01-02 1976-12-28 General Electric Company Bypass augmentation burner arrangement for a gas turbine engine
US3974646A (en) * 1974-06-11 1976-08-17 United Technologies Corporation Turbofan engine with augmented combustion chamber using vorbix principle
US3973395A (en) * 1974-12-18 1976-08-10 United Technologies Corporation Low emission combustion chamber
US3973390A (en) * 1974-12-18 1976-08-10 United Technologies Corporation Combustor employing serially staged pilot combustion, fuel vaporization, and primary combustion zones
US3937008A (en) * 1974-12-18 1976-02-10 United Technologies Corporation Low emission combustion chamber
US4045956A (en) * 1974-12-18 1977-09-06 United Technologies Corporation Low emission combustion chamber
US4058977A (en) * 1974-12-18 1977-11-22 United Technologies Corporation Low emission combustion chamber
US3931707A (en) * 1975-01-08 1976-01-13 General Electric Company Augmentor flameholding apparatus
US3993449A (en) * 1975-04-07 1976-11-23 City Of North Olmsted Apparatus for pollution abatement
US4012904A (en) * 1975-07-17 1977-03-22 Chrysler Corporation Gas turbine burner
US4204402A (en) * 1976-05-07 1980-05-27 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Reduction of nitric oxide emissions from a combustor
US4149373A (en) * 1977-08-29 1979-04-17 United Technologies Corporation Combustion chamber stress reducing means
FR2411968A1 (fr) * 1977-12-15 1979-07-13 Gen Electric Chambre de combustion annulaire double perfectionnee
US4194358A (en) * 1977-12-15 1980-03-25 General Electric Company Double annular combustor configuration
DE2901098A1 (de) * 1978-01-19 1979-07-26 United Technologies Corp Brennkammer und verfahren zum betreiben derselben
US4389848A (en) * 1981-01-12 1983-06-28 United Technologies Corporation Burner construction for gas turbines
US4928479A (en) * 1987-12-28 1990-05-29 Sundstrand Corporation Annular combustor with tangential cooling air injection
USRE34962E (en) * 1987-12-28 1995-06-13 Sundstrand Corporation Annular combustor with tangential cooling air injection
US5076053A (en) * 1989-08-10 1991-12-31 United Technologies Corporation Mechanism for accelerating heat release of combusting flows
US5207064A (en) * 1990-11-21 1993-05-04 General Electric Company Staged, mixed combustor assembly having low emissions
US5197278A (en) * 1990-12-17 1993-03-30 General Electric Company Double dome combustor and method of operation
US5406799A (en) * 1992-06-12 1995-04-18 United Technologies Corporation Combustion chamber
US5335501A (en) * 1992-11-16 1994-08-09 General Electric Company Flow spreading diffuser
US5407347A (en) * 1993-07-16 1995-04-18 Radian Corporation Apparatus and method for reducing NOx, CO and hydrocarbon emissions when burning gaseous fuels
US5470224A (en) * 1993-07-16 1995-11-28 Radian Corporation Apparatus and method for reducing NOx , CO and hydrocarbon emissions when burning gaseous fuels
US5865030A (en) * 1995-02-01 1999-02-02 Mitsubishi Jukogyo Kabushiki Kaisha Gas turbine combustor with liquid fuel wall cooling
US6058710A (en) * 1995-03-08 2000-05-09 Bmw Rolls-Royce Gmbh Axially staged annular combustion chamber of a gas turbine
US6668541B2 (en) * 1998-08-11 2003-12-30 Allison Advanced Development Company Method and apparatus for spraying fuel within a gas turbine engine
US6390805B1 (en) * 1998-09-16 2002-05-21 Asea Brown Boveri Ag Method of preventing flow instabilities in a burner
US8225611B2 (en) 2002-10-10 2012-07-24 Lpp Combustion, Llc System for vaporization of liquid fuels for combustion and method of use
US20100300103A1 (en) * 2002-10-10 2010-12-02 LLP Combustion, LLC System for vaporization of liquid fuels for combustion and method of use
US20060154189A1 (en) * 2004-12-08 2006-07-13 Ramotowski Michael J Method and apparatus for conditioning liquid hydrocarbon fuels
US8702420B2 (en) * 2004-12-08 2014-04-22 Lpp Combustion, Llc Method and apparatus for conditioning liquid hydrocarbon fuels
US20070254966A1 (en) * 2006-05-01 2007-11-01 Lpp Combustion Llc Integrated system and method for production and vaporization of liquid hydrocarbon fuels for combustion
US8529646B2 (en) 2006-05-01 2013-09-10 Lpp Combustion Llc Integrated system and method for production and vaporization of liquid hydrocarbon fuels for combustion
US20080053097A1 (en) * 2006-09-05 2008-03-06 Fei Han Injection assembly for a combustor
US7827797B2 (en) * 2006-09-05 2010-11-09 General Electric Company Injection assembly for a combustor
US20100192583A1 (en) * 2007-06-21 2010-08-05 Mariano Cano Wolff Non-rotational stabilization of the flame of a premixing burner
US20090214989A1 (en) * 2008-02-25 2009-08-27 Larry William Swanson Method and apparatus for staged combustion of air and fuel
US7775791B2 (en) * 2008-02-25 2010-08-17 General Electric Company Method and apparatus for staged combustion of air and fuel
US20120018543A1 (en) * 2009-02-05 2012-01-26 Snecma Diffuser/rectifier assembly for a turbine engine
US9512733B2 (en) * 2009-02-05 2016-12-06 Snecma Diffuser/rectifier assembly for a turbine engine with corrugated downstream walls
US20110197591A1 (en) * 2010-02-16 2011-08-18 Almaz Valeev Axially staged premixed combustion chamber
US20140004469A1 (en) * 2011-03-16 2014-01-02 L'air Liquide, Societe Anonyme Pour L'etude Et L'exploitation Des Procedes Low NOx Combustion Process and Burner Therefor
US9447969B2 (en) * 2011-03-16 2016-09-20 L'Air Liquide Société Anonyme Pour L'Étude Et L'Exploitation Des Procedes Georges Claude Low NOx combustion process and burner therefor
WO2013023147A1 (en) * 2011-08-11 2013-02-14 Beckett Gas, Inc. Combustor
CN103998867A (zh) * 2011-08-11 2014-08-20 贝克特瓦斯公司 燃烧室
US20130104552A1 (en) * 2011-10-26 2013-05-02 Jong Ho Uhm Fuel nozzle assembly for use in turbine engines and methods of assembling same
US8943832B2 (en) * 2011-10-26 2015-02-03 General Electric Company Fuel nozzle assembly for use in turbine engines and methods of assembling same
US20150013339A1 (en) * 2012-03-26 2015-01-15 Alstom Technology Ltd Mixing arrangement for mixing a fuel with a stream of oxygen containing gas
US9822981B2 (en) * 2012-03-26 2017-11-21 Ansaldo Energia Switzerland AG Mixing arrangement for mixing a fuel with a stream of oxygen containing gas
EP2831507B1 (en) * 2012-03-26 2019-12-18 Ansaldo Energia Switzerland AG Mixing arrangement for mixing a fuel with a stream of oxygen containing gas
US9677766B2 (en) * 2012-11-28 2017-06-13 General Electric Company Fuel nozzle for use in a turbine engine and method of assembly
WO2015022269A1 (de) * 2013-08-16 2015-02-19 Siemens Aktiengesellschaft Auslegung eines axialdiffusors unter berücksichtigung von einbauten
US10876407B2 (en) * 2017-02-16 2020-12-29 General Electric Company Thermal structure for outer diameter mounted turbine blades
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly

Also Published As

Publication number Publication date
FR2112339B1 (OSRAM) 1976-03-26
CA954313A (en) 1974-09-10
AU451788B2 (en) 1974-08-15
SE7401957L (OSRAM) 1974-02-14
DE2153085A1 (de) 1972-04-27
FR2112339A1 (OSRAM) 1972-06-16
SE389893B (sv) 1976-11-22
AU3177971A (en) 1973-02-01
GB1314970A (en) 1973-04-26

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