US3633361A - Burners for reheat combustion chambers - Google Patents

Burners for reheat combustion chambers Download PDF

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US3633361A
US3633361A US861918A US3633361DA US3633361A US 3633361 A US3633361 A US 3633361A US 861918 A US861918 A US 861918A US 3633361D A US3633361D A US 3633361DA US 3633361 A US3633361 A US 3633361A
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prevaporizing
reheat
fuel
feedpipe
burner
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US861918A
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Louis Jules Bauger
Armand Jean-Baptiste Lacroix
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Safran Aircraft Engines SAS
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SNECMA SAS
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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
    • F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
    • F23R3/32—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices being tubular

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  • a burner for the reheat chamber of a dual-flow gas turbine jet engine comprising a fuel-prevaporizing device having a feedpipe fed jointly from a liquid fuel source and a secondary air duct and having a discharge pipe opening into the reheat chamber to discharge thereinto a mixture of air from the secondary duct and of fuel preheated by heat exchange with a primary flow of hot gases from the turbine.
  • PATENTEB JAN I I972 SHEET 1 OF 4 PATENIEMAII 1 :12 16331361 SHEET 2 OF 4 PATENTEU JAN] 1 1912 SHEET 3 BF 4 BURNERS FOR REHEAT COMBUSTION CHAMBERS
  • This invention relates to reheat combustion chambers, sometimes known as after-bumer combustion chambers, forming part of gas turbine powerplants of the dual-flow type, more especially turbojet engines, as used for the propulsion of aircraft or similar vehicles, and relates more particularly to an improved liquid fuel burner designed for installation in such reheat combustion chambers.
  • the invention exhibits numerous advantages, in particular in the inhibition of phenomena such as chemical cracking and coking of the fuel, and also in the production, in the reheat combustion of a high-efficiency combustion zone.
  • a gas turbine powerplant of the dual-flow type should be broadly understood as indicating a gas turbine powerplant through which passes, on the one hand, a primary flow consisting essentially of combustion gas and, on the other hand, a secondary flow consisting essentially of air.
  • the primary and usually central flow successively passes through a compressor, a main combustionchamber and a turbine which form part of the powerplant.
  • the secondary flow usually passes through a separate duct generally of annular or peripheral kind which is fed from a compressor or blower, or possibly even from an intake orifice which receives air at the dynamic pressure created by the forward movement of the vehicle.
  • turbojet engines of aircraft flying at very high speed leads to the use of engines of very high thermal performance.
  • the temperature of the gases at the intake of the turbine is often equal to or higher than l,200 C. and this corresponds at the turbine exit to a temperature of the order of 800 C. for example, i.e., substantially higher than the temperature generally attained in engines of the kind designed to propel aircraft at lower speeds.
  • the bumers currently employed in reheat combustion chambers are generally constituted by stabilizer rings or gutters open in the downstream direction (considered in relation to the direction of gas flow), in which are incorporated fuel manifolds formed with fuel injection orifices, it also being possible to provide supplementary fuel manifolds distinct from those which are incorporated in said rings.
  • the use of burners of this kind even for medium performance plants (the turbine exit temperature of which is, however, relatively low, of the order of 650 to 700 C.), already means that, where high reheat ratios are involved, in addition to certain problems of mechanical stability of the burner elements, difficulties are encountered which arise out of the incipient chemical cracking and coking of the fuel inside the fuel manifolds.
  • Another problem is that of the relatively low level of the percentage of oxygen contained in the gases leaving the turbine. This oxygen deficiency can lead to incomplete or not sufficiently effective combustion of the fuel injected into the reheat combustion chamber, especially in the neighborhood of the injection zone, and this can impair not only the efficiency but also the attainment of the desired elevated temperatures which give the requisite performance.
  • the burner comprises, located in the reheat combustion chamber, at least one prevaporizing device through which passes a fuel flow, said device comprising an entry section communicating with a liquid fuel injection device, and at least one exit section through which the vaporized fuel is supplied to the reheat combustion chamber, and means furthermore for injecting into the fuel flow air emanating from the secondary air flow of the gas turbine powerplant.
  • the fuel is no longer injected directly in liquid condition into the reheat combustion chamber, through injection orifices which run the risk of being blocked by coking. Instead, it is delivered indirectly and in the gaseous condition, through the medium of a prevaporizing device which it traverses in the vaporized or semivaporized state at least in that zone of said device which is the most exposed to radiation from the flame.
  • the fuel can be emulsified with air, (contrary to procedure with the fuel in conventional fuel manifolds). The risk of chemical cracking of the fuel is thus reduced to the minimum and, consequently, so is the risk of blockage, by carbon deposits, of the exit orifices of said device;
  • the prevaporizing device efficiently protects the liquid fuel injection device which constitutes the supply source for the prevaporizing device, from direct radiation from the flame, in fact it acts as a screen in this respect.
  • the fresh air, which can be injected in the neighborhood of this source contributes, furthermore, to the cooling of said latter and eliminates any risk of cracking or coking at this point;
  • the fresh air rich in oxygen, which thus penetrates into the reheat combustion chamber, makes it possible to regenerate the contaminated primary flow leaving the turbine. Suitably distributed, this air can thus promote the creation of a high-efficiency combustion zone.
  • the prevaporizing device used may conveniently comprise two discharge passages connected to a feed pipe substantially symmetrically with respect to the axis of the latter; alternatively, it may comprise a plurality of discharge passages connected star fashion to said feed pipe.
  • the main feed pipe will accordingly preferably be internally partitioned to form as many compartments as there are discharge passages, each of said compartments communicating with one of said passages to permit selective control of the flow of fuel injected into each of the compartments, so as to make it possible to produce a predetermined richness in each discharge passage.
  • the prevaporizing device comprises a distributor pipe, substantially peripheral in arrangement, linking the feedpipe to the discharge passages, the latter being connected to the distributor pipe in substantially radial manner and preferably being split into two groups one of which extends from the distributor pipe towards the axis of the reheat combustion chamber while the other extends away from said axis.
  • the feedpipe and the distributor pipe can each be partitioned into two compartments corresponding respectively to one and to the other of the discharge passage groups, in order to make it possible to effect differential enrichment of the central and peripheral zones of the reheat combustion chamber.
  • the air emanating from the secondary flow can be injected into the entry section of the prevaporizing device in order to promote cooling of the fuel source and to form a mixture with the prevaporized fuel.
  • Air emanating from the secondary flow can further be injected, through appropriate injection orifices, directly into the reheat combustion chamber in the neighborhood of the exit section or sections of the discharge passages, in order to contribute to the stimulation of combustion and to the creation of a turbulent zone by judicious arrangement of said orifices.
  • the entry section of the prevaporizing device can be connected directly to said annular duct through an orifice in said wall, said orifice preferably being adapted to provide a total pressure tapping.
  • the entry section of the prevaporizing device can be located inside or in the neighborhood of said conical structure.
  • orifices can be formed through the walls which separate from one another the reheat combustion chamber and the peripheral annular duct or the interior of the hollow conical structure, in order to enable the direct injection of air to take place in the neighborhood of the exit sections of the passages through which vaporized fuel is injected.
  • These orifices will preferably have a projecting form in order to improve the effect of the radial penetration of the air into the reheat combustion chamber.
  • the prevaporizing device can be supported directly by the periphery of the reheat combustion chamber or by the end of the exhaust cone which follows the turbine, the latter arrangement having the advantage that the central zone or core of the reheat combustion chamber, usually difficult to involve in the combustion process, now more effectively participates in said process.
  • the prevaporizing device can also be supported by at least one profiled annular ring in the form of a gutter open in the downstream direction (considered in relation to the direction of gas flow through the chamber), said gutter being formed on its leading edge with openings which are designed to receive discharge passages forming part of the prevaporizing device.
  • a prevaporizing device comprising two discharge passages connected to a feedpipe in a substantially symmetrical disposition with respect to the axis of said pipe, the gutter having pierced in its leading edge a central opening flanked by two other openings, these openings being designed respectively to pass the feedpipe and the two discharge pipes.
  • This kind of prevaporizing device will advantageously be arranged to cooperate with a fuel manifold arranged upstream of the profiled gutter, that is to say in a zone shielded from direct radiation from the flame.
  • a prevaporizing device which comprises a plurality of discharge passages connected in star fashion to the feedpipe
  • an assembly of two coaxial profiled rings, connected with one another through substantially radial stays exhibiting, like the rings, a gutter form open in the downstream direction, can be employed.
  • the respective leading edges of the two rings and of the stays will then, as before, contain openings designed to receive the various discharge passages.
  • supplementary openings can be formed in the leading edge of each of the rings in order to enable a small fraction of the gas flow to pass directly through the ring and thus feed the wake area developed behind the ring.
  • FIG. 1 is a schematic axial half-section of the downstream part of the dual-flow gas turbine powerplant, comprising, in particular a reheat combustion chamber equipped with prevaporizing burners arranged and supplied in accordance with the invention;
  • FIG. 2 is a view on a larger scale, in accordance with the arrow II of FIG. 1, through one of the prevaporizing burners;
  • FIG. 3 is a view in section, on the line III--III of FIG. 2;
  • FIG. 4. is a sectional view, on a larger scale, of another of the prevaporizing burners illustrated in FIG. 1;
  • FIGS. 5 and 6 are respective sections on the lines V-V and VI-VI ofFIG. 4;
  • FIG. 7 is a view in transverse section through a prevaporizing burner, similar to that shown in FIGS. 4 to 6 but this time supported by an arrangement of two coaxial rings, said arrangement being seen in end elevation from the upstream direction;
  • FIG. 8 is a view similar to that of FIG. 1, showing a burner of the kind illustrated in FIGS. 4 to 6, assembled on the downstream end of a hollow exhaust cone located behind the turbine;
  • FIG. 9 is a view in section on the line IXIX of FIG. 8;
  • FIG. 10 is an end view, from the upstream direction, of a prevaporizing burner in accordance with a variant embodiment.
  • FIG. 11 is a view of a burner similar to that shown in FIG. 10 but carried by an arrangement of two coaxial rings.
  • the general reference 1 designates a reheat chamber or reheat combustion duct located downstream of the final stage of a gas turbine 2, part of a gas turbine powerplant such as a turbojet engine in an aircraft.
  • This powerplant is of the dual-flow kind, that is to say there is a primary central flow marked by the arrow f,, which passes through the turbine and essentially consists of combustion gases, and a secondary peripheral flow, marked by the arrow f which passes through an annular duct 3 and essentially comprises air uncontaminated by combustion gases.
  • This air may, for example, come from an upstream blower or compressor or, more simply, may be air delivered by a ram effect due to the forward speed of the aircraft.
  • the annular duct 3 is delimited by external casings 4, 5 and internal casings 6, 7 connected with one another by faired hollow stays 8.
  • These casings, in the neighborhood of the stays 8, form a supporting structure for the walls defining the reheat combustion chamber, namely an external casing 9, a heat shield 10 and an exhaust cone structure 11 located on the axis of the powerplant downstream of the turbine and carried by means of hollow faired stays I2 in line with the hollow stays 8.
  • the heat shield 10 is rigidly attached to the supporting structure so that its expansion during operation is in the downstream direction.
  • the secondary flow which has already been used to effect cooling by virtue of its passage around various parts of the structure such as the casings 4, 5, 6, 7, penetrates on the one hand into the annular space 13 defined between the external casing 9 and the heat shield 10 of the reheat chamber, and on the other hand through orifices 14 formed in the hollow faired stays 8 and through the hollow faired stays 12, into a collector space 15 contained within the conical structure 11.
  • the heat shield 10 screens off the external casing 9 which forms the strong external wall of the reheat chamber 1, and ensures that part of the secondary flow is directed to a discharge or propulsion nozzle (not shown).
  • this shield can be made of a series of successive casings 10a, 10b, 10c, 10d welded together through the medium of spacers l6 perforated in order to enable a certain fraction of the secondary airflow to be tapped off and develop a thin lamina film between the shield and the flame.
  • the casing is preferably adapted to present a frontal area to the secondary flow.
  • Communicating orifices 17, 18 formed in the casing a enable a fraction of the air flowing through the annular duct 13 to pass directly into the reheat chamber.
  • Certain of these orifices, in the present case the orifices 18, can be given a spigoted or projecting form.
  • Oriflces 19 similar to the orifices 18 can be provided in the wall of the hollow conical structure 11, at the collecting space 15.
  • the burner 20 for example of the kind illustrated on a larger scale in FIGS. 4 to 6, is one of an assembly of similar burners arranged in a circle around the axis XX of the powerplant and supported, in each case, by the upstream casing 10a of the heat shield.
  • the burner comprises, located in the reheat chamber, a prevaporizing device constituted, in particular, by a feedpipe 21 which passes through an opening 22 formed in said casing, and by a plurality of discharge passages or pipes 23 connected in star fashion to said feedpipe.
  • the feedpipe 21 has an entry section 24 which projects, preferably in such a manner as to act as a total pressure tapping, into the secondary flow, and adjacent this entry section is located a liquid fuel injector 25 having a series of calibrated injection orifices 29 (see FIG. 4), for example of the dual-feed kind.
  • the discharge pipes 23 each have an exit section 26 and are preferably curved so that each of said exit sections opens in the upstream direction.
  • the feedpipe is divided internally, by means of longitudinal partitions 27, into a plurality of compartments 28 equal in number to the number of discharge pipes or passages 23. Each of these compartments communicates with one of said passages and is supplied with liquid fuel injected through one of the calibrated orifices 29.
  • the prevaporizing device 21-23 locate in the high-temperature combustion gas flow, is itself raised to a high temperature.
  • the mixture made up of the flow of fuel fed from the injector 25 and the air injected through the entry section 24 and emanating from the secondary flow f passes through the prevaporizing device 21-23.
  • the fuel vaporizes progressively and consequently a preheated mixture of air and vaporized fuel exits in the upstream direction through the exit sections 26 of the discharge pipes 23.
  • this mixture At the time of entry into the primary flow, itself very hot, this mixture is thus easily ignited, either by self-ignition or by any suitable device such as a glow plug or high-energy plug.
  • the carbureted mixture discharges in counterflow fashion so as to contribute to stabilization of the flame by creating in the upstream part of the reheat chamber a stable turbulent zone.
  • the fuel which is both vaporized and mixed with fresh air, is discharged from the prevaporizing device virtually without any danger of cracking and coking, and in particular from that part thereof which is least vulnerable to radiation from the flame. Accordingly, there is no risk of the blocking of the exit sections 26 by carbon deposits.
  • the fuel injector 25 is itself efficiently protected from the flame radiation by the wall of the feedpipe 21 and is furthermore cooled by the fresh airflow in which it is located and which emanates from the secondary flow; thus, at this point too, risk is eliminated of chemical modification of the fuel.
  • the mixture leaving the exit sections 26 is much richer in oxygen than the combustion gases which make up the contaminated primary flow f, and this means that the latter flow can be regenerated and the efficiency of the reheat function improved.
  • Supplementary fresh air can penetrate into the reheat combustion chamber through the orifices 17, 18, in the neighborhood of the exit section 26 of the prevaporizing devices, and this further improves the oxygen percentage in this zone. It will be clear that it is necessary, in order for this to take place, for the pressure of the secondary airflow at the level of the orifices 17, 18, to be higher than that of the primary flow, the efficiency of penetration being the greater the higher the pressure difference is. It will be observed in this context that the shape of the upstream section of the casing 10a makes it possible to recover, across the orifices 17, part of the dynamic pressure of the secondary flow, this in accordance with the principle utilized in total pressure-tapping arrangements. As far as the orifices 18 are concerned, which are located more directly in the neighborhood of the exit sections 26, because of their spigot form they enable jets of air to be formed having a high transverse penetration effect.
  • the splitting of the prevaporizing device into several compartments 28 makes it possible to supply each compartment through an orifice 29 of predetermined characteristics. Thus, it is possible to vary the richness of the mixture leaving the prevaporizing device, in accordance with the desired local distribution in the reheat chamber.
  • the reheat chamber can be fitted, in the neighborhood of the conical structure 11, with another burner 30 designed in accordance with a variant embodiment of the invention and comprising a series of individual prevaporizing devices supported by one and the same profiled ring 31, again having a gutter form open in the downstream direction in relation to the general direction of flow of gas through the chamber.
  • Each of these prevaporizing devices may be of the kind shown on a larger scale in FIGS. 2 and 3 and comprising a feedpipe 32 having an entry section 33 and discharge pipes or passages 34 connected to the feedpipe 32 at either side thereof in a substantially symmetrical manner with respect to the axis of said pipe. As in the foregoing case, these discharge pipes are turned back in order that their exit sections 35 are directed upstream.
  • Each of the discharge pipes 34 corresponds with a compartment 36 in the feedpipe, said compartment being obtained by partitioning of the latter by a wall 37.
  • the profiled ring 31 is provided in its leading edge with a series of openings designed to pass the feedpipe 32 and the discharge pipes 34.
  • Supplementary openings 38 can likewise be provided in order to enable the passage directly downstream of a small portion of the primary flow, this portion being designed to feed the wake region formed behind the profiled ring 31.
  • the air-injection orifices 19 are located in the neighborhood of both the entry sections of the pipes 32 and the exit sections of the discharge passages 34.
  • the feedpipe 32 receives the fuel coming from the injector 39 as well as a mixture of combustion gases emanating from the primary flow and air coming from the injection orifices 19.
  • the discharge passages 34 supply, in the upstream direction of the reheat chamber, a preheated mixture containing the prevaporized fuel.
  • the fuel manifold 39 itself is concerned, it is on the one hand protected against direct radiation from the flame by the profiled ring 31 which acts as a shield, and on the other hand cooled by the jets of fresh air leaving the injection orifices 19, so that the danger of chemical alternation of the fuel which it contains is very much reduced.
  • FIG. 7 relates to a burner comprising a series of prevaporizing devices supported in substantially symmetrical fashion by an arrangement of two coaxial profiled rings 41, 42 connected with one another by intercommunicating stays 43.
  • the prevaporizing devices 40 are of the kind described in FIGS. 4 to 6, similar references designating similar elements.
  • the rings 41, 42 and the stays 43 are of the gutter type, open in the downstream direction, and contain in their leading edges a series of openings designed to receive the discharge pipes 23, the latter being elbowed so that they face upstream.
  • the prevaporizing devices are thus maintained in position by the supporting structure 41, 42, 43.
  • the references 38 have been used to designate supplementary openings formed in the leading edges of the rings 41, 42.
  • FIGS. 8 and 9 relate to an embodiment in accordance with which a prevaporizing device 44 is supported by the downstream extremity of the hollow conical structure 11 which is mounted behind the turbine.
  • This prevaporizing device is of the star-shaped kind, already described in relation to FIGS. 4 to 6, and similar references have been used to indicate similar elements.
  • the airflow f can, for example, be one which has previously been employed for the cooling of internal enclosures of the powerplant or of devices such as shafts, discs, turbine bearings and so on, and this has the supplementary advantage that a substantial amount of thermal energy can be recovered and ultimately consumed in the propulsion nozzle.
  • the mounting of the prevaporizing device on the axis of the reheat chamber is an advantageous arrangement since it enables the central zone or core of the reheat chamber (an area which is normally difficult properly to exploit), to participate in the combustion process.
  • the pure hot air injected into this zone promotes the creation of a local combustion which can be considered as a pilot flame and can help to improve stability, especially at high altitudes.
  • FIGS. and 11 relate to a variant embodiment in accordance with which a prevaporizing device 46 comprises a distributor pipe 49 of substantially peripheral extent linking a feedpipe 47 to discharge passages 48a, 48b, said discharge pipes being connected to said distributor passages in parallel in substantially radial manner.
  • These discharge passages will preferably be split into two groups, one of which extends towards the axis of the reheat chamber while the other extends away therefrom.
  • the references 50a, 50b have been used to mark the respective exit sections, which advantageously open in the upstream direction, of the discharge passage 48a, 48b.
  • the feedpipe 47 and distributor pipe 49 can each be partitioned to form two compartments corresponding respectively to the one and the other of the two discharge passage groups.
  • reference 51 has been used to indicate a partition of this kind
  • references 52a, 52b to indicate the two compartments resulting from the division of the distributor pipe 49.
  • means can be provided in order selectively to regulate the flow of fuel entering each of these compartments in order to be able to vary the richness of the mixture leaving the prevaporizing device to accord with the desired local distribution in the reheat chamber.
  • FIG. 10 relates to the case where the prevaporizing devices 46 are carried on the periphery of the reheat chamber, for example through the medium of the heat shield 10.
  • FIG. 11 relates to the case where the prevaporizing devices 46 are carried in substantially symmetrical fashion by an arrangement of two coaxial profiled rings 53, 54 similar to the rings 41, 42 described in relation to FIG. 7, the distributor pipe 49 extending through the space defined between these two rings.
  • the rings contain openings in their leading edges, through which the discharge passages 48a, 48b project into the chamber in the upstream direction.
  • an improved burner for the reheat chamber in the form of a fuelprevaporizing device comprising:
  • profiled ring of generally gutterlike crosssectional shape open in the downstream direction with respect to the general direction of flow of gases through the reheat chamber, said profiled ring supporting the prevaporizing device and having orifices in its leading edge adapted to receive the discharge passages.
  • a reheat burner as claimed in claim 1 wherein said ring is formed with supplementary openings in its leading edge.
  • a reheat burner as claimed in claim 1 wherein the prevaporizing device is supported substantially symmetrically 1 by an arrangement of two profiled rings located coaxially and connected together by substantially radial intercommunicating stays, said stays likewise having a generally gutter shape open in the downstream direction, and also having openings in their respective leading edges, which are adapted to receive in star arrangement discharge passages forming part of the prevaporizing device.
  • a reheat burner as claimed in claim 1 wherein the prevaporizing device is supported in substantially symmetrical fashion by an arrangement of two rings, and a distributor pipe linking the feedpipe to the discharge pipes extends through the space defined between said rings.

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US861918A 1968-10-02 1969-09-29 Burners for reheat combustion chambers Expired - Lifetime US3633361A (en)

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US3757522A (en) * 1971-07-16 1973-09-11 Moteurs D Aviat D Et Const Devices for pre-vaporising liquid fuel
US3977186A (en) * 1975-07-24 1976-08-31 General Motors Corporation Impinging air jet combustion apparatus
US4389185A (en) * 1980-10-31 1983-06-21 Alpkvist Jan A Combustor for burning a volatile fuel with air
US4549402A (en) * 1982-05-26 1985-10-29 Pratt & Whitney Aircraft Of Canada Limited Combustor for a gas turbine engine
US4896501A (en) * 1987-10-22 1990-01-30 Faulkner Robie L Turbojet engine with sonic injection afterburner
US5603212A (en) * 1994-09-21 1997-02-18 Abb Management Ag Fuel injector for a self-igniting combustion chamber
US6250066B1 (en) 1996-11-26 2001-06-26 Honeywell International Inc. Combustor with dilution bypass system and venturi jet deflector
EP1491752A1 (fr) * 2003-06-25 2004-12-29 Snecma Moteurs Canaux de ventilation sur tôle de confluence d'une chambre de post-combustion
RU2335651C1 (ru) * 2007-02-01 2008-10-10 Федеральное государственное унитарное предприятие "Московское машиностроительное производственное предприятие "Салют" Форсажная камера газотурбинного двигателя
US20110061395A1 (en) * 2009-09-13 2011-03-17 Kendrick Donald W Method of fuel staging in combustion apparatus
CN105716120A (zh) * 2016-02-22 2016-06-29 中国科学院工程热物理研究所 一种燃油冷却式蒸发管结构
CN107044636A (zh) * 2017-04-27 2017-08-15 中国科学院工程热物理研究所 一种蒸发管燃烧室用燃油喷射装置
US20230184438A1 (en) * 2019-10-08 2023-06-15 Safran Helicopter Engines Pre-vaporisation tube for a turbine engine combustion chamber

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FR2188060B1 (enrdf_load_stackoverflow) * 1972-06-01 1976-06-11 Snecma
GB2098719B (en) * 1981-05-20 1984-11-21 Rolls Royce Gas turbine engine combustion apparatus
GB2112125B (en) * 1981-12-24 1985-06-26 Rolls Royce Fuel vapouriser for a gas turbine engine combustion chamber
US5070690A (en) * 1989-04-26 1991-12-10 General Electric Company Means and method for reducing differential pressure loading in an augmented gas turbine engine
RU2209992C1 (ru) * 2002-03-06 2003-08-10 Государственное унитарное предприятие Тушинское машиностроительное конструкторское бюро "Союз" - дочернее предприятие Федерального государственного унитарного предприятия "Российской самолётостроительной корпорации "МиГ" Форсажная камера двухконтурного турбореактивного двигателя
US7509797B2 (en) 2005-04-29 2009-03-31 General Electric Company Thrust vectoring missile turbojet
US7448199B2 (en) 2005-04-29 2008-11-11 General Electric Company Self powdered missile turbojet
US7475545B2 (en) 2005-04-29 2009-01-13 General Electric Company Fladed supersonic missile turbojet
US7424805B2 (en) * 2005-04-29 2008-09-16 General Electric Company Supersonic missile turbojet engine
GB201819748D0 (en) * 2018-10-12 2019-01-16 Rolls Royce Plc Afterburner system

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US2978868A (en) * 1959-12-21 1961-04-11 Gen Electric Concentric combustion system with cooled dividing partition
US3151453A (en) * 1961-05-09 1964-10-06 Rolls Royce Reheat combustion apparatus for a gas turbine engine
US3236048A (en) * 1963-09-25 1966-02-22 Gen Motors Corp Vaporizing manifold and flameholder for afterburners
US3330117A (en) * 1964-11-27 1967-07-11 Rolls Royce By-pass gas turbine jet engine

Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3757522A (en) * 1971-07-16 1973-09-11 Moteurs D Aviat D Et Const Devices for pre-vaporising liquid fuel
US3977186A (en) * 1975-07-24 1976-08-31 General Motors Corporation Impinging air jet combustion apparatus
US4389185A (en) * 1980-10-31 1983-06-21 Alpkvist Jan A Combustor for burning a volatile fuel with air
US4549402A (en) * 1982-05-26 1985-10-29 Pratt & Whitney Aircraft Of Canada Limited Combustor for a gas turbine engine
US4896501A (en) * 1987-10-22 1990-01-30 Faulkner Robie L Turbojet engine with sonic injection afterburner
US5603212A (en) * 1994-09-21 1997-02-18 Abb Management Ag Fuel injector for a self-igniting combustion chamber
US6250066B1 (en) 1996-11-26 2001-06-26 Honeywell International Inc. Combustor with dilution bypass system and venturi jet deflector
RU2347930C2 (ru) * 2003-06-25 2009-02-27 Снекма Каналы вентиляции на обшивке смешивания форсажной камеры
FR2856744A1 (fr) * 2003-06-25 2004-12-31 Snecma Moteurs Canaux de ventilation sur tole de confluence d'une chambre de post-combustion
US20050274114A1 (en) * 2003-06-25 2005-12-15 Snecma Moteurs Ventilation channels in an afterburner chamber confluence sheet
US6976361B1 (en) 2003-06-25 2005-12-20 Snecma Moteurs Ventilation channels in an afterburner chamber confluence sheet
EP1491752A1 (fr) * 2003-06-25 2004-12-29 Snecma Moteurs Canaux de ventilation sur tôle de confluence d'une chambre de post-combustion
RU2335651C1 (ru) * 2007-02-01 2008-10-10 Федеральное государственное унитарное предприятие "Московское машиностроительное производственное предприятие "Салют" Форсажная камера газотурбинного двигателя
US20110061390A1 (en) * 2009-09-13 2011-03-17 Kendrick Donald W Inlet premixer for combustion apparatus
US20110061392A1 (en) * 2009-09-13 2011-03-17 Kendrick Donald W Combustion cavity layouts for fuel staging in trapped vortex combustors
US20110061391A1 (en) * 2009-09-13 2011-03-17 Kendrick Donald W Vortex premixer for combustion apparatus
US20110061395A1 (en) * 2009-09-13 2011-03-17 Kendrick Donald W Method of fuel staging in combustion apparatus
US8549862B2 (en) 2009-09-13 2013-10-08 Lean Flame, Inc. Method of fuel staging in combustion apparatus
US8689562B2 (en) 2009-09-13 2014-04-08 Donald W. Kendrick Combustion cavity layouts for fuel staging in trapped vortex combustors
US8689561B2 (en) 2009-09-13 2014-04-08 Donald W. Kendrick Vortex premixer for combustion apparatus
US8726666B2 (en) * 2009-09-13 2014-05-20 Donald W. Kendrick Inlet premixer for combustion apparatus
CN105716120A (zh) * 2016-02-22 2016-06-29 中国科学院工程热物理研究所 一种燃油冷却式蒸发管结构
CN107044636A (zh) * 2017-04-27 2017-08-15 中国科学院工程热物理研究所 一种蒸发管燃烧室用燃油喷射装置
CN107044636B (zh) * 2017-04-27 2018-11-06 中国科学院工程热物理研究所 一种蒸发管燃烧室用燃油喷射装置
US20230184438A1 (en) * 2019-10-08 2023-06-15 Safran Helicopter Engines Pre-vaporisation tube for a turbine engine combustion chamber
US11841140B2 (en) * 2019-10-08 2023-12-12 Safran Helicopter Engines Pre-vaporization tube for a turbine engine combustion chamber

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FR1588974A (enrdf_load_stackoverflow) 1970-03-16
GB1273017A (en) 1972-05-03

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