US3328956A - Pulsating combustion process and burner apparatus - Google Patents

Pulsating combustion process and burner apparatus Download PDF

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US3328956A
US3328956A US541473A US54147366A US3328956A US 3328956 A US3328956 A US 3328956A US 541473 A US541473 A US 541473A US 54147366 A US54147366 A US 54147366A US 3328956 A US3328956 A US 3328956A
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combustion
chamber
gas
combustion chamber
fuel
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US541473A
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English (en)
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Seewald Friedrich
Siencnik Lukas
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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
    • F23R7/00—Intermittent or explosive combustion chambers
    • D—TEXTILES; PAPER
    • D02—YARNS; MECHANICAL FINISHING OF YARNS OR ROPES; WARPING OR BEAMING
    • D02J—FINISHING OR DRESSING OF FILAMENTS, YARNS, THREADS, CORDS, ROPES OR THE LIKE
    • D02J13/00—Heating or cooling the yarn, thread, cord, rope, or the like, not specific to any one of the processes provided for in this subclass
    • D02J13/005—Heating or cooling the yarn, thread, cord, rope, or the like, not specific to any one of the processes provided for in this subclass by contact with at least one rotating roll
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/02—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the jet being intermittent, i.e. pulse-jet
    • F02K7/06—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the jet being intermittent, i.e. pulse-jet with combustion chambers having valves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
    • F02M1/00—Carburettors with means for facilitating engine's starting or its idling below operational temperatures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
    • F02M2700/00—Supplying, feeding or preparing air, fuel, fuel air mixtures or auxiliary fluids for a combustion engine; Use of exhaust gas; Compressors for piston engines
    • F02M2700/43—Arrangements for supplying air, fuel or auxiliary fluids to a combustion space of mixture compressing engines working with liquid fuel
    • F02M2700/4302—Arrangements for supplying air, fuel or auxiliary fluids to a combustion space of mixture compressing engines working with liquid fuel whereby air and fuel are sucked into the mixture conduit
    • F02M2700/4392—Conduits, manifolds, as far as heating and cooling if not concerned; Arrangements for removing condensed fuel

Definitions

  • This invention relates in general to a pulsating combustion process and burner apparatus therefor of the type wherein a combustion supporting gaseous charge is introduced into the intake of a combustion chamber, and fuel is injected into said gaseous charge for explosive combustion therewith within the chamber, resulting in a pressure rise within the chamber and the forcible expulsion of combustion products from the exhaust of said chamber, followed by a pressure drop in the combustion chamber induced by the momentum of such expelled gases, and then by the introduction of a fresh gas charge into the chamber for repeating the combustion cycle.
  • this combustion process is known in the prior art as disclosed for example by German Patent 523,655, and as more commonly exemplified by the pulse jet engine for the German V-l missile.
  • the combustion-supporting gas is preheated to a temperature which causes spontaneous ignition of the fuel injected into a combustion chamber containing a charge of the gas, thereby dispensing with the need for any other ignition means.
  • the invention provides for externally preheating the combustion-supporting gas, either independently or by heat derived from the combustion chamber, so that the aid of previous combustion cycle backwash is not required to achieve spontaneous fuel ignition. Consequently, the
  • United States Patent ice combustion cycle and burner apparatus of the invention can be controllably operated at various combustion gas generation rates and back pressures so as to make it practical forpower generation. With the invention, no longer must the combustion cycle timing be run in strict accordance with the resonant frequency of the combustion chamber.
  • combustion-supporting gas and fuel generally signify any two components which react exothermically with each other when in admixture at an ignition temperature, and which by themselves are incapable of any exothermic chemical reaction.
  • the combustion-supporting gas can be air
  • the fuel can be gasoline, oil, or in general any substance which is combustible with air.
  • the invention is not limited to such commonly designated fuel and combustion-supporting components, but is also applicable to other exothermically reacting fuel and oxidizer combinations, such as hydrogen and fluorine, hydrogen peroxide and kerosene, etc.
  • the combustion referred to herein is the result of an exothermic chemical reaction of one substance which is chemically oxidized and another substance which functions as an oxidizer and which is chemically reduced as a result of such combustion.
  • the combustion supporting component can be a gas or a vapor as can be the fuel component which is injected into the combustion chamber in a finely divided form, such as liquid droplets, vapor, or even a sprayed powder.
  • the fuel component' can be introduced first into the combustion charnber and then the oxidizer component injected therein, or vice versa.
  • Another object of the invention is to provide a pulsating combustion process, as aforesaid, which can be selectively varied as to the rate of combustion product generation.
  • a further object of the invention is to provide a pulsating combustion process, as aforesaid, which is substantially independent of the combustion chamber dimensions.
  • a further object of the invention is to provide a pulsating combustion process, as aforesaid, which can be operated at a selected combustion product generation rate over a Wide range of exhaust back pressures.
  • a further object of the invention is, to provide a burner apparatus for performing the aforesaid pulsating combus tion process.
  • a further object of the invention is to provide a burner apparatus, as aforesaid, having a plurality of combustion chambers supplied with combustion-supporting gas and fuel in a continuous cyclical sequence for greater output and thermal efficiency.
  • a further object of the invention is to provide a burner apparatus, as aforesaid, in which preheating of the combustion-supporting gas is accomplished externally of the combustion chamber from heat at least partially derived therefrom.
  • a further object of the invention is to provide a burner apparatus, as aforesaid, having a rotary intakevalve means controlling the admission of combustion-supporting gas to each combustion chamber and driven by the flow of such gas through said intake valve.
  • Still another and further object of the invention is to provide a burner apparatus, as aforesaid, wherein the fuel Patented July4, 1967 is injected into each combustion chamber by a nozzle carried by the rotary intake valve means.
  • FIG. 1 is a schematic illustration of a pulsating combustion burner of the type used in the prior art
  • FIG. 2 is a schematic illustration, partly in section, of a pulsating combustion burner according to a preferred embodiment of the invention
  • FIG. 3 is a schematic illustration of the burner shown in FIG. 2 as viewed at a section taken along line II therein;
  • FIG. 4 is a schematic illustration, partly in section, of a pulsating combustion burner according to another embodiment of the invention.
  • FIG. 5 is a schematic illustration of the burner shown in FIG. 4 as viewed at a section taken along line IIII therein;
  • FIG. 6 is a schematic illustration, partly in section, of a pulsating combustion burner according to a further embodiment of the invention.
  • FIG. 7 is a schematic illustration of the burner shown in FIG. 6, as viewed along the direction indicated by line III-III therein.
  • FIG. 1 illustrates a typical prior art burner apparatus having a tubular combustion chamber B.
  • fresh charges of combustion-supporting gas such as air
  • flapper intake valves F which are either positively controlled by external means (not shown) or are automatically operated in the nature of check valves so as to permit air flow only into the combustion chamber B and to block the escape of any combustion products therefrom through the inlet E.
  • a fuel injection nozzle N is located and extends into communication with the interior of the combustion chamber B.
  • the other end of the combustion chamber tube B namely its exhaust outlet end A, is open to discharge the gaseous products of combustion therefrom.
  • the exhaust outlet A can be provided with a valve device (not shown) installed thereat which is operable to close said exhaust outlet A during combustion of the fuel-air mixture, so as to achieve a constant-volume type of combustion.
  • the time that is required in order to raise all of the fresh air charge in the combustion chamber to the necessary temperature depends, on the one hand, on the tube walls having a certain minimum temperature, and on the other hand it depends on the length of the mixing paths and hence upon the diameter of a tubular combustion chamber B.
  • the time of the arrival of the backwash pressure wave is established by the resonant frequency of the combustion chamber tube B and depends substantially upon its length.
  • the length and the diameter of the tube must be coordinated with one another.
  • the operating combustion cycle frequency also is fixed, and as long as the ignition and combustion are brought about in the above-described manner, very little can be done to shift this frequency since if any significant frequency shift were attempted, the heating and ignition would no longer occur in the correct time sequence, and would cause the tube to cease operating as a pulsating combustion chamber.
  • the pulsating combustion tube B of the prior art and those of the patents or proposals thus far known represent pulsating combustion burner apparatus that, on account of their excessively poor efiiciency, are not competitive with stationary burners presently in use. Furthermore, due to their poor regulatability and insufficient adaptability to the changing conditions of practice, their practical value is still futher reduced to such an extent that successful application has been achieved in no field of the art, with the exception of certain special military applications.
  • the invention provides a process for the operation of one or more pulsating combustion tubes wherein the ignition and the ignition timing of the reacting gas mixture is relatively independent of the operating conditions and dimensions of the combustion chamber.
  • the process of the invention is characterized in that the fresh combustion-supporting charge that flows in during the charging portion of the combustion cycle at first consists only of those components of the combustible mixture which do not react with one another under the given operating conditions, and is heated before or during the intake process to such a temperature that, upon the addition of the components still lacking, the combustion reaction reliably and spontaneously takes place.
  • the still unignitable charge is thus not heated merely in the inevitable way described above, by the hot tube wall and by mixture with hot gas residues, but instead additional heat is added to it before and/or during its flow into the combustion chamber, and at least so much heat is added that the said first component charge reaches the mixture ignition temperature, so that after the remaining component or components of the mixture are introduced into the combustion chamber, spontaneous ignition and combustion will take place with certainty, without requiring the additional action of the backwash pressure wave.
  • the difference between the pulsating burner tube of the prior art process of operation and the combustion tube operated according to the new process can be approximately equated with the difference between Otto-cycle and Diesel-cycle engines.
  • ignition is additionally required.
  • Diesel-cycle engine the temperature is so elevated by high compression of the air charge that, when the fuel is injected, ignition reliably takes place.
  • the role which is played by the ignition spark in the Otto-cycle engine is played in the prior-art pulsating combustion tube, such as the Schmidt tube, by the above-mentioned pressure wave.
  • the cooperation of the pressure wave is not necessary because the fresh oxidizer gas is so heated that ignition and combustion reliably occur evenwithout the pressure Wave.
  • the process of the invention it is brought about that the moment in each cycle at which the combustion takes place is determined, not as in the prior art processes described previously, by the design of the tube, but rather it can be selected freely within wide limits by the appropriate controlling of the time of the fuel injection. Furthermore, it is possible by increasing the back pressure and also by varying the operating frequency of the tube by changing its length, to vary the combustion gas output within wide limits, without thereby impairing the reliability of the ignition and the quality of the combustion. A combustion chamber operating on this principle is thus controllable over a correspondingly Wide range. Furthermore, it can be made to operate at a higher back pressure without the danger of ignition failure.
  • One or the other of the possibilities otfered can be utilized to a greater or lesser extent, depending on the desired application.
  • auxiliary equipment such as preheater, control system, injection system, etc. can be used in whole or in part for all or several of these combustion chambers.
  • FIGS. 2 and 3 show a combustion chamber B with conventional automatic intake valves F, wherein the preheating of the gas aspirated through the intake duct P is accomplished by the fact that this gas passes around the combustion tube B, which can be provided with cooling fins (not shown).
  • FIGS. 4 and 5 there is shown a pulsating combustion burner according to another embodiment of the invention in which the preheating is performed by a separate gas heater (not shown) of any suit-able conventional type.
  • a separate gas heater not shown
  • previously heated gas or hot air flows in through the duct Z.
  • a rotary intake valve having a disk St provided with one or more openings G, hereinafter called control slits, which slide over the intake opening E or openings of the combustion chamber B or combustion chamber B when the disk St is rotated, and uncover these intake ports E for admitting gas charges to each chamber B in continuous cyclical succession.
  • the fuel line L and the injection nozzle D can be allowed to rotate with this disk. Then, due to centrifugal action in the radial part of the fuel line L, the pressure is developed ahead of injection nozzle D which is required for the injection. In this manner the need for a fuel pump can be eliminated.
  • FIG. 4 is schematically represented pulsating combustion burner embodiment with variable effective combustion tube B' length.
  • the outer telescoping tube portion T can be extended to various distances beyond the end of the burner tube B, thus varying the effective tube B length and the natural frequency.
  • FIGS. 6 and 7 show by way of example another embodiment in which a number of combustion chambers B are combined into a unit.
  • the combustion chambers B are so arranged in series that together they form the wall of a cylindrical tube.
  • the preheating which can be done by separate gas heaters ahead of the intake Z or in some other manner, as for example within the unit itself as in FIG. 2, has been omitted for greater clarity.
  • the control valve disk St with the control slit G or control slits, and with the fuel conduit L and injection nozzle or nozzles D, can in this case be arranged as in the case of the single tube represented in FIGS. 4 and 5.
  • FIGS. 6 and 7 there is provided in FIGS. 6 and 7 means for increasing the efficiency of the combustion chamber or chambers by supercharging with compressed gas or air, as the case may be, especially in the case of back pressure beyond the degree that can be achieved in the charging cycle in pulsating tubes by the use of the gas vibrations alone in the prior art manner.
  • a passage K corresponding to the bucket trough of a turbocompressor is created in the control valve disk St, the intake opening of said passage K being concentric with the disk St, and the discharge opening wiping over the intake port or ports of the combustion tube or tubes.
  • the discharge opening of passage K rotating with control disk St is wholly or partially opposite a combustion tube B, the gases or air compressed in the rotating passage K flow into the combustion chamber which already contains a charge which has flowed in through the control slit G under the effect of the gas vibration process.
  • the driving of the above described controlling members and the operation of the injection line combined therewith and of the compression passage can be performed by an outside drive.
  • These members can also be driven by a turbo drive arrangement consisting of individual vanes Sch or of a bucket wheel which is hit by the gases flowing into each combustion chamber B.
  • buckets or vanes Sch are provided in the control slit G, which like the buckets of turbines deflect the flowing gases. In this manner the flow produces a force which sets the wheel and the disk combined with it into rotation.
  • the rotary speed of the disk can be regulated, as is customary in turbines, by guiding mechanisms or other methods of varying the flow, or by increasing the mechanical work which the disk has to perform by connecting a work-dissipating apparatus to it, such as a dynamo for the production of electrical energy.
  • the preheated combustion-supporting gas can be supplied to each of the chambers B in succession by the duct Z and/or the duct Z Gas from duct Z flows directly through the control aperture G into each combustion chamber B" as the disk St rotates. Gas from duct Z flows through the radial passage K into the aperture G and thence into the combustion chambers B, and is delivered at a supercharging pressure by reason of centrifugal compression in passage G resulting from the rotation of the disk St.
  • the ducts Z and Z can be expediently connected to receive preheated gas from a common duct (not shown), which is either heated itself or is arranged to pass its gas flow through a preheating apparatus (not shown).
  • the duct Z and associated radial passage K can be omitted.
  • the disk St has a somewhat substantial thickness, and such thickness can be utilized to advantage to raise the effective temperature of the several combustion chambers B. If one or more cavities are machined into the disk St, preferably blind cavities, and arranged so as to define an extended portion of each combustion chamber as the disk S! is rotated to position such cavity or cavities into adjoining relation with the inlet of each successive chamber B, the effective temperature of said chambers B will be raised because the cavity portions participate in each combustion process in all combustion chambers B of the group.
  • a combustion supporting gaseous charge is introduced into the intake of a combustion chamber, and fuel is v injected into said gaseous charge for explosive combustion therewith within the chamber, resulting in a pressure rise within said chamber and the forcible expulsion of gaseous combustion products from the exhaust of said chamber, followed by a pressure drop in the combustion chamber induced by the momentum of such expelled gases, and then by the introduction of a fresh gaseous charge into the chamber for repeating the combustion cycle
  • the improvement which comprises preheating a combustion supporting gas to an elevated temperature at which spontaneous ignition of the fuel occurs upon injection into a charge of such preheated gas, introducing in repetitive cyclical succession, a charge of said preheated gas into each of a plurality of combustion chambers, and injecting a predetermined quantity of fuel into each of said combustion chambers following the introduction of a preheated gas charge therein for spontaneous ignition and combustion therewith.
  • a pulsating combustion burner apparatus which comprises a combustion chamber having an inlet disposed for receiving charges of combustion-supporting gas for combustion with fuel injected therein, and an exhaust outlet for discharging the gaseous products of such combustion, intake valve means interposed in the gas flow path to the inlet of said combustion chamber and operable to admit a predetermined gas charge thereto during each pulsating combustion cycle, means defining a nozzle disposed for communication with a source of fuel and for communication with said combustion chamber to inject a predetermined quantity of fuel therein during each combustion cycle, and a duct disposed for communication with a combustion-supporting gas source and for communication with said intake valve means for supplying charges of combustion-supporting gas therethrough to said combustion chamber, said duct being disposed to receive heat from said combustion chamber to preheat the gas flowing through said duct to thereby raise the temperature of each gas charge introduced into the combustion chamber to a level which spontaneously ignites the fuel injected into said chamber.
  • a pulsating combustion burner apparatus which comprises at least one combustion chamber having an inlet disposed for receiving charges of combustion-supporting gas for combustion with fuel injected therein, and an exhaust outlet for discharging the gaseous products of such combustion, nozzle means disposed for communication with a source of fuel and for communication with each combustion chamber to inject a predetermined quantity of fuel therein during each pulsating combustion cycle, rotary gas intake valve means interposed in the gas flow path to the inlet of each combustion chamber and disposed for rotation relative thereto, to admit a predetermined gas charge thereto during each combustion cycle, a duct disposed for communication with a combustion-supporting gas source and for communication with said rotary intake valve means for supplying charges of combustion-supporting gas therethrough to each combustion chamber, and means for preheating the gas supplied through said duct to raise the temperature of each gas charge introduced into each combustion chamber to a level which spontaneously ignites the fuel injected therein.
  • said rotary intake valve means includes a disk member having an. aperture and disposed for rotation relative to each combustion chamber in wiping contact with the inlet thereof to admit through said aperture a combustion supporting gas charge for each combustion chamber in continuos cyclical succession, and to block the escape of combustion products through the inlet of each combustion chamber.
  • the apparatus according to claim 8 including at least one blade member supported by said disk member and disposed across the aperture thereof for reaction with the gas flow therethrough to rotatably drive said disk member.
  • said nozzle means includes a nozzle supported by said disk member for rotation therewith and disposed for extension within the aperture thereof to inject fuel into each combustion chamber along with the gas charge introduced therein through said aperture.
  • the apparatus according to claim 8 including means defining a radial passage extending through said disk member and disposed for communication with said aperture and for communication with said duct to pass preheated combustion-supporting gas into each combustion chamber in succession, and to centrifugally compress said gas to a supercharging pressure by the rotation of said disk member.
  • each combustion chamber is generally tubular and has a length portion disposed for telescopic movement with respect to the remaining portion of the combustion chamber to accommodate selective adjustment of the effective overall length of the combustion chamber.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Textile Engineering (AREA)
  • Feeding And Controlling Fuel (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)
US541473A 1965-04-01 1966-03-30 Pulsating combustion process and burner apparatus Expired - Lifetime US3328956A (en)

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AT (1) AT260624B (enrdf_load_stackoverflow)
BE (1) BE678802A (enrdf_load_stackoverflow)
CH (1) CH458836A (enrdf_load_stackoverflow)
GB (1) GB1107196A (enrdf_load_stackoverflow)
NL (1) NL6604262A (enrdf_load_stackoverflow)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3768926A (en) * 1971-11-30 1973-10-30 R Pegg Pulse jet rotor drive for helicopter
US3877219A (en) * 1972-06-30 1975-04-15 Mtu Muenchen Gmbh Constant volume combustion gas turbine with intermittent flows
WO1987006976A1 (en) * 1986-05-14 1987-11-19 Daniel Buchser Ram jet engine

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0102411A1 (en) * 1982-09-08 1984-03-14 Joseph S. Adams Compression wave former
DE10251445B4 (de) 2002-11-05 2005-09-01 New-Logistics Gmbh Behälter zum Transport von Gütern

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2594765A (en) * 1945-10-06 1952-04-29 Esther C Goddard Resonance combustion apparatus
US2659198A (en) * 1950-08-04 1953-11-17 Harvey A Cook Explosion-cycle inducer-disk valve turbojet engine for aircraft propulsion
US2671314A (en) * 1950-01-26 1954-03-09 Socony Vacuum Oil Co Inc Gas turbine and method of operation therefor
US2795104A (en) * 1950-08-23 1957-06-11 Maschf Augsburg Nuernberg Ag Stationary jet engine power plant with preposed turbine
US2937500A (en) * 1957-10-02 1960-05-24 Jr Albert G Bodine Resonant combustion products generator with heat exchanger
US2942412A (en) * 1952-09-30 1960-06-28 Curtiss Wright Corp Pulse detonation jet propulsion

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2594765A (en) * 1945-10-06 1952-04-29 Esther C Goddard Resonance combustion apparatus
US2671314A (en) * 1950-01-26 1954-03-09 Socony Vacuum Oil Co Inc Gas turbine and method of operation therefor
US2659198A (en) * 1950-08-04 1953-11-17 Harvey A Cook Explosion-cycle inducer-disk valve turbojet engine for aircraft propulsion
US2795104A (en) * 1950-08-23 1957-06-11 Maschf Augsburg Nuernberg Ag Stationary jet engine power plant with preposed turbine
US2942412A (en) * 1952-09-30 1960-06-28 Curtiss Wright Corp Pulse detonation jet propulsion
US2937500A (en) * 1957-10-02 1960-05-24 Jr Albert G Bodine Resonant combustion products generator with heat exchanger

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3768926A (en) * 1971-11-30 1973-10-30 R Pegg Pulse jet rotor drive for helicopter
US3877219A (en) * 1972-06-30 1975-04-15 Mtu Muenchen Gmbh Constant volume combustion gas turbine with intermittent flows
WO1987006976A1 (en) * 1986-05-14 1987-11-19 Daniel Buchser Ram jet engine

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AT260624B (de) 1968-03-11
BE678802A (enrdf_load_stackoverflow) 1966-09-01
CH458836A (de) 1968-06-30
NL6604262A (enrdf_load_stackoverflow) 1966-10-03
GB1107196A (en) 1968-03-20

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