US3473879A - Shock wave burner - Google Patents

Shock wave burner Download PDF

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Publication number
US3473879A
US3473879A US3473879DA US3473879A US 3473879 A US3473879 A US 3473879A US 3473879D A US3473879D A US 3473879DA US 3473879 A US3473879 A US 3473879A
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Prior art keywords
burner
combustion
shock wave
device
fuel
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Expired - Lifetime
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Bertold Berberich
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Siemens AG
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Siemens AG
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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23CMETHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C15/00Apparatus in which combustion takes place in pulses influenced by acoustic resonance in a gas mass
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23CMETHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C99/00Subject-matter not provided for in other groups of this subclass
    • F23C99/003Combustion process using sound or vibrations
    • HELECTRICITY
    • H01BASIC ELECTRIC ELEMENTS
    • H01SDEVICES USING STIMULATED EMISSION
    • H01S3/00Lasers, i.e. devices for generation, amplification, modulation, demodulation, or frequency-changing, using stimulated emission, of infra-red, visible, or ultra-violet waves
    • H01S3/0007Applications not otherwise provided for
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23CMETHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2700/00Special arrangements for combustion apparatus using fluent fuel
    • F23C2700/02Combustion apparatus using liquid fuel
    • F23C2700/023Combustion apparatus using liquid fuel without pre-vaporising means
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23CMETHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/99003Combustion techniques using laser or light beams as ignition, stabilization or combustion enhancing means
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00006Using laser for starting or improving the combustion process
    • YGENERAL 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
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10STECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S65/00Glass manufacturing
    • Y10S65/04Electric heat

Description

Original Filed Sept. 22. 1966 3 Suns-Sheet 1 Fig. 1

a. BERBERICH Y l 3,473,879 'snocx uvz avanza voriginal man sept-.22, 1966. s shunts-snee: 2

ocr. 21, 1969 a :sERBERrcH 3,473,879 ssocx mrs am@ f l I 3 Sheets5heet 3 I 0d. 2l, 1969*.. ,Y

cm'giuax med sept. 22.` 196s 3,473.879 SHDCK WAVE BURNER Bertold Berberieh, Erlangen, Germany, assigner to Siemens Aktiengesellschaft, a corporation of Germany Continuation of application Ser. No. 581,284, Sept. 22, 1966. This application Sept. I6, 1968, Ser. No. 768,587 Claims priority, applictignGGrmany, Sept. 25, 1965,

.9, 6 Int. Cl. F23c 3/02; H018 3/00 U5. Cl. 431--1 4 Claims ABSTRACT F THE DISCLOSURE Shock wave burner includes equipment for periodically injecting fuel-oxidant mixture into a constant-volume combustion chamber, a laser pulse device for directing an intermittent beam of laser radiation pulses into the chamber so as to repeatedly ignite fuel-oxidant mixture supplied thereto, and equipment for synchronizing the frequency of injection of the fuel-oxidant mixture into the chamber with the pulse frequency of the laser beam.

kcal. o-10cm can be achieved.

Shock wave burners are generally constructed as oscillating burners provided with a burner head and an attached oscillation tube. The periodically ignited combustion occurs in the burner head, which can have the con struction of a combustion chamber, and thereafter the hot flaming combustion gases driven by the pressure waves discharge through the oscillation tube. Check valves are provided to permit the negative pressure produced in the bumer head after a combustion to suck in new starting components. A pressure wave reflected to the burner head from the end of the oscillation tube then igniles the next combustion. The frequency of ignition is largely determined by the dimensions of the burner head and of the oscillation tube.

(Journal ofthe German Engineering Society), vol. 92

(1950), No. 16, pp. 393-399, as well as VDI-Zeitschrift,

vol. 94 (1952), N0. 31, pp. 1005-1008.

A further disadvantage of oscillating burners is that they can only operate up to pressures that are slightly United States Patient above atmospheric pressure at the oscillation tube end.

They could therefore not be employed heretofore for driving turbines. Furthermore, the constant but unstable tiring frequency permits no eontrolof the power.

j 3,473,879 Patented Oct. 21, 1969 "ice It is accordingly an object of my invention to provide a bumer of constant-volume construction which can oper ate also at pressures greater than atmospheric pressure.

It is a further object of my invention to provide such a burner whose power can be easily controlled.

It is yet another object of my invention to provide a burner of this type whose rng frequency can ne very accurately adjusted.

It is moreove.` a general object of my invention to provide a burner for constant-volume combustion which avoids the aforementioned disadvantages of the heretofore known burners of this general type.

With the foregoing and other objects in view, I pro' vide in accordance with my invention a shock have burner having a combustion chamber for constant-volume combustion with a laser ignition device which is adjusted to the injection frequency of a combustible mixture. The shock wave burner of my invention can consequently operate without an osciilatory tube as heretofore required.

More particularly in accordance with my invention I provide a shock wave burner that will permit the periodic constant-volume combustions to occur without a reflecting pressure wave. 'lne-.starting material components for the combustion are supplied, for example, bv injection in premixed condition. Macromixing takes pas. at the combustion front, whereby the liquid fuel is comminuted into cells that are larger, however, than molecules. The fuel cells are then continuously entrained by the gasified oxidation skins cr layers in the vortex of the shock wave, whereby a further combustion and intermixing occurs. 'Ihis constiuten a micromixing phase, after which molecular digusion occurs. The vortices in the shock wave are produced because of the relative motion between the large masses of the slow moving fuel particles and the more rapidly moving particles of the oxidizing medium.

Ignition by laser beam not only permits dispensing with an oscillation tube but also, in specific applications, with the use of nozzles or tubes outside of the oscillation tube frequency. The frequency of combustions is changeable stepwise to a further range during the operation of the laser by adjusting the pulse frequency of the excitation energy source for the laser material. In addition, with the shock wave bumer of my invention, the combustion intensity is capable of being better controlled by snitable selection of the degree of focusing and of the beam intensity. It is consequently possible to construct a'suitable burner for a particular use or purpose without being limited by prerequisites. Furthermore, the constancy or steadiness of the combustion frequency permits several burners to be operated flow-wise in parallel. They can be operated in strokes having the same or alternating directions.

In the eopending application Ser. No. 562,233, filed July l, 1966, of B. Andress and L. Kuchelbacher, as-

signed to the same assignee as the instant application, it has been proposed that oil-tired boilers be ignited by a laser beam, however this copending application relates to a constant-pressure combustion and not to a constanty volume combustion as in the instant application.

But suitable guidance of the laser beam, such as by the Other features which are considered as characteristic for the invention are set forth in the appended claims.

Although the invention is illustrated andv described herein as embodied in shock wave burner, it is nevertheless not intended to be limited to the details shown, since various modifications and structural changes may be made therein without departing from the spirit of the of the claims.

The Construction and method of operation of the ini vention, together with additional objects and advantages thereof, will be best understood from the following description of specific embodiments when read in connection with the accompanying drawings, in which:

FIG. 1 is a schematic and partly sectional view of a shock wave burner constructed in accordan with my invention;

FIG. 2 shows the burner of FIG. l modified to accommodale auxiliary equipment:

FIG. 3 is a schematic circuit diagram for the burner assembly of FIG. 2; and v FIG. 4 is a schematic circuit diagram corresponding to the diagram of FIG. 3 for a parallel connection of three burner assemblies in accordance with the invention.

Referring now to the drawings and iirst particularly to FIGS. 1 and 2 thereof, there is shown a pressure wave burner in accordance with my invention having a combustion chamber 1 into which there extends a laser ignition device 2 and an injector device 3 for injecting fuel into the chamber 1, and a control stage 4 connected between the ignition device 2 and the injector device 3. The combustion chamber interior space 5 has the conventional pear shape which has been found to be most suitable heretofore for constant-volume combustions. The inner combustion space 5 can, however, also have a spherical or ellipsoidal form, for example. The combustion chamber 1 is provided with an outlet opening 6 which, as shown, is formed with a nozzle 7 of the Venturi type. Suitable structural components can be connected for any desired purpose to the flange 8 of the outlet tube 9. A laser beam 10 of the ignition device 2 is focused at a location in the vicinity of the center line or center axis 11 of the combustion chamber 1 near the outlet opening 6 whenever high temperatures are to be attained with strong shock waves. If the laser beam 10 is focused more to the center of the combustion chamber space 5, particularly in spherical combustion chamber spaces, more rapid combustions are achieved permitting a greater frequency of combustions.

The combustion chamber space 5 and the outlet opening 6 are of such dimensions that constant-volume combustions are achieved when the throughput through the injection device 3 is so adjusted that the respective hot combustion gases ow out of the combustion space 5 before new fuel is injected into it.

The laser ignition device has the following construction: In a laser head 12 a ruby laser crystal 13 is provided as the laser substance and a tiash lamp 14 as excitation energy source. The ignition device for the ash lamp is symbolically shown in FIGS. 1 and 2 by a capacitor and a diode 16. However, the actual circuitry thereof will be described more fully hereinafter with respect to FIG. 3. A lens 17 is disposed in a tube t8 so that the laser beam is focused in a desired manner.

As an operating example, it can be assumed that adjustment is made to a ratio of oil to air of 1: 1,000. When the mixture is heated to 80 C. in a hot combustion chamber, a combustible mixture is thus provided which can be ignited by a laser pulse having an energy of substantially 1.5 watt-seconds (ws.) and a pulse duration of 0.5 milliseconds (m.s.).

When the ruby crystal has an opening angle of about 30 minutes, the laser beam can be focused through a lens 17 having a focal distance of one meter to a region of highest energy density of approximately 2 millimeters (mm.). This region of highest energy can be sut-,stan tially 2 centimeters (cm.) long. Light pulses of 0.3 to 2 milliseconds (ms.) duration are suitable for exciting the laser crystal. The propagation speed of the combustion operation with the pressure wave is about 1,000 meters per second (m./s.).

The ignition sequence is simply controlled by suitably adjusting the ignition circuit of the Bash lamp, as described hereinafter in greater detail with regard to FIG. 3. A control device 4 accordingly controls the ignition sequence. The ccntrol device 4 simultaneously acts upon the device 19 which controls the fuel supply or the throughput of the combustible fuel to the combustion chamber space 5. The fuel supply control device 19 can be provided with injection pumps of a type known in diesel motors. The starting materials, i.e. the fuel. proper and the oxidant therefor, can be supplied in turbulently intermixed form to the combustion space 5 by either being injected separately or through an injector device 3 which is in the form of a ring nozzle. The pulse sequence of the laser beam is synchronized with the injection frequency of the combustible mixture b'y means cf the control device 4.

In FIG. 3 there is again shown the tiash lamp 14 which is connected to the ignition device 16, which, with devices i9 and 23, hereinafter more fully described, is in turn connected to the control device 4. Thus FIG. 3 is a schematic circuit diagram of the embodiment shown in FIG. 2. A transformer 40 is located in the device 16 for stepping up the line voltage to approximately 1.5 kilovoits (kv.). capacitor 41 and rectifier 42 are connected t0 the secondary winding of the transformer 40. The capacitor 41 is virtually loaded to the peak value of the alternating voltage of the secondary coil. In a narrower sense, the ignition device comprises an ignition coil in v; ich a voltage pulse in tbe order of magnitude of 10 kilovolts (kv.) is supplied by a spark gap 45 from a circuit 44 which ignites the flash lamp 14. The energy for the fiash lamp 14 is supplied by the capacitor 41 from the transformed line voltage. The ignition operation is initiated by a current pulse from the control device 4 to the transformer 46. The assembly 16 and the control device 4 are connected to the alternating current conductors 47 of a power line.

The control device 4 consists primarily of a time-limit switch 48 which, in the interest of simplicity, is shown as a mechanical component. The time-limit switch 48 has a Contact arm 49 rotatable in a clockwise direction, which sequentially engages the contacts 50, 51 and 52. The contact 52 is displaceable as shown in FIG. 3. A lead 53 connects one phase of the voltage line 47 with the rotatable switch arm 49. Leads 54, 55 and 56 extend respectively from the contacts 50, 51 and 52 and connect with the terminals of the device 19, the ignition device 16 and the device 2S. The branching conductor 57 connects the second pole of the terminals with the return voltage line 4 1 The device 19 which controls the throughput of the oxidant, as well as the device 28 which controls the supply of the fuel, which is the reactive partner to the oxidant, can each essentially consist of a magnetic valve 58. If the circuit to the device 19, for example, were closed by the timer 48, current would ow through the coil 59 and would electromagnetically displace an iron core, for example, to actuate the valve member 60. The device 28 can have an analogous construction to that of the device 19 and can alsoinclude a coil 59 and a valve member 60. In the simplest case, the valve members 60 can open the pressurized supply conduits by the actuation 'of the magnetic valves.

By means of the control device 4, the circuit for the .device 19 is closed first and thereafter the circuit for the ignition device 16 and finally for the device 28 are closed. n

Therefore oxidant is initially injected into the combustion space 5, ignition is then effected and reaction material supplied. The time interval between the fuel injection and the injection of the reaction partner therefor, such as the oxidant, can be adjusted by suitably displacing the contact 52.

FIG. 4 shows a circuit for three shock wave burners that are operated in parallel and are alternately ignited. The burner of FIG. 4 has three devices 16a, 1Gb and 16e, and three devices for controlling the injection of y l I c oxidant 19a, 191: and 19e. The control device 4' thus is provided with three time-delay switches 48a, 48b and 48e, each of which is connected to one of the shock wave burners (not shown). It only one ignition device and one device for supplying fuel are to be controlled, the time delay m'tches, as shown in FIG. 4, only require two contacts which are engageahle by the respective switching arms 49 as they are rotated clockwise. lf the respective switching arms 49 of the three time-delay switches 48a, 48h and 48C are rotated with the same rotary speed they can be so adjusted that they are displaced relative to one another at a specific phase angle. The circuits of the components of the shock wave burners which are to be controlled are then closed in a specific sequence. It is understood, of course, that the contacts 50a to 51e can each be of a predetermined width in the rotary direction so as to hold the circuit closed for a specitic period of time.

For the shock wave burner constructed in accordance with my invention, a great number of practical applications are available. Thus, it can be utilized in furnace technology and in metallurgical engineering as well as for maintaining turbine installations. ln comparison with shock wave humers which operate according to the conventional principle of the oscillating burners, a higher efficiency of combustion is advantageously achieved with the burners of my invention at higher temperatures and especially also at a counter or reactive pressure.

When the shock wave burner of my invention is employed for supplying gas to MHD generators, a particularly favorable etiect achieved is that the hot gas zones determine the productive power or output of the gem erator while the wall material of the iiow channel is sub jected only to the lower temperature delivered through thc hot and cold gas zones.

In chemical processing engineering the materials which are to be reacted can be injected intermittently alone into the combustion chamber or with fuel materials which tend to remain neutral with respect to the materials entering into the reaction and their products. 1f the combustion frequency s kept very steady or constant, optimum operating conditions are thereby able to be adjusted.

When the shocl: wave burners constructed in accordance with my invention are to be installed in missiles or space vehicles that operate by jet propulsion or reaction drive, an essential advantage is afforded by my burner over the known oscillating burners, in that the nozzle shape of the burner of my invention can be Selected solely according to ight technology aspects. A-supersonic or Laval nozzle can accordingly be directly connected to the combustion chamber. With oscillating burners, how- Oscillating burners must rely, however, for ignition on reflecting waves.

I claim:

1. Shock wave burner comprising a combustion chamber for constantwolume combustion, said combustion chamber having a waste gas outlet opening, means for periodically injecting a. given quantity of ignitahle fueloxidant mixture at a given rate into said combustion chamber, ignition means comprising a laser pulse devce for directing an intermittent beam of laser radiation pulses inte said combustion chamber so as to repeatedly ignite fuel-oxidant mixture supplied thereto, means for synchronizing the frequency of injection of the fuel-oxidant mixture into said combustion chamber with the pulse frequency of said laser beam and for adjusting the flow rate of said fuel-oxidant mixture through said injecting means so that waste gas from an ignited quantity of fueloxidant mixture injected in a previous period discharges through said outlet opening prior to injecting into said combustion chamber fucloxidant mixture in said given quantity for the next-succeeding period.

2. Shock wave burner according to clairs-t 1, wherein said mixture injecting means is adapted to intermittently supply fuel and oxidant to said combustion chamber in stoichiometric proportions.

3. Shock wave burner according to claim 1, wherein said mixture injecting means is adapted to intermittently supply fuel and oxidant reactive with each other and at least one other material remaining neutral with respect to the reactive fuel and oxidant and the'reaction products thereof.

4. Shock wave burner according to claim l, wherein said combustion chamber is substantially pear-shaped.

References Cited UNITED STATES PATENTS 3,171,465 3/1965 Rydberg 431-1 3,177,651 4/1965 Lawrence 331-945 3,276,505 lO/ 1966 Huber 431--1 3,296,795 1/ 1967 Nielsen S31- 94.5

FREDERICK L. MATIESON, IR., Primary Examiner E. G. FAVORS, Assistant Examiner U.S. C1. XR.

l t e i

US3473879A 1965-09-25 1968-09-10 Shock wave burner Expired - Lifetime US3473879A (en)

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DE1965S0099662 DE1252974B (en) 1965-09-25 1965-09-25 Constant volume combustion chamber

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DE (1) DE1252974B (en)
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Cited By (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3796535A (en) * 1971-04-28 1974-03-12 Sourdillon Matricage Robinette Gas burners, especially for domestic appliances
US3861371A (en) * 1973-12-10 1975-01-21 Joseph Gamell Ind Inc Ignition system for engine
US4069004A (en) * 1975-06-20 1978-01-17 Societe Nationale Elf Aquitaine (Production) Device to emit shock waves, with adjustable capacity
US4302933A (en) * 1979-03-01 1981-12-01 Smith Marvin M Jet engine augmentor operation at high altitudes
US4556020A (en) * 1981-07-06 1985-12-03 General Motors Corporation Method and means for stimulating combustion especially of lean mixtures in internal combustion engines
US4726336A (en) * 1985-12-26 1988-02-23 Eaton Corporation UV irradiation apparatus and method for fuel pretreatment enabling hypergolic combustion
US4852529A (en) * 1986-03-07 1989-08-01 Bennett Automotive Technology Pty. Ltd. Laser energy ignition system
US4947640A (en) * 1989-02-28 1990-08-14 University Of Tennessee Research Corporation Gas turbine engine photon ignition system
US5257926A (en) * 1991-12-17 1993-11-02 Gideon Drimer Fast, safe, pyrogenic external torch assembly
US5361737A (en) * 1992-09-30 1994-11-08 West Virginia University Radio frequency coaxial cavity resonator as an ignition source and associated method
US5367869A (en) * 1993-06-23 1994-11-29 Simmonds Precision Engine Systems Laser ignition methods and apparatus for combustors
US5404712A (en) * 1992-10-06 1995-04-11 University Of Tennessee Research Corporation Laser initiated non-linear fuel droplet ignition
US5473885A (en) * 1994-06-24 1995-12-12 Lockheed Corporation Pulse detonation engine
US5515681A (en) * 1993-05-26 1996-05-14 Simmonds Precision Engine Systems Commonly housed electrostatic fuel atomizer and igniter apparatus for combustors
US5542247A (en) * 1994-06-24 1996-08-06 Lockheed Corporation Apparatus powered using laser supplied energy
US5552675A (en) * 1959-04-08 1996-09-03 Lemelson; Jerome H. High temperature reaction apparatus
US5769621A (en) * 1997-05-23 1998-06-23 The Regents Of The University Of California Laser ablation based fuel ignition
US5845480A (en) * 1996-03-13 1998-12-08 Unison Industries Limited Partnership Ignition methods and apparatus using microwave and laser energy
US6062018A (en) * 1993-04-14 2000-05-16 Adroit Systems, Inc. Pulse detonation electrical power generation apparatus with water injection
WO2001035021A1 (en) * 1999-11-12 2001-05-17 Sarcos, Lc A controllable combustion device
US6302682B1 (en) * 1998-02-27 2001-10-16 The Regents Of The University Of California Laser controlled flame stabilization
US6305929B1 (en) * 1999-05-24 2001-10-23 Suk Ho Chung Laser-induced ignition system using a cavity
US20020175520A1 (en) * 1999-11-12 2002-11-28 Sarcos. Resonant electrical generation system
US6732665B1 (en) * 1999-10-01 2004-05-11 Johann Kuebel Method for generating thermal energy from fine-grained oilseeds, preferably from rapeseed, and device for carrying out the method
US20060156727A1 (en) * 1999-11-12 2006-07-20 Jacobsen Stephen C Method and apparatus for phase change driven actuator
US20070190470A1 (en) * 2006-02-02 2007-08-16 Aga Ab Method for igniting a burner
US20080037089A1 (en) * 2006-08-09 2008-02-14 Johann Klausner Apparatus for the distribution of laser light
US20090266047A1 (en) * 2007-11-15 2009-10-29 General Electric Company Multi-tube, can-annular pulse detonation combustor based engine with tangentially and longitudinally angled pulse detonation combustors
US20120131927A1 (en) * 2010-11-30 2012-05-31 General Electric Company Advanced Optics and Optical Access for Laser Ignition for Gas Turbines Including Aircraft Engines
US20120131926A1 (en) * 2010-11-30 2012-05-31 General Electric Company Advanced laser ignition systems for gas turbines including aircraft engines
US20130061571A1 (en) * 2011-09-14 2013-03-14 Robert Van Burdine Laser propelled flight vehicle
US20140237989A1 (en) * 2013-02-26 2014-08-28 Pratt & Whitney Canada Corp. Laser-ignition combustor for gas turbine engine
US9873315B2 (en) 2014-04-08 2018-01-23 West Virginia University Dual signal coaxial cavity resonator plasma generation

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US3177651A (en) * 1962-01-18 1965-04-13 United Aircraft Corp Laser ignition
US3276505A (en) * 1963-02-23 1966-10-04 Huber Resonant burner
US3296795A (en) * 1964-08-04 1967-01-10 Floyd B Nielsen Laser initiated rocket type igniter

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US3171465A (en) * 1960-09-22 1965-03-02 Gustavsbergs Fabriker Ab Furnace for intermittent combustion
US3177651A (en) * 1962-01-18 1965-04-13 United Aircraft Corp Laser ignition
US3276505A (en) * 1963-02-23 1966-10-04 Huber Resonant burner
US3296795A (en) * 1964-08-04 1967-01-10 Floyd B Nielsen Laser initiated rocket type igniter

Cited By (47)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5552675A (en) * 1959-04-08 1996-09-03 Lemelson; Jerome H. High temperature reaction apparatus
US5628881A (en) * 1959-04-08 1997-05-13 Lemelson; Jerome H. High temperature reaction method
US3796535A (en) * 1971-04-28 1974-03-12 Sourdillon Matricage Robinette Gas burners, especially for domestic appliances
US3861371A (en) * 1973-12-10 1975-01-21 Joseph Gamell Ind Inc Ignition system for engine
US4069004A (en) * 1975-06-20 1978-01-17 Societe Nationale Elf Aquitaine (Production) Device to emit shock waves, with adjustable capacity
US4302933A (en) * 1979-03-01 1981-12-01 Smith Marvin M Jet engine augmentor operation at high altitudes
US4556020A (en) * 1981-07-06 1985-12-03 General Motors Corporation Method and means for stimulating combustion especially of lean mixtures in internal combustion engines
US4726336A (en) * 1985-12-26 1988-02-23 Eaton Corporation UV irradiation apparatus and method for fuel pretreatment enabling hypergolic combustion
US4852529A (en) * 1986-03-07 1989-08-01 Bennett Automotive Technology Pty. Ltd. Laser energy ignition system
US4947640A (en) * 1989-02-28 1990-08-14 University Of Tennessee Research Corporation Gas turbine engine photon ignition system
US5257926A (en) * 1991-12-17 1993-11-02 Gideon Drimer Fast, safe, pyrogenic external torch assembly
US5361737A (en) * 1992-09-30 1994-11-08 West Virginia University Radio frequency coaxial cavity resonator as an ignition source and associated method
US5404712A (en) * 1992-10-06 1995-04-11 University Of Tennessee Research Corporation Laser initiated non-linear fuel droplet ignition
US5485720A (en) * 1992-10-06 1996-01-23 University Of Tennessee Research Corporation Laser initiated non-linear fuel droplet ignition
US5497612A (en) * 1992-10-06 1996-03-12 University Of Tennessee Research Corporation Laser initiated non-linear fuel droplet ignition method
US5598699A (en) * 1992-10-06 1997-02-04 University Of Tennessee Research Corporation Laser initiated non-linear fuel droplet ignition apparatus
US5524429A (en) * 1992-10-06 1996-06-11 University Of Tennessee Research Corporation Laser initiated non-linear fuel droplet ignition
US5673550A (en) * 1992-10-06 1997-10-07 University Of Tennessee Research Corporation Laser initiated non-linear fuel droplet ignition
US6062018A (en) * 1993-04-14 2000-05-16 Adroit Systems, Inc. Pulse detonation electrical power generation apparatus with water injection
US5590517A (en) * 1993-05-26 1997-01-07 Simmonds Precision Engine Systems, Inc. Ignition methods and apparatus for combustors
US5628180A (en) * 1993-05-26 1997-05-13 Simmonds Precision Engine Systems Ignition methods and apparatus for combustors
US5515681A (en) * 1993-05-26 1996-05-14 Simmonds Precision Engine Systems Commonly housed electrostatic fuel atomizer and igniter apparatus for combustors
US5367869A (en) * 1993-06-23 1994-11-29 Simmonds Precision Engine Systems Laser ignition methods and apparatus for combustors
US5473885A (en) * 1994-06-24 1995-12-12 Lockheed Corporation Pulse detonation engine
US5542247A (en) * 1994-06-24 1996-08-06 Lockheed Corporation Apparatus powered using laser supplied energy
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Also Published As

Publication number Publication date Type
GB1111080A (en) 1968-04-24 application
DE1252974B (en) 1967-10-26 application
NL6613197A (en) 1966-11-25 application
BE686735A (en) 1967-02-15 grant

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