US20080299504A1 - Resonance driven glow plug torch igniter and ignition method - Google Patents
Resonance driven glow plug torch igniter and ignition method Download PDFInfo
- Publication number
- US20080299504A1 US20080299504A1 US11/756,642 US75664207A US2008299504A1 US 20080299504 A1 US20080299504 A1 US 20080299504A1 US 75664207 A US75664207 A US 75664207A US 2008299504 A1 US2008299504 A1 US 2008299504A1
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- US
- United States
- Prior art keywords
- resonance
- recited
- glow plug
- media
- driven glow
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/264—Ignition
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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
- F23R3/002—Wall structures
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/99—Ignition, e.g. ignition by warming up of fuel or oxidizer in a resonant acoustic cavity
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23N—REGULATING OR CONTROLLING COMBUSTION
- F23N2227/00—Ignition or checking
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23N—REGULATING OR CONTROLLING COMBUSTION
- F23N2227/00—Ignition or checking
- F23N2227/04—Prepurge
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
- Ignition Installations For Internal Combustion Engines (AREA)
Abstract
Description
- The present invention relates to an igniter system for ignition of a rocket engine or other combustion device for propulsion, power, or industrial processing applications, and more particularly to a method which utilizes pressure energy to generate thermal energy which is transferred into a glow plug body to store the energy for transfer to ignitable propellant combinations in a torch assembly.
- Various conventional ignition systems have been used for ignition of an ignitable propellant mixture in a combustion chamber of a rocket engine. Some ignition systems employ a spark induced by an electrical current. Other ignition systems employ glow plugs which are electrically heated. These conventional systems, although effective, tend to be relatively complex and heavy as each system requires electrical cabling, connectors, power, and control systems.
- Accordingly, it is desirable to provide an uncomplicated, lightweight ignition system which is highly reliable, easy to integrate into complex assemblies, and readily extensible to multiple ignition point applications, such as in a baffled injector.
- The ignition system according to the present invention generally includes a resonance system in communication with a propellant or purge gas system to generate an oscillating pressure force. A resonance driven glow plug includes a gas resonance tube section in communication with the resonance system. Reflected shocks within the gas resonance tube section couple and reinforce detached shocks within the resonance cavity such that successive cycles of shocks cause the formation of a series of oscillating zones of elevated pressure within the gas resonance tube section that heats the gas within the resonance tube which then heats the walls of the gas resonance tube section. The resonance driven glow plug stores the thermal energy for transfer to ignitable propellant combinations within a torch assembly.
- The present invention therefore provides an uncomplicated, lightweight ignition system that is highly reliable, easy to integrate into complex assemblies, and readily extensible to multiple ignition point applications, such as in a multi-compartment combustor.
- The various features and advantages of this invention will become apparent to those skilled in the art from the following detailed description of the currently preferred embodiment. The drawings that accompany the detailed description can be briefly described as follows:
-
FIG. 1A is a general schematic view of an exemplary rocket engine embodiment for use with the present invention; -
FIG. 1B is a schematic view of an ignition system of the present invention; -
FIG. 1C is an expanded view of the igniter illustrated inFIG. 1B ; -
FIG. 2 is a schematic view of a notional start sequence; -
FIG. 3 is a schematic view of an ignition system illustrating factors driving temperature; and -
FIG. 4 is a schematic view of another igniter. -
FIG. 1 illustrates a general schematic view of a combustor 10. A rocket engine combustor is used in this example embodiment. The combustor 10 generally includes acombustion chamber assembly 12, afuel system 14, an oxidizer system 16 and anignition system 18. Thefuel system 14 and the oxidizer system 16 provide a gaseous ignitable propellant combination to the combustor 10, however, other propellant systems such as liquid will also be usable. - The
combustion chamber assembly 12 is defined by a fluid cooledwall 20 about a center axis A. The fluid cooledwall 20 defines anozzle section 22, acombustion chamber section 24 upstream of thenozzle section 22, and acombustion chamber throat 26 therebetween. Thecombustion assembly 12 includes aninjector system section 12A with aninjector face 28 having a multitude of fuel/oxidizer injector elements 30 (shown somewhat schematically) which receive fuel which passes first through the fuel cooledcombustion chamber wall 20 fed via fuel supply line 14 a of thefuel system 14 and an oxidizer such as Gaseous Oxygen (GOx) through an oxidizer supply line 16 a of the oxidizer system 16. - Referring to
FIG. 1B , theignition system 18 generally includes aresonance system 36 in communication with one of thefuel system 14, the oxidizer system 16, or apurge gas system 38 to power anigniter 40. Theigniter 40 is mounted within theinjector section 12A to ignite the fuel/oxidizer ignitable propellant combination flow from the fuel/oxidizer injector elements 30. Ignition of the fuel/oxidizer ignitable propellant combination flow from the fuel/oxidizer injector elements 30 is provided by theigniter 40. It should also be understood that while the example embodiment of this invention is for rocket combustor ignition, application for power generation and ignition of other combustion based devices are equally suitable. - The oxidizer is fed to the
igniter 40 via a dedicated line 16 b in this embodiment, and the fuel is also fed to theigniter 40 via a dedicated line 14 b. It should be understood that various propellant flow paths may also be usable. A purge gas such as helium from thepurge gas system 38 may also be directed to theigniter 40 such that pressure energy within aresonance cavity 44 generates thermal energy for transfer into a resonance drivenglow plug assembly 42. The resonance drivenglow plug assembly 42 stores the thermal energy for transfer to ignitable propellant combinations within a torch assembly 46 (also illustrated inFIG. 1C ) and thus ignition within thecombustion chamber 24. The purge gas, as illustrated in the disclosed embodiment, facilitates purging of theinjector section 12A during a start sequence (FIG. 2 ). It should be understood that although an inert purge gas is used as the resonance media in this application, propellants of the ignitable propellant combination, such as hydrogen, oxygen or methane, which may thereafter reintroduce into the propellant flow cycle for combustion, may alternatively be utilized to drive theigniter 40. - Referring to
FIG. 1C , theigniter 40 includes ahousing 45 which defines theresonance cavity 44. Aninlet 48 incorporates a sonic orsupersonic inlet nozzle 48N to receive the resonance media (e.g., purge gas or propellant). Anoutlet 50 from theresonance cavity 44 includes anoutlet nozzle 50N to maintain pressure in theresonance cavity 44 at a predetermined level. In a combustor, the resonance process, as disclosed in the illustrated embodiment, is driven by injector purge gas, using a resource already in the system to provide essentially “free” ignition. Theresonance cavity 44 exhaust flow then dumps to the injector for injector purge. By utilizing an inert purge gas and completely isolating the combustion process from the resonance process, theignition system 18 provides significant reliability. - The resonance driven
glow plug assembly 42 includes a resonance driven glow plug (RDGP) 52 in communication with anopening 54 in theresonance cavity 44 generally opposite theinlet nozzle 48N. The RDGP 52 generally includes a hollow member to receive flow. The gas flow entering theresonance cavity 44 through theinlet nozzle 48N as underexpanded flow is directed at theRDGP 52 to cause an oscillating detached shock 56 (FIG. 3 ) to form upstream of theentrance 52N to the RDGP 52. Reflected shocks within theRDGP 52 couple and reinforce the detached shock 56 and interact with the flow within theresonance cavity 44 such that the successive cycles of shocks cause the formation of a series of oscillating zones of elevated pressure within theRDGP 52 that heats the gas within the resonance tube which then heats the walls of theRDGP 52. - Physical criteria for the interaction may be defined by: “d” the diameter of the
supersonic inlet nozzle 48N; “G” the distance between theinlet nozzle 48N throat and theentrance 52N of theRDGP 52; “Dtube” the inner diameter ofRDGP 52 and “DMC” which is the throat diameter of theoutlet nozzle 50N. A steppedinner diameter RDGP 52 is depicted; however, it is understood that cylindrical, conical or other shaped resonance tube section may alternatively be utilized with the present invention. - The RDGP 52 is sealed at an end opposite the entrance 56N to form a resonance heated
glow plug tip 58. The pressure energy within theRDGP 52 generates thermal energy within the resonance heatedglow plug tip 58 which stores the thermal energy for transfer to the ignitable propellant combinations in thetorch assembly 46. The RDGP 52 is manufactured of a high temperature material such as molybdenum, platinum or iridium and located within aninsulator cylinder 60 manufactured of a ceramic or other high temperature insulator material. The RDGP 52 is spaced from theinsulator cylinder 60 by anannular air gap 62 for at least a partial length thereof. - The
torch assembly 46 includes atorch housing 62 arranged adjacent to the RDGP 52 to define at least one torchoxidizer inlet port 64 and at least one torchfuel inlet ports 66. Oxidizer is communicated from the oxidizer manifold (FIG. 1B ) through the at least one torchoxidizer inlet port 64 while fuel is communicated from the fuel manifold to the least one torchfuel inlet ports 66 adjacent the resonance heatedglow plug tip 58. Oxidizer and fuel are injected adjacent the resonance heatedglow plug tip 58 which is heated to temperatures upwards of 2000 degrees F. to thereby ignite the ignitable propellant combination within thetorch assembly 46. The resultant hot gas stream then exits the torch assembly and ignites the ignitable propellant combination within thecombustion chamber 24. - The thermal energy is stored as thermal capacitance in the
RDGP 52 which allows a relatively small energy generation source to provide adequate net energy for ignition as a higher temperature can be achieved for the same resonance flow parameters and then extracted at a higher rate for ignition of the propellants in thetorch assembly 46. The resonance drivenglow plug assembly 42 is uncomplicated, with no moving parts, no electrical cabling or connectors and no vehicle power or control requirements. These characteristics result in a system that is highly reliable, easy to integrate into complex assemblies, and readily extensible to multiple ignition point applications, such as in a baffled injector. Furthermore, the resonance drivenglow plug assembly 42 is more resistant to contamination or damage and is relatively insensitive to the ignition pressure. - Referring to
FIG. 4 , anotherignition system 18A is illustrated. The resonance drivenglow plug assembly 42A includes the steppedinner diameter RDGP 52 with a constantouter diameter 68 to form the resonance heatedglow plug tip 58A. Anair gap 62A also separates theRDGP 52 from aninsulator 72 for at least a portion of the length thereof. - It should be understood that relative positional terms such as “forward,” “aft,” “upper,” “lower,” “above,” “below,” and the like are with reference to the normal operational attitude of the vehicle and should not be considered otherwise limiting.
- It should be understood that although a particular component arrangement is disclosed in the illustrated embodiment, other arrangements will benefit from the instant invention.
- Although particular step sequences are shown, described, and claimed, it should be understood that steps may be performed in any order, separated or combined unless otherwise indicated and will still benefit from the present invention.
- The foregoing description is exemplary rather than defined by the limitations within. Many modifications and variations of the present invention are possible in light of the above teachings. The preferred embodiments of this invention have been disclosed, however, one of ordinary skill in the art would recognize that certain modifications would come within the scope of this invention. It is, therefore, to be understood that within the scope of the appended claims, the invention may be practiced otherwise than as specifically described. For that reason the following claims should be studied to determine the true scope and content of this invention.
Claims (20)
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
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US11/756,642 US20080299504A1 (en) | 2007-06-01 | 2007-06-01 | Resonance driven glow plug torch igniter and ignition method |
EP08251823A EP1998036A3 (en) | 2007-06-01 | 2008-05-27 | Resonance driven glow plug torch igniter and ignition method |
JP2008140230A JP2008298075A (en) | 2007-06-01 | 2008-05-29 | Ignition system for combustor, combustor, and combustor ignition method |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/756,642 US20080299504A1 (en) | 2007-06-01 | 2007-06-01 | Resonance driven glow plug torch igniter and ignition method |
Publications (1)
Publication Number | Publication Date |
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US20080299504A1 true US20080299504A1 (en) | 2008-12-04 |
Family
ID=39744038
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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US11/756,642 Abandoned US20080299504A1 (en) | 2007-06-01 | 2007-06-01 | Resonance driven glow plug torch igniter and ignition method |
Country Status (3)
Country | Link |
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US (1) | US20080299504A1 (en) |
EP (1) | EP1998036A3 (en) |
JP (1) | JP2008298075A (en) |
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US20120264070A1 (en) * | 2009-12-10 | 2012-10-18 | Michael Zettner | Burner system and a method for increasing the efficiency of a heat exchanger |
US9476399B1 (en) | 2012-05-16 | 2016-10-25 | Orbital Technologies Corporation | Glow plug type acoustic resonance igniter |
US20170350590A1 (en) * | 2016-06-01 | 2017-12-07 | Board Of Regents, The University Of Texas System. | Swirl torch igniter |
US10584639B2 (en) | 2014-08-18 | 2020-03-10 | Woodward, Inc. | Torch igniter |
CN111765017A (en) * | 2020-06-11 | 2020-10-13 | 安徽九州云箭航天技术有限公司 | Torch electric ignition chamber for liquid rocket engine |
US20220136696A1 (en) * | 2020-11-04 | 2022-05-05 | Delavan Inc. | Surface igniter cooling system |
US11421601B2 (en) | 2019-03-28 | 2022-08-23 | Woodward, Inc. | Second stage combustion for igniter |
US11635210B2 (en) | 2020-12-17 | 2023-04-25 | Collins Engine Nozzles, Inc. | Conformal and flexible woven heat shields for gas turbine engine components |
US11635027B2 (en) | 2020-11-18 | 2023-04-25 | Collins Engine Nozzles, Inc. | Fuel systems for torch ignition devices |
US11680528B2 (en) | 2020-12-18 | 2023-06-20 | Delavan Inc. | Internally-mounted torch igniters with removable igniter heads |
US11692488B2 (en) | 2020-11-04 | 2023-07-04 | Delavan Inc. | Torch igniter cooling system |
US11719162B2 (en) | 2020-11-04 | 2023-08-08 | Delavan, Inc. | Torch igniter cooling system |
US11754289B2 (en) | 2020-12-17 | 2023-09-12 | Delavan, Inc. | Axially oriented internally mounted continuous ignition device: removable nozzle |
US20230323811A1 (en) * | 2020-12-23 | 2023-10-12 | Collins Engine Nozzles, Inc. | Torch ignitors with gas assist start |
US11891956B2 (en) | 2020-12-16 | 2024-02-06 | Delavan Inc. | Continuous ignition device exhaust manifold |
US11913646B2 (en) | 2020-12-18 | 2024-02-27 | Delavan Inc. | Fuel injector systems for torch igniters |
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Also Published As
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EP1998036A3 (en) | 2011-10-26 |
JP2008298075A (en) | 2008-12-11 |
EP1998036A2 (en) | 2008-12-03 |
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