US20090173321A1 - Piezo-resonance igniter and ignition method for propellant liquid rocket engine - Google Patents
Piezo-resonance igniter and ignition method for propellant liquid rocket engine Download PDFInfo
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- US20090173321A1 US20090173321A1 US11/333,691 US33369106A US2009173321A1 US 20090173321 A1 US20090173321 A1 US 20090173321A1 US 33369106 A US33369106 A US 33369106A US 2009173321 A1 US2009173321 A1 US 2009173321A1
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- 238000000034 method Methods 0.000 title claims description 5
- 239000003380 propellant Substances 0.000 title abstract description 33
- 239000007788 liquid Substances 0.000 title description 5
- 238000002485 combustion reaction Methods 0.000 claims abstract description 20
- 238000012546 transfer Methods 0.000 claims description 50
- 230000005540 biological transmission Effects 0.000 claims description 30
- 239000012530 fluid Substances 0.000 claims description 22
- 238000004891 communication Methods 0.000 claims description 18
- 239000013078 crystal Substances 0.000 claims description 15
- 230000003993 interaction Effects 0.000 claims description 3
- 230000010355 oscillation Effects 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 abstract description 15
- 239000007800 oxidant agent Substances 0.000 description 28
- 239000000446 fuel Substances 0.000 description 23
- 239000007789 gas Substances 0.000 description 19
- 230000008901 benefit Effects 0.000 description 6
- 230000003750 conditioning effect Effects 0.000 description 5
- 238000006243 chemical reaction Methods 0.000 description 4
- 239000012212 insulator Substances 0.000 description 4
- 230000035939 shock Effects 0.000 description 4
- 238000013459 approach Methods 0.000 description 3
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 3
- 239000001301 oxygen Substances 0.000 description 3
- 229910052760 oxygen Inorganic materials 0.000 description 3
- 239000003990 capacitor Substances 0.000 description 2
- 230000008030 elimination Effects 0.000 description 2
- 238000003379 elimination reaction Methods 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 238000004513 sizing Methods 0.000 description 2
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- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000000295 complement effect Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000004146 energy storage Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
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- 238000010248 power generation Methods 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 238000003860 storage Methods 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02P—IGNITION, OTHER THAN COMPRESSION IGNITION, FOR INTERNAL-COMBUSTION ENGINES; TESTING OF IGNITION TIMING IN COMPRESSION-IGNITION ENGINES
- F02P15/00—Electric spark ignition having characteristics not provided for in, or of interest apart from, groups F02P1/00 - F02P13/00 and combined with layout of ignition circuits
- F02P15/001—Ignition installations adapted to specific engine types
- F02P15/003—Layout of ignition circuits for gas turbine plants
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02P—IGNITION, OTHER THAN COMPRESSION IGNITION, FOR INTERNAL-COMBUSTION ENGINES; TESTING OF IGNITION TIMING IN COMPRESSION-IGNITION ENGINES
- F02P3/00—Other installations
- F02P3/12—Piezoelectric ignition; Electrostatic ignition
Definitions
- the present invention relates to a piezo-resonance igniter system for passive auto ignition of a rocket engine, and more particularly to a method which utilizes the pressure energy in the propellants themselves to excite piezoelectric crystals such that high voltage electrical pulses are created to generate a spark in an igniter system.
- the ignition system generally includes a resonance system in communication with a propellant system, a piezoelectric system, and an electrical conditioning system to power an igniter and ignite a propellant flow.
- the resonance system is in communication with the piezoelectric system through a gas resonance tube which is sealed with a force transmission diaphragm.
- a force transfer member increases the surface area in contact with the force transmission diaphragm to react pressure loads from an oscillating flow within the resonance tube. The sizing of the diaphragm allows the resonance pressure pulses to act over a relatively large effective area to increase a net force output for a given resonance gas resonance tube diameter and supply pressure.
- the oscillating pressure force from the oscillating flow is transmitted to the piezoelectric crystal stack to generate electrical pulses and power the ignition system.
- the oscillating force can provide for direct spark ignition in which each pressure pulse results in a spark.
- the electrical pulses generated may be stored then metered out at various schedules to provide the desired spark repetition rate and spark power per pulse.
- the present invention therefore provides an uncomplicated, lightweight passive auto ignition system with restart capability that eliminates separate spark exciter electronics and switching command systems.
- FIG. 1 is a general perspective view an exemplary of rocket engine embodiment for use with the present invention
- FIG. 2A is a schematic view of an ignition system of the present invention.
- FIG. 2B is an expanded view of the ignition system components illustrated in FIG. 2A ;
- FIG. 3 is a schematic view of a flight ready ignition system of the present invention with an indirect piezo-resonance module
- FIG. 4 is a schematic view of a flight ready piezo-resonance module ignition system of the present invention utilizing a direct spark torch approach mounted directly within a combustion chamber;
- FIG. 5 is a schematic view of a flight ready piezo-resonance module ignition system of the present invention for use with an incompressible fluid flow.
- FIG. 1 illustrates a general schematic view of a rocket engine 10 .
- the engine 10 generally includes a thrust chamber assembly 12 , a fuel system 14 , an oxidizer system 16 and an ignition system 18 .
- the fuel system 14 and the oxidizer system 16 preferably provide a gaseous propellant system of the rocket engine 10 , however, other propellant systems such as liquid will also be usable with the present invention.
- a combustion chamber wall 20 about a thrust axis A defines the nozzle assembly 12 .
- the combustion chamber wall 20 defines a thrust chamber 22 , a combustion chamber 24 upstream of the thrust chamber 22 , and a combustion chamber throat 26 therebetween.
- the thrust chamber assembly 12 includes an injector 12 A with an injector face 28 which contains a multitude of fuel/oxidizer injector elements 30 (shown somewhat schematically) which receive fuel which passes first through the fuel cooled combustion chamber wall 20 fed via fuel supply line 14 a of the fuel system 14 and an oxidizer such as Gaseous Oxygen (GOx) through an oxidizer supply line 16 a of the oxidizer system 16 .
- GOx Gaseous Oxygen
- the ignition system 18 generally includes a resonance system 36 in communication with one of the propellants such as the oxidizer system 16 , a piezoelectric system 38 , and an electrical conditioning system 40 to power an igniter 42 mounted within the injector 12 A to ignite the fuel/oxidizer propellant flow from the fuel/oxidizer injector elements 30 .
- the oxidizer is fed to the igniter via a dedicated line 16 b in this embodiment, and the fuel is also fed to the igniter torch via a dedicated line 14 b .
- various propellant flow paths may be usable with the present invention so long as at least one propellant flow is in communication with the resonance system 36 .
- Ignition of the fuel/oxidizer propellant flow from the fuel/oxidizer injector elements 30 with the igniter 42 is conventional and need not be described in further detail herein. It should also be understood that while the current focus of this invention is a rocket ignition, other applications for power generation and ignition of other combustion based devices will also be usable with the present invention.
- one ignition system 18 includes a housing 32 which defines a resonance cavity 44 having an inlet 34 incorporating a supersonic inlet nozzle 46 to receive a flow of propellant such as the oxidizer from the oxidizer supply line 16 c of the oxidizer system 16 .
- An outlet 16 a from the resonance system 36 includes an outlet nozzle 50 to maintain pressure in the cavity 44 at a predetermined level.
- the illustrated embodiment of the oxidizer is a gaseous propellant (compressible flow) resonance configuration, it should be understood that resonant pressure pulses from incompressible liquid flow as well as from other propellant sources will likewise be usable with the present invention.
- the resonance system 36 is in communication with the piezoelectric system 38 through a gas resonance tube 52 .
- the piezoelectric system 38 is illustrated in a schematic form in what may be considered a ground based configuration which may include adjustment features that may or may not be required. That is, other even less complicated piezoelectric systems are achievable as illustrated in the following embodiments.
- the gas resonance tube 52 is located through an opening 54 in the resonance cavity 44 opposite the supersonic inlet nozzle 46 .
- the oxidizer entering through the supersonic inlet nozzle 46 as underexpanded flow is directed at the gas resonance tube 52 causing an oscillating detached shock 56 to form upstream of the entrance 56 N to the gas resonance tube 52 .
- Reflected shocks within the gas resonance tube 52 couple and reinforce the detached shock 56 and interact with the flow within the gas resonance tube 52 such that the successive cycles of shocks cause the formation of a series of unstable zones of elevated pressure within the gas resonance tube 52 .
- Physical criteria for the interaction may be defined by: “d” the diameter of the supersonic inlet nozzle 46 N; “G” the distance between the inlet nozzle 46 N throat and the entrance 56 N of the gas resonance tube 52 ; “Dtube” the internal diameter of resonance tube 52 and “DMC” which is the throat diameter of the outlet nozzle 50 .
- a constant diameter resonance tube 52 is depicted; however, it is understood that stepped, conical or other shaped resonance tubes may alternatively be utilized with the present invention.
- the gas resonance tube 52 is sealed at an end opposite the entrance 56 N with a force transmission diaphragm 58 (also illustrated in FIG. 2B ).
- a force transfer member 60 includes a force transfer rod 62 and a force transfer platen 64 in contact with the force transmission diaphragm 58 .
- the force transfer platen 64 is of a larger diameter than the force transfer rod 62 so as to increase the surface area in contact with the force transmission diaphragm 58 and react pressure loads from the oscillating pressures in the resonance tube 52 .
- the sizing of the force transmission diaphragm 58 allows the resonance pressure pulses to act over a relatively large effective area, increasing the net force output for a given gas tube 52 diameter (Dtube) and supply pressure.
- Flow relief passages 52 a may be incorporated into the mating faces of the resonance tube 52 and the force transmission diaphragm 58 to increase working fluid transfer across the face of the force transmission diaphragm 58 during the relatively short resonant pressure pulses in the resonance tube 52 .
- the force transfer rod 62 is received within a guide sleeve 65 .
- the guide sleeve 65 contains a piezoelectric crystal stack 66 mounted in contact with the force transfer rod 62 .
- the oscillating pressure force in the gas resonance tube 52 is transmitted to the piezoelectric crystal stack 66 through the force transfer member 60 to generate electrical pulses.
- the wire harness 67 is connected directly to the igniter 42 , eliminating the electrical conditioning system 40 .
- the oscillating force drives the direct spark ignition, in which each pressure pulse results in a spark, offering a persistent source of ignition.
- the electrical pulses are communicated to the igniter 42 through a wire harness 67 and the electrical conditioning system 40 .
- An energy storage system 68 A (illustrated schematically) such as an electrical capacitor or battery and a voltage multiplier system 68 B (illustrated schematically) within the electrical condition system 40 conditions the spark to a desired spark output energy and frequency independent of the crystal output. This permits the system to be sized to suit any application.
- the electrical condition system 40 may include various electrical subsystems such as storage capacitors or voltage amplifiers to specifically tailor the ignition system to provide various outputs.
- the force transmission diaphragm 58 is preferably sandwiched between an end segment 70 of the gas resonance tube 52 and a diaphragm support ring 72 which may be welded together through a weld W or other attachment.
- the force transmission diaphragm 58 preferably includes a relief feature 74 located between the diaphragm support ring 72 and the force transfer platen 64 .
- the relief feature 74 is preferably a circular flexed portion of the force transmission diaphragm 58 within which the force transfer platen 64 is received.
- the relief feature 74 minimizes tensile load losses on the force transmission diaphragm 58 thereby enhancing flexibility to maximize transfer of the oscillating pressure force to the force transfer platen 64 and thence to the piezoelectric crystal stack 66 through the force transfer rod 62 .
- Applicant has demonstrated relatively short ignition delay times of approximately 18 mseconds utilizing a gaseous propellant (compressible flow) resonance configuration.
- gaseous propellant compressorible flow
- the resonance system 36 A includes a more compact flight-ready piezoelectric system 38 A integrated with the resonance system 36 A.
- Such a system is readily mounted anywhere within the communicating conduits of a working fluid system such as embodied by the oxidizer system or fuel system ( FIG. 1 ).
- the piezoelectric system 38 A includes an electrical condition system 90 A to remotely power the igniter system 92 (illustrated schematically) mounted within a piezoelectric housing 80 .
- the resonance system 36 A includes a resonance housing 82 which defines the resonance cavity 44 therein.
- the resonance housing 82 is threaded to the piezoelectric housing 80 to provide an exceedingly compact and robust system which is readily maintained.
- a piezoelectric guide sleeve 84 is interfit with an insulator load reaction interface sleeve 86 and both are mounted within the piezoelectric housing 80 against a stop 88 .
- the force transmission diaphragm 58 is preferably sandwiched between and end segment 82 a of the resonance housing 82 which defines the gas resonance tube 52 and the piezoelectric guide sleeve 84 .
- the force transmission diaphragm 58 preferably includes a relief feature 74 as illustrated in FIG. 2B .
- a force transfer member 90 is mounted within the piezoelectric guide sleeve 84 adjacent the force transmission diaphragm 58 .
- the force transfer member 90 is preferably a frustro-conical member in which an apex 92 thereof is located in contact and preferably interfits with the piezoelectric crystal stack 66 . That is, the force transfer member 90 essentially combines the force transfer rod 62 and a force transfer platen 64 of the above embodiment, however operation is generally equivalent as the apex 92 is in contact with the piezoelectric crystal stack 66 .
- the oscillating pressure force in the gas resonance tube 52 is transmitted to the piezoelectric crystal stack 66 through the force transfer member 90 to generate electrical pulses in an electrode 94 opposite the piezoelectric crystal stack 66 .
- the electrical pulses from the electrode are communicated to the igniter system 42 through the electrical conditioning system 90 A via a wire harness 96 .
- the wire harness preferably terminates in a connector 98 which permits removable attachment to a spark power cable 99 such that the system 36 A, 38 A may be readily replaced during maintenance.
- a fully passive auto-ignition system is provided which is “detuned” when ignition occurs such that spark production automatically stops.
- the resonance system 36 B and piezoelectric system 38 B are integrated within a combustion chamber 24 B as would be preferred for a thruster system as each individual thruster system thereby includes an essentially self-contained ignition system.
- the resonance system 36 B is preferably defined by a resonance housing 12 B which defines the resonance cavity 44 therein.
- the resonance housing 12 B is attached directly to the injector 12 A through fasteners such as bolts b or the like.
- FIG. 4 embodiment generally includes components common to that of the previous embodiments, consistent reference numeral usage will be utilized while components more specific to the FIG. 4 embodiment will be described in detail.
- operation of the FIG. 4 embodiment is generally as the FIG. 3 embodiment, however, the electrode 100 of the FIG. 4 embodiment is mounted to provide a direct spark torch approach. That is, the electrode directly communicates with the combustion chamber 24 through the injector face 28 which contains the multitude of fuel/oxidizer injector elements 30 (shown schematically) which receive fuel from the fuel cooled combustion chamber wall 20 which is fed via fuel supply line 19 a of the fuel system 14 and an oxidizer such as Gaseous Oxygen (GOx) through an oxidizer supply line 36 a of the oxidizer system 16 (also illustrated in FIG. 1 ).
- GOx Gaseous Oxygen
- the electrode 100 extends through an oxidizer manifold 102 and a fuel manifold 103 to generate a spark within the combustion chamber 24 .
- the electrode 100 is mounted within an insulator load reaction interface 104 which extends along a significant length of the electrode 100 .
- the insulator load reaction interface 104 is interfit with the piezoelectric guide sleeve 84 and retained within the injector 12 A.
- a torch housing 106 is defined about the electrode and the insulator load reaction interface 104 to define a torch oxidizer feed annulus 108 .
- Oxidizer is communicated form the oxidizer manifold 102 through torch oxidizer inlet ports 110 through the torch housing 106 .
- a multitude of fuel injection ports 112 in communication with the fuel manifold 103 communicate fuel toward the distal end of the electrode 100 .
- Oxidizer and fuel is thereby injected adjacent a distal end of the electrode 100 from which the ignition spark is generated to thereby ignite the mixture within the combustion chamber 24 B.
- a fully passive auto-ignition system is provided which is “detuned” when ignition occurs such that spark production automatically stops.
- the resonance system 36 C includes an incompressible fluid resonance housing 120 which defines a resonance cavity 122 therein.
- the resonance housing 120 includes a threaded portion 120 A such that a piezoelectric housing 80 and associated piezoelectric system (as disclosed in FIG. 3 ) is threaded thereto.
- the piezoelectric housing 80 and associated piezoelectric system is a common system which may be driven by, for example only, either the resonance housing 82 illustrated of FIG. 3 or the incompressible fluid resonance housing 120 illustrated in FIG. 5 to provide an exceedingly compact and robust system.
- the incompressible fluid resonance housing 120 includes a split leg resonator 124 having a first leg 126 a and a second leg 126 b .
- the legs 126 a , 126 b split off from an incompressible fluid inlet 128 and rejoin at a common leg 126 c which form a generally triangular relationship. It should be understood that other paths will also be usable with the present invention.
- the common leg 126 C includes an incompressible fluid outlet 132 which is in communication with a combustion chamber as illustrated in FIG. 1 .
- a gas resonance tube 130 is in communication with the first leg 126 a of the split leg resonator 124 to generate an oscillating pressure force within the gas resonance tube 130 due to the unstable flow oscillations between the parallel flowpaths in legs 126 A and 126 B.
- the oscillating pressure force generated within the gas resonance tube 130 may then utilized to drive the piezoelectric system as described above.
Abstract
Description
- The present invention relates to a piezo-resonance igniter system for passive auto ignition of a rocket engine, and more particularly to a method which utilizes the pressure energy in the propellants themselves to excite piezoelectric crystals such that high voltage electrical pulses are created to generate a spark in an igniter system.
- Various conventional ignition systems have been used for ignition of a propellant mixture in a combustion chamber of a rocket engine. These ignition systems generally employed a spark induced by an electrical current from a source of electricity and a control for sensing when to supply and discontinue the spark. These conventional systems, although effective, tend to be relatively complex, heavy, and may not provide restart capability.
- With the increasing need for safe storable propellant systems such as Gaseous Oxygen (GOx) and Methane combinations, an uncomplicated fully passive auto ignition system is desired to complement the advantages of the safe storable propellants by reducing ignition system complexity, weight, and cost while increasing safety and reliability.
- Accordingly, it is desirable to provide an uncomplicated, lightweight passive auto ignition system with restart capability that eliminates separate spark exciter electronics, vehicle electrical power requirements for ignition and ignition control and monitoring systems.
- The ignition system according to the present invention generally includes a resonance system in communication with a propellant system, a piezoelectric system, and an electrical conditioning system to power an igniter and ignite a propellant flow. The resonance system is in communication with the piezoelectric system through a gas resonance tube which is sealed with a force transmission diaphragm. A force transfer member increases the surface area in contact with the force transmission diaphragm to react pressure loads from an oscillating flow within the resonance tube. The sizing of the diaphragm allows the resonance pressure pulses to act over a relatively large effective area to increase a net force output for a given resonance gas resonance tube diameter and supply pressure.
- The oscillating pressure force from the oscillating flow is transmitted to the piezoelectric crystal stack to generate electrical pulses and power the ignition system. The oscillating force can provide for direct spark ignition in which each pressure pulse results in a spark. Alternatively, the electrical pulses generated may be stored then metered out at various schedules to provide the desired spark repetition rate and spark power per pulse.
- Since the spark energy production is driven by the resonance of the propellant flow, a passive auto-ignition system is provided. When the propellant valves are opened, flow through the resonance system is such that resonance occurs and spark energy is generated. Once ignition occurs, the resultant backpressure in the combustion chamber reduces the pressure drop across the resonance system and “detunes” the resonance phenomena, such that spark production stops. Furthermore, should the engine flame out causing combustion chamber pressure to drop again, spark production automatically resumes as long as the propellant valves remain open. Control and operation of the rocket engine is considerably simplified through elimination of the heretofore necessity of an electrical power supply and separate switching commands and monitoring of the ignition system such that the otherwise typical uncertainties in setting spark timing and duration are obviated. Significant advantages are thereby provided for distributed multi-thruster systems, such as an Attitude Control System (ACS), where the characteristics of a conventional ignition system are multiplied by a significant number of thrusters.
- The present invention therefore provides an uncomplicated, lightweight passive auto ignition system with restart capability that eliminates separate spark exciter electronics and switching command systems.
- 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. 1 is a general perspective view an exemplary of rocket engine embodiment for use with the present invention; -
FIG. 2A is a schematic view of an ignition system of the present invention; -
FIG. 2B is an expanded view of the ignition system components illustrated inFIG. 2A ; -
FIG. 3 is a schematic view of a flight ready ignition system of the present invention with an indirect piezo-resonance module; -
FIG. 4 is a schematic view of a flight ready piezo-resonance module ignition system of the present invention utilizing a direct spark torch approach mounted directly within a combustion chamber; and -
FIG. 5 is a schematic view of a flight ready piezo-resonance module ignition system of the present invention for use with an incompressible fluid flow. -
FIG. 1 illustrates a general schematic view of arocket engine 10. Theengine 10 generally includes athrust chamber assembly 12, afuel system 14, anoxidizer system 16 and anignition system 18. Thefuel system 14 and theoxidizer system 16 preferably provide a gaseous propellant system of therocket engine 10, however, other propellant systems such as liquid will also be usable with the present invention. - A
combustion chamber wall 20 about a thrust axis A defines thenozzle assembly 12. Thecombustion chamber wall 20 defines athrust chamber 22, acombustion chamber 24 upstream of thethrust chamber 22, and acombustion chamber throat 26 therebetween. Thethrust chamber assembly 12 includes aninjector 12A with aninjector face 28 which contains 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 anoxidizer supply line 16 a of theoxidizer system 16. - The
ignition system 18 generally includes aresonance system 36 in communication with one of the propellants such as theoxidizer system 16, apiezoelectric system 38, and anelectrical conditioning system 40 to power anigniter 42 mounted within theinjector 12A to ignite the fuel/oxidizer propellant flow from the fuel/oxidizer injector elements 30. The oxidizer is fed to the igniter via a dedicated line 16 b in this embodiment, and the fuel is also fed to the igniter torch via a dedicated line 14 b. It should be understood that various propellant flow paths may be usable with the present invention so long as at least one propellant flow is in communication with theresonance system 36. Ignition of the fuel/oxidizer propellant flow from the fuel/oxidizer injector elements 30 with theigniter 42 is conventional and need not be described in further detail herein. It should also be understood that while the current focus of this invention is a rocket ignition, other applications for power generation and ignition of other combustion based devices will also be usable with the present invention. - Referring to
FIG. 2A , oneignition system 18 includes ahousing 32 which defines aresonance cavity 44 having aninlet 34 incorporating asupersonic inlet nozzle 46 to receive a flow of propellant such as the oxidizer from the oxidizer supply line 16 c of theoxidizer system 16. Anoutlet 16 a from theresonance system 36 includes anoutlet nozzle 50 to maintain pressure in thecavity 44 at a predetermined level. Although the illustrated embodiment of the oxidizer is a gaseous propellant (compressible flow) resonance configuration, it should be understood that resonant pressure pulses from incompressible liquid flow as well as from other propellant sources will likewise be usable with the present invention. - The
resonance system 36 is in communication with thepiezoelectric system 38 through agas resonance tube 52. It should be understood that inFIG. 2A thepiezoelectric system 38 is illustrated in a schematic form in what may be considered a ground based configuration which may include adjustment features that may or may not be required. That is, other even less complicated piezoelectric systems are achievable as illustrated in the following embodiments. - The
gas resonance tube 52 is located through anopening 54 in theresonance cavity 44 opposite thesupersonic inlet nozzle 46. The oxidizer entering through thesupersonic inlet nozzle 46 as underexpanded flow is directed at thegas resonance tube 52 causing an oscillating detachedshock 56 to form upstream of theentrance 56N to thegas resonance tube 52. Reflected shocks within thegas resonance tube 52 couple and reinforce thedetached shock 56 and interact with the flow within thegas resonance tube 52 such that the successive cycles of shocks cause the formation of a series of unstable zones of elevated pressure within thegas resonance tube 52. Physical criteria for the interaction may be defined by: “d” the diameter of the supersonic inlet nozzle 46N; “G” the distance between the inlet nozzle 46N throat and theentrance 56N of thegas resonance tube 52; “Dtube” the internal diameter ofresonance tube 52 and “DMC” which is the throat diameter of theoutlet nozzle 50. A constantdiameter resonance tube 52 is depicted; however, it is understood that stepped, conical or other shaped resonance tubes may alternatively be utilized with the present invention. - The
gas resonance tube 52 is sealed at an end opposite theentrance 56N with a force transmission diaphragm 58 (also illustrated inFIG. 2B ). Aforce transfer member 60 includes aforce transfer rod 62 and aforce transfer platen 64 in contact with theforce transmission diaphragm 58. Theforce transfer platen 64 is of a larger diameter than theforce transfer rod 62 so as to increase the surface area in contact with theforce transmission diaphragm 58 and react pressure loads from the oscillating pressures in theresonance tube 52. The sizing of theforce transmission diaphragm 58 allows the resonance pressure pulses to act over a relatively large effective area, increasing the net force output for a givengas tube 52 diameter (Dtube) and supply pressure.Flow relief passages 52 a (FIG. 2B ) may be incorporated into the mating faces of theresonance tube 52 and theforce transmission diaphragm 58 to increase working fluid transfer across the face of theforce transmission diaphragm 58 during the relatively short resonant pressure pulses in theresonance tube 52. - The
force transfer rod 62 is received within aguide sleeve 65. Theguide sleeve 65 contains apiezoelectric crystal stack 66 mounted in contact with theforce transfer rod 62. The oscillating pressure force in thegas resonance tube 52 is transmitted to thepiezoelectric crystal stack 66 through theforce transfer member 60 to generate electrical pulses. Thewire harness 67 is connected directly to theigniter 42, eliminating theelectrical conditioning system 40. The oscillating force drives the direct spark ignition, in which each pressure pulse results in a spark, offering a persistent source of ignition. - Alternatively or in addition thereto, the electrical pulses are communicated to the
igniter 42 through awire harness 67 and theelectrical conditioning system 40. Anenergy storage system 68A (illustrated schematically) such as an electrical capacitor or battery and avoltage multiplier system 68B (illustrated schematically) within theelectrical condition system 40 conditions the spark to a desired spark output energy and frequency independent of the crystal output. This permits the system to be sized to suit any application. In other words, theelectrical condition system 40 may include various electrical subsystems such as storage capacitors or voltage amplifiers to specifically tailor the ignition system to provide various outputs. - Since the spark energy production is driven by the resonance of the propellant flow, a fully passive auto-ignition system is provided. When the propellant valves are open, flow through the
resonance system 36 is such that resonance occurs and spark energy is created. Once ignition occurs, the resultant backpressure within the combustion chamber 24 (FIG. 1 ) “detunes” the resonance phenomena and spark production stops. Furthermore, should the engine flame out, spark production automatically resumes as the propellant valves remain open. Control and operation of the rocket engine is considerably simplified by the elimination of separate power supply and switching command systems in the igniter system such that the heretofore typical uncertainties in the spark duration control are obviated. This provides significant advantages for distributed multi-thruster systems, such as an attitude control system (ACS). - Referring to
FIG. 2B , theforce transmission diaphragm 58 is preferably sandwiched between anend segment 70 of thegas resonance tube 52 and adiaphragm support ring 72 which may be welded together through a weld W or other attachment. Theforce transmission diaphragm 58 preferably includes arelief feature 74 located between thediaphragm support ring 72 and theforce transfer platen 64. Therelief feature 74 is preferably a circular flexed portion of theforce transmission diaphragm 58 within which theforce transfer platen 64 is received. Therelief feature 74 minimizes tensile load losses on theforce transmission diaphragm 58 thereby enhancing flexibility to maximize transfer of the oscillating pressure force to theforce transfer platen 64 and thence to thepiezoelectric crystal stack 66 through theforce transfer rod 62. - Applicant has demonstrated relatively short ignition delay times of approximately 18 mseconds utilizing a gaseous propellant (compressible flow) resonance configuration. However, multiple approaches exist to achieve the resonant pressure pulses from incompressible liquid flow as well such that the present invention is adaptable to any propellants.
- Referring to
FIG. 3 , anotherignition system 18B is illustrated. Theresonance system 36A includes a more compact flight-ready piezoelectric system 38A integrated with theresonance system 36A. Such a system is readily mounted anywhere within the communicating conduits of a working fluid system such as embodied by the oxidizer system or fuel system (FIG. 1 ). - The
piezoelectric system 38A includes anelectrical condition system 90A to remotely power the igniter system 92 (illustrated schematically) mounted within a piezoelectric housing 80. Theresonance system 36A includes aresonance housing 82 which defines theresonance cavity 44 therein. Preferably, theresonance housing 82 is threaded to the piezoelectric housing 80 to provide an exceedingly compact and robust system which is readily maintained. - A
piezoelectric guide sleeve 84 is interfit with an insulator loadreaction interface sleeve 86 and both are mounted within the piezoelectric housing 80 against a stop 88. Theforce transmission diaphragm 58 is preferably sandwiched between and end segment 82 a of theresonance housing 82 which defines thegas resonance tube 52 and thepiezoelectric guide sleeve 84. Theforce transmission diaphragm 58 preferably includes arelief feature 74 as illustrated inFIG. 2B . - A
force transfer member 90 is mounted within thepiezoelectric guide sleeve 84 adjacent theforce transmission diaphragm 58. Theforce transfer member 90 is preferably a frustro-conical member in which an apex 92 thereof is located in contact and preferably interfits with thepiezoelectric crystal stack 66. That is, theforce transfer member 90 essentially combines theforce transfer rod 62 and aforce transfer platen 64 of the above embodiment, however operation is generally equivalent as the apex 92 is in contact with thepiezoelectric crystal stack 66. The oscillating pressure force in thegas resonance tube 52 is transmitted to thepiezoelectric crystal stack 66 through theforce transfer member 90 to generate electrical pulses in anelectrode 94 opposite thepiezoelectric crystal stack 66. The electrical pulses from the electrode are communicated to theigniter system 42 through theelectrical conditioning system 90A via awire harness 96. The wire harness preferably terminates in aconnector 98 which permits removable attachment to aspark power cable 99 such that thesystem - Referring to
FIG. 4 , another ignition system 18 c is illustrated. Theresonance system 36B andpiezoelectric system 38B are integrated within a combustion chamber 24B as would be preferred for a thruster system as each individual thruster system thereby includes an essentially self-contained ignition system. Theresonance system 36B is preferably defined by aresonance housing 12B which defines theresonance cavity 44 therein. Theresonance housing 12B is attached directly to theinjector 12A through fasteners such as bolts b or the like. - As the
FIG. 4 embodiment generally includes components common to that of the previous embodiments, consistent reference numeral usage will be utilized while components more specific to theFIG. 4 embodiment will be described in detail. It will be understood that operation of theFIG. 4 embodiment is generally as theFIG. 3 embodiment, however, theelectrode 100 of theFIG. 4 embodiment is mounted to provide a direct spark torch approach. That is, the electrode directly communicates with thecombustion chamber 24 through theinjector face 28 which contains the multitude of fuel/oxidizer injector elements 30 (shown schematically) which receive fuel from the fuel cooledcombustion chamber wall 20 which is fed via fuel supply line 19 a of thefuel system 14 and an oxidizer such as Gaseous Oxygen (GOx) through an oxidizer supply line 36 a of the oxidizer system 16 (also illustrated inFIG. 1 ). - The
electrode 100 extends through anoxidizer manifold 102 and afuel manifold 103 to generate a spark within thecombustion chamber 24. Theelectrode 100 is mounted within an insulatorload reaction interface 104 which extends along a significant length of theelectrode 100. The insulatorload reaction interface 104 is interfit with thepiezoelectric guide sleeve 84 and retained within theinjector 12A. Atorch housing 106 is defined about the electrode and the insulatorload reaction interface 104 to define a torchoxidizer feed annulus 108. - Oxidizer is communicated form the
oxidizer manifold 102 through torchoxidizer inlet ports 110 through thetorch housing 106. A multitude offuel injection ports 112 in communication with thefuel manifold 103 communicate fuel toward the distal end of theelectrode 100. Oxidizer and fuel is thereby injected adjacent a distal end of theelectrode 100 from which the ignition spark is generated to thereby ignite the mixture within the combustion chamber 24B. As discussed above, since the spark energy production is driven by the resonance of the propellant flow, a fully passive auto-ignition system is provided which is “detuned” when ignition occurs such that spark production automatically stops. - Referring to
FIG. 5 , anotherignition system 18D that utilizes an incompressible working fluid such as a liquid propellant is illustrated. Theresonance system 36C includes an incompressiblefluid resonance housing 120 which defines aresonance cavity 122 therein. Preferably, theresonance housing 120 includes a threadedportion 120A such that a piezoelectric housing 80 and associated piezoelectric system (as disclosed inFIG. 3 ) is threaded thereto. In other words, the piezoelectric housing 80 and associated piezoelectric system (as disclosed inFIG. 3 ) is a common system which may be driven by, for example only, either theresonance housing 82 illustrated ofFIG. 3 or the incompressiblefluid resonance housing 120 illustrated inFIG. 5 to provide an exceedingly compact and robust system. - The incompressible
fluid resonance housing 120 includes asplit leg resonator 124 having a first leg 126 a and a second leg 126 b. The legs 126 a, 126 b split off from anincompressible fluid inlet 128 and rejoin at a common leg 126 c which form a generally triangular relationship. It should be understood that other paths will also be usable with the present invention. Thecommon leg 126C includes anincompressible fluid outlet 132 which is in communication with a combustion chamber as illustrated inFIG. 1 . Agas resonance tube 130 is in communication with the first leg 126 a of thesplit leg resonator 124 to generate an oscillating pressure force within thegas resonance tube 130 due to the unstable flow oscillations between the parallel flowpaths inlegs gas resonance tube 130 may then utilized to drive the piezoelectric system as described above. - As discussed above, since the spark energy production is driven by the resonance of the propellant flow, a fully passive auto-ignition system is provided which is “detuned” when ignition occurs such that spark production automatically stops.
- 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 (38)
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US11/333,691 US7565795B1 (en) | 2006-01-17 | 2006-01-17 | Piezo-resonance igniter and ignition method for propellant liquid rocket engine |
US12/472,326 US8438831B2 (en) | 2006-01-17 | 2009-05-26 | Piezo-resonance igniter and ignition method for propellant liquid rocket engine |
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US11/333,691 US7565795B1 (en) | 2006-01-17 | 2006-01-17 | Piezo-resonance igniter and ignition method for propellant liquid rocket engine |
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US12/472,326 Continuation US8438831B2 (en) | 2006-01-17 | 2009-05-26 | Piezo-resonance igniter and ignition method for propellant liquid rocket engine |
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US12/472,326 Active 2029-05-30 US8438831B2 (en) | 2006-01-17 | 2009-05-26 | Piezo-resonance igniter and ignition method for propellant liquid rocket engine |
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US8438831B2 (en) | 2013-05-14 |
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