IP Library Granted Patent US 8,186,321
Granted Patent B2
US 8,186,321 · App. 12/313,927 · Granted May 29, 2012

Method and apparatus for operating traveling spark igniter at high pressure

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Quick Facts
Patent No.
US 8,186,321
App. No.
12/313,927
Granted
May 29, 2012
Kind
B2
Abstract

An ignition circuit and a method of operating an igniter (preferably a traveling spark igniter) in an internal combustion engine, including a high pressure engine. A high voltage is applied to electrodes of the igniter, sufficient to cause breakdown to occur between the electrodes, resulting in a high current electrical discharge in the igniter, over a surface of an isolator between the electrodes, and formation of a plasma kernel in a fuel-air mixture adjacent said surface. Following breakdown, a sequence of one or more lower voltage and lower current pulses is applied to said electrodes, with a low “simmer” current being sustained through the plasma between pulses, preventing total plasma recombination and allowing the plasma kernel to move toward a free end of the electrodes with each pulse.

Claims (50)

1. A method of plasma generation, comprising:

a. applying a voltage to an igniter, said voltage being of amplitude sufficient to cause breakdown to occur between the electrodes, resulting in an electrical discharge in the igniter in an initiation region, and formation of a plasma kernel adjacent said initiation region; and

b. following breakdown, applying to said electrodes at least one follow-on pulse,

whereby the plasma kernel is forced to move toward a free end of said electrodes by said at least one follow-on pulse.

2. A method of plasma generation, comprising:

a. applying a voltage to an igniter, said voltage being of amplitude sufficient to cause breakdown to occur between the electrodes, resulting in an electrical discharge in the igniter in an initiation region, and formation of a plasma kernel adjacent said initiation region; and

b. following breakdown, applying to said electrodes a sequence of one or more follow-on pulses of current sufficiently low as to maintain a diffuse attachment of the current arc to the electrodes,

whereby the plasma kernel is forced to, and can, move toward a free end of said electrodes under the influence of said follow-on pulses.

3. The method of claim 1 or claim 2 , wherein the initiation region is on or adjacent the surface of an isolator disposed between said electrodes.

4. The method of claim 1 or claim 2 , further including, preventing total kernel recombination of the plasma prior to at least one follow-on pulse.

5. The method of claim 4 , wherein preventing total recombination includes, between pulses of the sequence, maintaining a simmer current between the igniter electrodes sufficient to prevent total recombination of the plasma kernel.

6. The method of claim 4 , wherein preventing total recombination of the plasma kernel includes, in an interval between follow-on pulses, for at least part of said interval maintaining a voltage across electrodes of the igniter below a breakdown voltage but sufficient to sustain enough current to prevent total recombination before the end of the interval.

7. The method of claim 4 , wherein preventing total recombination of the plasma kernel includes setting timing if an interval between follow-on pulses to be shorter than total recombination time.

8. The method of claim 1 or claim 2 , wherein the follow-on pulses do not all have the same polarity of voltage and current.

9. The method of claim 1 or claim 2 , wherein the currents of the follow-on pulses are not constant.

10. A fuel ignition method, comprising:

a. applying a voltage to an igniter in the presence of a combustible fuel, said voltage being of amplitude sufficient to cause breakdown to occur between the electrodes of the igniter, resulting in an electrical discharge in the igniter in an initiation region, and formation of a plasma kernel adjacent said initiation region; and

b. following breakdown, applying to said electrodes a sequence of two or more follow-on pulses,

whereby the plasma kernel is forced to move toward a free end of said electrodes by said follow-on pulses.

11. The method of claim 10 , wherein the initiation region is on or adjacent the surface of an isolator disposed between said electrodes.

12. The method of claim 10 , wherein the igniter is in an internal combustion engine.

13. The method of claim 10 or 12 , further including, preventing total kernel recombination of the plasma prior to a follow-on pulse.

14. The method of claim 13 , wherein preventing total recombination includes, between pulses of the sequence, comprises maintaining a current (termed a simmer current) through the plasma kernel sufficient to prevent total recombination of the plasma kernel.

15. The method of claim 13 , wherein preventing total recombination of the plasma kernel includes, in an interval between follow-on pulses, for at least part of said interval maintaining a voltage across electrodes of the igniter below a breakdown voltage but sufficient to sustain enough current through the plasma to prevent total recombination before the end of the interval.

16. The method of claim 13 , wherein preventing total recombination of the plasma kernel includes setting timing if an interval between follow-on pulses to be shorter than total recombination time.

17. The method of claim 13 , wherein the follow-on pulses do not all have the same polarity of voltage and current.

18. The method of claim 13 , wherein the currents of the follow-on pulses are not constant.

19. The method of claim 13 , wherein the igniter is in an internal combustion engine in which there is a relatively high pressure at the time of ignition.

20. The method of any of claims 1 , 2 or 10 further including, after a follow-on pulse, re-triggering or re-striking the plasma kernel at a time an ionization level of the plasma kernel has fallen below a desired level, with a current and at a voltage sufficient to cause the plasma kernel to grow before total recombination occurs, followed by a next follow-on pulse.

21. The method of claim 20 further including simmering the plasma kernel between at least some follow-on pulse pairs.

22. An ignition circuit for powering an igniter in an internal combustion engine, comprising:

a. means for providing a voltage capable of causing an electrical breakdown discharge between electrodes of an igniter, in an initiation region between said electrodes, when said igniter is disposed in a fuel-air mixture of an engine, whereby a plasma kernel is formed in said region by said discharge; and

b. means for providing a sequence of one or more pulses having voltage and current amplitude and timing sufficient to force the plasma kernel to move toward a free end of said electrodes by said pulses.

23. The ignition circuit of claim 22 , wherein the means for providing a voltage capable of causing electrical breakdown discharge includes a high voltage, low inductance ignition coil having a primary winding and a secondary winding, the secondary winding having a lead for connection to one electrode of an igniter, and a circuit for triggering a signal in the primary winding to induce a high voltage pulse in the secondary winding.

24. The ignition circuit of claim 22 , wherein the means for providing a sequence of pulses comprises a voltage source and, for each said pulse, a capacitor charged by the voltage source and a pulse transformer having a secondary winding connected to said lead and a primary winding through which the capacitor is discharged in response to a trigger signal, inducing said pulse in said lead.

25. The ignition circuit of claim 22 , further including means for providing to the igniter, in an interval between the breakdown discharge and a first follow-on pulse a simmer current sufficient to prevent total recombination of the plasma kernel in said interval.

26. The ignition circuit of claim 25 , further including means for providing to the igniter, in an interval between each successive pair of follow-on pulses a simmer current sufficient to prevent total recombination of the plasma kernel in said interval.

27. The ignition circuit of claim 23 or claim 24 , wherein the ignition coil includes a saturable core on which the primary and secondary windings are formed and the core substantially saturates when said electrical breakdown occurs, whereby the secondary winding thereafter has substantially reduced inductance.

28. An ignition circuit for powering an igniter in an internal combustion engine, comprising:

a. a first voltage pulse generator which generates on an output for connection to an igniter a pulse whose maximum voltage, when delivered to the igniter, is capable of causing a breakdown discharge and consequent high current between electrodes of the igniter, in an initiation region between the electrodes, when said igniter is disposed in a fuel-air mixture, whereby a plasma kernel is formed adjacent said region by said discharge; and

b. a second voltage pulse generator which generates on the output a sequence of one or more follow-on pulses having voltage and current amplitude and timing sufficient to force the plasma kernel to move toward a free end of said electrodes by said follow-on pulses.

29. The ignition circuit of claim 28 , further including a simmer current source which supplies on the output line, in an interval between the breakdown discharge and a first follow-on pulse a simmer current sufficient to prevent total recombination of the plasma kernel in said interval.

30. The ignition circuit of claim 28 , further including a voltage source which maintains between follow-on pulses, for at least a portion of an interval between said follow-on pulses, a voltage on the igniter electrodes below a breakdown voltage but sufficient to prevent total recombination of the plasma kernel during said interval.

31. The ignition circuit of claim 22 or claim 28 including means operable after a follow-on pulse, for re-triggering or re-striking the plasma kernel at a time an ionization level of the plasma kernel has fallen below a desired level, with a current and at a voltage sufficient to cause the plasma kernel to grow before total recombination occurs, followed by a next follow-on pulse.

32. The ignition circuit of claim 22 or 28 , wherein the interval between follow-on pulses is set to be shorter than total recombination time.

33. The method of claim 1 wherein the at least one follow-on pulse is applied to said electrodes by discharging a plasma-sustaining capacitor via a current-controlling discharge path.

34. The method of claim 2 wherein each in the sequence of follow-on pulses is applied to said electrodes by discharging a plasma-sustaining capacitor via a current controlling discharge path.

35. The method of claim 10 wherein each in the sequence of follow-on pulses is applied to said electrodes by discharging a plasma-sustaining capacitor via a current controlling discharge path.

36. The ignition circuit of claim 22 wherein the means for providing a sequence of one or more pulses comprises a plasma-sustaining voltage source which energizes the electrodes and which includes a switch connected in a discharge path from one of said electrodes, wherein the switch is of a type that can be switched while the current through the switch is not zero, to modulate a current drain.

37. The ignition circuit of claim 28 wherein the second voltage pulse generator comprises a plasma-sustaining voltage source which energizes the electrodes and which includes a switch connected in a discharge path from one of said electrodes, wherein the switch is of a type that can be switched while the current through the switch is not zero, to modulate a current drain.

Assignments (10)
SECURITY INTEREST Recorded Sep 16, 2025
From: ADAMS RITE AEROSPACE, INC.; AEROSONIC LLC; AIRBORNE SYSTEMS NA INC; AMSAFE, INC.; ARMTEC DEFENSE PRODUCTS CO.; CHAMPION AEROSPACE LLC; HARCOSEMCO LLC; KING NUTRONICS, LLC; MASON ELECTRIC CO.; PEXCO AEROSPACE, INC.; SHIELD RESTRAINT SYSTEMS, INC; SIMPLEX MANUFACTURING CO.; WHIPPANY ACTUATION SYSTEMS, LLC
To: THE BANK OF NEW YORK MELLON TRUST COMPANY, N.A.
Reel/Frame 072267/0977 →
SECURITY INTEREST Recorded Sep 16, 2025
From: ADAMS RITE AEROSPACE, INC.; AEROSONIC LLC; AIRBORNE SYSTEMS NA INC; AMSAFE, INC.; ARMTEC DEFENSE PRODUCTS CO.; CHAMPION AEROSPACE LLC; HARCOSEMCO LLC; KING NUTRONICS, LLC; MASON ELECTRIC CO.; PEXCO AEROSPACE, INC.; SHIELD RESTRAINT SYSTEMS, INC; SIMPLEX MANUFACTURING CO.; WHIPPANY ACTUATION SYSTEMS, LLC
To: THE BANK OF NEW YORK MELLON TRUST COMPANY, N.A.
Reel/Frame 072268/0176 →
SECURITY INTEREST Recorded Sep 16, 2025
From: ADAMS RITE AEROSPACE, INC.; AEROSONIC LLC; AIRBORNE SYSTEMS NA INC; AMSAFE, INC.; ARMTEC DEFENSE PRODUCTS CO.; CHAMPION AEROSPACE LLC; HARCOSEMCO LLC; KING NUTRONICS, LLC; MASON ELECTRIC CO.; PEXCO AEROSPACE, INC.; SHIELD RESTRAINT SYSTEMS, INC; SIMPLEX MANUFACTURING CO.; WHIPPANY ACTUATION SYSTEMS, LLC
To: THE BANK OF NEW YORK MELLON TRUST COMPANY, N.A.
Reel/Frame 072267/0935 →
SECURITY INTEREST Recorded Sep 16, 2025
From: ADAMS RITE AEROSPACE, INC.; AEROSONIC LLC; AIRBORNE SYSTEMS NA INC; AMSAFE, INC.; ARMTEC DEFENSE PRODUCTS CO.; CHAMPION AEROSPACE LLC; HARCOSEMCO LLC; KING NUTRONICS, LLC; MASON ELECTRIC CO.; PEXCO AEROSPACE, INC.; SHIELD RESTRAINT SYSTEMS, INC; SIMPLEX MANUFACTURING CO.; WHIPPANY ACTUATION SYSTEMS, LLC
To: THE BANK OF NEW YORK MELLON TRUST COMPANY, N.A.
Reel/Frame 072268/0193 →
SECURITY INTEREST Recorded Sep 16, 2025
From: ADAMS RITE AEROSPACE, INC.; AEROSONIC LLC; AIRBORNE SYSTEMS NA INC; AMSAFE, INC.; ARMTEC DEFENSE PRODUCTS CO.; CHAMPION AEROSPACE LLC; HARCOSEMCO LLC; KING NUTRONICS, LLC; MASON ELECTRIC CO.; PEXCO AEROSPACE, INC.; SHIELD RESTRAINT SYSTEMS, INC; SIMPLEX MANUFACTURING CO.; WHIPPANY ACTUATION SYSTEMS, LLC
To: THE BANK OF NEW YORK MELLON TRUST COMPANY, N.A.
Reel/Frame 072268/0018 →
SECURITY INTEREST Recorded Sep 16, 2025
From: ADAMS RITE AEROSPACE, INC.; AEROSONIC LLC; AIRBORNE SYSTEMS NA INC; AMSAFE, INC.; ARMTEC DEFENSE PRODUCTS CO.; CHAMPION AEROSPACE LLC; HARCOSEMCO LLC; KING NUTRONICS, LLC; MASON ELECTRIC CO.; PEXCO AEROSPACE, INC.; SHIELD RESTRAINT SYSTEMS, INC; SIMPLEX MANUFACTURING CO.; WHIPPANY ACTUATION SYSTEMS, LLC
To: THE BANK OF NEW YORK MELLON TRUST COMPANY, N.A.
Reel/Frame 072268/0030 →
SECURITY INTEREST Recorded Sep 5, 2025
From: ADAMS RITE AEROSPACE, INC.; AEROSONIC LLC; AIRBORNE SYSTEMS NA INC.; AMSAFE, INC.; ARMTEC DEFENSE PRODUCTS CO.; CHAMPION AEROSPACE LLC; HARCOSEMCO LLC; KING NUTRONICS, LLC; MASON ELECTRIC CO.; PEXCO AEROSPACE, INC.; SHIELD RESTRAINT SYSTEMS, INC.; SIMPLEX MANUFACTURING CO.; WHIPPANY ACTUATION SYSTEMS, LLC
To: GOLDMAN SACHS BANK USA, AS AGENT
Reel/Frame 072167/0457 →
SECURITY INTEREST Recorded Aug 26, 2025
From: TRANSDIGM INC.; 17111 WATERVIEW PKWY LLC; 4455 GENESEE PROPERTIES, LLC; 4455 GENESEE STREET, LLC; ACME AEROSPACE, INC.; ADAMS RITE AEROSPACE, INC.; AEROCONTROLEX GROUP, INC.; AEROSONIC LLC; AIRBORNE ACQUISITION, INC.; AIRBORNE GLOBAL, INC.; AIRBORNE HOLDINGS, INC.; AIRBORNE SYSTEMS NA INC.; AIRBORNE SYSTEMS NORTH AMERICA INC.; AIRBORNE SYSTEMS NORTH AMERICA OF CA INC.; AMSAFE GLOBAL HOLDINGS, INC.; AMSAFE, INC.; ANGUS ELECTRONICS CO.; APICAL INDUSTRIES, INC.; ARKWIN INDUSTRIES, INC.; ARMTEC COUNTERMEASURES CO.; ARMTEC COUNTERMEASURES TNO CO.; ARMTEC DEFENSE PRODUCTS CO.; ASHFORD PROPERTIES, LLC; AUXITROL WESTON USA, INC.; AVIATION TECHNOLOGIES, INC.; AVIONIC INSTRUMENTS LLC; AVIONICS SPECIALTIES, INC.; AVTECHTYEE, INC.; BETA TRANSFORMER TECHNOLOGY LLC; BREEZE-EASTERN LLC; BRIDPORT HOLDINGS, INC.; BRIDPORT-AIR CARRIER, INC.; BRUCE AEROSPACE INC.; CALSPAN, LLC; CALSPAN AIR FACILITIES, LLC; CALSPAN AIR SERVICES, LLC; CALSPAN ASE PORTUGAL, INC.; CALSPAN HOLDINGS, LLC; CALSPAN JETS LLC; CALSPAN TECHNOLOGY ACQUISITION LLC; CDA INTERCORP LLC; CEF INDUSTRIES, LLC; CHAMPION AEROSPACE LLC; CHELTON AVIONICS HOLDINGS, INC.; CHELTON AVIONICS, INC.; CHELTON DEFENSE PRODUCTS, INC.; CMC ELECTRONICS AURORA LLC; CPI EDB INTERMEDIATE HOLDINGS, INC.; CPI ELECTON DEVICE BUSINESS, INC.; CTHC LLC; DART AEROSPACE USA, INC.; DART BUYER, INC.; DART HELICOPTER SERVICES, INC.; DART INTERMEDIATE, INC.; DART TOPCO, INC.; DATA DEVICE CORPORATION; DUKES AEROSPACE, INC.; ELECTROMECH TECHNOLOGIES LLC; ESTERLINE EUROPE COMPANY LLC; ESTERLINE INTERNATIONAL COMPANY; ESTERLINE TECHNOLOGIES CORPORATION; ESTERLINE TECHNOLOGIES SGIP LLC; FPT INDUSTRIES LLC; GENESEE HOLDINGS, LLC; GENESEE HOLDINGS II, LLC; GENESSE HOLDINGS III, LLC; HARCOSEMCO LLC; HARTWELL CORPORATION; HELI TECH, INC.; HYTEK FINISHES CO.; ICEMAN HOLDCO, INC.; ILC HOLDINGS, INC.; JANCO CORPORATION; JOHNSON LIVERPOOL LLC; KING NUTRONICS, LLC; KIRKHILL INC.; KORRY ELECTRONICS CO.; LEACH HOLDING CORPORATION; LEACH INTERNATIONAL CORPORATION; LEACH MEXICO HOLDING LLC; LEACH TECHNOLOGY GROUP, INC.; MARATHONNORCO AEROSPACE, INC.; MASON ELECTRIC CO.; MCKECHNIE AEROSPACE DE, INC.; MCKECHNIE AEROSPACE HOLDINGS, INC.; MCKECHNIE AEROSPACE US LLC; MEDTHERM LABS, LLC; MICROWAVE POWER PRODUCTS, INC.; NAT SEATTLE INC.; NMC GROUP, INC.; NORDISK AVIATION PRODUCTS LLC; NORTH HILLS SIGNAL PROCESSING CORP.; NORTH HILLS SIGNAL PROCESSING OVERSEAS LLC; NORWICH AERO PRODUCTS, INC.; OFFSHORE HELICOPTER SUPPORT SERVICES, INC.; PALOMAR PRODUCTS, INC.; PARAVION TECHNOLOGY, INC.; PEXCO AEROSPACE, INC.; PNEUDRAULICS, INC.; POWER DEVICE CORPORATION; RAPTOR LABS HOLDCO, LLC; RAPTOR LABS INTERMEDIATE, LLC; SCHNELLER LLC; SEMCO INSTRUMENTS, INC.; SENSOR CONCEPTS, LLC; SERVOTRONICS, INC.; SHIELD RESTRAINT SYSTEMS, INC.; SIMPLEX MANUFACTURING CO.; SKANDIA, INC.; SKURKA AEROSPACE INC.; SPACE ELECTRONICS LLC; SYMETRICS INDUSTRIES, LLC; TA AEROSPACE CO.; TACTIAR FLUID CONTROLS, INC.; TDG ESL HOLDINGS INC.; TEAC AEROSPACE TECHNOLOGIES, INC.; TELAIR US LLC; TESTVONICS, INC.; TEXAS ROTRONICS, INC.; TRANSICOIL LLC; WHIPPANY ACTUATION SYSTEMS, LLC; YOUNG & FRANKLIN INC.; AIRBORNE SYSTEMS NORTH AMERICA OF NJ INC.; BRIDPORT ERIE AVIATION, INC.; TRANSDIGM GROUP INCORPORATED; TRANSDIGM UK HOLDINGS LIMITED
To: THE BANK OF NEW YORK MELLON TRUST COMPANY, N.A., AS TRUSTEE
Reel/Frame 072473/0485 →
ASSIGNMENT OF ASSIGNOR'S INTEREST Recorded May 21, 2025
From: KNITE INC.
To: CHAMPION AEROSPACE LLC
Reel/Frame 071183/0378 →
ASSIGNMENT OF ASSIGNOR'S INTEREST Recorded Mar 31, 2014
From: SUCKEWER, ARTUR P.; SUCKEWER, SZYMON; SELMON, FREDERICK H., III
To: KNITE, INC.
Reel/Frame 032560/0961 →