Igniter for internal combustion engines operating over a wide range of air fuel ratios

Abstract

An igniter for ignition over a wide air/fuel ratio range is disclosed. The igniter includes an igniter body including an internal cavity disposed substantially within the igniter body, an internal spark gap disposed substantially within the internal cavity, an external spark gap disposed substantially on an exposed surface of the igniter body, and a fuel charge delivery system for delivering a fuel charge to the internal cavity. A method for compression-igniting an air/fuel mixture in a cylinder of an internal combustion engine is also disclosed. The method comprises introducing a substantially homogeneous charge of a first air/fuel mixture into a cylinder of the internal combustion engine during an intake stroke, compressing the substantially homogeneous charge of the first air/fuel mixture in the cylinder of the internal combustion engine during a compression stroke, and combusting the substantially homogeneous charge of the first air/fuel mixture in the cylinder of the internal combustion engine during a power stroke by injecting partially combusted products of a second air/fuel mixture into the cylinder, with the first air/fuel mixture having a substantially higher ratio, by weight, of air to fuel and the second air/fuel mixture.

1 . A turbine engine arrangement comprising: 
 a turbine engine body defining 
 an upstream portion and a downstream portion,  
 a compression section proximate the upstream portion,  
 a combustor operable to receive a combustion section fuel/air mixture to be ignited into a stationary flamefront to deliver pressurized downstream heated products of combustion, the combustion section having a wall structure defining an igniter aperture, and  
 an exhaust section downstream from the combustion section for receiving and passing the heated products of combustion out of the turbine engine body; and  
   an igniter disposed proximate the igniter aperture, the igniter comprising an igniter body defining an ignition prechamber in gaseous communication with the combustion section via a port to receive an igniter fuel mixture, the igniter being configured to ignite the igniter fuel mixture within the ignition prechamber and to project a jet of flame into the combustion section,    whereby the jet of flame reliably lights the flamefront and reliably relights the flamefront under a flameout condition.    
   
   
       2 . The turbine engine arrangement of  claim 1 , wherein the exhaust section comprises an expansion chamber downstream from the combustion section, the expansion chamber defining a jet engine output port that provides a thrust force in an upstream direction in response to the heated products of combustion passing out of the turbine engine body.  
   
   
       3 . The turbine engine arrangement of  claim 1 , wherein the exhaust section comprises a turbine section downstream from the combustion section, the turbine section defining an exhaust nozzle through which the expanding heated products of combustion are passed out of the turbine engine body.  
   
   
       4 . The turbine engine arrangement of  claim 3 , further comprising a turbine located in the turbine section, the turbine being rotatable by the expanding heated products of combustion passing through the turbine section.  
   
   
       5 . The turbine engine arrangement of  claim 4 , wherein the turbine is coupled to an aircraft propeller for driving the propeller in a rotational manner.  
   
   
       6 . The turbine engine arrangement of  claim 4 , wherein the turbine is configured to propel a ground vehicle.  
   
   
       7 . The turbine engine arrangement of  claim 4 , wherein the turbine is configured to propel a water vehicle.  
   
   
       8 . The turbine engine arrangement of  claim 4 , wherein the turbine is coupled to an industrial power shaft for rotating a mechanism having an industrial application.  
   
   
       9 . The turbine engine arrangement of  claim 8 , wherein the mechanism having an industrial application comprises at least one of a pump and an electrical generator.  
   
   
       10 . The turbine engine arrangement of  claim 1 , wherein the igniter comprises an igniter fuel mixture delivery arrangement configured to, when actuated, deliver an igniter fuel mixture into the igniter from an external source.  
   
   
       11 . The turbine engine arrangement of  claim 10 , wherein the igniter comprises an electrode arrangement disposed within the igniter body and defining an internal spark gap, the electrode arrangement being configured to, when actuated, generate a spark across the internal spark gap to ignite the igniter fuel mixture to generate the jet of flame, whereby the jet of flame is projected from the ignition prechamber into the combustion section.  
   
   
       12 . The turbine engine arrangement of  claim 11 , wherein the electrode arrangement comprises a first inner electrode and a second inner electrode.  
   
   
       13 . The turbine engine arrangement of  claim 11 , further comprising an electrode shell disposed proximate an outer surface of the igniter body and defining an external spark gap.  
   
   
       14 . The turbine engine arrangement of  claim 13 , further comprising a capacitor coupled to the electrode arrangement to cause the internal spark gap and the external spark gap to fire sequentially.  
   
   
       15 . The turbine engine arrangement of  claim 11 , wherein the electrode arrangement is disposed within the igniter body proximate the ignition prechamber.  
   
   
       16 . The turbine engine arrangement of  claim 11 , wherein the electrode arrangement is disposed within the igniter body proximate the port.  
   
   
       17 . The turbine engine arrangement of  claim 10 , further comprising a fuel and air storage module operatively coupled to the igniter fuel mixture delivery arrangement and configured to provide selectively and under pressure the igniter fuel mixture to the igniter fuel mixture delivery arrangement, the pressure actuating the igniter fuel mixture delivery arrangement to provide the igniter fuel mixture to the ignition prechamber.  
   
   
       18 . The turbine engine arrangement of  claim 17 , further comprising a solenoid operatively coupled to the fuel storage module and configured to provide selectively the igniter fuel mixture to the fuel storage module.  
   
   
       19 . The turbine engine arrangement of  claim 10 , further comprising an engine control subsystem operatively coupled to the igniter fuel mixture delivery arrangement and configured to control the igniter fuel mixture delivery arrangement to provide under pressure the igniter fuel mixture to the igniter fuel mixture delivery arrangement.  
   
   
       20 . The turbine engine arrangement of  claim 19 , further comprising a voltage source in electrical communication with the engine control subsystem and configurable to cause the igniter to ignite the igniter fuel mixture.  
   
   
       21 . The turbine engine arrangement of  claim 10 , wherein the igniter fuel mixture delivery arrangement facilitates pulsed delivery of the igniter fuel mixture, the igniter fuel mixture delivery arrangement comprising: 
 a delivery conduit to receive the igniter fuel mixture;    a valve arrangement operatively coupled to the delivery conduit and configured to open when the delivery conduit receives the igniter fuel mixture; and    a closure arrangement operatively coupled to the valve arrangement and configured to maintain the valve arrangement in a closed position when the delivery conduit does not receive the igniter fuel mixture.    
   
   
       22 . The turbine engine arrangement of  claim 21 , wherein the closure arrangement comprises a spring.  
   
   
       23 . The turbine engine arrangement of  claim 10 , wherein the igniter fuel mixture delivery arrangement facilitates continuous delivery of the igniter fuel mixture, the igniter fuel mixture delivery arrangement comprising: 
 a delivery conduit to receive the igniter fuel mixture; and    a flame regulation arrangement to prevent a jet of flame from moving into the delivery conduit.    
   
   
       24 . The turbine engine arrangement of  claim 23 , wherein the flame regulation arrangement comprises a flame arrestor.  
   
   
       25 . The turbine engine arrangement of  claim 1 , wherein the igniter fuel mixture comprises at least one of a gaseous fuel and a liquid fuel in combination with at least one of air and oxygen.  
   
   
       26 . The turbine engine arrangement of  claim 1 , further comprising means for evacuating the heated products of combustion from the ignition prechamber.  
   
   
       27 . The turbine engine arrangement of  claim 1 , further comprising an afterburner engine arrangement, the afterburner engine arrangement comprising an afterburner igniter, the afterburner igniter comprising an afterburner fuel mixture delivery arrangement configured to, when actuated, deliver an afterburner fuel mixture into the afterburner igniter from an external source, the afterburner igniter configured to ignite the afterburner fuel mixture and to project a jet of flame into an afterburner chamber, whereby the jet of flame reliably lights the afterburner flame.