Patent Publication Number: US-2018045163-A1

Title: Conditional engine igniters

Description:
FIELD OF THE INVENTION 
     The subject matter disclosed herein relates to engine operations in an aircraft, and to a system and a method for engaging an engine igniter in response to a high moisture environment. 
     DESCRIPTION OF RELATED ART 
     Typically, modern aircraft, e.g. fixed wing aircraft, rotary wing aircraft, unmanned aerial vehicles, etc., require certain operating conditions and adjustments for desired engine performance and flight performance. Further, such adjustments may require pilot or operator intervention, sometimes during severe conditions. 
     Aircraft engines are often sensitive to flame out conditions, including high moisture conditions. Engine flame outs can cause undesired low performance and require additional operator attention or poor performance. A system and method that can detect flame out conditions and prevent flame outs from occurring is desired. 
     BRIEF SUMMARY 
     According to an embodiment of the invention, a method for preventing a flame out condition in at least one engine, includes detecting a moisture content exceeding a threshold moisture content in an operating environment of the at least one engine, and engaging at least one igniter associated with the at least one engine in response to the moisture content. 
     In addition to one or more of the features described above, or as an alternative, further embodiments could include disengaging the at least one igniter associated with the at least one engine in response to the moisture content below the threshold moisture content. 
     In addition to one or more of the features described above, or as an alternative, further embodiments could include that the at least one engine is associated with an optionally piloted vehicle or an unmanned air vehicle. 
     In addition to one or more of the features described above, or as an alternative, further embodiments could include detecting the moisture content via a moisture sensor or an atmospheric condition sensor. 
     In addition to one or more of the features described above, or as an alternative, further embodiments could include comparing the moisture content with the threshold moisture content via a vehicle management computer. 
     In addition to one or more of the features described above, or as an alternative, further embodiments could include setting the threshold moisture content. 
     In addition to one or more of the features described above, or as an alternative, further embodiments could include that the threshold moisture content is a relative or absolute humidity percentage. 
     In addition to one or more of the features described above, or as an alternative, further embodiments could include indicating to an operator to engage the at least one igniter in response to the moisture content. 
     In addition to one or more of the features described above, or as an alternative, further embodiments could include indicating to the operator a status of the at least one igniter. 
     In addition to one or more of the features described above, or as an alternative, further embodiments could include that the moisture content includes an ice content. 
     According to an embodiment of the invention, a system for preventing a flame out condition in at least one engine, includes at least one sensor to detect a moisture content exceeding a threshold moisture content in an operating environment of the at least one engine, and a controller to engage at least one igniter associated with the at least one engine in response to the moisture content. 
     In addition to one or more of the features described above, or as an alternative, further embodiments could include that the controller disengages the at least one ignitor associated with the at least one engine in response to the moisture content below the threshold moisture content. 
     In addition to one or more of the features described above, or as an alternative, further embodiments could include that the controller is integrated with a vehicle management computer. 
     In addition to one or more of the features described above, or as an alternative, further embodiments could include that the controller sets the threshold moisture content. 
     In addition to one or more of the features described above, or as an alternative, further embodiments could include that the controller indicates to an operator a status of the at least one igniter. 
     Technical function of the embodiments described above includes engaging at least one igniter associated with the at least one engine in response to the moisture content. 
     Other aspects, features, and techniques of the invention will become more apparent from the following description taken in conjunction with the drawings. 
    
    
     
       BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWINGS 
       The subject matter, which is regarded as the invention, is particularly pointed out and distinctly claimed in the claims at the conclusion of the specification. The foregoing and other features, and advantages of the invention are apparent from the following detailed description taken in conjunction with the accompanying drawings in which like elements are numbered alike in the several FIGURES: 
         FIG. 1  is a schematic isometric view of an aircraft in accordance with an embodiment of the invention; 
         FIG. 2  illustrates a schematic view of an exemplary conditional igniter system in accordance with an embodiment of the invention; and 
         FIG. 3  is a flow diagram of a method of conditionally engaging igniters in accordance with an embodiment of the invention. 
     
    
    
     DETAILED DESCRIPTION OF THE INVENTION 
     Referring now to the drawings,  FIG. 1  illustrates a general perspective view of an exemplary vehicle in the form of aircraft  100  for use with a conditional igniter system in accordance with an embodiment of the invention. In an embodiment, aircraft  100  is an optionally piloted vehicle and can autonomously perform required igniter operations as it traverses a flight plan. In certain embodiments, aircraft  100  can be any suitable aircraft, including fixed wing, rotary wing aircraft, etc. Aircraft  100  includes an airframe  102 , an engine  118 , a plurality of sensors  122 , and a vehicle management computer  120 . 
     Airframe  102  of aircraft  100  includes a main rotor  104 , an extending tail  106  which mounts an anti-torque system, such as a tail rotor  108 . Main rotor  104  and tail rotor  108  are driven to rotate by one or more engines  118  through one or more gearboxes (not shown). In certain embodiments, performance and operation of engines  118  are affected by environmental conditions that can cause flame out conditions. 
     In an exemplary embodiment, sensors  122  are disposed on airframe  102  of aircraft  100 . Sensors  122  can include moisture sensors, atmospheric sensors, etc. Sensors  122  can be of any suitable type and can be used to sense potential flame out conditions. 
     Vehicle management computer  120  can be utilized to control vehicle functions, including but not limited to control functions, engine management, etc. In an exemplary embodiment, signals from sensors  122  are received by vehicle management computer  120  and are utilized to manage flame out conditions. 
     In an exemplary embodiment, flameout conditions logic controller  124  can work with, or independently from vehicle management computer  120  to monitor sensor feedback for flame out conditions. In certain embodiments, flame out logic controller  124  is integrated with vehicle management computer  120 . In certain embodiments, flameout logic controller  124  is software logic integrated with vehicle management computer  120 . 
     In certain embodiments, flameout conditions logic controller  124  and/or vehicle management computer  120  can signal to igniter  128  or igniter control  126  to engage the igniters  128  to proactively avoid a flame out condition. In an exemplary embodiment, igniters  128  are engaged as long as flame out conditions are present. After flame out conditions are no longer present, igniters  128  may be disengaged. 
     Although a particular aircraft is illustrated and described in the disclosed embodiment, it will be appreciated that other configurations and/or machines including autonomous and optionally piloted aircraft that may operate in land or water including fixed-wing aircraft, rotary-wing aircraft, and land vehicles (e.g., trucks, cars, etc.) may also benefit from embodiments disclosed. 
     As illustrated in  FIG. 2 , a conditional igniter system  200  is shown. In an exemplary embodiment, conditional igniter system  200  includes sensors  222   a  ,  222   b  , flameout conditions logic controller  224 , and igniters  228 . 
     In an exemplary embodiment, sensors  222   a  ,  222   b  can be standalone sensors, sensors for other vehicle systems, or sensors integrated with other vehicle systems. In an exemplary embodiment, moisture sensors  222   a  can detect moisture within an environment, while atmospheric sensors  222   b  can be configured to detect broadband atmospheric conditions. In an exemplary embodiment, sensors  222   a  ,  222   b  can generally detect atmospheric conditions that can cause flame out conditions in engines  218 . Flame out conditions may exist when atmospheric moisture, relative or absolute humidity, temperature, ice, etc., meet, exceed, or otherwise move beyond a certain threshold. Sensors  222   a  ,  222   b  can also detect clouds, rain, and other atmospheric conditions that may cause flame out conditions. 
     In an exemplary embodiment, flameout conditions logic controller  224  can work in conjunction with, or independently from vehicle management computer  220 . In certain embodiments, vehicle management computer  220  can contain or be integrated with flameout conditions logic controller  224 . In certain embodiments, flameout conditions logic controller  224  is a controller integrated with igniter controller  226 , engine  218  control etc. 
     In an exemplary embodiment, flameout conditions logic controller  224  monitors sensors  222   a  ,  222   b  for flameout conditions. In certain embodiments, readings from sensors  222   a  ,  222   b  are compared to predefined or preset thresholds for sensor readings, to indicate environmental conditions where flame outs are more likely to occur. In certain embodiments, a user, technician, etc. can set a threshold, such as a moisture threshold or temperature threshold to compare against sensor  222   a  ,  222   b  inputs. In an exemplary embodiment, flameout conditions logic controller  224  can accordingly engage a conditional response if a sensor  222   a  ,  222   b  reading meets or exceeds a predefined threshold. Similarly, flameout conditions logic controller  224  can disengage a conditional response if a threshold is no longer met. 
     In certain embodiments, flameout conditions logic controller  224  can automatically engage and disengage a conditional response in response to certain detected conditions. In other embodiments, flameout conditions logic controller  224  can additionally signal to a pilot, operator, etc., that a conditional response is being utilized. In certain embodiments, the flameout conditions logic controller  224  can signal for an operator or pilot to engage or disengage a conditional response. 
     In an exemplary embodiment, the conditional response can include, but is not limited to engaging or disengaging an igniter  228  of an engine  218 . In certain embodiments, igniters  228  are controlled by an igniter controller  226 , which can be part of an overall engine  218  controller. While in other embodiments, igniters  228  are directly controlled by flameout conditions logic controller  224 . Igniters are typically found on aircraft engines  228  and are used to ignite engines  218  to start or restart engines  218 . Igniters can be ignited by vehicle management computer  220 , flameout conditions logic controller  224 , engine  218  controller, or igniter controller  226 . 
     Advantageously, flameout conditions logic controller  224  can engage igniter  228  when flame out conditional thresholds are exceeded. In an exemplary embodiment, engaging igniters  228  can proactively prevent a flame out condition from occurring. In certain embodiments, when flame out conditions thresholds are not reached, igniters  228  can be disengaged. 
       FIG. 3  illustrates a method  300  for conditionally engaging an igniter to prevent flame out conditions. In operation  302 , in an exemplary embodiment, an operator, user, technician, etc., sets a threshold moisture content or other environmental parameter threshold for the conditional igniter logic. In an exemplary embodiment, previous experience, lookup tables, etc., are used to set a proper threshold. In certain embodiments, the threshold set can provide an additional safety factor or margin to prevent flameout conditions. In an exemplary embodiment, the threshold is adaptively set based on changing environmental parameters. 
     In operation  304 , in an exemplary embodiment, moisture content is detected via a moisture or atmospheric condition sensor. In an exemplary embodiment, the sensors are disposed relative to the engines to provide representative readings of the conditions experienced by the engines. In certain embodiments, moisture content is periodically or continuously detected via moisture or atmospheric condition sensors to allow moisture content comparisons to be performed. 
     In operation  306 , in an exemplary embodiment, sensor readings are compared to the previously determined threshold, via a flameout conditions logic controller. In certain embodiments, the flameout conditions logic controller is integrated in a vehicle management computer. 
     In operation  308 , in an exemplary embodiment, at least one igniter that is associated with at least one engine is engaged if a sensor reading exceeds a predetermined threshold. Advantageously, engaging at least one igniter can prevent flame out conditions. In an exemplary embodiment, an igniter is engaged if a moisture content exceeds a threshold moisture content. 
     In operation  307 , in an alternative embodiment, the flameout condition logic controller can indicate to the pilot or operator to engage at least one igniter in response to a threatened flame out condition or to otherwise prevent a flameout condition. 
     In operation  309 , in an exemplary embodiment, the status of the igniters are indicated to the user, pilot, operator, etc. 
     In operation  310 , in an exemplary embodiment, moisture content is detected via a moisture or atmospheric condition sensor. In an exemplary embodiment, the sensors are disposed relative to the engines to provide representative readings of the conditions experienced by the engines. In certain embodiments, moisture content is periodically or continuously detected via moisture or atmospheric condition sensors to allow moisture content comparisons to be performed. 
     In operation  311 , in an exemplary embodiment, after the igniters are engaged, sensor readings are compared to the previously determined threshold, via a flameout conditions logic controller. In certain embodiments, the flameout conditions logic monitor will continue to monitor sensor readings to determine if igniters need to remain engaged in response to threatened flameout conditions or to otherwise prevent a flameout condition. 
     In operation  312 , in an exemplary embodiment, the igniters are disengaged after a conditional threshold is no longer met and flameout conditions are no longer present. In an exemplary embodiment, flameout conditions logic controller can still compare sensor readings against a threshold to appropriately engage and disengage the igniters. In certain embodiments, the igniters can be disengaged automatically. 
     In operation  313 , in an alternative embodiment, the flameout condition logic controller can indicate to the pilot or operator to disengage at least one igniter after a conditional threshold is no longer met and flameout conditions are no longer present. 
     In operation  314 , in an exemplary embodiment, the status of the igniters are indicated to the user, pilot, operator, etc. In certain embodiments, the status of the igniters is periodically or continuously indicated. 
     The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. While the description of the present invention has been presented for purposes of illustration and description, it is not intended to be exhaustive or limited to the invention in the form disclosed. Many modifications, variations, alterations, substitutions or equivalent arrangement not hereto described will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the invention. Additionally, while the various embodiments of the invention have been described, it is to be understood that aspects of the invention may include only some of the described embodiments. Accordingly, the invention is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.