Patent Publication Number: US-11649735-B2

Title: Methods of cleaning a component within a turbine engine

Description:
CROSS REFERENCE TO RELATED APPLICATIONS 
     This Application claims priority to, and is a divisional application of, U.S. patent application Ser. No. 15/498,141 filed Apr. 26, 2017 which is incorporated by reference in its entirety herein. 
    
    
     BACKGROUND 
     The present disclosure relates generally to turbine engines and, more specifically, to cleaning coked hydrocarbons from a component within a turbine engine. 
     In a gas turbine engine, air is pressurized in a compressor, mixed with fuel in a combustor, and ignited such that hot combustion gas is generated. In at least some known turbine engines, ignition of the air and fuel can result in oxidation and partial decomposition of the mixture, thereby resulting in coking within the turbine engine. More specifically, coking is a process that forms hard deposits within a fuel supply system of the turbine engine, for example. The hard deposits also form from other hydrocarbon-based substances in other areas of the turbine engine, such as in a fan assembly of the turbine engine. Excess buildup of the hard deposits in the turbine engine can clog the components of the turbine engine, and necessitate service of the turbine engine after prolonged use. For example, servicing the fuel supply system generally includes detaching the turbine engine from an airframe, removing fuel nozzles of the fuel supply system from the turbine engine, replacing the fuel nozzles with different fuel nozzles, transferring the removed fuel nozzles to another location for cleaning, and reattaching the turbine engine to the airframe. As such, a stockpile of unused turbine engine components is maintained in the event a turbine engine is scheduled for service. In addition, removing and replacing fuel nozzles in the fuel supply system can be a time-consuming and laborious task. Moreover, if combusted engine oil is trapped outside of the fuel supply system, such as in the fan assembly, critical ventilation can be blocked, resulting in unscheduled engine removal and significant disassembly to service the components at a piece-part level. 
     BRIEF DESCRIPTION 
     In one aspect, a method of cleaning a component within a turbine engine is provided. The method includes disassembling the turbine engine to provide a flow path to an interior passageway of the component from an access point. The component has coked hydrocarbons formed thereon. The method further includes discharging a flow of cleaning solution towards the interior passageway from the access point, wherein the cleaning solution is configured to remove the coked hydrocarbons from the component. 
     In one embodiment, which may include at least a portion of the subject matter of any of the preceding and/or following examples and aspects, disassembling the turbine engine includes disassembling the turbine engine when the turbine engine is coupled to an airframe. 
     In one embodiment, which may include at least a portion of the subject matter of any of the preceding and/or following examples and aspects, disassembling the turbine engine includes disassembling a fuel manifold to define an inlet port within the fuel manifold, wherein the inlet port defines the access point. 
     In one embodiment, which may include at least a portion of the subject matter of any of the preceding and/or following examples and aspects, discharging a flow of cleaning solution includes discharging the flow of cleaning solution towards the interior passageway in a pulsed interval having a discharge time defined within a range between about 5 seconds and about 120 seconds. 
     In one embodiment, which may include at least a portion of the subject matter of any of the preceding and/or following examples and aspects, discharging a flow of cleaning solution includes discharging the flow of cleaning solution towards the interior passageway in at least a first pulsed interval and a second pulsed interval, wherein a residence time is defined between the first pulsed interval and the second pulsed interval. 
     In one embodiment, which may include at least a portion of the subject matter of any of the preceding and/or following examples and aspects, the method further includes defining the residence time within a range between about 2 minutes and about 30 minutes. 
     In one embodiment, which may include at least a portion of the subject matter of any of the preceding and/or following examples and aspects, discharging a flow of cleaning solution comprises heating the cleaning solution to a temperature defined within a range between about 30° C. and 95° C. 
     In one embodiment, which may include at least a portion of the subject matter of any of the preceding and/or following examples and aspects, the method further includes disassembling the turbine engine to define a drainage port in the turbine engine, wherein the cleaning solution is drained from the turbine engine through the drainage port. 
     In one embodiment, which may include at least a portion of the subject matter of any of the preceding and/or following examples and aspects, the method further includes discharging a flow of rinsing solution towards the interior passageway from the access point. 
     In another aspect, a method of cleaning a component within a turbine engine is provided. The method includes disassembling the turbine engine to provide a flow path to an interior passageway of the component from an access point, wherein the component has coked hydrocarbons formed thereon, and filling a volume of the interior passageway with an amount of cleaning solution. The cleaning solution is configured to remove the coked hydrocarbons from the component. The method further includes holding the amount of cleaning solution within the interior passageway for a predetermined residence time. 
     In one embodiment, which may include at least a portion of the subject matter of any of the preceding and/or following examples and aspects, disassembling the turbine engine includes disassembling a fan assembly of the turbine engine to define a first open end of a fan midshaft of the turbine engine, wherein the first open end defines the access point. 
     In one embodiment, which may include at least a portion of the subject matter of any of the preceding and/or following examples and aspects, the fan midshaft includes a second open end, and the method further includes sealing the second open end prior to discharging the flow of cleaning solution towards the interior passageway. 
     In one embodiment, which may include at least a portion of the subject matter of any of the preceding and/or following examples and aspects, sealing the second open end includes positioning a plug within the interior passageway of the component proximate the second open end, wherein the plug is insertable through the first open end of the fan midshaft when in a first operational mode, and actuating the plug into a second operational mode from the first operational mode, wherein the plug is configured to seal the second open end when in the second operational mode. 
     In one embodiment, which may include at least a portion of the subject matter of any of the preceding and/or following examples and aspects, filling a volume of the interior passageway includes filling the volume with the cleaning solution including a foaming agent. 
     In one embodiment, which may include at least a portion of the subject matter of any of the preceding and/or following examples and aspects, holding the amount of cleaning solution comprises holding the amount of cleaning solution for the predetermined residence time defined within a range between about 30 minutes and about 8 hours. 
     In yet another aspect, a method of cleaning a component within a turbine engine is provided. The method includes disassembling the turbine engine to define an access point to the component. The component has coked hydrocarbons formed thereon. The method further includes discharging a flow of cleaning solution towards the component from the access point, wherein the cleaning solution is configured to remove the coked hydrocarbons from the component, and wherein the cleaning solution includes at least one of citric acid or glycolic acid. 
     In one embodiment, which may include at least a portion of the subject matter of any of the preceding and/or following examples and aspects, disassembling the turbine engine includes disassembling the turbine engine when the turbine engine is coupled to an airframe. 
     In one embodiment, which may include at least a portion of the subject matter of any of the preceding and/or following examples and aspects, disassembling the turbine engine includes disassembling the turbine engine to provide access to a fuel nozzle of the turbine engine. 
     In one embodiment, which may include at least a portion of the subject matter of any of the preceding and/or following examples and aspects, discharging a flow of cleaning solution includes discharging the flow of cleaning solution that further includes a foaming agent. 
     In one embodiment, which may include at least a portion of the subject matter of any of the preceding and/or following examples and aspects, the method further includes disassembling a fuel manifold to define an inlet port within the fuel manifold, wherein the inlet port defines the access point, and discharging the flow of cleaning solution through the inlet port and towards the component. 
    
    
     
       DRAWINGS 
       These and other features, aspects, and advantages of the present disclosure will become better understood when the following detailed description is read with reference to the accompanying drawings in which like characters represent like parts throughout the drawings, wherein: 
         FIG.  1    is a schematic illustration of an exemplary turbine engine; 
         FIG.  2    is a schematic illustration of an exemplary fluid delivery system that may be used to clean the turbine engine shown in  FIG.  1   ; 
         FIG.  3    is a box diagram illustrating the fluid delivery system shown in  FIG.  2    providing fluid to a component of the turbine engine shown in  FIG.  1    from an exemplary access point; 
         FIG.  4    is a box diagram illustrating the fluid delivery system shown in  FIG.  2    providing fluid to the component of the turbine engine shown in  FIG.  1    from an alternative access point; 
         FIG.  5    is a box diagram illustrating the fluid delivery system shown in  FIG.  2    providing fluid to an alternative component of the turbine engine shown in  FIG.  1    from an exemplary access point; 
         FIG.  6    is a schematic illustration of an exemplary sealing and discharge assembly in a first operational mode that may be used when delivering fluid to the component shown in  FIG.  5   ; 
         FIG.  7    is a schematic illustration of the sealing and discharge assembly shown in  FIG.  6    in a second operational mode; 
         FIG.  8    is a flow diagram illustrating an exemplary method of cleaning a component within a turbine engine, in accordance with a first embodiment of the disclosure; 
         FIG.  9    is a flow diagram illustrating an exemplary method of cleaning a component within a turbine engine, in accordance with a second embodiment of the disclosure; and 
         FIG.  10    is a flow diagram illustrating an exemplary method of cleaning a component within a turbine engine, in accordance with a third embodiment of the disclosure. 
     
    
    
     Unless otherwise indicated, the drawings provided herein are meant to illustrate features of embodiments of the disclosure. These features are believed to be applicable in a wide variety of systems comprising one or more embodiments of the disclosure. As such, the drawings are not meant to include all conventional features known by those of ordinary skill in the art to be required for the practice of the embodiments disclosed herein. 
     DETAILED DESCRIPTION 
     In the following specification and the claims, reference will be made to a number of terms, which shall be defined to have the following meanings. 
     The singular forms “a”, “an”, and “the” include plural references unless the context clearly dictates otherwise. 
     “Optional” or “optionally” means that the subsequently described event or circumstance may or may not occur, and that the description includes instances where the event occurs and instances where it does not. 
     Approximating language, as used herein throughout the specification and claims, may be applied to modify any quantitative representation that could permissibly vary without resulting in a change in the basic function to which it is related. Accordingly, a value modified by a term or terms, such as “about”, “approximately”, and “substantially”, are not to be limited to the precise value specified. In at least some instances, the approximating language may correspond to the precision of an instrument for measuring the value. Here and throughout the specification and claims, range limitations may be combined and/or interchanged. Such ranges are identified and include all the sub-ranges contained therein unless context or language indicates otherwise. 
     As used herein, the terms “axial” and “axially” refer to directions and orientations that extend substantially parallel to a centerline of the turbine engine. Moreover, the terms “radial” and “radially” refer to directions and orientations that extend substantially perpendicular to the centerline of the turbine engine. In addition, as used herein, the terms “circumferential” and “circumferentially” refer to directions and orientations that extend arcuately about the centerline of the turbine engine. 
     Embodiments of the present disclosure relate to cleaning coked hydrocarbons from a component within a turbine engine. More specifically, the systems and methods described herein facilitate cleaning the turbine engine without, for example, having to detach the turbine engine from the airframe, and without having to remove the component to be cleaned from the turbine engine. In contrast, the systems and methods described herein provide a cleaning solution to the turbine engine via an access point, which is defined by disassembling a portion of the turbine engine while still coupled to the airframe. For example, in one embodiment, fuel nozzles of the turbine engine have coked hydrocarbons formed thereon, and the turbine engine is disassembled such that cleaning fluid may be provided to the fuel nozzles from a single access point. As such, the time and effort for disassembling and cleaning components of the turbine engine are reduced, thereby reducing the amount of time for returning a refurbished turbine engine to service. 
     While the following embodiments are described in the context of a turbofan engine, it should be understood that the systems and methods described herein are also applicable to turboprop engines, turboshaft engines, turbojet engines, and ground-based turbine engines, for example. 
       FIG.  1    is a schematic diagram of an exemplary turbine engine  10  coupled to an airframe  11 . Turbine engine  10  includes a fan assembly  12 , a low-pressure or booster compressor assembly  14 , a high-pressure compressor assembly  16 , and a combustor assembly  18 . Fan assembly  12 , booster compressor assembly  14 , high-pressure compressor assembly  16 , and combustor assembly  18  are coupled in flow communication. Turbine engine  10  also includes a high-pressure turbine assembly  20  coupled in flow communication with combustor assembly  18  and a low-pressure turbine assembly  22 . Fan assembly  12  includes an array of fan blades  24  extending radially outward from a rotor disk  26 . Low-pressure turbine assembly  22  is coupled to fan assembly  12  and booster compressor assembly  14  through a first drive shaft  28 , and high-pressure turbine assembly  20  is coupled to high-pressure compressor assembly  16  through a second drive shaft  30 . Turbine engine  10  has an intake  32  and an exhaust  34 . Turbine engine  10  further includes a centerline  36  about which fan assembly  12 , booster compressor assembly  14 , high-pressure compressor assembly  16 , and turbine assemblies  20  and  22  rotate. 
     In operation, air entering turbine engine  10  through intake  32  is channeled through fan assembly  12  towards booster compressor assembly  14 . Compressed air is discharged from booster compressor assembly  14  towards high-pressure compressor assembly  16 . Highly compressed air is channeled from high-pressure compressor assembly  16  towards combustor assembly  18 , mixed with fuel, and the mixture is combusted within combustor assembly  18 . High temperature combustion gas generated by combustor assembly  18  is channeled towards turbine assemblies  20  and  22 . Combustion gas is subsequently discharged from turbine engine  10  via exhaust  34 . 
       FIG.  2    is a schematic illustration of an exemplary fluid delivery system  100  that may be used to clean turbine engine  10  (shown in  FIG.  1   ). In the exemplary embodiment, fluid delivery system  100  is embodied as a mobile flight line cart including a plurality of components that, when used in combination, facilitate providing a flow of cleaning solution to turbine engine  10 . Fluid delivery system  100  includes a cleaning tank  102  that stores the cleaning solution therein, and a rinse tank  104  that stores a rinsing solution therein, such as deionized water. Cleaning tank  102  includes a heater  106  positioned therein for heating the cleaning solution to a predetermined temperature. Heater  106  facilitates heating the cleaning solution to any temperature that enables the systems and methods to function as described herein. In one embodiment, heater  106  heats the cleaning solution to a temperature defined within a range between about 30° C. and about 95° C. before being discharged towards turbine engine  10 . 
     Cleaning tank  102  and rinse tank  104  are coupled in flow communication with a first valve assembly  108  that is selectively operable to provide either the cleaning solution or the rinsing solution to turbine engine  10 . More specifically, fluid delivery system  100  includes a first pump  110  coupled in flow communication with first valve assembly  108 . First pump  110  discharges either the cleaning solution or the rinsing solution towards a second valve assembly  112 , which is selectively operable to discharge the selected solution towards turbine engine  10  via a discharge line  114 . In some embodiments, fluid delivery system  100  includes a compressor  116  coupled in flow communication with discharge line  114 , and compressor  116  is selectively operable to facilitate providing purge air through discharge line  114  when draining solution from turbine engine  10 . Fluid delivery system  100  also includes an accumulator  118  coupled between first pump  110  and second valve assembly  112 . Accumulator  118  modulates the flow pulses discharged from first pump  110  to provide a steady flow to second valve assembly  112 . 
     In one embodiment, fluid delivery system  100  further includes a receiving line  120  coupled in flow communication with turbine engine  10 . As will be explained in more detail below, receiving line  120  receives fluid that has been channeled towards turbine engine  10  through discharge line  114 , circulated through turbine engine  10 , and subsequently drained from turbine engine  10 . In the exemplary embodiment, fluid delivery system  100  includes a second pump  122  coupled in flow communication with receiving line  120 . When used cleaning solution is channeled through receiving line  120 , second pump  122  induces flow of the used cleaning solution from turbine engine  10  and discharges the used cleaning solution towards a filter  124 . In some embodiments, filter  124  removes contaminants from the used cleaning solution, thereby forming reconditioned cleaning solution, which is then discharged into cleaning tank  102  for further use. 
     Fluid delivery system  100  may use any cleaning solution to clean turbine engine  10  that enables the systems and methods to function as described herein. In the exemplary embodiment, the cleaning solution is formed a cleaning detergent and water. In one embodiment, the cleaning solution includes cleaning detergent of up to about 20 percent by weight of the composition. Moreover, the cleaning solution includes any cleaning detergent that enables the systems and methods to function as described herein. In one embodiment, the cleaning detergent is generally effective at degreasing and decoking, and contains an organic and alkaline solution of up to about 20 percent by weight of the detergent. In some embodiments, the organic and alkaline solution includes alkyl and aromatic amines, non-ionic, anionic, and cationic surfactants, and either a polycyclic aromatic hydrocarbon or di-propylene glycol methyl ether. 
     In an alternative embodiment, the cleaning solution includes at least one of citric acid or glycolic acid. An example cleaning solution that includes at least one of citric acid or glycolic acid includes, but is not limited to, Citranox® (“Citranox” is a registered trademark of Alconox, Inc., of White Plains, N.Y.). In some embodiments, the cleaning solution also includes at least one of a foaming agent, surfactants, or other suitable additives. In a further alternative embodiment, the cleaning solution includes an organic solvent, such as a Turco® 8226 cleaning solution. 
       FIGS.  3 - 5    are box diagrams illustrating fluid delivery system  100  (shown in  FIG.  2   ) providing solution to a component of turbine engine  10  from an access point. In the exemplary embodiment, turbine engine  10  includes a fuel supply system  126  including a component  127 , such as at least one fuel nozzle  128 . Fuel supply system  126  also includes a fuel circuit  130 , a split control unit (SCU)  132  coupled in selective flow communication with fuel circuit  130 , and a fuel manifold  134  coupled in flow communication SCU  132 . In operation, fuel is channeled towards fuel nozzle  128  from fuel circuit  130 , through SCU  132 , through fuel manifold  134 , and towards an interior passageway  136  of fuel nozzle  128 . As noted above, coked hydrocarbons sometimes form on a component within turbine engine  10  after prolonged use. In the exemplary embodiment, the component is a component of fuel supply system  126  or a fan midshaft, as will be described in more detail below. 
     Referring to  FIG.  3   , a method of cleaning a component, such as fuel nozzle  128 , within turbine engine  10  is described herein. In the exemplary embodiment, fuel nozzle  128  has coked hydrocarbons formed thereon, such as within interior passageway  136  or on an outer surface of fuel nozzle  128 . The method includes disassembling a first portion of turbine engine  10  to provide a flow path  137  to interior passageway  136  of fuel nozzle  128  from an access point  138 . More specifically, fuel manifold  134  is disassembled by disconnecting SCU  132  from fuel manifold  134  to define inlet port  140  and access point  138  at fuel manifold  134 . A flow of cleaning solution is then discharged towards interior passageway  136  from access point  138 , where the cleaning solution is configured to remove the coked hydrocarbons from fuel nozzle  128 . For example, in the exemplary embodiment, discharge line  114  of fluid delivery system  100  (shown in  FIG.  2   ) is connected to fuel manifold  134  at inlet port  140 , and fluid delivery system  100  is actuated to discharge cleaning solution towards turbine engine  10 . 
     In one embodiment, the flow of cleaning solution is discharged in at least one pulsed interval having a predetermined discharge time. For example, the flow of cleaning solution is discharged in at least a first pulsed interval and a second pulsed interval, where a predetermined residence time is defined between the first pulsed interval and the second pulsed interval. Introducing the cleaning solution into turbine engine  10  in the first pulsed interval and then allowing a predetermined residence time to elapse before discharging the second pulsed interval facilitates allowing the cleaning solution of the first pulsed interval to settle and interact with the coked hydrocarbons formed on fuel nozzle  128 . The second pulsed interval is then discharged after the predetermined residence time has elapsed such that the cleaning solution within turbine engine  10  is refreshed. Alternatively, a flow of rinsing solution is discharged into turbine engine  10  after the predetermined residence time has elapsed after the first pulsed interval. 
     The predetermined discharge time and the predetermined residence time may be of any duration that enables the systems and methods to function as described herein. In one embodiment, the predetermined discharge time is defined within a range between about 5 seconds and about 120 seconds. In addition, in one embodiment, the predetermined residence time is defined within a range between about 2 minutes and about 30 minutes. 
     In the exemplary embodiment, the flow of cleaning solution is channeled through inlet port  140 , through fuel manifold  134 , through interior passageway  136  of fuel nozzle  128 , and is then discharged from fuel nozzle  128 . The method further includes disassembling a second portion of turbine engine  10  to define a drainage port  142  therein. Drainage port  142  is coupled in flow communication with fuel nozzle  128  such that the solution channeled into turbine engine  10  is drained from turbine engine  10  through drainage port  142 . In one embodiment, drainage port  142  is defined by uninstalling at least one ignitor plug (not shown) from turbine engine  10 , where the at least one ignitor plug is located at about a 6 o&#39;clock position within turbine engine  10 . As such, the solution is gravity drained from turbine engine  10 . More specifically, the solution is discharged from fuel nozzle  128  and into a combustor dome, is drained through air holes in the combustor dome into a combustor case, and is then drained from the combustor case through drainage port  142 . Moreover, in the exemplary embodiment, receiving line  120  of fluid delivery system  100  is coupled to turbine engine  10  at drainage port  142  such that used cleaning solution is recycled to fluid delivery system  100 , as described above. 
     The method further includes discharging a flow of rinsing solution towards interior passageway  136  of fuel nozzle  128  from access point  138 . More specifically, fluid delivery system  100  is actuated as described above to facilitate discharging the flow of rinsing solution through discharge line  114  rather than the flow of cleaning solution. The rinsing solution is then drained through drainage port  142 . 
     Referring to  FIG.  4   , the method includes disassembling a portion of turbine engine  10  to provide direct access to fuel nozzle  128  having coked hydrocarbons formed thereon. More specifically, turbine engine  10  is disassembled to define an access point  144  at an inlet port  146  of turbine engine  10 . For example, inlet port  146  is defined by uninstalling at least one ignitor plug from turbine engine  10 , or by uninstalling a borescope cover from turbine engine  10 . The flow of cleaning solution is then discharged towards fuel nozzle  128  from access point  144 , such that the cleaning solution impinges against an outer surface  148  of fuel nozzle  128 . In some embodiments, the cleaning solution enters fuel nozzle  128  through an opening defined therein such that coked hydrocarbons are also removed the interior of fuel nozzle  128 . 
     Referring to  FIG.  5   , the method includes disassembling fan assembly  12  of turbine engine  10  to provide access to component  127  installed therein. For example, in the exemplary embodiment, fan assembly  12  includes a fan midshaft  150  and a center body  152  and a center vent tube  153  coupled to fan midshaft  150 . Disassembling fan assembly  12  includes removing center body  152  from fan midshaft  150  to define a first open end  154  in fan midshaft  150 , and removing center vent tube  153  from fan midshaft  150  to provide access to an interior of fan midshaft  150 . More specifically, first open end  154  defines an access point  156  to an interior passageway  158  of fan midshaft  150 , which has coked hydrocarbons formed therein. The cleaning solution is then discharged into interior passageway  158 , and a volume of interior passageway  158  is filled with an amount of cleaning solution in the form of an aerated foam. Interior passageway  158  is filled with the amount of cleaning solution for a predetermined residence time that facilitates allowing the cleaning solution to interact with the coked hydrocarbons formed therein, ranging effectively from 30 minutes to 8 hours. The cleaning solution is then drained through first open end  154  and rinsing solution is discharged into interior passageway  158  followed by mechanical removal of additional coking products lifted from the fan mid shaft inner diameter employing an articulating brush comprised of nylon. 
       FIG.  6    is a schematic illustration of an exemplary sealing and discharge assembly  160  in a first operational mode that may be used when delivering fluid to fan midshaft  150 , and  FIG.  7    is a schematic illustration of sealing and discharge assembly  160  in a second operational mode. In the exemplary embodiment, sealing and discharge assembly  160  includes a discharge shaft  162 , an inflatable plug  164 , and a supply line  166  coupled in flow communication with inflatable plug  164 . Discharge shaft  162  includes a first end  168  and a second end  170 . Inflatable plug  164  is coupled to discharge shaft  162  at first end  168 , and a sealing cap  172  is coupled to discharge shaft  162  at second end  170 . 
     Referring to  FIG.  7   , fan midshaft  150  includes first open end  154  and a second open end  174 . When in the first operational mode, inflatable plug  164  is deflated to a size such that sealing and discharge assembly  160  is insertable through first open end  154 , and such that inflatable plug  164  is positionable within interior passageway  158  proximate second open end  174 . Referring to  FIG.  7   , the inflatable plug  164  is then actuated from the first operational mode to the second operational mode, where the inflatable plug  164  seals second open end  174  when in the second operational mode. More specifically, fluid is supplied to inflatable plug  164  via supply line  166  to inflate inflatable plug  164  to a size that facilitates sealing second open end  174 . Second open end  174  is sealed prior to discharging the flow of cleaning solution towards interior passageway  158 . 
     When sealing and discharge assembly  160  is fully inserted within interior passageway  158 , sealing cap  172  couples to fan midshaft  150  with an interference fit to facilitate sealing first open end  154 . Discharge shaft  162  is coupled in flow communication with discharge line  114  (shown in  FIG.  2   ), for example, and includes at least one discharge outlet  176  defined therein. As such, when sealed, interior passageway  158  is provided with cleaning solution discharged from discharge outlet  176  to facilitate removing coked hydrocarbons formed therein. 
     In one embodiment, a volume of interior passageway  158  is filled with an amount of the cleaning solution, and the amount of cleaning solution is held within interior passageway  158  for a predetermined residence time. The predetermined residence time is defined within a range between about 30 minutes and about 8 hours. In some embodiments, the cleaning solution includes a foaming agent, which facilitates filling the volume of interior passageway  158  and enabling the cleaning solution to interact with coked hydrocarbons on the surface of fan midshaft  150  without being directly applied thereto. 
     After the predetermined residence time has elapsed, interior passageway  158  is drained through at least one of first open end  154  and second open end  174 . In some embodiments, the method includes suctioning the cleaning solution from interior passageway  158 . Moreover, in the exemplary embodiment, fan midshaft  150  includes at least one annular member  178  positioned within interior passageway  158 . When draining solution from interior passageway  136 , the solution may pool in a space defined between adjacent annular members  178 . As such, in one embodiment, suctioning solution from interior passageway  158  includes providing a directed suction force to the space defined between adjacent annular members  178  to facilitate removing pooled solution from interior passageway  158 . Fan midshaft  150  is then cleaned mechanically and rinsed, or a second application of cleaning solution is provided. 
       FIGS.  8 - 10    are flow diagrams illustrating exemplary methods of cleaning a component within turbine engine  10 . Referring to  FIG.  8   , a method  200  includes disassembling  202  turbine engine  10  to provide a flow path  137  to interior passageway  136  of component  127  from access point  138  in turbine engine  10 . Component  127  has coked hydrocarbons formed thereon. Method  200  further includes discharging  204  a flow of cleaning solution towards interior passageway  136  from access point  138 . The cleaning solution is configured to remove the coked hydrocarbons from component  127 . 
     Referring to  FIG.  9   , a method  206  includes disassembling  208  turbine engine  10  to provide a flow path to interior passageway  158  of component  127  from access point  156  in turbine engine  10 . Component  127  has coked hydrocarbons formed thereon. Method  206  further includes filling  210  a volume of interior passageway  158  with an amount of cleaning solution, wherein the cleaning solution is configured to remove the coked hydrocarbon from the component, and holding  212  the amount of cleaning solution within interior passageway  158  for a predetermined residence time. 
     Referring to  FIG.  10   , a method  214  includes disassembling  216  turbine engine  10  to define access point  144  to component  127 . Component  127  has coked hydrocarbons formed thereon. Method  214  further includes discharging  218  a flow of cleaning solution towards component  127  from access point  144 . The cleaning solution is configured to remove the coked hydrocarbons from component  127 , and the cleaning solution includes at least one of citric acid or glycolic acid. 
     An exemplary technical effect of the assembly and methods described herein includes at least one of: (a) cleaning internal components of a turbine engine while coupled to an airframe; (b) cleaning internal components of the turbine engine in a quick and efficient manner; and (c) reducing an amount of time for cleaning and returning a cleaned turbine engine to service. 
     Exemplary embodiments of a cleaning system for use with a turbine engine and related components are described above in detail. The system is not limited to the specific embodiments described herein, but rather, components of systems and/or steps of the methods may be utilized independently and separately from other components and/or steps described herein. For example, the configuration of components described herein may also be used in combination with other processes, and is not limited to practice with a fuel nozzles or a fan section of a turbine engine. Rather, the exemplary embodiment can be implemented and utilized in connection with many applications where removing coked hydrocarbons from an object is desired. 
     Although specific features of various embodiments of the present disclosure may be shown in some drawings and not in others, this is for convenience only. In accordance with the principles of embodiments of the present disclosure, any feature of a drawing may be referenced and/or claimed in combination with any feature of any other drawing. 
     This written description uses examples to disclose the embodiments of the present disclosure, including the best mode, and also to enable any person skilled in the art to practice embodiments of the present disclosure, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the embodiments described herein is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal languages of the claims.