Solenoid valve to reduce gear box wear in gas turbine engine wash events

Abstract

A system for preventing wear during a wash event of a gas turbine engine is provided. The system includes an accessory gear box, a drive gear box drivingly and fluidly coupled to the accessory gear box, and a lubrication system fluidly coupled to the accessory gear box and the drive gear box. The lubrication system includes a lubricant reservoir fluidly connected to the drive gear box and the accessory gear box. The lubrication system further includes a solenoid valve in fluid communication with the lubricant reservoir. The solenoid valve is selectively actuatable between an open position and a closed position when current is provided from a power source, the open position allowing the flow of lubricant from the lubricant reservoir to the accessory gear box and the drive gear box, the closed position preventing the flow of lubricant from the lubricant reservoir to the accessory gear box and the drive gear box.

Description

Cross-reference to related applications

[0001] This application claims priority to Indian Provisional Application No. 202411098634, filed December 13, 2024, and U.S. Utility Application No. 19 / 211,419, filed May 19, 2025, the entire contents of which are incorporated herein by reference. Technical Field

[0002] This disclosure relates to systems and methods for preventing wear in one or more gearboxes of a gas turbine engine during a cleaning event by introducing lubricant using a solenoid valve. Background Technology

[0003] A typical aircraft propulsion system comprises one or more gas turbine engines. For some propulsion systems, the gas turbine engine typically includes a fan and a core arranged in fluid communication with each other. Furthermore, the core of a typical gas turbine engine generally comprises, in series flow sequence, a compressor section, a combustor section, a turbine section, and an exhaust section. In operation, air is supplied from the fan to the inlet of the compressor section, where one or more axial compressors progressively compress the air until it reaches the combustor section. Fuel is mixed with the compressed air and burned within the combustor section to provide combustion gases. These combustion gases are then directed from the combustor section to the turbine section. The flow of combustion gases through the turbine section drives the turbine section and is then directed through the exhaust section, for example, discharged into the atmosphere.

[0004] During operation, this type of gas turbine engine draws in a large amount of air. However, this air may contain foreign particles. Most of these foreign particles will travel along the gas path through the engine and be expelled with the exhaust. However, at least some of these particles may adhere to certain components within the gas path of the gas turbine engine, potentially altering the engine's aerodynamic characteristics and reducing its performance.

[0005] To remove these foreign particles from the gas path of a gas turbine engine, a cleaning operation can be performed by directing water or other fluids toward the engine inlet while simultaneously using, for example, an electric starter to rotate the core engine. However, this cleaning operation is often not tailored to the specific type of cleaning actually required for a particular part of the engine. For example, depending on the previous operating conditions of the gas turbine engine, a quick and simple water wash may be necessary. In other cases, a longer cleaning cycle using cleaning foam with specific foam properties may be required to properly clean the engine and restore it to peak efficiency.

[0006] In all the engine cleaning scenarios described above, the engine is offline during the cleaning process. Therefore, lubricant does not circulate through the individual gearboxes of the gas turbine engine. This can lead to excessive gear scuffing and wear. Therefore, improved lubrication systems and methods for reducing or preventing wear during the cleaning of gas turbine engines are needed and will be beneficial in the art. Attached Figure Description

[0007] The complete and feasible disclosure of this disclosure, including its best mode, is set forth in the specification with reference to the accompanying drawings, for those skilled in the art, wherein:

[0008] Figure 1 A cross-sectional view of a gas turbine engine according to an exemplary aspect of this disclosure is shown.

[0009] Figure 2 This is a schematic diagram of a system for reducing or preventing wear during a cleaning cycle of a gas turbine engine, according to embodiments of the present disclosure.

[0010] Figure 3A and Figure 3B Cross-sectional views of an integrated check solenoid valve according to an embodiment of the present disclosure are shown in two different locations.

[0011] Figure 4A , Figure 4B and Figure 4C Cross-sectional views of an integrated check solenoid valve according to an embodiment of the present disclosure are shown in three different locations.

[0012] Figure 5 This is a flowchart of a method for reducing or preventing wear during a cleaning event of a gas turbine engine utilizing a cleaning system, according to embodiments of the present disclosure.

[0013] Figure 6 Block diagrams of computing systems for implementing one or more aspects of the present disclosure are provided according to exemplary embodiments of the present disclosure. Detailed Implementation

[0014] Reference will now be made in detail to the present embodiments of this disclosure, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerals and letter reference numerals to denote features in the drawings. Similar or analogous reference numerals in the drawings and description have been used to denote similar or analogous portions of this disclosure.

[0015] The term "exemplary" is used herein to mean "serving as an example, instance, or illustration." Any implementation described herein as "exemplary" is not necessarily to be construed as superior or better than other implementations. Furthermore, unless explicitly stated otherwise, all embodiments described herein should be considered exemplary.

[0016] Unless the context clearly indicates otherwise, the singular forms “a,” “a,” and “the” include plural references.

[0017] In a context such as “at least one of A, B and C”, the term “at least one” means only A, only B, only C, or any combination of A, B and C.

[0018] As used herein, the term “pipeline” can refer to fluid transport components, such as pipes, tubes, hoses or other fluid transport and / or load-bearing conduits.

[0019] This disclosure generally relates to systems and methods for reducing or preventing wear in one or more gearboxes of a gas turbine engine during a cleaning event by utilizing solenoid valves. During cleaning of the gas turbine engine, the shaft or spool of the gas turbine engine can be rotated at a low speed (e.g., 50-150 RPM for several hours) by connecting an electric motor (e.g., a starter motor) to the accessory gearbox and / or drive gearbox, while forcing cleaning fluid through the gas turbine engine (e.g., through rotor blades, stator blades, and various other components). In other embodiments, instead of an electric motor, a hybrid / electric starter, such as a hybrid pneumatic-electric starter, or a hydraulic press, can be connected to the accessory gearbox. Because the engine is offline during cleaning, lubricant does not circulate through the accessory gearbox and drive gearbox as it does during normal operation of the gas turbine engine, which can lead to gear scuffing and / or wear during engine cleaning. For example, during normal operation, one or more supply pumps and one or more return pumps driven to the accessory gearbox (and / or drive gearbox) can circulate lubricant throughout the lubrication system fluidly connected to the gearbox. However, during a cleaning event, the supply and / or return pumps may operate at slower speeds than in conventional operation, so that lubricant does not circulate to the accessory gearbox and / or drive gearbox at the same rate or amount as during normal operation. That is, because the gearbox is driven at lower speeds (potentially for several hours) during a cleaning event, driving the gas turbine shaft at low speed, and thus the supply / return pumps at low speed, wear or gear scuffing may occur in the gearbox due to insufficient lubricant supply. Those skilled in the art will understand that while the term "cleaning" is generally used to describe wetting processes involving liquid or foam cleaning media, in the context of this invention, it is intended to encompass all cleaning processes that require rotation of the gas turbine engine during the cleaning process, including but not limited to water washing, foam cleaning, abrasive media cleaning, dry ice (carbon dioxide) blasting, cleaning with refrigerant liquid media exhibiting a phase change during cleaning, laser ablation cleaning, etc.

[0020] An improved system and method reduces or prevents gear scuffing and / or wear within accessory gearboxes and drive gearboxes by introducing or supplying additional lubricant to the lubrication system via an actuable solenoid valve during cleaning. For example, once the cleaning system is connected and cleaning of the gas turbine engine begins, current can be applied to the solenoid valve to actuate it to the open position, allowing lubricant to flow from a lubricant reservoir to the individual gearboxes during cleaning. In some embodiments, the current can be supplied directly from the cleaning system. In other embodiments, the cleaning system can signal to the engine controller that cleaning has begun, and the engine controller can instruct the power source associated with the gas turbine engine to supply current to the solenoid valve. The solenoid valve allows for the supply of additional lubricant to the gearboxes during gas turbine engine cleaning, which advantageously prevents wear and / or scuffing of gears and other components in the gearboxes during the cleaning event. The improved lubrication system advantageously reduces equipment costs because it allows the onboard lubrication system of the gas turbine engine to be used for lubricating the gearboxes during the cleaning event, eliminating the need for any additional lubrication system (e.g., the lubrication system on the cleaning system or on the vehicle or other external oil drilling rig system). The system also extends the life of the gearbox by reducing or preventing wear during cleaning events, which can last for several hours.

[0021] Referring now to the accompanying drawings, where the same number indicates the same element throughout the drawings, Figure 1 This is a schematic cross-sectional view of a gas turbine engine according to an exemplary embodiment of the present disclosure. More specifically, for Figure 1 In one embodiment, the gas turbine engine is a high-bypass turbofan jet engine, sometimes also referred to as a "turbofan engine." For example... Figure 1 As shown, the gas turbine engine 10 defines an axial direction A (extending parallel to the longitudinal centerline 12 provided for reference), a radial direction R, and a circumferential direction C extending about the longitudinal centerline 12. Generally, the gas turbine engine 10 includes a fan section 14 and a turbine 16 disposed downstream of the fan section 14.

[0022] The depicted exemplary turbine 16 generally comprises a basic tubular housing 18 defining an annular inlet 20. The housing 18 surrounds, in a series flow relationship: a compressor section comprising a supercharger or low-pressure (LP) compressor 22 and a high-pressure (HP) compressor 24; a combustion section 26; a turbine section comprising a high-pressure (HP) turbine 28 and a low-pressure (LP) turbine 30; and an exhaust nozzle section 32. The compressor section, combustion section 26, and turbine section together at least partially define the core airflow path of the turbofan engine 10. A high-pressure (HP) shaft or spool 34 drives the HP turbine 28 to the HP compressor 24. A low-pressure (LP) shaft or spool 36 drives the LP turbine 30 to the LP compressor 22.

[0023] In the depicted embodiment, fan section 14 includes a fan 38 having a plurality of fan blades 40 spaced apart and coupled to disk 42. As depicted, the fan blades 40 extend generally radially outward from disk 42. Each fan blade 40 is operably coupled to a suitable pitch mechanism, which is configured to, for example, uniformly and collectively change the pitch of the fan blades 40, by means of a pitch mechanism, allowing rotation about a pitch axis relative to disk 42. Disk 42 is covered by a rotatable front hub 48 (sometimes referred to as a “rotator”) of fan section 14. The front hub 48 is aerodynamically shaped to facilitate airflow through the plurality of fan blades 40. The fan blades 40 and disk 42 can rotate together about longitudinal centerline 12 via LP shaft 36.

[0024] Still referencing Figure 1 In an exemplary embodiment, the exemplary fan section 14 includes an annular fan housing or outer nacelle 50 circumferentially surrounding at least a portion of the fan 38 and / or turbine 16. The nacelle 50 is supported relative to the turbine 16 by a plurality of circumferentially spaced outlet guide blades 52. Additionally, a downstream section 54 of the nacelle 50 extends above the outer portion of the turbine 16 to define a bypass airflow passage 56 therebetween.

[0025] During operation of the turbofan engine 10, a certain amount of air 58 enters the gas turbine engine 10 through the nacelle 50 and / or the relevant inlet 60 of the fan section 14. As the certain amount of air 58 passes through the fan blades 40, a first portion of the air 58, as indicated by arrow 62, is directed or directed into the bypass airflow passage 56, and a second portion of the air 58, as indicated by arrow 64, is directed or directed into the LP compressor 22. The ratio between the first portion of air 62 and the second portion of air 64 is commonly referred to as the bypass ratio. Then, as the second portion of air 64 is directed through the high-pressure (HP) compressor 24 and into the combustion section 26, the pressure of the second portion of air 64 increases, and in the combustion section 26, the second portion of air 64 mixes with fuel and burns to provide combustion gases 66.

[0026] Combustion gas 66 is directed through HP turbine 28, where a portion of the thermal and / or kinetic energy from the combustion gas 66 is extracted via a series of stages of HP turbine stator blades 68 connected to housing 18 and HP turbine rotor blades 70 connected to HP shaft or spool 34, thus causing HP shaft or spool 34 to rotate and support the operation of HP compressor 24. Combustion gas 66 is then directed through LP turbine 30, where a second portion of thermal and kinetic energy is extracted from the combustion gas 66 via a series of stages of LP turbine stator blades 72 connected to housing 18 and LP turbine rotor blades 74 connected to LP shaft or spool 36, thus causing LP shaft or spool 36 to rotate and support the operation of LP compressor 22 and / or fan 38.

[0027] Combustion gas 66 is then directed through the injection exhaust nozzle section 32 of turbine 16 to provide propulsive thrust. Simultaneously, the pressure of the first portion of air 62 increases significantly as it is directed through the bypass airflow passage 56 before exiting from the fan nozzle exhaust section 76 of gas turbine engine 10, also providing propulsive thrust. HP turbine 28, LP turbine 30, and injection exhaust nozzle section 32 at least partially define a hot gas path 78 for directing combustion gas 66 through turbine 16.

[0028] However, it should be understood that Figure 1 The exemplary turbofan engine 10 depicted is merely an example, and in other exemplary embodiments, the turbofan engine 10 may have any other suitable configuration. For example, in other exemplary embodiments, the turbofan engine 10 may be configured as a geared turbofan engine (i.e., including a reduction gearbox); may not include variable pitch fan blades; may include any other suitable number of spools, compressors, or turbines; and so on. Furthermore, the turbofan engine 10 may be modified to be configured as any other suitable aero gas turbine engine, such as a turboshaft engine, turboprop engine, turbojet engine, etc. Additionally, the turbofan engine 10 may also be modified to be configured as an aero-derivative gas turbine engine (e.g., for marine applications), an industrial gas turbine engine, or any other suitable gas turbine engine.

[0029] As depicted, the exemplary turbofan engine 10 also includes an accessory gearbox 45, which is attached to and mechanically coupled to a spool of the gas turbine engine. The accessory gearbox 45 may be mounted external to the flow path of the gas turbine engine 10, for example, coupled to the housing of the HP compressor 24, or coupled to the nacelle 50 or any other stationary structure of the gas turbine engine 10. During at least some operations, the accessory gearbox may power one or more suitable accessory systems of the gas turbine engine 10.

[0030] More specifically, the accessory gearbox 45 can be attached to the turbine 16 of the turbofan engine 10 and mechanically coupled to the LP spool 36 of the turbofan engine 10 via a drive gearbox 46 and a drive shaft 47. The drive shaft 47 can extend through the outlet guide vane 52. The drive shaft 47 can be drivenly coupled to the LP spool 36 and the drive gearbox 46 such that the LP spool 36 can rotate together with the drive shaft 47 (e.g., the drive gearbox 46 and the drive shaft 47 allow the LP spool 36 to rotate). A motor 84 (i.e., a starter motor / generator) can be coupled to the accessory gearbox 45 for, for example, starting the turbofan engine 10 and / or generating electricity while the turbofan engine 10 is running.

[0031] In an exemplary embodiment, the gas turbine engine 10 may include a lubrication system 100 fluidly connected to an accessory gearbox 45 and a drive gearbox 46. The lubrication system 100 may supply lubricant (e.g., oil) to the accessory gearbox 45 and the drive gearbox 46 during operation of the gas turbine engine 10. In this way, the accessory gearbox 45 is driven and fluidly coupled to the drive gearbox 46. The accessory gearbox 45 and the drive gearbox 46 may be fluidly connected to the lubrication system 100.

[0032] Furthermore, it is understandable that, Figure 1 After prolonged use, deposits, foreign particles, and other sediments may adhere to or form on certain components within the core airflow path 37 of the turbofan engine 10. Therefore, it may be beneficial to clean the turbofan engine 10 at regular intervals to remove these deposits, foreign particles, and other sediments. Thus, when the gas turbine engine 10 is shut down, a cleaning system 80 can be used and configured to clean, rinse, or otherwise clean the gas turbine engine 10. The cleaning system 80 may be at least partially housed on or within a modular and mobile cleaning vehicle, providing mobility and facilitating quick and easy cleaning of the gas turbine engine 10. The cleaning system 80 may include one or more cleaning lines 82 that can discharge cleaning fluid to one or more sections and / or one or more components of the gas turbine engine 10 (e.g., fan blades 40 as shown). For example, as Figure 1As shown, at least one cleaning line 82 can supply cleaning fluid to the fan blades 40; at least one cleaning line 82 can supply cleaning fluid to the annular inlet 20 of the core flow path 37; at least one cleaning line 82 can supply cleaning fluid to (e.g., directly to) the HP compressor 24 (e.g., via one or more endoscope ports); and at least one cleaning line 82 can supply cleaning fluid to (e.g., directly to) the combustion section 26 (e.g., via one or more endoscope ports).

[0033] For all the various components of the gas turbine engine 10 to be cleaned by the cleaning system 80 during shutdown, the gas turbine engine 10 can be rotated by an electric motor 84 while the cleaning line 82 pumps cleaning fluid (e.g., heated detergent) into the engine. The electric motor 84 can be driven and coupled to an accessory gearbox 45 to rotate the gas turbine engine 10 as needed during cleaning. The electric motor 84 can be able to drive the accessory gearbox 45, the drive gearbox 46, the drive shaft 47, the LP spool 36, and / or the HP spool 34. For example, the drive shaft 86 of the electric motor 84 can be coupled to the accessory gearbox 45.

[0034] In other embodiments, instead of an electric motor, a hybrid / electric motor, such as a hybrid pneumatic-electric starter, or a hydraulic press, can be coupled to an accessory gearbox. In other embodiments, during a cleaning event, the gas turbine engine 10 can rotate without the use of an electric motor. For example, a blower or suction pump can be used to drive the gas turbine engine 10. As a result, gearboxes 45, 46 can also be driven.

[0035] As will be understood, because the gas turbine engine is offline during cleaning (e.g., foam cleaning), the lubrication system 100 may not actively circulate lubrication to the accessory gearbox 45 and drive gearbox 46 as it would during conventional operation. For example, during normal operation, one or more supply pumps and one or more return pumps driven by the accessory gearbox 45 (and / or drive gearbox 46) may be fluidly connected to the gearboxes 45, 46 throughout (e.g., ...). Figure 1The lubricant circulates in the lubrication system 100 (as indicated by the arrow in the diagram). However, during a cleaning event, the supply pump and / or return pump may operate at a slower speed than in conventional operation, causing the lubricant to not circulate to the accessory gearbox 45 and / or drive gearbox 46 at the same rate or in the same amount as during normal operation. That is, since the gearboxes are driven at a lower speed (potentially for several hours) during a cleaning event, driving the shaft of the gas turbine engine 10 at a low speed, and thus driving the oil supply / return pumps at a low speed, wear or gear scuffing may occur in the gearboxes due to insufficient lubricant supply. However, since the accessory gearbox 45 and drive gearbox 46 are driven by the motor 84 to rotate the gas turbine engine during cleaning, this may cause gear scuffing and wear on various components (e.g., gears, bevel gears, etc.) in the accessory gearbox 45 and / or drive gearbox 46.

[0036] In an exemplary embodiment, as discussed in more detail below, the lubrication system 100 may include a solenoid valve 140 in fluid communication with the lubrication system 100. The solenoid valve 140 is selectively actuated between an open position and a closed position when current 101 is received (or applied) from a power source; the open position allows lubricant 104 to flow to the accessory gearbox 45 and the drive gearbox 46, and the closed position prevents lubricant 104 from flowing to the accessory gearbox 45 and the drive gearbox 46. In an exemplary embodiment, the solenoid valve 140 may be an integrated check solenoid valve (e.g., referred to below). Figure 3A , 3B The integrated check solenoid valve 300 or 400 described in 4A, 4B and 4C. The integrated check solenoid valve can be a mechanically loaded check valve that prevents backflow from the lubrication reservoir 102 ( Figure 2 The lubricant 104 is discharged into the lubrication and return system 110. Figure 2 (When the gas turbine engine is not operating), accessory gearbox 45 and / or drive gearbox 46. Additionally, the integrated check solenoid valve may include a solenoid that allows the integrated check solenoid valve to be actuated to the open position during a cleaning event.

[0037] In some embodiments, the gas turbine engine 10 may include an engine power supply 91 and an engine controller 90. Similarly, the cleaning system 80 may include a cleaning system power supply 88 and a cleaning controller 96. The engine power supply 91 may be a battery, a capacitor (e.g., a supercapacitor for energy storage), or another energy storage device. The engine power supply 88 may be electrically connected to one or more electrical systems of the gas turbine engine 10, such as an electric motor 84 (e.g., a starter motor / generator) or other electrical systems. In some embodiments, the cleaning system power supply 88 may be a battery or other energy storage device on the cleaning system 80 (e.g., on a mobile cleaning vehicle).

[0038] The cleaning controller 96 and the engine controller 90 are operatively communicable to each other, enabling the transmission and reception of communication signals between the controllers 90 and 96. For example, the cleaning controller 96 may signal to the engine controller 90 that a cleaning event has commenced, and the engine controller 90 may, in response, rotate one or more shafts of the gas turbine engine 10 using the motor 84. In an exemplary embodiment, the engine power supply 91, the engine controller 90, the motor 84, the cleaning controller 96, and the cleaning power supply 88 are operatively communicable to each other. For example, any one or both of the controllers 90 and 96 may be configured to regulate the operation of the cleaning power supply 88 (e.g., supplying current 101 to the solenoid valve 140), the engine power supply 91 (e.g., supplying current 101 to the solenoid valve 140), and / or the motor 84 (e.g., rotating one or more shafts of the gas turbine engine 10 during a cleaning event).

[0039] For example, the cleaning system power supply 88 can be selectively electrically connected to the solenoid valve 140 to provide current 101 during a cleaning event. For instance, during a cleaning event in which the gas turbine engine 10 is started using the cleaning system 80, the cleaning power supply 88 can be connected to the solenoid valve 140 and can supply current 101 to it, thereby actuating the solenoid valve 140 to the open position and allowing lubricant 104 to flow into the accessory gearbox 45 and the drive gearbox 46. After the cleaning event is completed, the cleaning power supply 88 can be disconnected from the solenoid valve 140, thereby actuating the solenoid valve 140 to the closed position and preventing lubricant 104 from flowing into the accessory gearbox 45 and the drive gearbox 46.

[0040] Alternatively or additionally, one or both of the controllers 90 and 96 may signal one of the power sources (e.g., cleaning power source 88 and / or engine power source 91) to provide current 101 during a cleaning event. For example, during a cleaning event when the gas turbine engine 10 is started using the cleaning system 80, the engine controller 90 (and / or the cleaning controller 96) may instruct the cleaning power source 88 and / or the engine power source 91 to supply current 101 to the solenoid valve 140, thereby actuating the solenoid valve 140 to the open position and allowing lubricant 104 to flow into the accessory gearbox 45 and the drive gearbox 46. Upon completion of the cleaning event, the engine controller 90 (and / or the cleaning controller 96) may instruct the cleaning power source 88 and / or the engine power source 91 to stop supplying current 101 to the solenoid valve 140, thereby actuating the solenoid valve 140 to the closed position and preventing lubricant 104 from flowing into the accessory gearbox 45 and the drive gearbox 46.

[0041] Now for reference Figure 2A schematic diagram of a system 200 for reducing or preventing wear during a cleaning cycle of a gas turbine engine is provided. The system includes a lubrication system 100 that supplies lubricant 104 to an accessory gearbox 45 and / or a drive gearbox 46 during the cleaning of the gas turbine engine. The lubrication system 100 advantageously provides an improved configuration that, during the cleaning of the gas turbine engine (e.g., via the reference above...) Figure 1 The cleaning system 80 provides and / or circulates sufficient lubricant to the accessory gearbox 45 and / or the drive gearbox 46, thereby reducing or preventing scratches and / or wear on the accessory gearbox 45 and / or the drive gearbox 46.

[0042] As shown in the figure, system 200 includes an accessory gearbox 45 and a transmission gearbox 46, the transmission gearbox 46 being drivably connected to the accessory gearbox 45. For example, the transmission gearbox 46 can be drivably connected to the accessory gearbox 45 (as referenced above). Figure 1 (As shown and described). The lubrication system 100 is fluidly coupled to both the accessory gearbox 45 and the drive gearbox 46 to provide lubricant to the accessory gearbox 45 and the drive gearbox 46 during operation of the gas turbine engine and / or during a cleaning event of the gas turbine engine.

[0043] The lubrication system 100 may include a lubricant reservoir 102, which may be a tank or container, that holds and supplies lubricant 104 (e.g., oil) for circulation through the lubrication system 100, accessory gearbox 45, and drive gearbox 46. Furthermore, the lubrication system 100 includes a supply circuit 106 and a return circuit 108, each circuit including one or more fluid-carrying conduits that supply and return lubricant 104 to various components within the lubrication system 100, accessory gearbox 45, and drive gearbox 46. Specifically, the supply circuit 106 can supply and provide lubricant 104 from the lubricant reservoir 102 to the accessory gearbox 45 and drive gearbox 46. The return circuit 108 can return lubricant 104 from the accessory gearbox 45 and drive gearbox 46 to the lubricant reservoir 102.

[0044] In many embodiments, the lubrication system 100 may include a lubrication and return system 110 fluidly connected to a supply circuit 106 and a return circuit 108. The lubrication and return system 110 may include a pump shaft 112 drivenly connected to an accessory gearbox 45, such that rotation of the pump shaft 112 causes rotation of components (e.g., gears and / or accessories) connected to the accessory gearbox 45, thereby also causing rotation of components of the drive gearbox 46 via a drive shaft 47, and further causing rotation of one or more shafts of the gas turbine engine (as referenced above). Figure 1 As shown and described, it is connected to the transmission gearbox 46) for rotation.

[0045] The lubrication and return system 110 may further include a supply pump 114 and one or more return pumps 116. The supply pump 114 is fluidly coupled to the supply circuit 106 and drivably coupled to the pump shaft 112. The supply pump 114 can cause lubricant 104 to circulate through the lubrication system 100 (specifically, through the supply circuit 106). One or more return pumps 116 may each be fluidly coupled to the return circuit 108 and drivably coupled to the pump shaft 112. The one or more return pumps 116 can cause lubricant 104 to circulate through the lubrication system 100 (specifically, through the return circuit 108). The pump shaft 112 can drivably connect both the supply pump 114 and the one or more return pumps 116.

[0046] In various embodiments, the lubrication system 100 may further include a reservoir system 118 having one or more reservoirs 120A, 120B, 120C, which are fluidly connected to at least one of the supply circuit 106 and the return circuit 108. In a non-limiting example, the reservoir system 118 may be a bearing reservoir region for lubricating engine bearings. A first reservoir 120A, a second reservoir 120B, and a third reservoir 120C may be included in the reservoir system 118. Each reservoir 120A, 120B, 120C may be supplied from a gas turbine engine (as referenced above). Figure 1 The gas turbine engine 10) has one or more engine bearings that collect used lubricant 104 (e.g., used oil) in reservoirs or containers. In other words, each reservoir 120A, 120B, 120C may be fluidly connected to the engine bearings of the gas turbine engine. Although three reservoirs are shown, any number of reservoirs can be considered. In one example, a valve may control the supply of lubricant 104 to any one of the reservoirs.

[0047] The return circuit 108 may include one or more return lines 122, 124, 126, 128, 130 extending to the lubrication and return system 110, and a main return line extending from the lubrication and return system 110 to the lubrication reservoir 102. Specifically, a first reservoir return line 122 may extend from a first reservoir 120A to the lubrication and return system 110 (e.g., to one or more return pumps 116 extending to the lubrication and return system 110) to supply used lubricant from the first reservoir 120A to the lubrication and return system 110. A second reservoir return line 124 may extend from a second reservoir 120B to the lubrication and return system 110 (e.g., to one or more return pumps 116 extending to the lubrication and return system 110) to supply used lubricant from the second reservoir 120B to the lubrication and return system 110. The third reservoir return line 126 can extend from the third reservoir 120C to the lubrication and return system 110 (e.g., to one or more return pumps 116 extending to the lubrication and return system 110) to supply used lubricant from the third reservoir 120C to the lubrication and return system 110.

[0048] Furthermore, the accessory gearbox return line 128 can extend from the accessory gearbox 45 to the lubrication and return system 110 (e.g., to one or more return pumps 116 extending to the lubrication and return system 110) to supply used lubricant from the accessory gearbox 45 to the lubrication and return system 110. Similarly, the drive gearbox return line 130 can extend from the drive gearbox 46 to the lubrication and return system 110 (e.g., to one or more return pumps 116 extending to the lubrication and return system 110) to supply used lubricant from the drive gearbox 46 to the lubrication and return system 110.

[0049] In various embodiments, inlet filter 132 may be fluidly connected to each of one or more return lines 122, 124, 126, 128, 130, immediately upstream of one or more return pumps 116. Inlet filter 132 may filter used lubricant within each of the one or more return lines 122, 124, 126, 128, 130 before the lubricant enters the one or more return pumps 116. For example, inlet filter 132 may remove contaminants and / or particles from the used lubricant flowing through the one or more return lines 122, 124, 126, 128, 130 that could otherwise damage components of system 100.

[0050] In an exemplary embodiment, the lubrication and return system 110 may include a return manifold 134 fluidly connected to and extending from one or more return pumps 116. The return manifold 134 may collect all lubricant from each of the one or more return pumps 116. The return loop 108 may also include a main return line 136 extending from the lubrication and return system 110 to an oil reservoir 102. Specifically, the main return line 136 may extend from the return manifold 134 to the lubricant reservoir 102 (e.g., to the top of the lubricant reservoir).

[0051] Supply circuit 106 can supply clean (e.g., filtered) lubricant to lubrication and return system 110, accessory gearbox 45, and drive gearbox 46. Supply circuit 106 may include inlet supply line 138 fluidly connecting lubrication reservoir 102 and lubrication and return system 110. Specifically, the inlet supply line can extend from lubrication reservoir 102 to lubrication and return system 110. Specifically, the inlet supply line can extend from lubrication reservoir 102 to supply pump 114 of lubrication and return system 110.

[0052] The supply circuit 106 may also include an outlet supply line 142 extending from the lubrication and return system 110 to the accessory gearbox 45 and the drive gearbox 46. Specifically, the outlet supply line 142 may extend from the supply pump 114 to the accessory gearbox 45 and the drive gearbox 46.

[0053] In many embodiments, system 100 may further include one or more heat exchangers 144, 146, 148 thermally connected to outlet supply line 142. Specifically, one or more heat exchangers may include a servo heat exchanger 144, a fuel heat exchanger 146, and an air heat exchanger 148. During normal operation of the gas turbine engine, the servo heat exchanger 144 may provide lubricant 104 within the outlet supply line 142 and interact with system 100 and / or the gas turbine engine (as referenced above). Figure 1 The gas turbine engine 10) is associated with one or more servo motors that transfer heat between them. Furthermore, during normal operation of the gas turbine engine, the fuel heat exchanger 146 can transfer heat between the lubricant 104 within the outlet supply line 142 and, for example, from the gas turbine engine (as described above). Figure 1 The combustion section of the gas turbine engine 10) is connected to the fuel supply system that supplies fuel to the gas turbine engine, which transfers heat between them. Furthermore, during normal operation of the gas turbine engine, the air heat exchanger 148 can transfer heat between the lubricant 104 in the outlet supply line 142 and the air supplied to the gas turbine engine (e.g., from the gas turbine engine, as described above). Figure 1Heat is transferred between the air in the fan section and / or compressor section of the gas turbine engine 10.

[0054] In some embodiments, a supply-side filter 150 may be fluidly connected to an outlet supply line 142. The supply-side filter 150 may be located immediately downstream of the supply pump 114. The supply-side filter 150 may remove contaminants and / or particles from lubricant supplied via the outlet supply line to the accessory gearbox 45 and / or the drive gearbox 46. As shown, a filter bypass line may be included on the outlet supply line 142, allowing selective bypassing of the supply-side filter.

[0055] The lubrication system 100 may further include an exhaust circuit for discharging gases (e.g., air and / or other gases) from the lubrication system 100 (e.g., venting them to the atmosphere). The exhaust circuit may include an accessory conduit 158 ​​extending from an accessory gearbox 45 to a drive gearbox 46 for discharging excess gas from the accessory gearbox 45. A drive conduit 160 extends from the drive gearbox to a reservoir system 118 (e.g., to a first reservoir 120A within the reservoir system 118) for discharging or removing excess gas from the drive gearbox 46. A reservoir discharge section 162 extends from the lubrication reservoir 102 to the first reservoir 120A for discharging or removing excess gas from the lubrication reservoir 102. An overflow conduit 164 extends from a second reservoir 120B to the first reservoir 120A for discharging excess gas from the second reservoir 120B to the first reservoir 120A. The main duct 166 extends from the first reservoir 120A, through the second reservoir 120B and the third reservoir 120C, to an outlet for venting gas (e.g., to the atmosphere). The main duct 166 may be located on the LP shaft of the gas turbine engine (e.g., as referenced above). Figure 1 Within the LP axis 36.

[0056] In many embodiments, the outlet supply line 142 may include a first branch 152 extending to the accessory gearbox 45 and a second branch 154 extending to the drive gearbox 46. Furthermore, the outlet supply line 142 may include an overflow branch 156 connected to each of the reservoirs 120A, 120B, 120C in the reservoir system 118 to prevent overcharging of the lubricant in the accessory gearbox 45 and / or the drive gearbox 46. The overflow branch 156 may extend from the second branch 154 to each of the reservoirs 120A, 120B, 120C.

[0057] In the exemplary embodiment, reference is still made to Figure 2 System 200 may also include a cleaning system 80, which can be used and constructed for cleaning, rinsing or otherwise purifying a gas turbine engine (as described in the above reference). Figure 1 (The gas turbine engine is mentioned). The cleaning system 80 can be at least partially housed on or within a modular and mobile cleaning vehicle, which provides mobility for the cleaning system 80 and facilitates quick and easy cleaning of the gas turbine engine. The cleaning system 80 may include one or more cleaning lines that can discharge cleaning fluid to one or more components of the gas turbine engine during downtime.

[0058] As will be understood, since the gas turbine engine is offline during cleaning (e.g., foam cleaning), the lubrication system 100 may not actively circulate lubrication from the lubrication reservoir 102 to the accessory gearbox 45 and the drive gearbox 46 as in conventional operation. However, since the accessory gearbox 45 and the drive gearbox 46 are driven (e.g., by an electric motor or by other means such as an electric starter, hybrid / electric starter, or hybrid pneumatic / electric starter) to rotate the gas turbine engine during cleaning, this may result in gear scuffing and wear of various components (e.g., gears, bevel gears, etc.) in the accessory gearbox 45 and / or the drive gearbox 46.

[0059] In an exemplary embodiment, the lubrication system 100 may include a solenoid valve 140 in fluid communication with a lubrication reservoir 102 of the lubrication system 100. When current 101 is supplied from a power source ( Figure 1 When the lubricant 104 is in the open position, the solenoid valve 140 can be selectively actuated between the open position and the closed position. The open position allows lubricant 104 to flow from the lubricant reservoir 102 to the accessory gearbox 45 and the drive gearbox 46, while the closed position prevents lubricant 104 from flowing from the lubricant reservoir 102 to the accessory gearbox 45 and the drive gearbox 46.

[0060] In many embodiments, as shown, a solenoid valve 140 may be fluidly connected to the supply circuit 106. Specifically, the solenoid valve 140 may be fluidly connected to the inlet supply line 138 of the supply circuit 106 between the lubrication reservoir 102 and the lubrication and return system 110. All lubricant 104 from the lubrication reservoir may flow through the inlet supply line 138 and the solenoid valve 140 (when in the open position). In some embodiments, the solenoid valve 140 may be integrated with the lubrication and return system 110, for example, connected to or integrated into the housing of the lubrication and return system 110.

[0061] In many embodiments, system 200 may include engine power supply 91 and engine controller 90, which may be connected to a gas turbine engine (such as those referenced above). Figure 1This is associated with the gas turbine engine 10. Similarly, the cleaning system 80 may include a cleaning system power supply 88 and a cleaning controller 96. The engine power supply 91 may be a battery, a capacitor (e.g., a supercapacitor for energy storage), or another energy storage device. The engine power supply 88 may be electrically connected to one or more electrical systems of the gas turbine engine 10, such as an electric motor 84 (e.g., a starter motor / generator) or other electrical systems. In some embodiments, the cleaning system power supply 88 may be a battery or other energy storage device on the cleaning system 80 (e.g., on a mobile cleaning vehicle). In some embodiments, current 101 may be received from the cleaning power supply 88 by a solenoid valve 140. In other embodiments, current 101 may be received from the engine power supply 91 by a solenoid valve 140.

[0062] In an exemplary embodiment, a cleaning system 80 can be used to perform cleaning events for a gas turbine engine. As described below, both the cleaning controller 96 and the engine controller 90 may include a memory and one or more processors. The memory stores instructions that, when executed by the one or more processors, cause the system 200 to operate. Operation may include receiving a signal indicating that a cleaning event has begun (e.g., from the cleaning controller 96) using the engine controller. In response, the engine controller 90 and / or the cleaning controller 96 may supply current 101 from one of the cleaning power supply 88 and / or the engine power supply 91 to actuate the solenoid valve 140 to an open position, which allows lubricant 104 to flow from the lubrication reservoir 102 to the accessory gearbox 45 and the drive gearbox 46.

[0063] In many embodiments, system 200 may also include a flow meter 180 (or flow sensor) in fluid communication with lubrication system 100. In some embodiments, flow meter 180 may be fluidly disposed on supply circuit 106. Specifically, flow meter 180 may be fluidly disposed on inlet supply line 138 of supply circuit 106 between lubrication reservoir 102 and solenoid valve 140. All lubricant 104 from lubrication reservoir 102 may flow through flow meter 180. Flow meter 180 may measure and monitor the amount of fluid (e.g., lubricant) passing through inlet supply line 138 and solenoid valve 140, thereby monitoring the amount of lubricant supplied to accessory gearbox 45 and drive gearbox 46. Flow meter 180 may be monitored by controllers 90, 96 to prevent overfilling of lubricant into accessory gearbox 45 and drive gearbox 46 during gas turbine engine cleaning events. For example, flow meter 180 can be operatively communicated with controllers 90, 96, such that controllers 90, 96 can receive data from flow meter 180 indicating the amount of lubricant 104 supplied to accessory gearbox 45 and drive gearbox 46.

[0064] In many embodiments, controllers 90, 96 can determine, based on data indicating the amount of lubricant supplied, that the amount of lubricant supplied to the accessory gearbox and drive gearbox has exceeded a predetermined threshold. The predetermined threshold may be the lubricant limit of accessory gearbox 45 and / or drive gearbox 46 (e.g., the maximum amount of lubricant that accessory gearbox 45 and / or drive gearbox 46 can maintain without overcharging). In some embodiments, the predetermined threshold may be within about ±20% (or, for example, about ±10%) of the lubricant limit of accessory gearbox 45 and / or drive gearbox 46. In various embodiments, in response to determining that the data indicating the amount of lubricant supplied to accessory gearbox 45 and drive gearbox 46 has exceeded the predetermined threshold, controllers 90, 96 can actuate solenoid valve 140 to the closed position by stopping the current 101 from power supplies 88, 91. Thus, flow meter 180 can be advantageously used, as described above, to prevent accessory gearbox 45 and / or drive gearbox 46 from being overcharged by lubricant 104 during a cleaning event. In embodiments where the lubrication reservoir 102 does not contain enough lubricant to supply gearboxes 45, 46 throughout the cleaning period (e.g., the lubrication reservoir runs out of lubricant during the cleaning period), an external lubricant reservoir may be connected to the lubrication reservoir 102 to supply additional lubricant.

[0065] In other embodiments, controllers 90, 96 may determine, after or during a predetermined time period, that the amount of lubricant supplied to (or already supplied to) accessory gearbox 45 and drive gearbox 46 is insufficient, based on data indicating the amount of lubricant supplied to the accessory gearbox and drive gearbox. In response, controllers 90, 96 may stop the cleaning event and / or stop the rotation of one or more gearboxes 45, 46 to prevent wear or gear scuffing. For example, when controllers 90, 96 determine (by monitoring flow meter 180) that insufficient lubricant is being (or has already been) supplied to gearboxes 45, 46, controllers 90, 96 may stop the cleaning event and / or stop the rotation of gearboxes 45, 46.

[0066] Now for reference Figure 3A and 3B Two cross-sectional views of an integrated check solenoid valve 300 according to an embodiment of the present disclosure are shown. Specifically, Figure 3A The integrated check solenoid valve 300 in the closed position is shown. Figure 3B The integrated check solenoid valve 300 in the open position is shown. Figure 3A and 3B The integrated check solenoid valve 300 shown can be implemented as described in the above reference. Figure 2 The solenoid valve 140 shown and described. That is, in some embodiments, the above reference... Figure 2 The solenoid valve 140 can be Figure 3Aand 3B The integrated check solenoid valve 300 is shown and described below.

[0067] The integrated check solenoid valve 300 may be a mechanically loaded one-way valve that prevents lubricant 104 from the lubrication reservoir 102 from flowing into the accessory gearbox 45 and the drive gearbox 46 when the gas turbine engine is not in operation. Furthermore, as described below, the integrated check solenoid valve 300 may include a solenoid that allows the integrated check solenoid valve 300 to be actuated to the open position, for example, during a cleaning event.

[0068] An integrated check solenoid valve 300 may include a valve body 301 defining a passage 302. A baffle wall 304 may extend into the passage 302 and define an orifice 306. The baffle wall 304 may divide the passage 302 into an inlet region 303 and an outlet region 305. A solenoid assembly 308 may be positioned within the passage 302. The solenoid assembly 308 may include a solenoid piston 310 and a solenoid 312 connected to the solenoid piston 310. In various embodiments, the solenoid piston 310 may be shaped as a cone extending from the solenoid 312 at a base to a tip. In some embodiments, the solenoid 312 may be connected to the valve body 301, for example, via a rear wall 314 extending from the valve body 301 into the passage 302. In various embodiments, the solenoid assembly 308 may also include a mechanical spring 316 extending between and coupled to the solenoid 310 and the rear wall 314.

[0069] In the closed position, such as Figure 3A As shown, the solenoid piston 310 can extend into the orifice 306 and fluidly isolate the inlet region 303 and the outlet region 305, thereby preventing lubricant 104 from flowing from the lubricant reservoir 102 to the gearboxes 45, 46. In the open position, one of the mechanical spring 316 and / or the solenoid 312 can be compressed. As a result, the solenoid piston 310 can be spaced apart from the orifice 306 to allow lubricant 104 to flow from the inlet region 303 through the orifice 306 to the outlet region 305, thereby allowing lubricant 104 to flow from the lubricant reservoir 102 to the gearboxes 45, 46.

[0070] For ease of discussion, Figure 3A and 3BSolenoid 312 is shown in simplified form. It should be understood that solenoid 312 may include a coil (wire) wound around a core, an armature, and a spring that biases the armature away from the core. When current is applied to the coil, the core generates a magnetic field that attracts the armature toward the core, thereby compressing the spring. When the power is turned off, the magnetic field disappears, and the spring biases the armature away from the core. Therefore, as used herein, the phrase "solecular compression" may mean that when current is applied to the coil of the solenoid, the core generates a magnetic field that attracts the armature toward the core, which compresses the solenoid's spring, thereby moving the solenoid piston 310 away from the orifice 306.

[0071] Depending on the operating mode of the gas turbine engine, the integrated check solenoid valve 300 can be moved to the open position in two ways. During normal operation of the gas turbine engine (e.g., cruise, climb, steady-state operating conditions, etc.), the pressure of the lubricant 104 in the inlet region 303 may exceed the spring force of the mechanical spring 316, which compresses the mechanical spring 316 and allows the lubricant 104 to flow through the orifice 306. During a cleaning event, the pressure of the lubricant 104 in the inlet region 303 does not exceed the spring force of the mechanical spring 316, therefore, the integrated check solenoid valve 300 can be actuated (e.g., via controllers 90, 96) to the open position by applying (or providing) current from the power source 318 to the solenoid 312. The power source 318 can be electrically connected to the solenoid 312, for example, via one or more wires.

[0072] The integrated check solenoid valve 300 may also include a flow meter 320 disposed in channel 302, for example, disposed in outlet area 305 of channel 302. The flow meter 320 may be operatively connected to controllers 90, 96 for monitoring the amount of lubricant 104 flowing from lubricant reservoir 102 and gearboxes 45, 46, as described in detail above.

[0073] Now for reference Figure 4A , 4B Figures 4C and 4C show three cross-sectional views of an integrated check solenoid valve 400 according to an embodiment of the present disclosure. Specifically, Figure 4A The integrated check solenoid valve 400 in the fully closed position is shown. Figure 4B An integrated check solenoid valve 400 in the check open position is shown, and Figure 4C An integrated check solenoid valve 400 in the solenoid open position is shown.

[0074] The integrated check solenoid valve 400 may include a mechanically loaded one-way valve that prevents lubricant 104 from the lubrication reservoir 102 from flowing into the accessory gearbox 45 and the drive gearbox 46 when the gas turbine engine is not in operation. Furthermore, as described below, the integrated check solenoid valve 400 may include a solenoid valve that allows the integrated check solenoid valve 400 to be actuated to an open position, for example, during a cleaning event.

[0075] The integrated check solenoid valve 400 may include a common valve body 402 having a check valve 404 and a solenoid valve 406. The common valve body 402 of the check valve 404 defines a main passage 408, which is divided into a main inlet region 410 and a main outlet region 412 by a main baffle wall 414. The main baffle wall 414 may extend into the main passage 408 and define a main orifice 416. The check valve 404 also includes a check piston 418, which, in the check closed position (… Figure 4A The device is mechanically loaded and pressed against the stop wall 414 (e.g., via a mechanical spring 420), and can move to the check valve open position when the pressure in the main inlet area exceeds the mechanical spring force of the mechanical spring 420. Figure 4B The main rear wall 422 can extend from the common valve body 402, and the mechanical spring 420 extends between the main rear wall 420 and the check piston 418. The mechanical spring 420 extends between the check piston 418 and the main rear wall 422 and is connected to the check piston 418 and the main rear wall 422.

[0076] The common valve body 402 of the solenoid valve 406 defines a bypass passage 424, which is divided into a bypass inlet region 426 and a bypass outlet region 428 by a bypass barrier wall 430. The bypass barrier wall 430 may extend into the bypass passage 424 and define a bypass orifice 432. The solenoid valve 406 includes a solenoid piston 434, which is in the solenoid closed position ( Figure 4A and 4B The solenoid valve 406 is loaded and abuts against the bypass stop wall 430. When current is received from the power supply 438, the solenoid valve 406 can be selectively actuated to the solenoid open position. Figure 4C ).

[0077] Solenoid 436 and solenoid piston 434 may be located within bypass channel 424. In various embodiments, solenoid piston 434 may be shaped as a cone extending from the base of solenoid 436 to a tip. In some embodiments, solenoid 436 may be connected to common valve body 402, for example, via a rear wall 440 extending from common valve body 402 into channel 302. In various embodiments, mechanical spring 442 may extend between and engage with solenoid 436 and bypass rear wall 440.

[0078] In the solenoid closed position, such as Figure 4A and 4B As shown, the solenoid piston 434 can extend into the bypass port 432 and fluidly isolate the bypass inlet region 426 and the bypass outlet region 428, thereby preventing lubricant 104 from flowing from the lubricant reservoir 102 into the gearboxes 45, 46. In the solenoid open position ( Figure 4C The solenoid 312 can be compressed. As a result, the solenoid piston 434 can be spaced apart from the bypass orifice 432 to allow lubricant 104 to flow from the bypass inlet region 426 through the bypass orifice 432 to the bypass outlet region 428, thereby allowing lubricant 104 to flow from the lubricant reservoir 102 to the gearboxes 45, 46.

[0079] Depending on the operating mode of the gas turbine engine, the integrated check solenoid valve 400 can be moved to the open position in several ways. During normal operation of the gas turbine engine (e.g., cruise, climb, steady-state operating conditions, etc.), the pressure of the lubricant 104 in the inlet region 410 may exceed the spring force of the mechanical spring 420, which compresses the mechanical spring 420 and allows the lubricant 104 to flow. During a cleaning event, the pressure of the lubricant 104 in the inlet region 410 does not exceed the spring force of the mechanical spring 420, therefore, by applying current from the power source 438 to the solenoid 436, the integrated check solenoid valve 400 can be actuated to the open position (e.g., via controllers 90, 96). The power source 438 can be electrically connected to the solenoid 436, for example, via one or more wires.

[0080] The solenoid piston 434 and the check piston can be loaded and abutted against corresponding blocking walls 414, 430. For example, the solenoid piston 434 is loaded and abutted against the bypass blocking wall 330 in the direction of lubricant flow, and the check piston 418 is loaded and abutted against the main blocking wall 414 in the direction of lubricant flow. Therefore, during normal operation of the gas turbine engine, the pressure of the lubricant 104 in the inlet region 426 can force the solenoid piston 434 against the bypass blocking wall 430, thereby preventing flow through the bypass passage 424. In contrast, during normal operation, the pressure of the lubricant 104 in the inlet region 410 may exceed the spring force of the mechanical spring 420, which compresses the mechanical spring 420 and allows the lubricant 104 to flow. The integrated check solenoid valve 400 may also include a flow meter 444. The flow meter 444 may be disposed in the bypass outlet region 428. The flow meter 444 can be operatively connected to the controllers 90, 96 to monitor the amount of lubricant 104 flowing from the lubricant reservoir 102 and gearboxes 45, 46, as described in detail above.

[0081] In many embodiments, the common valve body 402 may include a partition wall 446 separating the main passage 408 and the bypass passage 424. As shown, the bypass inlet region 426 is fluidly connected to the main inlet region 410 via a first bypass orifice 448 defined in the partition wall 446, and the bypass outlet region 428 is fluidly connected to the main outlet region 412 via a second bypass orifice 450 defined in the partition wall 446.

[0082] Now for reference Figure 5 According to embodiments of this subject matter, a flowchart of a method 500 for preventing wear (e.g., wear in one or more gearboxes) during a cleaning event of a gas turbine engine utilizing a cleaning system is shown. Generally, this document will refer to the foregoing references. Figure 1 Method 500 is described using the gas turbine engine 10, cleaning system 80, system 200, lubrication system 100, and integrated check solenoid valves 300 and 400 as shown in Figure 4. However, those skilled in the art will understand that the disclosed method 500 can generally be used with any other suitable system configuration. Furthermore, although Figure 5 For illustrative and discussion purposes, steps performed in a particular order are depicted, but unless otherwise specified in the claims, the methods discussed herein are not limited to any particular order or arrangement. Those skilled in the art will understand, using the disclosure provided herein, that the steps of the methods disclosed herein may be omitted, rearranged, combined, and / or modified in various ways without departing from the scope of this disclosure.

[0083] As shown in the figure, method 500 may include, at (502), rotating an accessory gearbox and a drive gearbox (e.g., using an electric motor) that are driven and connected to one or more shafts of the gas turbine engine during a cleaning event. Alternatively or additionally, the gearboxes may be rotated using an electric starter, a hybrid / electric starter, a hybrid pneumatic / electric starter, or other means, thereby rotating one or more shafts of the gas turbine engine during cleaning. In various embodiments, the cleaning event may be between about 0.5 hours and about 5 hours (or, for example, between about 0.5 hours and about 3 hours). The accessory gearbox and the drive gearbox are fluidly connected to the supply circuit of the lubrication system. For example, during cleaning of the gas turbine engine, the accessory gearbox and the drive gearbox may be driven by an electric motor to rotate one or more shafts of the gas turbine engine (e.g., the LP shaft and / or the HP shaft). In many embodiments, rotation at (502) may include, during a cleaning event, for the duration of which one or more shafts of the gas turbine engine are rotated at a speed between about 10 revolutions per minute (RPM) and about 400 RPM (or, for example, between about 50 RPM and about 200 RPM, or, for example, between about 100 RPM and about 150 RPM) using a motor drivenly connected to the accessory gearbox and drive gearbox, or by another means (e.g., an electric starter, a hybrid / electric starter, a hybrid pneumatic / electric starter). Thus, components of the accessory gearbox and drive gearbox (e.g., gears) rotate together with one or more shafts.

[0084] In an exemplary embodiment, method 500 may further include, at (504), actuating the solenoid of the solenoid valve from a closed position to an open position by supplying current from a power source, the closed position preventing lubricant from the lubrication reservoir from flowing to the accessory gearbox and the drive gearbox, the open position allowing lubricant from the lubrication reservoir to flow to the accessory gearbox and the drive gearbox.

[0085] In various embodiments, the cleaning system may include a cleaning controller, and the gas turbine engine includes an engine controller operatively communicating with both the cleaning controller and the engine controller. In such embodiments, the method may further include utilizing the engine controller to receive a signal indicating that a cleaning event has commenced. In response to receiving the signal indicating that a cleaning event has commenced, current may be supplied from the engine power supply to the solenoid valve, thereby opening the solenoid to an open position and allowing lubricant flow. Furthermore, in these embodiments, the method may also include utilizing the engine controller to receive data from a flow meter in fluid communication with the lubrication system indicating the amount of lubricant supplied to the accessory gearbox and the drive gearbox. The engine controller may then determine that the data indicating the amount of lubricant supplied to the accessory gearbox and the drive gearbox has exceeded a predetermined threshold (e.g., indicating that the gearbox is being overcharged). In response, the method may include actuating the solenoid valve to a closed position by stopping the current from the power supply.

[0086] In many embodiments, the method may include receiving data from a flow meter in fluid communication with the lubrication system, indicating the amount of lubricant supplied to the accessory gearbox and drive gearbox, using the engine controller. In this embodiment, the method may also include determining, after or during a predetermined time period, based on the data indicating the amount of lubricant supplied to the accessory gearbox and drive gearbox, that insufficient lubricant is being delivered to them. In response, the method may include stopping the rotation of the accessory gearbox and drive gearbox to protect them from scuffing and / or gear wear.

[0087] In an exemplary embodiment, method 500 may further include, at (506), cleaning the gas turbine engine with a cleaning system during a cleaning period. The cleaning system may include one or more cleaning lines that can discharge cleaning fluid onto one or more components of the gas turbine engine while the shaft of the gas turbine engine is rotated by an electric motor. In many embodiments, cleaning at (506) may include discharging cleaning fluid onto one or more components of the gas turbine engine while the shaft of the gas turbine engine is rotated by an electric motor and the solenoid is in an open position.

[0088] Figure 6 A block diagram of an example computing system 600 is provided. The computing system 600 can be used to implement the aspects disclosed herein. The computing system 600 may include one or more computing devices 602. For example, referenced above... Figure 1 The controllers 90 and 96 described in -4 can be constructed and operated in the same or similar manner as one of the computing devices 602.

[0089] like Figure 6As shown, one or more computing devices 602 may each include one or more processors 604 and one or more memory devices 606. The one or more processors 604 may include any suitable processing means, such as a microprocessor, microcontroller, integrated circuit, logic device, or other suitable processing means. The one or more memory devices 606 may include one or more computer-readable media, including but not limited to non-transient computer-readable media or media, RAM, ROM, hard disk drives, flash drives, and other memory devices, such as one or more buffer devices.

[0090] One or more memory devices 606 may store information accessible to one or more processors 604, including computer-readable or computer-executable instructions 608 that can be executed by one or more processors 604. Instructions 608 may be any set of instructions or control logic that, when executed by one or more processors 604, causes one or more processors 604 to perform operations. Instructions 608 may be software written in any suitable programming language or implemented in hardware. The computing system 600 may implement the above-mentioned references. Figure 1 The controllers 90 and 96 described in -4 enable the execution of instruction 608 to implement the above-mentioned reference. Figure 5 The method 500 or one or more portions thereof. For example, instruction 608 may be executed by one or more processors 604 of computing system 600 to cause the system to perform one or more operations, including, but not limited to: during a cleaning event, rotating an accessory gearbox and a drive gearbox drivenly connected to one or more shafts of the gas turbine engine, the accessory gearbox and the drive gearbox being fluidly connected to a lubrication system having a lubrication reservoir; actuating the solenoid of a solenoid valve from a closed position to an open position by supplying current from a power source, the closed position preventing lubricant from the lubrication reservoir from flowing to the accessory gearbox and the drive gearbox, the open position allowing lubricant from the lubrication reservoir to flow to the accessory gearbox and the drive gearbox; and cleaning the gas turbine engine with the cleaning system during a cleaning event.

[0091] The memory device 606 may also store data 610 accessible by the processor 604. For example, data 610 may include sensor data (such as engine parameters), model data, logic data, etc., as described herein. According to exemplary embodiments of this disclosure, data 610 may include one or more tables, functions, algorithms, models, equations, etc.

[0092] One or more computing devices 602 may also include a communication interface 612 for communicating, for example, with other components of the gas turbine engine, such as flow meters, power supplies, or other components. The communication interface 612 may include any suitable components for interfacing with one or more networks, including, for example, transmitters, receivers, ports, controllers, antennas, or other suitable components.

[0093] Further details are provided by the following topics:

[0094] A system for reducing wear during a cleaning event in a gas turbine engine, the system comprising: an accessory gearbox; a drive gearbox drivably and fluidly coupled to the accessory gearbox; and a lubrication system fluidly coupled to the accessory gearbox and the drive gearbox, the lubrication system comprising: a lubricant reservoir fluidly connected to the drive gearbox and the accessory gearbox; and a solenoid valve in fluid communication with the lubricant reservoir, the solenoid valve being selectively actuated between an open position and a closed position when current is supplied from a power source, the open position allowing lubricant to flow from the lubricant reservoir to the accessory gearbox and the drive gearbox, and the closed position preventing lubricant from flowing from the lubricant reservoir to the accessory gearbox and the drive gearbox.

[0095] The system according to any of the foregoing clauses, wherein the power source is a cleaning system power source, the cleaning system power source being included in a cleaning system for performing the cleaning event on the gas turbine engine.

[0096] In any of the foregoing clauses, the power source is an engine power source.

[0097] According to any of the foregoing clauses, the cleaning event is performed using a cleaning system with a cleaning controller, wherein the gas turbine engine further includes an engine controller operatively communicating with the cleaning controller, and wherein the engine controller includes a memory and one or more processors, the memory storing instructions that, when executed by the one or more processors, cause the system to operate, the operation including: receiving a signal indicating that the cleaning event has commenced using the engine controller; and, in response to receiving the signal indicating that the cleaning event has commenced, supplying current from an engine power source to the solenoid valve.

[0098] According to any of the foregoing clauses, the operation further includes: receiving data from a flow meter in fluid communication with the lubrication system, indicating the amount of lubricant supplied to the accessory gearbox and the drive gearbox, using the engine controller; determining, using the engine controller, that the data indicating the amount of lubricant supplied to the accessory gearbox and the drive gearbox has exceeded a predetermined threshold; and in response to determining that the data indicating the amount of lubricant supplied to the accessory gearbox and the drive gearbox has exceeded the predetermined threshold, actuating the solenoid valve to the closed position by stopping the current from the power supply.

[0099] According to any of the foregoing clauses, the lubrication system comprises: a supply circuit that supplies lubricant from the lubricant reservoir to the accessory gearbox and the drive gearbox; and a return circuit that returns lubricant from the accessory gearbox and the drive gearbox back to the lubricant reservoir, wherein a solenoid valve is fluidly disposed on the supply circuit.

[0100] According to any of the foregoing clauses, the lubrication system includes a lubrication and return system, wherein the supply circuit includes an inlet supply line extending from the lubricant reservoir to the lubrication and return system, and wherein the solenoid valve is fluidly disposed on the inlet supply line.

[0101] According to any of the foregoing clauses, the solenoid valve is an integrated check solenoid valve, the integrated check solenoid valve comprising: a valve body defining a passage divided into an inlet region and an outlet region by a barrier wall; a solenoid assembly disposed in the passage, the solenoid assembly having a solenoid piston, a solenoid, and a mechanical spring, the solenoid piston being mechanically loaded against the barrier wall in a closed position and capable of moving to an open position when the pressure in the inlet region exceeds the mechanical spring force of the mechanical spring; or when current is supplied to the solenoid from a power source.

[0102] According to any of the foregoing clauses, wherein the solenoid valve is an integrated valve, the integrated valve comprising: a check valve defining a main channel divided into a main inlet area and a main outlet area by a main baffle wall, the check valve including a check piston mechanically loaded against the baffle wall in a check-closed position and movable to a check-open position when the pressure in the main inlet area exceeds the mechanical spring force; and the solenoid valve defining a bypass channel divided into a bypass inlet area and a bypass outlet area by a bypass baffle wall, the solenoid valve including a solenoid piston solenoid loaded against the bypass baffle wall in a solenoid closed position, the solenoid valve being selectively actuated to a solenoid open position upon receiving current from a power source.

[0103] According to any of the foregoing clauses, the bypass inlet region is fluidly connected to the main inlet region via a first bypass orifice, and the bypass outlet region is fluidly connected to the main outlet region via a second bypass orifice.

[0104] The system according to any of the foregoing clauses further includes a flow meter disposed in the bypass outlet area.

[0105] A method for reducing wear during a cleaning event of a gas turbine engine utilizing a cleaning system, the method comprising: during the cleaning event, rotary drive of an accessory gearbox and a drive gearbox to one or more shafts of the gas turbine engine, the accessory gearbox and the drive gearbox being fluidly connected to a lubrication system having a lubrication reservoir; actuating a solenoid valve from a closed position to an open position by supplying current from a power source, the closed position preventing lubricant from the lubrication reservoir from flowing to the accessory gearbox and the drive gearbox, the open position allowing lubricant from the lubrication reservoir to flow to the accessory gearbox and the drive gearbox; and cleaning the gas turbine engine using the cleaning system during the cleaning event.

[0106] According to any of the foregoing clauses, the cleaning system includes a washing controller, wherein the gas turbine engine further includes an engine controller operatively communicating with the washing controller and the engine controller, and wherein the method includes: receiving a signal indicating that the cleaning event has commenced using the engine controller; and in response to receiving the signal indicating that the cleaning event has commenced, supplying the current from an engine power source to the solenoid.

[0107] The method according to any of the foregoing clauses, wherein the method further comprises: receiving data from a flow meter in fluid communication with the lubrication system, using the engine controller, indicating the amount of lubricant supplied to the accessory gearbox and the drive gearbox; determining, using the engine controller, that the data indicating the amount of lubricant supplied to the accessory gearbox and the drive gearbox has exceeded a predetermined threshold; and in response to determining that the data indicating the amount of lubricant supplied to the accessory gearbox and the drive gearbox has exceeded the predetermined threshold, actuating the solenoid to the closed position by stopping the current from the power supply.

[0108] The method according to any of the foregoing clauses, wherein the method further comprises: receiving data from a flow meter in fluid communication with the lubrication system, using the engine controller, indicating the amount of lubricant supplied to the accessory gearbox and the drive gearbox; determining, based on the data indicating the amount of lubricant supplied to the accessory gearbox and the drive gearbox, after or during a predetermined time period, that insufficient lubricant is being delivered to the accessory gearbox and the drive gearbox; and stopping the rotation of the accessory gearbox and the drive gearbox.

[0109] According to any of the foregoing clauses, cleaning the gas turbine engine includes discharging cleaning fluid onto one or more components of the gas turbine engine while the one or more shafts of the gas turbine engine are rotating and the solenoid is in the open position.

[0110] According to any of the foregoing clauses, the accessory gearbox and the transmission gearbox are drivably connected to the one or more shafts, and rotating the accessory gearbox and the transmission gearbox comprises: during the cleaning event, for the duration of the cleaning event, rotating the one or more shafts of the gas turbine engine at a speed of about 10 revolutions per minute (RPM) to about 400 RPM.

[0111] The method according to any of the foregoing clauses, wherein the solenoid valve is an integrated check solenoid valve.

[0112] An integrated valve includes: a check valve defining a main channel divided into a main inlet area and a main outlet area by a main barrier wall, the check valve including a check piston mechanically loaded against the barrier wall in a check-closed position and movable to a check-open position when the pressure in the main inlet area exceeds a mechanical spring force; and a solenoid valve defining a bypass channel divided into a bypass inlet area and a bypass outlet area by a bypass barrier wall, the solenoid valve including a solenoid piston solenoid loaded against the bypass barrier wall in a solenoid closed position, the solenoid valve being selectively actuated to a solenoid open position upon receiving current from a power source.

[0113] According to any of the preceding clauses, the integrated check solenoid valve wherein the bypass inlet region is fluidly connected to the main inlet region via a first bypass orifice, and the bypass outlet region is fluidly connected to the main outlet region via a second bypass orifice.

[0114] The integrated valve according to any of the foregoing clauses further includes a flow meter disposed in the bypass outlet area.

[0115] An integrated check solenoid valve includes: a valve body defining a channel divided into an inlet region and an outlet region by a barrier wall; and a solenoid assembly disposed in the channel, the solenoid assembly having a solenoid piston, a solenoid, and a mechanical spring, the solenoid piston being mechanically loaded against the barrier wall in a closed position and capable of moving to an open position when the pressure in the inlet region exceeds the mechanical spring force of the mechanical spring; or when current is supplied to the solenoid from a power source.

[0116] The integrated check solenoid valve according to any of the foregoing clauses further includes a flow meter disposed in the outlet area of ​​the channel.

[0117] The integrated check solenoid valve according to any of the foregoing clauses further includes a rear wall connected to the solenoid assembly.

[0118] This written description uses examples to disclose this disclosure, including best practices, and also enables any person skilled in the art to practice this disclosure, including making and using any device or system and methods of making any combination. The patentable scope of this disclosure is defined by the claims, but may include other examples that would occur to a person skilled in the art. Such other examples are intended to fall within the scope of the claims if they include structural elements that are not indistinguishable from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims.

Claims

1. A system for reducing wear during a cleaning event in a gas turbine engine, characterized in that, The system includes: Accessory gearbox; A transmission gearbox, which is drivably and fluidly coupled to the accessory gearbox; and A lubrication system fluidly connected to the accessory gearbox and the transmission gearbox, the lubrication system comprising: A lubricant reservoir, fluidly connected to the drive gearbox and the accessory gearbox; and A solenoid valve, in fluid communication with the lubricant reservoir, is selectively actuated between an open position and a closed position when current is supplied from a power source. The open position allows lubricant to flow from the lubricant reservoir to the accessory gearbox and the drive gearbox, while the closed position prevents lubricant from flowing from the lubricant reservoir to the accessory gearbox and the drive gearbox.

2. The system according to claim 1, characterized in that, in, The power source is a cleaning system power source, which is included in the cleaning system used for performing the cleaning event on the gas turbine engine.

3. The system according to claim 1, characterized in that, in, The power source is the engine power source.

4. The system according to claim 1, characterized in that, in, The cleaning event is performed using a cleaning system with a cleaning controller, wherein the gas turbine engine further includes an engine controller operatively communicating with the cleaning controller, and wherein the engine controller includes a memory and one or more processors, the memory storing instructions that, when executed by the one or more processors, cause the system to operate, the operation including: The engine controller receives a signal indicating that the cleaning event has begun; and In response to receiving the signal indicating that the cleaning event has begun, current is supplied from the engine power supply to the solenoid valve.

5. The system according to claim 4, characterized in that, in, The operation further includes: The engine controller receives data from a flow meter in fluid communication with the lubrication system, indicating the amount of lubricant supplied to the accessory gearbox and the transmission gearbox; The engine controller determines that the data indicating the amount of lubricant supplied to the accessory gearbox and the drive gearbox has exceeded a predetermined threshold; and In response to determining that the data indicating the amount of lubricant supplied to the accessory gearbox and the transmission gearbox has exceeded the predetermined threshold, the solenoid valve is actuated to the closed position by stopping the current from the power source.

6. The system according to claim 1, characterized in that, in, The lubrication system includes: A supply circuit that supplies lubricant from the lubricant reservoir to the accessory gearbox and the drive gearbox; and A return circuit that returns lubricant from the accessory gearbox and the drive gearbox to the lubricant reservoir, wherein the solenoid valve is fluidly connected to the supply circuit.

7. The system according to claim 6, characterized in that, in, The lubrication system includes a lubrication and return system, wherein the supply circuit includes an inlet supply line extending from the lubricant reservoir to the lubrication and return system, and wherein the solenoid valve is fluidly disposed on the inlet supply line.

8. The system according to claim 1, characterized in that, in, The solenoid valve is an integrated check solenoid valve, which includes: A valve body defining a passage divided into an inlet area and an outlet area by a barrier wall; A solenoid assembly disposed in the channel, the solenoid assembly having a solenoid piston, a solenoid, and a mechanical spring, the solenoid piston being mechanically loaded against the blocking wall in the closed position and capable of moving to the open position under the following conditions: The pressure within the inlet area exceeds the mechanical spring force of the mechanical spring; or When current is supplied from the power source to the solenoid.

9. The system according to claim 1, characterized in that, in, The solenoid valve is an integrated valve, and the integrated valve includes: A check valve defining a main channel divided into a main inlet area and a main outlet area by a main barrier wall, the check valve including a check piston mechanically loaded against the barrier wall in a check-closed position and movable to a check-open position when the pressure in the main inlet area exceeds the mechanical spring force; and The solenoid valve defines a bypass passage, which is divided into a bypass inlet area and a bypass outlet area by a bypass barrier wall. The solenoid valve includes a solenoid piston, which is loaded by the solenoid and abuts against the bypass barrier wall when the solenoid is in the closed position. The solenoid valve can be selectively actuated to the solenoid open position when it receives current from the power source.

10. The system according to claim 9, characterized in that, in, The bypass inlet region is fluidly connected to the main inlet region via a first bypass orifice, and the bypass outlet region is fluidly connected to the main outlet region via a second bypass orifice.

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