Turbine engine with lubrication system

Abstract

A turbine engine includes a turbocharged engine, a gearbox assembly, a propulsion unit, and a lubrication system. The lubrication system includes a lubricant tank therein for storing lubricant, one or more primary gearbox lubricant supply lines in fluid communication with the lubricant tank and the gearbox assembly, one or more secondary gearbox lubricant supply lines in fluid communication with the lubricant tank and the gearbox assembly, and a lubricant pump for supplying lubricant from the lubricant tank to the gearbox assembly through the one or more primary gearbox lubricant supply lines and the one or more secondary gearbox lubricant supply lines. The lubrication system regulates the mass flow rate of lubricant to the gearbox assembly through at least one of the one or more primary gearbox lubricant supply lines or the one or more secondary gearbox lubricant supply lines.

Description

Technical Field

[0001] This disclosure generally relates to turbine engines having, for example, a lubrication system for a gearbox assembly in a turbine engine. Background Technology

[0002] A turbine engine typically comprises a propeller (such as a fan or propeller) and a turbocharger that are in fluid communication with each other. A gearbox assembly transmits torque and power from one rotating component to another (e.g., from a turbocharger to a propeller). A lubrication system provides lubricant to one or more rotating components of the turbine engine, including the gearbox assembly. Attached Figure Description

[0003] Features and advantages will become apparent from the following more detailed description of various exemplary embodiments as shown in the accompanying drawings, wherein similar reference numerals generally denote identical, functionally similar, and / or structurally similar elements.

[0004] Figure 1 This is a schematic cross-sectional view of the turbine engine according to the present disclosure, taken along the longitudinal centerline axis of the turbine engine.

[0005] Figure 2 It is part of the gearbox assembly and lubrication system according to this disclosure. Figure 1 A schematic axial end cross-section view taken from detail 2-2 in the image.

[0006] Figure 3 Based on this disclosure Figure 2 A schematic diagram of the lubrication system.

[0007] Figure 4 According to another embodiment, it is used for Figure 1 A schematic diagram of the lubrication system of a turbine engine.

[0008] Figure 5 According to another embodiment, it is used for Figure 1 A schematic diagram of the lubrication system of a turbine engine.

[0009] Figure 6 According to another embodiment, it is used for Figure 1 A schematic diagram of the lubrication system of a turbine engine. Detailed Implementation

[0010] The features, advantages, and embodiments of this disclosure will be apparent or understood by considering the following detailed description, drawings, and claims. Furthermore, the following detailed description is exemplary and intended to provide further explanation, without limiting the scope of the claimed disclosure.

[0011] Various embodiments of this disclosure are discussed in detail below. While specific embodiments are discussed, they are for illustrative purposes only. Those skilled in the art will recognize that other components and configurations can be used without departing from this disclosure.

[0012] As used herein, the terms “first,” “second,” “third,” etc., are used interchangeably to distinguish one component from another and are not intended to indicate the position or importance of the components.

[0013] The terms "upstream" and "downstream" refer to the relative directions of fluid flow within a fluid path. For example, "upstream" refers to the direction from which the fluid flows, while "downstream" refers to the direction in which it flows.

[0014] The terms "front" and "rear" refer to the relative positions within a turbine engine or vehicle, and to the normal operating posture of the turbine engine or vehicle. More specifically, as used herein, "front" and "rear" refer to the direction of travel of the vehicle and the direction of the propulsive thrust of the gas turbine engine.

[0015] Unless otherwise specified herein, the terms “connection,” “fixation,” “attachment,” “linkage,” etc., refer to both direct connection, fixation, attachment, or linking, and indirect connection, fixation, attachment, or linking through one or more intermediate components or features.

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

[0017] As used herein, the terms "axial" and "axially" refer to a direction and orientation that extends substantially parallel to the centerline of the turbine engine. Furthermore, the terms "radial" and "radially" refer to a direction and orientation that extends substantially perpendicular to the centerline of the turbine engine. Additionally, as used herein, the terms "circumferential" and "circumferentially" refer to a direction and orientation that extends in an arc around the centerline of the turbine engine.

[0018] As used herein, a "thruster" is a component of a turbine engine that is drivenly coupled to a turbocharged engine, such that rotation of components of the turbocharged engine causes the thruster to rotate and generate thrust. A thruster may include a fan or a propeller. In a turbofan engine (such as a ducted fan engine or a non-ducted fan engine), the thruster is a fan. In a turboprop engine, the thruster is a propeller.

[0019] As used herein, the terms “meshing,” “engaged,” or “mutually meshing” refer to the position where the teeth of two gears are engaged or meshed with each other.

[0020] As used herein, the “friction” between two rotating components occurs at the contact interface between them and is a result of the sliding and rolling contact between the two rotating components relative to each other. Friction is a function of geometry and operating conditions (e.g., the power transmitted through the two rotating components).

[0021] As used in this article, the "wind resistance" of a rotating component arises from the interaction between the rotating component and the fluid (such as air or lubricant) surrounding it. Wind resistance is caused by the resistance of the rotating component within the fluid and is a function of geometry and operating conditions. One of the main driving factors of wind resistance is the amount of lubricant interacting with the rotating component.

[0022] As used herein, "gearbox efficiency" is the ratio of the output power of a gearbox assembly to the input power of the gearbox assembly. Specifically, gearbox efficiency is the ratio of the output power through the output shaft to the input power from the input shaft. In some embodiments, the input shaft is the shaft of a turbocharged engine (e.g., the low-pressure shaft), and the output shaft is the propeller shaft of a thruster.

[0023] As used herein, the terms “low,” “medium” (or “medium”), and “high,” or their respective comparative degrees (e.g., “lower” and “higher”, as applicable), when used with compressors, combustors, turbines, shafts, propellers, or turbofan engine components, refer, unless otherwise specified, to a relative pressure, relative speed, relative temperature, or relative power output within the turbine engine. For example, a “low power” setting defines a turbine engine or combustor configured to operate at a power output lower than a “high power” setting, while a “medium power” setting defines a turbine engine or combustor configured to operate at a power output higher than a “low power” setting and lower than a “high power” setting. The terms “low,” “medium” (or “medium”), or “high” may additionally or alternatively relate to minimum permissible speed, pressure, or temperature. The terms “low,” “medium” (or “medium”), or “high” can be understood as minimum or maximum permissible speed, pressure, or temperature relative to normal, desired, steady-state, etc., operation of the turbine engine. Turbine engine duty cycles include, for example, low power operation, medium power operation, and high power operation. Low-power operations include, for example, engine start, idling, taxiing, and approach. Medium-power operations include, for example, cruise. High-power operations include, for example, takeoff and climb.

[0024] The various power levels of the turbofan engine are defined as a percentage of the maximum engine rated thrust at sea level static (SLS). Low-power operation includes, for example, less than 30 percent (30%) of the maximum engine rated thrust at SLS of the turbofan engine. Medium-power operation includes, for example, from 30 percent (30%) to 85 percent (85%) of the maximum engine rated thrust at SLS of the turbofan engine. High-power operation includes, for example, greater than 85 percent (85%) of the maximum engine rated thrust at SLS of the turbofan engine. The thrust values ​​for each of the low-power, medium-power, and high-power operations of the turbofan engine are merely exemplary, and other thrust values ​​may be used to define low-power, medium-power, and high-power operations.

[0025] Scope limitations are combined and interchanged herein, and throughout the specification and claims. Unless the context or language otherwise indicates, these scopes are identified and include all subscopes contained herein. For example, all scopes disclosed herein include endpoints, which may be combined independently of each other.

[0026] Gear assemblies in turbine engines or other applications are used to transfer power and motion from one rotating component to another. For example, a turbine engine may include a gearbox assembly that transfers power from the shaft of a turbocharged engine to the turbine's propeller. However, the efficiency of rotating components, such as gears, is not 100%. During operation of the gear assembly, power losses occur in the gears and bearings due to friction (F) (e.g., between the teeth of the gears) and the interaction between the rotating components and fluids (e.g., lubricants) within the gear assembly. The interaction between the rotating components and the fluid is called wind resistance (W), which is caused by the resistance of the rotating components within the fluid. Friction and wind resistance generate heat within the gear assembly that needs to be dissipated. Lubricants, such as oil (as a non-limiting example), can be used to lubricate and cool the gear assembly components (e.g., gears and bearings) by directing a dedicated lubricant flow to the meshing points of the bearings and gears.

[0027] The amount of lubricant required in a lubrication system for gears or bearings is determined based on the maximum ΔT temperature (dT) that each component can withstand before damage (e.g., gear scuffing). For example, the maximum ΔT temperature (dT) is based on the material properties of the component, as well as the amount of power loss due to friction and air resistance (such as fluid losses), which heats the component (e.g., increases its temperature). Using more lubricant in a lubrication system can reduce dT, reducing damage to gears and bearings. However, a larger lubricant flow rate through the lubrication system results in greater fluid losses, thus reducing gearbox efficiency. In particular, friction and air resistance on the gears due to lubrication in a lubrication system lead to a reduction in output torque at the same power output level compared to a lubrication system with less lubricant. Using less lubricant in a lubrication system can improve efficiency because of lower fluid losses, but it also results in a higher dT and a higher risk of gear and bearing damage.

[0028] Furthermore, the amount of lubricant supplied through the lubrication system varies during the typical power cycle of a turbine engine. In aircraft turbine engines, particularly, lubricant flow is lower under low-power conditions (such as idling and taxiing), higher under medium-power conditions (such as cruise), and even higher under high-power conditions (such as takeoff or climb). Typically, the amount of lubricant supplied to the lubrication system is determined based on the lubricant requirements during high-power operation. Therefore, the amount of lubricant supplied to the gearbox is not optimized for low- and medium-power conditions (e.g., reducing dT while maintaining gearbox efficiency). Consequently, during low- and medium-power conditions, more lubricant is supplied than is needed to reduce dT and minimize damage to gears and bearings, thus reducing gearbox efficiency.

[0029] Furthermore, in standard gearbox lubrication systems, each component requiring lubrication has a single delivery line connected to a pump. The dimensions of the pipes and nozzles belonging to this single delivery line are designed with the required lubricant flow rate at a design point (DP), typically during takeoff (e.g., high-power conditions), to match a number of thermal and fluid constraints (e.g., dT and efficiency mentioned above). Under all other operating conditions, the lubricant flow rate is driven by the value set at the design point, and the pump output is typically linearly related to the speed of the low-pressure shaft of the turbine engine. Therefore, the lubricant flow rate cannot be optimized for less demanding conditions, such as cruise (e.g., medium- or low-power conditions). This negatively impacts the turbine engine's engine efficiency and fuel consumption. Thus, under medium- and low-power conditions, the lubricant flow rate exceeds the required amount compared to a gearbox assembly with the same gear size and shaft speed, resulting in an unreasonable increase in drag and hydrodynamic losses, which represent a significant portion of the total heat dissipation of the gearbox assembly, without the benefits of this disclosure.

[0030] Therefore, this disclosure provides two sets of lubricant supply lines (such as a primary supply line and a secondary supply line) for each component requiring lubrication (such as a gearbox assembly, turbine engine bearing, etc.). Specifically, this disclosure includes a primary lubricant injector fluidly connected to the primary supply line and a secondary lubricant injector fluidly connected to the secondary supply line. The area of ​​the injector orifice is configured to achieve a specific injection velocity of the lubricant ejected from the injector. The optimal injection velocity depends on the ratio between the gearbox speed and the injection velocity. In systems without the benefits of this disclosure, this ratio is selected based on high-power (e.g., takeoff) conditions, and thus optimized for medium and low power conditions because the lubricant flow rate and gearbox speed are linearly related to engine speed (e.g., turbine engine speed).

[0031] Under demanding conditions (such as takeoff), both supply lines are open, allowing all pumped lubricant flow into the gearbox assembly. Under less demanding conditions (such as cruise), a shut-off valve (e.g., controlled by the controller) closes the secondary supply line, reducing the amount of lubricant in the gearbox assembly and thus improving gearbox efficiency because drag losses are controlled. Furthermore, a proportional valve on the primary supply line can be connected in parallel with the shut-off valve. The proportional valve allows for further optimization of lubricant flow under low- or medium-power conditions.

[0032] Therefore, this disclosure provides a lubrication system that, by regulating the flow rate of lubricant to the gearbox assembly, provides a specific amount of lubricant and lubricant temperature throughout the entire operating cycle of the turbine engine for all operating conditions, thereby reducing damage to the gearbox assembly while minimizing gearbox losses (e.g., due to gear friction and wind resistance) and maximizing gearbox efficiency. Furthermore, having two lubricant supply lines allows for linear scaling of the lubricant flow rate with engine speed by reducing the number of orifices (e.g., total orifice area) when one line is closed, while also allowing for lubricant regulation.

[0033] Now refer to the attached diagram, Figure 1 This is a schematic cross-sectional view of a turbine engine 10 according to an embodiment of the present disclosure, taken along the longitudinal centerline axis 12 of the turbine engine 10. Figure 1 As shown, the turbine engine 10 defines an axial direction A (extending parallel to the longitudinal centerline axis 12 provided as a reference) and a radial direction R orthogonal to the axial direction A. Typically, the turbine engine 10 includes a propeller section 14 and a turbocharger engine 16 disposed downstream of the propeller section 14.

[0034] The turbocharged engine 16 comprises a compressor section 21, a combustion section 26, and a turbine section 27 in a series flow relationship. The turbocharged engine 16 is substantially enclosed within a housing 18, which is substantially tubular and defines a core inlet 20 in an annular shape around a longitudinal centerline axis 12. Figure 1 As schematically shown, compressor section 21 includes a turbocharger or low-pressure (LP) compressor 22, downstream of which is a high-pressure (HP) compressor 24. Combustion section 26 is located downstream of compressor section 21. Turbine section 27 is located downstream of combustion section 26 and includes a high-pressure (HP) turbine 28, followed by a low-pressure (LP) turbine 30. Turbocharged engine 16 also includes an injection exhaust nozzle section 32, a high-pressure (HP) shaft 34, and a low-pressure (LP) shaft 36 located downstream of turbine section 27. HP shaft 34 drivesly connects HP turbine 28 to HP compressor 24. HP turbine 28 and HP compressor 24 rotate synchronously via HP shaft 34. LP shaft 36 drivesly connects LP turbine 30 to LP compressor 22. LP turbine 30 and LP compressor 22 rotate synchronously via LP shaft 36. Compressor section 21, combustion section 26, turbine section 27, and injection exhaust nozzle section 32 together define the core airflow path.

[0035] The turbine engine 10 also includes one or more shaft bearings, including one or more HP shaft bearings 35 and one or more LP shaft bearings 37. The HP shaft bearings 35 support the rotation of the HP shaft 34. The LP shaft bearings 37 support the rotation of the LP shaft 36. The HP shaft bearings 35 and LP shaft bearings 37 can include any type of bearing for supporting the rotation of the shafts, such as ball bearings, roller bearings, etc.

[0036] for Figure 1 In the illustrated embodiment, thruster section 14 includes a thruster 38 (e.g., a variable pitch thruster) having a plurality of thruster blades 40 spaced apart and coupled to disk 42. Figure 1In some embodiments, the thruster 38 is a fan driven by the turbocharged engine 16. In some embodiments, the thruster 38 is a propeller driven by the turbocharged engine 16. The thruster blades 40 typically extend outward from the disk 42 in a radial direction R. In the case of a variable-pitch thruster, since the thruster blades 40 are operatively coupled to an actuating member 44, multiple thruster blades 40 can rotate relative to the disk 42 about a pitch axis P, the actuating member being configured to collectively and uniformly change the pitch of the thruster blades 40. The thruster blades 40, disk 42, and actuating member 44 can rotate together about a longitudinal centerline axis 12 via a thruster shaft 45, which is powered by an LP shaft 36 passing through a power gearbox (also referred to as gearbox assembly 46). Thus, the thruster 38 is drivenly coupled to and powered by the turbocharged engine 16, and the turbocharged engine 10 is an indirectly driven engine. The gearbox assembly 46 is in... Figure 1 The diagram is schematically shown. Gearbox assembly 46 is a reduction gearbox assembly used to regulate the rotational speed of the propeller shaft 45 as power is transmitted from the LP shaft 36 to the propeller shaft 45, thereby regulating the rotational speed of the propeller 38 relative to the LP shaft 36.

[0037] Still referencing Figure 1 In an exemplary embodiment, the disk 42 is covered by a thruster hub 48, which has an aerodynamic profile to facilitate airflow through a plurality of thruster blades 40. Furthermore, the thruster section 14 includes an annular thruster housing or nacelle 50 circumferentially surrounding at least a portion of the thruster 38 and the turbocharged engine 16. The nacelle 50 is supported relative to the turbocharged engine 16 by a plurality of outlet guide vanes 52 circumferentially spaced around the nacelle 50 and the turbocharged engine 16. Additionally, a downstream section 54 of the nacelle 50 extends externally over the turbocharged engine 16 and, together with the housing 18, defines a bypass airflow passage 56 therebetween.

[0038] During operation of the turbine engine 10, a certain amount of air 58 enters the turbine engine 10 through the nacelle 50 or the inlet 60 of the propeller section 14. As the air 58 passes through the propeller blades 40, a first portion of the air (also called bypass air 62) is directed into the bypass airflow passage 56, and a second portion of the air (called core air 64) is directed into the upstream section of the core air flow path through the core inlet 20 of the LP compressor 22. The pressure of the core air 64 then increases, producing compressed air 65. The compressed air 65 is directed through the HP compressor 24 and into the combustion section 26, where it is mixed with fuel and ignited to produce combustion gases 66.

[0039] Combustion gas 66 is introduced into and expanded by the HP turbine 28. In the HP turbine 28, a portion of the thermal or kinetic energy from the combustion gas 66 is extracted via one or more stages of the HP turbine rotor blades 70 and HP turbine stator blades 68, which are connected to the HP shaft 34. This causes the HP shaft 34 to rotate, thereby supporting the operation of the HP compressor 24 (self-sustaining cycle). Thus, the combustion gas 66 performs work on the HP turbine 28. The combustion gas 66 is then guided into the LP turbine 30 and expanded there. Here, a second portion of the thermal or kinetic energy is extracted from the combustion gas 66 via one or more stages of the LP turbine rotor blades 74 and LP turbine stator blades 72, which are connected to the LP shaft 36. This causes the LP shaft 36 to rotate, thereby supporting the operation of the LP compressor 22 (self-sustaining cycle) and the rotation of the propeller 38 via the gearbox assembly 46. Thus, the combustion gas 66 performs work on the LP turbine 30.

[0040] Combustion gas 66 is then directed through the injector exhaust nozzle section 32 of the turbocharged engine 16 to provide propulsive thrust. Simultaneously, bypass air 62 is directed through bypass airflow passage 56 and then exits from the propeller nozzle exhaust section 76 of the turbocharged engine 10, also providing propulsive thrust. The HP turbine 28, LP turbine 30, and injector exhaust nozzle section 32 at least partially define a hot gas path 78 for directing combustion gas 66 through the turbocharged engine 16.

[0041] Controller 90 communicates with turbine engine 10 to control various aspects of turbine engine 10. For example, controller 90 communicates bidirectionally with turbine engine 10 to receive signals from various sensors and control systems of turbine engine 10 and to control components of turbine engine 10, as described in further detail below. Controller 90 or components thereof may be located on turbine engine 10, on the aircraft, or remotely from turbine engine 10 and each of the aircraft. Controller 90 may be a Full Authority Digital Engine Control (FADEC) system that controls various aspects of turbine engine 10.

[0042] The controller 90 may be a standalone controller or part of an engine controller to operate various systems of the turbine engine 10. In this embodiment, the controller 90 is a computing device having one or more processors and memory. The one or more processors may be any suitable processing device, including but not limited to microprocessors, microcontrollers, integrated circuits, logic devices, programmable logic controllers (PLCs), application-specific integrated circuits (ASICs), or field-programmable gate arrays (FPGAs). The memory may include one or more computer-readable media, including but not limited to non-transient computer-readable media, computer-readable non-volatile media (e.g., flash memory), RAM, ROM, hard disk drives, flash drives, or other memory devices.

[0043] The memory may store information accessible to one or more processors, including computer-readable instructions executable by one or more processors. Instructions may be any set or sequence of instructions that, when executed by one or more processors, cause one or more processors and controller 90 to perform operations. Controller 90, and more specifically, one or more processors, are programmed or configured to perform these operations, such as those discussed further below. In some embodiments, instructions may be executed by one or more processors to cause one or more processors to perform any operations and functions configured for controller 90, as described further below. Instructions may be software written in any suitable programming language or implemented in hardware. Additionally or alternatively, instructions may be executed on the processor in logically or virtually separate threads. The memory may also store data accessible to one or more processors.

[0044] The techniques discussed herein relate to computer-based systems and actions taken by computer-based systems, as well as information sent to and from computer-based systems. Those skilled in the art will recognize that the inherent flexibility of computer-based systems allows for a wide variety of possible configurations, combinations, and divisions of tasks and functions between and within components. For example, the processes discussed herein can be implemented using a single computing device or multiple computing devices working in combination. Databases, memory, instructions, and applications can be implemented on a single system or distributed across multiple systems. Distributed components can operate sequentially or in parallel.

[0045] Figure 1 The turbine engine 10 shown is merely an example. In other exemplary embodiments, the turbine engine 10 may have any other suitable configuration. For example, in other exemplary embodiments, the thruster 38 may be configured in any other suitable manner (e.g., as a fixed-pitch thruster) and may also be supported using any other suitable thruster frame configuration. Furthermore, in other exemplary embodiments, any other suitable number or configuration of compressors, turbines, shafts, or combinations thereof may be provided. In still other exemplary embodiments, aspects of this disclosure may be incorporated into any other suitable turbine engine, such as a turbofan engine, propeller fan engine, turbojet engine, or turboprop engine.

[0046] Figure 2 It is part of the gearbox assembly 46 and lubrication system 100 according to this disclosure. Figure 1 A schematic axial end cross-section view taken at detail 2-2. (See also...) Figure 2As shown, the gearbox assembly 46 includes a gear assembly 47 having a plurality of gears 49. The gears 49 mesh with each other at a meshing portion 51. At least one of the plurality of gears 49 includes one or more bearings 53 disposed in at least one of the plurality of gears 49, such that at least one of the plurality of gears 49 rotates relative to the one or more bearings 53. In this embodiment, the one or more bearings 53 are roller bearings. The gear assembly 47 also includes a planetary carrier 55. The gearbox assembly 46 includes a housing 57 that surrounds at least a portion of the gear assembly 47.

[0047] The gear assembly 47 includes a plurality of gears 49, including a first gear 49a, a plurality of second gears 49b, and a third gear 49c. Figure 2 In this configuration, the first gear 49a is a sun gear, the second gear 49b is a planetary gear, and the third gear 49c is a ring gear. Gear assembly 47 is a star-shaped or rotating ring gear assembly (e.g., the third gear 49c rotates while the planet carrier 55...). Figure 2 (Illustrated schematically) is fixed and stationary. In this arrangement, the thruster 38 ( Figure 1 The third gear 49c is driven by the third gear 49c. Thus, the third gear 49c is the output of the gear assembly 47. Although the gear assembly 47 is shown as a planetary gear assembly configuration, the gear assembly 47 can include any type of gear assembly configuration for transmitting power and torque from the input to the output.

[0048] The input shaft is connected to the first gear 49a. The input shaft is connected to the turbine section 27 of the turbine engine 10. Figure 1 For example, LP axis 36 ( Figure 1 ) is the input axis. In some embodiments, HP axis 34 ( Figure 1 The input shaft is located radially outside the first gear 49a. Meshing into it are multiple second gears 49b, which are connected and supported by a planet carrier 55 (shown schematically). The first gear 49a and the corresponding second gears 49b mesh at meshing portion 51. The planet carrier 55 supports and constrains the multiple second gears 49b, allowing them to rotate about their respective axes without rotating around the periphery of the first gear 49a. Meshing radially outside the multiple second gears 49b is a third gear 49c, which is a ring gear. The third gear 49c is connected to the pusher 38 via an output shaft. Figure 1 ), and rotate to drive thruster 38 (see Figure 1 It rotates around the longitudinal centerline axis 12. For example, the thruster shaft 45 is the output shaft.

[0049] In operation, the input shaft (e.g., LP shaft 36 or HP shaft 34) rotates, causing the first gear 49a to rotate. The first gear 49a meshes with a plurality of second gears 49b at the meshing portion 51, causing the plurality of second gears 49b to rotate. A bearing 53 is disposed within the plurality of second gears 49b and connected to the planetary carrier 55, causing the plurality of second gears 49b to rotate relative to the bearing 53. As described above, in Figure 2 In some embodiments, the third gear 49c rotates. In some embodiments, the third gear 49c is stationary, and a plurality of second gears 49b rotate relative to the longitudinal centerline axis 12, such that the plurality of second gears 49b are the output of the gearbox assembly 46.

[0050] The lubrication system 100 includes a lubricant tank 102, a lubricant pump 104, and one or more lubricant supply lines 106. The lubricant tank 102 includes a container, reservoir, or oil pan for storing lubricant (e.g., oil), and supplies lubricant to the turbine engine 10 via one or more lubricant supply lines 106. Figure 1 ) or gearbox assembly 46. Lubricant pump 104 is in fluid communication with lubricant tank 102 and one or more lubricant supply lines 106. Although the lubrication system 100 described herein is used to transfer power and torque from turbocharged engine 16 ( Figure 1 ) is transmitted to fan 38 ( Figure 1 The power gearbox is a type of gearbox, but the lubrication system 100 can be used for other types of gearboxes, including, for example, accessory gearbox assemblies.

[0051] The lubrication system 100 includes a gearbox lubrication system 108. The gearbox lubrication system 108 supplies lubricant to the gearbox assembly 46 to lubricate the gear assembly 47. Specifically, the gearbox lubrication system 108 supplies lubricant to at least one of the meshing portions 51 of a plurality of gears 49 or bearings 53. The gearbox lubrication system 108 includes one or more primary gearbox lubricant supply lines 110 and one or more secondary gearbox lubricant supply lines 112.

[0052] The primary gearbox lubricant supply line 110 is in fluid communication with one or more lubricant supply lines 106 and the gearbox assembly 46 for supplying lubricant from the lubricant tank 102 to the gearbox assembly 46. In some embodiments, the primary gearbox lubricant supply line 110 is fluidly coupled to the lubricant supply line 106. In some embodiments, the primary gearbox lubricant supply line 110 is embodied as a part of the lubricant supply line 106 (e.g., as a branch of the lubricant supply line 106).

[0053] One or more secondary gearbox lubricant supply lines 112 are in fluid communication with lubricant supply lines 106 and gearbox assembly 46 for supplying lubricant from lubricant tank 102 to gearbox assembly 46. In some embodiments, the secondary gearbox lubricant supply lines 112 are fluidly coupled to lubricant supply lines 106. In some embodiments, the secondary gearbox lubricant supply lines 112 are embodied as a portion of lubricant supply lines 106 (e.g., as a branch of lubricant supply lines 106).

[0054] The gearbox lubrication system 108 also includes one or more gearbox lubricant return lines 114, one or more gearbox lubricant injectors 116, and an oil pan 118. The gearbox lubricant return lines 114 are in fluid communication with the gearbox assembly 46 and the lubricant tank 102 for returning lubricant discharged from the gear assembly 47 (e.g., meshing portion 51 or bearing 53) to the lubricant tank 102.

[0055] Gearbox lubricant injector 116 is in fluid communication with primary gearbox lubricant supply line 110 and secondary gearbox lubricant supply line 112 to inject lubricant into gear assembly 47. Specifically, gearbox lubricant injector 116 is positioned to inject lubricant into at least one of the meshing portions 51 or to inject lubricant into bearing 53. For example, one or more gearbox lubricant injectors 116 may be positioned to inject lubricant into meshing portions 51, and one or more gearbox lubricant injectors 116 may be positioned to inject lubricant into bearing 53.

[0056] The gearbox lubricant injector 116 includes one or more primary gearbox lubricant injectors 116a in fluid communication with the primary gearbox lubricant supply line 110 and one or more secondary gearbox lubricant injectors 116b in fluid communication with the secondary gearbox lubricant supply line 112. In some embodiments, the primary gearbox lubricant injectors 116a and the secondary gearbox lubricant injectors 116b are the same size (e.g., the same diameter). In some embodiments, the primary gearbox lubricant injectors 116a and the secondary gearbox lubricant injectors 116b are different sizes (e.g., different diameters).

[0057] The oil pan 118 is a reservoir within the housing 57 for collecting lubricant discharged from the gear assembly 47 or its bearing 53. The oil pan 118 is in fluid communication with the gearbox lubricant return line 114 for discharging lubricant from the oil pan 118. Thus, the gearbox lubrication system 108 includes the oil pan 118.

[0058] In operation, the lubricant pump 104 pumps lubricant from the lubricant tank 102 to the turbine engine 10 via one or more lubricant supply lines 106. Figure 1The lubrication system 100 supplies lubricant to one or more rotating components of the turbine engine 10 or gearbox assembly 47, or pumps lubricant to the gearbox assembly 46, to lubricate one or more rotating components or gearbox assembly 47. One or more primary gearbox lubricant supply lines 110 and one or more secondary gearbox lubricant supply lines 112 direct lubricant to the gearbox assembly 47 (e.g., to the meshing part 51 or bearing 53). Specifically, primary gearbox lubricant injectors 116a and secondary gearbox lubricant injectors 116b inject lubricant into the gearbox assembly 47. The lubrication system 100 supplies lubricant to the turbine engine 10 or gearbox assembly 46 at a given mass flow rate. Figure 2 In one embodiment, the lubrication system 100 adjusts the mass flow rate of the gearbox assembly 46 based on the operating conditions of the turbine engine 10, as described in further detail below.

[0059] Lubricant is discharged from gear assembly 47 into oil pan 118. Gearbox lubricant return line 114 guides lubricant from oil pan 118 back to lubricant tank 102. For example, lubricant pump 104 (or a separate pump) pumps lubricant through gearbox lubricant return line 114 and recirculates lubricant back to lubricant tank 102. In this way, lubricant can be reused to lubricate the various gears 49 of gear assembly 47 (e.g., meshing elements 51), bearings 53, other components of gearbox assembly 46, or rotating components of turbine engine 10.

[0060] Figure 3 This is a schematic diagram of a lubrication system 100 for a turbine engine 10 according to this disclosure. Figure 3 As shown, one or more primary gearbox lubricant supply lines 110 include a first primary gearbox lubricant supply line 110a and a second primary gearbox lubricant supply line 110b. The first primary gearbox lubricant supply line 110a is in fluid communication with the meshing part 51 and is used to supply lubricant to the meshing part 51. The second primary gearbox lubricant supply line 110b is in fluid communication with the bearing 53 and is used to supply lubricant to the bearing 53.

[0061] One or more secondary gearbox lubricant supply lines 112 include a primary gearbox lubricant supply line 112a and a secondary gearbox lubricant supply line 112b. The primary gearbox lubricant supply line 112a is in fluid communication with the meshing part 51 and is used to supply lubricant to the meshing part 51. The secondary gearbox lubricant supply line 112b is in fluid communication with the bearing 53 and is used to supply lubricant to the bearing 53.

[0062] The gearbox lubrication system 108 includes one or more valves 120 disposed in one or more lubricant supply lines 106 for regulating the flow rate of lubricant to the gearbox assembly 46. Specifically, the one or more valves 120 include a primary valve 120a and a secondary valve 120b. The primary valve 120a is in fluid communication with the primary gearbox lubricant supply line 110. The secondary valve 120b is in fluid communication with the secondary gearbox lubricant supply line 112. A valve 120 may include at least one of the primary valve 120a or the secondary valve 120b. For example, a valve 120 may include only the primary valve 120a, only the secondary valve 120b, or both the primary valve 120b and the secondary valve 120b.

[0063] Primary valve 120a is a proportional control valve (PMV) that includes a primary valve member 122 that moves between a fully open position and a fully closed position to regulate the flow rate of lubricant through primary gearbox lubricant supply line 110. Primary valve 120a is a control valve controlled by controller 90. Specifically, primary valve 120a is in communication with controller 90 such that controller 90 controls primary valve 120a to move primary valve member 122 between a fully open position and a fully closed position, as described in further detail below. In some embodiments, primary valve 120a may be a passive valve, controlled by, for example, the pressure of the lubricant rather than controller 90. In the fully open position, primary valve 120a allows lubricant to flow completely through primary gearbox lubricant supply line 110. In the fully closed position, primary valve 120a prevents lubricant from flowing through primary gearbox lubricant supply line 110. The primary valve 120a can move the primary valve member 122 to any position between the fully open and fully closed positions to regulate the flow rate of lubricant through the primary gearbox lubricant supply line 110.

[0064] Secondary valve 120b is a shut-off valve (SOV) that includes a secondary valve member 124 that moves between an open position and a closed position. Secondary valve 120b is a control valve controlled by controller 90. Specifically, secondary valve 120b is in communication with controller 90 such that controller 90 controls secondary valve 120b to move secondary valve member 124 between an open position and a closed position. In some embodiments, secondary valve 120b may be a passive valve, controlled by, for example, the pressure of a lubricant rather than controller 90. In the open position, secondary valve 120b allows lubricant to flow completely through the secondary gearbox lubricant supply line 112. In the closed position, secondary valve 120b prevents lubricant from flowing through the secondary gearbox lubricant supply line 112.

[0065] The lubrication system 100 also includes a turbine engine lubrication system 130. The turbine engine lubrication system 130 supplies lubricant to one or more rotating components of the turbine engine 10. The one or more rotating components include an HP shaft 34 (…). Figure 1 ), LP axis 36 ( Figure 1 The turbine engine lubrication system 130 includes at least one of one or more turbine engine bearings or one or more dampers. The turbine engine lubrication system 130 includes one or more turbine engine lubricant supply lines 132 in fluid communication with one or more lubricant supply lines 106 and one or more rotating components of the turbine engine 10, for supplying lubricant from the lubricant tank 102 to the one or more rotating components. In some embodiments, the one or more turbine engine lubricant supply lines 132 are fluidly coupled to one or more lubricant supply lines 106. In some embodiments, the one or more turbine engine lubricant supply lines 132 are embodied as part of one or more lubricant supply lines 106 (e.g., as branches of one or more lubricant supply lines 106). The turbine engine lubrication system 130 may also include one or more turbine engine lubricant return lines 134 for returning lubricant to the lubricant tank 102 after lubricant has been discharged from the rotating components.

[0066] During operation, the lubrication system 100 regulates the flow rate of lubricant to the gearbox assembly 46. Specifically, the controller 90 adjusts the flow rate based on the gearbox inlet pressure (e.g., the pressure of the lubricant at the inlet of gearbox assembly 46), the turbine engine delivery pressure (e.g., the pressure of the lubricant flowing through the turbine engine lubrication system 130), and the turbine engine speed (e.g., the speed of the turbocharged engine 16). Figure 1 The primary valve 120a can be controlled based on at least one of the following: the speed of the gearbox assembly 46, the temperature of the lubricant in the gearbox assembly 46 (e.g., the temperature of the lubricant in the return reservoir of the gearbox assembly 46), or the input torque or output torque of the gearbox assembly 46. The controller 90 can also control the primary valve 120a based on the turbine engine power (e.g., the power output from the turbocharged engine 16), the turbine engine pressure (e.g., the pressure of the compressor section 21), or the gearbox lubricant temperature (e.g., the temperature of the lubricant in the gearbox assembly 46, for example, the temperature of the lubricant in the return reservoir of the gearbox assembly 46), or the input torque or output torque of the gearbox assembly 46. Figure 1 The primary valve 120a is controlled by at least one of the pressure in the compressor section 21 or the turbine engine temperature (e.g., the temperature in the compressor section 21).

[0067] The controller 90 controls the secondary valve 120b based on at least one of the turbine engine power, turbine engine speed, turbine engine pressure, or turbine engine temperature. The controller 90 may also control the secondary valve 120b based on at least one of the gearbox inlet pressure, turbine engine delivery pressure, turbine engine speed, gearbox lubricant temperature, or input torque or output torque of the gearbox assembly 46.

[0068] During high-power operation (e.g., when turbine engine speed or power exceeds a threshold), primary valve 120a is fully open and secondary valve 120b is open. Thus, lubricant is supplied at a first mass flow rate ( The lubricant flows through the primary gearbox lubricant supply line 110 to the gearbox assembly 46 (e.g., through the first primary gearbox lubricant supply line 110a to the engagement part 51, and through the second primary gearbox lubricant supply line 110b to the bearing 53). When the primary valve 120a is in the fully open position, the first mass flow rate is at its maximum. Similarly, the lubricant is supplied at a second mass flow rate ( The lubricant is supplied through the secondary gearbox lubricant supply line 112 (flowing to the meshing part 51 through the primary gearbox lubricant supply line 112a and to the bearing 53 through the secondary gearbox lubricant supply line 112b). When the secondary valve 120b is in the open position, the second mass flow rate ( ) is at its maximum. Thus, the lubricant flows at its maximum mass flow rate ( The flow rate is to the gearbox assembly 46, and the total mass flow rate is the first mass flow rate. ) and second mass flow rate ( The sum of ) when primary valve 120a is in the fully open position and secondary valve 120b is in the open position, the total mass flow rate ( (At maximum total mass flow rate)

[0069] During low-power or medium-power operation (e.g., when turbine engine speed or power is below a threshold), primary valve 120a is in a partially open position (e.g., between a fully open and fully closed position), and secondary valve 120b is in a closed position. Thus, in the partially open position, a first mass flow rate of lubricant (i.e., between the primary gearbox lubricant supply line 110 and the gearbox assembly 46) is... The second mass flow rate of lubricant through the secondary gearbox lubricant supply line 112 is less than the maximum first mass flow rate (and greater than zero). In the closed position, the second mass flow rate of lubricant through the secondary gearbox lubricant supply line 112 is less than the maximum first mass flow rate (and greater than zero). The total mass flow rate of lubricant to gearbox assembly 46 is zero. The total mass flow rate is less than the maximum total mass flow rate. When the primary valve 120a is in the partially open position, it directs a portion of the lubricant to the lubricant tank 102 and a portion to the gearbox assembly 46 via the primary gearbox lubricant supply line 110. When the secondary valve 120b is in the closed position, it directs lubricant to the lubricant tank 102 (via the gearbox lubricant return line 114) and prevents lubricant from flowing to the gearbox assembly 46 via the secondary gearbox lubricant supply line 112. Thus, when the secondary valve 120b is in the closed position, the total mass flow rate of lubricant to the gearbox assembly 46 is less than the maximum total mass flow rate. ) equals the first mass flow rate ( The controller 90 can control the primary valve 120a in low-power conditions by moving the primary valve member 122 between a fully open position and a fully closed position to regulate the flow rate of lubricant through the primary gearbox lubricant supply line 110. In some embodiments, either the primary valve 120a or the secondary valve 120b may be excluded. For example, the lubrication system 100 may include only the primary valve 120a and exclude the secondary valve 120b, such that the lubrication system 100 regulates the flow rate of lubricant using only the primary valve 120a. In some embodiments, the lubrication system 100 may include only the secondary valve 120b and exclude the primary valve 120a, such that the lubrication system 100 regulates the flow rate of lubricant using only the secondary valve 120b. In some embodiments, the lubrication system 100 regulates only the mass flow rate to the engagement portion 51, such that the mass flow rate to the bearing 53 is not regulated. In this way, the mass flow rate of lubricant to the bearing 53 is linearly related to the speed of the lubricant pump 104.

[0070] This disclosure provides a method for operating a turbine engine 10, including operating a lubrication system 100. Specifically, the method for operating the turbine engine 10 and the lubrication system 100 includes the operations described above.

[0071] Figure 4 It is according to another embodiment for a turbine engine 10 ( Figure 1 A schematic diagram of the lubrication system 200. The lubrication system 200 and... Figure 2 and Figure 3 The lubrication system 100 is substantially similar to that of the lubrication system 200. The same or similar reference numerals will be used for components of the lubrication system 200 that are identical or similar to those of the lubrication system 100 described above. The above description of these components also applies to this embodiment, and detailed descriptions of these components are omitted here.

[0072] The lubrication system 200 includes one or more valves 220. Each of the one or more valves 220 includes a primary valve 220a and a secondary valve 220b. Thus, the primary valve 220a and the secondary valve 220b... Figure 4 A single integral valve is formed in the middle. The primary valve 220a includes a primary valve component 222. The secondary valve 220b includes a secondary valve component 224. The primary valve 220a and the secondary valve 220b are respectively connected to... Figure 3 The primary valve 120a and secondary valve 120b operate similarly to regulate the mass flow rate of lubricant to gearbox assembly 46.

[0073] This disclosure provides a method for operating a turbine engine 10, including operating a lubrication system 200. Specifically, the method for operating the turbine engine 10 and the lubrication system 200 includes the operations described above.

[0074] Figure 5 According to another embodiment, it is used for Figure 1 A schematic diagram of the lubrication system 300 of the turbine engine 10. The lubrication system 300 and... Figure 2 and Figure 3 The lubrication system 100 is substantially similar to that of the lubrication system 300. The same or similar reference numerals will be used for components of the lubrication system 300 that are identical or similar to those of the lubrication system 100 described above. The above description of these components also applies to this embodiment, and detailed descriptions of these components are omitted here.

[0075] like Figure 5 As shown, turbine engine 10 ( Figure 1 This includes a motor 92. The motor 92 can be drivenly coupled to one of the shafts of the turbine engine 10, such as the LP shaft 36. Figure 1 ) or HP axis 34 ( Figure 1 Thus, turbine engine 10 is a hybrid turbine engine. Electric motor 92 can be used in many different power configurations.

[0076] In one configuration, motor 92 can operate as a generator configured to draw mechanical power from turbine engine 10 (e.g., from LP shaft 36 or HP shaft 34). Motor 92 converts the mechanical power into electrical power. The mechanical power drawn from LP shaft 36 and converted into electrical power can be used to charge onboard energy storage devices (such as batteries), or alternatively, to provide power to another electrical device (such as an electric motor, electrical accessories on an aircraft, etc.).

[0077] In other forms, motor 92 can operate as an electric motor to power turbine engine 10 (e.g., LP shaft 36 or HP shaft 34) to supplement the power extracted by LP turbine 30 from combustion gases 66. In these forms, in various embodiments, motor 92 can be configured to provide a minimum of 10% supplemental thrust to turbine engine 10, a minimum of 20% supplemental thrust to turbine engine 10, and up to 40% supplemental thrust to turbine engine 10. In another form, motor 92 can be configured to drive 100% of the thrust from thruster section 14. The situation where motor 92 provides all power to thruster section 14 can include shutting down turbine engine 10. In a non-limiting example of turbine engine 10 shutdown, during or near landing, controller 90 can command turbocharger engine 16 to shut down and command motor 92 to drive further thrust requirements, such as power when thruster section 14 is configured to pitch backward to assist aircraft deceleration.

[0078] The lubrication system 300 includes an electric motor lubrication system 340 for supplying lubricant to the electric motor 92 to lubricate or cool one or more rotating components of the electric motor 92. The electric motor lubrication system 340 includes one or more primary electric motor lubricant supply lines 342 and one or more secondary electric motor lubricant supply lines 344 in fluid communication with the lubricant tank 102 and the electric motor 92. The electric motor 92 also includes one or more electric motor lubricant return lines 346 for returning lubricant from the electric motor 92 to the lubricant tank 102.

[0079] The motor lubrication system 340 is in fluid communication with the gearbox lubrication system 108. Specifically, the primary motor lubricant supply line 342 is in fluid communication with the primary gearbox lubricant supply line 110. The secondary motor lubricant supply line 344 is in fluid communication with the secondary gearbox lubricant supply line 112. The motor lubricant return line 346 is in fluid communication with the gearbox lubricant return line 114. Thus, one or more valves 120 can regulate the mass flow rate of lubricant to the motor 92, similar to how one or more valves 120 regulate the mass flow rate of lubricant to the gearbox assembly 46. In some embodiments, the motor lubrication system 340 may be directly fluidly connected to the lubricant tank 102 without being in fluid communication with the gearbox lubrication system 108. In these embodiments, one or more valves are disposed in at least one of the primary motor lubricant supply line 342 or the secondary motor lubricant supply line 344. Specifically, the primary valve 120a may be disposed in the primary motor lubricant supply line 342. The secondary valve 120b can be installed in the secondary motor lubricant supply line 344.

[0080] During operation, the lubrication system 300 supplies lubricant to the motor 92 at a certain mass flow rate. Figure 5 In this embodiment, the lubrication system 300 adjusts the mass flow rate of the motor 92 based on the operating conditions of the turbine engine 10. Specifically, as referred to above... Figure 3 The controller 90 controls the primary valve 120a and the secondary valve 120b to regulate the mass flow rate of the lubricant flowing to the motor 92.

[0081] This disclosure provides a method for operating a turbine engine 10, including operating a lubrication system 300. Specifically, the method for operating the turbine engine 10 and the lubrication system 300 includes the operations described above.

[0082] Figure 6 According to another embodiment, it is used for Figure 1 A schematic diagram of the lubrication system 400 of the turbine engine 10. The lubrication system 400 and... Figure 2The lubrication system 100 is substantially similar to that of the lubrication system 400. The same or similar reference numerals will be used for components of the lubrication system 400 that are identical or similar to those of the lubrication system 100 described above. The above description of these components also applies to this embodiment, and detailed descriptions of these components are omitted here.

[0083] like Figure 6 As shown, the turbine engine 10 includes one or more LP shaft oil pans 39 and one or more HP shaft oil pans 41. The LP shaft oil pan 39 is in fluid communication with the LP shaft bearing 37. The HP shaft oil pan 41 is in fluid communication with the HP shaft bearing 35. The LP shaft oil pan 39 collects lubricant discharged from the LP shaft bearing 37. The HP shaft oil pan 41 collects lubricant discharged from the HP shaft bearing 35.

[0084] The lubrication system 400 includes a turbine engine lubrication system 430, which includes a turbine engine lubricant supply line 132 and a turbine engine lubricant return line 134. The turbine engine lubricant supply line 132 includes one or more primary turbine engine lubricant supply lines 450 and one or more secondary turbine engine lubricant supply lines 452.

[0085] One or more primary turbine engine lubricant supply lines 450 include a first primary turbine engine lubricant supply line 450a and a second primary turbine engine lubricant supply line 450b. The first primary turbine engine lubricant supply line 450a is in fluid communication with the LP shaft bearing 37 and is used to supply lubricant to the LP shaft bearing 37. The second primary turbine engine lubricant supply line 450b is in fluid communication with the HP shaft bearing 35 and is used to supply lubricant to the HP shaft bearing 35.

[0086] One or more secondary turbine engine lubricant supply lines 452 include a primary turbine engine lubricant supply line 452a and a secondary turbine engine lubricant supply line 452b. The primary turbine engine lubricant supply line 452a is in fluid communication with the LP shaft bearing 37. Figure 1 This is used to supply lubricant to the LP shaft bearing 37. The second-stage turbine engine lubricant supply line 452b is in fluid communication with the HP shaft bearing 35. Figure 1 ), used to supply lubricant to HP shaft bearing 35.

[0087] The turbine engine lubrication system 430 includes one or more valves 460 disposed in one or more lubricant supply lines 106 for regulating the flow rate of lubricant to the turbine engine 10 (e.g., LP shaft bearing 37 and HP shaft bearing 35). Specifically, the one or more valves 460 include a primary valve 460a and a secondary valve 460b. The primary valve 460a is in fluid communication with the primary turbine engine lubricant supply line 450. The secondary valve 460b is in fluid communication with the secondary turbine engine lubricant supply line 452. A valve 460 may include at least one of the primary valve 460a or the secondary valve 460b. For example, a valve 460 may include only the primary valve 460a, only the secondary valve 460b, or both the primary valve 460a and the secondary valve 460b.

[0088] Primary valve 460a is a proportional control valve (PMV) that includes a primary valve member 462 that moves between a fully open position and a fully closed position to regulate the flow rate of lubricant through primary turbine engine lubricant supply line 450. Primary valve 460a is a control valve controlled by controller 90. Specifically, primary valve 460a communicates with controller 90 such that controller 90 controls primary valve 460a to move primary valve member 462 between a fully open position and a fully closed position, as described in further detail below. In some embodiments, primary valve 460a may be a passive valve, controlled by, for example, the pressure of the lubricant rather than by controller 90. In the fully open position, primary valve 460a allows lubricant to flow completely through primary turbine engine lubricant supply line 450. In the fully closed position, primary valve 460a prevents lubricant from flowing through primary turbine engine lubricant supply line 450. The primary valve 460a allows the primary valve member 462 to move at any position between the fully open and fully closed positions to regulate the flow of lubricant through the primary turbine engine lubricant supply line 450.

[0089] Secondary valve 460b is a shut-off valve (SOV) that includes a secondary valve member 464 that moves between an open position and a closed position. Secondary valve 460b is a control valve controlled by controller 90. Specifically, secondary valve 460b communicates with controller 90 such that controller 90 controls secondary valve 460b to move secondary valve member 464 between an open position and a closed position. In some embodiments, secondary valve 460b may be a passive valve, controlled by, for example, the pressure of a lubricant rather than by controller 90. In the open position, secondary valve 460b allows lubricant to flow completely through the secondary turbine engine lubricant supply line 452. In the closed position, secondary valve 460b prevents lubricant from flowing through the secondary turbine engine lubricant supply line 452.

[0090] The turbine engine lubricant return line 134 is in fluid communication with the LP shaft bearing 37 and the HP shaft bearing 35, for returning lubricant to the lubricant tank 102. Specifically, the LP shaft oil pan 39 and the HP shaft oil pan 41 are in fluid communication with the turbine engine lubricant return line 134, for returning lubricant from the LP shaft oil pan 39 and the HP shaft oil pan 41 to the lubricant tank 102.

[0091] During operation, the lubrication system 400 adjusts the flow rate of lubricant to the turbine engine 10, similar to the above-mentioned... Figure 3 The details describe the adjustment of the lubricant flow rate to gearbox assembly 46.

[0092] During high-power operation (e.g., when the rotational speed of at least one of the HP shaft 34 or LP shaft 36 exceeds a threshold), the primary valve 460a is in the fully open position, and the secondary valve 460b is in the open position. Thus, the lubricant flows at a first mass flow rate ( The lubricant flows to the turbine engine 10 via the primary turbine engine lubricant supply line 450 (e.g., to the LP shaft bearing 37 via the first primary turbine engine lubricant supply line 450a, and to the HP shaft bearing 35 via the second primary turbine engine lubricant supply line 450b). When the primary valve 460a is in the fully open position, the first mass flow rate is at its maximum. Similarly, the lubricant is supplied at a second mass flow rate ( The second mass flow rate is supplied via secondary turbine engine lubricant supply line 452 (via primary turbine engine lubricant supply line 452a to LP shaft bearing 37, and via secondary turbine engine lubricant supply line 452b to HP shaft bearing 35). When secondary valve 460b is in the open position, the second mass flow rate ( The lubricant is at its maximum value. In this way, the lubricant is at its maximum mass flow rate ( The flow is directed to turbine engine 10, and this total mass flow rate is the first mass flow rate ( ) and second mass flow rate ( The sum of ) when primary valve 460a is in the fully open position and secondary valve 460b is in the open position, the total mass flow rate ( () represents the maximum total mass flow rate.

[0093] During low-power or medium-power operation (e.g., when the rotational speed of at least one of the HP shaft 34 or LP shaft 36 is less than a threshold), the primary valve 460a is in a partially open position (e.g., between a fully open and fully closed position), and the secondary valve 460b is in a closed position. Thus, in the partially open position, a first mass flow rate of lubricant to the turbine engine 10 via the primary turbine engine lubricant supply line 450 (…) The second mass flow rate of lubricant through the secondary turbine engine lubricant supply line 452 is less than the maximum first mass flow rate (and greater than zero). In the closed position, the second mass flow rate of lubricant through the secondary turbine engine lubricant supply line 452 is less than the maximum first mass flow rate (and greater than zero). The total mass flow rate of lubricant to turbine engine 10 is zero. The total mass flow rate is less than the maximum total mass flow rate. When the primary valve 460a is in the partially open position, it directs a portion of the lubricant to the lubricant tank 102 (e.g., via the turbine engine lubricant return line 134) and a portion to the turbine engine 10 via the primary turbine engine lubricant supply line 450. When the secondary valve 460b is in the closed position, it directs lubricant to the lubricant tank 102 (via the turbine engine lubricant return line 134) and prevents lubricant from flowing to the turbine engine 10 via the turbine engine lubricant supply line 452. Thus, when the secondary valve 460b is in the closed position, the total mass flow rate of lubricant to the turbine engine 10 is less than the maximum total mass flow rate. ) equals the first mass flow rate ( During low-power conditions, controller 90 can control primary valve 460a to regulate the flow of lubricant through primary turbine engine lubricant supply line 450 by moving primary valve member 462 between a fully open position and a fully closed position. In some embodiments, either primary valve 460a or secondary valve 460b may be excluded. For example, lubrication system 400 may include only primary valve 460a and exclude secondary valve 460b, such that lubrication system 400 regulates the flow of lubricant to turbine engine 10 using only primary valve 460a. In some embodiments, lubrication system 400 may include only secondary valve 460b and exclude primary valve 460a, such that lubrication system 400 regulates the flow of lubricant using only primary valve 460b.

[0094] Therefore, lubrication systems 100, 200, 300, and 400, by regulating the flow of lubricant to gearbox assembly 46, provide a certain amount of lubricant and lubricant temperature for all operating conditions of gearbox assembly 46 throughout the entire operating cycle of turbine engine 10, in order to reduce damage to gear assembly 47, while minimizing gearbox losses (e.g., due to friction and wind resistance of the multiple gears 49) and maximizing gear efficiency. Similarly, lubrication system 300, by regulating the flow of lubricant to motor 92, reduces damage to the rotating parts of motor 92 throughout the entire operating cycle of turbine engine 10, while minimizing losses of motor 92 and maximizing motor efficiency. The lubrication system 400 reduces damage to the LP shaft bearing 37 or HP shaft bearing 35 (or LP shaft damper or HP shaft damper) throughout the entire operating cycle of the turbine engine 10 by regulating the flow of lubricant to bearings 35 and 37 (or dampers), while minimizing losses and maximizing the efficiency of bearings 35 and 37. Furthermore, having two lubricant supply lines allows for linear scaling of lubricant flow with engine speed by reducing the number of orifices (e.g., total orifice area) when one line is closed, while also allowing for lubricant regulation.

[0095] This disclosure provides a method for operating a turbine engine 10, including operating a lubrication system 400. Specifically, the method for operating the turbine engine 10 and the lubrication system 400 includes the operations described above.

[0096] Further aspects of this disclosure are provided by the subject matter of the following clauses.

[0097] A turbocharged engine includes a turbocharged engine comprising a compressor section, a combustor, and a turbine section, the turbocharged engine having an input shaft connecting the compressor section to the turbine section; a gearbox assembly including a gear assembly having a plurality of gears; a propeller having an output shaft drivably connected to the input shaft via the gear assembly; and a lubrication system comprising: a lubricant tank storing lubricant therein; one or more primary gearbox lubricant supply lines connected to the input shaft. The lubricant tank and the gearbox assembly are in fluid communication; one or more secondary gearbox lubricant supply lines are in fluid communication with the lubricant tank and the gearbox assembly; and a lubricant pump is used to supply lubricant from the lubricant tank to the gearbox assembly through the one or more primary gearbox lubricant supply lines and the one or more secondary gearbox lubricant supply lines, the lubrication system regulating the mass flow rate of the lubricant to the gearbox assembly through at least one of the one or more primary gearbox lubricant supply lines or the one or more secondary gearbox lubricant supply lines.

[0098] The turbine engine according to the foregoing clause further includes an electric motor, the electric motor being drivably connected to the input shaft, wherein the lubrication system further includes: one or more primary motor lubricant supply lines, the one or more primary motor lubricant supply lines being in fluid communication with the lubricant tank and the electric motor; and one or more secondary motor lubricant supply lines, the one or more secondary motor lubricant supply lines being in fluid communication with the lubricant tank and the electric motor, the lubricant pump supplying lubricant from the lubricant tank to the electric motor through the one or more primary motor lubricant supply lines and the one or more secondary motor lubricant supply lines, the lubrication system regulating the mass flow rate of the lubricant to the electric motor through at least one of the one or more primary motor lubricant supply lines or the one or more secondary motor lubricant supply lines.

[0099] The turbine engine according to any one of the preceding clauses further includes one or more shaft bearings supporting rotation of the input shaft, wherein the lubrication system further includes: one or more primary turbine engine lubricant supply lines in fluid communication with the lubricant tank and the one or more shaft bearings; and one or more secondary turbine engine lubricant supply lines in fluid communication with the lubricant tank and the one or more shaft bearings, wherein a lubricant pump supplies lubricant from the lubricant tank to the one or more shaft bearings through the one or more primary turbine engine lubricant supply lines and the one or more secondary turbine engine lubricant supply lines, and the lubrication system regulates the mass flow rate of the lubricant to the turbine engine through at least one of the one or more primary turbine engine lubricant supply lines or the one or more secondary turbine engine lubricant supply lines.

[0100] According to any one of the preceding clauses, in the turbine engine, the plurality of gears mesh with each other at the meshing portion, and the one or more primary gearbox lubricant supply lines and the one or more secondary gearbox lubricant supply lines guide the lubricant to the meshing portion.

[0101] The turbine engine according to any one of the preceding clauses, wherein the one or more primary gearbox lubricant supply lines include a first primary gearbox lubricant supply line in fluid communication with the meshing portion.

[0102] The turbine engine according to any one of the preceding clauses, wherein the one or more secondary gearbox lubricant supply lines include a primary gearbox lubricant supply line in fluid communication with the meshing portion.

[0103] According to any one of the preceding clauses, the gear assembly of the turbine engine includes one or more bearings, and the one or more primary gearbox lubricant supply lines and the one or more secondary gearbox lubricant supply lines guide the lubricant to the one or more bearings.

[0104] According to any one of the preceding clauses, the turbine engine, the one or more primary gearbox lubricant supply lines include a second primary gearbox lubricant supply line in fluid communication with the one or more bearings.

[0105] According to any one of the preceding clauses, the turbine engine, the one or more secondary gearbox lubricant supply lines include a second-stage gearbox lubricant supply line in fluid communication with the one or more bearings.

[0106] According to any one of the preceding clauses, the lubrication system of the turbine engine further includes one or more valves disposed in at least one of the primary gearbox lubricant supply lines or the secondary gearbox lubricant supply lines for regulating the mass flow rate of the lubricant to the gearbox assembly.

[0107] According to any one of the preceding clauses, the turbine engine, the one or more valves include a primary valve disposed in one or more primary gearbox lubricant supply lines for regulating the mass flow rate of the lubricant to the gearbox assembly through the one or more primary gearbox lubricant supply lines.

[0108] In the turbine engine according to any one of the preceding clauses, the primary valve is a proportional control valve, the primary valve including a primary valve member that moves between a fully open position and a fully closed position to regulate the mass flow rate of the lubricant through the one or more primary gearbox lubricant supply lines.

[0109] According to any one of the preceding clauses, the turbine engine, the one or more valves include secondary valves disposed in the one or more secondary gearbox lubricant supply lines for regulating the mass flow rate of the lubricant to the gearbox assembly through the one or more secondary gearbox lubricant supply lines.

[0110] According to any one of the preceding clauses, the secondary valve of the turbine engine is a shut-off valve, the secondary valve including a secondary valve member that moves between an open position and a closed position to open or close the lubricant through the one or more secondary gearbox lubricant supply lines.

[0111] A turbocharged engine includes a turbocharged engine comprising a compressor section, a combustor, and a turbine section, the turbocharged engine having an input shaft connecting the compressor section to the turbine section; a gearbox assembly including a gear assembly having a plurality of gears meshing with each other at a meshing portion; a propeller having an output shaft drivably connected to the input shaft via the gear assembly; and a lubrication system comprising: a lubricant tank storing lubricant therein; one or more primary gearbox lubricant supply lines in fluid communication with the lubricant tank and the gearbox assembly, the one or more primary gearbox lubricant supply lines guiding the lubricant to the meshing portion; and one or more secondary gearbox lubricants... The lubricant supply lines include one or more secondary gearbox lubricant supply lines in fluid communication with the lubricant tank and the gearbox assembly, the one or more secondary gearbox lubricant supply lines guiding the lubricant to the engagement portion; one or more valves disposed in at least one of the one or more primary gearbox lubricant supply lines or the one or more secondary gearbox lubricant supply lines; and a lubricant pump for supplying the lubricant from the lubricant tank to the engagement portion through the one or more primary gearbox lubricant supply lines and the one or more secondary gearbox lubricant supply lines, the lubrication system controlling the one or more valves to regulate the mass flow rate of the lubricant to the engagement portion through at least one of the one or more primary gearbox lubricant supply lines or the one or more secondary gearbox lubricant supply lines.

[0112] The turbine engine according to any one of the preceding clauses further includes an electric motor, the electric motor being drivably connected to the input shaft, wherein the lubrication system further includes: one or more primary motor lubricant supply lines in fluid communication with the lubricant tank and the electric motor; and one or more secondary motor lubricant supply lines in fluid communication with the lubricant tank and the electric motor, the lubricant pump supplying lubricant from the lubricant tank to the electric motor through the one or more primary motor lubricant supply lines and the one or more secondary motor lubricant supply lines, the lubrication system regulating the mass flow rate of the lubricant to the electric motor through at least one of the one or more primary motor lubricant supply lines or the one or more secondary motor lubricant supply lines.

[0113] The turbine engine according to any one of the preceding clauses further includes one or more shaft bearings supporting rotation of the input shaft, and the lubrication system further includes: one or more primary turbine engine lubricant supply lines in fluid communication with the lubricant tank and the one or more shaft bearings; and one or more secondary turbine engine lubricant supply lines in fluid communication with the lubricant tank and the one or more shaft bearings, the lubricant pump supplying lubricant from the lubricant tank to the one or more shaft bearings through the one or more primary turbine engine lubricant supply lines and the one or more secondary turbine engine lubricant supply lines, and the lubrication system regulating the mass flow rate of the lubricant to the turbine engine through at least one of the one or more primary turbine engine lubricant supply lines or the one or more secondary turbine engine lubricant supply lines.

[0114] According to any one of the preceding clauses, the gear assembly of the turbine engine includes one or more bearings, and the one or more primary gearbox lubricant supply lines and the one or more secondary gearbox lubricant supply lines guide the lubricant to the one or more bearings.

[0115] According to any one of the preceding clauses, the turbine engine, the one or more valves include a primary valve disposed in one or more primary gearbox lubricant supply lines for regulating the mass flow rate of the lubricant to the meshing portion through the one or more primary gearbox lubricant supply lines.

[0116] According to any one of the preceding clauses, the turbine engine, the one or more valves include secondary valves disposed in one or more secondary gearbox lubricant supply lines for regulating the mass flow rate of the lubricant to the meshing portion through the one or more secondary gearbox lubricant supply lines.

[0117] A method of operating a turbine engine according to any one of the preceding clauses, the method comprising supplying lubricant from a lubricant tank to a gearbox assembly via one or more primary gearbox lubricant supply lines and one or more secondary gearbox lubricant supply lines, and regulating the mass flow rate of the lubricant to the gearbox assembly via at least one of the one or more primary gearbox lubricant supply lines or one or more secondary gearbox lubricant supply lines.

[0118] The method described in the foregoing clause further includes supplying lubricant to the motor from the lubricant tank through one or more primary motor lubricant supply lines and one or more secondary motor lubricant supply lines, and adjusting the mass flow rate of the lubricant to the motor through at least one of the one or more primary motor lubricant supply lines or the one or more secondary motor lubricant supply lines.

[0119] The method according to any one of the preceding clauses further includes supplying lubricant from a lubricant tank to one or more shaft bearings of a turbine engine through one or more primary turbine engine lubricant supply lines and one or more secondary turbine engine lubricant supply lines, and adjusting the mass flow rate of lubricant to the turbine engine through at least one of the one or more primary turbine engine lubricant supply lines or one or more secondary turbine engine lubricant supply lines.

[0120] The method according to any one of the preceding clauses further includes guiding lubricant to the meshing portion of the plurality of gears through the one or more primary gearbox lubricant supply lines and the one or more secondary gearbox lubricant supply lines.

[0121] The method according to any one of the preceding clauses further includes guiding lubricant to the meshing portion through a first primary gearbox lubricant supply line among the one or more primary gearbox lubricant supply lines.

[0122] The method according to any one of the preceding clauses further includes guiding lubricant to the meshing portion through a primary gearbox lubricant supply line in one or more secondary gearbox lubricant supply lines.

[0123] The method according to any one of the preceding clauses further includes directing lubricant to one or more bearings of the gearbox assembly via one or more primary gearbox lubricant supply lines and one or more secondary gearbox lubricant supply lines.

[0124] The method according to any one of the preceding clauses further includes directing lubricant to one or more bearings via a second primary gearbox lubricant supply line in one or more primary gearbox lubricant supply lines.

[0125] The method according to any one of the preceding clauses further includes directing lubricant to one or more bearings via a secondary gearbox lubricant supply line in one or more secondary gearbox lubricant supply lines.

[0126] The method according to any one of the preceding clauses further includes using one or more valves disposed in at least one of one or more primary gearbox lubricant supply lines or one or more secondary gearbox lubricant supply lines to regulate the mass flow rate of lubricant to the gearbox assembly.

[0127] The method according to any one of the preceding clauses further includes adjusting the mass flow rate of lubricant to the gearbox assembly using a primary valve in one or more valves in one or more primary gearbox lubricant supply lines.

[0128] According to any one of the preceding clauses, the primary valve is a proportional regulating valve including a primary valve component, and the method further includes moving the primary valve component between a fully open position and a fully closed position to regulate the mass flow rate of lubricant through one or more primary gearbox lubricant supply lines.

[0129] The method according to any one of the preceding clauses further includes adjusting the mass flow rate of lubricant to the gearbox assembly using a secondary valve in one or more valves in one or more secondary gearbox lubricant supply lines.

[0130] According to any one of the preceding clauses, the secondary valve is a shut-off valve including a secondary valve component, and the method further includes moving the secondary valve component between an open position and a closed position to open or close the lubricant supply line through one or more secondary gearbox lubricant supply lines.

[0131] A turbocharged engine includes a turbocharged engine comprising a compressor section, a combustor, and a turbine section, the turbocharged engine having an input shaft connecting the compressor section to the turbine section; a propeller having an output shaft drivably connected to the input shaft; an electric motor drivably connected to the input shaft; and a lubrication system including a lubricant tank storing lubricant therein; one or more primary motor lubricant supply lines in fluid communication with the lubricant tank and the electric motor; one or more secondary motor lubricant supply lines in fluid communication with the lubricant tank and the electric motor; and a lubricant pump for supplying lubricant from the lubricant tank to the electric motor via the one or more primary motor lubricant supply lines and the one or more secondary motor lubricant supply lines, the lubrication system regulating the mass flow rate of lubricant to the electric motor via at least one of the one or more primary motor lubricant supply lines or the one or more secondary motor lubricant supply lines.

[0132] According to any one of the preceding clauses, the lubrication system of the turbine engine further includes one or more valves disposed in at least one of the primary motor lubricant supply lines or the secondary motor lubricant supply lines for regulating the mass flow rate of lubricant to the motor.

[0133] The turbine engine according to any one of the preceding clauses, the one or more valves include primary valves disposed in the one or more primary motor supply lines for regulating the mass flow rate of lubricant to the motor through the one or more primary motor lubricant supply lines.

[0134] According to any one of the preceding clauses, the primary valve of the turbine engine is a proportional control valve, the primary valve including a primary valve member that moves between a fully open position and a fully closed position to regulate the mass flow rate of lubricant through one or more primary motor lubricant supply lines.

[0135] According to any one of the preceding clauses, the turbine engine, the one or more valves include secondary valves disposed in the one or more secondary motor lubricant supply lines for regulating the mass flow rate of lubricant to the motor through the one or more secondary motor lubricant supply lines.

[0136] According to any one of the preceding clauses, the secondary valve of the turbine engine is a shut-off valve, the secondary valve including a secondary valve member that moves between an open position and a closed position to open or close the lubricant supply line through one or more secondary motor lubricant lines.

[0137] A method of operating a turbine engine according to any one of the preceding clauses, the method comprising supplying lubricant from a lubricant tank to the motor via one or more primary motor lubricant supply lines and one or more secondary motor lubricant supply lines, and regulating the mass flow rate of the lubricant to the motor via at least one of the one or more primary motor lubricant supply lines or one or more secondary motor lubricant supply lines.

[0138] The method according to any one of the preceding clauses further includes adjusting the mass flow rate of lubricant to the motor using one or more valves disposed in at least one of one or more primary motor lubricant supply lines or one or more secondary motor lubricant supply lines.

[0139] The method according to any one of the preceding clauses further includes adjusting the mass flow rate of lubricant to the motor using a primary valve in one or more valves in one or more primary motor lubricant supply lines.

[0140] According to any one of the preceding clauses, the primary valve is a proportional regulating valve including a primary valve component, and the method further includes moving the primary valve component between a fully open position and a fully closed position to regulate the mass flow rate of lubricant through the one or more primary motor lubricant supply lines.

[0141] The method according to any one of the preceding clauses further includes adjusting the mass flow rate of the lubricant to the motor using a secondary valve in one or more valves in the one or more secondary motor lubricant supply lines.

[0142] According to any one of the preceding clauses, the secondary valve is a shut-off valve including a secondary valve component, and the method further includes moving the secondary valve component between an open position and a closed position to open or close the lubricant supply line through one or more secondary motor lubricant supply lines.

[0143] A turbine engine comprising a turbocharged engine including a compressor section, a combustor, and a turbine section, the turbocharged engine having an input shaft connecting the compressor section to the turbine section; a propeller having an output shaft drivably connected to the input shaft; one or more shaft bearings for supporting rotation of the input shaft; and a lubrication system including a lubricant tank therein for storing lubricant; one or more primary turbine engine lubricant supply lines in fluid communication with the lubricant tank and the one or more shaft bearings; one or more secondary turbine engine lubricant supply lines in fluid communication with the lubricant tank and the one or more shaft bearings; and a lubricant pump for supplying lubricant from the lubricant tank to the one or more shaft bearings via the one or more primary turbine engine lubricant supply lines and the one or more secondary turbine engine lubricant supply lines, the lubrication system regulating the mass flow rate of lubricant to the one or more shaft bearings via at least one of the one or more primary turbine engine lubricant supply lines or the one or more secondary turbine engine lubricant supply lines.

[0144] According to the preceding clause, the turbine engine includes a compressor section comprising a low-pressure compressor, a turbine section comprising a low-pressure turbine, and the turbine engine further includes a low-pressure shaft connecting the low-pressure compressor to the low-pressure turbine.

[0145] The turbine engine according to any one of the preceding clauses, wherein the compressor section includes a high-pressure compressor, the turbine section includes a high-pressure turbine, and the turbine engine further includes a high-pressure shaft connecting the high-pressure compressor to the high-pressure turbine.

[0146] In any of the preceding clauses, the input shaft of the turbine engine is either a low-pressure shaft or a high-pressure shaft.

[0147] The turbine engine according to any one of the preceding clauses, wherein the one or more shaft bearings include one or more low-pressure shaft bearings supporting the rotation of the low-pressure shaft, and the one or more primary turbine engine lubricant supply lines and the one or more secondary turbine engine lubricant supply lines guide lubricant to the one or more low-pressure shaft bearings.

[0148] The turbine engine according to any one of the preceding clauses, wherein the one or more shaft bearings include one or more high-pressure shaft bearings supporting the rotation of the high-pressure shaft, and the one or more primary turbine engine lubricant supply lines and the one or more secondary turbine engine lubricant supply lines guide lubricant to the one or more high-pressure shaft bearings.

[0149] The turbine engine according to any one of the preceding clauses, wherein the one or more primary turbine engine lubricant supply lines include a first primary turbine engine lubricant supply line in fluid communication with the low-pressure shaft bearing.

[0150] According to any one of the preceding clauses, the turbine engine has one or more secondary turbine engine lubricant supply lines including a primary turbine engine lubricant supply line in fluid communication with the low-pressure shaft bearing.

[0151] The turbine engine according to any one of the preceding clauses, wherein the one or more primary turbine engine lubricant supply lines include a second primary turbine engine lubricant supply line in fluid communication with the high-pressure shaft bearing.

[0152] The turbine engine according to any one of the preceding clauses, wherein the one or more secondary turbine engine lubricant supply lines include a second-stage turbine engine lubricant supply line in fluid communication with the one or more high-pressure shaft bearings.

[0153] According to any one of the preceding clauses, the lubrication system of the turbine engine further includes one or more valves disposed in at least one of the primary turbine engine lubricant supply lines or the secondary turbine engine lubricant supply lines for regulating the mass flow rate of lubricant to the one or more shaft bearings.

[0154] According to any one of the preceding clauses, the turbine engine, the one or more valves include primary valves disposed in the one or more primary turbine engine lubricant supply lines for regulating the mass flow rate of lubricant through the one or more primary turbine engine lubricant supply lines to the one or more shaft bearings.

[0155] According to any one of the preceding clauses, the primary valve of the turbine engine is a proportional control valve, the primary valve including a primary valve member that moves between a fully open position and a fully closed position to regulate the mass flow rate of lubricant through one or more primary turbine engine lubricant supply lines.

[0156] According to any one of the preceding clauses, the turbine engine, the one or more valves include secondary valves disposed in the one or more secondary turbine engine lubricant supply lines for regulating the mass flow rate of lubricant through the one or more secondary turbine engine lubricant supply lines to the one or more shaft bearings.

[0157] According to any of the preceding clauses, the secondary valve is a shut-off valve, the secondary valve including a secondary valve member that moves between an open position and a closed position to open or close the lubricant supply line through one or more secondary turbine engine lubricant supply lines.

[0158] A method of operating a turbine engine according to any one of the preceding clauses, the method comprising supplying lubricant from a lubricant tank to one or more shaft bearings via one or more primary turbine engine lubricant supply lines and one or more secondary turbine engine lubricant supply lines, and regulating the mass flow rate of the lubricant to one or more shaft bearings via at least one of the one or more primary turbine engine lubricant supply lines or one or more secondary turbine engine lubricant supply lines.

[0159] The method according to any one of the foregoing clauses further includes directing lubricant to one or more low-pressure shaft bearings of the one or more shaft bearings via the one or more primary turbine engine lubricant supply lines and the one or more secondary turbine engine lubricant supply lines.

[0160] The method according to any one of the foregoing clauses further includes guiding lubricant to one or more high-pressure shaft bearings of the one or more shaft bearings via the one or more primary turbine engine lubricant supply lines and the one or more secondary turbine engine lubricant supply lines.

[0161] The method according to any one of the preceding clauses further includes directing lubricant to one or more low-pressure shaft bearings via a first primary turbine engine lubricant supply line among one or more primary turbine engine lubricant supply lines.

[0162] The method according to any one of the preceding clauses further includes directing lubricant to one or more low-pressure shaft bearings through a primary turbine engine lubricant supply line in one or more secondary turbine engine lubricant supply lines.

[0163] The method according to any one of the foregoing clauses further includes directing lubricant to the one or more high-pressure shaft bearings via one or more second primary turbine engine lubricant supply lines from the one or more primary turbine engine lubricant supply lines.

[0164] The method according to any one of the preceding clauses further includes directing lubricant to the one or more high-pressure shaft bearings via one or more of the secondary turbine engine lubricant supply lines.

[0165] The method according to any one of the preceding clauses further includes using one or more valves disposed in at least one of one or more primary turbine engine lubricant supply lines or one or more secondary turbine engine lubricant supply lines to regulate the mass flow rate of lubricant to one or more shaft bearings.

[0166] The method according to any one of the preceding clauses further includes adjusting the mass flow rate of lubricant to the one or more shaft bearings using a primary valve of one or more valves in the one or more primary turbine engine lubricant supply lines.

[0167] According to any one of the preceding clauses, the primary valve is a proportional regulating valve including a primary valve component, and the method further includes moving the primary valve component between a fully open position and a fully closed position to regulate the mass flow rate of lubricant through the one or more primary turbine engine lubricant supply lines.

[0168] The method according to any one of the preceding clauses further includes adjusting the mass flow rate of lubricant to the one or more shaft bearings using a secondary valve of one or more valves in one or more secondary turbine engine lubricant supply lines.

[0169] According to any one of the preceding clauses, the secondary valve is a shut-off valve including a secondary valve member, and the method further includes moving the secondary valve member between an open position and a closed position to open or close the lubricant supply line through one or more secondary turbine engine lubricant supply lines.

[0170] While the foregoing description is directed to preferred embodiments of the present disclosure, other variations and modifications will be apparent to those skilled in the art and can be made without departing from the present disclosure. Furthermore, features described in connection with one embodiment of the present disclosure may be used in conjunction with other embodiments, even if not explicitly stated above.

Claims

1. A turbine engine, characterized in that, include: A turbocharged engine, the turbocharged engine including a compressor section, a combustor and a turbine section, the turbocharged engine having an input shaft connecting the compressor section to the turbine section; A gearbox assembly, the gearbox assembly including a gear assembly having a plurality of gears; A thruster having an output shaft that is drivably connected to an input shaft via the gear assembly; and Lubrication system, the lubrication system comprising: A lubricant tank, wherein the lubricant is stored; One or more primary gearbox lubricant supply lines, wherein the one or more primary gearbox lubricant supply lines are in fluid communication with the lubricant tank and the gearbox assembly; One or more secondary gearbox lubricant supply lines, wherein the one or more secondary gearbox lubricant supply lines are in fluid communication with the lubricant tank and the gearbox assembly; and A lubricant pump for supplying lubricant from the lubricant tank to the gearbox assembly via one or more primary gearbox lubricant supply lines and one or more secondary gearbox lubricant supply lines, the lubrication system regulating the mass flow rate of the lubricant to the gearbox assembly via at least one of the one or more primary gearbox lubricant supply lines or the one or more secondary gearbox lubricant supply lines.

2. The turbine engine according to claim 1, characterized in that, The system further includes a motor, which is drivably connected to the input shaft, wherein the lubrication system further includes: One or more primary motor lubricant supply lines, wherein the one or more primary motor lubricant supply lines are in fluid communication with the lubricant tank and the motor; and One or more secondary motor lubricant supply lines are provided, the one or more secondary motor lubricant supply lines being in fluid communication with the lubricant tank and the motor, wherein the lubricant pump supplies lubricant from the lubricant tank to the motor through the one or more primary motor lubricant supply lines and the one or more secondary motor lubricant supply lines, and the lubrication system regulates the mass flow rate of the lubricant to the motor through at least one of the one or more primary motor lubricant supply lines or the one or more secondary motor lubricant supply lines.

3. The turbine engine according to claim 1, characterized in that, The system further includes one or more shaft bearings that support rotation of the input shaft, wherein the lubrication system further includes: One or more primary turbine engine lubricant supply lines, said one or more primary turbine engine lubricant supply lines being in fluid communication with said lubricant tank and said one or more shaft bearings; and One or more secondary turbine engine lubricant supply lines, the one or more secondary turbine engine lubricant supply lines being in fluid communication with the lubricant tank and the one or more shaft bearings, wherein the lubricant pump supplies lubricant from the lubricant tank to the one or more shaft bearings through the one or more primary turbine engine lubricant supply lines and the one or more secondary turbine engine lubricant supply lines, the lubrication system regulating the mass flow rate of the lubricant to the turbine engine through at least one of the one or more primary turbine engine lubricant supply lines or the one or more secondary turbine engine lubricant supply lines.

4. The turbine engine according to claim 1, characterized in that, The plurality of gears mesh with each other at the meshing portion, and the one or more primary gearbox lubricant supply lines and the one or more secondary gearbox lubricant supply lines guide the lubricant to the meshing portion.

5. The turbine engine according to claim 4, characterized in that, The one or more primary gearbox lubricant supply lines include a first primary gearbox lubricant supply line in fluid communication with the meshing portion.

6. The turbine engine according to claim 4, characterized in that, The one or more secondary gearbox lubricant supply lines include a primary gearbox lubricant supply line that is in fluid communication with the meshing portion.

7. The turbine engine according to claim 1, characterized in that, The gear assembly includes one or more bearings, and the one or more primary gearbox lubricant supply lines and the one or more secondary gearbox lubricant supply lines guide the lubricant to the one or more bearings.

8. The turbine engine according to claim 7, characterized in that, The one or more primary gearbox lubricant supply lines include a second primary gearbox lubricant supply line in fluid communication with the one or more bearings.

9. The turbine engine according to claim 7, characterized in that, The one or more secondary gearbox lubricant supply lines include secondary gearbox lubricant supply lines in fluid communication with the one or more bearings.

10. The turbine engine according to claim 1, characterized in that, The lubrication system further includes one or more valves disposed in at least one of the primary gearbox lubricant supply lines or the secondary gearbox lubricant supply lines for regulating the mass flow rate of the lubricant to the gearbox assembly.

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