Turbine engine comprising lubrication system

Abstract

The turbine engine includes a turbocharged engine, a fan, a frame, and a lubrication system. A turbocharged engine includes a core air flow path. The fan is drivingly coupled to the turbocharged engine. The frame supports the core air flow path and includes a plurality of lubricant struts extending through the core air flow path. The lubrication system includes an oil pan having lubricant therein, a purge reservoir, and a lubricant strut flow path disposed through each of a plurality of lubricant struts. A lubricant strut flow path is in fluid communication with the sump and the purge reservoir. The lubricant strut flow path of each of the plurality of lubricant struts directs lubricant from the sump to the purge reservoir.

Description

Technical Field

[0001] This disclosure generally relates to turbine engines, and more specifically to turbine engines including lubrication systems. Background Technology

[0002] For example, a turbine engine used in an aircraft typically includes a fan and a turbocharger arranged in fluid communication with each other. The gearbox assembly transmits torque and power from one rotating component to another (e.g., from a turbocharger to a fan). A lubrication system provides lubricant to one or more components of the gearbox assembly. Attached Figure Description

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

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

[0005] Figure 2 It is based on this disclosure Figure 1 The details of the two sections show the lubrication system. Figure 1 An enlarged schematic cross-sectional view of a turbine engine.

[0006] Figure 3A It is based on the purpose of this disclosure. Figure 1 A schematic axial end view of the lubrication system of a turbine engine. Figure 3A The turbine engine is shown in its first rotating position.

[0007] Figure 3B Based on this disclosure Figure 3A A schematic axial end view of the lubrication system, with the turbine engine in the second rotating position.

[0008] Figure 4 This illustrates the operation according to this disclosure. Figures 1 to 3B A flowchart of a method for developing a turbine engine. Detailed Implementation

[0009] The features, advantages, and embodiments of this disclosure will be set forth or apparent from consideration of the following detailed description, accompanying drawings, and claims. Furthermore, the following detailed description is exemplary and intended to provide further explanation, without limiting the scope of the claimed disclosure.

[0010] 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 constructions can be used without departing from this disclosure.

[0011] 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.

[0012] 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, and "downstream" refers to the direction from which the fluid flows.

[0013] The terms "front" and "rear" refer to relative positions within a turbine engine or vehicle, and specifically to the normal operating posture of the turbine engine or vehicle. For example, for a turbine engine, "front" refers to the position closer to the propeller or fan, and "rear" refers to the position further away from the propeller or fan. When the turbine engine is configured as a thrust-type configuration, the fan is located aft of the turbofan engine, making "front" refer to the position further away from the fan, and "rear" refer to the position closer to the fan.

[0014] As used herein, the terms "axial" and "axially" refer to a direction and orientation extending substantially parallel to the longitudinal centerline of the turbine engine. Furthermore, the terms "radial" and "radially" refer to a direction and orientation extending substantially perpendicular to the centerline of the turbine engine. Additionally, as used herein, the terms "circumferential" and "circumferentially" refer to a direction and orientation extending in an arc around the longitudinal centerline of the turbine engine.

[0015] As used in this article, “top” refers to the highest or uppermost point, part or surface of a component in the orientation shown in the figure.

[0016] As used in this article, “bottom” refers to the lowest point or lowest point, part or surface of a component in the orientation shown in the figure.

[0017] Unless otherwise stated 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.

[0018] Unless the context clearly indicates otherwise, the singular forms “a,” “one,” and “the” include plural references.

[0019] The approximate language used throughout this specification and claims is intended to modify any quantitative expression that may allow for variation without altering its underlying function. Therefore, values ​​modified by one or more terms (such as “about,” “approximate,” “general,” and “basic”) are not limited to specified precise values. In at least some cases, approximate language may correspond to the precision of the instrument used to measure the value, or the precision of the method or machine used to construct the component and / or system or manufacture the component and / or system. For example, approximate language may refer to a range of 1%, 2%, 4%, 10%, 15%, or 20% at the endpoints of a single value, a range of values, and / or a defined range of values.

[0020] This disclosure provides a lubrication system for a gearbox assembly in a turbine engine. The turbine engine includes a core airflow path through which core air is introduced, compressed (by one or more compressors), mixed with fuel for combustion to produce combustion gases (in a combustor), expanded (by one or more turbines), and discharged from the turbine engine to generate thrust. The gearbox assembly, also known as a power gearbox, is used to transmit power and torque from the turbine shaft (such as a low-pressure shaft) to the turbine engine's fan.

[0021] This gearbox assembly requires a large amount of lubricant (such as oil) to ensure continuous operation, high efficiency, and adequate heat dissipation. The large amount of lubricant that must be supplied and emptied leads to severe packing problems associated with the core airflow path of the turbine engine. The gearbox assembly occupies a significant portion of the space beneath the core airflow path. Therefore, the space required for lubricant scavenging directly forces the core airflow path outward, posing a challenge to the fan hub-to-radius ratio and the inlet radius ratio of the core airflow path, resulting in additional weight and reduced efficiency for the turbine engine. This problem is further exacerbated when considering aircraft maneuvers. For example, even during roll, tilt, or turn, the scavenger pickup must always be completely covered by lubricant. To account for roll, tilt, and turn, the turbine engine may require up to three large scavenger elements (such as pumps and reservoirs) and scavenger pickups that must be packed within the radially inward space of the core airflow path. This results in very large main lubricant pumps and scavenger pumps, significantly increasing packing pressure. Packing constraints are further exacerbated when the turbine engine includes an accessory gearbox in addition to the power gearbox. When a turbocharged engine includes an accessory gearbox, this configuration results in a 1% increase in fuel combustion, making it difficult to implement a scheme that incorporates an accessory gearbox.

[0022] Some turbine engines include a single lubricant strut through which lubricant flows into a scavenging element to lubricate one or more bearings of the turbine engine. However, bearings require far less lubricant than gearbox assemblies. Therefore, if this lubricant strut is used to scavenge lubricant from gearbox assemblies, the lubrication system will be unable to scavenge lubricant when the aircraft rolls, tilts, or turns. In particular, during such rolling, tilting, or turning, the lubricant may lose contact with the lubricant strut, preventing the lubrication system from scavenging lubricant through it. This leads to lubrication interruption and generates excessive heat due to reduced lubrication during the interruption. Furthermore, because the lubricant is not scavenged in this situation, the lubricant level increases and may come into contact with the gears of the gearbox assembly, thus agitating the lubricant as it is immersed in it.

[0023] Therefore, this disclosure provides a lubrication system having a plurality of oil-wetting struts, also known as lubricant struts, connected outside the core airflow path at a common scavenging collector (also known as a scavenging reservoir), wherein a single scavenging element (e.g., a scavenging pump) can pump lubricant from the scavenging reservoir. Each lubricating strut is in fluid communication with the scavenging reservoir. The plurality of lubricant struts are circumferentially spaced around the gearbox assembly such that lubricant remains in contact with at least one lubricating strut even when the aircraft rolls, tilts, or turns. Thus, the scavenging reservoir is covered with lubricant even during rolls, tilts, or turns.

[0024] Therefore, although the gearbox assembly is in a rotating position when the aircraft is rotating, the lubrication system and method detailed herein still allow lubricant to be drained into the clean reservoir. This prevents overflow of the gearbox assembly and allows the lubrication system to continuously circulate lubricant through the gears, even when the aircraft is in a rotating position. The lubrication system disclosed herein prevents lubricant interruption and prevents lubricant from increasing and contacting the gears, regardless of the turbine engine's rotational position. Therefore, the lubrication system prevents the gears from being immersed in the lubricant. In this way, the lubrication system can prevent excessive wind resistance in the gearbox assembly (e.g., friction generated by the gears rotating through the lubricant).

[0025] Now refer to the attached diagram, Figure 1 This is a schematic cross-sectional view of the turbine engine 10 taken along the longitudinal centerline axis 12 of the turbine engine 10 according to an embodiment of the present disclosure. 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 fan section 14 and a turbocharger engine 16 disposed downstream of the fan section 14.

[0026] 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 casing 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, downstream of which is a low-pressure (LP) turbine 30. Turbocharged engine 16 also includes an injection exhaust nozzle section 32, a high-pressure (HP) shaft 34 or spool, 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 core airflow path 29.

[0027] for Figure 1 In the illustrated embodiment, fan section 14 includes a fan 38 (e.g., a variable pitch fan) having a plurality of fan blades 40 spaced apart and coupled to disk 42. Figure 1 As shown, fan blades 40 typically extend outward from disk 42 along the radial direction R. In the case of a variable pitch fan, multiple fan blades 40 are operably coupled to an actuating member 44 by means of the fan blades 40, enabling them to rotate relative to disk 42 about a pitch axis P. This actuating member is configured to collectively and uniformly change the pitch of the fan blades 40. The fan blades 40, disk 42, and actuating member 44 are rotatable together about a longitudinal centerline axis 12 via a fan shaft 45, which is powered by an LP shaft 36 passing through a power gearbox, also referred to as gearbox assembly 46. Thus, fan 38 is driven and powered by turbocharged engine 16, and turbocharged engine 10 is an indirectly driven engine. Gearbox assembly 46 in Figure 1 The diagram is schematically shown. Gearbox assembly 46 is a reduction gearbox assembly used to regulate the speed of fan shaft 45 when power is transmitted from LP shaft 36 to fan shaft 45, thereby regulating the speed of fan 38 relative to LP shaft 36.

[0028] Still referencing Figure 1In an exemplary embodiment, the disk 42 is covered by a fan hub 48 having an aerodynamic profile to facilitate airflow through a plurality of fan blades 40. Furthermore, the fan section 14 includes an annular fan housing or nacelle 50 circumferentially surrounding at least a portion of the fan 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 above the exterior of the turbocharged engine 16 and, together with the housing 18, defines a bypass airflow passage 56 therebetween.

[0029] 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 fan section 14. As the air 58 passes through the fan 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 through the core inlet 20 of the LP compressor 22 to the upstream section of the core airflow path 29. The ratio between bypass air 62 and core air 64 is commonly referred to as the bypass ratio. The pressure of the core air 64 is then increased, 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.

[0030] Combustion gas 66 is guided 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 fan 38 via the gearbox assembly 46. Thus, the combustion gas 66 performs work on the LP turbine 30.

[0031] 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 before exiting from the fan 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.

[0032] Figure 1 The turbine engine 10 depicted 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 fan 38 may be configured in any other suitable manner (e.g., as a fixed-pitch fan) and may also be supported using any other suitable fan 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, turboprop engine, or turboshaft engine.

[0033] Figure 2 It is based on this disclosure Figure 1 The image shows an enlarged, partially schematic cross-sectional view of the turbine engine 10, taken at detail 2, which includes the lubrication system 100. (See image for details.) Figure 2 As shown, the turbine engine 10 includes a frame 31 supporting a core airflow path 29. The frame 31 includes a radially inner frame wall 33 and a radially outer frame wall 35. The core airflow path 29 is defined between the radially inner frame wall 33 and the radially outer frame wall 35. The frame 31 includes a plurality of oil-wetting struts, also referred to as a plurality of lubricant struts 37, extending from the radially inner frame wall 33 to the radially outer frame wall 35. The plurality of lubricant struts 37 support the radially inner frame wall 33 and the radially outer frame wall 35. The plurality of lubricant struts 37 are axially positioned at the core inlet 20 and the compressor section 21 (e.g., LP compressor 22). Figure 1 Between. Each of the plurality of lubricant pillars 37 includes a lubricant pillar flow path, such that lubricant can flow through the lubricant pillar 37, as described in further detail below.

[0034] like Figure 2 As further shown, the gearbox assembly 46 includes a gearbox housing 47 and a gear assembly having a plurality of gears 49 disposed within the gearbox housing 47. The plurality of gears 49 includes a first gear 49a, one or more second gears 49b, and a third gear 49c. The second gear 49b is secured by a planetary carrier 51. Figure 2In this configuration, the first gear 49a is a sun gear, one or more second gears 49b are planetary gears, and the third gear 49c is a ring gear. The multiple gears 49 can be arranged as a planetary gear assembly. When the multiple gears 49 are a planetary gear assembly, one or more second gears 49b include multiple second gears 49b (e.g., two or more second gears 49b). For example, one or more second gears 49b include five second gears 49b (e.g.,...). Figure 3A (as shown), but may include any number of second gears 49b.

[0035] In a planetary gear assembly, multiple gears 49 can be arranged in a star configuration, also known as a rotating ring gear configuration (e.g., a third gear 49c is rotating, while the planet carrier 51 is fixed and stationary). In this arrangement, the fan 38 is driven by the third gear 49c. For example, the third gear 49c is coupled to the fan shaft 45 such that rotation of the third gear 49 causes rotation of the fan shaft 45, which in turn causes rotation of the fan 38. Thus, the third gear 49c is the output of the gearbox assembly 46. However, other suitable types of gear assemblies may also be used. In a non-limiting embodiment, multiple gears 49 are arranged in a planetary configuration, wherein the third gear 49c remains fixed and the planet carrier 51 is allowed to rotate. In this arrangement, the fan 38 is driven by the planet carrier 51. For example, the planet carrier 51 is coupled to the fan shaft 45 such that rotation of the planet carrier 51 causes rotation of the fan shaft 45, which in turn causes rotation of the fan 38. Thus, one or more second gears 49b (e.g., the planet carrier 51) are the output of the gearbox assembly 46. In another non-limiting embodiment, the plurality of gears 49 may be arranged in a differential gear configuration, wherein both the third gear 49c and the planet carrier 51 are rotatable. Although the planetary gear assembly is described in detail herein, the plurality of gears 49 may include any type of gear, such as compound gears, multi-stage gears, etc.

[0036] One or more second gears 49b each include one or more bearings 53 disposed therein. Thus, the gear assembly includes one or more bearings 53. The one or more bearings 53 enable the one or more second gears 49b to rotate about the one or more bearings 53. The one or more bearings 53 can include any type of bearing used for gears, such as journal bearings, roller bearings, etc. Any gear 49 can include bearings 53.

[0037] A first gear 49a is coupled to the input shaft of the turbine engine 10. For example, the first gear 49a is coupled to the LP shaft 36, such that rotation of the LP shaft 36 causes rotation of the first gear 49a. Radially outside the first gear 49a, meshing with it are one or more second gears 49b, which are coupled together and supported by a planet carrier 51 (shown schematically). The planet carrier 51 supports and constrains the one or more second gears 49b, such that each of the one or more second gears 49b can rotate about its respective axis, but not about the periphery of the first gear 49a. Radially outside the one or more second gears 49b, meshing with them is a third gear 49c, which is a ring gear. The third gear 49c is coupled to a fan 38 via an output shaft and rotates to drive the fan 38 to rotate about a longitudinal centerline axis 12. For example, a fan shaft 45 is coupled to the third gear 49c. Radially outside the third gear 49c is a lubricant groove 55. The lubricant trough 55 is defined by the gearbox housing 47 and collects lubricant injected or discharged from the gear 49 (e.g., the third gear 49c) or the bearing 53. The lubricant trough 55 is annular about the longitudinal centerline axis 12 (e.g., about the gear 49).

[0038] Lubrication system 100 includes a lubricant storage 101 therein. Figure 3A and Figure 3B The system comprises a housing 102, a lubricant pump 104, and a lubricant supply line 106. Preferably, the lubricant 101 is oil. The lubricant 101 can be any type of lubricant used for lubricating gears 49 (e.g., a first gear 49a, one or more second gears 49b, or a third gear 49c) or one or more bearings 53. The lubricant pump 104 is in fluid communication with the housing 102 and the lubricant supply line 106. The lubricant supply line 106 is in fluid communication with the gearbox assembly 46. The lubricant pump 104 pumps the lubricant 101 from the housing 102 to the gearbox assembly 46 via the lubricant supply line 106 for supplying the lubricant 101 to the gearbox assembly 46 (e.g., to gears 49 or bearings 53), as described in further detail below. In some embodiments, the lubrication system 100 supplies the lubricant 101 from the housing 102 to the gearbox assembly 46 without a pump, for example by gravity or centrifugal force generated by the rotation of the planetary carrier 51 in the planetary arrangement of the gears 49.

[0039] The lubrication system 100 includes an oil pan 108 within the turbine engine 10, which is in fluid communication with the gearbox assembly 46. In one embodiment, the oil pan 108 is located within the gearbox assembly 46 (e.g., within the gearbox housing 47). The oil pan 108 is a reservoir for collecting and storing lubricant 101 discharged from the gear 49 or bearing 53. The oil pan 108 is in fluid communication with a lubricant reservoir 55 to receive lubricant 101 from the lubricant reservoir 55. For example, the lubricant reservoir 55 may include one or more slots through which lubricant is discharged from the lubricant reservoir 55 into the oil pan 108.

[0040] The lubrication system 100 also includes a lubricant strut flow path 110 in fluid communication with the oil pan 108. The lubricant strut flow path 110 is disposed through a corresponding lubricant strut 37. Thus, each of the plurality of lubricant struts 37 includes the lubricant strut flow path 110, as described in further detail below. The lubricant strut flow path 110 includes a lubricant strut flow path inlet 112 and a lubricant strut flow path outlet 114. The lubricant strut flow path inlet 112 is in fluid communication with the oil pan 108 (e.g., via one or more strut holes in the lubricant struts 37 or via a lubricant line from the oil pan 108 to the lubricant strut flow path 110). Thus, the lubricant strut flow path 110 receives lubricant 101 from the oil pan 108 through the lubricant strut flow path inlet 112.

[0041] The lubrication system 100 includes a clean reservoir 120 and a clean line 122. The clean reservoir 120 is in fluid communication with the lubricant strut flow path 110 and the tank 102. For example, the clean reservoir 120 is in fluid communication with the lubricant strut flow path outlet 114, allowing lubricant 101 to flow into the clean reservoir 120 through the outlet 114. The clean reservoir 120 is located radially outside the core airflow path 29. For example, the clean reservoir 120 is located within the housing 18. This configuration allows for a common clean reservoir located outside the core airflow path 29 for multiple lubricant struts 37, thus not interfering with the limited dimensions of the radially inward region of the core airflow path 29. The clean reservoir 120 is a tank, line, etc., for collecting lubricant 101 from each of the multiple lubricant struts 37.

[0042] The lubrication system 100 includes a purge pump 124 in fluid communication with a purge reservoir 120 and a purge line 122. The purge pump 124 pumps lubricant 101 and pumps air from within the purge reservoir 120 or leaked into the purge reservoir 120 during operation of the turbine engine 10. The purge pump 124 is a suction pump that generates suction to draw lubricant 101 and / or air through the purge line 122 toward the tank 102. The purge pump 124 includes a single purge pump that can pump lubricant 101 from the purge reservoir 120. In some embodiments, the lubrication system 100 supplies lubricant 101 from the purge reservoir 120 to the tank 102 without a pump, for example by gravity, centrifugal force due to the rotation of the planetary carrier 51 in the planetary arrangement of the gears 49, or by the lubricant pump 104.

[0043] Figure 3A This is a schematic axial end cross-sectional view of the lubrication system 100, with the turbine engine 10 in a first rotating position. Figure 3A In the orientation of the turbine engine 10, the turbine engine 10 can be viewed relative to a "clock" orientation having a 12 o'clock position, a 3 o'clock position, a 6 o'clock position, and a 9 o'clock position. Although no reference figures are provided, the clock orientation should be understood to include all clock positions in between.

[0044] like Figure 3A As shown, each of the plurality of lubricant struts 37 is fluidly connected to a sludge reservoir 120. Specifically, the lubricant strut flow path 110 of each of the plurality of lubricant struts 37 is in fluid communication with the sludge reservoir 120 (e.g., via a lubricant strut flow path outlet 114). The plurality of lubricant struts 37 are circumferentially spaced around a longitudinal centerline axis 12. The plurality of lubricant struts 37 are located at the bottom of the turbine engine 10, for example, between the three o'clock and nine o'clock positions.

[0045] The plurality of lubricant pillars 37 include a first lubricant pillar 37a, a second lubricant pillar 37b, and a third lubricant pillar 37c. Figure 3AAs shown in the first rotational position, the first lubricant strut 37a is located at the six o'clock position. When the turbine engine 10 and therefore the gearbox assembly 46 changes rotational position, the second lubricant strut 37b and the third lubricant strut 37c facilitate the discharge of lubricant 101 from the oil pan 108. For example, when the turbine engine 10 powers the aircraft, the aircraft turns, tilts, or rolls, causing the turbine engine 10 and therefore the gearbox assembly 46 to change rotational position. The second lubricant strut 37b is located on the first circumferential side of the first lubricant strut 37a. The third lubricant strut 37c is located on the second circumferential side of the first lubricant strut 37a. For example, the second lubricant strut 37b is typically located between the six o'clock and nine o'clock positions. The third lubricant strut 37c is typically located between the three o'clock and six o'clock positions.

[0046] The first lubricant support 37a, the second lubricant support 37b, and the third lubricant support 37c all include a lubricant support flow path 110 with a lubricant support flow path inlet 112 and a lubricant support flow path outlet 114. The first lubricant support 37a includes a first lubricant support flow path 110a, the second lubricant support 37b includes a second lubricant support flow path 110b, and the third lubricant support 37c includes a third lubricant support flow path 110c.

[0047] The clean reservoir 120 extends circumferentially around the core airflow path 29. Specifically, the clean reservoir 120 is located radially outside the radial outer frame wall 35 and extends circumferentially around the radial outer frame wall 35. Thus, the clean reservoir 120 is arcuate. This configuration allows each of the plurality of lubricant supports 37 to be in fluid communication with the clean reservoir 120. Therefore, a single clean reservoir 120 is provided to receive lubricant 101 from each of the plurality of lubricant supports 37. In some embodiments, the clean reservoir 120 is annular around the core airflow path 29, such that the clean reservoir 120 extends circumferentially completely around the core airflow path 29 (e.g., the radial outer frame wall 35). The clean reservoir 120 includes a clean line 122 ( Figure 2 The fluid-connected clean reservoir outlet 121 is used to guide lubricant 101 from the clean reservoir 120 to the clean line 122.

[0048] like Figure 3AAs further shown, the turbine engine includes one or more structural struts 39 extending from the radially inner frame wall 33 to the radially outer frame wall 35. The one or more structural struts 39 support the radially inner frame wall 33 and the radially outer frame wall 35. The structural struts 39 are circumferentially spaced around the longitudinal centerline axis 12. Specifically, the structural struts 39 are located at the top of the turbine engine, particularly between the nine o'clock and three o'clock positions. The one or more structural struts 39 are axially positioned between the core inlet 20 and the compressor section 21 (e.g., LP compressor 22). Figure 1 This is achieved by axially aligning one or more structural struts 39 with a plurality of lubricant struts 37. Thus, the turbine engine 10 includes lubricant struts 37 and structural struts 39. In some embodiments, the structural struts 39 may include a lubricant strut flow path 110, such that the structural strut 39 is also a lubricant strut 37. In such embodiments, each strut can be a lubricant strut 37.

[0049] The third gear 49c includes a third gear flange 57 for connecting the third gear 49c to the static structure of the turbine engine 10. An oil pan 108 is radially defined between the third gear flange 57 and the core airflow path 29. Specifically, the oil pan 108 is radially defined between the third gear flange 57 and the radially inner frame wall 33. Thus, the lubricant 101 in the oil pan 108 accumulates on the radially inner frame wall 33 due to gravity and is in fluid communication with at least one of the plurality of lubricant supports 37. Even when the turbine engine 10 (e.g., gearbox assembly 46) is rotating, the lubricant 101 in the oil pan 108 remains in fluid communication with at least one of the plurality of lubricant supports 37.

[0050] Reference Figure 2 and Figure 3A During operation, the LP shaft 36 rotates as described above, causing the first gear 49a to rotate. The first gear 49a meshes with one or more second gears 49b, causing the one or more second gears 49b to rotate about their respective axes of rotation. The one or more second gears 49b rotate relative to one or more bearings 53 within the planetary carrier 51. When gear 49 is in a star arrangement, the one or more second gears 49b meshing with the third gear 49c cause the third gear 49c to rotate about the longitudinal centerline axis 12. In such an embodiment, the planetary carrier 51 remains stationary, causing the one or more second gears 49b not to rotate about the longitudinal centerline axis 12. When gear 49 is in a planetary arrangement, the third gear 49c is stationary, while the one or more second gears 49b (and the planetary carrier 51) rotate about the longitudinal centerline axis 12. When gear 49 is in a differential gear arrangement, both the planetary carrier 51 (e.g., one or more second gears 49b) and the third gear 49c rotate about the longitudinal centerline axis 12.

[0051] When gear 49 rotates, lubrication system 100 supplies lubricant 101 to the gear assembly (e.g., to gear 49 or at least one of one or more bearings 53) to lubricate the gear assembly (e.g., gear 49 or at least one of one or more bearings 53). During operation of turbine engine 10, lubricant pump 104 ( Figure 2 Lubricant 101 is removed from tank 102. Figure 2 (middle) pumped and supplied through lubricant supply line 106 ( Figure 2 (In the middle) enters the gearbox assembly 46. The lubrication system 100 supplies lubricant 101 to the gear assembly (e.g., gear 49 or at least one of one or more bearings 53). For example, the lubricant supply line 106 is in fluid communication with the gear assembly (e.g., gear 49 or one or more bearings 53).

[0052] Lubricant 101 is discharged from the gear assembly and enters the oil pan 108. The lubricant 101 in the oil pan 108 is discharged from the oil pan 108 through multiple lubricant struts 37. When the aircraft is operating in level flight (e.g., the aircraft is not turning, not tilting, or not rolling), the gearbox assembly 46 is in... Figure 3A The first rotational position shown is such that the six o'clock position of the gearbox assembly 46 is substantially located at the bottom of the gearbox assembly 46. In this orientation, lubricant 101 is discharged from the oil pan 108 through the first lubricant support 37a and enters the clean reservoir 120.

[0053] Then, the purge pump 124 pumps lubricant 101 from the purge reservoir 120 through the purge line 122. Figure 2 The lubricant is pumped to tank 102. Then, lubricant pump 104 recirculates lubricant 101 through lubrication system 100 (e.g., through lubricant supply line 106) and gearbox assembly 46. In this way, lubricant 101 can be reused to lubricate gear assembly.

[0054] During operation of the turbine engine 10, lubricant 101 fills the oil pan 108 to a maximum lubricant level 109. The maximum lubricant level 109 is below the gear assembly, preventing the lubricant 101 within the oil pan 108 from contacting the gears 49 (e.g., the third gear 49c) of the gear assembly when stored in the oil pan 108. The lubricant 101 is discharged through a first lubricant strut 37a and enters a clearing reservoir 120 to maintain the level of lubricant 101 in the oil pan 108 at or below the maximum lubricant level 109.

[0055] Figure 3B The gearbox assembly 46 is shown in a second rotational position. The gearbox assembly 46 is in this position when the aircraft turns right, tilts, or rolls. Figure 3BThe second rotational position, as shown, causes the six o'clock position of gearbox assembly 46 to rotate to the right. In this orientation, the second lubricant strut 37b is positioned approximately at the lowest point of gearbox assembly 46, allowing lubricant 101 to drain from oil pan 108 through the second lubricant strut 37b (e.g., through the second lubricant strut flow path 110a). In this configuration, lubricant 101 can also drain through the first lubricant strut 37a if the lubricant level in oil pan 108 is at the first lubricant strut flow path 110a. When the aircraft turns left, tilts, or rolls, gearbox assembly 46 is in a third rotational position, causing the six o'clock position of gearbox assembly 46 to rotate to the left. In this orientation, the third lubricant strut 37c is positioned approximately at the lowest point of gearbox assembly 46, allowing lubricant 101 to drain from oil pan 108 through the third lubricant strut 37c (e.g., through the third lubricant strut flow path 110c). Therefore, regardless of the rotational position of the gearbox assembly 46, the lubricant 101 can be discharged from the oil pan 108 into the clean reservoir 120.

[0056] Therefore, lubricant 101 is discharged through at least one of the plurality of lubricant struts 37 (e.g., a first lubricant strut 37a, a second lubricant strut 37b, or a third lubricant strut 37c) and enters a clearing reservoir 120 to maintain the level of lubricant 101 in the oil pan 108 at the maximum lubricant level 109. This configuration helps ensure that even when the turbine engine 10 (e.g., gearbox assembly 46) is rotating, the lubricant 101 in the oil pan 108 is always in fluid communication with at least one of the plurality of lubricant struts 37. For example, the lubricant 101 in the oil pan 108 is in fluid communication with the first lubricant strut 37a in a first rotational position and with the second lubricant strut 37b in a second rotational position. Thus, the lubrication system 100 disclosed herein prevents lubricant interruption and prevents the lubricant 101 in the oil pan 108 from increasing beyond the maximum lubricant level 109, regardless of the rotational position of the gearbox assembly 46.

[0057] In some embodiments, the plurality of lubricant struts 37 includes at least one circumferentially positioned lubricant strut 37 to maintain contact with the lubricant 101 in the oil pan 108 when the turbine engine 10 is at its maximum roll angle. For example, a second lubricant strut 37b may be positioned such that the lubricant 101 in the oil pan 108 contacts the second lubricant strut 37b when the turbine engine 10 is at its maximum roll angle. The maximum roll angle may include any roll angle between 0° and 360°. Thus, the plurality of lubricant struts 37 may include lubricant struts 37 circumferentially spaced around the entire core airflow path 29. In some embodiments, the maximum roll angle is between 0° and 30° or between 0° and -30°, and the plurality of lubricant struts 37 include lubricant struts 37 circumferentially spaced around a portion of the core airflow path 29 to maintain contact with the lubricant 101 at the maximum roll angle.

[0058] Figure 4 This is a flowchart illustrating a method 200 for operating a turbine engine 10 according to this disclosure. Further details of the method have been described above regarding the operation and description of the aforementioned components.

[0059] In step 205, method 200 includes guiding lubricant 101 from the oil pan 108 to the clean reservoir 120 via a first lubricant support 37a. Specifically, a first lubricant support flow path 110a guides lubricant 101 from the oil pan 108 through a lubricant support flow path inlet 112 and into the clean reservoir 120 through a lubricant support flow path outlet 114. Thus, lubricant 101 fills the clean reservoir 120 via the first lubricant support 37a at a first rotational position.

[0060] In step 210, method 200 includes rotating the gearbox assembly 46. For example, when the turbine engine 10 powers the aircraft, the aircraft turns, tilts, or rolls, causing the turbine engine 10 and therefore the gearbox assembly 46 to rotate and change its rotational position to a second rotational position. When the gearbox assembly 46 rotates, the lubricant 101 in the oil pan 108 is held at the six o'clock position due to gravity. Therefore, in the second rotational position, the oil pan 108 is no longer in fluid communication with the first lubricant strut 37a. In this position, the lubricant 101 in the oil pan 108 is in fluid communication with the second lubricant strut 37b.

[0061] In step 215, method 200 includes guiding lubricant from the oil pan 108 to the clean reservoir 120 via a second lubricant strut 37b. Specifically, a second lubricant strut flow path 110b guides lubricant 101 from the oil pan 108 through a lubricant strut flow path inlet 112 and into the clean reservoir 120 through a lubricant strut flow path outlet 114. Thus, lubricant 101 fills the clean reservoir 120 via the second lubricant strut 37b in the second rotational position. Similarly, when the gearbox assembly 46 is in the third rotational position, a third lubricant strut 37c can guide lubricant 101 through the third lubricant strut flow path 110c into the clean reservoir 120. In some embodiments, method 200 further includes guiding lubricant 101 from the oil pan 108 to the clean reservoir 120 via at least one lubricant strut 37 when the turbine engine 10 is at its maximum roll angle.

[0062] In step 220, method 200 includes supplying lubricant 101 from the sludge reservoir 120 to the gearbox assembly 46. Specifically, a sludge pump 124 pumps lubricant 101 from the sludge reservoir 120 through the sludge reservoir outlet 121 to the tank 102. A sludge line 122 guides lubricant 101 from the sludge reservoir 120 to the tank 102. The lubrication system 100 then supplies lubricant 101 back to the gearbox assembly 46, as described above.

[0063] Therefore, although the gearbox assembly 46 is in a rotating position when the aircraft is rotating, the above-described lubrication system and method allow lubricant 101 to be drained into the clean reservoir 120. This prevents overflow of the gearbox assembly 46 and allows the lubrication system 100 to continuously circulate lubricant 101 through the gears 49 even when the aircraft is in a rotating position. The lubrication system 100 disclosed herein prevents lubrication interruption and prevents the lubricant 101 in the oil pan 108 from increasing above the maximum lubricant level 109, regardless of the rotational position of the turbine engine 10. Therefore, the lubrication system 100 prevents lubricant 101 from filling the oil pan 108 above the maximum lubricant level 109, thereby preventing gears 49 from being immersed in the lubricant 101. Therefore, the lubrication system 100 prevents excessive wind resistance in the gearbox assembly 46.

[0064] Further aspects are provided by the following items.

[0065] A turbocharged engine includes a turbocharged engine having a core airflow path; a fan droguely coupled to the turbocharged engine; a frame supporting the core airflow path, the frame including a plurality of lubricant struts extending through the core airflow path; and a lubrication system including: an oil pan having lubricant therein; a clean reservoir; and lubricant strut flow paths passing through each of the plurality of lubricant struts, the lubricant strut flow paths being in fluid communication with the oil pan and the clean reservoir, wherein the lubricant strut flow paths of each of the plurality of lubricant struts guide the lubricant from the oil pan to the clean reservoir.

[0066] According to the turbine engine described in the foregoing clause, the lubrication system further includes a purge pump in fluid communication with the purge reservoir for pumping the lubricant from the purge reservoir.

[0067] The turbine engine according to any of the preceding clauses, wherein the scavenging reservoir is located radially outside the core airflow path.

[0068] The turbine engine according to any of the preceding clauses, wherein the scavenging reservoir extends circumferentially in part around the core airflow path.

[0069] The turbine engine according to any of the preceding clauses, wherein the frame includes a radially inner frame wall and a radially outer frame wall, the core airflow path is defined between the radially inner frame wall and the radially outer frame wall, and the plurality of lubricant struts extend from the radially inner frame wall to the radially outer frame wall.

[0070] According to the turbine engine described in the foregoing clause, the clearing reservoir is located radially outside the radial outer frame wall.

[0071] The turbine engine according to any of the preceding clauses, wherein the plurality of lubricant struts includes a first lubricant strut having a first lubricant strut flow path that guides the lubricant from the oil pan to the purge reservoir when the turbine engine is in a first rotating position.

[0072] According to the turbine engine described in the foregoing clause, the plurality of lubricant struts includes a second lubricant strut having a second lubricant strut flow path that guides the lubricant from the oil pan to the purge reservoir when the turbine engine is in a second rotational position.

[0073] The turbine engine according to any of the preceding clauses, wherein the oil pan includes a maximum lubricant level, and when the turbine engine rotates, the lubricant in the oil pan remains in contact with at least one of the plurality of lubricant struts, such that the lubricant is maintained at or below the maximum lubricant level.

[0074] According to the turbine engine described in the foregoing clause, the plurality of lubricant struts includes at least one lubricant strut circumferentially positioned to remain in contact with the lubricant in the oil pan when the turbine engine is at its maximum roll angle.

[0075] The turbocharged engine according to any of the preceding clauses further includes a gearbox assembly comprising a plurality of gears, the fan being droopily coupled to the turbocharged engine via the gearbox assembly.

[0076] According to the turbine engine described in the foregoing clause, the oil pan is defined radially outside the plurality of gears.

[0077] The turbine engine according to any of the preceding clauses, wherein the lubrication system further includes a tank for storing the lubricant therein, a lubricant pump, and a lubricant supply line in fluid communication with the tank and the gearbox assembly, the lubricant pump pumping the lubricant from the tank to the gearbox assembly via the lubricant supply line to lubricate the plurality of gears.

[0078] The turbine engine according to any of the preceding clauses, wherein the lubricant strut flow path includes a lubricant strut flow path inlet in fluid communication with the oil pan, the lubricant strut flow path inlet guiding the lubricant from the oil pan into the lubricant strut flow path.

[0079] The turbine engine according to any of the preceding clauses, wherein the lubricant strut flow path includes a lubricant strut flow path outlet in fluid communication with the sludge reservoir, the lubricant strut flow path outlet guiding the lubricant from the lubricant strut flow path into the sludge reservoir.

[0080] The turbine engine according to any of the preceding clauses further includes a purging line in fluid communication with the purging reservoir and the oil pan, the purging line guiding the lubricant from the purging reservoir to the tank.

[0081] The turbine engine according to any of the preceding clauses, wherein the purge reservoir includes a purge reservoir outlet in fluid communication with the purge line, the purge reservoir outlet directing the lubricant from the purge reservoir to the purge line.

[0082] A method of operating a turbine engine according to any of the preceding claims, the method comprising: guiding lubricant from the oil pan to the purge reservoir via a flow path of one or more of the plurality of lubricant struts, based on the rotational position of the turbine engine.

[0083] According to the method described in the foregoing clause, the turbocharger includes a gearbox assembly comprising a plurality of gears, the fan is drivably coupled to the turbocharger via the gearbox assembly, the lubrication system further includes a tank for storing the lubricant therein, a lubricant pump, and a lubricant supply line in fluid communication with the tank and the gearbox assembly, and the method further includes pumping the lubricant from the tank to the gearbox assembly via the lubricant supply line using the lubricant pump to lubricate the plurality of gears.

[0084] The method according to any of the preceding clauses, wherein the lubrication system further includes a cleaning pump in fluid communication with the cleaning reservoir, and the method further includes pumping the lubricant from the cleaning reservoir using the cleaning pump.

[0085] The method according to any of the preceding clauses, wherein the plurality of lubricant struts includes a first lubricant strut having a first lubricant strut flow path, the method further comprising, when the turbine engine is in a first rotating position, guiding the lubricant from the oil pan to the purge reservoir using the first lubricant strut flow path.

[0086] According to the method described in the foregoing clause, wherein the plurality of lubricant pillars includes a second lubricant pillar having a second lubricant pillar flow path, the method further includes guiding the lubricant from the oil pan to the purge reservoir when the turbine engine is in a second rotational position.

[0087] The method according to any one of the preceding clauses, wherein the oil pan includes a maximum lubricant level, the method further comprising maintaining the lubricant in the oil pan at or below the maximum lubricant level by maintaining the lubricant in contact with at least one of the plurality of lubricant struts while the turbine engine is rotating.

[0088] According to the method described in the foregoing clause, the plurality of lubricant struts includes at least one lubricant strut circumferentially positioned to remain in contact with the lubricant in the oil pan when the turbine engine is at its maximum roll angle, and the method further includes guiding the lubricant from the oil pan to the purge reservoir via the at least one lubricant strut when the turbine engine is at the maximum roll angle.

[0089] The method according to any of the preceding clauses further includes guiding the lubricant from the oil pan into the lubricant strut flow path through a lubricant strut flow path inlet.

[0090] The method according to any of the preceding clauses further includes guiding the lubricant from the lubricant pillar flow path to the clearing reservoir via a lubricant pillar flow path outlet of the lubricant pillar flow path.

[0091] The method according to any of the foregoing clauses further includes guiding the lubricant from the cleanup reservoir to the tank via a cleanup line.

[0092] The method according to any of the preceding clauses further includes directing the lubricant from the clean reservoir to the clean line through the clean reservoir outlet of the clean reservoir.

[0093] 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 having a core airflow path; A fan, which is drivenly connected to the turbocharged engine; A frame that supports the core airflow path, the frame including a plurality of lubricant struts extending through the core airflow path; and Lubrication system, the lubrication system comprising: An oil pan containing a lubricant; Clean the reservoir; and A lubricant support flow path, the lubricant support flow path passing through each of the plurality of lubricant supports, the lubricant support flow path being in fluid communication with the oil pan and the purge reservoir, wherein... The lubricant flow path of each of the plurality of lubricant struts guides the lubricant from the oil pan to the clear reservoir.

2. The turbine engine according to claim 1, characterized in that, in, The lubrication system further includes a cleaning pump in fluid communication with the cleaning reservoir for pumping the lubricant from the cleaning reservoir.

3. The turbine engine according to claim 1, characterized in that, in, The purging reservoir is located radially outside the core airflow path.

4. The turbine engine according to claim 3, characterized in that, in, The clearing reservoir extends circumferentially around the core airflow path.

5. The turbine engine according to claim 1, characterized in that, in, The frame includes a radially inner frame wall and a radially outer frame wall, the core airflow path is defined between the radially inner frame wall and the radially outer frame wall, and the plurality of lubricant struts extend from the radially inner frame wall to the radially outer frame wall.

6. The turbine engine according to claim 5, characterized in that, in, The clearing reservoir is located radially outside the radial outer frame wall.

7. The turbine engine according to claim 1, characterized in that, in, The plurality of lubricant struts includes a first lubricant strut having a first lubricant strut flow path that guides the lubricant from the oil pan to the purge reservoir when the turbine engine is in a first rotating position.

8. The turbine engine according to claim 7, characterized in that, in, The plurality of lubricant struts includes a second lubricant strut having a second lubricant strut flow path that guides the lubricant from the oil pan to the purge reservoir when the turbine engine is in a second rotational position.

9. The turbine engine according to claim 1, characterized in that, in, The oil pan includes a maximum lubricant level, and when the turbine engine rotates, the lubricant in the oil pan remains in contact with at least one of the plurality of lubricant struts, such that the lubricant is maintained at or below the maximum lubricant level.

10. The turbine engine according to claim 9, characterized in that, in, The plurality of lubricant struts includes at least one lubricant strut circumferentially positioned to remain in contact with the lubricant in the oil pan when the turbine engine is at its maximum roll angle.

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