Gearbox assembly with segmented oil return groove for turbine engine

Abstract

A gearbox assembly for a turbine engine. The gearbox assembly includes a gearbox having a plurality of gears, and a return chute located radially outward of the gearbox and mounted to a fan frame flange of a fan frame of the turbine engine, the return chute configured to collect lubricant injected by the plurality of gears of the gearbox during rotation of the plurality of gears. An interface between the fan frame flange and the oil return chute is located at a first radial distance R1 relative to a longitudinal centerline axis of the turbine engine, and the oil return chute is located at a second radial distance R2 relative to the longitudinal centerline axis. The second radial distance R2 is greater than the first radial distance R1. The return chute is segmented and includes a plurality of fan-shaped portions that are joined together to form the return chute.

Description

TECHNICAL FIELD

[0001] The present disclosure relates generally to a gearbox assembly for a turbine engine. BACKGROUND

[0002] For example, turbine engines for aircraft generally include a fan and a turbocharger engine arranged in flow communication with one another. Some turbine engines include a speed sensor for sensing a rotational speed of one or more rotating components of the turbine engine. BRIEF DESCRIPTION OF DRAWINGS

[0003] The foregoing and other features and advantages of the present disclosure will be apparent to those skilled in the art, from the following more particular description of various exemplary embodiments thereof, as illustrated in the accompanying drawings, in which like reference numerals generally represent like, functionally similar, or structurally similar elements.

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

[0005] Figure 2 is a partial schematic cross-sectional view of a turbine engine having a fan speed sensor system, taken at detail 2 in Figure 1 Figure 1 is a partial schematic cross-sectional view of a turbine engine having a fan speed sensor system, taken at detail 2 in

[0006] Figure 3A is a schematic cross-sectional view of an upper half of an oil return sump of a gearbox assembly of a turbine engine, in accordance with an embodiment of the present disclosure.

[0007] Figure 3B is a schematic cross-sectional view of an upper half of an oil return sump, in accordance with another embodiment of the present disclosure.

[0008] Figure 4 is a partial schematic cross-sectional view of a turbine engine, taken at detail 4 in Figure 2

[0009] Figure 5 is a partial schematic cross-sectional view of a turbine engine, taken at detail 4 in

[0010] Figure 6 is a partial schematic cross-sectional view of a turbine engine, taken at detail 4 in

[0011] Figures 7A to 7H ​​This is a partial schematic cross-sectional view of a turbine engine taken at various stages of installing the return oil sump to the fan hub of the turbine engine, according to embodiments of the present disclosure. Detailed Implementation

[0012] 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.

[0013] 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.

[0014] 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.

[0015] 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.

[0016] The terms "front" and "rear" refer to relative positions within a turbine engine or vehicle, and 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 engine inlet, and "rear" refers to the position closer to the engine nozzle or exhaust port.

[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] 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.

[0020] This disclosure provides a segmented return groove for a gearbox assembly in a turbine engine. Rotating gearboxes centrifugally and outwardly inject large quantities of lubricant (e.g., oil), particularly in radial gearbox configurations. A lubricant collector, commonly referred to as a return groove, is positioned radially outside the gearbox of a gearbox containing multiple gears of the gearbox assembly to collect the lubricant and guide it from the gearbox cavity into the return groove. The return groove is the outermost part of the gearbox assembly and therefore likely sets the minimum radius of the airflow path of the turbocharger that allows airflow into the turbine engine through the fan frame. This can affect the fan hub radius ratio, which influences fan aerodynamic efficiency and reduces the fan diameter of the entire propulsion system. However, with a segmented return groove, the airflow path can be more tightly encapsulated within the gearbox of the gearbox assembly, thereby improving fan aerodynamic efficiency, reducing fan diameter, and improving turbocharger performance (due to the turbocharger inlet radius ratio). The turbocharger inlet radius ratio is the ratio of the radius of the first stage of the turbocharger or the ratio of the leading edge radius of the LP compressor rotor hub to the leading edge radius of the LP compressor rotor tip. The turbocharger inlet radius ratio provides a measure of how tightly the gearbox is packaged. If the gearbox is large, the turbocharger must be moved radially outward to accommodate it. A tighter encapsulation of the airflow path into the gearbox can be achieved by installing the gearbox assembly into any number of slots in the turbine engine's fan frame before mounting the gearbox into the fan frame.

[0021] Now refer to the attached diagram, Figure 1 This is a schematic cross-sectional view of the turbine engine 110 taken along the longitudinal centerline axis 112 of the turbine engine 110 according to an embodiment of the present disclosure. Figure 1 As shown, the turbine engine 110 defines an axial direction A (extending parallel to the longitudinal centerline axis 112) and a radial direction R orthogonal to the axial direction A. Typically, the turbine engine 110 includes a fan assembly 114 and a turbocharger engine 116 disposed downstream of the fan assembly 114.

[0022] The turbocharged engine 116 comprises a compressor section 121, a combustor 126, and a turbine section 127 in a series flow relationship. The turbocharged engine 116 is substantially enclosed within a core housing 118 (e.g., a casing), which is substantially tubular and defines a core inlet 120 having an annular shape about a longitudinal centerline axis 112. Figure 1As schematically shown, compressor section 121 includes a turbocharger or low-pressure (LP) compressor 122, downstream of which follows a high-pressure (HP) compressor 124. Combustion 126 is located downstream of compressor section 121. Turbine section 127 is located downstream of combustor 126 and includes a high-pressure (HP) turbine 128, downstream of which follows a low-pressure (LP) turbine 130, also referred to as a power turbine. Turbocharged engine 116 also includes a core exhaust nozzle 132 located downstream of turbine section 127. Turbocharged engine 116 also includes a high-pressure (HP) shaft 134, also referred to as a high-speed shaft, which drivesly connects HP turbine 128 to HP compressor 124. HP turbine 128 and HP compressor 124 rotate synchronously via HP shaft 134. Turbocharged engine 116 includes a low-pressure (LP) shaft 136, also referred to as a low-speed shaft, which drivesly connects LP turbine 130 to LP compressor 122. LP turbine 130 and LP compressor 122 rotate synchronously via LP shaft 136. The compressor section 121, burner 126, turbine section 127 and core exhaust nozzle 132 together define the core airflow path.

[0023] for Figure 1 In the illustrated embodiment, fan assembly 114 includes a fan 138 (e.g., a variable pitch fan) having a plurality of fan blades 140 spaced apart and coupled to fan disk 142. Figure 1 As shown, fan blades 140 generally extend outward from fan disk 142 along a radial direction R. Each fan blade 140 is operatively coupled to a fan actuation system 144 by means of the fan blades 140, which is rotatable relative to the fan disk 142 about a pitch axis P. The fan actuation system 144 is configured to collectively and uniformly change the pitch of the fan blades 140, as described in further detail below. The fan actuation system 144 is disposed within a fan hub 148. The fan blades 140, fan disk 142, and fan actuation system 144 are rotatable together about a longitudinal centerline axis 112 via a fan shaft 145, which is powered by an LP shaft 136 across a power gearbox (also referred to as gearbox assembly 146) (i.e., integral drive configuration).

[0024] Gearbox assembly 146 in Figure 1The diagram is schematically shown. Gearbox assembly 146 includes multiple gears for regulating the rotational speed of fan shaft 145, and thus the rotational speed of fan 138 relative to LP shaft 136. For a tubular engine (e.g., turbine engine 110), gearbox assembly 146 has a gear ratio in the range of 3.5:1 to 5:1. LP shaft 136, gearbox assembly 146, and fan shaft 145 are arranged in an in-line configuration such that LP shaft 136, gearbox assembly 146, and fan shaft 145 are coaxial and each is arranged about a longitudinal centerline axis 112. Compared to turboprop engines, the in-line configuration helps reduce the space required within turbine engine 110 for gearbox assembly 146 and allows a greater amount of torque to be transmitted through gearbox assembly 146 from LP shaft 136 to fan shaft 145. In turboprop engines, gearbox assembly 146 is typically arranged in a stepped configuration and is not coaxial with LP shaft and fan shaft.

[0025] Still referencing Figure 1 In an exemplary embodiment, the fan disk 142 is covered by a fan hub 148, which rotates and has an aerodynamic profile to facilitate airflow through a plurality of fan blades 140. Furthermore, the fan assembly 114 includes an annular fan housing or nacelle 150 circumferentially surrounding at least a portion of the fan 138 and the turbocharged engine 116. Thus, the turbocharged engine 110 is a ducted engine. The nacelle 150 is supported relative to the turbocharged engine 116 by a fan frame 151 having a plurality of fan guide blades 152, also referred to as outlet guide blades, circumferentially spaced around the nacelle 150. Additionally, a downstream section 154 of the nacelle 150 extends above the outer portion of the turbocharged engine 116 to define a bypass airflow passage 156 therebetween.

[0026] During operation of the turbine engine 110, a volume of air 158 enters the turbine engine 110 through the nacelle 150 or the inlet 160 of the fan assembly 114. As the volume of air 158 passes through the fan blades 140, a first portion of the air, referred to as bypass air 162, is directed into the bypass airflow passage 156, and a second portion of the air, referred to as core air 164, is directed into the upstream section of the core air flow path, or more specifically, into the core inlet 120 of the LP compressor 122. The ratio between bypass air 162 and core air 164 is commonly referred to as the bypass ratio. The LP compressor 122 then increases the pressure of the core air 164 to produce compressed air 165, and the compressed air 165 is directed through the HP compressor 124 into the combustor 126, where it is mixed with fuel and burned to produce combustion gases 166.

[0027] Combustion gas 166 is directed into and expanded in HP turbine 128, where a first portion of the thermal and kinetic energy from the combustion gas 166 is extracted via one or more stages of HP turbine stator blades 168 connected to core housing 118 and HP turbine rotor blades 170 connected to HP shaft 134. This causes HP shaft 134 to rotate, thereby supporting the operation of HP compressor 124 (e.g., self-sustaining cycle). Thus, combustion gas 166 performs work in HP turbine 128 to rotate HP turbine rotor blades 170 (and HP shaft 134) at a sufficient rate to maintain the compression ratio of HP compressor 124 (e.g., self-sustaining cycle). Combustion gas 166 is then directed into and expanded in LP turbine 130. Here, a second portion of the thermal and kinetic energy is extracted from combustion gas 166 via one or more stages of LP turbine stator blades 172 connected to core housing 118 and LP turbine rotor blades 174 connected to LP shaft 136. This causes the LP shaft 136 to rotate, thereby supporting the operation of the LP compressor 122 and the rotation of the fan 138 via the gearbox assembly 146 (e.g., self-sustaining circulation). In this way, the combustion gas 166 does work in the LP turbine 130, causing the LP turbine rotor blades 174 (and the LP shaft 136) to rotate.

[0028] Combustion gases 166 are then directed through the core exhaust nozzle 132 of the turbocharged engine 116 to provide propulsive thrust. Simultaneously, bypass air 162 is directed through bypass airflow passage 156 before exiting from the fan exhaust nozzle 176 of the turbocharged engine 110, also providing propulsive thrust. The HP turbine 128, LP turbine 130, and core exhaust nozzle 132 at least partially define a hot gas path 178 for directing combustion gases 166 through the turbocharged engine 116.

[0029] The turbine engine 110 includes a fuel system 180 for supplying fuel to the burner 126. For example, the fuel system 180 may include a fuel tank for storing fuel, one or more fuel lines in flow communication with the fuel tank and the burner 126, and a fuel pump for delivering fuel from the fuel tank to the burner 126 via one or more fuel lines.

[0030] The turbine engine 110 includes a controller 190. The controller 190 communicates with the turbine engine 110 to control various aspects of the turbine engine 110. For example, the controller 190 communicates bidirectionally with the turbine engine 110 to receive signals from various sensors (e.g., speed sensors described in detail herein) and the turbine engine 110's control system (e.g., fuel system 180), and to control components of the turbine engine 110 (e.g., fan blades 140), as described further in detail below. The controller 190 or components thereof may be located on the turbine engine 110, on the aircraft, or remotely from each location within the turbine engine 110 and the aircraft. The controller 190 may be a Full Authority Digital Engine Control (FADEC) system that controls various aspects of the turbine engine 110.

[0031] Controller 190 may be a standalone controller or part of an engine controller to operate various systems of the turbine engine 110. In this embodiment, controller 190 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). 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.

[0032] 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 190 to perform operations. Controller 190, 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 that controller 190 is configured for, as will be further described below. Instructions may be software written in any suitable programming language or implemented in hardware. Additionally, or alternatively, instructions may execute in logically or virtually independent threads on the processors. The memory may also store data accessible by one or more processors.

[0033] 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, memories, instructions, and applications can be implemented on a single system or distributed across multiple systems. Distributed components can operate sequentially or in parallel.

[0034] Figure 1 The turbine engine 110 depicted is merely an example. In other exemplary embodiments, the turbine engine 110 may have other suitable configurations. 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 other suitable turbine engines, such as propeller fan (e.g., ductless fan) engines, turboprop engines, etc.

[0035] Figure 2 It is based on this disclosure Figure 1 The image shows a partial schematic cross-sectional view of the turbine engine 110 with an oil return groove 200, taken from detail 2. Figure 2 As shown, core shield 118 (also) Figure 1 (As shown in the image) includes a hollow interior 119. The core inlet 120 includes inlet guide vanes 123, which direct core air 164 (…). Figure 1 The flow is directed to the turbocharged engine 116 ( Figure 1 As shown in the diagram. Fan frame 151 includes fan frame flange 153. Gearbox assembly 146 (oil return gearbox) is coupled to fan frame flange 153 such that fan frame 151 supports gearbox assembly 146 via fan frame flange 153. Fan frame flange 153 also rotatably supports fan shaft 145 via one or more bearings 147. Turbine engine 110 also includes lubricant groove 149 positioned about gearbox assembly 146 for collecting lubricant (e.g., oil) supplied to one or more bearings 147 and gearbox assembly 146. Specifically, lubricant groove 149 is radially positioned within fan frame 151. In an embodiment, lubricant groove 149 is an oil-lubricated bearing groove. Fan 138 includes fan rotor assembly 139, which includes fan disk 142.

[0036] Gearbox assembly 146 includes a gearbox 197 having a plurality of gears 198 and an oil return groove 200. The oil return groove 200 serves as a lubricant collector to collect lubricant ejected by the plurality of gears 198 of the gearbox 197 during rotation of the plurality of gears 198. The oil return groove 200 is configured to collect lubricant and guide it from a gearbox cavity 199 housing the plurality of gears 198 of the gearbox 197 into a collection groove (not shown). The oil return groove 200 is located radially outside the plurality of gears 198 of the gearbox assembly 146 relative to the longitudinal centerline axis 112. Furthermore, the oil return groove 200 is also located radially outside the interface 153A between the fan frame flange 153 and the oil return groove 200. Figure 2 As shown, the interface 153A between the fan frame flange 153 and the oil return groove 200 is located at a first radial distance R1 relative to the longitudinal centerline axis 112, and the oil return groove 200 is located at a second radial distance R2 relative to the longitudinal centerline axis 112. The second radial distance R2 is greater than the first radial distance R1. The oil return groove 200 is provided radially outside the interface 153A between the fan frame flange 153 and the oil return groove 200, and the oil return groove 200 is the outermost part of the gearbox assembly 146. The oil return groove 200 can be configured to allow oil to enter the turbine engine 110 through the fan frame. Figure 1 The minimum airflow path radius of the turbocharged engine 116 (as shown in the diagram) is thus affected. Therefore, the radial position of the oil return sump 200 may influence the radius ratio of the fan hub 148, which could affect fan aerodynamic efficiency and ultimately affect the fan 138 (as shown in the diagram). Figure 1 The diameter of the fan 138 is shown in the figure. Therefore, positioning the return groove 200 radially outward of the fan frame flange 153 allows for more space for the gearbox assembly 146 and the associated return groove 200, while reducing the radius of the fan hub 148 and ultimately reducing the diameter of the fan 138.

[0037] In one embodiment, the oil return groove 200 may have an annular shape. In another embodiment, the oil return groove 200 may be segmented.

[0038] Figure 3A This is a schematic cross-sectional view of the upper half of the oil return groove 200 according to an embodiment of the present invention. In the embodiment, as... Figure 3A As shown, the oil return groove 200 is annular and segmented in the circumferential direction around the longitudinal centerline axis 112 into a first plurality of sector portions 200A. In another embodiment, the oil return groove 200 is annular and segmented in the longitudinal direction along the longitudinal centerline axis. As will be further described below, the first plurality of sector portions 200A of the oil return groove 200 are assembled to form the oil return groove 200. Figure 3AOnly the upper half of the oil return groove 200 is shown. However, the lower half of the oil return groove 200 is similar to the upper half. By segmenting the oil return groove 200, the airflow path can be more tightly encapsulated within the gearbox assembly 146, thereby improving fan aerodynamic efficiency, reducing fan diameter, and improving turbocharger performance (due to the turbocharger radius ratio). This can be achieved, for example, by mounting the remaining portion of the gearbox assembly 146 to the fan frame 151 ( Figure 2 As shown, any number of first plurality of sector sections 200A can be installed into the fan frame 151 previously.

[0039] Figure 3B This is a schematic cross-sectional view of the upper half of the oil return groove 200 according to another embodiment of the present invention. In the embodiment, as... Figure 3B As shown, the oil return groove 200 is annular and segmented circumferentially around the longitudinal centerline axis 112 into a first plurality of sector-shaped portions 200A and a second plurality of sector-shaped portions 200B. The first plurality of sector-shaped portions 200A and the second plurality of sector-shaped portions 200B of the oil return groove 200 are joined together to form the oil return groove 200. The second plurality of sector-shaped portions 200B of the oil return groove 200 contact the first plurality of sector-shaped portions 200A of the oil return groove 200 via a plurality of sealing members 200C. Figure 3B As shown, the first plurality of sector-shaped portions 200A and the second plurality of sector-shaped portions of the oil return groove 200 alternate to form an oil return groove 200 having an annular shape. The first plurality of sector-shaped portions 200A overlap with the second plurality of sector-shaped portions 200B, and a sealing member 200C is disposed between the overlapping portions of the first plurality of sector-shaped portions 200A and the second plurality of sector-shaped portions 200B. Figure 3B Only the upper half of the return oil groove 200 is shown. However, the lower half of the return oil groove 200 is similar to the upper half.

[0040] Figure 4 It is based on the embodiments of this disclosure. Figure 2 The schematic cross-sectional view of the turbine engine 110, taken at detail 4, shows a portion of the oil return groove 200 of the gearbox assembly 146, which is segmented in the circumferential direction. (See details below.) Figure 4 As shown, the gearbox assembly 146 also includes a mounting assembly 400 for mounting the oil return groove 200 to the fan frame 151. The mounting assembly 400 includes a first plurality of fastener segments 400A (e.g., C-clamp segments) connected to the fan frame 151 and a second plurality of fastener segments 400B not connected to the fan frame 151. The oil return groove 200 has a plurality of arms 202 configured to mate with the first plurality of fastener segments 400A and the second plurality of fastener segments 400B of the mounting assembly 400. Figure 4As shown, the return groove 200 with arms 202 forms an "H-shape". However, other shapes are also possible. The mounting assembly 400 may also include a stop 400C, which is configured to apply force to a second plurality of fastener segments 400B once the plurality of arms 202 of the return groove 200 are mounted to a first plurality of fastener segments 400A, to secure the second plurality of fastener segments 400B to one or more of the plurality of arms 202. The stop 400C is attached to the fan frame 151 using one or more fasteners 400D.

[0041] In another embodiment, mounting component 400 may not be used. In this case, oil return groove 200 may be incorporated into fan frame 151.

[0042] Figure 5 According to another embodiment of this disclosure Figure 2 A partial schematic cross-sectional view of the turbine engine 110 shows a portion of the oil return groove 300 of the gearbox assembly 146. (See attached image.) Figure 5 As shown, the oil return groove 300 is a component of the fan frame 151. For example, the oil return groove 300 may be formed of the same material as a part of the fan frame 151. Figure 5 As shown, the oil return groove 300 may have an inverted "V-shape", wherein the apex of the "V-shape" is connected to the fan frame 151.

[0043] Figure 6 This is a partial schematic cross-sectional view of a turbine engine 110 according to another embodiment of the present disclosure, showing a portion of the oil return groove 200 of a gearbox assembly 146 segmented in the longitudinal direction. This embodiment is similar in some respects to... Figure 4 The embodiment shown. Therefore, in Figure 6 The same reference numerals are used to represent the same parts. Figure 4 In the embodiment shown, the oil return groove 200 is annular and is segmented in the circumferential direction around the longitudinal centerline axis 112 into a first plurality of sector-shaped portions 200A and a second plurality of sector-shaped portions 200B, as shown. Figure 3A and Figure 3B As shown. In Figure 6 In the embodiment shown, the return oil groove 200 is annular and extends along the longitudinal centerline axis 112. Figure 2 (As shown) it is segmented in the longitudinal direction. For example, as... Figure 6As shown, the oil return groove 200 is divided into multiple longitudinal segments along the dividing line 601, and specifically into a first longitudinal segment 600A and a second longitudinal segment 600B. The first longitudinal segment 600A of the oil return groove 200 is provided with a first attachment element 602. The first attachment element 602 has a groove 602A. The second longitudinal segment 600B of the oil return groove 200 is provided with a second attachment element 604. The second attachment element 604 has a tongue 604A. The tongue 604A is configured to mate with the groove 602A so as to extend along the longitudinal centerline axis 112 (…). Figure 2 As shown, the second attachment element 604 is connected to the first attachment element 602 in the longitudinal direction, and thus the second longitudinal segment 600B is connected to the first longitudinal segment 600A. A fastener 603 (e.g., a C-clamp) may optionally be used to fasten the first attachment element 602 to the second attachment element 604.

[0044] Figures 7A to 7H This is a partial schematic cross-sectional view of a turbine engine 110 taken at various stages of mounting the return oil sump 200 to the fan frame 151 according to embodiments of the present disclosure. Figures 7A to 7H The assembly shelf from the oil return trough 200 to the fan frame 151 is shown. Initially, as... Figure 7A and Figure 7B As shown, the first sector 201 of the oil return groove 200 passes between the longitudinal centerline axis 112 and the fan frame flange 153 (e.g., below the fan frame flange 153 in the example shown). Then, as Figure 7C As shown, the first sector portion 201 of the oil return groove 200 is brought closer to the first plurality of fastener segments 400A of the mounting assembly 400. Then, as Figure 7D and Figure 7E As shown, the first sector portion 201 of the oil return groove 200 is installed onto the first plurality of fastener segments 400A of the mounting assembly 400 by engaging multiple arms 202 of the first sector portion 201 of the oil return groove 200 with first plurality of fastener segments 400A. After the multiple arms 202 of the first sector portion 201 of the oil return groove 200 are installed onto the first plurality of fastener segments 400A, a stopper 400C is used to lock a second plurality of fastener segments 400B onto the multiple arms 202 to prevent the first sector portion 201 of the oil return groove 200 from disconnecting from the mounting assembly 400, as shown. Figure 7F As shown.

[0045] like Figure 7A and Figure 7BAs shown, a second sector-shaped portion (not shown) of the oil return groove 200 passes between the fan frame flange 153 and the longitudinal centerline axis 112. The second sector-shaped portion of the oil return groove 200 can be similar to the first sector-shaped portion 201 of the oil return groove 200. For example, the first sector-shaped portion 201 can be one of a first plurality of sector-shaped portions 200A or one of a second plurality of sector-shaped portions 200B. Figure 3A and Figure 3B (As shown). For example, the second sector (not shown) can be one of the first plurality of sector portions 200A or one of the second plurality of sector portions 200B. Figure 3A and Figure 3B (As shown in the diagram). The second sector is in Figures 7A to 7H The second sector (not shown) can be installed using a similar installation process to that described above for the first sector 201. Therefore, when describing the process of installing the second sector (not shown), reference will be made to the same... Figures 7A to 7H .like Figure 7C As shown, the second sector of the oil return groove 200 is closer to the first plurality of fastener segments 400A of the mounting assembly 400. Then, as Figure 7D and Figure 7E As shown, the second sector portion of the oil return groove 200 is installed onto the first plurality of fastener segments 400A of the mounting assembly 400 by engaging multiple arms 202 of the second sector portion of the oil return groove 200 with first plurality of fastener segments 400A. Figure 7F As shown, after the multiple arms 202 of the second sector portion of the oil return groove 200 are installed onto the first plurality of fastener segments 400A, the second plurality of fastener segments 400B are locked onto the multiple arms 2020 using a stopper 400C to prevent the second sector portion of the oil return groove 200 from disconnecting from the mounting assembly 400. This process is repeated multiple times until all sector portions of the oil return groove 200 are installed to form an oil return groove 200 with an annular shape. After all sector portions are installed, the oil return groove 200 can have a shape similar to... Figure 3A A structure similar to the one shown, or having the same structure as... Figure 3B The structure shown is similar to the one described.

[0046] Then, as Figure 7G As shown, a plurality of gears 198 having a gearbox assembly 146 Figure 2 The gearbox 197 passes between the fan frame flange 153 and the longitudinal centerline axis 112 (e.g., below the fan frame flange 153). Then, as... Figure 7H As shown, the gearbox 197 of the gearbox assembly 146 contacts the oil return groove 200 and is then connected to the fan frame flange 153, such that the fan frame 151 supports the gearbox assembly 146 via the fan frame flange 153. Figure 2As shown. Therefore, dividing the oil return groove 200 into multiple sector-shaped sections facilitates its installation. In the above embodiment, the gearbox 197 of the gearbox assembly 146 passes between the fan frame flange 153 and the longitudinal centerline axis 112 (e.g., below the fan frame flange 153) and is installed onto the fan frame flange 153 after the multiple sector-shaped sections of the oil return groove 200 are installed. In another embodiment, before the multiple sector-shaped sections of the oil return groove 200 are installed, the gearbox 197 of the gearbox assembly 146 passes between the fan frame flange 153 and the longitudinal centerline axis 112 (e.g., below the fan frame flange 153) and is installed onto the fan frame 151.

[0047] Further aspects are provided by the following items.

[0048] A gearbox assembly for a turbine engine includes a gearbox having a plurality of gears; and an oil return groove located radially outward of the gearbox and mounted to a fan frame flange of a fan frame of the turbine engine. The oil return groove is configured to collect lubricant ejected by the plurality of gears during rotation of the plurality of gears. The interface between the fan frame flange and the oil return groove is located at a first radial distance R1 relative to the longitudinal centerline axis of the turbine engine, and the oil return groove is located at a second radial distance R2 relative to the longitudinal centerline axis, the second radial distance R2 being greater than the first radial distance R1. The oil return groove is segmented and includes a plurality of fan-shaped portions that join together to form the oil return groove.

[0049] According to the gearbox assembly described in the foregoing clause, the oil return groove is annular and segmented in the circumferential direction around the longitudinal centerline axis.

[0050] The gearbox assembly according to any of the preceding clauses, wherein the oil return groove is annular and segmented in the longitudinal direction along the longitudinal centerline axis.

[0051] The gearbox assembly according to any of the foregoing clauses, wherein the oil return groove is part of the fan frame.

[0052] The gearbox assembly according to any of the foregoing clauses, wherein the oil return groove is formed of the same material as the fan frame.

[0053] The gearbox assembly according to any of the preceding clauses, wherein the plurality of sector portions includes a first plurality of sector portions and a second plurality of sector portions, the first plurality of sector portions and the second plurality of sector portions are joined together to form the oil return groove, the first plurality of sector portions and the second plurality of sector portions alternate, and the first plurality of sector portions contact the second plurality of sector portions via a plurality of sealing members.

[0054] The gearbox assembly according to any of the preceding clauses, wherein the first plurality of sector portions overlap with the second plurality of sector portions, and the sealing member is disposed between the overlapping portions of the first plurality of sector portions and the second plurality of sector portions.

[0055] The gearbox assembly according to any of the preceding clauses further includes a mounting assembly configured to mount the oil return groove to the fan frame.

[0056] The gearbox assembly according to any of the preceding clauses, wherein the mounting assembly includes a first plurality of fastener segments, a second plurality of fastener segments, and a stop, the first plurality of fastener segments being connected to the fan frame, the second plurality of fastener segments not being connected to the fan frame, and the stop being configured to apply force on the second plurality of fastener segments to prevent the return groove from being disconnected from the mounting assembly.

[0057] The gearbox assembly according to any of the preceding clauses, wherein the oil return groove has a plurality of arms configured to engage with the first plurality of fastener segments and the second plurality of fastener segments.

[0058] The gearbox assembly according to any of the preceding clauses, wherein the stop is configured to apply force against one or more of the plurality of arms on the second plurality of fastener segments.

[0059] The gearbox assembly according to any of the preceding clauses, wherein the oil return groove comprises a plurality of longitudinal sections.

[0060] The gearbox assembly according to any of the preceding clauses, wherein the oil return groove includes a first longitudinal section and a second longitudinal section.

[0061] According to any of the preceding clauses, the gearbox assembly wherein the first longitudinal section of the oil return groove is provided with a first attachment element having a groove.

[0062] The gearbox assembly according to any of the preceding clauses, wherein the second longitudinal section of the oil return groove is provided with a second attachment element having a tongue.

[0063] According to any of the preceding clauses, the gearbox assembly wherein the tongue is configured to engage with the groove to connect the second attachment element to the first attachment element in the longitudinal direction along the longitudinal centerline axis, and to connect the second longitudinal segment to the first longitudinal segment.

[0064] The gearbox assembly according to any of the preceding clauses further includes a fastener configured to secure the first attachment element to the second attachment element.

[0065] A turbine engine includes a fan frame and a fan frame flange connected to the fan frame; and a gearbox assembly including a gearbox having a plurality of gears; and an oil return groove located radially outward of the gearbox and mounted to the fan frame flange, the oil return groove being configured to collect lubricant ejected by the plurality of gears during rotation of the plurality of gears. The interface between the fan frame flange and the oil return groove is located at a first radial distance R1 relative to the longitudinal centerline axis of the turbine engine, and the oil return groove is located at a second radial distance R2 relative to the longitudinal centerline axis, the second radial distance R2 being greater than the first radial distance R1, and the oil return groove is segmented and includes a plurality of fan-shaped portions that join together to form the oil return groove.

[0066] According to the turbine engine described in the foregoing clause, the oil return groove is annular and segmented in the circumferential direction around the longitudinal centerline axis.

[0067] The turbine engine according to any of the preceding clauses, wherein the oil return groove is annular and segmented in the longitudinal direction along the longitudinal centerline axis.

[0068] The turbine engine according to any of the preceding clauses, wherein the oil return groove is part of the fan frame.

[0069] The turbine engine according to any of the preceding clauses, wherein the oil return groove is formed of the same material as the fan frame.

[0070] The turbine engine according to any of the preceding clauses, wherein the plurality of sector portions includes a first plurality of sector portions and a second plurality of sector portions, the first plurality of sector portions and the second plurality of sector portions are joined together to form the oil return groove, the first plurality of sector portions and the second plurality of sector portions alternate, and the first plurality of sector portions contact the second plurality of sector portions via a plurality of sealing members.

[0071] The turbine engine according to any of the preceding clauses, wherein the first plurality of sector portions overlap with the second plurality of sector portions, and the sealing member is disposed between the overlapping portions of the first plurality of sector portions and the second plurality of sector portions.

[0072] The turbine engine according to any of the foregoing items further includes a mounting assembly configured to mount the oil return groove to the fan frame.

[0073] The turbine engine according to any of the preceding clauses, wherein the mounting assembly includes a first plurality of fastener segments, a second plurality of fastener segments, and a stopper, the first plurality of fastener segments being connected to the fan frame, the second plurality of fastener segments not being connected to the fan frame, and the stopper being configured to apply force on the second plurality of fastener segments to prevent the return oil groove from being disconnected from the mounting assembly.

[0074] The turbine engine according to any of the preceding clauses, wherein the oil return groove has a plurality of arms configured to cooperate with the first plurality of fastener segments and the second plurality of fastener segments.

[0075] According to any of the preceding clauses, the turbine engine wherein the stop is configured to apply force against one or more of the plurality of arms on the second plurality of fastener segments.

[0076] The turbine engine according to any of the preceding clauses, wherein the oil return groove comprises a plurality of longitudinal sections.

[0077] The turbine engine according to any of the preceding clauses, wherein the oil return groove includes a first longitudinal section and a second longitudinal section.

[0078] The turbine engine according to any of the preceding clauses, wherein the first longitudinal section of the oil return groove is provided with a first attachment element having a groove.

[0079] The turbine engine according to any of the preceding clauses, wherein the second longitudinal section of the oil return groove is provided with a second attachment element having a tongue.

[0080] According to any of the preceding clauses, the turbine engine wherein the tongue is configured to engage with the groove to connect the second attachment element to the first attachment element in the longitudinal direction along the longitudinal centerline axis, and to connect the second longitudinal segment to the first longitudinal segment.

[0081] The turbine engine according to any of the preceding clauses further includes a fastener configured to secure the first attachment element to the second attachment element.

[0082] A method for mounting a gearbox assembly having a gearbox and an oil return groove to a fan frame flange of a turbine, the method comprising: passing a first sector of the oil return groove of the gearbox assembly between the fan frame flange of the turbine and a longitudinal centerline axis; mounting the first sector of the oil return groove to a plurality of fastener segments of a mounting assembly; passing a second sector of the oil return groove of the gearbox assembly between the fan frame flange of the turbine and the longitudinal centerline axis; mounting the second sector of the oil return groove to the plurality of fastener segments of the mounting assembly; passing the gearbox of the gearbox assembly between the fan frame flange of the turbine and the longitudinal centerline axis; and mounting the gearbox to the fan frame flange to support the gearbox.

[0083] The method described in the foregoing clauses further includes repeatedly installing the first sector portion of the oil return groove and installing the second sector portion of the oil return groove until all sector portions of the oil return groove are installed.

[0084] The method according to any of the preceding clauses further includes installing the first sector portion of the oil return groove and the second sector portion of the oil return groove before installing the gearbox to the fan frame flange.

[0085] The method according to any of the foregoing clauses further includes, after mounting the gearbox to the fan frame flange, mounting the first sector portion of the oil return groove and mounting the second sector portion of the oil return groove.

[0086] According to the method of any of the preceding clauses, installing the first sector portion of the oil return groove to the plurality of fastener segments includes engaging a plurality of arms of the first sector portion of the oil return groove with the plurality of fastener segments.

[0087] The method according to any of the preceding clauses further includes using a stopper to lock one or more of the plurality of fastener segments onto one or more of the plurality of arms in order to prevent the first sector portion of the oil return groove from being disconnected from the mounting assembly.

[0088] According to the method of any of the preceding clauses, installing the second sector portion of the oil return groove to the plurality of fastener segments includes engaging a plurality of arms of the second sector portion of the oil return groove with the plurality of fastener segments.

[0089] The method according to any of the preceding clauses further includes using a stopper to lock one or more of the plurality of fastener segments onto one or more of the plurality of arms in order to prevent the second sector portion of the oil return groove from being disconnected from the mounting assembly.

[0090] 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, even if not explicitly stated above, features described in connection with one embodiment of the present disclosure can be used in conjunction with other embodiments.

Claims

1. A gearbox assembly for a turbine engine, characterized by, The gearbox assembly comprises: a gearbox having a plurality of gears; and an oil return groove located radially outward of the gearbox and mounted to a fan frame flange of a fan frame of the turbine engine, the oil return groove being configured to collect lubricant ejected by the plurality of gears of the gearbox during rotation of the plurality of gears, wherein an interface between the fan frame flange and the oil return groove is located at a first radial distance R1 with respect to a longitudinal centerline axis of the turbine engine, and the oil return groove is located at a second radial distance R2 with respect to the longitudinal centerline axis, the second radial distance R2 being greater than the first radial distance R1, and wherein the oil return groove is segmented and comprises a plurality of sector portions that are joined together to form the oil return groove.

2. The gearbox assembly of claim 1, wherein, wherein the oil return groove is annular and segmented in a circumferential direction around the longitudinal centerline axis.

3. The gearbox assembly of claim 1, wherein, wherein the oil return groove is annular and segmented in a longitudinal direction along the longitudinal centerline axis.

4. The gearbox assembly of claim 1, wherein, wherein the oil return groove is an integral part of the fan frame.

5. The gearbox assembly of claim 4, wherein, wherein the oil return groove is formed from the same material as the fan frame.

6. The gearbox assembly of claim 1, wherein, wherein the plurality of sector portions comprises a first plurality of sector portions and a second plurality of sector portions, the first plurality of sector portions and the second plurality of sector portions being joined together to form the oil return groove, the first plurality of sector portions alternating with the second plurality of sector portions, and the first plurality of sector portions being in contact with the second plurality of sector portions via a plurality of sealing members.

7. The gearbox assembly of claim 6, wherein, wherein the first plurality of sector portions overlap the second plurality of sector portions, and the sealing members are disposed between the overlapping portions of the first plurality of sector portions and the second plurality of sector portions.

8. The gearbox assembly of claim 1, wherein, further comprising a mounting assembly configured to mount the oil return groove to the fan frame.

9. The gearbox assembly of claim 8, wherein, wherein the mounting assembly comprises a first plurality of fastener segments connected to the fan frame, a second plurality of fastener segments not connected to the fan frame, and a stopper configured to exert a force on the second plurality of fastener segments so as to prevent the oil return groove from being disconnected from the mounting assembly.

10. The gearbox assembly of claim 9, wherein, wherein the oil return groove has a plurality of arms configured to mate with the first plurality of fastener segments and the second plurality of fastener segments.

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