Accessory gearboxes for turbine engines

Abstract

A turbine engine includes an engine core, an inner shroud, an outer shroud and an accessory gearbox. The engine core includes at least a compressor section, a combustion section and a turbine section arranged in an axial flow. The accessory gearbox is operably coupled to the engine core and includes a first portion and a second portion.

Description

Technical Field

[0001] The present disclosure relates to an accessory gearbox (sometimes also referred to as an accessory case), and more particularly, to an accessory gearbox for a turbine engine. Background Art

[0002] Gas turbine engines often include an accessory gearbox to provide power to or drive accessory systems (sometimes referred to as auxiliary systems), such as fuel pumps, lubrication pumps, air compressors, oil return pumps, generators, hydraulic pumps, etc. The accessory gearbox may be driven by one or more components of the gas turbine engine. When powered or mechanically driven by the gas turbine engine, the accessory gearbox may be connected to accessory systems that require different rotational inputs, torques, or horsepower. Summary of the invention

[0003] Aspects and advantages of the disclosure will be set forth in part in the following description, or may be obvious from the description, or may be learned through practice of the disclosure.

[0004] In one aspect, the present disclosure is directed to a turbine engine comprising an engine core, an inner shroud radially spaced from and circumscribing the engine core, an outer shroud radially spaced from and circumscribing at least a portion of the inner shroud, and an accessory gearbox comprising a first portion located within the inner shroud and spanning the engine core and a second portion located between the inner shroud and the outer shroud.

[0005] In another aspect, the present disclosure is directed to a turbine engine comprising a fan assembly defining an inlet; an engine core; an inner shroud radially spaced from the engine core and having an inner face that circumscribes at least a portion of the engine core; an outer shroud radially spaced from the inner shroud and circumscribes at least a portion of the inner shroud; a bifurcated airflow path comprising a first portion extending from the inlet through the engine core and a second portion extending from the inlet through a secondary airflow path defined between the inner shroud and the outer shroud; and an accessory gearbox having a first portion located within the inner shroud and a second portion located in the secondary airflow path.

[0006] These and other features, aspects and advantages of the present disclosure will become better understood with reference to the following description and appended claims.The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate aspects of the present disclosure and, together with the description, serve to explain the principles of the present disclosure.

[0007] Technical Solution 1. A turbine engine, comprising:

[0008] Engine core;

[0009] an inner shroud radially spaced from and circumscribing the engine core;

[0010] an outer shroud radially spaced from the inner shroud and circumscribing at least a portion of the inner shroud; and

[0011] An accessory gearbox includes a first portion located within the inner shroud and across the engine core and a second portion located between the inner shroud and the outer shroud.

[0012] Technical Solution 2. The turbine engine according to Technical Solution 1, wherein the accessory gearbox defines an accessory gearbox axis parallel to the turbine engine rotation axis.

[0013] Technical Solution 3. A turbine engine according to Technical Solution 2, wherein the second portion of the accessory gearbox is perpendicular to the accessory gearbox axis.

[0014] Technical Solution 4. A turbine engine according to Technical Solution 2, wherein the accessory gearbox comprises a first set of interfaces defined by a first plane, a second set of interfaces defined by a second plane, and a third set of interfaces defined by a third plane.

[0015] Technical Solution 5. A turbine engine according to Technical Solution 4, wherein the first portion of the accessory gearbox comprises a V-shaped cross-section.

[0016] Technical Solution 6. A turbine engine according to Technical Solution 5, wherein the V-shaped cross section defines a first surface perpendicular to the first plane and a second surface perpendicular to the second plane.

[0017] Technical Solution 7. A turbine engine according to any one of Technical Solutions 1 to 6, wherein the first portion of the accessory gearbox comprises a C-shaped or arc-shaped cross-section.

[0018] Technical Solution 8. A turbine engine according to Technical Solution 7, wherein the arcuate cross-section defines a first end point and a second end point, and the second portion of the accessory gearbox is unequally spaced between the first end point and the second end point.

[0019] Technical Solution 9. The turbine engine according to any one of Technical Solutions 1 to 6, wherein at least a portion of the second portion of the accessory gearbox extends through the inner surface of the outer cover.

[0020] Technical Solution 10. The turbine engine according to any one of Technical Solutions 1 to 6, further comprising a strut extending radially from the inner shroud and operably coupling the inner shroud and the outer shroud.

[0021] Technical Solution 11. A turbine engine according to Technical Solution 10, wherein at least a portion of the second portion of the accessory gearbox is located in the strut.

[0022] Technical Solution 12. A turbine engine according to any one of Technical Solutions 1 to 6, wherein the engine core comprises at least one compressor section, a combustion section and a turbine section arranged in an axial flow.

[0023] Technical Solution 13. A turbine engine comprising:

[0024] a fan assembly defining an inlet;

[0025] Engine core;

[0026] an inner shroud radially spaced from the engine core and having an inner face circumscribing at least a portion of the engine core;

[0027] an outer shroud radially spaced from the inner shroud and circumscribing at least a portion of the inner shroud;

[0028] a bifurcated airflow path including a first portion extending from the inlet through the engine core and a second portion extending from the inlet through a secondary airflow path defined between the inner cowl and the outer cowl; and

[0029] An accessory gearbox has a first portion located within the inner shroud and a second portion located in the secondary airflow path.

[0030] Technical Solution 14. The turbine engine according to Technical Solution 13 further includes a strut extending radially through the secondary airflow path and connecting the inner cover and the outer cover, wherein the second portion of the accessory gear box is located in the strut.

[0031] Technical Solution 15. A turbine engine according to Technical Solution 13, wherein the accessory gearbox defines an accessory gearbox axis parallel to the turbine engine rotation axis.

[0032] Technical Solution 16. A turbine engine according to Technical Solution 15, wherein the accessory gearbox comprises a first set of interfaces defined by a first plane, a second set of interfaces defined by a second plane, and a third set of interfaces defined by a third plane.

[0033] Technical Solution 17. A turbine engine according to Technical Solution 15, wherein the second portion of the accessory gearbox is perpendicular to the accessory gearbox axis.

[0034] Technical Solution 18. A turbine engine according to Technical Solution 15, wherein the first portion of the accessory gearbox comprises a C-shaped or arc-shaped cross-section.

[0035] Technical Solution 19. A turbine engine according to Technical Solution 18, wherein the arcuate cross-section defines a first end point and a second end point, and the second portion of the accessory gearbox is unequally spaced between the first end point and the second end point.

[0036] Technical Solution 20. A turbine engine according to any one of Technical Solutions 13 to 19, wherein at least a portion of the second portion of the accessory gearbox extends through an inner surface of the outer cover. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] A complete and enabling disclosure, including the best mode thereof, to one of ordinary skill in the art is set forth in the specification with reference to the accompanying drawings, in which:

[0038] In the attached picture:

[0039] Figure 1 is a schematic diagram of a turbine engine according to aspects of the present disclosure, wherein a partial cutaway view along the turbine engine rotation axis shows the engine static structure and the accessory gearbox in the lower half.

[0040] Figure 2 According to aspects of the present disclosure Figure 1 Rear perspective view of selected components of a turbine engine.

[0041] Figure 3 yes Figure 1 A side perspective view of selected components of a turbine engine further illustrating an accessory gearbox according to aspects of the present disclosure.

[0042] Figure 4 FIG. 1 shows an exemplary embodiment of an ... Figure 2 Schematic cross section of an accessory gearbox.

[0043] Figure 5 Shows the available Figure 1 Schematic cross section of an alternative accessory gearbox in a turbine engine.

[0044] Figure 6 Shows the available Figure 1 Schematic cross section of an alternative accessory gearbox in a turbine engine. DETAILED DESCRIPTION

[0045] One or more aspects described herein provide an accessory gearbox (AGB) equipped with an engine core of a turbine engine. The accessory gearbox includes a first portion and a second portion. The first portion of the AGB is located within an inner cowl and spans the engine core. A second portion formed with or operably connected to the first portion extends at least partially between the inner cowl and the outer cowl. In this way, the core-mounted accessory gearbox includes a component that extends outside the inner cowl into the diverging airflow between the inner cowl and the outer cowl, which allows for a more aerodynamic fairing.

[0046] Additionally, the first and second portions of the AGB may provide power to interfaces defined by at least three different planes.The location of the core mounted AGB allows for easier access to the AGB and other components or systems within the turbine engine, such as but not limited to fuel lines.

[0047] For purposes of illustration, the present disclosure will be described with respect to a turbine engine for an aircraft. The present disclosure may be applicable to a variety of vehicles or engines and may be used to provide benefits in industrial, commercial, and residential applications. Other non-limiting examples of other vehicles or engines to which the present disclosure may relate may include boats, helicopters, automobiles, or other water, air, space, or land vehicles. Industrial, commercial, or residential applications of the present disclosure may include, but are not limited to, marine power plants, wind turbines, or small power plants.

[0048] As used herein, the term "upstream" refers to the direction opposite to the direction of fluid flow, while the term "downstream" refers to the direction in the same direction as the direction of fluid flow. The terms "front" or "forward" refer to in front of something, and "rear" or "rearward" refer to behind something. For example, when used in relation to fluid flow, front / forward may refer to upstream, while rear / rearward may refer to downstream.

[0049] Furthermore, as used herein, the terms "radial" or "radially" refer to directions away from a common center. For example, in the overall context of a turbine engine, radial refers to directions along a ray extending between a central longitudinal axis of the engine and an outer engine circumference. Furthermore, as used herein, the terms "group" or a "group" of elements may be any number of elements, including only one.

[0050] Furthermore, as used herein, an element that is "electrically connected," "electrically coupled," or "in signal communication" may include electrical transmissions or signals sent, received, or communicated to or from such connected or coupled elements. Furthermore, such electrical connections or couplings may include wired or wireless connections, or a combination thereof.

[0051] Likewise, as used herein, although a sensor may be described as "sensing" or "measuring" a corresponding value, sensing or measuring may include determining a value indicative of or associated with the corresponding value, rather than directly sensing or measuring the value itself. The sensed or measured value may be further provided to an additional component. For example, the value may be provided to a controller module or processor as defined above, and the controller module or processor may perform processing on the value to determine a representative value or an electrical characteristic representing the value.

[0052] All directional references (e.g., radial, axial, proximal, distal, up, down, upward, downward, left, right, lateral, front, back, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, upstream, downstream, forward, backward, etc.) are used only for identification purposes to help the reader understand the present disclosure and should not be interpreted as limitations on the examples, especially with respect to the position, direction or use of the disclosed aspects described herein. Unless otherwise stated, connection references (e.g., attachment, connection, connection and engagement) should be interpreted broadly and may include intermediate members between sets of elements and relative movement between elements. Therefore, connection references do not necessarily infer that two elements are directly connected and have a fixed relationship to each other. The exemplary drawings are for illustrative purposes only, and the sizes, positions, orders and relative sizes reflected in the attached drawings may vary.

[0053] Figure 1 is a schematic partial cross-sectional view of a turbine engine 10 for an aircraft, wherein Figure 1 The upper part of shows a cross section of the turbine engine 10 and the lower part shows a schematic diagram of the static support structure and the accessory gearbox.

[0054] Turbine engine 10 has a centerline or turbine engine rotational axis 12 extending forward 14 to aft 16. Turbine engine 10 includes, in downstream series flow relationship, a fan section 18 including a fan assembly 20, a compressor section 22 including a boost or low pressure (LP) compressor 24 and a high pressure (HP) compressor 26, a combustion section 28 including a combustor 30, a turbine section 32 including an HP turbine 34 and an LP turbine 36, and an exhaust section 38.

[0055] The fan section 18 includes a fan case 40 surrounding the fan assembly 20. The fan assembly 20 includes a plurality of fan blades 42 radially arranged around the turbine engine rotation axis 12. The HP compressor 26, the combustor 30, and the HP turbine 34 form an engine core 44 that produces combustion gases. The engine core 44 is surrounded by a core case 46 that can be connected to the fan case 40.

[0056] An HP shaft or HP spool 48 disposed coaxially about the turbine engine rotation axis 12 of the turbine engine 10 drivingly connects the HP turbine 34 to the HP compressor 26. An LP shaft or LP spool 50 disposed coaxially about the turbine engine rotation axis 12 of the turbine engine 10 within the larger diameter annular HP spool 48 drivingly connects the LP turbine 36 to the LP compressor 24 and the fan assembly 20. The HP spool 48 and the LP spool 50 are rotatable about the engine centerline and are coupled to a plurality of rotatable elements that may collectively define an inner rotor / stator. Although illustrated as a rotor, it is contemplated that the inner rotor / stator may be a stator.

[0057] The LP compressor 24 and the HP compressor 26 each include a plurality of compressor stages 52, 54 in which a set of compressor blades 56, 58 rotate relative to a corresponding set of static compressor vanes 60, 62, which may also be referred to as nozzles, to compress or pressurize a fluid flow through the stage. In a single compressor stage 52, 54, the plurality of compressor blades 56, 58 may be arranged in a ring and may extend radially outward relative to the turbine engine rotation axis 12, from a blade platform to a blade tip, with the corresponding static compressor vanes 60, 62 located upstream of and adjacent to the rotating compressor blades 56, 58. Note that Figure 1 The number of blades, guide vanes, and compressor stages shown in are selected for illustration purposes only, and other numbers are possible.

[0058] Compressor blades 56, 58 for a compressor stage may be mounted to a disk 61 mounted to a respective one of the HP spool 48 and the LP spool 50, with each stage having its own disk 61. Guide vanes 60, 62 for a compressor stage may be mounted to the core shell 46 in a circumferential arrangement.

[0059] The HP turbine 34 and the LP turbine 36 each include a plurality of turbine stages 64, 66 in which a set of turbine blades 68, 70 rotate relative to a corresponding set of static turbine vanes 72, 74, which may also be referred to as nozzles, to extract energy from a fluid flow passing through the stage. In a single turbine stage 64, 66, the plurality of turbine blades 68, 70 may be arranged in a ring and may extend radially outward relative to the turbine engine rotation axis 12, from a blade platform to a blade tip, while the corresponding static turbine vanes 72, 74 are located upstream of and adjacent to the rotating blades 68, 70. Note that Figure 1 The number of blades, guide vanes, and turbine stages shown in FIG. 5 are selected for illustration purposes only, and other numbers are possible.

[0060] The blades 68, 70 for the turbine stage may be mounted to a disk 71 mounted to a respective one of the HP spool 48 and the LP spool 50, with each stage having a dedicated disk 71. The guide vanes 72, 74 for the compressor stage may be mounted to the core shell 46 in a circumferential arrangement.

[0061] Complementary to the rotor portion, the stationary portion of the turbine engine 10, such as the static guide vanes 60, 62, 72, 74 between the compressor section 22 and the turbine section 32, are also referred to individually or collectively as outer rotor / stators. As shown, the outer rotor / stator may refer to a combination of non-rotating elements throughout the turbine engine 10. Alternatively, the outer rotor / stator that restricts at least a portion of the inner rotor / stator may be designed to rotate. The inner or outer rotor / stator may include at least one component, which may be a shroud, a guide vane, a nozzle, a nozzle body, a combustor, a pylon, or a blade, as a non-limiting example, wherein at least one component is a plurality of circumferentially arranged component segments having facing circumferential end pairs.

[0062] The inner shroud 76 is radially spaced from the engine core 44 and may circumscribe at least a portion of the engine core 44. The inner shroud 76 may include an outer face 78 and an inner face 80, wherein the inner face 80 of the inner shroud 76 may face the engine core 44 or the core shell 46.

[0063] Nacelle or outer shroud 82 is radially spaced from inner shroud 76 and may circumscribe at least a portion of inner shroud 76. Outer shroud 82 has a radially outer surface 84 and a radially inner surface 86, wherein radially inner surface 86 faces outer face 78 of inner shroud 76. Outer shroud 82 may support or define fan case 40.

[0064] An accessory gearbox (AGB) 90 may be provided with the engine core 44 or core housing 46 and at least partially confined within the inner cover 76. It is contemplated that the AGB 90 is mounted or operably coupled to the engine core 44 with a hinged mount. That is, when one or more buckles or fasteners are removed, the AGB 90 may swing away from at least a portion of the engine core 44 or core housing 46, with the remainder of the AGB 90 remaining operably coupled to the engine core 44 or core housing 46. The AGB 90 is operably coupled to the engine core 44 or core housing 46 in a position and orientation to provide easy access to the AGB 90 and other components, such as, but not limited to, fuel lines, cables, electrical connectors, fuel lines, sight glasses, and fuel filler ports.

[0065] An accessory gearbox axis 92 may be defined by the AGB 90. In the illustrated example, when the AGB 90 is fully installed and in use within a turbine engine, the accessory gearbox axis 92 is parallel to the turbine engine rotation axis 1210. However, it is contemplated that the accessory gearbox axis 92 and the turbine engine rotation axis 12 may be at any suitable angle and need not be parallel.

[0066] The AGB 90 includes a first portion 94 and a second portion 96. The first portion 94 is located within the inner cover 76. That is, the first portion 94 is located between the inner surface 80 of the inner cover 76 and the engine core 44 or the core shell 46. The first portion 94 of the AGB 90 may span the engine core 44 or the core shell 46.

[0067] The second portion 96 of the AGB 90 is located between the inner shroud 76 and the outer shroud 82. That is, the second portion 96 of the AGB 90 is located between the radially inner surface 86 of the outer shroud 82 and the outer face 78 of the inner shroud 76. However, it is contemplated that a portion of the second portion 96 of the AGB 90 may extend beyond the radially inner surface 86 of the outer shroud 82. That is, the second portion 96 of the AGB 90 may be operably coupled to one or more components located in the outer shroud 82.

[0068] At least one strut 98 may extend radially from the inner shroud 76 to the outer shroud 82. The strut 98 may operably couple the inner shroud 76 and the outer shroud 82. It is contemplated that at least a portion of the second portion 96 of the AGB 90 is located within the strut 98.

[0069] The second portion 96 of the AGB 90 is shown as being perpendicular to the accessory gearbox axis 92. However, this need not be the case, and it is further contemplated that the second portion 96 and the accessory gearbox axis 92 may be at any relative angle.

[0070] In operation, airflow passes through the fan portion 18 to an inlet 108 defined by the fan assembly 20. Airflow exiting the fan portion 18 through the inlet 108 enters a bifurcated airflow path. The bifurcated airflow path includes a first portion or first airflow 100 through the engine core 44 and a second portion 96 or second airflow 102 through a secondary airflow path 104. Thus, the inlet 108 may be fluidly coupled to the engine core 44 and the secondary airflow path 104.

[0071] The first airflow 100 is directed into the LP compressor 24, which then supplies the pressurized airflow 100 to the HP compressor 26, which further pressurizes the air. The pressurized airflow 100 from the HP compressor 26 is mixed with fuel and ignited in the combustor 30, thereby producing combustion gases. The HP turbine 34 extracts some work from these gases, which drives the HP compressor 26. The combustion gases are exhausted into the LP turbine 36, which extracts additional work to drive the LP compressor 24, and the exhaust gases are ultimately exhausted from the turbine engine 10 via the exhaust section 38. The drive of the LP turbine 36 drives the LP spool 50 to rotate the fan assembly 20 and the LP compressor 24.

[0072] A portion of the pressurized gas stream 100 may be extracted from the compressor section 22 as bleed air 106. The bleed air 106 may be extracted from the pressurized gas stream 100 and provided to engine components requiring cooling. The temperature of the pressurized gas stream 100 entering the combustor 30 is significantly increased. Therefore, the cooling provided by the bleed air 106 is necessary for operating such engine components in an elevated temperature environment.

[0073] The second airflow 102 travels through a secondary airflow path 104 defined by the inner shroud 76 and the outer shroud 82. That is, the outer face 78 of the inner shroud 76 and the radial inner surface 86 of the outer shroud 82 may define the secondary airflow path 104.

[0074] The second airflow 102 bypasses the LP compressor 24 and the engine core 44 and exits the turbine engine 10. The secondary airflow path 104 may include a fixed guide vane row, and more specifically, an exit guide vane assembly 110 that includes a plurality of airfoil guide vanes 112. More specifically, a circumferential row of radially extending airfoil guide vanes 112 is utilized adjacent the fan section 18 to exert some directional control of the second airflow 102.

[0075] Some of the air supplied by the fan assembly 20 may bypass the engine core 44 and be used to cool portions of the turbine engine 10, particularly the hot portion, and / or to cool or power other aspects of the aircraft. In the context of a turbine engine, the hot portion of the engine is typically downstream of the combustor 30, particularly the turbine section 32, with the HP turbine 34 being the hottest portion as it is located directly downstream of the combustion section 28. Other sources of cooling fluid may be, but are not limited to, fluid exhausted from the LP compressor 24 or the HP compressor 26.

[0076] Figure 2 The static support structure of the turbine engine 10 and the position of the second portion 96 of the AGB 90 relative thereto are further shown. Figure 2 Only the outer shroud 82, the inner shroud 76, the core shell 46, the support struts including the struts 98, and the second portion 96 of the AGB 90 are included. The struts 98 extending through the secondary airflow path 104 include a first wall 120 and a second wall 122 spaced apart from the first wall 120, although any number of walls are contemplated. Although shown as open, it is contemplated that the first wall 120 and the second wall 122 may be coupled or otherwise connected behind the second portion 96 of the AGB 90. It is also contemplated that the first wall 120 and the second wall 122 may be joined at a point forward of the second portion 96 of the AGB 90. It will be appreciated that the struts 98 may form an aerodynamic housing for at least a portion of the second portion 96.

[0077] The upper strut 124 is shown as having a single wall. However, it is contemplated that the upper strut 124 may be reconfigured to accommodate or partially surround the second portion 96 of the AGB 90. It will be appreciated that the second portion 96 of the AGB 90 may be located in any portion of the secondary airflow path 104. This is but is not limited to being within a strut located anywhere around the turbine engine 10. The second portion 96 may extend from the inner shroud 76 to any suitable radial position, including into the outer shroud 82 or radially outward from the secondary airflow path 104.

[0078] Figure 3 Further shown is the AGB 90 with the engine core 44. For clarity, the outer shroud 82, the inner shroud 76, and the interior portion of the engine core 44 are not shown. A set of forks, illustrated as a first fork 121 and a second fork 123, may be included in the AGB 90. As used herein, the term "fork" is a Y-shaped object having a post or base from which two arms branch off in different directions.

[0079] In the illustrated example, the first fork 121 includes a first base portion 125 defined by a portion of the second portion 96 of the AGB 90. A first arm 130 and a second arm 132 extend from the first base portion 125. The first arm 130 and the second arm 132 are a portion of the first portion 94 of the AGB 90 that can span the engine core 44 or the core shell 46. That is, as the base portion 125 extends, bifurcates, splits, branches, or otherwise couples to the first arm 130 and the second arm 132, wherein the first arm 130 and the second arm 132 form a V-shape, a U-shape, etc., so as to support, span, or otherwise partially constrain the engine core 44 or the core shell 46.

[0080] Similarly, the second fork 123 may be defined by a second base portion 127 that forks, splits, or otherwise couples to a first arm 128 and a second arm (not shown as it wraps behind the core shell 46) that spans the engine core 44 or the core shell 46. It is contemplated that any number of one or more forks may be included in the AGB 90.

[0081] The first tine 121 and the second tine 123 are shown as being spaced apart along the accessory gearbox axis 92. The first tine 121 and the second tine 123 may be coupled by one or more of a drive shaft, a gearbox, a hydraulic drive, etc. The drive shaft or hydraulic drive may include one or more housings 126 located between the first tine 121 and the second tine 123. It is contemplated that only a single tine may be included, or additional parts, housings, drive shafts, etc. may be included to increase the number of interfaces or tine members.

[0082] AGB 90 may be coupled to any number of interfaces, shown by way of non-limiting example as interfaces 131a, 131b, 131c. Further, it is contemplated that AGB 90 may be coupled to any number of components or systems, shown by way of non-limiting example as systems 133a, 133b, 133c. Systems powered by AGB 90 may be located axially or radially spaced relative to AGB 90. For example, systems or interfaces may include, but are not limited to, any one or more of an output shaft, a fuel pump, a gearbox, a lubrication pump, an air compressor, a scavenge pump, a generator, a fuel control, a fuel pump, a permanent magnet alternator, a lubrication pump, or a hydraulic pump.

[0083] Figure 4 FIG. 1 further illustrates a cross section of the AGB 90, which is generally Figure 2 90 is a schematic cross section taken at the axial position of the first fork 121 further shown as a cross-section line. The engine core 44 and the core shell 46 are schematically shown together with the turbine engine rotation axis 12. The C-shaped or arcuate cross section can be defined by a first arm 130 and a second arm 132 and span the engine core 44. Although no spacing or connecting components are shown between the core shell 46 and the AGB 90, it will be understood that any suitable spacing and components may be included. The first arm 130 extends from the accessory gearbox axis 92 to a first termination point or first distal surface 134. The first distal surface 134 may have a first endpoint 136, which is defined as a point on the first distal surface 134 that is radially farthest from the turbine engine rotation axis 12. The first distance 140 can be measured radially from the accessory gearbox axis 92 to the first endpoint 136.

[0084] The first arm 130 may include a first plane 144. The two dimensions defining the first plane 144 are illustrated by way of example as a first dimension that is substantially perpendicular to the first distal surface 134, and a second dimension that is in / out of the page. As used herein, the term "substantially perpendicular" defines an angle between two objects that is between 80 degrees and 100 degrees. Additionally or alternatively, the plane 144 may be defined by at least an obtuse angle extending from the yaw axis or the pitch axis (i.e., from inside / out of the page, or Figure 1 In the plane defined from top to bottom respectively. Figure 4 In the example, the obtuse angle is formed with the yaw-roll plane. In other examples, the plane 144 can be defined by rotation around one or more of these three mutually orthogonal axes. It is also contemplated that the first plane 144 can form any angle with the first distal surface 134 in any dimension.

[0085] The first set of interfaces 142a, 142b can be operably coupled to or defined by a portion of the first arm 130. The first set of interfaces 142a, 142b can extend along or be defined by a first plane 144. Although illustrated as two interfaces 142a, 142b located on the plane 144, any number of interfaces in the first plane 144 is contemplated, including one.

[0086] The first arm 130 may define a first arm rotation axis 146. It is contemplated that rotation of an output shaft or other portion of the first arm 130 about the first arm rotation axis 146 may be considered an interface to the AGB 90. An interface as defined herein may be an input to the AGB 90 or an output from the AGB 90. It is also contemplated that the first arm 130 may define any number of rotation axes.

[0087] The first arm 130 may sweep a first arc length 150 from the accessory gearbox axis 92 to the first distal surface 134. The first arm 130 may cover, span, or otherwise surround between 5% and 50% of the engine core 44 or core shell 46. It is contemplated that the length of the first arc length 150 is between 1% and 60% of the circumference of the engine core 44 or core shell 46.

[0088] The second arm 132 extends from the plane of the accessory gearbox axis 92 to a second termination point or second distal surface 154. The second distal surface 154 may have a second endpoint 156 defined as a point on the second distal surface 154 that is radially farthest from the turbine engine rotation axis 12. A second distance 160 may be measured radially from the accessory gearbox axis 92 to the second endpoint 156. Although illustrated as being equal, the first distance 140 may be greater than or less than the second distance 160. That is, the second portion 96 of the AGB 90 is not equally spaced between the first endpoint 136 and the second endpoint 156, wherein the first endpoint 136 and the second endpoint 156 are defined by an arcuate cross-section.

[0089] The second arm 132 may include a second plane 164. The two dimensions defining the second plane 164 are illustrated by way of example as a first dimension that is generally perpendicular to the second distal surface 154 and a second dimension that is in / out of the page. Similar to the first plane 144, the second plane 164 may be defined by at least an obtuse angle extending from the yaw axis or the pitch axis (i.e., from the inside / out of the page, or Figure 1 It is further contemplated that the second plane 164 may form any angle with the second distal surface 154 in any dimension.

[0090] The second set of interfaces 162a, 162b can be operably coupled to or defined by a portion of the first arm 132. The second set of interfaces 162a, 162b can be defined by a second plane 164. Although illustrated as two interfaces 162a, 162b located on or extending along the plane 164, any number of interfaces in the second plane 164 is contemplated, including one.

[0091] The second arm 132 may define a second arm rotation axis 166. It is contemplated that rotation of the output shaft or other portion of the second arm 132 about the second arm rotation axis 166 may be considered an interface to the AGB 90. It is further contemplated that the second arm 132 may define any number of rotation axes.

[0092] The second arm 132 may sweep a second arc length 170 from the accessory gearbox axis 92 to the second distal surface 154. The second arm 132 may cover or otherwise surround between 5% and 50% of the engine core 44 or core shell 46. It is contemplated that the length of the second arc length 170 is between 1% and 60% of the circumference of the engine core 44 or core shell 46. Although illustrated as being equal, the second arc length 170 may be less than or greater than the first arc length 150.

[0093] The third plane 174 may define a third set of interfaces 172a, 172b included in the second portion 96 of the AGB 90. As shown, by way of non-limiting example, the second portion 96 of the AGB 90 may be generally perpendicular to the accessory gearbox axis 92. The third set of interfaces 172a, 172b may extend along the third plane 174. It is contemplated that one or more of the third set of interfaces 172a, 172b may extend beyond the radially inner surface 86 of the outer cover 82. That is, the AGB 90 may include a first set of interfaces 142a, 142b defined by the first plane 144, a second set of interfaces 162a, 162b defined by the second plane 164, and a third set of interfaces 172a, 172b defined by the third plane 174. The interfaces may include, but are not limited to, systems, components, or other engine elements that receive energy from the rotation of the AGB 90 about the accessory gearbox axis 92. It is contemplated that interfaces 172a, 172b, 142a, 142b, 162a and 162b may correspond to interfaces for servicing one or more or any of a service output shaft, a fuel pump, a gearbox, a lubrication pump, an air compressor, a scavenge air pump, a generator, a fuel control, a fuel pump, a permanent magnet alternator, a lubrication pump or a hydraulic pump. It is further contemplated that second portion 96 of AGB 90 may define any number of axes of rotation.

[0094] Similar to the first plane 144 and the second plane 164, the third plane 174 includes two dimensions, shown by way of example as a first dimension that is generally perpendicular to the accessory gearbox axis 92, extending radially outward from the longitudinal axis 12, and a second dimension that is in / out of the page. Similar to the first plane 144 and the second plane 164, the third plane 174 can be formed by extending from the yaw axis or the pitch axis (i.e., from the inside / out of the page, or respectively in Figure 1 It is further contemplated that the second plane 174 may form any angle with the accessory gearbox axis 92 in any dimension.

[0095] As shown, by way of example, each of the corresponding pair of interfaces 142a, 142b, 162a and 162b, 172a, 172b or the rotational axes 146, 166 associated with the corresponding planes 144, 164, 174 are generally perpendicular to each other. However, it is contemplated that the angle between the interfaces 142a, 142b, 162a and 162b, 172a, 172b or the rotational axes 146, 166 associated with the corresponding planes 144, 164, 174 can be any angle, including between 50 degrees and 100 degrees.

[0096] A first angle 176 can be defined by rotating clockwise from the third plane 174 to the first plane 144. As shown, the first angle 176 can be an acute angle, however, any angle between but not including zero and 180 degrees is contemplated. A second angle 178 can be defined by rotating counterclockwise from the third plane 174 to the second plane 164. As shown, the first angle 178 can be an acute angle, however, any angle between but not including zero and 180 degrees is contemplated. Although shown as being equal, it is contemplated that the first angle 176 can be greater than or less than the second angle 178.

[0097] It is contemplated that any number of additional planes defining an interface or rotational axis may extend from or be defined by the first portion 94 or the second portion 96. It is also contemplated that additional planes of interface or rotational axis may extend from or be defined by one or more portions of the first plane 144, the second plane 164, the third plane 174, the first arm rotational axis 146, the second arm rotational axis 166, the accessory gearbox axis 92, the first arc length 150, or the second arc length 170.

[0098] In operation, the AGB 90 may be operably coupled to one or more components of the engine core 44. That is, one or more components of the engine core 44 provide or otherwise communicate energy to the AGB 90. By way of non-limiting example, the AGB 90 may be powered by energy provided by a drive shaft located in the engine core 44 along the turbine engine rotation axis 12 or the LP spool 50. Additionally or alternatively, the AGB 90 may be electrically driven using electrical energy generated by the rotation of the engine core 44 or an electrical energy storage device.

[0099] The AGB 90, when powered, causes one or more components to rotate about the accessory gearbox axis 92. The rotation about the accessory gearbox axis 92 can then provide energy in the form of rotational energy or electromagnetic energy to at least one of the interfaces from the first group of interfaces 142a, 142b, the second group of interfaces 162a, 162b, or the third group of interfaces 172a, 172b. The first group of interfaces 142a, 142b, the second group of interfaces 162a, 162b, and the third group of interfaces 172a, 172b are located in the first plane 144, the second plane 164, and the third plane 174, respectively. The first plane 144, the second plane 164, and the third plane 174 are three different planes that may be parallel or intersecting.

[0100] Energy transfer from the AGB 90 to the first set of interfaces 142a, 142b, the second set of interfaces 162a, 162b, and the third set of interfaces 172a, 172b can come from the rotation of the bevel gear arrangement. That is, one or more of the first set of interfaces 142a, 142b, the second set of interfaces 162a, 162b, or the third set of interfaces 172a, 172b can be driven using a bevel gear system with a shared drive shaft. It is further contemplated that the AGB 90 may include multiple motors to provide power to the hydraulic or electric drive interfaces.

[0101] The third set of interfaces 172a, 172b coupled to or defined by the second portion 96 of the AGB 90 allows the first portion 94 of the AGB 90 to be smaller. That is, having the second portion 96 of the AGB 90 allows the distance between the inner cowl 76 and the engine core 44 or the core shell 46 to be reduced. The smaller distance between the inner cowl 76 and the engine core 44 or the core shell 46 can increase the aerodynamics of the secondary airflow path 104 by reducing resistance to the second airflow 102. Additionally or alternatively, the smaller first portion 94 of the AGB 90 can provide space for additional components, such as, but not limited to, reverse thruster components.

[0102] The AGB 90 as disclosed may be used in smaller applications such as, but not limited to, regional aircraft. The AGB 90 having a first portion 94 between the core shell 46 and the inner cowl 76 and a second portion 96 between the inner cowl 76 and the outer cowl 82 allows the engine 10 to include, for example, a slimline nacelle fan cowl and / or an advanced thrust reverser.

[0103] Figure 5 An AGB 290 is illustrated which is similar to the previously described AGB 90. Accordingly, like parts will be identified with like numerals increased by 200, and it will be understood that the description of like parts of AGB 90 applies to AGB 290 unless otherwise noted. Figure 4 Likewise, will understand Figure 5 The engine core 44 and core shell 46 are schematically illustrated along with the turbine engine rotation axis 12 , and while spacing or coupling components between the core shell 46 and the AGB 290 are not illustrated, it will be appreciated that any suitable spacing and components may be included.

[0104] The C-shaped or arcuate cross-section may be defined by a first arm 330 and a second arm 332. However, unlike the previously described AGB 90, the first arm 330 and the second arm 332 of the AGB 290 are not equidistant in length. The first arm 330 extends from the accessory gearbox axis 292 to a first termination point or first distal surface 334. The first distal surface 334 may have a first endpoint 336, which is defined as the point on the first distal surface 334 that is radially farthest from the turbine engine rotation axis 12. A first distance 340 may be measured radially from the accessory gearbox axis 292 to the first endpoint 336.

[0105] The first arm 330 may include a first plane 344. The two dimensions defining the first plane 344 are illustrated by way of example as a first dimension that is generally perpendicular to the first distal surface 334 and a second dimension that is in / out of the page. Additionally or alternatively, the plane 344 may be defined by at least one of the yaw axis and the pitch axis (i.e., from inside / out of the page, or Figure 1 The plane defined by the obtuse angle extending from the top to the bottom of each of the two axes. Figure 5 In the example, the obtuse angle forms a yaw-roll plane. In other examples, the plane 344 can be defined by a rotation around one or more of the three mutually orthogonal axes. It is further contemplated that the first plane 344 can form any angle with the first distal surface 334 in any dimension.

[0106] The first set of interfaces 342a, 342b can be operably coupled to or defined by a portion of the first arm 330. The first set of interfaces 342a, 342b can extend along or be defined by a first plane 344. Although illustrated as two interfaces 342a, 342b located on the plane 344, any number of interfaces in the first plane 344 is contemplated, including one.

[0107] The first arm 330 can define a first arm rotation axis 346. It is contemplated that rotation of the output shaft or other portion of the first arm 330 about the first arm rotation axis 346 can be considered an interface. It is further contemplated that the first arm 330 can define any number of rotation axes.

[0108] The first arm 330 may sweep a first arc length 350 from the accessory gearbox axis 292 to the first distal surface 334. The first arm 330 may cover or otherwise surround between 5% and 50% of the engine core 44 or core shell 46. It is contemplated that the length of the first arc length 350 is between 1% and 60% of the circumference of the engine core 44 or core shell 46.

[0109] The second arm 332 extends from the plane of the accessory gearbox axis 292 to a second termination point or second distal surface 354. The second distal surface 354 may have a second endpoint 356 defined as a point on the second distal surface 354 that is radially farthest from the turbine engine rotation axis 12. A second distance 360 ​​may be measured radially from the accessory gearbox axis 292 to the second endpoint 356. Although shown as being greater than the first distance 340, the second distance 360 ​​may be less than or equal to the first distance 340. That is, the second portion 96 of the AGB 290 is not equally spaced between the first endpoint 336 and the second endpoint 356, wherein the first endpoint 336 and the second endpoint 356 are defined by an arcuate cross-section.

[0110] The second arm 332 may include a second plane 364. The two dimensions defining the second plane 364 are illustrated by way of example as a first dimension that is generally perpendicular to the second distal surface 354 and a second dimension that is in / out of the page. Similar to the first plane 344, the second plane 364 may be defined by at least one of the yaw axis and the pitch axis (i.e., from inside / out of the page, or Figure 1 The second plane 364 is defined by a plane defined by an obtuse angle extending from top to bottom, respectively. It is further contemplated that the second plane 364 may form any angle with the second distal surface 354 in any dimension.

[0111] The second set of interfaces 362a, 362b can be operably coupled to or defined by a portion of the first arm 332. The second set of interfaces 362a, 362b can be defined by the second plane 164. Although illustrated as two interfaces 162a, 162b located on the plane 164, any number of interfaces in the second plane 164 is contemplated, including one.

[0112] The second arm 332 can define a second arm rotation axis 366. It is contemplated that rotation of the output shaft or other portion of the second arm 332 about the second arm rotation axis 366 can be considered an interface. It is further contemplated that the second arm 332 can define any number of rotation axes.

[0113] The second arm 332 may sweep a second arc length 370 from the accessory gearbox axis 292 to the second distal surface 354. The second arm 332 may cover or otherwise surround between 5% and 50% of the engine core 44 or core shell 46. It is contemplated that the length of the second arc length 370 is between 1% and 60% of the circumference of the engine core 44 or core shell 46. Although shown as being larger, the second arc length 370 may be less than or equal to the first arc length 350.

[0114] The third plane 174 may define a third set of interfaces 372a, 372b that may be included in the second portion 296 of the AGB 290. As shown, by way of non-limiting example, the second portion 296 of the AGB 290 may be generally perpendicular to the accessory gearbox axis 292. The third set of interfaces 372a, 372b may extend along the third plane 374. It is contemplated that one or more of the third set of interfaces 372a, 372b may extend beyond the radial inner surface 86 of the outer cover 82. That is, the AGB 90 may include a first set of interfaces 342a, 342b defined by the first plane 344, a second set of interfaces 362a, 362b defined by the second plane 364, and a third set of interfaces 372a, 372b defined by the third plane 374. The interfaces may include, but are not limited to, systems, components, or other engine elements that receive energy from the rotation of the AGB 290 about the accessory gearbox axis 292. It is contemplated that the interface may include, but is not limited to, any one or more of an output shaft, a fuel pump, a gearbox, a lubrication pump, an air compressor, a scavenge pump, a generator, a fuel control, a fuel pump, a permanent magnet alternator, a lubrication pump, or a hydraulic pump. It is further contemplated that the second portion 296 of the AGB 290 may define any number of axes of rotation.

[0115] Similar to the first plane 344 and the second plane 364, the third plane 374 includes two dimensions, shown by way of example as a first dimension that is generally perpendicular to the accessory gearbox axis 292, extending radially outward from the longitudinal axis 12, and a second dimension that is in / out of the page. Similar to the first plane 344 and the second plane 364, the third plane 374 can be formed by extending from the yaw axis or the pitch axis (i.e., from inside / out of the page, or from inside / out of the page). Figure 1 The second plane 374 is defined by at least one obtuse angle extending from top to bottom in the embodiment of the present invention. It is further contemplated that the second plane 374 may form any angle with the accessory gearbox axis 292 in any dimension.

[0116] As shown, by way of example, each of the corresponding pair of interfaces 342a, 342b, 362a and 362b, 372a, 372b or the rotational axes 346, 366 associated with the corresponding planes 344, 364, 374 are substantially perpendicular to each other. However, it is contemplated that the angle between the interfaces 342a, 342b, 362a and 362b, 372a, 372b or the rotational axes 346, 366 associated with the corresponding planes 344, 364, 374 can be any angle, including between 50 degrees and 100 degrees.

[0117] It is contemplated that any number of additional planes defining an interface or rotation axis may extend from or be defined by the first portion 294 or the second portion 296. It is also contemplated that additional planes defining an interface or rotation axis may extend from or be defined by one or more portions of the first plane 344, the second plane 364, the third plane 374, the first arm rotation axis 346, the second arm rotation axis 366, the accessory gearbox axis 292, the first arc length 350, or the second arc length 370.

[0118] Figure 6 An AGB 490 is illustrated which is similar to the previously described AGB 90 and AGB 290. Accordingly, like components will be identified with like numerals further increased by 200, and it will be understood that the description of like components of AGB 90 and AGB 290 applies to AGB 490 unless otherwise noted. Figure 4 Likewise, will understand Figure 6 The engine core 44 and core shell 46 are schematically illustrated along with the turbine engine rotation axis 12 , and while spacing or coupling components between the core shell 46 and the AGB 490 are not illustrated, it will be appreciated that any suitable spacing and components may be included.

[0119] One difference is that AGB 490 includes a V-shaped cross-section defined by a first arm 530 and a second arm 532. First arm 530 extends from accessory gearbox axis 492 to a first termination point or first distal surface 534. First distal surface 534 may have a first endpoint 536 defined as the point on first distal surface 534 that is radially farthest from turbine engine rotation axis 12. A first distance 540 may be measured radially from accessory gearbox axis 492 to first endpoint 536.

[0120] The first arm 530 can include a first plane 544. The two dimensions defining the first plane 544 are illustrated by way of example as a first dimension that is generally perpendicular to the first distal surface 534, while the second dimension is in / out of the page. It is further contemplated that the first plane 544 can form any angle with the first distal surface 534 in either dimension.

[0121] The first set of interfaces 542a, 542b can be operably coupled to or defined by a portion of the first arm 530. The first set of interfaces 542a, 542b can extend along or be defined by a first plane 544. Although illustrated as two interfaces 542a, 542b located on the plane 544, any number of interfaces in the first plane 544 is contemplated, including one.

[0122] The first arm 530 can define a first arm rotation axis 546. It is contemplated that rotation of the output shaft or other portion of the first arm 530 about the first arm rotation axis 546 can be considered an interface. It is further contemplated that the first arm 530 can define any number of rotation axes.

[0123] The first arm 530 may sweep a first arm length 551 from the accessory gearbox axis 492 to the first distal surface 534. The first arm 530 may cover between 5% and 50% of the engine core 44 or core shell 46. It is contemplated that the first arm length 551 is between 1% and 60% of the circumference of the engine core 44 or core shell 46.

[0124] The second arm 532 extends from the plane of the accessory gearbox axis 492 to a second termination point or second distal surface 554. The second distal surface 554 may have a second endpoint 556 defined as a point on the second distal surface 554 that is radially farthest from the turbine engine rotation axis 12. A second distance 560 may be measured radially from the accessory gearbox axis 492 to the second endpoint 556. Although shown as being greater than the first distance 540, the second distance 560 may be less than or equal to the first distance 540. That is, the second portion 496 of the AGB 490 is not equally spaced between the first endpoint 536 and the second endpoint 556, wherein the first endpoint 536 and the second endpoint 556 are defined by an arcuate cross-section.

[0125] The second arm 532 can include a second plane 564. The two dimensions defining the second plane 564 are illustrated by way of example as being generally perpendicular to the first dimension of the second distal surface 554, and the second dimension being in / out of the page. It is further contemplated that the second plane 564 can form any angle with the second distal surface 554 in either dimension.

[0126] The second set of interfaces 562a, 562b can be operably coupled to or defined by a portion of the first arm 532. The second set of interfaces 562a, 562b can be defined by a second plane 564. Although illustrated as two interfaces 562a, 562b located on or extending along the plane 564, any number of interfaces in the second plane 564 is contemplated, including one.

[0127] The second arm 532 can define a second arm rotation axis 566. It is contemplated that rotation of the output shaft or other portion of the second arm 532 about the second arm rotation axis 566 can be considered an interface. It is further contemplated that the second arm 532 can define any number of rotation axes.

[0128] The second arm 532 may have a second arm length 571 from the accessory gearbox axis 492 to the second distal surface 554. The second arm 532 may cover between 5% and 50% of the engine core 44 or core shell 46. It is contemplated that the second arm length 571 is between 1% and 60% of the circumference of the engine core 44 or core shell 46. Although illustrated as being equal, the second arm length 571 may be greater or less than the first arm length 551.

[0129] The third plane 574 may define a third set of interfaces 572a, 572b that may be included in the second portion 496 of the AGB 490. As shown, by way of non-limiting example, the second portion 496 of the AGB 490 may be perpendicular to the accessory gearbox axis 492. The third set of interfaces 572a, 572b may extend along the third plane 574. It is contemplated that one or more of the third set of interfaces 572a, 572b may extend beyond the radial inner surface 86 of the outer cover 82. That is, the AGB 490 may include a first set of interfaces 542a, 542b defined by the first plane 544, a second set of interfaces 562a, 562b defined by the second plane 564, and a third set of interfaces 572a, 572b defined by the third plane 574. The interfaces may include, but are not limited to, systems, components, or other engine elements that receive energy from the rotation of the AGB 490 about the accessory gearbox axis 492. It is contemplated that the interface may include, but is not limited to, any one or more of an output shaft, a fuel pump, a gearbox, a lubrication pump, an air compressor, a scavenge pump, a generator, a fuel control, a fuel pump, a permanent magnet alternator, a lubrication pump, or a hydraulic pump. It is further contemplated that the second portion 496 of the AGB 490 may define any number of axes of rotation.

[0130] Similar to the first plane 544 and the second plane 564, the third plane 574 includes two dimensions, shown by way of example as a first dimension that is generally perpendicular to the accessory gearbox axis 492, extending radially outward from the longitudinal axis 12, and a second dimension that is in / out of the page. Similar to the first plane 544 and the second plane 564, the third plane 574 can be formed by extending from the yaw axis or the pitch axis (i.e., from the inside / out of the page, or from the inside / out of the page) Figure 1 The second plane 574 is defined by at least one obtuse angle extending from top to bottom in the embodiment of the present invention. It is further contemplated that the second plane 574 may form any angle with the accessory gearbox axis 492 in any dimension.

[0131] As shown, as an example, each of the corresponding pair of interfaces 542a, 542b, 562a and 562b, 572a, 572b or the rotation axes 546, 566 associated with the corresponding planes 544, 564, 574 are substantially perpendicular to each other. However, it is contemplated that the angle between the interfaces 542a, 542b, 562a and 562b, 572a, 572b or the rotation axes 546, 566 associated with the corresponding planes 544, 564, 574 can be any angle, including between 50 degrees and 100 degrees.

[0132] It is contemplated that any number of additional planes defining an interface or rotation axis may extend from or be defined by the first portion 494 or the second portion 496. It is also contemplated that additional planes defining an interface or rotation axis may extend from or be defined by one or more portions of the first plane 544, the second plane 564, the third plane 574, the first arm rotation axis 546, the second arm rotation axis 566, the accessory gearbox shaft 492, the first arm length 551, or the second arm length 571.

[0133] Benefits of aspects of the present disclosure include improved fuel efficiency. A core mounted accessory gearbox with components that extend tangentially beyond the inner cowl into the diverging airflow allows for a more aerodynamic cowl. That is, because a portion of the AGB is located between the inner cowl and the outer cowl, the inner cowl or the outer cowl can be smaller and / or more streamlined or aerodynamic. Improved airflow through the cowl can improve fuel efficiency.

[0134] As described herein, the accessory gearbox may include a smaller inner or outer shroud. A smaller inner and / or outer shroud may also provide cost and weight savings.

[0135] As disclosed herein, a core mounted accessory gearbox improves maintainability and accessibility because the accessory gearbox is located near the entry point of the turbine engine.

[0136] As disclosed herein, a core mounted accessory gearbox may be used for smaller applications, such as, but not limited to, regional aircraft. An accessory gearbox having a first portion between the core shell and the inner cowl and a second portion between the inner cowl and the outer cowl allows the accessory gearbox to have a smaller first portion. An accessory gearbox having a smaller first portion allows the turbine engine 10 to have additional components, such as, but not limited to, reverse thruster components and / or a slimline nacelle fan cowl.

[0137] Other aspects of the disclosure are provided by the subject matter of the following clauses:

[0138] 1. A turbine engine comprising an engine core, an inner shroud radially spaced from and circumscribing the engine core, an outer shroud radially spaced from and circumscribing at least a portion of the inner shroud, and an accessory gearbox including a first portion located within the inner shroud and spanning the engine core and a second portion located between the inner shroud and the outer shroud.

[0139] 2. A turbine engine according to any preceding clause, wherein the accessory gearbox defines an accessory gearbox axis parallel to the turbine engine axis of rotation.

[0140] 3. A turbine engine according to any preceding clause, wherein the second portion of the accessory gearbox is perpendicular to the accessory gearbox axis.

[0141] 4. A turbine engine according to any preceding clause, wherein the accessory gearbox comprises a first set of interfaces defined by a first plane, a second set of interfaces defined by a second plane and a third set of interfaces defined by a third plane.

[0142] 5. A turbine engine according to any preceding clause, wherein the first portion of the accessory gearbox comprises a V-shaped cross-section.

[0143] 6. A turbine engine according to any preceding clause, wherein the V-shaped cross section defines a first surface perpendicular to the first plane and a second surface perpendicular to the second plane.

[0144] 7. A turbine engine according to any preceding clause, wherein the first portion of the accessory gearbox comprises a C-shaped or arcuate cross-section.

[0145] 8. A turbine engine according to any preceding clause, wherein the arcuate cross-section defines a first end point and a second end point, and the second portion of the accessory gearbox is unequally spaced between the first end point and the second end point.

[0146] 9. A turbine engine according to any preceding clause, wherein at least a portion of the second portion of the accessory gearbox extends through an inner surface of the outer shroud.

[0147] 10. A turbine engine according to any preceding clause, further comprising a strut extending radially from the inner shroud and operably coupling the inner shroud and the outer shroud.

[0148] 11. A turbine engine according to any preceding clause, wherein at least a portion of the second portion of the accessory gearbox is located in the strut.

[0149] 12. A turbine engine according to any preceding clause, wherein the engine core comprises at least a compressor section, a combustion section and a turbine section arranged in an axial flow.

[0150] 13. A turbine engine comprising a fan assembly defining an inlet; an engine core; an inner shroud radially spaced from the engine core and having an inner surface that circumscribes at least a portion of the engine core; an outer shroud radially spaced from the inner shroud and circumscribing at least a portion of the inner shroud; a bifurcated airflow path comprising a first portion extending from the inlet through the engine core and a second portion extending from the inlet through a secondary airflow path defined between the inner shroud and the inner shroud; and an accessory gearbox having a first portion located within the inner shroud and a second portion located in the secondary airflow path.

[0151] 14. A turbine engine according to any preceding clause, further comprising a strut extending radially through the secondary airflow path and coupling the inner shroud and the outer shroud, wherein the second portion of the accessory gearbox is located in the strut.

[0152] 15. A turbine engine according to any preceding clause, wherein the accessory gearbox defines an accessory gearbox axis parallel to the turbine engine axis of rotation.

[0153] 16. A turbine engine according to any preceding clause, wherein the accessory gearbox comprises a first set of interfaces defined by a first plane, a second set of interfaces defined by a second plane and a third set of interfaces defined by a third plane.

[0154] 17. A turbine engine according to any preceding clause, wherein the second portion of the accessory gearbox is perpendicular to the accessory gearbox axis.

[0155] 18. A turbine engine according to any preceding clause, wherein the first portion of the accessory gearbox comprises a C-shaped or arcuate cross-section.

[0156] 19. A turbine engine according to any preceding clause, wherein the arcuate cross-section defines a first end point and a second end point, and the second portion of the accessory gearbox is unequally spaced between the first end point and the second end point.

[0157] 20. A turbine engine according to any preceding clause, wherein at least a portion of the second portion of the accessory gearbox extends through an inner surface of the outer shroud.

Claims

1. A turbine engine, comprising: a fan assembly defining an inlet; Engine core; an inner shroud radially spaced from and surrounding the engine core; an outer shroud radially spaced from the inner shroud and surrounding at least a portion of the inner shroud, the outer shroud including a radially inner surface; a bifurcated airflow path including a first portion extending from the inlet through the engine core and a second portion extending from the inlet through a secondary airflow path defined between the inner cowl and the outer cowl; and Accessory gearbox, comprising: a first portion located within the inner cowl and spanning the engine core, the first portion comprising: a first arm, wherein a first set of interfaces is defined by portions of the first arm; and a second arm, wherein a second set of interfaces is defined by a portion of the second arm; and a second portion located between the inner shroud and the radially inner surface of the outer shroud, wherein the second portion defines a base, the first arm and the second arm of the first portion extend from the base to define a Y-shaped object, and wherein a third set of interfaces is defined by the second portion of the accessory gearbox; and One or more of a fuel pump, a gearbox, a lubrication pump, an air compressor, a scavenge pump, a generator, a fuel control device, a permanent magnet alternator, or a hydraulic pump operably coupled to the third set of interfaces.

2. The turbine engine according to claim 1, wherein: The accessory gearbox defines an accessory gearbox axis that is parallel to the turbine engine's axis of rotation.

3. The turbine engine according to claim 2, wherein: The accessory gearbox includes the first set of interfaces defined by a first plane, the second set of interfaces defined by a second plane, and the third set of interfaces defined by a third plane.

4. The turbine engine according to claim 3, wherein: A first angle is defined from the third plane to the first plane when rotating in a clockwise direction, wherein the first angle is greater than 0 degrees and less than 180 degrees.

5. The turbine engine according to claim 4, wherein: A second angle is defined from the third plane to the second plane when rotating in a counterclockwise direction, wherein the second angle is greater than 0 degrees and less than 180 degrees.

6. The turbine engine according to claim 5, wherein: The first angle or the second angle is greater than 0 degrees and less than 90 degrees.

7. The turbine engine according to claim 3, wherein: The first portion of the accessory gear case includes a V-shaped cross-section, wherein the V-shaped cross-section defines a first surface perpendicular to the first plane and a second surface perpendicular to the second plane.

8. The turbine engine according to claim 2, wherein: The first portion of the accessory gear case includes a C-shaped or arcuate cross-section.

9. The turbine engine according to claim 8, wherein: The arcuate cross-section defines a first end point and a second end point, and the second portion of the accessory gear case is unequally spaced between the first end point and the second end point.

10. The turbine engine according to claim 9, wherein: The first arm includes a first arm distance measured from an accessory gearbox axis to a first distal surface or the first end point, wherein the first arm distance is between 5% and 50% of a circumference of the engine core or core shell.

11. The turbine engine according to claim 10, wherein: The second arm includes a second arm distance measured from the accessory gearbox axis to a second distal surface or the second end point, wherein the second arm distance is between 5% and 50% of a circumference of the engine core or the core shell.

12. The turbine engine of claim 1, further comprising a strut extending radially from the inner shroud and operably coupling the inner shroud and the outer shroud.

13. The turbine engine according to claim 12, wherein: At least a portion of the second portion of the accessory gearbox is located in the strut.

14. The turbine engine of claim 13, further comprising an upper strut spaced apart from the strut, wherein the upper strut couples the inner shroud and the outer shroud.

15. The turbine engine according to claim 1, wherein: The accessory gearbox is mounted to the engine core using a hinged mount.

16. The turbine engine according to claim 1, wherein: The Y-shaped object operably coupled to the first, second, and third groups of interfaces is a first fork, wherein the turbine engine further comprises a group of forks comprising at least a first fork and a second fork.

17. The turbine engine of claim 16, the first and second forks being coupled by one or more of a drive shaft, a gearbox, or a hydraulic drive.

18. The turbine engine according to claim 17, wherein: The one or more of a drive shaft, a gearbox, or a hydraulic driver further comprises one or more housings located between the first fork and the second fork.

19. A turbine engine comprising: a fan assembly defining an inlet; Engine core; an inner shroud radially spaced from and surrounding the engine core; an outer shroud radially spaced from the inner shroud and surrounding at least a portion of the inner shroud, the outer shroud including a radially inner surface; a bifurcated airflow path including a first portion extending from the inlet through the engine core and a second portion extending from the inlet through a secondary airflow path defined between the inner cowl and the outer cowl; and Accessory gearbox, comprising: a first portion located within the inner cowl and spanning the engine core, the first portion comprising: a first arm, wherein a first set of interfaces is defined by portions of the first arm; and a second arm, wherein a second set of interfaces is defined by a portion of the second arm; and a second portion located between the inner shroud and the radially inner surface of the outer shroud, wherein the second portion defines a base, the first arm and the second arm of the first portion extend from the base to define a Y-shaped object, and wherein a third set of interfaces is defined by the second portion of the accessory gearbox.

20. A turbine engine comprising: a fan assembly defining an inlet; Engine core; an inner shroud radially spaced from and surrounding the engine core; an outer shroud radially spaced from the inner shroud and surrounding at least a portion of the inner shroud, the outer shroud including a radially inner surface; a bifurcated airflow path including a first portion extending from the inlet through the engine core and a second portion extending from the inlet through a secondary airflow path defined between the inner cowl and the outer cowl; a strut extending radially from the inner shroud and operably coupling the inner shroud and the outer shroud; and An accessory gearbox having an accessory gearbox housing, the accessory gearbox comprising: a first portion located within the inner cowl and spanning the engine core, the first portion comprising: a first arm, wherein a first set of interfaces is defined by portions of the first arm; and a second arm, wherein a second set of interfaces is defined by a portion of the second arm; and a second portion located between the inner and outer shroud radially inner surfaces, wherein the second portion extends from the first and second arms of the first portion to define a single yoke, and wherein a third set of interfaces is defined by the second portion of the accessory gearbox, wherein the accessory gearbox housing includes the single yoke and is located partially in the inner shroud and partially in the strut; and One or more of a fuel pump, a gearbox, a lubrication pump, an air compressor, a scavenge pump, a generator, a fuel control device, a permanent magnet alternator, or a hydraulic pump operably coupled to the third set of interfaces.

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