Non-ducted fan turbine engine with a cowl

Abstract

A non-ducted fan turbine engine includes an engine core including a first airflow, and a nacelle surrounding at least a portion of the engine core and having an exterior surface defining a second airflow. The nacelle further includes an internal passage between the exterior surface and the engine core, the internal passage defining a third airflow. The non-ducted fan turbine engine further includes a plurality of rotatable fan blades extending radially beyond the exterior surface of the nacelle, and a shroud door located in the nacelle.

Description

Technical Field

[0001] This disclosure generally relates to non-ducted fan turbine engines, and more specifically, to hoods for non-ducted fan turbine engines. Background Technology

[0002] A gas turbine engine is a rotary engine that extracts energy from a flow of working air to provide thrust in an aircraft. This working air flow passes sequentially through a compressor section (where working air is compressed), a combustor section (where fuel is added to the working air and ignited), and a turbine section (where the combusted working air is expanded and work is extracted from the working air to drive the compressor section and other systems). The compressor and turbine stages comprise axially arranged pairs of rotating and stationary blades. A gas turbine engine may be arranged as an engine core comprising at least an axially flowing compressor section, a combustor section, and a turbine section, defining at least one rotating element or rotor and at least one stationary component or stator.

[0003] Turbine engines can have different configurations, such as turboprop engines (which are turbine engines that drive the propeller of an aircraft), turbofan engines (which are turbine engines with a fan upstream of the engine core, where both the fan and the engine core are housed within a nacelle), and propfan turbine engines (also known as ductless fan turbine engines). Ductless fans encompass aspects of both turboprop and turbofan engines. For example, similar to a turboprop engine, a ductless fan turbine engine may include a set of rotating blades or a propeller outside the engine casing, without the blades being confined within the nacelle. The absence of a nacelle or other casing surrounding the rotating blades in the fan section gives rise to the name "ductless" fan or propeller fan engine. A nacelle or other casing can still be used to enclose the engine core, rather than the fan blades. Historically, while ductless fan engines have been more fuel-efficient at commercial aircraft cruise speeds, other characteristics (such as relatively high noise levels) have prevented their widespread adoption in commercial aircraft. Attached Figure Description

[0004] The complete and practical disclosure of this specification, including its best mode, is set forth in the description with reference to the accompanying drawings, for those skilled in the art, wherein:

[0005] Figure 1 It is a schematic cross-sectional view of a non-ducted fan turbine engine for an aircraft, and includes a cabin that defines an internal passage and includes a shroud, a third airflow within the internal passage, and the engine core.

[0006] Figure 2 It is along Figure 1 A schematic diagram of the axial view of the engine taken by section line II-II further illustrates a set of hinges operably connecting a set of hoods to the engine mount, the hoods being in the closed position.

[0007] Figure 3 yes Figure 2 A schematic diagram of the axial view of the cover, in which the set of cover doors are in the open position.

[0008] Figure 4 yes Figure 2 A schematic diagram of an axial view of an exemplary cover, including an exemplary cover door.

[0009] Figure 5 yes Figure 2 A schematic diagram of an axial view of an exemplary cover, including an exemplary hinge.

[0010] Figure 6 yes Figure 2 A schematic diagram of an axial view of an exemplary cover, including an exemplary engine mount.

[0011] Figure 7 yes Figure 2 A schematic diagram of an axial view of an exemplary cover, including a set of exemplary hinges, the set of exemplary cover doors being in the closed position.

[0012] Figure 8 yes Figure 7 A schematic diagram of an axial view of an exemplary cover, including the set of exemplary cover doors in the open position.

[0013] Figure 9 yes Figure 2 A schematic diagram of an axial view of an exemplary cover, including the exemplary outer edge of the set of exemplary cover doors in the closed position.

[0014] Figure 10 yes Figure 9 A schematic diagram of an axial view of an exemplary cover, including the set of exemplary cover doors in the open position. Detailed Implementation

[0015] This disclosure relates to a set of hoods for a turbine engine, and more specifically, to a set of hoods for a non-ducted fan turbine engine. As described herein, a non-ducted fan turbine engine may comprise a fan, a set of blades downstream of the fan, and an engine core, wherein the fan and the set of blades are positioned along a portion of the exterior of a nacelle, the nacelle defining at least a portion of the exterior of the non-ducted fan turbine engine. The non-ducted fan turbine engine may be further defined by three main airflows (a first airflow, a second airflow, and a third airflow). The first airflow may be defined as an airflow flowing through the engine core, the second airflow may be defined as an airflow flowing over the fan, the exterior of the nacelle, and the set of blades, and the third airflow may be defined as an airflow flowing through at least a portion of the nacelle, particularly through an internal passageway formed within the nacelle. The set of hoods may be included within the nacelle, particularly within a portion of the nacelle defining a portion of the third airflow. It is envisioned that the set of hoods may be connected to an engine mount via a set of hinges, allowing the hoods to move between a first or closed position and a second or open position.

[0016] As described herein, this set of hoods in a non-ducted fan turbine engine allows selective access to at least a portion of the engine core without physically removing parts of the non-ducted fan turbine engine. For illustrative purposes, an exemplary environment in which a set of hoods may be used will be described in the form of a non-ducted fan turbine engine. However, it should be understood that this set of hoods as described herein is generally applicable to any turbine engine, such as, but not limited to, gas turbine engines, turboprop engines, turboshaft engines, turbofan engines with power gearboxes, or non-ducted fan turbine engines in the non-limiting examples. However, it will be understood that the aspects of this disclosure described herein are not limited thereto and can have general applicability in other turbine engines. For example, this disclosure may be applicable to a set of hoods in other engines or vehicles and may be used to provide benefits in industrial, commercial, and residential applications.

[0017] 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 fluid flow. The terms "front" or "in front" indicate what is in front of something, and "back" or "behind" indicate what is behind something. For example, when used in relation to fluid flow, "front" or "in front" can indicate upstream, and "back" or "behind" can indicate downstream.

[0018] Furthermore, as used herein, the term "radial" or "radially" refers to a direction away from a common center. For example, in the overall context of a turbine engine, radial refers to the direction of a ray extending between the engine's central longitudinal axis and the outer circumferential direction. Additionally, as used herein, the term "group" or a "set" of elements can refer to any number of elements, including only one element.

[0019] All directional references (e.g., radial, up, down, upward, downward, left, right, lateral, front, back, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise) are used for identification purposes only to aid the reader's understanding of this disclosure and do not impose limitations, particularly regarding their location, orientation, or purpose. Unless otherwise stated, connection references (e.g., attachment, coupling, connection, and joining) are to be interpreted broadly and may include intermediate members between sets of elements and relative movement between elements. Therefore, a connection reference does not necessarily imply that two elements are directly connected and have a fixed relationship with each other. Exemplary figures are for illustrative purposes only, and the dimensions, positions, order, and relative sizes reflected in the accompanying figures may vary. As used herein, a "set" may include any number of elements, including only one element. As used herein, "monolithic monolith" or "monolithic" means a single entity as a single, inseparable part or formed as a single integral part during manufacture, as opposed to combining individual elements into one during manufacture.

[0020] Figure 1 This is a schematic cross-sectional view of a turbine engine, particularly a non-ducted fan turbine engine 10 for use in an aircraft. The non-ducted fan turbine engine 10 has a generally longitudinally extending axis or engine centerline 12 extending from the front 14 to the rear 16. The non-ducted fan turbine engine 10 includes a set of circumferentially spaced blades or propellers in a downstream series flow relationship, defining: a fan section 18, which includes a fan 20; a compressor section 22, which includes a supercharger or low-pressure (LP) compressor 24 and a high-pressure (HP) compressor 26; a combustion section 28, which includes a combustor 30; a turbine section 32, which includes an HP turbine 34 and an LP turbine 36; and an exhaust section 38. The non-ducted fan turbine engine 10 described herein is a non-limiting example, and other architectures are possible, such as, but not limited to, steam turbine engines, supercritical carbon dioxide turbine engines, or any other suitable turbine engine.

[0021] The external surface of the non-ducted fan turbine engine 10, defined by the nacelle 40, extends from the front 14 toward the rear of the non-ducted fan turbine engine 10 and covers at least a portion of the compressor section 22, combustion section 28, turbine section 32, and exhaust section 38. A fan section 18 may be located at the front 14 of the nacelle 40 and extends radially outward from the nacelle 40 of the non-ducted fan turbine engine 10; specifically, the fan section 18 may extend radially outward from the nacelle 40. The fan section 18 includes a set of fan blades 42 and a set of stationary fan blades 82 downstream of the set of fan blades 42, both radially arranged about the engine centerline 12. As a non-limiting example, the non-ducted fan turbine engine 10 may include a single set of rotating blades or a propeller (e.g., the set of fan blades 42) disposed upstream of the set of stationary fan blades 82. Therefore, the non-ducted fan turbine engine 10 may be further defined as a non-ducted single-fan turbine engine. The non-ducted fan turbine engine 10 can be further defined by the position of the fan section 18 relative to the combustion section 28. As shown, the fan section 18 is in front of or ahead of the combustion section 28, such that the non-ducted fan turbine engine 10 is considered to be a non-ducted fan turbine engine 10 having a front fan section 18 or a tractor fan section 18. Alternatively, the fan section 18 may be downstream of or behind the combustion section 28, such that the non-ducted fan turbine engine 10 is considered to be a non-ducted fan turbine engine 10 having a rear fan section 18 or a propeller fan section 18.

[0022] The compressor section 22, combustion section 28, and turbine section 32 can be collectively referred to as the engine core 44, which generates combustion gases. The engine core 44 is surrounded by an engine housing 46, which can be connected to a portion of the nacelle 40 of the non-ducted fan turbine engine 10.

[0023] An HP shaft or spool 48, coaxially arranged around the engine centerline 12 of the non-ducted fan turbine engine 10, drives the HP turbine 34 to the HP compressor 26. An LP shaft or spool 50, coaxially arranged within a larger diameter annular HP spool 48 around the engine centerline 12 of the non-ducted fan turbine engine 10, drives the LP turbine 36 to the LP compressor 24 and the fan 20. The spools 48 and 50 are rotatable around the engine centerline 12 and are connected to a set of rotatable elements that collectively define the rotor 51.

[0024] LP compressor 24 and HP compressor 26 each include a set of compressor stages 52 and 54, respectively, in which a set of compressor blades 56 and 58 rotate relative to a corresponding set of static compressor impeller blades 60 and 62 (also referred to as nozzles) to compress or pressurize the fluid flow passing through the stage. In a single compressor stage 52 or 54, multiple compressor blades 56 and 58 can be arranged in a ring and can extend radially outward from the blade platform relative to the engine centerline 12 to the blade tips, while the corresponding static compressor impeller blades 60 and 62 are positioned upstream of and adjacent to the compressor blades 56 and 58. It is worth noting that... Figure 1 The number of blades, impellers, and compressor stages shown is selected for illustrative purposes only, and other numbers are also possible.

[0025] Compressor blades 56 and 58 for the compressor stage can be mounted to disc 61, which is mounted to a corresponding one of HP spool 48 and LP spool 50, with each stage having its own disc 61. Static compressor impellers 60 and 62 for the compressor stage can be mounted to the engine housing 46 in a circumferential arrangement.

[0026] HP turbine 34 and LP turbine 36 each include a set of turbine stages 64 and 66, respectively, in which a set of turbine blades 68 and 70 rotate relative to a corresponding set of static turbine blades 72 and 74 (also referred to as nozzles) to extract energy from the fluid flow passing through the stage. In a single turbine stage 64 and 66, multiple turbine blades 68 and 70 may be arranged in a ring and may extend radially outward from the blade platform relative to the engine centerline 12 to the blade tip, while the corresponding static turbine blades 72 and 74 are positioned upstream of and adjacent to the turbine blades 68 and 70. It is worth noting that... Figure 1 The number of blades, impellers, and turbine stages shown is selected for illustrative purposes only; other numbers are also possible.

[0027] Turbine blades 68 and 70 for the turbine stage can be mounted on disc 71, which is mounted on a corresponding one of HP spool 48 and LP spool 50, with each stage having a dedicated disc 71. Turbine blades 72 and 74 for the compressor stage can be mounted circumferentially to the engine housing 46.

[0028] As a complement to the rotor section, the stationary parts of the non-ducting fan turbine engine 10 (e.g., the static blades 60, 62, 72, 74 in the compressor section 22 and turbine section 32) are also referred to individually or collectively as the stator 63. Therefore, the stator 63 can refer to the combination of non-rotating elements throughout the non-ducting fan turbine engine 10.

[0029] The nacelle 40 is operatively coupled to the inline fan-turbo engine 10 and covers at least a portion of the engine core 44, engine casing 46, or exhaust section 38. As a non-limiting example, at least a portion of the nacelle 40 may extend further axially forward or upstream in the illustrated location. For example, the nacelle 40 may extend axially forward such that a portion of the nacelle 40 covers or conceals a portion of the fan section 18 or turbocharger section (not shown) of the inline fan-turbo engine 10. The nacelle 40 may also include a shroud 100 having an inner cylinder 102 and an outer cylinder 104, the outer cylinder 104 being disposed radially outward from the inner cylinder 102 relative to the engine centerline 12. The space between the inner cylinder 102 and the outer cylinder 104 may define an internal passage 94 extending circumferentially around a portion of the inline fan-turbo engine 10.

[0030] The nacelle 40 can be operatively coupled to the non-ducted fan turbine engine 10 at the engine split line 84. As a non-limiting example, the shroud 100 can be operatively coupled to the non-ducted fan turbine engine 10 at or along the engine split line 84. The engine split line 84 can extend from a first interface 86 with the inner cylinder 102 to a second interface 88 with the outer cylinder 104. The first interface 86 and the second interface 88 of the engine split line 84 can be axially displaced from each other. As a non-limiting example, the first interface 86 can be axially rearward of the second interface 88. However, it should be understood that the first interface 86 can be axially positioned in front of, behind, or coincide with the second interface 88. As a non-limiting example, the engine split line 84 can extend linearly from the first interface 86 to the second interface 88. Alternatively, the engine split line 84 can include various non-linear portions along its length. For example, the engine split line 84 at the first interface 86 and the second interface 88 can be perpendicular to the engine centerline 12, while the engine split line between the first interface 86 and the second interface 88 can be obliquely oriented relative to the engine centerline 12. The engine dividing line 84 may further extend circumferentially around the engine centerline 12 and include interfaces to the inner cylinder 102 and outer cylinder 104 along the entire circumferential range. It should be understood that the axial positions of the first interface 86 and the second interface 88 may vary circumferentially along the inner cylinder 102 and outer cylinder 104.

[0031] The first interface 86 and the second interface 88 may also represent the connection points between the shroud 100 and the inner cylinder 102 and the outer cylinder 104, respectively. Therefore, the nacelle 40 can be coupled to the non-ducted fan turbine engine 10. The coupling can be accomplished by any suitable method, such as, but not limited to, fastening, bonding, welding, hinges, or any combination thereof. Additional components may be positioned along the engine partition line 84 to seal the nacelle 40 to the non-ducted fan turbine engine 10. For example, a series of seals may be provided along the engine partition line 84 at the starting point of the inner cylinder 102 or the outer cylinder 104 to restrict or prevent fluid from entering from the internal passage 94 and into other parts of the non-ducted fan turbine engine 10 (e.g., the space between the nacelle 40 and the engine casing 46).

[0032] As shown in the figure, the internal passage 94 can have a varying cross-section from the inlet 96 to the outlet 98. Specifically, the cross-section of the internal passage 94 can decrease from the engine dividing line 84 to the outlet 98. Therefore, the internal passage 94 near the outlet 98 can function as a nozzle and pressurize the fluid flow within the outlet 98 before discharging the fluid from the outlet 98. Alternatively, the internal passage can have a constant cross-sectional area from the inlet 96 to the outlet 98.

[0033] As shown in the figure, during the operation of the non-ducted turbine engine 10, the airflow flowing through or passing through the non-ducted fan turbine engine 10 can be divided into three discrete airflows. A first portion of the airflow defining the first airflow 76 can pass through the engine core 44, a second portion of the airflow defining the second airflow 78 can pass through the exterior of the nacelle 40, and a third portion of the airflow defining the third airflow 80 passes through the interior of the nacelle 40 between the engine core 44 and the exterior of the nacelle 40.

[0034] The second airflow 78 can flow around the set of fan blades 42 and over the nacelle 40 of the non-ducted fan turbine engine 10. Subsequently, the second airflow 78 can flow over at least a portion of the set of stationary fan blades 82, which can guide the second airflow 78 laterally toward the engine centerline 12. The second airflow 78 can then flow over the set of stationary fan blades 82, following the curvature of the nacelle 40 of the non-ducted fan turbine engine 10 and toward the exhaust section 38.

[0035] The remainder of the airflow not defined by the second airflow 78 can flow into the inline fan turbine engine 10, where the remaining airflow is divided into a first airflow 76 and a third airflow 80. The first airflow 76 can first flow into the LP compressor 24, which then pressurizes it, thereby defining a pressurized airflow supplied to the HP compressor 26, which further pressurizes the air. The first airflow 76, or pressurized airflow, from the HP compressor 26 mixes with and ignites fuel in the combustor 30, generating combustion gases. Some work is extracted from these gases by the HP turbine 34, which drives the HP compressor 26. The combustion gases are discharged into the LP turbine 36, which extracts additional work to drive the LP compressor 24, and the first airflow 76, or exhaust gas, is finally discharged from the inline fan turbine engine 10 via the exhaust section 38. The drive of the LP turbine 36 drives the LP spool 50 to rotate the fan 20 and the LP compressor 24. The first airflow 76, which includes pressurized airflow and combustion gas, can define the working airflow flowing through the compressor section 22, combustion section 28 and turbine section 32 of the non-ducted fan turbine engine 10.

[0036] A third airflow 80 can flow within an internal passage 94 located between an inlet 96 and an outlet 98 upstream of the engine core 44, the outlet 98 being positioned along a portion of the nacelle 40 of the non-ducted fan turbine engine 10, particularly along a portion of the nacelle 40. The third airflow 80 can flow from the inlet 96 across the engine split line 84 and into the internal passage 94 of the shroud 100. As shown, a portion of the internal passage 94 through which the third airflow 80 flows can be formed as part of the non-ducted fan turbine engine 10, particularly the portion of the internal passage 94 between the inlet 96 and the engine split line 84, while the remainder can be formed by the shroud 100. However, it should be understood that the engine split line 84 can be positioned along any portion of the internal passage 94. For example, the engine split line 84 can coincide with the inlet 96, such that the entire internal passage 94 is formed by the shroud 100. A portion of the third airflow 80 exiting the outlet 98 can then mix with the second airflow 78 and flow toward the rear portion 16 of the non-ducted fan turbine engine 10. The first airflow 76, the second airflow 78, and the third airflow 80 exiting the exhaust section 38 can together generate thrust in the inline fan turbine engine 10. It is envisioned that the first airflow 76 generates most of the thrust, while the second airflow 78 and the third airflow 80 can generate less thrust than the first airflow 76. As a non-limiting example, the third airflow 80 can generate up to 8% of the thrust of the inline fan turbine engine 10.

[0037] It is conceivable that a portion of the first airflow 76 or the third airflow 80 can be extracted as bleed air (in the case of the first airflow 76, extracted from compressor section 22). Bleed air can provide airflow to engine components requiring cooling. The temperature of the first airflow 76 entering the combustor 30 is significantly increased. Therefore, cooling provided by bleed air is necessary for operating these engine components in elevated temperature environments or in the hot sections of the non-ducted fan turbine engine 10. In the case of a turbine engine, the hot sections of the engine are typically downstream of the combustor 30, particularly downstream of the turbine section 32, where the HP turbine 34 is the hottest section because it is directly downstream of the combustion section 28. Other sources of cooling fluid can be, but are not limited to, fluids discharged from the LP compressor 24 or the HP compressor 26.

[0038] Figure 2 It is along Figure 1 A schematic diagram of the axial view of the internal passage 94 of a non-ducted fan turbine engine 10, taken at section II-II. As discussed herein, the internal passage 94 can at least partially define a third airflow 80 ( Figure 1 A set of doors (particularly a pair of doors) shown as a first door 108 and a second door 110 may each define at least a portion of the internal passage 94. As a non-limiting example, both the first door 108 and the second door 110 may be received in a first or closed position. In the closed position, the first door 108 and the second door 110 at least partially surround the engine core 44. The closed position may be further defined as the positioning of the cover 100 when the non-ducted fan turbine engine 10 is operating.

[0039] The first gate 108 and the second gate 110 may each include corresponding portions of the inner cylinder 102 and the outer cylinder 104 that define the radial inner and radial outer boundaries of the gates 108 and 110, respectively. The first gate 108 and the second gate 110 may extend between a first outer edge 112 and a second outer edge 114 that is circumferentially displaced from the first outer edge 112. The first outer edge 112 and the second outer edge 114 of the first gate 108 face the first outer edge 112 and the second outer edge 114 of the second gate 110, respectively. The space divided by the inner cylinder 102, the outer cylinder 104, the first outer edge 112, and the second outer edge 114 may define an internal channel 94 formed by the first gate 108 and the second gate 110.

[0040] As shown in the figure, when in the closed position, the first door 108 and the second door 110 can be coupled to each other or to at least a portion of the cabin 40. The coupling between the first door 108, the second door 110, or the cabin 40 can be accomplished by any suitable coupling method (e.g., but not limited to latching, fastening, welding, adhesive, magnetism, or any other suitable coupling method). It is contemplated that the first door 108 and the second door 110 can be separated from each other or from the cabin 40; therefore, the coupling can be, for example, a latch extending between the first door 108 and the second door 110 that can be locked or unlocked to couple or separate the first door 108 and the second door 110.

[0041] The first gate 108 and the second gate 110 may each be semi-circular and external to at least a portion of the engine core 44. Therefore, the internal channel 94 can form a ring around the engine core 44. The ring may extend circumferentially around the entire engine core 44. Alternatively, the ring may extend circumferentially less than the entire outer periphery of the engine core 44. As a non-limiting example, the ring may extend at least 240 degrees around the engine core 44 in total. As shown, the first gate 108 and the second gate 110 may be separate from each other, such that the internal channel 94 or the ring may be discontinuous. In the case where the set of gates includes the pair of gates 108, 110, the ring may be defined by two portions symmetrical about a plane perpendicular to the engine centerline 12 and intersecting with the mount 116. As a non-limiting example, the ring may be defined by two portions symmetrical about a plane intersecting with the mount 116 and extending in the axial direction. However, it should be understood that any number of two or more portions defining the ring are possible. Further, the ring may include a set of struts (not shown) that extend from the inner cylinder 102 to the outer cylinder 104.

[0042] Although shown as circular, it should be understood that cover 100, and therefore the first cover 108 and the second cover 110, may include at least one non-circular portion. For example, at least a portion of covers 108, 110 may be defined by linear segments or other non-circular curved segments. Since the internal passage 94 is at least partially defined by covers 108, 110, at least a portion of the internal passage 94 may also be defined by non-circular portions.

[0043] The nacelle 40 may further include engine mounts that operatively connect the nacelle 40 and, therefore, the non-ducted fan turbine engine 10 to one or more parts of the aircraft (e.g., the wing or fuselage of the aircraft). As a non-limiting example, the engine mount is shown as a pylon 116 that operatively connects the nacelle 40 and, therefore, the non-ducted fan turbine engine 10 to one or more parts of the aircraft. The pylon 116 may be defined by a distal end 120, which may be coupled to at least one part of the aircraft.

[0044] The cabin 40 may also include a set of hinges 118 positioned adjacent to the pylon 116. As used herein, the term “adjacent” may otherwise be defined as “near,” “within,” or “connected to.” Thus, the set of hinges 118 may be adjacent to, near, within, or otherwise connected to the pylon 116. The set of hinges 118 may operatively connect the first hatch 108 and the second hatch 110 to the cabin 40 or the pylon 116. Specifically, the set of hinges 118 may be operatively connected to a first outer edge 112 corresponding to the first hatch 108 or the second hatch 110. The set of hinges 118 may be located where the outer cylinder 104 and the first outer edge 112 meet. Thus, the first outer edge 112 may be defined as the hinge edge corresponding to the first hatch 108 and the second hatch 110. As shown, the set of hinges 118 is positioned near a portion of the pylon 116 opposite the distal end 120. Therefore, the set of door panels 108 and 110 can be radially spaced from the distal end 120 of the hanger 116.

[0045] Although shown in two dimensions along engine partition line 84, it should be understood that aspects of the nacelle 40, the first hatch 108, and the second hatch 110 can be defined by similar features along the entire nacelle 100. For example, the mount 116 may be located only at engine partition line 84. Alternatively, the mount 116 may be positioned along any one or more suitable portions of the nacelle 100 or the nacelle 40. Similarly, the set of hinges 118 may be axially spaced from each other, such that each hatch 108, 110 is connected to any number of hinges 118.

[0046] It should also be understood that there can be any number of first gates 108 or second gates 110 that are axially displaced along the hood 100. As a non-limiting example, there can be two second gates 110, one of which is axially ahead or upstream of the other. In other words, the two second gates 110 are axially displaced from each other. The axially displaced first gates 108 and second gates 110 can allow the gates to be positioned along the axial range of the hood 100 to allow selective access to the engine core 44 or various parts of the non-ducted fan turbine engine 10 along the axial range of the hood 100. It will be further understood that the first gate 108 or the second gate 110 can be formed within the other first gate 108 or the other second gate 110, respectively. As a non-limiting example, there can be two first gates 108, one of which is smaller than the other. The smaller of the two first doors 108 can be positioned along the larger first door 108 and operably connected to the larger first door 108 via a set of hinges, or otherwise removable from the larger first door 108. This allows selective access to specific portions of the non-ducted fan turbine engine 10 without opening the larger of the two first doors 108. Any number of smaller doors 108, 110 can be positioned along the larger doors 108, 110.

[0047] Figure 3 It is along Figure 1 A schematic diagram of the axial view of the non-ducted fan turbine engine 10, taken from section II-II, further illustrates... Figure 2 The first door 108 and the second door 110 are in a second or open position. In the open position, at least one of the first door 108 or the second door 110 is open. Figure 2 The closed position is at least partially radially displaced. In the open position, at least a portion of the engine core 44 is exposed, thereby allowing access to the engine core 44. The open position can be further defined as the positioning of the shroud 100 when the non-ducted fan turbine engine 10 is not in operation. As shown, both the first shroud 108 and the second shroud 110 are open; however, although shrouds 108 and 110 are both shown in the open position, it should be understood that shrouds 108 and 110 can be opened independently of each other. For example, the first shroud 108 can be at least partially open or in the open position, while the second shroud 110 remains closed or in the closed position.

[0048] The first door 108 and the second door 110 can each pivot about a corresponding portion of the set of hinges 118, similar to the pivoting of a gull-wing door or a clamshell door. Therefore, the first door 108 and the second door 110 can be defined as a set of gull-wing doors.

[0049] The first door 108 and the second door 110 can be in the closed position ( Figure 2 ) and opening position ( Figure 3 The movable doors 108 and 110 are movable to allow selective access to the engine core 44 or any other non-ducted fan turbine engine 10 component (e.g., accessory gearbox, electronics, generator, or any other suitable component within the nacelle 40). One non-limiting use of the movable doors 108 and 110 is to provide easy access to the engine core 44 during maintenance work. As discussed herein, the doors 108 and 110 can be easily separated from each other, so that when maintenance is required, the doors 108 and 110 can be separated and pivoted about the set of hinges 118, thereby moving at least one of the first door 108 or the second door 110 from a closed position to an open position to allow access to the engine core or any other non-ducted fan turbine engine 10 component. When maintenance is complete, the first door 108 and the second door 110 can be closed (e.g., in the closed position) and engaged with each other to secure the engine core 44 within the nacelle 40.

[0050] Figure 4 yes Figure 2 A schematic diagram of an axial view of an exemplary cover 200. The exemplary cover 200 is similar to cover 100; therefore, in the 200 series, similar parts will be identified by similar numbers, and it should be understood that, unless otherwise stated, the description of similar parts of cover 100 applies to cover 200.

[0051] As shown in the figure, cover 200 is in the closed position (e.g., similar to...). Figure 2 (as shown in the image) and is able to be in both the closed and open positions (e.g., similar to...). Figure 3 The cover 200 is movable between the positions shown in the diagram. The cover 200 includes a first cover 208 and a second cover 210, each cover including corresponding portions of an inner cylinder 202 and an outer cylinder 204. Both the first cover 208 and the second cover 210 extend circumferentially between a first outer edge 112 and a second outer edge 214, the first outer edge 112 being coupled to a set of hinges 118 adjacent to a hanger 116 and radially opposite to the distal end 120 of the hanger 116, and the second outer edge 214 defining the circumferentially distal ends of the first cover 208 and the second cover 210 relative to the first outer edge 112. An internal passage 294 may be divided by the inner cylinder 202, the outer cylinder 204, the first outer edge 112, and the second outer edge 214, and is located within the first cover 208 and the second cover 210.

[0052] The first cover 208 and the second cover 210 may circumferentially surround at least a portion of the engine core 44. As shown, the first cover 208 may extend circumferentially across the engine core 44 over a larger circumferential range than the second cover 210. The first cover 208 may extend more than 180 degrees around the engine core 44, while the second cover 210 may extend less than 180 degrees around the engine core 44. In other words, the first cover 208 and the second cover 210 are asymmetrical about a plane perpendicular to the engine centerline 12 and intersecting with the mount 116. It should be understood that the first cover 208 may include any circumferential length greater than the circumferential length of the second cover 210. In a non-limiting example, the first cover 208 may extend across the entire circumferential range of both the first cover 208 and the second cover 210, such that the cover 200 includes only the first cover 208. Alternatively, the circumferential length of the second gate 210 may be any multiple greater than that of the first gate 208, or may be limited such that the second gate 210 extends across the entire circumferential range of the first gate 208.

[0053] Figure 5 yes Figure 2 A schematic diagram of an axial view of an exemplary cover 300. The exemplary cover 300 is similar to covers 100 and 200; therefore, in the 300 series, similar parts will be identified by similar numbers, and it should be understood that, unless otherwise stated, the description of similar parts of covers 100 and 200 applies to cover 300.

[0054] Cover 300 includes a first cover door 308 and a second cover door 310, each cover door including corresponding portions of an inner cylinder 302 and an outer cylinder 304. Both the first cover door 308 and the second cover door 310 extend circumferentially between a first outer edge 312 and a second outer edge 114, the first outer edge 312 being adjacent to a hanger 116 and radially opposite to the distal end 120 of the hanger 116, and the second outer edge 114 defining the circumferentially distal ends of the first cover door 308 and the second cover door 310 relative to the first outer edge 312. An internal passage 94 may be divided by the inner cylinder 302, the outer cylinder 304, the first outer edge 312, and the second outer edge 114, and is located within the first cover door 308 and the second cover door 310.

[0055] Hinge 318 can be connected to a portion of hanger 116, and to one of the first outer edge 312 or hinge edge of the first door 308 or the second door 310. Therefore, hinge 318 can operatively connect one of the first door 308 or the second door 310 to hanger 116. As a non-limiting example, hinge 318 can be connected only to the first door 308 where the outer cylinder 304 and the first outer edge 312 meet. In this way, only the first door 308 can be in the closed or open position as shown (e.g., similar to...). Figure 3The second door 310 can be moved between the positions shown in the diagram. Alternatively, hinge 318 may operably connect only the second door 310 to the cabin 40, such that only the second door 310 is operably movable between the closed and open positions.

[0056] Figure 6 yes Figure 2 A schematic diagram of an axial view of an exemplary cover 400. The exemplary cover 400 is similar to covers 100, 200, and 300; therefore, in the 400 series, similar parts will be identified by similar numbers, and it should be understood that, unless otherwise stated, the description of similar parts of covers 100, 200, and 300 applies to cover 400.

[0057] As shown in the figure, cover 400 is in the closed position (e.g., similar to...). Figure 2 (as shown in the image) and is able to be in both the closed and open positions (e.g., similar to...). Figure 3 The cover 400 includes sections similar to the first cover 108 and the second cover 110, respectively. Figure 2 The first door 408 and the second door 410, wherein each door includes corresponding portions of the inner cylinder 402 and the outer cylinder 404. Except for the bracket 416 relative to... Figure 2 In addition to the circumferential offset of the bracket 116 shown, the cover 400 is similar to the cover 100. Figure 2 Therefore, the entire shroud 400 is circumferentially offset relative to the shroud 100. The shroud 400 is a non-limiting example showing the pylon 416 in different positions. It should be understood that the pylon 416 can move at any part of the circumferential range of the shroud 400, depending on how the non-ducted fan turbine engine 10 is mounted to the corresponding environment (e.g., an aircraft). Both the first shroud door 408 and the second shroud door 410 can extend in the circumferential direction between a first outer edge 412 and a second outer edge 414, the first outer edge 412 being coupled to the set of hinges 418 adjacent to the pylon 116 and radially opposite to the distal end 420 of the pylon 116, and the second outer edge 414 defining the circumferentially distal ends of the first shroud door 408 and the second shroud door 410 relative to the first outer edge 412. The pylon 116 can be defined by the distal end 420, which can be coupled to at least a portion of the aircraft. As shown, the second outer edge 414 can be displaced 180 degrees from the pylon 416. Thus, the first door 408 and the second door 410 can be symmetrical. However, it should be understood that the second outer edge 414 can be displaced from the bracket 416 by more or less than 180 degrees. Therefore, the first door 408 and the second door 410 can be asymmetrical, similar to the first door 208 and the second door 210, respectively. Figure 4 ).For example, Figure 2 The cover 100 shown can be used to mount the non-ducted fan turbine engine 10 to the underside of the wing, while Figure 6The cover 400 can be used to mount the non-ducted fan turbine engine 10 to the side of the fuselage.

[0058] Figure 7 yes Figure 2 A schematic diagram of an axial view of an exemplary cover 500. The exemplary cover 500 is similar to covers 100, 200, 300, and 400; therefore, in the 500 series, similar parts will be identified by similar numbers. It should be understood that, unless otherwise stated, the description of similar parts of covers 100, 200, 300, and 400 applies to cover 500.

[0059] As shown in the figure, cover 500 is in the closed position (e.g., similar to...). Figure 2 (as shown in the image) and is able to be in both the closed and open positions (e.g., similar to...). Figure 3 The cover 500 is movable between the positions shown in the diagram. The cover 500 includes a first cover 508 and a second cover 510, each cover including corresponding portions of an inner cylinder 502 and an outer cylinder 504. Both the first cover 508 and the second cover 510 extend circumferentially between a first outer edge 512 and a second outer edge 514, the first outer edge 512 being adjacent to the hanger 116 and radially opposite to the distal end 120 of the hanger 116, and the second outer edge 514 defining the circumferentially distal ends of the first cover 508 and the second cover 510 relative to the first outer edge 512. An internal passage 594 may be divided by the inner cylinder 502, the outer cylinder 504, the first outer edge 512, and the second outer edge 514, and is located within the first cover 508 and the second cover 510.

[0060] A set of hinges 518 adjacent to the mounting bracket 116 operably connects the first hatch 508 and the second hatch 510 to the cabin 40. As shown, the set of hinges 518 can connect to the first hatch 508 and the second hatch 510 at radially different locations. Specifically, the set of hinges 518 can connect to the first hatch 508 and the second hatch 510 at the meeting point of the inner cylinder 502 and the first outer edge 512, and at the meeting point of the outer cylinder 504 and the first outer edge 512. Alternatively, any combination of connections is possible. For example, the set of hinges 518 can be located only at the meeting point of the inner cylinder 502 and the first outer edge 512, or the set of hinges 518 can be located at the meeting point of the inner cylinder 502 and the first outer edge 512 on one of the doors 508 and 510, and at the meeting point of the outer cylinder 504 and the first outer edge 512 on the other of the doors 508 and 510.

[0061] Figure 8 yes Figure 7 A schematic diagram of an axial view of an exemplary cover 500, wherein the first cover door 508 and the second cover door 510 are in the open position.

[0062] As shown in the figure, when the set of hinges 518 is directly connected to the point where the inner cylinder 502 and the outer cylinder 504 meet the first outer edge 512, the inner cylinder 502 and the outer cylinder 504 of the first door 508 and the second door 510 can move independently of each other. Therefore, the inner cylinder 502 and the outer cylinder 504 of each of the first door 508 and the second door 510 can move to different degrees of opening or different positions. For example, as shown in the figure, the inner cylinder 502 of the first door 508 can be held in the closed position, while the outer cylinder 504 of the first door 510 can be at least partially opened. Furthermore, either the inner cylinder 502 or the outer cylinder 504 may include a portion defining a second outer edge 514. As shown in the figure, the outer cylinder 504 of the first door 508 and the inner cylinder 502 of the second door 510 may include second outer edges 514 extending radially outward from the outer cylinder 504 and the inner cylinder 502, respectively. Alternatively, either or both of the inner cylinder 502 or the outer cylinder 504 may include at least a portion of the second outer edge 514.

[0063] Figure 9 yes Figure 2 A schematic diagram of an axial view of an exemplary cover 600. The exemplary cover 600 is similar to covers 100, 200, 300, 400, and 500; therefore, in the 600 series, similar parts will be identified by similar numbers, and it should be understood that, unless otherwise stated, the description of similar parts of covers 100, 200, 300, 400, and 500 applies to cover 600.

[0064] As shown in the figure, cover 600 is in the closed position (e.g., similar to...). Figure 2 (as shown in the image) and is able to be in both the closed and open positions (e.g., similar to...). Figure 3 The cover 600 is movable between the positions shown in the diagram. The cover 600 includes a first cover 608 and a second cover 610, each cover including corresponding portions of an inner cylinder 602 and an outer cylinder 604. Both the first cover 608 and the second cover 610 extend circumferentially between a first outer edge 612 and a second outer edge 614, the first outer edge 612 being adjacent to the hanger 116 and radially opposite to the distal end 120 of the hanger 116, and the second outer edge 614 defining the circumferentially distal ends of the first cover 608 and the second cover 610 relative to the first outer edge 612. An internal passage 694 may be divided by the inner cylinder 602, the outer cylinder 604, the first outer edge 612, and the second outer edge 614, and is located within the first cover 608 and the second cover 610.

[0065] The cover 600 may include a set of hinges 618 adjacent to the hangar 116, which can operatively connect the first cover door 508 and the second cover door 510 to the cabin 40. The cover 600 is similar to the cover 500 in that it includes the set of hinges 518, which can be connected to the first cover door 608 and the second cover door 610 at radially different positions.

[0066] As shown, a second outer edge 614 may extend radially inward from the inner cylinder 602. As a non-limiting example, the second outer edge 614 may be defined as part of a non-ducted fan turbine engine 10. The second outer edge 614 may extend from at least a portion of the engine core 44 and between the circumferentially distal ends of the first hood 608 and the second hood 610 relative to the first outer edge 612. The second outer edge 614 may be further defined, but not limited to, extending from the engine core 44 and facing the circumferentially distal ends of the first hood 608 and the second hood 610 relative to the first outer edge 612, as a beam, wall, plate, or sheet. The second outer edge 614 may be further defined as the connection point between the first hood 608 and the second hood 610 and the engine core 44. For example, when in the illustrated position, at least a portion of the first hood 608 and the second hood 610 may be connected to the second outer edge 614 by any suitable connection method (e.g., but not limited to welding, adhesive, magnetism, fastening, bolting, or any combination thereof).

[0067] Figure 10 yes Figure 9 A schematic diagram of an axial view of an exemplary cover 600, wherein the first cover door 608 and the second cover door 610 are in the open position.

[0068] As shown in the figure, when the inner cylinder 602 or the outer cylinder 604 moves or is otherwise opened, the second outer edge 614 can remain in place. Figure 9 The location is shown. The shroud 600 is envisioned to allow selective access to the internal passage 694, the engine core 44, or other parts of the non-ducted fan turbine engine 10. For example, the internal passage 694, at least partially defined by the inner cylinder 602 and the outer cylinder 604 (… Figure 9 It can be accessed simply by moving a portion of the outer cylinder 604. Thus, the space between the inner cylinder 602 and the outer cylinder 604 is opened or otherwise exposed, thereby allowing access to the internal passage 694.

[0069] The benefits of this disclosure include hoods for turbine engines (particularly inline fan turbine engines) that increase the thrust of the turbine engine compared to conventional turbine engines. For example, a conventional turbine engine may include a hood that is contained within the nacelle and can be moved or removed from the nacelle to provide access to the engine core. However, a hood as described herein allows selective access to at least a portion of an inline fan turbine engine (e.g., the engine core, internal passageways, the space between the hood and the engine core, etc.) while also defining at least a portion of the internal passageway, as discussed herein, which may include a third airflow that increases the total thrust of the inline fan turbine engine. Specifically, the third airflow may flow from an inlet within the inline fan turbine engine through a portion of the internal passageway, at least partially defined by the inner and outer cylinders of the hood, and exit through an outlet to the outside of the inline fan turbine engine, where the third airflow may merge with at least a portion of a second airflow. Thus, the third airflow can contribute to the total thrust of the inline fan turbine engine, whereas a conventional hood does not contribute to the total thrust of the turbine engine at all. Furthermore, a third airflow can contribute to the thrust of a non-ducted fan turbine engine without the need for combustion or additional components (e.g., rotating or stationary blades). Specifically, the hood is configured such that the third airflow is directed only to the external surface of the non-ducted fan turbine engine through an internal passage at least partially defined by the hood. Generating this thrust requires no additional components. Therefore, including hoods as described herein not only allows selective access to portions of the turbine engine, but also increases the total thrust of the turbine engine, thereby increasing the overall efficiency of the turbine engine compared to a conventional turbine engine.

[0070] Further benefits of this disclosure include hoods for turbine engines (particularly ductless fan turbine engines) that allow easy, selective access to the engine core or other parts of the turbine engine, compared to conventional turbine engines. For example, a conventional turbine engine may include a set of hoods that can be attached to the nacelle by conventional coupling methods such as welding, fastening, or bonding. Therefore, the hoods need to be physically separated before access to the engine core. This process can ultimately be very time-consuming. However, the turbine engine described herein includes a set of hoods capable of moving between a closed and open position via a set of hinges, thus allowing selective access to at least a portion of the turbine engine. This set of hoods is not attached to the nacelle by conventional coupling methods. Therefore, the set of hoods can be easily moved between open and closed positions and secured in the closed position without requiring extensive couplings. This further reduces the time required to disassemble or move the hoods compared to the time required to disassemble or remove hoods from a conventional turbine engine.

[0071] Within the scope not yet described, different features and structures of each aspect may be combined with each other as needed. A feature not shown in all aspects is not to be interpreted as being forbidden, but rather for the sake of brevity. Thus, various features of different aspects may be mixed and matched as needed to form new examples, whether or not the new examples are explicitly described. Combinations or arrangements of features described herein are covered by this disclosure. In addition to the embodiments and constructions shown in the foregoing figures, this disclosure contemplates many other possible embodiments and constructions.

[0072] This written description uses examples to illustrate aspects of the disclosure described herein, including best practices, and also enables any person skilled in the art to practice aspects of the disclosure, including making and using any apparatus or system and performing any combination of methods. The patentable scope of aspects of this disclosure is defined by the claims, and may include other examples that would occur to a person skilled in the art. Such other examples are intended to fall within the scope of the claims if they have structural elements that are not indistinguishable from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims.

[0073] Further aspects of this disclosure are provided by the subject matter of the following clauses:

[0074] A non-ducted fan turbine engine includes: an engine core having a compressor section, a combustor section, and a turbine section arranged in series for axial flow and defining a first airflow axially through the engine core; a nacelle surrounding at least a portion of the engine core and having an outer surface and an internal passage, the outer surface defining a second airflow along the outer surface, the internal passage being located between the outer surface and the engine core and defining a third airflow; a plurality of rotatable blades extending radially beyond the outer surface of the nacelle and rotatably driven by the engine core; and a hood located within the nacelle and movable between an open position and a closed position to provide selective access to at least a portion of the engine core, wherein the hood has an interior forming at least a portion of the internal passage.

[0075] In a non-ducted fan turbine engine according to any of the foregoing clauses, the hood includes an inner cylinder and an outer cylinder, the outer cylinder being radially outwardly positioned relative to the engine core from the inner cylinder, and the space between the inner cylinder and the outer cylinder defining at least a portion of the internal passage.

[0076] The non-ducted fan turbine engine according to any of the foregoing clauses, wherein the nacelle includes hinges for mounting the hood to the nacelle.

[0077] The non-ducted fan turbine engine according to any of the foregoing clauses, wherein the nacelle further includes an engine mount, and the hinge is positioned adjacent to the engine mount.

[0078] The non-ducted fan turbine engine according to any of the foregoing clauses, wherein the hood comprises a pair of hoods, wherein the nacelle has hinges for each hood, each hinge being positioned adjacent to the engine mount.

[0079] According to any of the preceding clauses, the non-ducted fan turbine engine, wherein the pair of doors are gull-wing doors, each door having a hinge edge and an outer edge, the hinge edge being coupled to a corresponding hinge such that at least one of the inner or outer cylinders of each gull-wing door is movable between an open position and a closed position, and the outer edges facing each other.

[0080] The non-ducted fan turbine engine according to any of the foregoing clauses, wherein the hood comprises a pair of gull-wing doors.

[0081] The non-ducted fan turbine engine according to any of the foregoing clauses, wherein each of the pair of gull-wing doors extends 180 degrees around the engine core.

[0082] A non-ducted fan turbine engine according to any of the foregoing clauses, wherein the internal passage forms a ring around the engine core.

[0083] In any of the foregoing clauses, the non-pipeline fan turbine engine wherein the ring is discontinuous.

[0084] The non-ducted fan turbine engine according to any of the foregoing clauses, wherein the total extension around the engine core is at least 240 degrees.

[0085] The non-pipeline fan turbine engine according to any of the foregoing clauses, wherein the plurality of blades are axially upstream of the combustor section.

[0086] The non-pipeline fan turbine engine according to any of the foregoing clauses, wherein the plurality of blades are axially downstream of the combustor section.

[0087] The non-pipeline fan turbine engine according to any of the foregoing clauses further includes a gearbox that connects the plurality of blades to the engine core.

[0088] The non-ducted fan turbine engine according to any of the foregoing clauses further includes a plurality of stationary blades extending radially beyond the outer surface of the nacelle and downstream of the plurality of rotatable blades.

[0089] The non-ducted fan turbine engine according to any of the foregoing clauses, wherein the hood extends 180 degrees across the engine core.

[0090] A non-ducted fan turbine engine includes: an engine core having a compressor section, a combustor section, and a turbine section arranged in series for axial flow and defining a first airflow axially through the engine core; a nacelle surrounding at least a portion of the engine core and having an outer surface and an internal passage, the outer surface defining a second airflow along the outer surface, the internal passage being located between the outer surface and the engine core and defining a third airflow; a plurality of rotatable blades extending radially beyond the outer surface of the nacelle and rotatably driven by the engine core; and a pair of gull-wing doors located in the nacelle and movable between an open position and a closed position to provide selective access to at least a portion of the engine core, wherein each of the pair of gull-wing doors has an interior forming at least a portion of the internal passage.

[0091] The non-ducted fan turbine engine according to any of the foregoing clauses, wherein each of the pair of gull-wing doors includes an inner cylinder and an outer cylinder, the outer cylinder being radially outwardly positioned relative to the engine core from the inner cylinder, the space between the inner cylinder and the outer cylinder defining at least a portion of the internal passage, the non-ducted fan turbine engine further including: an engine mount; and a hinge for each gull-wing door, the hinge being adjacent to the engine mount and mounting the pair of gull-wing doors to the nacelle; wherein the pair of gull-wing doors includes a hinge edge and an outer edge, the hinge edge being coupled to a corresponding hinge such that at least one of the inner cylinder or the outer cylinder of each gull-wing door is movable between an open position and a closed position, and the outer edges facing each other.

[0092] A non-ducted fan turbine engine according to any of the foregoing clauses, wherein the internal passage forms a ring around the engine core, the ring around the engine core extending a total of at least 240 degrees.

[0093] The non-ducted fan turbine engine according to any of the foregoing clauses, wherein the ring is discontinuous and symmetrical about a plane intersecting the engine support and extending in the axial direction.

Claims

1. A non-tubulated fan turbine engine characterized in that, having an engine centerline and comprising: an engine core having a compressor section, a combustor section, and a turbine section arranged in serial axial flow, and defining a first airflow axially through the engine core; a nacelle surrounding at least a portion of the engine core and having an exterior surface defining a second airflow along the exterior surface, and an interior passage between the exterior surface and the engine core defining a third airflow; a plurality of rotatable fan blades extending radially beyond the exterior of the surface of the nacelle and rotationally driven by the engine core; and a door comprising a first door and a second door, each door extending between a first outer edge and a second outer edge, the door located in the nacelle and movable between an open position and a closed position to provide selective access to at least a portion of the engine core, wherein the door has an interior forming at least a portion of the interior passage; wherein the second outer edge of the first door opposes the second outer edge of the second door when the first and second doors are in the closed position, and the first and second doors are asymmetric about a vertical plane extending along the engine centerline and intersecting the second outer edges of the first and second doors when the first and second doors are in the closed position.

2. The un-tubulated fan turbine engine of claim 1, wherein, wherein, the door comprises an inner barrel and an outer barrel, the outer barrel positioned radially outward from the inner barrel relative to the engine core, a space between the inner barrel and the outer barrel defining at least a portion of the interior passage.

3. The un-tubulated fan turbine engine of claim 2, wherein, wherein, the nacelle comprises a hinge mounting the door to the nacelle.

4. The un-tubulated fan turbine engine of claim 3, wherein, wherein, the nacelle further comprises an engine support, and the hinge is positioned adjacent to the engine support.

5. The un-tubulated fan turbine engine of claim 4, wherein, wherein, the nacelle comprises a hinge for the first door and a hinge for the second door, each hinge positioned adjacent to the engine support.

6. The un-tubulated fan turbine engine of claim 1, wherein, wherein, the interior passage extends discontinuously around the engine core.

7. The un-tubulated fan turbine engine of claim 6, wherein, wherein, the interior passage extends at least 240 degrees in total around the engine core.

8. The un-tubulated fan turbine engine of any one of claims 1-5, wherein, wherein, the plurality of rotatable fan blades are axially upstream of the combustor section.

9. The un-tubulated fan turbine engine of any one of claims 1-5, wherein, wherein, the plurality of rotatable fan blades are axially downstream of the combustor section.

10. The un-tubulated fan turbine engine of any one of claims 1-5, wherein, further comprising a gearbox coupling the plurality of rotatable fan blades to the engine core.

11. The un-tubulated fan turbine engine of any one of claims 1-5, wherein, further comprising a plurality of stationary fan vanes extending radially beyond the exterior surface of the nacelle and downstream of the plurality of rotatable fan blades.

12. The un-tubulated fan turbine engine of any one of claims 1-5, wherein, wherein, the door extends across 180 degrees of the engine core.

13. A non-ducted fan turbine engine characterized by, having an engine centerline and comprising: an engine core having a compressor section, a combustor section, and a turbine section arranged in serial axial flow, and defining a first airflow axially through the engine core; a nacelle enclosing at least a portion of the engine core and having an exterior surface and an interior passage, the exterior surface defining a second airflow along the exterior surface, the interior passage being located between the exterior surface and the engine core and defining a third airflow; a plurality of rotatable fan blades extending radially beyond the exterior of the surface of the nacelle and rotationally driven by the engine core; and a pair of gull-wing doors including a first gull-wing door and a second gull-wing door, each gull-wing door extending between a first outer edge and a second outer edge, the pair of gull-wing doors being located in the nacelle and movable between an open position and a closed position to provide selective access to at least a portion of the engine core, wherein the pair of gull-wing doors each have an interior forming at least a portion of the interior passage; wherein, when the pair of gull-wing doors are in the closed position, the second outer edge of a first gull-wing door of the pair of gull-wing doors opposes the second outer edge of a second gull-wing door of the pair of gull-wing doors, and the pair of gull-wing doors are asymmetric about a vertical plane extending along the engine centerline and intersecting the second outer edges of the first and second gull-wing doors when the pair of gull-wing doors are in the closed position.

14. The un-tubulated fan turbine engine of claim 13, wherein, wherein, each door of the pair of gull-wing doors includes an inner barrel and an outer barrel, the outer barrel being positioned radially outward from the inner barrel relative to the engine core, a space between the inner barrel and the outer barrel defining at least a portion of the interior passage, the unducted fan turbine engine further comprising: an engine support; and a hinge for each gull-wing door, the hinge being adjacent to the engine support and mounting the pair of gull-wing doors to the nacelle; wherein, the pair of gull-wing doors include a hinge edge coupled to a corresponding hinge such that at least one of the inner barrel or the outer barrel of each gull-wing door is independently movable relative to one another.

15. The un-tubulated fan turbine engine of any one of claims 13-14, wherein, wherein, the interior passage forms a ring around the engine core, the ring extending at least 240 degrees in total around the engine core.

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