Propulsion engine and fairing

Abstract

A propulsion system for an aircraft, the propulsion system including a core engine connected to a front frame and a turbine frame assembly, and a rear frame assembly connected to the core engine behind the turbine frame assembly through a turbine housing. A core cowl surrounds the core engine, wherein the core cowl is connected to the front frame. A plurality of cowl mounting links selectively load the core cowl onto the rear frame assembly and the turbine frame assembly, wherein the plurality of cowl mounting links are all loaded by deflection of the core engine.

Description

[0001] Priority Information

[0002] This application claims priority to Indian Patent Application No. 202011045065, filed on October 16, 2020. Technical Field

[0003] The present subject matter generally relates to a propulsion system nacelle and its mounting structure. Background Art

[0004] A propulsion engine, such as a turbofan engine, includes a nacelle that surrounds a core engine or gas generator of the propulsion engine. Conventional nacelle mounting structures include links at the front fan and rear plane of the turbofan engine. Certain nacelle mounting systems, such as cantilever nacelle mounts, can cause bending moments that would otherwise distort engine clearances without being transmitted through the core engine.

[0005] However, cantilever nacelle mounting systems are vulnerable to excessive engine deflections after extreme aircraft maneuvers that may be caused by foreign object ingestion, bird strikes, blade shedding, or other failure modes. Excessive engine deflections can result in excessive loads at the nacelle mounting locations, such as at the front mount, flange, or other attachment points. After extreme engine or aircraft events, the excessive loads may manifest as engine oscillations. However, such additional strengthening components significantly increase the engine weight, which has an adverse effect on engine and aircraft fuel consumption.

[0006] Accordingly, there is a desire for an improved propulsion engine nacelle mounting system that provides improved clearance deformation characteristics and reduces excessive deflections. Summary of the Invention

[0007] Aspects and advantages of the invention will be set forth in part in the following description, or may be apparent from the description, or may be learned through practice of the invention.

[0008] Aspects of the present disclosure relate to a propulsion system for an aircraft that includes a core engine connected to a front frame and a turbine frame assembly, and a rear frame assembly connected to the core engine behind the turbine frame assembly via a turbine housing. A core nacelle surrounds the core engine, wherein the core nacelle is connected to the front frame. A plurality of nacelle mounting links selectively load the core nacelle to the rear frame assembly and the turbine frame assembly, wherein the plurality of nacelle mounting links are each loaded by deflection of the core engine.

[0009] A propulsion system for an aircraft, the propulsion system defining a nominal centerline axis, characterized in that the propulsion system comprises: a fan assembly including a front frame; a core engine connected to the front frame, wherein the core engine includes a turbine frame assembly, and wherein the core engine defines an engine centerline axis, and further wherein, during normal propulsion system operation, the engine centerline axis is substantially coaxial with the nominal centerline axis, and wherein when the core engine is deflected, the engine centerline axis forms an acute angle with the nominal centerline axis; a rear frame assembly connected to the core engine behind the turbine frame assembly through a turbine housing; a core cowl surrounding the core engine, wherein the core cowl is connected to the front frame; and a plurality of cowl mounting links selectively loading the core cowl to the rear frame assembly and the turbine frame assembly, wherein the plurality of cowl mounting links are each loaded by deflection of the core engine; wherein the plurality of cowl mounting links include a first cowl mounting link coupled between the core cowl and the rear frame assembly, wherein the plurality of cowl mounting links include a second cowl mounting link coupled between the core cowl and the turbine frame assembly; wherein the second cowl mounting link is axially located in front of the first cowl mounting link, wherein the rear frame assembly and the turbine frame assembly include a plurality of members extending radially towards the core cowl, wherein the plurality of members are configured to be selectively loaded by the plurality of cowl mounting links; wherein the first cowl mounting link selectively loads the core cowl to the rear frame assembly, and wherein the second cowl mounting link selectively loads the core cowl to the turbine frame assembly.

[0010] These and other features, aspects, and advantages of the present invention will be better understood with reference to the following description and the appended claims. The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and, together with the description, serve to explain the principles of the invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] In the specification with reference to the accompanying drawings, a complete and workable disclosure of the invention for a person of ordinary skill in the art is set forth, including its best mode, wherein:

[0012] Figure 1 is a perspective view of an exemplary aircraft in accordance with aspects of the present disclosure;

[0013] Figure 2A cross-sectional view of an exemplary embodiment of a portion of an aircraft including a propulsion system in accordance with aspects of the present disclosure;

[0014] Figure 3 A perspective view of an exemplary embodiment of a propulsion system deflected at a pylon;

[0015] Figure 4 A schematic view of a propulsion system including a nacelle mounting link in accordance with aspects of the present disclosure;

[0016] Figures 5 - 9 Depicts Figures 2 - 4 An embodiment of a nacelle mounting link of a propulsion system;

[0017] Figure 10 Depicts Figures 2 - 4 An embodiment of a nacelle mounting link of a propulsion system; and

[0018] Figure 11 Depicts Figure 10 An embodiment of a propulsion system.

[0019] Reference numerals repeated in this specification and the drawings are intended to represent the same or similar features or elements of the present invention. Detailed Description

[0020] Reference will now be made in detail to embodiments of the present invention, one or more examples of which are illustrated in the drawings. Each example is provided for the purpose of explaining the present invention and not as a limitation thereof. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made to the present invention without departing from the scope or spirit thereof. For example, features shown or described as part of one embodiment can be used with another embodiment to yield yet another embodiment. Accordingly, the present invention is intended to cover such modifications and variations that fall within the scope of the appended claims and their equivalents.

[0021] As used herein, the terms “first,” “second,” and “third” may be used interchangeably to distinguish one component from another and are not intended to denote the position or importance of the individual components.

[0022] The terms “upstream” and “downstream” refer to the relative direction with respect to the flow of fluid in a fluid path. For example, “upstream” refers to the direction from which the fluid flows and “downstream” refers to the direction towards which the fluid flows.

[0023] Embodiments of a propulsion system mounting system including a cantilever core construction with a deflection-limiting aft mounting structure are depicted and described herein. Embodiments of the propulsion systems and aircraft provided herein may allow for the benefits associated with a cantilever core construction. Benefits include reducing the transfer of bending moments and other loads through the aft mount during normal operation, such as reducing deformation, asymmetry, and undesired clearances between the rotating structure of the propulsion system and the surrounding static housing of the propulsion system. Additionally, the aft mounting structures depicted and described herein limit excessive deflection, oscillation, swaying, or other movement of the core engine relative to the nominal centerline axis after extreme maneuvers. The aft mounting structures provided herein allow for load sharing between the aft and forward mounts after extreme maneuvers while remaining cantilevered or substantially unloaded at the aft mount during normal operation.

[0024] Now referring to the drawings, in Figure 1 an exemplary embodiment of an aircraft 100 in accordance with aspects of the present disclosure is provided. The aircraft 100 includes an aircraft structure or airframe 105. The airframe 105 includes a fuselage 110 to which wings 120 and a tail 130 are attached. A propulsion system 10 in accordance with aspects of the present disclosure is attached to one or more portions of the airframe. In some cases, the propulsion system 10 is attached to the rear of the fuselage 110. In some other cases, the propulsion system 10 is attached below, above, or through a portion of the wings 120 and / or the tail 130.

[0025] In various embodiments, the propulsion system 10 is attached to the airframe 105 via pylons or other mounting structures. In still other embodiments, the propulsion system 10 is housed within the airframe, as may be illustrated in certain supersonic military or commercial aircraft.

[0026] Now referring to Figure 2 an embodiment of the propulsion system 10 is provided. The propulsion system 10 may generally be configured as a turbine, such as a gas turbine engine including a compressor section 42, a heat addition or combustion section 44, and a turbine section 46 in a serial flow arrangement. The core engine 40 includes one or more rotor assemblies, and one or more rotor assemblies include one or more shafts coupling respective compressors and turbines. In certain embodiments, the core engine 40 includes a high-speed or first shaft 242 operably coupled to a high-speed compressor 141 and a high-speed turbine 146. In certain embodiments, the propulsion system 10 may include a low-speed or second shaft 244 operably coupled to a low-speed compressor 143 and a low-speed turbine 246.

[0027] Certain embodiments of the propulsion system 10 are configured to include a turbofan or turbojet engine operably connected to a fan assembly 14 of a core engine 40. The core engine 40 includes a core housing 240 surrounding a rotating element of the core engine 40. In various embodiments, the core housing 240 extends from a front frame 12 to a turbine frame assembly 24. In certain embodiments, the core housing 240 includes a plurality of segments surrounding at least a portion of a compressor section 42 and a heat addition or combustion section 44. A core cowl 140 surrounds the core engine 40. Various other embodiments may define the propulsion system 10 as an open rotor engine, a propfan engine, or a Brayton cycle machine.

[0028] The front frame 12 connects the core engine 40 and the fan assembly 14 to the airframe 105. In particular, the core cowl 140 is connected to the front frame 12. In various embodiments, the front frame 12 is a fan hub frame (FHF). In certain embodiments, a nacelle 16 surrounds the core engine 40 and the core cowl 140 and is attached to the front frame 12. In one embodiment, the propulsion system 10 is configured as an open rotor engine or a ducted fan engine arrangement. In another embodiment, the nacelle 16 or portions thereof surround a fan rotor assembly 18 of the fan assembly 14 or portions thereof, such as in a turbofan engine configuration.

[0029] In various embodiments, the front frame 12 generally includes a front housing that typically includes bearing assemblies, dampers, and lubricant scavenge and supply ducts. The front frame 12 may further enclose or support one or more additional rotating fan stages or superchargers. In various embodiments, the front frame 12 is a fan hub frame, a compressor intermediate case, or other static structure surrounding at least a portion of the compressor section 42 or positioned at least partially in front of the compressor section.

[0030] The core engine 40 includes a turbine frame assembly 24 positioned at a turbine section 46. In certain embodiments, the turbine frame assembly 24 is positioned between a high speed or first turbine 146 and a low speed or second turbine 246 (i.e., lower in speed relative to the first turbine 146). The turbine frame assembly 24 generally may include a static housing that includes bearing assemblies, dampers, and lubricant scavenge and supply ducts. In various embodiments, the turbine frame assembly 24 defines a turbine center frame (TCF), an intermediate turbine frame, or other static structure surrounding at least a portion of the turbine section 46. The turbine frame assembly 24 further includes a turbine housing 124 surrounding the second turbine 246 and connected to a rear frame assembly 22. The rear frame assembly 22 is positioned axially rearward along the turbine frame assembly 24 relative to the direction of fluid flow through the aircraft 100. In various embodiments, the rear frame assembly 22 is a turbine rear frame (TRF) or a nozzle assembly 50 of the propulsion system 10.

[0031] The frame 105 is connected to the propulsion system 10 at the front frame 12. In certain embodiments, the propulsion system 10 is connected to the frame via the front engine mounting link 32. In some embodiments, the propulsion system 10 is mounted from the frame 105 generally and substantially in a cantilever arrangement via the front engine mounting link 32.

[0032] In certain embodiments, the rear frame assembly 22 is selectively connected or selectively loaded to the frame 105 via the rear engine mounting link 34. The rear engine mounting link 34 extends between the rear frame assembly 22 and the frame. The rear engine mounting link 34 is selectively loaded by the deflection of the core engine 40.

[0033] Reference Figures 1 - 4 , the nominal centerline axis 101 defines the reference centerline of the propulsion system 10 when attached to the frame 105 under static conditions (e.g., when the propulsion system 10 is not operating). The engine centerline axis 11 defines the reference centerline of the propulsion system 10 during operation of the propulsion system 10. The operation of the propulsion system 10 includes but is not limited to dry and wet drive, ignition, idle, takeoff or maximum power, climb, cruise, approach, landing, and reverse thrust. During normal operation of the propulsion system 10 and the aircraft 100, the propulsion system may be deflected relative to the nominal position of the propulsion system. For example, during non-operation or certain operating conditions, the nominal centerline axis 101 and the engine centerline axis 11 may be substantially coaxial or collinear. However, under certain high-load conditions, such as after ingesting foreign object debris, bird strike or ingestion, fan blade detachment, ice ingestion, or other adverse operating conditions, the propulsion system 10 may be deflected excessively such that the angle 103 between the nominal centerline axis 101 and the engine centerline axis 11 reaches or exceeds an angle threshold. The angle threshold may generally define the angle by which the core engine 40 is deflected relative to the nominal centerline axis 101 such that the core engine 40 contacts the frame, e.g., around the housing.

[0034] To provide reduced bending of the core housing 240, a plurality of cowl mounting links 300 selectively load the core cowl 140 to the rear frame assembly 22 and the turbine frame assembly 24. Each of the plurality of cowl mounting links 300 is loaded by the deflection of the core engine 40. In various embodiments, both the rear frame assembly 22 and the turbine frame assembly 24 include respective cowl mounting links 300 selectively connected to the core cowl 140. In certain embodiments, for example Figures 5 - 11As depicted, each of the plurality of nacelle mounting links 300 includes a plurality of members 310 extending toward the core nacelle 140. The plurality of members 310 are configured to be selectively loaded by the plurality of nacelle mounting links 300. Additionally or alternatively, the plurality of nacelle mounting links 300 selectively load the core nacelle 140 onto the aft frame assembly 22 and the turbine frame assembly 24, alleviating adverse operating conditions associated with rotor bow (e.g., at the first shaft 242 and / or the second shaft 244).

[0035] In certain embodiments, such as those depicted in Figures 5 - 9 each of the plurality of nacelle mounting links 300 includes a coupler 320 configured to be selectively loaded onto a corresponding mounting member 310. In various embodiments, the coupler 320 is positioned adjacent to or in close proximity to the corresponding mounting member 310. In one embodiment, the coupler 320 at least partially surrounds the corresponding member among the plurality of mounting members 310. When the engine centerline axis 11 is substantially coaxial with the nominal centerline axis, the coupler 320 and the member 310 are unloaded relative to each other. When the engine centerline axis 11 is deflected at an acute angle 103 ( Figure 3 with respect to the nominal centerline axis 101 ( Figure 3 ), the coupler 320 and the member 310 are loaded onto each other.

[0036] Referring to Figures 5 - 6 , the plurality of nacelle mounting links 300 may include a front mounting link 300a that selectively loads the core nacelle 140 onto the turbine frame assembly 24 ( Figure 5 ) and a rear mounting link 300b that selectively loads the core nacelle 140 onto the aft frame assembly 22 ( Figure 6 ). It should be understood that the embodiments further depicted and described with respect to Figures 7 - 11 may be applied as the front mounting link 300a, the rear mounting link 300b, or a combination thereof.

[0037] Returning to Figures 5 - 6 , the plurality of members 310 include a front member 310a located at the turbine frame assembly 24 and a rear member 310b located at the aft frame assembly 22. The corresponding front coupler 320a and rear coupler 320b are positioned close to the corresponding front member 310a and rear member 310b, respectively. In one embodiment, such as those depicted in Figures 5 - 6 the corresponding couplers 320a, 320b surround the corresponding members 310a, 310b extending toward the corresponding couplers 320a, 320b. In various embodiments, the coupler 320 defines a fork-shaped member extending circumferentially adjacent to the corresponding member 310.

[0038] Referring to Figures 7 - 9 , the provided embodiments are configured to be associated with those with respect to Figures 5 - 6The provided embodiments are substantially similar. Figure 8 is Figure 7 an axial side view of the view provided in. Additionally, Figure 8 is depicted at the front mounting link 300a depicted in Figure 5 . However, it should be understood that a similar arrangement can be applied to Figure 6 the rear mounting link 300b shown in. In Figures 7 - 8 , a plurality of fairing mounting links 300 include joint members 315 that connect corresponding connectors 320 at the core fairing 140 to corresponding members 310. The connectors 320 can be axially positioned in front of or behind the corresponding members 310 and are connected together via the joint members 315, as Figure 8 shown. In Figure 9 , the connectors 320 can be positioned tangentially or circumferentially adjacent to the corresponding members 310. Regarding Figures 5 - 9 the embodiments depicted and described, they can particularly allow deformation (e.g., ovalization, out-of-roundness, eccentricity relative to the centerline axis 11) of the turbine static structure 23 (e.g., turbine frame assembly 24, rear frame assembly 22). In various embodiments, the joint members 315 can provide loads in the axial, radial, and tangential directions.

[0039] Now referring to Figures 10 - 11 , embodiments of mounting links 300 that define springs are provided. Figures 10 - 11 The embodiments provided in can be constructed such as those described regarding Figures 1 - 9 . Figure 11 depicts the core fairing 140 at Figure 10 in an open position. Additionally, the mounting links 300 that define springs can be positioned at the front fairing mount 300a, rear fairing mount 300b, or a combination thereof, with one or more embodiments depicted and described regarding Figures 5 - 9 . The mounting links 300 can define leaf springs that extend to and connect to the turbine static structure 23 (e.g., Figures 2 - 4 the turbine frame assembly 24 or rear frame assembly 22 depicted in). The mounting links 300 include one or more portions that extend at least partially tangentially and radially to the turbine static structure.

[0040] Still referring to Figures 10 - 11, the hinge 325 can be positioned at the core cowl 140 to allow the core cowl 140 to be divided into at least two parts 140a, 140b. The turbine static structure 23 may also include a member 310 that extends tangentially and radially toward the core cowl 140, for example to allow articulated movement of the core cowl parts 140a, 140b. The mounting link 300 that defines the spring can allow stiffness during bending of the turbine static structure. In various embodiments, the mounting link 300 may be circumferentially arranged symmetrically or asymmetrically about the axis of symmetry of the propulsion system 10.

[0041] The embodiments of the propulsion system 10 and the aircraft 100 depicted and described herein may reduce undesired bending at the core housing 240. Reducing the undesired bending at the core housing 240 may allow modal closure of the out-of-phase rotor bow (e.g., at the first axis 242 or the second axis 244). Reducing the undesired bending at the core housing 240 may improve engine operation during bow rotor start conditions (i.e., during start-up or operation of one or both of the axes 242, 244 that define the eccentricity relative to the engine centerline axis 11). Such improvement may reduce the time period used to attenuate the rotor bow during windmilling or propulsion system drive. Additionally or alternatively, reducing the undesired bending at the core housing 240 may reduce the Alford force, reduce the risk associated with undesired rotor or blade and surrounding housing friction, and improve the stability of the propulsion system.

[0042] This written description uses examples to disclose the invention, including the best mode, and also enables those skilled in the art to practice the invention, including making and using any device or system and performing any incorporated method. The patentable scope of the invention is defined by the claims and may include other examples that occur to those skilled in the art. If these other examples include structural elements that are not different 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, then these other examples are intended to fall within the scope of the claims.

[0043] A further aspect of the invention is provided by the subject matter of the following articles:

[0044] 1. A propulsion system for an aircraft, the propulsion system comprising: a core engine connected to a front frame and a turbine frame assembly; and a rear frame assembly connected to the core engine behind the turbine frame assembly through a turbine housing. A core cowl surrounds the core engine, wherein the core cowl is connected to the front frame. A plurality of cowl mounting links selectively load the core cowl onto the rear frame assembly and the turbine frame assembly, wherein the plurality of cowl mounting links are each loaded by deflection of the core engine.

[0045] 2. The propulsion system according to any item herein, wherein the aft frame assembly and the turbine frame assembly include a plurality of members extending in a radial direction toward the core cowl, and wherein the plurality of members are configured to be selectively loaded by the plurality of cowl mounting links.

[0046] 3. The propulsion system according to any item herein, wherein the plurality of cowl mounting links include a coupler configured to at least partially surround a respective one of the plurality of members, and wherein, when the engine centerline axis is substantially coaxial with the nominal centerline axis, the coupler and the member are unloaded relative to each other.

[0047] 4. The propulsion system according to any item herein, wherein when the engine centerline axis is deflected at the acute angle relative to the nominal centerline axis, the coupler and the member are loaded onto each other.

[0048] 5. The propulsion system according to any item herein, wherein the plurality of cowl mounting links include a coupler that at least partially surrounds a respective one of the plurality of members, wherein the member extends toward the core cowl, and wherein the coupler extends toward the member, and wherein when the engine centerline axis is substantially coaxial with the nominal centerline axis, the coupler and the member are unloaded relative to each other.

[0049] 6. The propulsion system according to any item herein, wherein the aft frame assembly includes a first one of the plurality of members extending in a radial direction toward the nacelle, and wherein a first mounting link of the plurality of cowl mounting links includes a first coupler extending in the radial direction toward the core engine, and wherein the turbine housing includes a second one of the plurality of members extending toward the core cowl, and wherein a second mounting link of the plurality of cowl mounting links includes a second coupler extending in the radial direction toward the core engine.

[0050] 7. The propulsion system according to any item herein, wherein at least a portion of the first coupler is circumferentially positioned adjacent the respective first member.

[0051] 8. The propulsion system according to any item herein, wherein at least a portion of the second coupler is circumferentially positioned adjacent the respective second member.

[0052] 9. The propulsion system according to any item herein, wherein the first coupler, the second coupler, or both define a fork, the fork including a portion that circumferentially extends adjacent the respective first member or second member.

[0053] 10. The propulsion system according to any item herein, wherein the joint member connects the corresponding mounting link at the core fairing to the corresponding member.

[0054] 11. The propulsion system according to any item herein, wherein a first joint member connects a first member of the plurality of members to a first coupler of the plurality of fairing mounting links, and wherein a second joint member connects a second member of the plurality of members to a second coupler of the plurality of fairing mounting links.

[0055] 12. The propulsion system according to any item herein, wherein the plurality of fairing mounting links are arranged circumferentially at the core fairing.

[0056] 13. The propulsion system according to any item herein, wherein the plurality of fairing mounting links include a first spring coupled to the core fairing and the rear frame assembly, and wherein the plurality of fairing mounting links include a second spring coupled to the core fairing and the turbine frame assembly.

[0057] 14. The propulsion system according to any item herein, the engine includes a nacelle surrounding the core fairing, wherein the nacelle is connected to the front frame.

[0058] 15. The propulsion system according to any item herein, wherein the nacelle is connected to the core engine by a rear nacelle mount.

[0059] 16. The propulsion system according to any item herein, wherein the rear nacelle mount connects the nacelle to the core engine at one or both of the turbine frame assembly or the rear frame assembly.

[0060] 17. A gas turbine engine, the engine defining a nominal centerline axis, the propulsion system comprising: a fan assembly including a front frame; a core engine connected to the front frame, wherein the core engine includes a turbine frame assembly, and wherein the core engine defines an engine centerline axis, and further wherein during normal propulsion system operation, the engine centerline axis is substantially coaxial with the nominal centerline axis, and wherein when the core engine is deflected, the engine centerline axis is at an acute angle to the nominal centerline axis; a rear frame assembly, wherein the turbine frame assembly includes a turbine casing, the rear frame assembly being connected to the core engine at the turbine casing behind the turbine frame assembly, and wherein the rear frame includes a nozzle assembly; a core cowl surrounding the core engine, wherein the core cowl is connected to the front frame; and a plurality of cowl mounting links selectively loading the core cowl to the rear frame assembly and the turbine frame assembly, wherein the plurality of cowl mounting links are each loaded by deflection of the core engine.

[0061] 18. The gas turbine engine according to any item herein, wherein the rear frame assembly and the turbine frame assembly each include a plurality of members extending towards the core cowl, and wherein the plurality of cowl mounting links include couplings, and wherein the plurality of members are configured to be selectively loaded by the plurality of cowl mounting links, and further wherein when the engine centerline axis is substantially coaxial with the nominal centerline axis, the couplings and the members are unloaded relative to each other, and wherein when the engine centerline axis is deflected at the acute angle relative to the nominal centerline axis, the couplings and the members are loaded onto each other.

[0062] 19. The gas turbine engine according to any item herein, wherein joint members connect the respective mounting links at the core cowl to the respective members.

[0063] 20. The gas turbine engine according to any item herein, the engine including a nacelle surrounding the core cowl, wherein the nacelle is connected to the front frame, and wherein the nacelle is connected to the core engine by a rear nacelle mount, and further wherein the rear nacelle mount connects the nacelle to the core engine at one or both of the turbine frame assembly or the rear frame assembly.

[0064] 21. The gas turbine engine according to any item herein, including a propulsion system according to any item herein.

[0065] 22. A propulsion system according to any item herein, including a gas turbine engine according to any item herein.

[0066] 23. An aircraft comprising a gas turbine engine according to any item herein.

[0067] 24. An aircraft comprising a propulsion system according to any item herein.

[0068] 25. An aircraft according to any item herein, wherein the propulsion system or the gas turbine engine is coupled to the fuselage, wing or tail of the aircraft.

Claims

1. A propulsion system for an aircraft, the propulsion system defining a nominal centerline axis, characterized in that, the propulsion system comprises: a fan assembly including a front frame; a core engine connected to the front frame, wherein the core engine includes a turbine frame assembly, and wherein the core engine defines an engine centerline axis, and further wherein, during normal propulsion system operation, the engine centerline axis is substantially coaxial with the nominal centerline axis, and wherein when the core engine is deflected, the engine centerline axis forms an acute angle with the nominal centerline axis; a rear frame assembly connected to the core engine behind the turbine frame assembly by a turbine housing; a core nacelle surrounding the core engine, wherein the core nacelle is connected to the front frame; and a plurality of nacelle mounting links selectively loading the core nacelle to the rear frame assembly and the turbine frame assembly, wherein the plurality of nacelle mounting links are each loaded by deflection of the core engine; wherein the plurality of nacelle mounting links include a first nacelle mounting link coupled between the core nacelle and the rear frame assembly, wherein the plurality of nacelle mounting links include a second nacelle mounting link coupled between the core nacelle and the turbine frame assembly; wherein the second nacelle mounting link is axially located in front of the first nacelle mounting link, wherein the rear frame assembly and the turbine frame assembly include a plurality of members extending radially towards the core nacelle, wherein the plurality of members are configured to be selectively loaded by the plurality of nacelle mounting links; wherein the first nacelle mounting link selectively loads the core nacelle to the rear frame assembly, and wherein the second nacelle mounting link selectively loads the core nacelle to the turbine frame assembly.

2. The propulsion system according to claim 1, characterized in that, the rear frame assembly is selectively connected or selectively loaded to the airframe by a rear engine mounting link; the rear engine mounting link is selectively loaded by deflection of the core engine.

3. The propulsion system according to claim 1, characterized in that, wherein the plurality of nacelle mounting links include a coupler configured to at least partially surround a respective one of the plurality of members, and wherein, when the engine centerline axis is substantially coaxial with the nominal centerline axis, the coupler and the member are unloaded relative to each other.

4. The propulsion system according to claim 3, characterized in that, wherein when the engine centerline axis is deflected at the acute angle relative to the nominal centerline axis, the coupler and the member are loaded onto each other.

5. The propulsion system according to claim 1, characterized in that, The plurality of fairing mounting links include a coupler that at least partially surrounds a respective one of the plurality of members, wherein the members extend toward the core fairing, and wherein the coupler extends toward the member, and wherein the coupler and the member are unloaded relative to each other when the engine centerline axis is substantially coaxial with the nominal centerline axis.

6. The propulsion system according to claim 5, wherein, wherein the aft frame assembly includes a first one of the plurality of members that extends toward the nacelle along a radial direction, and wherein a first mounting link of the plurality of fairing mounting links includes a first coupler that extends toward the core engine along the radial direction, and wherein the turbine housing includes a second one of the plurality of members that extends toward the core fairing, and wherein a second mounting link of the plurality of fairing mounting links includes a second coupler that extends toward the core engine along the radial direction.

7. The propulsion system according to claim 6, wherein, at least a portion of the first coupler is circumferentially positioned adjacent the respective first member.

8. The propulsion system according to claim 6, wherein, at least a portion of the second coupler is circumferentially positioned adjacent the respective second member.

9. The propulsion system according to claim 6, wherein, the first coupler, the second coupler, or both define a fork, the fork including a portion that extends circumferentially adjacent the respective first member or second member.

10. The propulsion system according to claim 1, wherein, a joint member connects a respective mounting link at the core fairing to the respective member.

11. The propulsion system according to claim 1, wherein, a first joint member connects a first one of the plurality of members to the first coupler of the plurality of fairing mounting links, and wherein a second joint member connects a second one of the plurality of members to the second coupler of the plurality of fairing mounting links.

12. The propulsion system according to claim 1, wherein, the plurality of fairing mounting links are disposed at the core fairing in a circumferential arrangement.

13. The propulsion system according to claim 12, wherein, the plurality of fairing mounting links include a first spring coupled to the core fairing and the aft frame assembly, and wherein the plurality of fairing mounting links include a second spring coupled to the core fairing and the turbine frame assembly.

14. The propulsion system according to claim 1, wherein, comprising: a nacelle that surrounds the core fairing, wherein the nacelle is connected to the front frame.

15. The propulsion system according to claim 14, wherein, the nacelle is connected to the core engine by a rear nacelle mount.

16. The propulsion system according to claim 15, wherein, wherein the aft nacelle mount attaches the nacelle to the core engine at one or both of the turbine frame assembly or the aft frame assembly.

17. The propulsion system of claim 1, wherein, wherein the plurality of nacelle mounting links includes a coupler configured to at least partially surround a respective one of the plurality of members, wherein a joint member connects the respective mounting link at the core nacelle to the respective member, wherein the joint member is pivotally coupled to the coupler via a first pivot point, and the joint member is pivotally coupled to the respective member of the plurality of members via a second pivot point.

18. A gas turbine engine defining a nominal centerline axis, wherein, a propulsion system comprising: a fan assembly including a front frame; a core engine connected to the front frame, wherein the core engine includes a turbine frame assembly, and wherein the core engine defines an engine centerline axis, and further wherein, during normal propulsion system operation, the engine centerline axis is substantially coaxial with the nominal centerline axis, and wherein when the core engine is deflected, the engine centerline axis is at an acute angle to the nominal centerline axis; an aft frame assembly, wherein the turbine frame assembly includes a turbine case, the aft frame assembly being connected to the core engine behind the turbine frame assembly at the turbine case, and wherein the aft frame includes a nozzle assembly; a core nacelle surrounding the core engine, wherein the core nacelle is connected to the front frame; and a plurality of nacelle mounting links selectively loading the core nacelle to the aft frame assembly and the turbine frame assembly, wherein the plurality of nacelle mounting links are each loaded by deflection of the core engine; wherein the plurality of nacelle mounting links includes a first nacelle mounting link coupled between the core nacelle and the aft frame assembly, wherein the plurality of nacelle mounting links includes a second nacelle mounting link coupled between the core nacelle and the turbine frame assembly; wherein the second nacelle mounting link is axially forward of the first nacelle mounting link, and wherein each of the aft frame assembly and the turbine frame assembly includes a plurality of members extending toward the core nacelle, wherein the plurality of members are configured to be selectively loaded by the plurality of nacelle mounting links.

19. The gas turbine engine of claim 18, wherein, wherein the plurality of nacelle mounting links includes a coupler wherein, when the engine centerline axis is substantially coaxial with the nominal centerline axis, the coupler and the member are unloaded relative to each other, and wherein when the engine centerline axis is deflected at the acute angle relative to the nominal centerline axis, the coupler and the member are loaded onto each other.

20. The gas turbine engine according to claim 19, wherein: a joint member connects a respective mounting link at the core cowl to a respective member.

21. The gas turbine engine according to claim 20, wherein: comprising: a nacelle that surrounds the core cowl, wherein the nacelle is connected to the front frame, and wherein the nacelle is connected to the core engine by a rear nacelle mount, and further wherein the rear nacelle mount connects the nacelle to the core engine at one or both of the turbine frame assembly or the rear frame assembly.

22. The gas turbine engine according to claim 18, wherein: the plurality of cowl mounting links includes couplings, and a joint member connects a respective mounting link at the core cowl to a respective member of the plurality of members, wherein the joint member is pivotally connected to the coupling via a first pivot point and the joint member is pivotally connected to the respective member of the plurality of members via a second pivot point.

23. The gas turbine engine according to claim 21, wherein: the coupling is circumferentially positioned adjacent to the respective member of the plurality of members.

24. The gas turbine engine according to claim 22, wherein: the coupling is circumferentially positioned adjacent to the respective member of the plurality of members.

25. The gas turbine engine according to claim 18, wherein: the rear frame assembly is selectively connected or selectively loaded to the frame by a rear engine mounting link; the rear engine mounting link is selectively loaded by deflection of the core engine.

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