Method and apparatus for mounting gas turbine engine to pylon

Abstract

Systems, apparatus, articles of manufacture, and methods for mounting a gas turbine engine to a pylon are disclosed. An example gas turbine engine disclosed herein includes a first mount, a first frame portion coupled to a pylon via the first mount, a second frame portion coupled to the first frame portion such that the second frame portion cantilevers from the first frame portion, and a second mount coupling the second frame portion to the pylon, the second mount defines a load path between the hanger and the second frame portion, the second mount including a resilient element disposed in the load path.

Description

[0001] Related Applications

[0002] This application claims priority to U.S. Provisional Patent Application No. 63 / 589,170, filed on October 10, 2023, entitled “Method and Apparatus for Mounting a Gas Turbine Engine to a Pedestal,” and U.S. Provisional Patent Application No. 63 / 518,992, filed on August 11, 2023, entitled “Method and Apparatus for Mounting a Gas Turbine Engine to a Pedestal,” both of which are incorporated herein by reference in their entirety. Technical Field

[0003] The present disclosure relates generally to gas turbines and, more particularly, to methods and apparatus for mounting a gas turbine to a pylon. Background Art

[0004] Gas turbine engines typically include an inlet section, a compressor section, a combustion section, a turbine section, and an exhaust section in a serial flow order. In operation, air enters the inlet section and flows to the compressor section, where one or more axial compressors gradually compress the air until it reaches the combustion section, thereby producing combustion gases. The combustion gases flow from the combustion section through a hot gas path defined within the turbine section and then exit the turbine section via the exhaust section. BRIEF DESCRIPTION OF THE DRAWINGS

[0005] A full and enabling disclosure of the present disclosure, including the best mode thereof, to one skilled in the art is set forth in the specification with reference to the accompanying drawings, in which:

[0006] Figure 1 is a cross-sectional view of an example gas turbine engine in which examples disclosed herein may be implemented.

[0007] Figure 2 is a perspective view of an example frame component of a gas turbine engine coupled to a pylon including an aft mount implemented in accordance with the teachings of the present disclosure.

[0008] Figure 3 yes Figure 2 A perspective view of the rear mounting part.

[0009] Figure 4 is a perspective view of another rear mount implemented in accordance with the teachings of the present disclosure.

[0010] Figure 5A is a perspective view of another rear mount implemented in accordance with the teachings of the present disclosure.

[0011] Figure 5B is a cross-sectional view of another rear mount implemented in accordance with the teachings of the present disclosure.

[0012] Figure 6It is possible to Figure 2 A perspective view of a thrust link construction used in conjunction with a frame member and a rear mounting member.

[0013] Figure 7 yes Figure 6 A stereoscopic view of the rear connecting piece of the thrust link structure.

[0014] Figure 8 It is possible to Figure 2 A perspective view of another thrust link configuration used in conjunction with the frame member and rear mounting member.

[0015] Fig. 9 It is possible to Figure 2 A perspective view of another thrust link configuration used in conjunction with the frame member and rear mounting member.

[0016] Fig.10 Yes Figure 5A The rear mounting parts and Figure 6 A perspective view of a gas turbine engine with a thrust connecting rod structure.

[0017] Fig.11 is comprised of another rear mounting piece and Figure 6 A perspective view of a gas turbine engine with a thrust connecting rod structure.

[0018] Fig. 12A is an example first frame connector Fig.11 Front view of the rear mounting.

[0019] Fig. 12B is an example second frame connector Fig.11 Front view of the rear mounting.

[0020] Fig. 12C is an example third frame connector Fig.11 Front view of the rear mounting.

[0021] Fig.12D is an example of a fourth frame connector Fig.11 Front view of the rear mounting.

[0022] Fig.12E is an example fifth frame connector Fig.11 Front view of the rear mounting.

[0023] Fig.12F is an example sixth frame connector Fig.11 Front view of the rear mounting.

[0024] Figure 12G The seventh connecting member includes the example Fig.11 Front view of the rear mounting.

[0025] The drawings are not drawn to scale. Instead, the thickness of a layer or region may be exaggerated in the drawings. Typically, the same reference numerals will be used throughout the drawings and accompanying written descriptions to represent the same or similar parts. As used in this patent, stating that any part (e.g., layer, film, zone, region, or plate) is in any way on another part (e.g., positioned on another part, located on another part, set on another part, or formed on another part, etc.) indicates that the referenced part is in contact with the other part, or the referenced part is above the other part, with one or more intermediate parts located between the two. Unless otherwise specified, connection references (e.g., attachment, connection, connection, engagement, etc.) will be interpreted broadly and may include intermediate members between a collection of elements and relative movement between elements. Therefore, a connection / disconnection reference does not necessarily infer that the two elements are directly connected and in a fixed relationship to each other. Stating that any part is "in contact" with another part means that there is no intermediate part between the two parts.

[0026] Descriptors "first," "second," "third," etc., are used when identifying multiple elements or components that can be referred to separately. Unless otherwise specified or understood based on the context of their use, such descriptors are not intended to imply any meaning of priority, physical order, or arrangement in a list, or ordering in time, but are merely used as labels to individually reference multiple elements or components to facilitate understanding of the disclosed examples. In some examples, the descriptor "first" may be used to indicate an element in the detailed description, while the same element may be indicated by a different descriptor in the claims, such as "second" or "third." In this case, it should be understood that such descriptors are only used to easily reference multiple elements or components. DETAILED DESCRIPTION

[0027] Compressor blade tip clearance in a gas turbine engine is affected by operational deformation caused by internal forces of the gas turbine engine. In particular, thrust, aerodynamic and / or propeller loads may generate internal bending moments in the gas turbine engine, which may cause the gas turbine engine to bend between the mounting links of the gas turbine engine. In recent years, some gas turbine engines have mitigated deformation caused by such internal forces via cantilevered core sections. However, the reaction of the gravity load of the cantilevered core via the front mounting of the gas turbine engine may cause deformation within the core section. The example disclosed herein provides a mounting system comprising a rear mounting having an elastic element. The example mounting disclosed herein reacts to a portion of the vertical load of the cantilevered core while reducing operational deformation caused by the bending moments associated with thrust, aerodynamic and / or propeller loads. The example mounting disclosed herein reduces deformation caused by gravity loads via elastic members.

[0028] Some engines including cantilever cores may experience relatively large vertical (e.g., yaw axis alignment, etc.) and lateral (e.g., pitch axis alignment, etc.) displacements during operation. In particular, because the cantilever core is not directly connected to the pylon, such a core may move vertically and laterally during operation. In some examples, such displacements may reduce the effectiveness of seals within the gas turbine engine and may make integration of the cantilever core with the nacelle difficult. Examples disclosed herein include thrust link configurations that mitigate such vertical and lateral displacements associated with a cantilever core. Examples disclosed herein include mounting systems for cantilever core engines to react to some or all of the bending moments between the thrust links of the engine. In some example mounting systems disclosed herein, thrust links having laterally displaced connection points are provided, which enable the thrust links to react to yaw moments and reduce lateral displacements. In some example mounting systems disclosed herein, a thrust link is provided with a vertically displaced connection point, which enables the thrust link to react pitch moments and reduce vertical displacement.

[0029] The terms "upstream" and "downstream" refer to relative directions relative to the flow of a fluid in a fluid passage. For example, "upstream" refers to the direction from which the fluid is flowing, and "downstream" refers to the direction to which the fluid is flowing. As used herein, the term "connecting rod" refers to a connection between two parts that restricts the relative motion of the two parts (e.g., restricts at least one degree of freedom of the parts, etc.).

[0030] Various terms are used herein to describe the orientation of features. As used herein, the orientation of features, forces and moments is described with reference to the yaw axis, pitch axis and roll axis of the vehicle associated with the features, forces and moments. Typically, the drawings are annotated with reference to the axial direction, radial direction and circumferential direction of the gas turbine associated with the features, forces and moments. Typically, the drawings are annotated with a set of axes including the roll axis R, the pitch axis P and the yaw axis Y. As used herein, the terms "longitudinal" and "axial" are used interchangeably to refer to the direction parallel to the roll axis. As used herein, the term "lateral" is used to refer to the direction parallel to the pitch axis. As used herein, the term "vertical" is used to refer to the direction parallel to the yaw axis.

[0031] "Include" and "comprising" (and all forms and tenses thereof) are used herein as open-ended terms. Thus, whenever a claim employs any form of "include" or "comprising" (e.g., includes, comprises, including, comprising, etc.) as a preamble or within any type of claim recitation, it should be understood that additional elements, terms, etc. may be present without exceeding the scope of the corresponding claim or recitation. As used herein, when the phrase "at least" is used as a transitional term, such as in the preamble of a claim, it is open-ended in the same manner as the terms "include" and "comprising" are open-ended. The term "and / or" when used, for example, in a form such as A, B, and / or C, refers to any combination or subset of A, B, and C, such as (1) only A, (2) only B, (3) only C, (4) B and A, (5) A and C, (6) B and C, and (7) A and B and C. As used herein in the context of describing structures, components, items, objects, and / or things, the phrase "at least one of A and B" is intended to mean embodiments that include any of the following: (1) at least one A, (2) at least one B, and (3) at least one A and at least one B. Similarly, as used herein in the context of describing structures, components, items, objects, and / or things, the phrase "at least one of A or B" is intended to mean embodiments that include any of the following: (1) at least one A, (2) at least one B, and (3) at least one A and at least one B. As used herein in the context of describing the execution or performance of processes, instructions, actions, activities, and / or steps, the phrase "at least one of A and B" is intended to mean embodiments that include any of the following: (1) at least one A, (2) at least one B, and (3) at least one A and at least one B. Similarly, as used herein in the context of describing the execution or performance of a process, instruction, action, activity and / or step, the phrase "at least one of A or B" is intended to mean an embodiment that includes any of the following: (1) at least one A, (2) at least one B and (3) at least one A and at least one B.

[0032] As used herein, singular references (e.g., "a," "an," "first," "second," etc.) do not exclude a plurality. The term "a" or "an" entity as used herein refers to one or more of that entity. The terms "a" (or "an"), "one or more," and "at least one" may be used interchangeably herein. Furthermore, although listed separately, multiple devices, elements, or method actions may be implemented by, for example, a single unit or processor. In addition, although individual features may be included in different examples or claims, these features may be combined, and inclusion in different examples or claims does not mean that a combination of features is not feasible and / or disadvantageous.

[0033] As used herein, "approximately" and "about" modify the subject matter / values ​​thereof to recognize possible variations that occur in real-world applications. For example, as understood by one of ordinary skill in the art, "approximately" and "approximately" may modify dimensions that may not be exact due to manufacturing tolerances and / or other real-world imperfections. For example, "approximately" and "approximately" may indicate that such dimensions may be within a tolerance range of + / - 10%, unless otherwise indicated herein.

[0034] Some existing gas turbine engines are configured to be mounted to the wings of an aircraft via pylons (e.g., underwing mounting). These pylons transfer loads associated with the operation of the gas turbine engine (e.g., thrust loads, air inlet loads, propeller loads, gravity loads / weight, etc.) to the wings of the aircraft. Some such existing gas turbine engines are mounted to the pylons via front and rear mounts for the engine. In some prior art examples, the front mounts couple the fan case of the gas turbine engine to the pylons, while the rear mounts couple the core section of the gas turbine engine to the gas turbine engine. Other existing gas turbine engines do not include mounts that couple the core section to the pylons, but rather include two front mounts that couple the front frame portion of such gas turbine engine to the pylons. The core section of such a gas turbine engine is referred to as a "cantilevered core section" because such a core section is cantilevered relative to the front section of the gas turbine engine.

[0035] An open rotor gas turbine engine (also known as an open fan gas turbine engine), a propeller fan engine, and / or a non-ducted fan gas turbine engine is a gas turbine engine that includes a fan with non-ducted blades. An open rotor gas turbine provides high performance and fuel efficiency and lacks the fan case of a conventional turbofan gas turbine engine. In some such engine configurations, gas turbine engine components that are typically disposed within a fan case (e.g., accessory gearbox, oil tank, etc.) are disposed at another location of the gas turbine engine, such as a core case. However, arranging such components within a core case may increase the gravity load on the core engine.

[0036] In some gas turbine engines, particularly open rotor engines and turboprop engines, high vibration loads are experienced during various phases of flight due to asymmetric propeller loads (e.g., P factors or 1P loads). 1P loads, also known as + / -1P loads, are asymmetric forces on the blades and asymmetric disk loads caused by aerodynamic forces at the aircraft angle of attack. 1P loads are typically highest in operating conditions with high power and high angle of attack, such as takeoff and climb.

[0037] During takeoff (TO) rotation maneuvers, blade tip clearances at several locations throughout the engine are typically defined based on the sum of axisymmetric closures and local circumferential clearance deformations. That is, in some examples, during TO engine operation, the minimum blade tip clearance in the compressor may occur (e.g., the closest clearance, etc.). In some examples, the minimum blade tip clearance at which the compressor can operate during takeoff is based on clearance reductions caused in part by engine vibrations and deformations (e.g., strains, etc.) caused by engine operation. Operational deformations in the engine may be caused by internal forces and / or moments in the engine, which are caused by thrust, IP loads, air inlet loads, etc. For example, operational loads may cause the engine body to bend and / or deform between the front and rear mounting points of the gas turbine engine on the aircraft. Designing the engine to compensate for these deformations (e.g., by increasing cold clearance or cruise clearance) correspondingly reduces engine operating efficiency (e.g., specific fuel consumption, etc.). In some prior art engine configurations, the resulting bending moments (e.g., moments around yaw and pitch axes, etc.) are reacted through the engine body (e.g., the fan and core sections of the engine, etc.). The reaction of the bending moment through the engine body may cause degradation of the engine (eg, deformation, distortion), which in turn affects blade tip clearance.Other prior art engine configurations, such as cantilever core gas turbine engines, do not experience body bending due to the lack of aft mountings.

[0038] Examples disclosed herein provide a mounting system suitable for use with a cantilevered open rotor gas turbine engine. The example mounting system described herein includes a gas turbine engine frame, wherein a partially cantilevered core section is coupled to a hanger. Examples disclosed herein include a tuned stiffness rear mount that couples the rear frame of the core section to the hanger. Some example rear mounts disclosed herein include an elastomer to partially react to vertical loads and reduce deformation transmitted through the engine body. Some example rear mounts disclosed herein include a spring to partially react to vertical loads and reduce deformation transmitted through the engine body. Some example rear mounts disclosed herein include a composite coil spring to partially react to vertical loads. In some examples disclosed herein, the rear mount includes a feature to react to yaw moments during operation beyond the standard. In some such examples disclosed herein, the rear mount includes a slot. In some examples disclosed herein, the rear mount includes a first member having a hollow interior and a second member disposed within the hollow interior. The example mounting systems disclosed herein reduce operational deformations associated with reaction to a curved mount between front and rear engine mounts and reduce gravity deformations associated with cantilever engine configurations.

[0039] Figure 11 is a schematic cross-sectional view of an example gas turbine engine 100 that may be used to implement the teachings of the present disclosure. The gas turbine engine 100 may be mounted to an aircraft, such as a fixed-wing aircraft, and may generate thrust for propelling the aircraft. The gas turbine engine 100 includes a fan that is not ducted through a nacelle or cowling, such that it may be referred to herein as a "non-ducted fan," or the entire gas turbine engine 100 may be referred to as a "non-ducted engine," "open rotor gas turbine engine," "open fan gas turbine engine," or the like.

[0040] The gas turbine engine 100 includes a core engine 120 and a fan section 150 located upstream thereof. Generally, the core engine 120 includes a compressor section, a combustion section, a turbine section, and an exhaust section in a serial flow order. In particular, as shown in FIG. Figure 1 As shown, the core engine 120 includes a core cover 122 defining an annular core inlet 124. The core cover 122 further surrounds the low pressure system and the high pressure system. In some examples, the core cover 122 can surround and support a supercharger or low pressure ("LP") compressor 126 for pressurizing the air entering the core engine 120 through the core inlet 124. The high pressure ("HP") multi-stage axial compressor 128 receives compressed air from the LP compressor 126 and further increases the air pressure. The pressurized air flows downstream to the combustor 130, where the fuel is injected into the pressurized air flow and ignited to increase the temperature and energy level of the pressurized air. It should be understood that, as used herein, the terms "high speed / low speed" and "high pressure / low pressure" are interchangeable for high pressure / high speed systems and low pressure / low speed systems. In addition, it should be understood that the terms "high" and "low" are used to distinguish between the two systems in the same context, and are not meant to imply any absolute speed and / or pressure values.

[0041] The high energy combustion products flow downstream from the combustor 130 to the high pressure turbine 132. The high pressure turbine 132 drives the HP compressor 128 through the high pressure shaft 136. At this point, the high pressure turbine 132 is drivingly coupled to the HP compressor 128. The high energy combustion products then flow to the low pressure turbine 134. The low pressure turbine 134 drives the LP compressor 126 and the components of the fan section 150 through the low pressure shaft 138. At this point, the low pressure turbine 134 is drivingly coupled to the components of the LP compressor 126 and the fan section 150. In this example, the LP shaft 138 is coaxial with the HP shaft 136. After driving each turbine 132, 134, the combustion products leave the core engine 120 through the core exhaust nozzle 140 to generate propulsive thrust. Therefore, the core engine 120 defines a core flow path or core duct 142, which extends between the core inlet 124 and the core exhaust nozzle 140. The core duct 142 is an annular duct located substantially inside the core cover 122 in the radial direction R.

[0042] The fan section 150 includes a fan 152, which in this example is the main fan. Figure 1 In the example shown, fan 152 is an open rotor or non-ducted fan. However, in other examples, fan 152 may be ducted, for example, by a fan housing or a nacelle surrounding fan 152. As shown, fan 152 includes an array of fan blades 154 ( Figure 1 Only one is shown in FIG. 1 ). Fan blades 154 are rotatable, for example, about longitudinal axis 112. As described above, fan 152 is drivingly coupled to low pressure turbine 134 via LP shaft 138. Fan 152 may be directly coupled to LP shaft 138, for example, in a direct drive configuration. Figure 1 As shown, the fan 152 may be coupled to the LP shaft 138 via a reduction gearbox 155 , for example, in an indirect drive or gear drive configuration.

[0043] In addition, fan blades 154 can be arranged at equal intervals around longitudinal axis 112. Each blade 154 has a root and a tip and a span defined between them. Each fan blade 154 defines a central blade axis 156. For this example, each blade 154 of fan 152 can rotate around its respective central blade axis 156, for example, in unison with each other. One or more actuators 158 can be controlled to make blades 154 pitch around their respective central blade axis 156. However, in other examples, each fan blade 154 can be fixed or unable to pitch around its central blade axis 156.

[0044] The fan section 150 also includes a fan guide vane array 160 including fan guide vanes 162 ( Figure 1 For this example, fan guide vanes 162 are not rotatable about longitudinal axis 112. Each fan guide vane 162 has a root and a tip and a span defined therebetween. Figure 1 As shown, the fan guide vanes 162 may be unshrouded, or may be covered by, for example, an annular shroud spaced outwardly from the tip of the fan guide vanes 162 in a radial direction R. Each fan guide vane 162 defines a central blade axis 164. For this example, each fan guide vane 162 of the fan guide vane array 160 may rotate about its respective central blade axis 164, for example, in unison with each other. One or more actuators 166 may be controlled to pitch the fan guide vanes 162 about their respective central blade axes 164. However, in other examples, each fan guide vane 162 may be fixed or unable to pitch about its central blade axis 164. The fan guide vanes 162 are mounted to the fan cover 170.

[0045] like Figure 1 As shown, in addition to the non-ducted fan 152, a ducted fan 184 is also included behind the fan 152, so that the gas turbine engine 100 includes a ducted fan and a non-ducted fan, both of which are used to generate thrust by the movement of air (not passing through the core engine 120). The ducted fan 184 shown in the figure is located at approximately the same axial position as the fan guide vanes 162, and is radially inside the fan guide vanes 162. Alternatively, the ducted fan 184 can be between the fan guide vanes 162 and the core duct 142, or further in front of the fan guide vanes 162. The ducted fan 184 can be driven by the low pressure turbine 134 (e.g., connected to the LP shaft 138), or by any other suitable rotation source, and can be used as the first stage of the supercharger or can operate alone.

[0046] The fan cover 170 surrounds at least a portion of the core cover 122 annularly, and is usually positioned on the outside of the core cover 122 in the radial direction R. Specifically, the downstream section of the fan cover 170 extends on the front part of the core cover 122 to define a fan flow path or fan duct 172. The incoming air can enter through the fan duct inlet 176 through the fan duct 172, and can leave through the fan exhaust nozzle 178 to generate propulsion thrust. The fan duct 172 is an annular duct that is usually positioned on the outside of the core duct 142 in the radial direction R. Each of the fixed struts 174 can have an aerodynamic profile to guide air to flow therefrom. In addition to the fixed struts 174, other struts can also be used to connect and support the fan cover 170 and / or the core cover 122. In many examples, the fan duct 172 and the core cover 122 can extend at least partially together (usually axially) on the opposite sides (e.g., opposite radial sides) of the core cover 122. For example, the fan duct 172 and the core cowl 122 may each extend directly from the leading edge 144 of the core cowl 122 and may extend axially together partially on opposite radial sides of the core cowl.

[0047] The gas turbine engine 100 further defines or includes an inlet duct 180. The inlet duct 180 extends between an engine inlet 182 and the core inlet 124 / fan duct inlet 176. The engine inlet 182 is generally defined at the front end of the fan casing 170 and is positioned between the fan 152 and the fan guide vane array 160 in the axial direction A. The inlet duct 180 is an annular duct that is positioned inside the fan casing 170 in the radial direction R. Air flowing downstream along the inlet duct 180 is divided (not necessarily evenly) into the core duct 142 and the fan duct 172 by the splitter or leading edge 144 of the core casing 122. The inlet duct 180 is wider than the center duct 142 in the radial direction R. The inlet duct 180 is also wider than the fan duct 172 in the radial direction R.

[0048] Figure 2 2 is a perspective view of an example engine mounting system 200 including a first frame portion 202, a second frame portion 204, and a third frame portion 206. Figure 2 In the example shown, the frame portions 202 , 204 , 206 are coupled to the hanger 208 via a first front mount 210 , a second front mount 212 , and a rear mount 214 implemented in accordance with the teachings of the present disclosure.

[0049] The frame sections 202, 204, 206 are gas turbine engine (e.g., Figure 1 Frame portions 202, 204, 206 contain and / or support components of the gas turbine engine and facilitate coupling thereof to hanger 208. Figure 2 In the example shown, the first frame portion 202 is a front frame portion (e.g., front frame, etc.), the second frame portion 204 is an intermediate frame portion (e.g., intermediate frame, etc.), and the third frame portion 206 is a turbine bucket frame portion (e.g., turbine bucket frame, etc.). Because the frame portions 202, 204, 206 are similar to open rotor engines (e.g., Figure 1 As a result, the frame packaging space within the frame portions 202, 204 (e.g., the frame portions associated with the fan section 150, etc.) is limited by the fan blades. Therefore, in some examples, components that are normally supported by the front frame portions 202, 204, such as the accessory gearbox and the oil tank, are supported by the frame portions associated with the core engine 120 (e.g., the third frame portion 206, etc.).

[0050] exist Figure 2 In the example shown, the first frame portion 202 is coupled to the hanger 208 via a first front mount 210, the second frame portion 204 is coupled to the hanger 208 via a second front mount 212, and the third frame portion 206 is coupled to the hanger 208 via a rear mount 214. In some examples, the first frame portion 202 and the second frame portion 204 are Figure 1 The fan section 150 of the gas turbine engine 100 is a component of the fan section 150 (eg, the first frame portion 202 is a first fan frame portion, the second frame portion 204 is a second fan frame portion, etc.), and the third frame portion 206 is Figure 1 Components of the core engine 120 of the gas turbine engine 100. It should be appreciated that the gas turbine engine including the frame portions 202, 204, 206 may include one or more additional frame portions disposed between each of the frame portions 202, 204, 206.

[0051] exist Figure 2In the illustrated example, third frame portion 206 is cantilevered (e.g., partially cantilevered, etc.) relative to first frame portion 202 and second frame portion 204. That is, third frame portion 206 is primarily supported via connections (not shown) to first frame portion 202 and second frame portion 204. In some examples, as described above, third frame portion 206 and / or other frame portions associated with the core portion support components (e.g., auxiliary gearbox (AGB), fuel tank, etc.) that are typically coupled within a fan frame portion (e.g., a frame portion similar to frame portions 204, 206, etc.). In some such examples, the added weight of such components increases the gravity load on the core section (e.g., core engine 120, etc.). Figure 2 In the illustrated example, to reduce (eg, mitigate, etc.) potential deformation associated with gravity loads on the core section, the engine mounting system 200 includes an aft mount 214 that couples the third frame portion 206 to the pylon 208 .

[0052] exist Figure 2 In the example shown, the rear mount 214 includes a resilient element 216 that enables the rear mount 214 to have a lower stiffness than the front mounts 210, 212. The relatively lower stiffness of the rear mount 214 enables some of the vertical loads associated with the core engine 120 to be transmitted to the pylon 208 via the rear mount 214 while reducing the bending moment transmitted through the core engine 120. In some examples, the rear mount 214 is a tuned mount. That is, in some examples, the material of the resilient element 216, the cross-sectional shape of the resilient element 216, and / or the thickness of the resilient element 216 may be selected (e.g., tuned, etc.) to balance the deformation associated with gravity loads (e.g., 1G loads, etc.) and the deformation associated with propeller loads (e.g., 1P loads, etc.). In some examples, the resilient element 216 dampens vibrations transmitted between the pylon 208 and the core engine 120. In some examples, elastic element 216 is a device for elastically coupling core engine 120 and / or third frame portion 206 to pylon 208 .

[0053] exist Figure 2 In the example shown, the elastic element 216 comprises an elastic body. Figure 3 The rear mounting member 214 and the elastic element 216 are further described in detail. Additionally or alternatively, the rear mounting member 214 may include a spring. For example, the rear mounting member 214 may include one or more tension coil springs, one or more hollow tube springs, one or more leaf springs, one or more volute springs, one or more gas springs (e.g., one or more air springs, etc.), one or more coil springs (e.g., one or more Belleville washers, etc.), etc. Figure 4 An example rear mounting member including a coil spring is described. Figure 5A and 5B Another example rear mounting member including a coil spring is described below. Figure 11-12F Other example rear mounts are described that include leaf springs.

[0054] In some examples, the elastic element 216 may have an adjustable stiffness. For example, if the elastic element 216 is an air spring and / or a hydro-pneumatic spring, the stiffness may be adjusted based on the expected and / or sensed loads transmitted via the rear mount 214. In some such examples, the stiffness of the elastic element 216 may be adjusted based on the environmental conditions of the engine mounting system 200, the flight phase of the gas turbine engine 100, the characteristics of the gas turbine engine 100, and / or the characteristics of the aircraft propelled by the gas turbine engine 100.

[0055] In some examples, the rear mount 214 may include one or more features that enable the rear mount 214 to react to the yaw moment (e.g., constrain the yaw degree of freedom, etc.) during operations that exceed standard (e.g., during a blade detachment event, etc.). For example, the rear mount 214 may include a slot that allows the third frame portion 206 and the hanger 208 to rotate relative to each other about the yaw axis within an arc defined by the slot and constrains such rotation outside the arc. In other examples, the rear mount 214 may include other features that enable the rear mount 214 to react to the yaw moment (e.g., constrain the yaw degree of freedom, etc.) during operations that exceed standard (e.g., during a blade detachment event, etc.) while allowing such rotation during standard operations (e.g., expected flight phases, etc.). The following is in conjunction with Figure 5A and 5B An example rear mount including such a feature is described.

[0056] Figure 3 It is possible to implement Figure 2 A perspective view of an example rear mount 300 of the rear mount 214. Figure 3 In the example shown, the rear mount 300 includes a hanger connector 302, a frame connector 304, and a structural member 305. Figure 3 In the example shown, the hanger coupling 302 includes a first elastic body 306, a first pin 308, a bracket 310, a load plate 311, and a U-shaped clip 312. Figure 3 In the example shown, the frame coupler 304 includes a second pin 314 , a second plate 316 , and a second yoke 318 .

[0057] The hanger connector 302 connects the rear mount 300 to the hanger 208. Figure 3In the example shown, the bracket 310 of the hanger coupling 302 is coupled to the hanger 208 (e.g., via one or more welds, via one or more fasteners, via one or more interference couplings, via one or more mechanical retainers, etc.). The U-clip 312 of the hanger coupling 302 is an interface formed between the first elastomeric body 306 and the bracket 310. Figure 3 In the example shown, the first pin 308 extends through the U-shaped clip 312. Figure 3 In the example shown, the U-shaped clamp 312 includes a first mounting plate 319A and a second mounting plate 319B. Figure 3 In the example shown, the first pin 308 extends through the openings in the mounting plates 319A, 319B and the structural member 305, forming an interface between the structural member 305 and the hanger coupling 302. The clevis 312 reacts to the vertical load applied via the rear mount 300 and allows the structural member 305 to rotate about the first pin 308 extending through the clevis 312.

[0058] exist Figure 3 In the example shown, structural member 305 is a rigid structural member that extends between hanger connector 302 and frame connector 304 and reacts the vertical loads transmitted therebetween. Structural member 305 may be constructed of any suitable rigid material, including steel, titanium, aluminum, nickel alloys, etc. Figure 3 In the example shown, the structural member 305 is coupled to the hanger coupling 302 via a clevis 312 and a first pin 308. The clevis 312 and the first pin 308 facilitate rotation of the structural member 305 about the first pin 308 (eg, about a roll axis, etc.).

[0059] The load plate 311 and the first elastic body 306 are provided with an interior 320 which is defined by the coupling of the bracket 310 and the hanger 208. Figure 3 In the example shown, the mounting plates 319A, 319B of the U-clip 312 extend through the openings in the bracket 310 and the first elastomeric body 306 and are coupled to the load plate 311. In some examples, the load plate 311 and the U-clip 312 can be coupled via one or more welds, one or more fasteners, one or more interference couplings, etc. Additionally or alternatively, the load plate 311 and the U-clip 312 are an integral component. Figure 3 In the example shown, load plate 311 is not directly coupled to bracket 310 and is able to translate therein. In some examples, the coupling of clevis 312 and load plate 311 retains load plate 311 within interior 320 .

[0060] The first elastic body 306 is an elastic element disposed in the bracket 310 so that the first elastic body 306 reacts to the vertical load (e.g., gravity load, aerodynamic load, maneuvering load, etc.) applied downward on the rear mount 300. Figure 2 In the example shown, the rear mount 300 includes a second elastic body 321 disposed between the top of the load plate 311 and the hanger 208. The second elastic body 321 reacts to vertical loads (e.g., aerodynamic loads, maneuvering loads, etc.) applied upwardly to the rear mount 300. The first elastic body 306 and / or the second elastic body 321 can be any suitable elastic material (e.g., natural rubber, isoprene rubber, silicone rubber, acrylic rubber, ethylene propylene rubber, thermoplastics, etc.) having a relatively low stiffness (e.g., compared to other components of the rear mount 300, etc.).

[0061] The load plate 311 is movably disposed within the bracket 310. That is, the load plate 311 can translate vertically within the bracket 310 (e.g., toward the hanger 208, away from the hanger 208, etc.). During operation, a downwardly applied vertical load (e.g., a load applied in a negative direction along the yaw axis, etc.) causes the load plate 311 to compress the first elastic body 306 and transfer the applied load thereto. In some such examples, the first elastic body 306 transfers the applied load to the bracket 310, which is then transferred to the hanger 208. Generally, the stiffness of the first elastic body 306 affects the portion of the negative vertical load associated with the gas turbine engine 100 that is transferred through the rear mount 300. That is, the greater stiffness of the first elastic body 306 causes a corresponding increase in the portion of the negative vertical load (e.g., gravity load, maneuvering load, etc.) that is transferred via the rear mount 300, as well as via other mounts associated with the gas turbine engine 100 (e.g., Figure 2 There is a corresponding reduction in the portion of the negative vertical load applied by the front mounts 210, 212, etc.

[0062] During operation, an upwardly applied vertical load (e.g., a load applied in a positive direction along the yaw axis, etc.) causes the load plate 311 to move upward within the bracket 310, compressing the second elastomer 321 and transferring the applied load thereto. In some such examples, the second elastomer 321 transfers the applied load to the hanger 208. Generally, the stiffness of the second elastomer 321 affects the portion of the positive vertical load associated with the gas turbine engine 100 that is transferred via the aft mount 300. That is, the greater stiffness of the second elastomer 321 causes a corresponding increase in the portion of the positive vertical load (e.g., aerodynamic loads, maneuvering loads, etc.) that is transferred via the aft mount 300, as well as via other mounts associated with the gas turbine engine 100 (e.g., Figure 2In some examples, the second elastomer 321 is not present. In some such examples, because the load plate 311 can freely translate in response to the applied vertical load, the rear mount 300 does not react to the positive vertical load. In some examples, the geometry (e.g., shape, thickness, presence of openings, etc.) and / or materials of the first elastomer 306 and / or the second elastomer 321 can be selected to tune the portions of the negative and positive vertical loads, respectively, carried by the rear mount 300.

[0063] The frame connector 304 connects the structural member 305 to the third frame portion 206. Figure 3 In the example shown, the structural member 305 is coupled to the second yoke 318 (eg, via one or more welds, one or more threaded connections, one or more fasteners, one or more interference connections, etc.) Additionally or alternatively, the structural member 305 and the second yoke 318 may be integral.

[0064] The second plate 316 of the frame connector 304 can be coupled to the third frame portion 206 via the hole 322. For example, the second plate 316 can be coupled to the third frame portion 206 via one or more fasteners (e.g., one or more bolts, one or more screws, one or more rivets, etc.) extending through the hole 322. Additionally or alternatively, the second plate 316 can be coupled to the third frame portion via one or more welds, via one or more interference connections, etc. In other examples, the second plate 316 and the third frame portion 206 can be integral.

[0065] exist Figure 3 In the example shown, the second pin 314 extends through the slot 324 of the second yoke 318 and the second plate 316. Figure 3 In the example shown, the second plate 316, the second yoke 318, and the second pin 314 form a U-shaped clip that facilitates the transfer of vertical loads between the third frame portion 206 and the structural member 305. The coupling of the structural member 305 and the third frame portion 206 via the second pin 314 facilitates rotation of the structural member 305 about the second pin 314 (e.g., about a roll axis, etc.). In some such examples, the pins 308, 314 prevent the rear mount 300 from transferring moments about the roll axis.

[0066] exist Figure 3 In the example shown, the slot 324 of the second plate 316 includes a first end 326A and a second end 326B. Figure 3In the example shown, the slot 324 defines an example arc 328 between the ends 326A, 326B. During standard operation (e.g., takeoff, cruise, descent, landing, etc.), the second pin 314 slides in the slot 324, which prevents the rear mount 300 from reacting to the yaw moment. In some examples, the yaw moment may be generated by a 1P load. In some such examples, because the rear mount 300 does not react to the yaw moment during standard operation, the operational deformation associated with the 1P load transmitted via the rear mount 300 can be reduced. In some examples, during non-standard operation (e.g., blade separation event, etc.), the yaw moment applied by the gas turbine engine 100 can increase and cause the gas turbine engine 100 to rotate so that the second pin 314 abuts one of the ends 326A, 326B. In some such examples, contact between the second pin 314 and one of the ends 326A, 326B causes the rear mount 300 to react to the yaw moment, which can mitigate the effects of such non-standard operation. In other examples, the slot 324 may not be present. In some such examples, the second plate 316 may include a hole to accommodate the second pin 314.

[0067] Figure 4 is a perspective view of another example rear mounting member 400 implemented according to the teachings of the present disclosure. The rear mounting member 400 may be used to implement Figure 2 The rear mounting member 214. Figure 4 In the example shown, the rear mounting member 400 includes a hanger coupling member 402, Figure 3 The frame connector 304, structural member 403 and spring 404. The example rear mounting member 400 is similar to Figure 3 The rear mounting member 300 is the same as the rear mounting member 400, except that the rear mounting member 400 includes a spring 404 instead of the first elastic body 306. Figure 4 In the example shown, the rear mounting member 400 does not include a slot, but in other examples, the rear mounting member 400 may include a slot similar to Figure 3 The slot of slot 324.

[0068] exist Figure 4 In the example shown, the hanger coupling 402 includes a yoke 405, a pin 406, and a mounting plate 408. Figure 4 In the example shown, the structural member 403 is coupled to the yoke 405 (e.g., via one or more welds, one or more threaded connections, one or more fasteners, one or more interference connections, etc.). Additionally or alternatively, the structural member 403 and the yoke 405 may be integral. In the example shown, a mounting plate 408 extends from the hanger 208 and facilitates its coupling with the rear mount 400. Figure 4 In the example shown, pin 406 extends through yoke 405 and mounting plate 408. Figure 3In the example shown, mounting plate 408, yoke 405, and pin 406 form a U-shaped clamp that facilitates the transfer of vertical loads between third frame portion 206 and structural member 403. The coupling of structural member 403 and third frame portion 206 via pin 406 facilitates rotation of structural member 403 about pin 406 (e.g., about a roll axis, etc.). In some such examples, pin 406 and frame coupling 304 (e.g., Figure 3 The second pin 314, etc.) prevents the rear mount 400 from transmitting torque about the roll axis.

[0069] The spring 404 is a coil spring (e.g., a helical spring, etc.) that resists the tension applied between the hanger connector 302 and the frame connector 304. Figure 4 In the example shown, the spring 404 is disposed in the load path between the hanger coupling 402 and the frame coupling 304 such that the spring 404 reacts to negative vertical loads (e.g., gravity loads, aerodynamic loads, maneuvering loads, etc.) transmitted between the hanger coupling 402 and the frame coupling 304. In some examples, the spring 404 does not react to positive vertical loads between the hanger coupling 402 and the frame coupling 304.

[0070] In some examples, the aft mount 400 may include additional structural members (not shown) disposed between the hanger coupling 302 and the frame coupling 304. In some examples, the geometry and / or material of the spring 404 may be selected to reduce deformation associated with gravity and maneuvering loads and to reduce deformation associated with bending moments transmitted between the aft mount 400 and the forward mount (e.g., forward mounts 210, 212, etc.) of the gas turbine engine. In some examples, the material may be any suitable material, including spring steel, titanium, nickel alloys, composite materials, and / or any other suitable material.

[0071] Figure 5A is a perspective view of another example rear mount 500 implemented in accordance with the teachings of the present disclosure. Figure 5B is a cross-sectional view of the rear mounting member 500. The rear mounting member 500 may be implemented Figure 2 The rear mounting member 214. Figure 5A and 5B In the example shown, the rear mounting member 500 includes a Figure 3 The second pin 314, Figure 3 The second plate 316 and Figure 3 The first pin 502, the plate 504 and the yoke 506 of the second yoke 318 are shown in FIG. Figure 3 and 4The aft mount 500 is coupled to a frame portion of the core engine 120 (eg, the third frame portion 206, etc.) by means of the frame coupling member 304 of the aft mount 500. In other examples, the aft mount 500 may be coupled to the core engine 120 via any other suitable coupling member.

[0072] exist Figure 5A and 5B In the example shown, the rear mount 500 includes a first coil spring 508, a second coil spring 510, a first structural member 512, a second structural member 514, a first flange 516, a second flange 518, a second pin 520, and a mounting plate 522. Figure 5A and 5B In the example shown, each coil spring 508, 510 includes two frustoconical portions. In other examples, one or both of the coil springs 508, 510 may have any other suitable shape (e.g., conical, frustoconical, etc.). Figure 5A and 5B In the example shown, each of the coil springs 508, 510 is a single spring. In other examples, one or both of the coil springs 508, 510 may include one or more portions stacked in parallel and / or one or more portions stacked in sequence. In some examples, the thickness and / or amount of the portions of the coil springs 508, 510 may be used to adjust the stiffness of the rear mount 500 in the negative vertical direction and the positive vertical direction, respectively. Figure 5A and 5B In the example shown, the coil springs 508, 510 are composite springs. In other examples, the coil springs 508, 510 can be made of any other suitable material (e.g., steel, aluminum, nickel alloy, bronze, etc.).

[0073] The first structural member 512 is a rigid structural member (e.g., a tubular member, a pipe, etc.) that transfers loads between the yoke 506 and one or both of the coil springs 508, 510. Figure 5A and 5B In the example shown, the first structural member 512 has a generally circular cross-section. In other examples, the first structural member 512 can have any other suitable cross-section (e.g., an oval cross-section, a polygonal cross-section, etc.). The first structural member 512 can be constructed of any suitable rigid material, including steel, titanium, aluminum, nickel alloys, composite materials, etc. Figure 5B In the example shown, the first structural member 512 has an interior 523 that receives the second structural member 514 .

[0074] The second structural member 514 is a rigid structural member (e.g., a tubular member, a pipe, etc.) that transfers loads between the mounting plate 522 and one or both of the coil springs 508, 510. Figure 5BIn the example shown, the second structural member 514 has the same cross-sectional shape as the first structural member 512, and has a smaller cross-sectional dimension than the first structural member 512, thereby forming a gap 526 between the outer diameter 527A of the second structural member 514 and the inner diameter 527B of the first structural member 512. The second structural member 514 can be constructed of any suitable rigid material, including steel, titanium, aluminum, nickel alloys, composite materials, etc.

[0075] The first flange 516 is an annular member disposed between the second pin 520 and the first coil spring 508. Figure 5A and 5B In the example shown, the first flange 516 is not fixedly coupled to the first structural member 512 or the second structural member 514, but is held under compression between the second pin 520 and the first coil spring 508. The first flange 516 can be constructed of any suitable rigid material, including steel, titanium, aluminum, nickel alloys, composite materials, etc. In some examples, the first flange 516 is a washer and / or a disc. In other examples, the first flange 516 can be any other suitable shape. The second flange 518 is an annular member disposed between the first coil spring 508 and the second coil spring 510. Figure 5A and 5B In the example shown, the second flange 518 is integral with the first structural member 512. In other examples, the second flange 518 can be an annular member coupled to the first structural member 512 via one or more welds, via one or more fasteners (e.g., bolts, screws, rivets, etc.), via one or more interference connections, and / or via one or more mechanical interfaces. In some examples, the second flange 518 is constructed of the same material as the first structural member 512. In other examples, the second flange 518 can be constructed of a different rigid material.

[0076] The second pin 520 connects the first structural member 512 and the second structural member 514. Figure 5A and 5B In the example shown, the second pin 520 abuts the first flange 516, which maintains the coupling of the first structural member 512 to the second structural member 514. Figure 5A and 5B In the example shown, the first structural member includes a groove 524. Figure 5A and 5B In the example shown, the second pin 520 extends through a slot 524 and an opening 521 in the second structural member 514 .

[0077] The mounting plate 522 enables the rear mount 500 to be coupled to a hanger (e.g., Figure 2For example, the mounting plate 522 can be coupled to the hanger 208 via one or more welds, via one or more fasteners (e.g., bolts, screws, rivets, etc.), via one or more interference connections, and / or via one or more mechanical interfaces. In other examples, the mounting plate 522 can be integral with the hanger and / or be part of the hanger. Figure 5B In the example shown, the mounting plate 522 is integral with the second structural member 514. In other examples, the mounting plate 522 can be coupled to the second structural member 514 via one or more welds, via one or more fasteners (e.g., bolts, screws, rivets, etc.), via one or more interference connections, and / or via one or more mechanical interfaces.

[0078] During operation, the slot 524 allows the first structural member 512 to translate vertically relative to the second structural member 514 and the second pin 520. For example, during a positive vertical load (e.g., the gas turbine engine 100 pushing upward on the pylon 208, a compressive load, etc.), the second pin 520 slides downward within the slot 524 until the second pin 520 abuts the bottom of the slot 524, which enables compression of the second coil spring 510. The compression of the second coil spring 510 reduces the stiffness of the aft mount 500 under tension, which reduces the portion of the positive vertical load associated with the gas turbine engine 100 that is transmitted via the aft mount 500 and increases the portion of the positive vertical load that is transmitted via other mounts of the gas turbine engine 100. In some examples, the second coil spring 510 is not present. In some such examples, the aft mount 500 may include a rigid connection that reacts to the positive vertical load.

[0079] During operation, if a negative vertical load is applied to the aft mount 500 (e.g., the gas turbine engine 100 pulling down on the pylon 208, a tensile load, etc.), the second flange 518 applies a compressive load to the first coil spring 508. In some such examples, the first coil spring 508 is compressed between the second flange 518 and the first flange 516. In compression, the compression of the first coil spring 508 reduces the stiffness of the aft mount 500, which reduces the portion of the negative vertical load associated with the gas turbine engine 100 that is transmitted via the aft mount 500 and increases the portion of the negative vertical load that is transmitted via other mounts of the gas turbine engine 100. In some examples, the first coil spring 508 is not present. In some such examples, the aft mount 500 may include a rigid connection that reacts to the negative vertical load.

[0080] The gap 526 enables the first structural member 512 and the second structural member 514 to rotate relative to each other about the second pin 520. During standard operation (e.g., takeoff, cruise, descent, landing, etc.), the second structural member 514 rotates within the inner portion 523 about the second pin 520, which prevents the rear mounting member 500 from reacting to the yaw moment. In some examples, the yaw moment may be generated by a 1P load. In some such examples, because the rear mounting member 500 does not react to the yaw moment during standard operation, the operational deformation associated with the 1P load transmitted via the rear mounting member 214 may be reduced. In some examples, during non-standard operation (e.g., blade detachment events, etc.), the yaw moment applied by the gas turbine engine 100 may increase and cause the gas turbine engine 100 to rotate, causing the second structural member 514 to rotate within the gap 526 until the outer diameter 527A of the second structural member 514 abuts the inner diameter 527B of the first structural member 512. In some such examples, contact between second structural member 514 and first structural member 512 causes rear mount 500 to react to the yaw moment, which can mitigate the effects of such non-standard operation. In other examples, gap 526 may not exist, and rear mount 500 may react to the yaw moment during standard operation.

[0081] Figure 6 Can be combined Figure 2 A perspective view of an example first thrust link configuration 600 for use with the second frame portion 204 of FIG. Figure 6 In the example shown, the first thrust link structure 600 includes a first thrust link 602 and a second thrust link 604, which are Figure 2 The second frame portion 204 extends between the hanger block 606. Figure 6 In the example shown, the first thrust link 602 is coupled to the hanger block 606 at a first block attachment point 608 , and the second thrust link 604 is coupled to the hanger block 606 at a second block attachment point 610 .

[0082] The hanger block 606 is coupled to a hanger (eg, Figure 2 In some examples, the hanger block 606 may not be present. In some such examples, the thrust links 602, 604 may extend directly to the hanger 208. In some examples, the rear mounting member (e.g., Figure 2-5B The rear mounting member 214, one of 400, 500, etc.) can be connected to the bracket block 606.

[0083] The first thrust link configuration 600 enables a gas turbine engine (eg, Figure 1The yaw moment generated by the operation of the gas turbine engine 100 (e.g., a yaw moment) can be restrained by the thrust links 602, 604 in combination. The thrust links 602, 604 prevent the yaw moment from being transmitted through the cantilever core. Figure 6 In the illustrated example, the thrust links 602, 604 transmit axial forces between the second frame portion 204 and the hanger block 606. In some examples, one or both of the thrust links 602, 604 can be implemented by multiple thrust links (e.g., two thrust links, three thrust links, etc.). In some such examples, the multiple links implementing the first thrust link 602 can be connected together via a yoke and / or a whiffle tree connection, which evenly distributes the load between each of the multiple links. In some such examples, the multiple links implementing the second thrust link 604 can be connected together via a yoke and / or a whiffle tree connection, which evenly distributes the load between each of the multiple thrust links.

[0084] The block attachment points 608, 610 of the thrust links 602, 604 on the pylon block 606 are separated by a lateral displacement 612. The lateral displacement 612 enables the thrust links 602, 604 to withstand different amounts of axial loads generated by the gas turbine engine 100. Thus, this imbalance of axial forces between the thrust links 602, 604 enables the thrust links to transfer the yaw moment generated by the gas turbine engine 100 between the second frame portion 204 and the pylon block 606.

[0085] Figure 7 yes Figure 6 The thrust links 602, 604 and Figure 6 A perspective view of the connection between the hanger blocks 606. Figure 7 In the example shown, the first thrust link 602 is coupled to the first lug 702 via a first pin 704, and the second thrust link 604 is coupled to the second lug 706 via a second pin 708. Figure 7 In the example shown, the lugs 702, 706 are separate components that can be coupled to the hanger block 606 via one or more fasteners (e.g., bolts, rivets, etc.). In other examples, one or both of the lugs 702, 706 can be integral with the hanger block 606. In some examples, one or both of the pins 704, 708 can include and / or be coupled to one or more bearings and / or bushings. In some such examples, the bearings and / or bushings can prevent non-axial forces from reacting via the thrust links 602, 604.

[0086] exist Figure 7In the example shown, the block attachment points 608, 610 independently couple the thrust links 602, 604 to the hanger block 606. That is, unlike some existing connections, the thrust links 602, 604 are not coupled via a yoke (e.g., a crossbar connection), but are directly coupled to the hanger block 606. Thus, the thrust links 602, 604 are able to react to different amounts of axial force, which enables the thrust links 602, 604 to react to yaw moments between the second frame portion 204 and the hanger block 606.

[0087] Figure 8 Can be combined Figure 2 A perspective view of an example second thrust link configuration 800 for use with the second frame portion 204 of FIG. Figure 8 In the example shown, the second thrust link configuration 800 includes Figure 6 The first thrust link 602, Figure 6 The second thrust link 604 and the third thrust link 802. Figure 8 In the example shown, the third thrust link 802 is coupled to the Figure 6 The second thrust link configuration 800 enables both yaw and pitch moments generated by the operation of the gas turbine engine (e.g., gas turbine engine 100, etc.) to be restrained by the thrust links 602, 604, 802, which mitigates lateral and vertical displacements of the cantilevered core of the gas turbine engine. Figure 8 In the example shown, the hanger block 606 is coupled to the hanger 208. Figure 8 In the example shown, the second frame portion 204 includes an outer ring 808, an inner ring 810, and a branch 811. In the example shown, the first thrust link 602 is coupled to the inner ring 810 at a first frame attachment point 812, the second thrust link 604 is coupled to the inner ring 810 at a second frame attachment point 814, and the third thrust link 802 is coupled to the branch 811 at a third frame attachment point 816.

[0088] exist Figure 8 In the example shown, the thrust links 602, 604, 802 transfer the axial force generated by the second frame portion 204 to the hanger block 606 and the hanger 208. The block attachment points 608, 610 of the thrust links 602, 604 and the third block attachment point 804 of the third thrust link 802 are separated by a vertical displacement 806. Similarly, the thrust links 602, 604 are separated by a vertical displacement 806. Figure 6606 and lateral displacement 612. The vertical displacement 806 and lateral displacement 612 allow an axial force imbalance to occur between the thrust links 602, 604, 802. Therefore, the thrust links 602, 604, 802 can transfer the yaw and pitch moments associated with the second frame portion 204 to the hanger 208 (e.g., via the hanger block 606, etc.). In other examples, the thrust links 602, 604, 802 can have any other suitable position (e.g., having both a vertical position and a lateral displacement, etc.).

[0089] Fig. 9 Can be combined Figure 2 A perspective view of an example third thrust link configuration 900 for use with the second frame portion 204 of FIG. Fig. 9 In the example shown, the third thrust link configuration 900 includes Figure 6 The first thrust link 602, Figure 6 The second thrust link 604 and the third thrust link 902. Fig. 9 In the example shown, the third thrust link 902 is coupled to the hanger 208 at a third block attachment point 904. The example third thrust link configuration 900 is similar to the second thrust link configuration 800, except that the third thrust link 902 is directly coupled to the hanger 208 via a lug 906, as opposed to being coupled to the hanger block 606. Figure 8 The third thrust link 802 is different.

[0090] exist Fig. 9 In the example shown, the thrust links 602, 604, 902 transfer the axial force generated by the second frame portion 204 to the hanger block 606 and the hanger 208. The block attachment points 608, 610 of the thrust links 602, 604 and the third attachment point 904 of the third thrust link 802 are separated by a vertical displacement 908. Similarly, the thrust links 602, 604 are connected by a vertical displacement 908. Figure 6 The lateral displacement 612 of the second frame portion 204 is displaced. The vertical displacement 908 and the lateral displacement 612 allow an axial force imbalance to occur between the thrust links 602, 604, 902. Therefore, the thrust links 602, 604, 902 can transfer the yaw and pitch moments associated with the second frame portion 204 to the hanger 208 (e.g., via the hanger block 606, etc.). In other examples, the thrust links 602, 604, 902 can have any other suitable configuration (e.g., having both a vertical position and a lateral displacement, etc.).

[0091] Figure 6 and 7 The first thrust link structure 600, Figure 8The second thrust link configuration 800 and the third thrust link configuration 900 are structures that react to the yaw and / or pitch moments and mitigate the lateral and / or vertical displacements of the cantilever core section associated therewith. Figure 6 and 7 The first thrust link structure 600, Figure 8 The second thrust link structure 800 and / or the third thrust link structure 900 may be connected with Figure 2 and 3 The rear mounting part 214, Figure 4 The rear mounting member 400 and / or Figure 5A and 5B In some such examples, Figure 6-9 The thrust link configuration 600, 800, 900 of the present invention reacts yaw and / or pitch moments transmitted through the gas turbine engine and prevents the aft mount 214, 400, 500 from reacting yaw and pitch moments. In some such examples, by preventing the aft mount 214, 400, 500 from reacting yaw and pitch moments, operational deformations in the engine body are reduced (e.g., eliminated, etc.).

[0092] In some examples, including Figure 6-9 The frame mounting system of the thrust link configuration 600, 800, 900 may be over-constrained and / or statically indeterminate. In some such examples, thermal expansion of the thrust link configuration 600, 800, 900 may cause deformation of the engine body due to stresses and strains associated with the expansion of the thrust links of the thrust link configuration 600, 800, 900. Fig.10 and 11 Example mounting systems for mitigating such deformation associated with thermal expansion are described.

[0093] Fig.10 Yes Figure 5A and 5B The rear mounting part 500, Figure 8 The second thrust link structure 800, the first front mounting member 1001 and Figure 2 A perspective view of another example engine mounting system 1000 of the second front mounting member 212 is shown. Fig.10 In the illustrated example, engine mounting system 1000 couples gas turbine engine 1002 to pylon 208. Gas turbine engine 1002 includes Figure 1 The core engine 120 and Figure 2 The gas turbine engine 1002 is similar to the frame portions 202, 204, 206. Figure 1 of the gas turbine engine 100 unless otherwise indicated.

[0094] exist Fig.10 In the example shown, the rear mount 500 extends between the hanger 208 and the third frame portion 206. Fig.10 In the example shown, the first front mount 1001 extends between the hanger 208 and the first frame portion 202. Fig.10 In the example shown, Figure 8 The first thrust link 602 of the second thrust link configuration 800 is coupled to the second frame portion 204 at a first frame attachment point 812, the second thrust link 604 of the second thrust link configuration 800 is coupled to the second frame portion 204 at a second frame attachment point 814, and the third thrust link 802 of the second thrust link configuration 800 is coupled to the second frame portion 204 at a third frame attachment point 816. Fig.10 In the illustrated example, the first thrust link 602 and the second thrust link 604 have a first length 1004 , and the third thrust link 802 has a second length 1006 .

[0095] exist Fig.10In the example shown, the engine mounting system 1000 over-constrains the gas turbine engine 100. That is, the mounting components (e.g., the front mountings 212, 1001, the rear mountings 500, the first thrust link 602, the second thrust link 604, the third thrust link 802, etc.) of the engine mounting system 1000 include nine static constraints. For example, the front mountings 212, 1001 constrain lateral translation, vertical translation, longitudinal translation, yaw translation, and roll, the thrust links 602, 604, 802 constrain longitudinal translation, yaw rotation, and pitch translation, and the rear mounting 500 constrains vertical translation. In other examples, engine mounting system 1000 may include fewer static constraints (e.g., 6 static constraints, 7 static constraints, 8 static constraints, etc.) and / or additional static constraints (e.g., 10 static constraints, etc.) depending on the configuration of front mount 212, 1001, rear mount 500, first thrust link 602, second thrust link 604, third thrust link 802. Therefore, because engine mounting system 1000 includes more than 6 static constraints, engine mounting system 1000 is statically indeterminate (e.g., overconstrained, statically overdetermined, not resolvable via force and moment balance, etc.). Because the engine mounting system 1000 is statically indeterminate, the loads carried by the front mounting components 212, 1001, the rear mounting component 500, the first thrust link 602, the second thrust link 604, and the third thrust link 802 depend on the environmental conditions (e.g., temperature, etc.), material properties (e.g., stiffness, thermal properties, etc.), and geometric shapes (e.g., length, thickness, etc.) of the front mounting components 212, 1001, the rear mounting component 500, the first thrust link 602, the second thrust link 604, and the third thrust link 802.

[0096] During operation of gas turbine engine 1002, a portion of the air entering gas turbine engine 1002 flows through core engine 120. Within core engine 120, the air is pressurized (e.g., via Figure 1 LP compressor 126 and HP compressor 128, etc.) and combusted (e.g., via combustor 130, etc.). The relatively hotter and denser air increases the relative temperature of the core engine 120 and components adjacent to the core engine 120 of the gas turbine engine 1002 compared to other components of the gas turbine engine 1002. Additionally, during operation of the gas turbine engine 1002, ambient air (e.g., approximately -50 degrees Fahrenheit at operating altitude, etc.) passes between the inner ring 810 and the outer ring 808, which is cooler than the air flowing through the core engine 120 (e.g., approximately 3000 degrees Fahrenheit, etc.). Fig.10In the example shown, the frame attachment points 812, 814 and the block attachment points 608, 610 of the first thrust link 602 and the second thrust link 604 are closer to the core engine 120 than the third frame attachment point 816 and the third block attachment point 804 of the third thrust link 802. Therefore, the first thrust link 602 and the second thrust link 604 are closer to the core engine 120 than the third thrust link 802. The closer proximity of the thrust links 602, 604 to the core engine 120 and the location of the third thrust link 802 on the branch 811 cause the operating temperature of the thrust links 602, 604 to be greater than the operating temperature of the third thrust link 802.

[0097] The linear expansion of a component due to temperature changes is described in formula (1):

[0098] ΔL=αLΔT (1)

[0099] Where ΔL is the change in length, α is the linear thermal expansion coefficient of the component's material, L is the original length of the component, and ΔT is the temperature change of the component. Fig.10 In the illustrated example, the first length 1004 of the thrust links 602, 604 is greater than the second length 1006 of the third thrust link 802. Because the thrust links 602, 604 are greater in length (e.g., greater L, etc.) and are subject to greater temperature changes (e.g., greater ΔT, etc.) than the third thrust link 802, during operation of the gas turbine engine 100, the thrust links 602, 604 are more susceptible to thermal expansion (e.g., greater ΔL, etc.) than the third thrust link 802. In some examples, the thermal expansion of the thrust links 602, 604 greater than the thermal expansion of the third thrust link 802 may generate bending stresses in the second frame portion 204 and / or deformations in the core engine 120. For example, thermal expansion of the thrust links 602, 604, 802 may cause the thrust links 602, 604, 802 to apply a pitch moment between the frame attachment points 812, 814 and the third frame attachment point 816 (e.g., thermal expansion of the thrust links 602, 604 pushes the bottom of the second frame portion 204 along the roll axis and causes the second frame portion 204 to pivot about the third frame attachment point 816, etc.).

[0100] In some examples, to reduce bending deformation caused by thermal expansion of the thrust links 602, 604, 802, the thrust links 602, 604, 802 can be made of materials with different thermal expansion coefficients. For example, the first thrust link 602 and the second thrust link 604 can be made of a first material having a lower thermal expansion coefficient than the second material of the third thrust link 802. For example, the thrust links 602, 604 can be made of nickel alloy 909 (e.g., 909, etc.), and the third thrust link 802 may be made of nickel alloy 718 (e.g., 718, etc.), because the thermal expansion coefficient of nickel alloy 718 is 40% greater than that of nickel alloy 909. In other examples, the thrust links 602, 604, 802 may be made of any other material with a different coefficient. Additionally or alternatively, the length 1004, 1006 and / or material of the thrust links 602, 604, 802 may be selected so that formula (2) holds true:

[0101] α1L1ΔT1≈α2L2ΔT2(2)

[0102] Wherein α1 is the linear thermal expansion coefficient of the material of the thrust links 602 and 604, α2 is the linear thermal expansion coefficient of the material of the thrust link 802, L1 is the original length of the thrust links 602 and 604 (e.g., the room temperature length of the thrust links 602 and 604, etc.), L2 is the original length of the thrust link 802 (e.g., the room temperature length of the third thrust link 802, etc.), ΔT1 is the temperature change experienced by the thrust links 602 and 604, and ΔT2 is the temperature change experienced by the third thrust link 802. Formula (2) includes the symbol "≈". As used herein, the symbol "≈" indicates that two quantities associated with the symbols are approximately equal. In some examples, Fig. 9 The thrust link of the third thrust link configuration 900 (eg, Fig. 9 The material and length of the thrust links (602, 604, 902, etc.) can be similarly constructed based on formula (2).

[0103] The first front mounting member 1001 is similar to Figure 2 The first front mount 210 is provided with an elastomeric bearing 1008 in addition to the first front mount 1001. The elastomeric bearing 1008 is disposed in a load path between the gas turbine engine 1002 and the pylon 208 through the first front mount 1001. Fig.10In the example shown, the elastomeric bearing 1008 is an elastomeric bushing disposed around a pin of the first front mount 1001. In other examples, the elastomeric bearing 1008 is disposed at another appropriate location in the load path through the first front mount 1001. The relatively low stiffness of the elastomeric bearing 1008 relieves stresses associated with thermal expansion of the gas turbine engine 1002 during operation and static indeterminacy of the engine mounting system 1000. That is, the bending moment transmitted through the gas turbine engine 1002 is relieved (e.g., partially released, fully released, etc.) via deformation of the elastomeric bearing 1008 associated with small displacements of the gas turbine engine 1002 relative to the hanger 208. In some examples, the elastomeric bearing 1008 includes one or more of natural rubber, silicone rubber, thermoplastic elastomer, synthetic rubber, etc. In other examples, the first front side mount 1001 is made of Figure 2 The first front mount 210 is implemented without the elastomeric bearing 1008 .

[0104] Fig.11 Yes Figure 8 The second thrust connecting rod structure 800, Fig.10 The first front mounting member 1001 and Figure 2 A perspective view of another example engine mounting system 1100 of the second front mounting member 212 is shown. The engine mounting system 1100 is similar to Fig.10 The engine mounting system 1000, except that the engine mounting system 1100 includes another example rear mounting member 1102 instead of Figure 5A , 5B and 10 rear mounting pieces 500. Fig.11 In the example shown, the engine mounting system 1100 will Fig.10 The gas turbine engine 1002 is coupled to Figure 2 and 10 The hanger 208. Fig.11 In the illustrated example, the engine mounting system 1100 includes Figure 8 The second thrust link 800.

[0105] and Fig.10Similar to the engine mounting system 1000 of FIG. 1 , the engine mounting system 1100 is overconstrained (e.g., statically indeterminate, etc.). Therefore, the components of the engine mounting system 1100 and the gas turbine engine 1002 are sensitive to thermal stresses on the engine mounting system 1100 (e.g., thermal expansion of the components of the engine mounting system 1100 may introduce internal stresses into the gas turbine engine 1002 and the engine mounting system 1100, etc.). In some examples, the thrust links 602, 604, 802 may be designed based on equation (2). That is, the length and material of the thrust links 602, 604, 802 may be selected to mitigate (e.g., prevent, reduce, etc.) internal deformation caused by thermal expansion of the engine mounting system 1100 and the gas turbine engine 1002.

[0106] Rear mount 1102 is another rear mount implemented according to the teachings of the present disclosure and can be used to implement Figure 2 The rear mounting member 214. Fig.11 In the example shown, the rear mount 1102 includes a leaf spring 1104, a mounting member 1106, and a hanger connector 1108. The leaf spring 1104 is an elastic element that resists the tension applied between the hanger connector 1108 and the third frame portion 206. Fig.11 In the example shown, the leaf spring 1104 is disposed in the load path between the pylon 208 and the third frame portion 206 such that the leaf spring 1104 reacts to negative vertical loads (e.g., gravity loads, aerodynamic loads, maneuvering loads, etc.) transmitted between the pylon 208 and the third frame portion 206. In some examples, the leaf spring 1104 also reacts to positive vertical loads (e.g., aerodynamic loads, maneuvering loads, etc.). In some examples, the geometry and / or material of the leaf spring 1104 may be selected to reduce deformation associated with gravity and maneuvering loads and to reduce deformation associated with bending moments transmitted between the aft mount 1102 and the forward mount 212, 1001. For example, the thickness of the leaf spring 1104, the thickness profile of the leaf spring 1104, and / or the length of the leaf spring 1104 may be used to change the stiffness of the aft mount 1102 and to modify deformation associated with reacting bending moments associated with the gas turbine engine 1002 via the engine mounting system 1100.

[0107] Leaf spring 1104 may be constructed of any suitable rigid material (e.g., nickel alloy, steel, titanium, etc.) that is resistant to plastic deformation. In some examples, to reduce internal stress on gas turbine engine 1002 caused by thermal expansion of leaf spring 1104, leaf spring 1104 and / or mounting member 1106 may be constructed of a material having a relatively low coefficient of thermal expansion (e.g., nickel alloy 909, etc.). Fig.11In the example shown, the leaf spring 1104 includes a single spring leaf (e.g., a single strip of material, etc.) In other examples, the leaf spring 1104 may include multiple spring leaves (e.g., two spring leaves, three spring leaves, five spring leaves, etc.), which may modify the stiffness of the rear mount 1102 (e.g., the spring response of the leaf spring 1104 is non-linear, etc.).

[0108] The hanger connector 1108 connects the rear mount 1102 to the hanger 208. In some examples, the hanger connector 1108 can be connected by a pin link and / or a U-shaped clip (e.g., similar to Figure 3 The hanger connector 302 is similar to Figure 4 In other examples, the hanger connector 1108 may be implemented by a dart-type link, a crossbar-type link, a ball joint, a cotter joint, etc. Figures 12A-12G Example couplings that may be used to couple rear mount 1102 to third frame portion 206 are described.

[0109] exist Fig.11 In the example shown, the mounting member 1106 is a rigid structural member that extends between the hanger coupling 1108 and the third frame portion 206 and reacts vertical loads transmitted therebetween. Fig.11 In the example shown, the mounting member 1106 is a rod-shaped member. In other examples, the mounting member 1106 can be implemented by a cylindrical member, a prismatic member, a tube, etc. The mounting member 1106 can be made of any suitable rigid material, including the same material as the leaf spring 1104, steel, titanium, aluminum, nickel alloys, etc.

[0110] Fig. 12A is an example first frame connector 1200 Fig.11 A front view of the rear mounting member 1102. Fig. 12A In the example shown, the leaf spring 1104 includes a first eye 1201A and a second eye 1201B. Fig. 12A In the example shown, the first frame connector 1200 includes a first pin link 1202 and a first swing link 1204A. Fig. 12A In the example shown, the first pin link 1202 includes a first pin 1206 and a first mounting boss 1208. Fig. 12B In the example shown, the first swing link 1204A includes a second pin 1210 , a third pin 1212 , a second mounting boss 1214 , and a link member 1216 .

[0111] exist Fig. 12AIn the example shown, the mounting bosses 1208, 1214 are plates (e.g., sheet-like members, etc.) fixedly coupled to and extending from the third frame portion 206. In other examples, one or both of the mounting bosses 1208, 1214 may be integral with the third frame portion 206. The first pin link 1202 is formed via the first pin 1206 through the coupling of the first eye 1201A of the leaf spring 1104 and the first mounting boss 1208. The first pin link 1202 reacts forces in the yaw and pitch directions. Fig. 12A In the example shown, the first swing link 1204A is formed by: (1) the connection of the second pin 1210 through the second eye 1201B of the leaf spring 1104 and the link member 1216, and (2) the connection of the third pin 1212 through the link member 1216 and the second mounting boss 1214. The first swing link 1204A reacts to forces in the negative yaw direction. Therefore, the combined use of the first swing link 1204A and the first pin link 1202 allows the first frame coupling 1200 to react only to forces in the negative yaw direction. By releasing pitch and positive yaw reactions through the first swing link 1204A and allowing small relative displacements between the rear mounting member 1102 and the third frame portion 206 in the pitch and positive yaw directions, the first frame coupling 1200 facilitates thermal expansion of the leaf spring 1104, the mounting member 1106 and / or the third frame portion 206.

[0112] Fig. 12B is an example second frame connector 1218 Fig.11 12. A front view of the rear mount 1102. The second frame link 1218 includes a first swing link 1204A and is similar to the first frame link 1200, except that the second frame link 1218 includes a second swing link 1204B instead of the first pin link 1202. Fig. 12A In the example shown, the second swing link 1204B is formed by: (1) the connection of the fourth pin 1220 through the first eye 1201A of the leaf spring 1104 and the second link member 1222, and (2) the connection of the fifth pin 1224 through the second link member 1222 and the second mounting boss 1214. Similar to the first swing link 1204A, the second swing link 1204B reacts to the forces in negative yaw. Therefore, the second frame coupling 1218 facilitates thermal expansion of the leaf spring 1104, the mounting 1106 and / or the third frame portion 206 by relieving the pitch and positive yaw reactions via the first and second swing links 1204A, 1204B and allowing small relative displacements between the rear mounting 1102 and the third frame portion 206 in the pitch and positive yaw directions.

[0113] Fig. 12C The third frame connector 1225 is included Fig.11 A front view of the rear mounting member 1102. The third frame connecting member 1225 includes Fig. 12A The first pin link 1202 is similar to Fig. 12A The first frame link 1200, except that the third frame link 1225 includes a first radial groove link 1226A instead of Fig. 12A The first swing link 1204A. Fig. 12C In the example shown, the first radial groove link 1226A is composed of Fig. 12A The second pin 1210 passes through the second eye 1201B and through Fig. 12A The connection of the first groove 1228 of the second mounting boss 1214 is formed. Fig. 12C In the example shown, the first slot 1228 has a radial orientation in the second mounting boss 1214. That is, the first slot 1228 has a major axis oriented along an axis perpendicular to the axial centerline of the third frame portion 206. The first slot 1228 enables the second pin 1210 to move within the first slot 1228 during operation of the gas turbine engine 1002. The radial orientation of the first slot 1228 facilitates movement of the second pin 1210 in the yaw direction and the radial direction. Therefore, the first radial slot link 1226A only reacts forces in negative yaw. Therefore, the combined use of the first radial slot link 1226A and the first pin link 1202 enables the third frame coupling 1225 to only react forces in the negative yaw direction. The third frame connector 1225 facilitates thermal expansion of the leaf spring 1104, the mount 1106 and / or the third frame portion 206 by releasing pitch and yaw reactions via the first radial slot link 1226A and allowing small relative displacements between the rear mount 1102 and the third frame portion 206 in the pitch and yaw directions.

[0114] Fig.12D The fourth frame connector 1230 includes an example Fig.11 The fourth frame connecting member 1230 includes Fig.12D The first radial groove connecting rod 1226A, and similar to Fig. 12C The third frame link 1225, except that the fourth frame link 1230 includes a second radial groove link 1226B instead of the first pin link 1202. Fig.12DIn the example shown, the second radial slot link 1226B is formed by: (1) coupling of the first pin 1206 through the first eye 1201A of the leaf spring 1104 and the second slot 1232 in the first mounting boss 1208. Like the first radial slot link 1226A, the second radial slot link 1226B reacts forces in the negative yaw direction. Thus, the fourth frame coupling 1230 facilitates thermal expansion of the leaf spring 1104, the mount 1106, and / or the third frame portion 206 by relieving pitch and positive yaw reactions via the radial slot links 1226A, 1226B and allowing small relative displacements between the rear mount 1102 and the third frame portion 206 in the pitch and positive yaw directions.

[0115] Fig.12E The fifth frame connector 1234 includes an example Fig.11 The fifth frame connector 1234 includes Fig. 12A The first pin link 1202, and similar to Fig. 12A The first frame connector 1200, except that the fifth frame connector 1234 includes a first lateral groove link 1236A instead of Fig. 12A The first swing link 1204A. Fig.12E In the example shown, the first lateral groove link 1236A is composed of Fig. 12A The second pin 1210 passes through the second eye 1201B and through Fig. 12A The second lateral groove 1240 of the second mounting boss 1214 is formed by the connection. That is, the second lateral groove 1240 has a major axis oriented along the pitch axis. The second lateral groove 1240 enables the second pin 1210 to move in the second lateral groove 1240 during operation of the gas turbine engine 1002. The lateral orientation of the second lateral groove 1240 facilitates the movement of the second pin 1210 in the pitch direction. Therefore, the first lateral groove link 1236A only reacts to forces in the negative yaw direction. Therefore, the combined use of the first lateral groove link 1236A and the first pin link 1202 enables the fifth frame connector 1234 to only react to forces in the negative yaw direction. The fifth frame connector 1234 facilitates thermal expansion of the leaf spring 1104, the mount 1106 and / or the third frame portion 206 by releasing pitch and yaw reactions via the first lateral slot link 1236A and allowing small relative displacements between the rear mount 1102 and the third frame portion 206 in the pitch and yaw directions.

[0116] Fig.12F The sixth frame connector 1238 includes an example Fig.11 The sixth frame connector 1238 includes a first lateral slot connector 1236A and is similar to Fig.12EThe fifth frame link 1234, except that the sixth frame link 1238 includes a second lateral slot link 1236B instead of the first pin link 1202. Fig.12F In the example shown, the second lateral slot link 1236B is formed by coupling the first pin 1206 through the first eye 1201A of the leaf spring 1104 and the second lateral slot 1240 in the first mounting boss 1208. Like the first lateral slot link 1236A, the second lateral slot link 1236B reacts loads on negative yaw. Thus, the sixth frame coupling 1238 facilitates thermal expansion of the leaf spring 1104, the mounting 1106, and / or the third frame portion 206 by relieving pitch and positive yaw reactions via the lateral slot links 1236A, 1236B and allowing small relative displacements between the rear mounting 1102 and the third frame portion 206 in the pitch and positive yaw directions.

[0117] Figure 12G The seventh frame connector 1241 includes an example Fig.11 The seventh frame connecting member 1241 includes Fig. 12A The first pin link 1202 and the example second pin link 1242. The example second pin link 1242 is similar to Fig. 12A The first pin connecting rod 1202. Fig. 12A In the example shown, the second pin link 1242 is formed via the coupling of the second pin 1210 through the second eye 1201B of the leaf spring 1104 and the second mounting boss 1214. The seventh frame link 1241 reacts loads in positive and negative yaw and pitch directions.

[0118] As can be appreciated from the foregoing, example systems, apparatus, articles, and methods have been disclosed to reduce engine body deformation associated with operational deformations caused by bending moments associated with thrust, aerodynamic, and / or propeller loads, and to reduce deformations caused by gravity loads associated with cantilever core engines. The example mounting systems disclosed herein include a rear mount having a resilient member that provides a relatively reduced stiffness of the connection between the rear frame and the pylon. The examples disclosed herein facilitate tighter blade tip clearances, particularly in cantilever open rotor gas turbine engines, which can provide increased engine performance and reduced fuel consumption. The examples disclosed herein include a mounting configuration of multiple thrust links with lateral and vertical displacements, which enables reaction of yaw and / or pitch moments via the thrust links.

[0119] Methods and apparatus for mounting a gas turbine engine to a pylon are disclosed herein. Other examples and combinations thereof include the following:

[0120] A gas turbine engine comprises: a first mounting member; a first frame portion, the first frame portion being coupled to a hanger via the first mounting member; a second frame portion, the second frame portion being coupled to the first frame portion so that the second frame portion is cantilevered from the first frame portion; and a second mounting member, the second mounting member coupling the second frame portion to the hanger, the second mounting member defining a load path between the hanger and the second frame portion, the second mounting member comprising an elastic element disposed in the load path.

[0121] A gas turbine engine according to any preceding clause, wherein the elastic element is an elastomer.

[0122] A gas turbine engine according to any one of the preceding clauses, wherein the second mounting member comprises: a frame coupling member; a hanger coupling member, the hanger coupling member comprising: a bracket, the bracket being coupled to the hanger; and a load plate, the load plate being movably disposed within the bracket; wherein the elastomer is disposed between the load plate and the bracket; and a structural member, the structural member extending between the frame coupling member and the hanger coupling member, the structural member being coupled to the load plate.

[0123] The gas turbine engine according to any of the preceding clauses, wherein the elastomer is a first elastomer, and further comprising a second elastomer disposed between the load plate and the pylon.

[0124] A gas turbine engine according to any of the preceding clauses, wherein the elastic element is a leaf spring.

[0125] A gas turbine engine according to any of the preceding clauses, wherein the resilient element is a coil spring.

[0126] A gas turbine engine according to any of the preceding clauses, wherein the second mounting member comprises: a first member, the first member being coupled to the hanger; a second member, the second member being coupled to the second frame portion; a flange, the flange being coupled to the first member; and a pin, the pin extending through the first member and the second member, the disc spring being disposed between the flange and the pin.

[0127] A gas turbine engine according to any of the preceding clauses, wherein the coil spring is a first coil spring and the second mount further comprises: a mounting plate coupled to the hanger and the second member; and a second coil spring disposed between the flange and the mounting plate.

[0128] A gas turbine engine according to any of the preceding clauses, wherein the first component has a hollow interior, the second component is arranged in the hollow interior so that a gap is formed between the outer diameter of the second component and the inner diameter of the first component, and the pin and the gap facilitate rotation of the first component relative to the second component.

[0129] A gas turbine engine according to any of the preceding clauses, wherein the second mount comprises a slot via which the second frame portion is coupled to the second mount, the slot facilitating rotation relative to the pylon about a yaw axis.

[0130] The gas turbine engine according to any of the preceding clauses, further comprising: a first thrust link, the first thrust link extending between the third frame portion and the hanger at a first block attachment point; a second thrust link, the second thrust link extending between the third frame portion and the hanger at a second block attachment point, the second block attachment point being laterally displaced from the first block attachment point; and a third thrust link extending between the third frame portion and a third block attachment point, the third block attachment point being vertically displaced from the first block attachment point.

[0131] A gas turbine engine according to any of the preceding clauses, wherein the first thrust link has a first length and comprises a first material, and the third thrust link has a second length and comprises a second material, the first length being greater than the second length, the first material having a lower coefficient of thermal expansion than the second material.

[0132] An apparatus comprises: a first mount coupling a first frame portion of a gas turbine engine to a hanger; and a second mount coupling a second frame portion of the gas turbine engine to the hanger, the second mount comprising a resilient element, the second frame portion being cantilevered relative to the first frame portion, the second mount defining a load path between the hanger and the second frame portion, wherein the resilient element is disposed in the load path.

[0133] Apparatus according to any preceding clause wherein the resilient element is an elastomer.

[0134] An apparatus according to any one of the preceding clauses, wherein the second mounting member comprises: a frame coupling member; a hanger coupling member, the hanger coupling member comprising: a bracket, the bracket being coupled to the hanger; and a load plate, the load plate being movably disposed within the bracket; wherein the elastomer is disposed between the load plate and the bracket; and a structural member extending between the frame coupling member and the hanger coupling member, the structural member being coupled to the load plate.

[0135] Apparatus according to any preceding clause, wherein the resilient element is a spring.

[0136] The apparatus of any of the preceding clauses, wherein the second mount further comprises at least one of a slot link or a swing link coupling the eye of the spring to the second frame portion.

[0137] An apparatus according to any of the preceding clauses, wherein the second mounting member further comprises: a first member, the first member being coupled to the hanger; a second member, the second member being coupled to the second frame portion; a flange, the flange being coupled to the first member; and a pin, the pin extending through the first member and the second member, the spring being disposed between the flange and the pin.

[0138] The apparatus of any of the preceding clauses, wherein the spring is a first spring and the second mount further comprises: a mounting plate coupled to the hanger and the second member; and a second spring disposed between the flange and the mounting plate.

[0139] An apparatus according to any of the preceding clauses, wherein the first member has a hollow interior, the second member is arranged within the hollow interior so that a gap is formed between the outer diameter of the second member and the inner diameter of the first member, and the pin and the gap facilitate rotation of the first member relative to the second member.

[0140] The following claims are incorporated by reference into this detailed description. Although certain example systems, devices, articles, and methods have been disclosed herein, the coverage of this patent is not limited thereto. On the contrary, this patent covers all systems, devices, articles, and methods that fully fall within the scope of the claims of this patent.

Claims

1. A gas turbine engine, characterized in that: include: a first mounting member; a first frame portion coupled to a hanger via the first mount; a second frame portion coupled to the first frame portion such that the second frame portion is cantilevered from the first frame portion; and A second mount couples the second frame portion to the hanger, the second mount defining a load path between the hanger and the second frame portion, the second mount including a resilient element disposed in the load path.

2. The gas turbine engine according to claim 1, characterized in that The elastic element is an elastomer.

3. The gas turbine engine according to claim 2, characterized in that The second mounting member comprises: Frame connectors; A hanger coupling member, the hanger coupling member comprising: a bracket coupled to the hanger; and a load plate, the load plate being movably disposed in the bracket; wherein the elastic body is disposed between the load plate and the bracket; and A structural member extends between the frame coupling and the hanger coupling, the structural member being coupled to the load plate.

4. The gas turbine engine according to claim 3, characterized in that The elastic body is a first elastic body, and further includes a second elastic body, wherein the second elastic body is arranged between the load plate and the hanger.

5. The gas turbine engine according to claim 1, characterized in that The elastic element is a leaf spring.

6. The gas turbine engine according to claim 1, characterized in that The elastic element is a coil spring.

7. The gas turbine engine according to claim 6, characterized in that The second mounting member comprises: a first member coupled to the hanger; a second member coupled to the second frame portion; a flange coupled to the first member; and A pin extends through the first member and the second member, and the coil spring is disposed between the flange and the pin.

8. The gas turbine engine according to claim 7, characterized in that wherein the coil spring is a first coil spring, and the second mounting member further comprises: a mounting plate coupled to the hanger and the second member; and A second coil spring is disposed between the flange and the mounting plate.

9. The gas turbine engine according to claim 7, characterized in that The first member has a hollow interior, the second member is disposed within the hollow interior such that a gap is formed between an outer diameter of the second member and an inner diameter of the first member, and the pin and the gap facilitate rotation of the first member relative to the second member.

10. The gas turbine engine according to claim 1, characterized in that Wherein the second mount includes a slot via which the second frame portion is coupled to the second mount, the slot facilitating rotation relative to the pylon about a yaw axis.

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