Gas turbine mounting configuration to mitigate bending

Abstract

A gas turbine mounting configuration for mitigating trunk bending is described herein. An example gas turbine engine disclosed herein includes a pylon; an inlet subjected to an inlet load along an inlet load axis; a shell assembly comprising a first shell portion and a second shell portion; a forward mounting member coupling the first shell portion to the pylon, the forward mounting member coupling to the pylon defining a first line of action; an aft mounting member; and a thrust link coupling the second shell portion to the pylon, the thrust link defining a second line of action, the intersection of the first line of action and the second line of action being located at least one of: (1) on the inlet load axis and on the centerline, (2) downstream of the inlet load axis and below the centerline, and (3) upstream of the inlet load axis and above the centerline.

Description

Technical Field

[0001] The present disclosure relates generally to gas turbine engines and, more particularly, to gas turbine mounting configurations for mitigating bending. Background Art

[0002] Turbine engines are some of the most widely used power generation technologies, commonly used in aircraft and power generation applications. Turbine engines typically include a fan and a core arranged in flow communication with each other. The core of a turbine engine typically includes, in serial flow order, a compressor section, a combustion section, a turbine section coaxially with the compressor section, and an exhaust section. Typically, a casing or outer shell surrounds the turbine engine core. BRIEF DESCRIPTION OF THE DRAWINGS

[0003] Figure 1 is a cross-sectional view of a gas turbine engine in which examples disclosed herein may be implemented.

[0004] FIG2 is a schematic diagram of an existing installation configuration.

[0005] Figure 3 is a schematic diagram of a mounting configuration implemented according to the teachings of the present disclosure.

[0006] Figure 4 is a cross-sectional view of a second mounting configuration implemented in accordance with the teachings of the present disclosure.

[0007] Figure 5 is a cross-sectional view of a third mounting configuration implemented in accordance with the teachings of the present disclosure.

[0008] The drawings are not to scale. Generally, the same reference numerals will be used throughout the drawings and the accompanying written description to refer to the same or similar parts. As used in this patent, a statement that any part (e.g., a layer, film, zone, region, or plate) is in any way on (e.g., positioned on, located on, disposed on, or formed on, etc.) another part indicates that the part is in contact with the other part, or that the part is above the other part with one or more intermediate parts located between the two. As used herein, a connection reference (e.g., attaching, coupling, connecting, and joining) may include intermediate members between the elements referred to by the connection reference and / or relative movement between these elements, unless otherwise indicated. Therefore, a connection reference does not necessarily infer that two elements are directly connected and / or are in a fixed relationship to each other. As used herein, a statement that any part is "in contact" with another part means that there is no intermediate part between the two parts.

[0009] Some drawings are depicted herein in which portions are cross-hatched in cross-section to indicate those portions. To distinguish between the different portions shown in the drawings, different cross-hatching patterns are applied to the different portions. The different cross-hatching patterns should not be interpreted as implying any relationship between the portions. Furthermore, the use of the same cross-hatching pattern on different drawings should not be interpreted as implying any relationship between the portions having the same cross-hatching pattern.

[0010] In the following detailed description, reference is made to the accompanying drawings forming a part thereof, wherein specific examples that can be put into practice are shown by way of example. These examples are described in sufficient detail to enable those skilled in the art to practice this theme, and it should be understood that other examples may also be used. Therefore, the following detailed description is provided to describe exemplary embodiments, rather than to limit the scope of the theme described in this disclosure. Certain features from the different aspects described below can be combined to form another new aspect of the theme discussed below. DETAILED DESCRIPTION

[0011] Compressor blade tip clearance in gas turbine engines is reduced due to operational deformations caused by internal forces within the gas turbine engine. Specifically, thrust and air inlet loads can generate internal bending moments in the gas turbine engine, which can cause the gas turbine engine to bend between its mountings (e.g., mounting points attached to these locations, etc.). Examples disclosed herein include engine casings and / or mounting configurations that reduce trunk bending by applying inlet and thrust loads in opposite directions, thereby reducing the net bending moment applied to the gas turbine engine.

[0012] A turbine engine, also referred to herein as a gas turbine engine, is an internal combustion engine that uses atmospheric air as a moving fluid. In operation, atmospheric air enters the turbine engine via a fan and flows through a compressor section, where one or more compressors gradually compress (e.g., pressurize, etc.) the air until it reaches the combustion section. In the combustion section, the pressurized air is combined with fuel and ignited to produce a high-temperature, high-pressure gas stream (e.g., hot combustion gases) before the gas stream enters the turbine section of the turbine engine. The hot combustion gases expand as they flow through the turbine section, rotating the blades of one or more turbines. The rotating blades of the turbine generate a spool work output that powers the corresponding compressor. A spool is a combination of a compressor, a shaft, and a turbine. A turbine engine typically includes multiple spools, such as a high-pressure spool (e.g., an HP compressor, a shaft, and a turbine) and a low-pressure spool (e.g., an LP compressor, a shaft, and a turbine). In additional or alternative examples, a turbine engine may include one spool or more than two spools.

[0013] "Include" and "comprising" (and all their forms and tenses) are used herein as open-ended terms. Thus, whenever a claim employs any form of "include" or "comprising" (e.g., includes, comprises, has, etc.) as a preamble or in any type of claim recitation, it is understood that additional elements, terms, etc. may be present without falling outside the scope of the corresponding claim or recitation. As used herein, the phrase "at least" when used as a transition term, such as in a claim preamble, 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) A only, (2) B only, (3) C only, (4) A and B, (5) A and C, (6) B and C, or (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 refer to embodiments that include any of the following: (1) at least one A, (2) at least one B, or (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 refer to embodiments that include any of the following: (1) at least one A, (2) at least one B, or (3) at least one A and at least one B. As used herein in the context of describing the performance or execution of processes, instructions, actions, activities, and / or steps, the phrase "at least one of A and B" is intended to refer to embodiments that include any of the following: (1) at least one A, (2) at least one B, or (3) at least one A and at least one B. Similarly, as used herein in the context of describing the performance or execution of a process, instruction, action, activity, and / or step, the phrase "at least one of A or B" is intended to refer to an embodiment that includes any of the following: (1) at least one A, (2) at least one B, or (3) at least one A and at least one B.

[0014] As used herein, singular references (such as "a", "an", "first", "second", etc.) do not exclude the plural. As used herein, the term "a" or "an" object refers to one or more of the object. The terms "a" (or "an"), "one or more" and "at least one" are used interchangeably herein. In addition, although listed separately, multiple devices, elements or method actions can be implemented by, for example, the same entity or object. In addition, although individual features can be included in different examples or claims, these features can be combined, and inclusion in different examples or claims does not mean that the combination of features is not feasible and / or disadvantageous.

[0015] Unless otherwise specified, descriptors such as "first," "second," and "third" are used herein without in any way implying or otherwise indicating any meaning of priority, physical order, arrangement in a list, and / or ordering, but are merely used as labels and / or arbitrary names to distinguish elements to facilitate understanding of the disclosed examples. In some examples, the descriptor "first" may be used to refer to an element in the detailed description, while the same element may be referred to by a different descriptor (e.g., "second" or "third") in the claims. In such cases, it should be understood that such descriptors are only used to clearly identify elements that might otherwise share the same name, for example.

[0016] As used herein throughout the specification and claims, approximating language is used to modify any quantitative representation that could be permissibly varied without resulting in a change in the basic function to which it is related. Accordingly, a value modified by one or more terms (e.g., "approximately," "approximately," and "substantially") is not limited to the precise value specified. In some examples used herein, the term "substantially" is used to describe a relationship between two parts that is within three degrees of the stated relationship (e.g., a substantially collinear relationship is within three degrees of linearity, a substantially perpendicular relationship is within three degrees of perpendicularity, a substantially parallel relationship is within three degrees of parallelism, a substantially flush relationship is within three degrees of flushness, etc.).

[0017] The terms "upstream" and "downstream" refer to the relative directions of fluid flow in a fluid path. 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. Various terms are used herein to describe the orientation of features. As used herein, the orientation of features, forces and moments are described with reference to the yaw axis, pitch axis and roll axis of the vehicle with which the features, forces and moments are associated. Typically, the drawings are annotated with a set of axes, including a yaw axis Y, a roll axis R and a pitch axis P. As used herein, the terms "longitudinal" and "axial" are used interchangeably to refer to directions parallel to the roll axis. As used herein, the term "lateral" is used to refer to directions parallel to the pitch axis. As used herein, the terms "vertical" and "orthogonal" are used interchangeably to refer to directions parallel to the yaw axis.

[0018] Cold blade tip clearances (e.g., blade tip clearances when the engine is not operating, etc.) and the resulting operating clearances of the compressor and / or fan are typically defined (e.g., designed, etc.) based on clearance closure during a takeoff (TO) rotational maneuver (e.g., the TO rotational maneuver is a clearance pinch point at several locations / engine stages throughout the engine, etc.). That is, in some examples, the minimum blade tip clearances (e.g., the closest clearances, etc.) in the fan, compressor, low-pressure turbine, and / or high-pressure turbine occur during TO engine operation. Therefore, the minimum blade tip clearance at which the engine can operate is based on a clearance reduction under a minimum clearance condition (also known as a "pinch point"), which typically occurs during takeoff (e.g., the takeoff flight phase, etc.). The clearance reduction at the pinch point may be caused by axisymmetric closure caused by engine vibration, heat, and mechanical component deflection, as well as deformation caused by engine operation (e.g., strain, etc.). The operational deformation of the engine may be caused by internal forces generated by thrust and / or air inlet loads in the engine. The engine body may flex between the forward and aft mounting attachment points of the engine to the aircraft. To prevent the blade tips from intruding into the engine case, many compressors are designed to accommodate the reduction in blade tip clearance during takeoff. However, this adaptation also creates larger clearances during other flight phases, which reduces engine performance during these phases. Thus, reducing the trunk bending caused by thrust and inlet loads enables the compressor to have smaller (e.g., tighter, etc.) tip clearances, which improves engine performance (e.g., specific fuel consumption, thrust output, etc.) throughout the entire operating phase.

[0019] Example mounting and casing configurations disclosed herein mitigate these deformations by causing the inlet load bending moment and the thrust load bending moment to act in opposite directions. In some examples disclosed herein, a mounting configuration for a gas turbine engine includes a forward mount, an aft mount, and a thrust link. In some such examples disclosed herein, the forward mount defines a first line of action, while the thrust link defines a second line of action. As used herein, a "line of action" is a vector along which a force acts. In some such examples disclosed herein, the intersection of the first and second lines of action is on the opposite side of the gas turbine engine's centerline from the forward mount, the aft mount, the thrust link, and the pylon. In other such examples disclosed herein, the intersection of the first and second lines of action is forward of the applied inlet load. In some examples disclosed herein, during certain conditions / flight phases (e.g., takeoff), the bending moment associated with the gas turbine's thrust and the bending moment associated with the inlet load act in opposite directions, which reduces the net bending moment on the gas turbine engine.

[0020] Referring now to the drawings, wherein like numerals represent like elements throughout, Figure 11 is a schematic cross-sectional view of a turbofan gas turbine engine 100 ("turbofan engine 100"). Although the illustrated example is a high-bypass turbofan engine, the principles of the present disclosure may also be applied to other types of engines, such as low-bypass turbofan engines, turbojet engines, turboprop engines, etc. Figure 1 As shown, turbofan engine 100 defines a longitudinal or axial centerline axis 102 extending therethrough for reference. Generally, turbofan engine 100 may include a core turbine 104 or gas turbine engine disposed downstream of a fan section 106 . Figure 1 Annotated directional diagrams referencing the axial direction A, the circumferential direction C, and the radial direction R are also included.

[0021] The core turbine 104 generally includes a substantially tubular outer casing 108 ("turbine casing 108") that defines an annular inlet 110. The casing 108 can be formed from a single casing or multiple casings. The casing 108 encloses a compressor section having a supercharger or low-pressure compressor 112 ("LP compressor 112") and a high-pressure compressor 114 ("HP compressor 114"), a combustion section 116, a turbine section having a high-pressure turbine 118 ("HP turbine 118") and a low-pressure turbine 120 ("LP turbine 120"), and an exhaust section 122 in a serial flow relationship. A high-pressure shaft or spool 124 ("HP shaft 124") drivingly couples the HP turbine 118 and the HP compressor 114. A low-pressure shaft or spool 126 ("LP shaft 126") drivingly couples the LP turbine 120 and the LP compressor 112. The LP shaft 126 may also be coupled to a fan spool or shaft 128 (“fan shaft 128 ”) of the fan section 106 . In some examples, the LP shaft 126 may be directly coupled to the fan shaft 128 (i.e., a direct drive configuration). In an alternative configuration, the LP shaft 126 may be coupled to the fan shaft 128 via a reduction gearbox 130 (e.g., an indirect drive or gear drive configuration).

[0022] like Figure 1 As shown, fan section 106 includes a plurality of fan blades 132 coupled to and extending radially outward from fan shaft 128. An annular fan casing or nacelle 134 (also referred to herein as a fan case) circumferentially surrounds fan section 106 and / or at least a portion of core turbine 104. Nacelle 134 is supported relative to core turbine 104 by a plurality of circumferentially spaced outlet guide vanes 136. In addition, a downstream section 138 of nacelle 134 may surround the exterior of core turbine 104 to define a bypass airflow passage 140 therebetween.

[0023] like Figure 1As shown, during operation of turbofan engine 100, air 142 enters an inlet portion 144 of turbofan engine 100. A first portion 146 of air 142 flows into bypass airflow passage 140, while a second portion 148 of air 142 flows into inlet 110 of LP compressor 112. One or more sequential stages of LP compressor stator blades 150 and LP compressor rotor blades 152 coupled to LP shaft 126 progressively compress the second portion 148 of air 142 flowing through LP compressor 112 on its way to HP compressor 114. Next, one or more sequential stages of HP compressor stator blades 154 and HP compressor rotor blades 156 coupled to HP shaft 124 further compress the second portion 148 of air 142 flowing through HP compressor 114. This provides compressed air 158 to combustion section 116, where the compressed air 158 is mixed with fuel and combusted to provide combustion gases 160.

[0024] The combustion gases 160 flow through the HP turbine 118, where one or more sequential stages of HP turbine stator blades 162 and HP turbine rotor blades 164 coupled to the HP shaft 124 extract a first portion of the kinetic and / or thermal energy from the combustion gases 160. This energy extraction supports the operation of the HP compressor 114. The combustion gases 160 then flow through the LP turbine 120, where one or more sequential stages of LP turbine stator blades 166 and LP turbine rotor blades 168 coupled to the LP shaft 126 extract a second portion of the thermal and / or kinetic energy therefrom. This energy extraction causes the LP shaft 126 to rotate, thereby supporting the operation of the LP compressor 112 and / or the rotation of the fan shaft 128. The combustion gases 160 then exit the core turbine 104 through the exhaust section 122 of the core turbine 104.

[0025] As with turbofan engine 100, core turbine 104 performs a similar function and is similarly found in land-based gas turbines, turbojets having a smaller ratio of first portion 146 of air 142 to second portion 148 of air 142 than turbofan engines, and non-ducted fan engines in which fan section 106 lacks nacelle 134. In each of turbofan, turbojet, and non-ducted engines, a reduction gear (e.g., reduction gearbox 130) may be included between any shaft and spool. For example, reduction gearbox 130 may be provided between LP shaft 126 and fan shaft 128 of fan section 106. Figure 1 Also included is a cowling 170 and offset-arch gimbals 172, 174, 176. The cowling 170 is a covering that reduces drag and cools the engine. The offset-arch gimbals 172, 174, 176 may, for example, include infrared cameras to detect thermal anomalies in the under-cowl area of ​​the turbofan engine 100.

[0026] FIG2 is a schematic side view of a gas turbine engine 200 coupled to a pylon 201, the pylon 201 including a first shell section 202, a second shell section 204, and a third shell section 206. In FIG2 , the gas turbine engine 200 includes a forward mount 208, a strut 209, an aft mount 210, and a thrust link 212. In FIG2 , the thrust link 212 extends between the aft mount 210 and a mounting location 214 on the first shell section 202. In FIG2 , the strut 209 and / or the forward mount 208 define a first line of action 216, and the thrust link 212 defines a second line of action 218. In FIG2 , the first line of action 216 and the second line of action 218 have an intersection 220.

[0027] The first housing portion 202 comprises a portion of the housing of the gas turbine engine 200 that houses a fan (eg, Figure 1 106, etc.), fan frame and / or LP compressor (e.g., Figure 1 LP compressor 112, etc.). In FIG2, the fan case portion includes a mounting location 214 for a thrust link 212. The second case portion 204 includes core turbomachinery components (e.g., Figure 1 HP compressor 114, Figure 1 The combustion section 116 and HP turbine 118, etc.). As used herein, portions of the gas turbine engine 200 including one or more of the HP compressor, combustion section, and HP turbine are interchangeably referred to as the "airframe" and "core structure" of the gas turbine engine. The airframe of the gas turbine engine 200 is disposed between the mounts 208, 210 and is subject to trunk bending caused by the reaction of forces at the mounts 208, 210 (e.g., engine weight, inlet loads 222, thrust loads 228, etc.). The third shell portion 206 is the portion of the gas turbine engine 200 including the low pressure turbine (e.g., Figure 1 2 , the third shell portion 206 is coupled to the pylon 201 via the rear mount 210 .

[0028] Forward mounts 208, aft mounts 210, and thrust links 212 couple the gas turbine engine to pylon 201. Pylon 201 is the mechanical structure that couples the gas turbine engine to the aircraft (e.g., via the aircraft's wings, the aircraft's tail, the aircraft's fuselage, etc.). The forces and moments generated by the weight and operation of gas turbine engine 200 react via mounts 208, 210 and thrust links 212. Mounts 208, 210, and thrust links 212 fully constrain the motion of gas turbine engine 200. In other words, each of the six degrees of freedom of gas turbine engine 200 (e.g., yaw rotation, pitch rotation, roll rotation, yaw translation, pitch translation, and pitch translation, etc.) reacts via mounts 208, 210 and thrust links 212. Bending moments 224, 230 generated during operation of gas turbine engine 200 react between mounts 208, 210 via an imbalance of reaction forces at mounts 208, 210. Consequently, bending moments 224, 230 may cause deformation (e.g., strain, bending, flexing, twisting, etc.) of components between mounts 208, 210. Consequently, flow path components of gas turbine engine 200, including the HP compressor and the LP compressor, deform due to the bending moments 224, 230 reacting between mounts 208, 210. For example, such deformation may reduce blade tip clearance and / or engine performance.

[0029] In FIG2 , gas turbine engine 200 is subjected to a loading condition 215 that includes an inlet load 222 that, in conjunction with a corresponding first moment arm 226, causes a first bending moment 224. Loading condition 215 also includes a thrust load 228 that, in conjunction with a corresponding second moment arm 232, causes a second bending moment 230. Loading condition 215 may be associated with high-stress operation (e.g., takeoff) of gas turbine engine 200. In some examples, loading condition 215 occurs during a minimum clearance condition of gas turbine engine 200. In FIG2 , bending moments 224, 230 are calculated relative to intersection point 220. In FIG2 , calculating bending moments 224, 230 at intersection point 220 reduces the computational complexity of force and moment calculations associated with the mounting configuration of gas turbine engine 200. In particular, the intersection point 220 lies on the lines of action 216 , 218 , and therefore, the forces associated with the front mount 208 and the thrust link 212 do not impart a bending moment at the intersection point 220 .

[0030] The inlet load 222 is an aerodynamic load experienced by the gas turbine engine 200 (e.g., loads caused by asymmetric pressures on surfaces of the gas turbine engine, etc.). The inlet load 222 is caused by air entering the inlet 233. In particular, during the loading condition 215, the angle of attack (α) of the gas turbine engine 200 causes the incoming air at the inlet 233 to encounter the top surface of the inlet 233 (e.g., causing wear, etc.), which increases the pressure experienced at the top of the inlet 233 and reduces the pressure experienced at the bottom of the inlet 233. The pressure differential applied to the inlet 233 causes the inlet load 222 and the first bending moment 224. In FIG. 2 and FIG. Figure 3-5 In the example of FIG, inlet load 222 is described as a load applied to inlet 233. It should be understood that inlet load 222 is a force equivalent to the pressure applied to the interior of the inlet of the gas turbine engine described herein.

[0031] Thrust load 228 is the operational load experienced by gas turbine engine 200. During operation, gas turbine engine 200 generates thrust, which propels gas turbine engine 200. The thrust generated by gas turbine engine 200 is transferred to pylon 201 via one or more mounts 208, 210 and thrust link 212, which propels gas turbine engine 200 forward along the roll axis. In FIG2 , thrust load 228 acts along centerline 229 of gas turbine engine 200.

[0032] In FIG2 , the inlet load 222 and the thrust load 228 induce a first reaction force 221 at the front mount 208. In FIG2 , the inlet load 222 and the resulting first bending moment 224 induce a corresponding second reaction force 234 (e.g., inlet load reaction force, etc.) at the rear mount 210. The second reaction force 234 can be expressed via the principles of statics and the sum of moments about the intersection 220 as:

[0033]

[0034] where R aft，inlet load is the second reaction force 234, F inlet is the inlet load 222, a is the first moment arm 226, and b is the distance 235 between the intersection 220 and the rear mount 210. In Figure 2, the thrust load 228 and the resulting second bending moment 230 cause a corresponding third reaction force 236 at the rear mount 210. The third reaction force 236 can be expressed via the principles of statics and calculation of the bending moment about the intersection 220 as:

[0035]

[0036] where R aft，thrust loadis the third reaction force 236, F thrust is the thrust load 228, c is the second moment arm 232, and b is the distance 235 between the intersection 220 and the rear mount 210. In FIG2 , the second reaction force 234 and the third reaction force 236 are both applied in the same direction. As described above, the backbone bending in the second shell portion 204 is caused by the mismatch in reaction forces between the front mount 208 and the rear mount 210. In FIG2 , due to the orientation of the thrust link 212 and the strut 209, the reaction forces 234 and 236 act in the same upward direction.

[0037] The bending moments 224, 230 and the resulting opposing forces at the forward and aft mounts 208, 210 (e.g., the difference between the first reaction force 221 and the sum of the second reaction force 234 and the third reaction force 236, etc.) cause some or all of the shell sections 202, 204, 206 to bend (e.g., deform, twist, flex, etc.) between the forward and aft mounts 208, 210. Such bending may reduce blade tip clearance of compressor blades (e.g., blades similar to the HP compressor rotor blades 156, blades similar to the LP compressor rotor blades 152, etc.) within the second shell section 204 (e.g., particularly a circumferential portion of the second shell section 204, etc.). This deformation requires the gas turbine engine 200 to be designed to prevent encounters between the compressor blades and radially adjacent shell sections by increasing blade tip clearance when the engine is not operating (e.g., cold, etc.).

[0038] 2 , a first bending moment 224 caused by the inlet load 222 and a second bending moment 230 caused by the thrust load 228 act in the same direction (e.g., in a negative pitch direction, clockwise, etc.). Because the bending moments 224, 230 act in the same direction, the associated reaction forces 234, 236, respectively, at the aft mount 210 are also in the same direction (e.g., in a positive yaw direction in FIG. 2 , etc.). Therefore, the deformations (e.g., strain, bending, twisting, etc.) caused by the inlet load 222 and the thrust load 228 are additive, which causes an increase in the inlet load 222 or the thrust load 228 to increase the bending of the second shell portion 204.

[0039] The following examples relate to a gas turbine engine similar to the gas turbine engine 200 described with reference to FIG2 , except that the engine is modified to reduce the bending moments experienced by the casing. Figure 3-5 Use with Figure 1 Unless otherwise specified, the same element numbers as those used in the drawings have the same meanings.

[0040] Figure 3is a side schematic diagram of an example gas turbine engine 300 coupled to a pylon 301 implemented in accordance with the teachings of the present disclosure. Figure 3 In the example shown, gas turbine engine 300 includes an example first shell section 302, an example second shell section 304, an example third shell section 306, and an example fourth shell section 308. In some examples, gas turbine engine 300 may include additional shell sections (not shown) between corresponding ones of shell sections 302, 304, 306, 308 and / or downstream of fourth shell section 308.

[0041] exist Figure 3 In the example shown, the gas turbine engine 300 includes an example front mount 310, an example strut 311, an example aft mount 312, and an example thrust link 314. Figure 3 In the example shown, the thrust link 314 extends between the rear mount 312 and an example mounting location 316 on the example second shell portion 304. Figure 3 In the example shown, the strut 311 and / or the front mount 310 define an example first line of action 318, and the thrust link 314 defines an example second line of action 320. Figure 3 In the example shown, first line of action 318 and second line of action 320 have an example intersection point 322 .

[0042] Forward mount 310, aft mount 312, and thrust link 314 couple gas turbine engine 300 to pylon 301. Pylon 301 is a mechanical structure that couples gas turbine engine 300 to an aircraft (e.g., via the underside of an aircraft wing, etc.). In some examples, pylon 301 may not be present. In some such examples, gas turbine engine 300 may be coupled to another suitable location on the aircraft and / or to another vehicle. For example, gas turbine engine 300 may be coupled to the tail of an aircraft, to the fuselage of an aircraft, and / or above a wing of an aircraft.

[0043] exist Figure 3 In the example shown, the first housing portion 302 comprises a portion of the housing of the gas turbine engine 200 that houses the fan (e.g., Figure 1 The fan section 106, etc.) of the turbomachinery components and fan frame. Figure 3 In the example shown, the first housing portion 302 is coupled to the pylon 301 via a front mount 310. The second housing portion 304 comprises a portion of the gas turbine engine 300 that houses a supercharger (e.g., Figure 1LP compressor 112, etc.). In some examples, the second shell portion 304 is a supercharger shell portion. The third shell portion 306 is disposed between the second shell portion 304 and the fourth shell portion 308. In some examples, the third shell portion 306 is an intermediate shell portion. Figure 3 In the example shown, the mounting location 316 of the thrust link 314 is provided on the third shell portion 306. The fourth shell portion 308 includes the core turbomachinery components of the gas turbine engine 300 (eg, Figure 1 HP compressor 114, Figure 1 2 ). Unlike the gas turbine engine 200 of FIG. 2 , the gas turbine engine 300 includes a second shell portion 304 and a third shell portion 306 disposed between a fan shell portion (e.g., a first shell portion 302, etc.) and a shell portion housing the HP compressor, combustor, and HP turbine. Figure 3 In the example shown, the presence of the second shell portion 304 and the third shell portion 306 increases the distance between the forward mount 310 and the mounting location 316 and results in the intersection point 322 being below the example centerline 323 of the gas turbine engine 300 (e.g., closer to the ground, on the opposite side of the centerline 323 from the pylon 301, etc.) and axially downstream of the inlet load axis 342, unlike the intersection point 220 of the gas turbine engine 200 of FIG. 2 .

[0044] exist Figure 3 In the example shown, the second shell portion 304, the third shell portion 306, and the fourth shell portion 308 form the body of the gas turbine engine 300. Figure 3 In the example shown, the body of the gas turbine engine 300 is disposed between mounts 310, 312 and is subject to trunk bending caused by the reaction of forces at the mounts 310, 312 (e.g., engine weight, inlet load 222, thrust load 228, etc.). The fifth shell section 309 is the portion of the gas turbine engine 300 that includes the low pressure turbine (e.g., Figure 1 LP turbine 120, etc.). Figure 3 In the example shown, fifth shell portion 309 is coupled to hanger 301 via rear mount 312 .

[0045] exist Figure 3In the illustrated example, a forward mount 310, an aft mount 312, and a thrust link 314 couple the gas turbine engine 300 to a pylon 301. The pylon 301 is the mechanical structure that couples the gas turbine engine 300 to the aircraft (e.g., via the aircraft's wings, etc.). The forces and moments generated by the weight and operation of the gas turbine engine 300 react via the mounts 310, 312, and the thrust links 314. The mounts 310, 312, and the thrust links 314 fully constrain the motion of the gas turbine engine 300. In other words, each of the six degrees of freedom of the gas turbine engine 300 (e.g., yaw rotation, pitch rotation, roll rotation, yaw translation, pitch translation, and pitch translation, etc.) is reacted via the mounts 310, 312, and the thrust links 314. Bending moments (e.g., bending moments 326, 334, etc.) generated during operation of gas turbine engine 300 react between mounts 310, 312 via an imbalance in loads at mounts 310, 312. Consequently, these bending moments (e.g., bending moments 326, 334, etc.) can cause deformation (e.g., strain, bending, flexing, twisting, etc.) of components between mounts 310, 312. Consequently, flow path components of gas turbine engine 300, including the HP compressor and the LP compressor, deform due to the bending moments (e.g., bending moments 326, 334, etc.) reacting between mounts 310, 312. This deformation can reduce blade tip clearance and / or engine performance.

[0046] exist Figure 3 In the example shown, the front mount 310 is a structural linkage that couples the first shell portion 302 to the hanger 301. Figure 3In the example shown, strut 311 extends between first shell section 302 and forward mount 310. In some examples, strut 311 may be implemented by a structural outlet guide vane (OGV). In other examples, strut 311 may be implemented by a non-aerodynamic structural member. In some examples, strut 311 may not be present. In some such examples, forward mount 310 may directly couple first shell section 302 and pylon 301. In some examples, forward mount 310 may be implemented by one or more two-pin swing linkages, one or more three-pin fixed linkages (e.g., boomerang linkages, delta linkages, straight linkages with a center pin, etc.), one or more pivot linkages, one or more ball linkages, etc. Aft mount 312 is a structural linkage coupled to fifth shell section 309. In some examples, aft mount 312 may be implemented by a two-pin swing linkage and / or a three-pin fixed linkage (e.g., boomerang linkages, delta linkages, straight linkages with a center pin, etc.) having any of a variety of shapes. Thrust link 314 is a structural member that extends between mounting location 316 and aft mount 312. In some examples, thrust link 314 can transfer axial loads between the front and aft of gas turbine engine 300. Additionally or alternatively, in some configurations, thrust link 212 can similarly react to applied axial loads and / or yawing moments.

[0047] exist Figure 3 In the example shown, the gas turbine engine 300 is subjected to the load conditions 215 of FIG. 2 , which include an inlet load 222 and a thrust load 228 . Figure 3 In the example shown, the inlet load 222 acts along an example inlet load axis 342 and generates an example first bending moment 326 with a corresponding example first moment arm 328. Figure 3 In the example shown, the thrust load 228 acts along the example centerline 323, generating an example second bending moment 334 with a corresponding example second moment arm 336. The second moment arm 336 is the displacement of the intersection point 322 from the centerline 323 along the yaw axis. As described above, the load condition 215 can be associated with high stress operation (e.g., takeoff / lift-off) of the gas turbine engine 200. In other examples, the gas turbine engine 300 can be subjected to any suitable load condition. Figure 3 In the example shown, bending moments 326, 334 are calculated relative to intersection 322. Calculating bending moments 326, 334 at intersection 322 reduces the computational complexity of calculating forces and moments associated with the mounting configuration of gas turbine engine 300. In particular, intersection 322 lies on lines of action 318, 320, and therefore, forces associated with forward mount 310 and thrust link 314 do not exert bending moments at intersection 322.

[0048] exist Figure 3 In the example shown, the inlet load 222 and the thrust load 228 cause an example first reaction force 321 at the front mount 310. Figure 3 In the example shown, the inlet load 222 and the resulting first bending moment 326 induce a corresponding second reaction force 338 (e.g., inlet load reaction force, etc.) at the rear mount 312. The second reaction force 338 can be expressed via the principles of statics and the sum of moments about the intersection point 322 as:

[0049]

[0050] where R aft，inlet load is the second reaction force 338, F inlet is the inlet load 222, c is the first moment arm 328, and d is the example distance 339 between the intersection 322 and the rear mount 312. Figure 3 In the example shown, the thrust load 228 and the resulting second bending moment 334 induce a corresponding third reaction force 340 at the rear mount 312. The third reaction force 340 can be expressed via the principles of statics and calculation of the bending moment about the intersection 322 as:

[0051]

[0052] where R aft，thrust load is the third reaction force 340, F thrust is the thrust load 228, e is the second lever arm 336, and d is the distance 339. Figure 3 In the example shown, the second reaction force 338 and the third reaction force 340 are applied in opposite directions. As described above, trunk bending in the gas turbine engine 300 is caused by a mismatch in the reaction forces between the front mount 310 and the rear mount 312. Figure 3 In the example shown, the reaction forces 338, 340 act in opposite directions due to the orientation of the thrust link 314 and the strut 311. Specifically, because the intersection point 322 is below the centerline 323 and axially downstream of the inlet load axis 342, the second moment arm 336 extends downward, which causes the second bending moment 334 and the associated third reaction force 340 to act in opposite directions to the first bending moment 326 and the associated second reaction force 338, respectively.

[0053] exist Figure 3In the illustrated example, the first bending moment 326 caused by the inlet load 222 and the second bending moment 334 caused by the thrust load 228 act in opposite directions (e.g., the first bending moment 326 acts in the negative pitch direction, the second bending moment 334 acts in the positive pitch direction, etc.). Because the bending moments 326 and 334 act in opposite directions, the associated reaction forces 338 and 340 at the aft mount 312 also act in opposite directions, respectively. Thus, unlike the gas turbine engine 200 of FIG. 2 , the first bending moment 326 and the second bending moment 334 are subtractive, reducing the overall magnitude of the forces applied to the aft mount 312. In some examples, the bending moments 326 and 334 and / or the reaction forces 338 and 340 may cancel (e.g., partially cancel, completely cancel, etc.) when compared to the net bending moments on the gas turbine engine 200 of FIG. 2 , which reduces the resulting load on the aft mount 312 and the resulting airframe deformation. 2 , the reduced net bending moment on the gas turbine engine 300 reduces the deformations (e.g., strain, deflection, bending, etc.) experienced by the gas turbine engine 300, which reduces the required cold blade tip clearance of the gas turbine engine 300. Tighter operating tip clearances improve engine efficiency and engine operability, and reduce fuel consumption (e.g., reduced specific fuel consumption (SFC), etc.).

[0054] Figure 4 is a side schematic diagram of an example gas turbine engine 400 coupled to a pylon 401 implemented in accordance with the teachings of the present disclosure. Figure 4 In the illustrated example, the gas turbine engine 400 includes the first shell portion 202 of FIG. 2 , the second shell portion 204 of FIG. 2 , and the third shell portion 206 of FIG. 2 . Figure 4 The gas turbine engine 400 is described as having the same arrangement of shell portions as the gas turbine engine 200 of FIG. 2 , but in other examples, the gas turbine engine 400 may have any other suitable arrangement of shell portions, including Figure 3 The arrangement of the casing portion of the gas turbine engine 300 (e.g., including similar Figure 3 The supercharger shell portion of the second shell portion 304 and similar Figure 3 Additionally or alternatively, gas turbine engine 400 may include additional shell sections (not shown) between shell sections of shell sections 202 , 204 , 206 and / or downstream of third shell section 206 .

[0055] exist Figure 4 In the example shown, the gas turbine engine 400 includes an example front mount 402, an example strut 403, an example aft mount 404, and an example thrust link 406. Figure 4In the example shown, the thrust link 406 extends between the rear mount 404 and an example mounting location 408 on the first shell portion 202. Figure 4 In the example shown, the strut 403 and / or the front mount 402 define an example first line of action 410, and the thrust link 406 defines an example second line of action 412. Figure 4 In the example shown, first line of action 410 and second line of action 412 have an example intersection point 414 .

[0056] exist Figure 4 In the example shown, the front mount 402 is a structural linkage that couples the first shell portion 202 to the hanger 401. Figure 4 In the example shown, struts 403 extend between first shell portion 202 and forward mounting member 402. In some examples, struts 403 may be implemented by structural outlet guide vanes (OGVs). In other examples, struts 403 may be implemented by non-aerodynamic structural members. In some examples, struts 403 may not be present. In some such examples, forward mounting member 402 may directly couple first shell portion 202 and pylon 401. Figure 4 In the example shown, the struts 403 form an acute angle 415 with the roll axis. Figure 4 In the example shown, acute angle 415 is approximately 40 degrees. In other examples, acute angle 415 can have any other suitable value (e.g., between 70 degrees and 20 degrees, etc.). In some examples, front mount 402 can be implemented by one or more 2-pin swing linkages, one or more 3-pin fixed linkages (e.g., boomerang linkages, triangular linkages, straight linkages with a center pin, etc.), one or more pivot linkages, one or more ball linkages, etc.

[0057] exist Figure 4 In the illustrated example, aft mount 404 is a structural linkage that couples third shell portion 206. In some examples, aft mount 404 can be implemented as a 2-pin swing linkage and / or a 3-pin fixed linkage having any of a variety of shapes (e.g., a boomerang linkage, a delta linkage, a straight linkage with a center pin, etc.). Thrust link 406 is a structural member that extends between mounting location 408 and aft mount 404. Thrust link 406 transfers axial loads between the front and rear of gas turbine engine 400. Additionally or alternatively, in some configurations, thrust link 406 can similarly react to axial loads and / or yawing moments.

[0058] The forces and moments generated by the weight and operation of the gas turbine engine 400 are reacted through the mounts 402, 404 and the thrust link 406. Figure 4In the illustrated example, the mounts 402, 404 and the thrust links 406 fully constrain the motion of the gas turbine engine 400. For example, each of the six degrees of freedom of the gas turbine engine 400 (e.g., yaw rotation, pitch rotation, roll rotation, yaw translation, pitch translation, and pitch translation, etc.) is reacted via the mounts 402, 404 and the thrust links 406. Bending moments generated during operation of the gas turbine engine 400 are reacted between the mounts 402, 404 via an imbalance in the loads at the mounts 402, 404.

[0059] exist Figure 4 In the example shown, the gas turbine engine 400 is subjected to the load conditions 215 of FIG. 2 , which include the thrust load 228 and the inlet load 222 . Figure 4 In the example shown, the inlet load 222 acts along an example inlet load axis 421 and generates an example first bending moment 422 with a corresponding example first moment arm 420. Figure 4 In the example shown, the thrust load 228 acts along the example centerline 429 and generates an example second bending moment 425 with the corresponding second moment arm 424. The second moment arm 424 is the displacement of the intersection point 414 from the centerline 429 of the gas turbine engine along the yaw axis. Figure 4 In the example shown, bending moments 422, 425 are calculated relative to intersection 414. Calculating the bending moment at intersection 414 reduces the computational complexity of calculating forces and moments associated with the mounting configuration of gas turbine engine 400. In particular, intersection 414 lies on lines of action 410, 412, respectively, and therefore, forces associated with forward mount 402 and thrust link 406 do not exert bending moments at intersection 414.

[0060] exist Figure 4 In the example shown, the inlet load 222 and the thrust load 228 cause an example first reaction force 426 at the front mount 402. Figure 4 In the example shown, the inlet load 222 and the resulting bending moment 422 induce an example second reaction force 428 (e.g., inlet load reaction force, etc.) at the rear mount 210. The second reaction force 428 can be expressed via the principles of statics and the sum of moments about the intersection 414 as:

[0061]

[0062] where R aft，inlet load is the second reaction force 428, F inlet is the inlet load 222, f is the first moment arm 420, and d is the example distance 430 between the intersection 414 and the rear mount 404. Figure 4In the example shown, the thrust load 228 and the resulting second bending moment 425 induce an example third reaction force 432 at the rear mount 404. The third reaction force 432 can be expressed via the principles of statics and calculation of the bending moment about the intersection 414 as:

[0063]

[0064] where R aft，thrust load is the third reaction force 432, F thrust is the thrust load 228, h is the second moment arm 424, and d is the distance 430. Figure 4 In the example shown, the second reaction force 428 and the third reaction force 432 are applied in opposite directions. As described above, trunk bending in the gas turbine engine 400 is caused by a bending moment transmitted through the second shell portion 204, which is associated with a mismatch in reaction forces between the front mount 402 and the rear mount 404. Figure 4 In the example shown, the reaction forces 428, 432 act in opposite directions due to the orientation of the thrust link 406 and the strut 403. Specifically, because the intersection point 414 is forward of the inlet load axis 421 (e.g., forward of the roll axis, axially upstream, etc.) and above the centerline 429, the first moment arm 420 extends forward, which causes the first bending moment 422 and the associated second reaction force 428 to act in opposite directions from the second bending moment 425 and the associated third reaction force 432, respectively. Figure 4 In the example shown, intersection point 414 is external to gas turbine engine 400 .

[0065] exist Figure 4 In the example shown, the first bending moment 422 caused by the inlet load 222 and the second bending moment 425 caused by the thrust load 228 act in opposite directions. Figure 3In the gas turbine engine 300 of FIG. 2 , the opposing bending moments 422 and 425 result in associated reaction forces 428 and 432 also in opposite directions. Thus, unlike the gas turbine engine 200 of FIG. 2 , the first bending moment 422 and the second bending moment 425 are subtractive and reduce the overall magnitude of the forces applied to the aft mount 404. In some examples, the bending moments 422 and 425 and / or the reaction forces 428 and 432 can cancel (e.g., partially cancel, completely cancel, sum to substantially zero, etc.) compared to the net bending moment on the gas turbine engine 400, which reduces the ultimate load on the aft mount 404 and the resulting airframe deformation. The reduced net bending moment on the gas turbine engine 400 reduces the deformation (e.g., strain, deflection, bending, etc.) experienced by the gas turbine engine 400 compared to the gas turbine engine 200 of FIG. 2 , which reduces the required cold blade tip clearance of the gas turbine engine 400. Tighter operating tip clearances improve engine efficiency and engine operability, and reduce fuel consumption (eg, reduced specific fuel consumption (SFC), etc.).

[0066] Figure 5 is a side schematic diagram of an example gas turbine engine 500 coupled to a pylon 501 implemented in accordance with the teachings of the present disclosure. Figure 5 In the example shown, the gas turbine engine 500 includes Figure 3 The first shell portion 302, Figure 3 The second shell portion 304, Figure 3 The third shell portion 306, Figure 3 The fourth shell portion 308 and Figure 3 The fifth shell portion 309. Although Figure 5 The gas turbine engine 500 is described as having a Figure 3 2 , but in other examples, the gas turbine engine 500 may have any other suitable shell section arrangement, including the shell section arrangement of the gas turbine engine 200 of FIG. 2 (e.g., excluding the second shell section 304 and / or the third shell section 306, etc.). Additionally or alternatively, the gas turbine engine 500 may include additional shell sections (not shown) between the shell sections of the shell sections 302, 304, 306, 308, 309 and / or downstream of the fifth shell section 309.

[0067] exist Figure 5 In the example shown, the gas turbine engine 500 includes an example front mount 502, an example strut 504, an example aft mount 506, and an example thrust link 508. Figure 5 In the example shown, the thrust link 508 extends between the rear mount 506 and an example mounting location 510 on the third shell portion 306. Figure 5 In the example shown, the strut 504 and / or the front mount 502 define an example first line of action 512, and the thrust link 508 defines an example second line of action 514. Figure 5 In the example shown, first line of action 512 and second line of action 514 have an example intersection 516 .

[0068] exist Figure 5 In the example shown, the front mount 502 is a structural linkage that couples the first shell portion 302 to the hanger 501. Figure 5 In the example shown, struts 504 extend between first shell portion 302 and front mount 502. In some examples, struts 504 may be implemented by OGVs. In other examples, struts 504 may be implemented by non-aerodynamic structural members. In some examples, struts 504 may not be present. In some such examples, front mount 502 may directly couple first shell portion 302 and pylon 501. Figure 5 In the example shown, the strut 504 forms an acute angle 517 with the roll axis. Figure 5 In the example shown, acute angle 517 is approximately 60 degrees. In other examples, acute angle 517 can have any other suitable value (e.g., between 70 degrees and 20 degrees, etc.). In some examples, front mount 502 can be implemented by one or more 2-pin swing linkages, one or more 3-pin fixed linkages (e.g., boomerang linkages, triangular linkages, straight linkages with a center pin, etc.), one or more pivot linkages, one or more ball linkages, etc.

[0069] exist Figure 5 In the illustrated example, aft mount 506 is a structural linkage that couples fifth shell section 309. In some examples, aft mount 506 can be implemented as a 2-pin swing linkage and / or a 3-pin fixed linkage having any of a variety of shapes (e.g., a boomerang linkage, a delta linkage, a straight linkage with a center pin, etc.). Thrust link 508 is a structural member extending between mounting location 510 and aft mount 506. Thrust link 508 transfers axial loads between the front and rear of gas turbine engine 500. Additionally or alternatively, in some configurations, thrust link 508 can similarly react to axial loads and / or yawing moments.

[0070] The forces and moments generated by the weight and operation of the gas turbine engine 500 are reacted through the mounts 502, 506 and the thrust link 508. Figure 5In the example shown, the mounts 502, 506 and the thrust links 508 fully constrain the motion of the gas turbine engine 500. For example, each of the six degrees of freedom of the gas turbine engine 500 (e.g., yaw rotation, pitch rotation, roll rotation, yaw translation, pitch translation, and pitch translation, etc.) is reacted via the mounts 502, 506 and the thrust links 508. Bending moments generated during operation of the gas turbine engine 500 are reacted via the imbalance of loads at the mounts 502, 506.

[0071] exist Figure 5 In the example shown, the gas turbine engine 500 is subjected to the load condition 215 of FIG. 2 , which includes the thrust load 228 and the inlet load 222 . Figure 5 In the example shown, the inlet load 222 acts along an example inlet load axis 517, while the thrust load 228 acts along an example centerline 518. Figure 5 In the example shown, the thrust link 508 and the forward mount 502 are arranged so that the intersection 516 is located on the centerline 518 of the gas turbine engine 500 and the inlet load axis 517. Figure 5 In the example shown, the intersection point 516 is at the same axial position as the inlet load 222 and at the same pitch position as the thrust load 228. Figure 5 In the example shown, the inlet load 222 and the thrust load 228 do not impose a bending moment on the gas turbine engine 500. Consequently, the total bending moment on the gas turbine engine 500 is reduced (e.g., other loads including engine weight and other aerodynamic loads may still impose a bending moment on the gas turbine engine 500, etc.). The reduced net bending moment on the gas turbine engine 500 reduces the deformation (e.g., strain, deflection, bending, etc.) experienced by the gas turbine engine 500 compared to the gas turbine engine 200 of FIG. 2 , which reduces the required cold blade tip clearance of the gas turbine engine 500. Tighter operating tip clearances improve engine efficiency and engine operability and reduce fuel consumption (e.g., reduce specific fuel consumption (SFC), etc.).

[0072] Figure 3 Gas turbine engine 300, Figure 4 Gas turbine engines 400 and Figure 5The gas turbine engines are described as being wing mounted. Although the examples disclosed herein are described with reference to wing mounted gas turbine engines, the teachings of the present disclosure should not be limited to wing mounted gas turbine engines. Instead, the gas turbine engines 300, 400, and 500 may be located at another suitable location on the aircraft (e.g., fuselage mounted, tail mounted, tail mounted, etc.). Figure 3-5 The gas turbine engine 300, gas turbine engine 400, and gas turbine engine 500 shown and described in detail in FIG. 3 are axial-flow turbofan engines. In other examples, the gas turbine engine 300, gas turbine engine 400, and / or gas turbine engine 500 may be another suitable type of gas turbine engine (e.g., a turboprop engine, a turbojet engine, a turboshaft engine, a centrifugal flow engine, etc.). Furthermore, although Figure 3 Gas turbine engine 300, Figure 4 The gas turbine engine 400 and / or Figure 5 The gas turbine engine 500 is described and depicted as a two spool engine, but in other examples, the gas turbine engine 300, Figure 4 The gas turbine engine 400 and / or Figure 5 The gas turbine engine 500 can have any suitable number of spools (e.g., one spool, three spools, etc.). In some examples, Figure 3 Gas turbine engine 300, Figure 4 The gas turbine engine 400 and / or Figure 5 The gas turbine engine 500 may include Figure 3-5 Components not shown (e.g., afterburner, etc.).

[0073] Based on the foregoing, it can be appreciated that example systems, apparatus, and articles of manufacture have been disclosed that improve gas turbine efficiency (e.g., specific fuel consumption, etc.) by reducing blade tip clearance in an engine rotor. The example mounting configurations disclosed herein reduce trunk bending via an engine mounting configuration that causes inlet loads and thrust loads to be applied in opposite directions, which reduces the net bending moment applied to the engine. The examples disclosed herein reduce deformation, strain, and / or bending caused by gas turbine operation.

[0074] Further aspects of the present disclosure are provided by the subject matter of the following clauses:

[0075] Example 1 includes a gas turbine engine defining a centerline, the gas turbine engine comprising: a pylon; an inlet subjected to an inlet load along an inlet load axis; a shell assembly comprising a first shell portion and a second shell portion; a front mounting member coupling the first shell portion to the pylon, the coupling of the front mounting member to the pylon defining a first line of action; an aft mounting member; and a thrust link coupling the second shell portion to the pylon, the thrust link defining a second line of action, the intersection of the first line of action and the second line of action being arranged at least one of: (1) on the inlet load axis and the centerline, (2) downstream of the inlet load axis and below the centerline, or (3) upstream of the inlet load axis and above the centerline.

[0076] Example 2 includes the gas turbine engine of any preceding clause, wherein the casing assembly includes a supercharger casing, the first casing portion is a fan casing, and the second casing portion is an intermediate casing disposed downstream of the fan casing and the supercharger casing.

[0077] Example 3 includes the gas turbine engine of any preceding clause, wherein a first end of the forward mount is coupled to the fan case, and a second end of the forward mount is coupled to the pylon.

[0078] Example 4 includes the gas turbine engine of any preceding clause, wherein the first end of the thrust link is coupled to the center casing, and the second end of the thrust link is disposed adjacent the aft mount.

[0079] Example 5 includes the gas turbine engine of any preceding clause, wherein the thrust link is configured to be subjected to a thrust load during a condition of the gas turbine engine, the intersection point has a displacement from the centerline, the displacement defining a moment arm of a first moment associated with the thrust load, and the first moment is in a rotational direction opposite to a second moment associated with the inlet load.

[0080] Example 6 includes the gas turbine engine of any preceding clause, wherein the condition is a takeoff condition.

[0081] Example 7 includes the gas turbine engine of any preceding clause, wherein the first moment induces a first reaction force at the aft mount, the second moment induces a second reaction force at the aft mount, the first reaction force being in a direction opposite to the second reaction force.

[0082] Example 8 includes the gas turbine engine of any preceding clause, wherein the forward mount comprises an outlet guide vane.

[0083] Example 9 includes the gas turbine engine of any preceding clause, wherein the exit guide vanes form an acute angle with the centerline.

[0084] Example 10 includes the gas turbine engine of any preceding clause, wherein the intersection point is external to the gas turbine engine.

[0085] Example 11 includes an apparatus for coupling a gas turbine engine to a pylon, the gas turbine engine having a centerline, the gas turbine engine being subjected to an inlet load along an inlet load axis, the apparatus comprising: a forward mount coupling a first portion of the gas turbine engine to the pylon along a first line of action; an aft mount; and a thrust link configured to couple a second portion of the gas turbine engine to the pylon, the thrust link defining a second line of action, the intersection of the first line of action and the second line of action being arranged at least one of: (1) on the inlet load axis and the centerline, (2) downstream of the inlet load axis and below the centerline, or (3) upstream of the inlet load axis and above the centerline.

[0086] Example 12 includes the apparatus of any preceding clause, wherein the first portion is a fan case, and the second portion is a center case disposed downstream of the fan case and a supercharger case of the gas turbine engine.

[0087] Example 13 includes the apparatus of any preceding clause, wherein a first end of the front mount is coupled to the fan case, and a second end of the front mount is coupled to the hanger.

[0088] Example 14 includes the apparatus of any preceding clause, wherein a first end of the thrust link is coupled to the center housing, and a second end of the thrust link is disposed adjacent the aft mount.

[0089] Example 15 includes the apparatus of any preceding clause, wherein the thrust link is configured to be subjected to a thrust load during a condition of the gas turbine engine, the intersection point has a displacement from the centerline, the displacement defining a moment arm of a first moment associated with the thrust load, and the first moment is in a rotational direction opposite to a second moment associated with the inlet load.

[0090] Example 16 includes the apparatus of any preceding clause, wherein the condition is a takeoff condition.

[0091] Example 17 includes the apparatus of any preceding clause, wherein the first moment induces a first reaction force at the rear mount, the second moment induces a second reaction force at the rear mount, the first reaction force being in a direction opposite to the second reaction force.

[0092] Example 18 includes the apparatus of any preceding clause, wherein the forward mount comprises exit guide vanes.

[0093] Example 19 includes the apparatus of any preceding clause, wherein the exit guide vanes form an acute angle with the centerline.

[0094] Example 20 includes the apparatus of any preceding clause, wherein the intersection point is external to the gas turbine engine.

[0095] Example 21 includes a gas turbine engine having a centerline, the gas turbine engine comprising: a pylon; a shell assembly comprising a first shell portion and a second shell portion; and a front mounting member, the front mounting member connecting the first shell portion to the pylon, the connection between the front mounting member and the pylon defining a first line of action; an aft mounting member; and a thrust link connecting the second shell portion to the pylon, the thrust link and the aft mounting member defining a second line of action, the intersection of the first line of action and the second line of action being disposed on a side of the centerline opposite the pylon.

[0096] Example 22 includes the gas turbine engine of any preceding clause, wherein the casing assembly includes a supercharger casing, the first casing portion is a fan casing, and the second casing portion is a center casing disposed downstream of the fan casing and the supercharger casing.

[0097] Example 23 includes the gas turbine engine of any preceding clause, wherein a first end of the forward mount is coupled to the fan case, and a second end of the forward mount is coupled to the pylon.

[0098] Example 24 includes the gas turbine engine of any preceding clause, wherein the first end of the thrust link is coupled to the center casing, and the second end of the thrust link is disposed adjacent the aft mount.

[0099] Example 25 includes the gas turbine engine of any preceding clause, wherein the thrust link is configured to be subjected to a thrust load during a condition of the gas turbine engine, the intersection point has a displacement from the centerline, the displacement defining a moment arm of a first moment associated with the thrust load, and the first moment is in a direction opposite to a second moment associated with a second load.

[0100] Example 26 includes the gas turbine engine of any preceding clause, wherein the second load is an inlet load, and further comprising an inlet configured to be subjected to the inlet load during the condition.

[0101] Example 27 includes the gas turbine engine of any preceding clause, wherein the condition is takeoff.

[0102] Example 28 includes the gas turbine engine of any preceding clause, wherein the forward mount comprises an outlet guide vane.

[0103] Example 29 includes a gas turbine engine having a centerline, the gas turbine engine comprising: an inlet; a pylon; a shell assembly comprising a first shell portion and a second shell portion; and a front mount, the front mount coupling the first shell portion to the pylon, the coupling of the front mount to the pylon defining a first line of action; an aft mount; and a thrust link coupling the second shell portion to the pylon, the thrust link and the aft mount defining a second line of action, the intersection of the first and second lines of action being axially forward of the inlet.

[0104] Example 30 includes the gas turbine engine of any preceding clause, wherein a first end of the forward mount is coupled to the first casing portion, and a second end of the forward mount is coupled to the pylon.

[0105] Example 31 includes the gas turbine engine of any preceding clause, wherein the thrust link is subjected to a thrust load during certain conditions, the intersection point has a displacement from the centerline, the displacement defining a moment arm of a first moment associated with the thrust load, and the first moment is in a direction opposite to a second moment associated with a second load.

[0106] Example 32 includes the gas turbine engine of any preceding clause, wherein the second load is an inlet load applied to the inlet during the condition.

[0107] Example 33 includes the gas turbine engine of any preceding clause, wherein the condition is takeoff.

[0108] Example 34 includes the gas turbine engine of any preceding clause, wherein the forward mount comprises an outlet guide vane.

[0109] Example 35 includes an apparatus for coupling a gas turbine engine to a pylon, the apparatus comprising: a forward mount coupling a first portion of the gas turbine engine to the pylon along a first line of action; an aft mount; and a thrust link configured to couple a second portion of the gas turbine engine to the pylon, the thrust link and the aft mount defining a second line of action, the intersection of the first line of action and the second line of action being disposed on a centerline of the gas turbine engine.

[0110] Example 36 includes the apparatus of any preceding clause, wherein the gas turbine engine is subjected to an inlet load during a flight phase, the inlet load acting at an axial location at which the intersection point is disposed.

[0111] Example 37 includes the apparatus of any preceding clause, wherein the phase of flight is takeoff.

[0112] Example 38 includes the apparatus of any preceding clause, wherein the first portion is a fan case, and the second portion is a center case disposed downstream of the fan case and a supercharger case of the gas turbine engine.

[0113] Example 39 includes the apparatus of any preceding clause, wherein a first end of the front mount is coupled to the fan case, and a second end of the front mount is coupled to the hanger.

[0114] Example 40 includes the apparatus of any preceding clause, wherein the forward mount comprises exit guide vanes.

[0115] Example 41 includes an apparatus for coupling a gas turbine engine to a pylon, the apparatus comprising a first device for mounting a first portion of the gas turbine engine to the pylon along a first line of action, a second device for mounting the gas turbine engine to the pylon, and a third device for mounting the gas turbine engine to couple the second portion of the gas turbine engine to the pylon, the third mounting device defining a second line of action with the second mounting device, the intersection of the first line of action and the second line of action being disposed on a side of a centerline of the gas turbine engine opposite the pylon.

[0116] Example 42 includes the apparatus of any preceding clause, wherein the first portion is a fan case, and the second portion is an intermediate case disposed downstream of the fan case and a supercharger case.

[0117] Example 43 includes the apparatus of any preceding clause, wherein a first end of the first mounting device is coupled to the fan case, and a second end of the first mounting device is coupled to the hanger.

[0118] Example 44 includes the apparatus of any preceding clause, wherein a first end of the third mounting device is coupled to the intermediate housing, and a second end of the third mounting device is disposed adjacent to the second mounting device.

[0119] Example 45 includes the apparatus of any preceding clause, wherein the third mounting device is subjected to a thrust load during a condition of the gas turbine engine, the intersection point has a displacement from the centerline, the displacement defining a moment arm of a first moment associated with the thrust load, and the first moment is in a direction opposite to a second moment associated with a second load.

[0120] Example 46 includes the apparatus of any preceding clause, wherein the second load is an inlet load applied to an inlet of the gas turbine engine during the condition.

[0121] Example 47 includes the apparatus of any preceding clause, wherein the condition is takeoff.

[0122] Example 48 includes the apparatus of any preceding clause, wherein the first line of action forms a first angle with the centerline, the first angle being between 90 degrees and 45 degrees.

[0123] Example 49 includes the apparatus of any preceding clause, wherein the second line of action forms a second angle with the centerline, the second angle being less than 20 degrees.

[0124] Example 50 includes the apparatus of any preceding clause, wherein the condition is a minimum gap condition.

[0125] The following claims are incorporated by reference into this detailed description. Although certain example systems, methods, apparatus, and articles of manufacture have been disclosed herein, the scope of coverage of this patent is not limited thereto. On the contrary, this patent covers all systems, methods, apparatus, and articles of manufacture that fully fall within the scope of the claims of this patent.

Claims

1. A gas turbine engine defining a centerline, characterized in that The gas turbine engine comprises: hanger; an inlet, the inlet being subjected to an inlet load along an inlet load axis, the inlet load being caused by air entering the inlet; A shell assembly, the shell assembly comprising: fan housing; a supercharger housing disposed downstream of the fan housing; and an intermediate housing, the intermediate housing being disposed downstream of the fan housing and the supercharger housing; a front mount coupling the fan case to the pylon, the coupling of the front mount to the pylon defining a first line of action; rear mountings; and a thrust link coupling the intermediate housing to the pylon, the thrust link defining a second line of action, the intersection of the first line of action and the second line of action being positioned at least one of: (1) on the inlet load axis and the centerline, (2) axially rearward of the inlet load axis and below the centerline, or (3) axially forward of the inlet load axis and above the centerline, wherein the inlet load axis is orthogonal to the centerline.

2. The gas turbine engine according to claim 1, wherein: A first end of the front mount is coupled to the fan housing, and a second end of the front mount is coupled to the hanger.

3. The gas turbine engine according to claim 1, wherein: Wherein a first end of the thrust link is coupled to the center housing, and a second end of the thrust link is disposed adjacent to the rear mount.

4. The gas turbine engine according to claim 1, wherein: wherein the thrust link is configured to be subjected to a thrust load during a condition of the gas turbine engine, the intersection point having a displacement from the centerline, the displacement defining a moment arm for a first moment associated with the thrust load, and the first moment being in a rotationally opposite direction to a second moment associated with the inlet load.

5. The gas turbine engine according to claim 4, characterized in that The conditions are take-off conditions.

6. The gas turbine engine according to claim 4, characterized in that The first moment causes a first reaction force at the rear mounting member, and the second moment causes a second reaction force at the rear mounting member, wherein the first reaction force is in a direction opposite to the second reaction force.

7. The gas turbine engine according to claim 1, wherein: The front mounting member includes an outlet guide vane.

8. The gas turbine engine according to claim 7, characterized in that The outlet guide vanes form an acute angle with the centerline.

9. The gas turbine engine according to claim 1, wherein: The intersection point is outside the gas turbine engine.

10. An apparatus for coupling a gas turbine engine to a pylon, the gas turbine engine having a centerline, the gas turbine engine being subjected to an inlet load along an inlet load axis, the inlet load being caused by air entering the inlet, characterized in that The device comprises: a forward mount coupling a fan case of the gas turbine engine to the pylon along a first line of action; rear mountings; and A thrust link configured to couple a center casing of the gas turbine engine to the pylon, the center casing being disposed downstream of the fan casing and the supercharger casing of the gas turbine engine, the supercharger casing being disposed downstream of the fan casing, the thrust link defining a second line of action, the intersection of the first line of action and the second line of action being disposed at least one of: (1) on the inlet load axis and the centerline, (2) axially rearward of the inlet load axis and below the centerline, or (3) axially forward of the inlet load axis and above the centerline, wherein the inlet load axis is orthogonal to the centerline.

11. The device according to claim 10, characterized in that A first end of the front mount is coupled to the fan housing, and a second end of the front mount is coupled to the hanger.

12. The device according to claim 10, characterized in that Wherein a first end of the thrust link is coupled to the center housing, and a second end of the thrust link is disposed adjacent to the rear mount.

13. The device according to claim 10, characterized in that wherein the thrust link is configured to be subjected to a thrust load during a condition of the gas turbine engine, the intersection point having a displacement from the centerline, the displacement defining a moment arm for a first moment associated with the thrust load, and the first moment being in a rotationally opposite direction to a second moment associated with the inlet load.

14. The device according to claim 13, characterized in that The conditions are take-off conditions.

15. The device according to claim 13, characterized in that The first moment causes a first reaction force at the rear mounting member, and the second moment causes a second reaction force at the rear mounting member, wherein the first reaction force is in a direction opposite to the second reaction force.

16. The device according to claim 10, characterized in that The front mounting member includes an outlet guide vane.

17. The device according to claim 16, characterized in that The outlet guide vanes form an acute angle with the centerline.

18. The device according to claim 10, characterized in that The intersection point is outside the gas turbine engine.

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