Patent Description:
A gas turbine engine includes a stationary structure and a rotating structure rotatably mounted with the stationary structure via a plurality of bearings. Under certain conditions, one or more portions of the rotating structure may vibrate, wobble and/or otherwise shift relative to the stationary structure. Various devices and systems are known in the art for accommodating and/or controlling such shifting between the rotating structure and the stationary structure. While these known devices and systems have various benefits, there is still room in the art for improvement.

<CIT> discloses a prior art assembly for a turbine engine comprising a bearing support arrangement with a shock-absorbing element provided in parallel to a predetermined breaking point formed in the area of the fan bearing.

According to the invention, an assembly is provided for a turbine engine according to claim <NUM>.

A preferred embodiment of the invention is described in claim <NUM>.

The following optional features may be applied to any of the above aspects:
An annular gap may be formed radially between the flexible bearing support and the crushable bumper during the first mode of operation.

The flexible bearing support may also be configured to crush the crushable bumper during the second mode of operation.

The flexible bearing support may also be configured to permanently deform the crushable bumper during the second mode of operation.

The crushable bumper may circumscribe the flexible bearing support.

A first portion of the crushable bumper may be configured to crush when subject to a first load. A second portion of the crushable bumper may be configured to crush when subject to a second load that is different than the first load.

The first load may be greater than the second load. The first portion of the crushable bumper may be arranged radially between the second portion of the crushable bumper and the flexible bearing support.

The first load may be greater than the second load. The second portion of the crushable bumper may be arranged radially between the first portion of the crushable bumper and the flexible bearing support.

The first portion of the crushable bumper may include a first cavity with a first dimension in a direction. The second portion of the crushable bumper may include a second cavity with a second dimension in the direction. The second dimension may be different than the first dimension.

The first portion of the crushable bumper may have a first porosity. The second portion of the crushable bumper may have a second porosity that is different than the first porosity.

The first portion of the crushable bumper may include an empty cavity. The second portion of the crushable bumper may include a cavity at least partially filled with filler material.

The crushable bumper may be configured from or otherwise include honeycomb.

The crushable bumper may be configured from or otherwise include foam.

The crushable bumper may be configured from or otherwise include a lattice structure.

The stationary structure may also include a fixed support. The crushable bumper may be mounted to the fixed support.

A radial outer side of the fixed support may be configured to form a peripheral boundary of a flowpath within the turbine engine.

The flexible bearing support may include a mount section, a bearing support section and a spring section axially between and connected to the mount section and the bearing support section. The bearing may be mounted to the bearing support section. The spring section may include a plurality of slots arranged circumferentially about a rotational axis of the rotating structure. Each of the slots may extend radially through the spring section.

<FIG> illustrates an assembly <NUM> for a turbine engine. This turbine engine assembly <NUM> includes a rotating structure <NUM>, a stationary structure <NUM> and at least one bearing <NUM> rotatably mounting the rotating structure <NUM> with the stationary structure <NUM>.

The rotating structure <NUM> extends axially along and is rotatable about a rotational axis <NUM>, which rotational axis <NUM> may be coaxial with an axial centerline of the turbine engine assembly <NUM>. The rotating structure <NUM> of <FIG> includes a shaft <NUM> and a second component <NUM>. Examples of the second component <NUM> of the rotating structure <NUM> include, but are not limited to, a sleeve, a spacer, a baffle, another shaft, a coupling, a seal land and a retainer (e.g., a clip, a nut, etc.).

The shaft <NUM> of <FIG> includes a (e.g., tubular) shaft base <NUM> and a (e.g., annular) shaft shoulder <NUM>. The shaft base <NUM> extends axially along and circumferentially about (e.g., completely around) the rotational axis <NUM>. The shaft base <NUM> extends radially between and to an inner side <NUM> of the shaft <NUM> and an outer side <NUM> of the shaft base <NUM>. The shaft inner side <NUM> of <FIG> forms an internal bore <NUM> within the shaft <NUM>, which internal bore <NUM> extends axially within (e.g., and into, or through) the shaft <NUM> and its shaft base <NUM>.

The shaft shoulder <NUM> is connected to the shaft base <NUM> at the base outer side <NUM>. The shaft shoulder <NUM> of <FIG> projects radially out from the shaft base <NUM> and its base outer side <NUM> to a distal end <NUM> of the shaft shoulder <NUM>. The shaft shoulder <NUM> of <FIG> extends axially along the rotational axis <NUM> between and to a first side <NUM> of the shaft shoulder <NUM> and a second side <NUM> of the shaft shoulder <NUM>. The shaft shoulder <NUM> may extend circumferentially about (e.g., completely around) the rotational axis <NUM>.

The stationary structure <NUM> of <FIG> includes a bearing support <NUM>, a fixed support <NUM> and a bumper <NUM>.

The bearing support <NUM> of <FIG> is cantilevered from another portion <NUM> of the stationary structure <NUM>. The bearing support <NUM>, for example, projects axially along the rotational axis <NUM> out from the stationary structure portion <NUM> to a distal (e.g., unsupported) end <NUM> of the bearing support <NUM>. Referring to <FIG>, the bearing support <NUM> extends circumferentially about (e.g., completely around) the rotational axis <NUM>, thereby providing the bearing support <NUM> with a tubular body. The bearing support <NUM> may be configured as a flexible bearing support. The bearing support <NUM> of <FIG>, for example, includes a mount section <NUM>, an intermediate (e.g., spring) section <NUM> and a bearing support section <NUM>.

The mount section <NUM> extends axially along the rotational axis <NUM> between and to the stationary structure portion <NUM> and the intermediate section <NUM>. The mount section <NUM> is connected to (e.g., formed integral with or otherwise attached to) the stationary structure portion <NUM> and the intermediate section <NUM>. The mount section <NUM> thereby connects and structurally ties the bearing support <NUM> to the stationary structure portion <NUM>. The mount section <NUM> of <FIG> extends circumferentially about (e.g., completely around) the rotational axis <NUM>, and may be circumferentially and/or axially uninterrupted.

The intermediate section <NUM> extends axially along the rotational axis <NUM> between and to the mount section <NUM> and the support section <NUM>. The intermediate section <NUM> is connected to (e.g., formed integral with or otherwise attached to) the mount section <NUM> and the support section <NUM>. The intermediate section <NUM> thereby connects and structurally ties the support section <NUM> to the mount section <NUM>. Furthermore, under normal operating conditions, the intermediate section <NUM> may provide the only structural support for the support section <NUM> given, for example, the cantilevered connection of the bearing support <NUM> to the stationary structure portion <NUM>. The intermediate section <NUM> of <FIG> extends circumferentially about (e.g., completely around) the rotational axis <NUM>, and may be circumferentially and/or axially interrupted; e.g., configured as a squirrel cage spring. The intermediate section <NUM> of <FIG>, for example, includes a plurality of beams <NUM> and/or a plurality of slots <NUM>.

The beams <NUM> and the slots <NUM> are distributed circumferentially about the rotational axis <NUM>. The beams <NUM> are interspersed with the slots <NUM> such that: (A) each of the beams <NUM> is disposed and extends laterally (e.g., circumferentially or tangentially) between a respective lateral neighboring (e.g., adjacent) pair of the slots <NUM>; and (B) each of the slots <NUM> is disposed and extends laterally within the intermediate section <NUM> between a respective laterally neighboring pair of the beams <NUM>. Each of the beams <NUM> extends axially along the rotational axis <NUM> between and is connected to the mount section <NUM> and the support section <NUM>. Each of the slots <NUM> extends axially along the rotational axis <NUM> within the bearing support <NUM> (and through the intermediate section <NUM>) between and to the mount section <NUM> and the support section <NUM>. Referring to <FIG>, each of the slots <NUM> extends (e.g., completely) radially through the bearing support <NUM> and its intermediate section <NUM> between and to an inner side <NUM> of the intermediate section <NUM> and an outer side <NUM> of the intermediate section <NUM>, which may also be an outer side <NUM> of the bearing support <NUM>.

Referring to <FIG>, each of the beams <NUM> has a longitudinal length <NUM> and a lateral width <NUM>. The beam longitudinal length <NUM> is measured along a longitudinal centerline <NUM> of the respective beam <NUM> from the mount section <NUM> to the support section <NUM>. Each beam longitudinal centerline <NUM> of <FIG> is straight and parallel with the rotational axis <NUM>; however, the present disclosure is not limited to such an exemplary configuration. The beam lateral width <NUM> is measured between opposing lateral sides of the respective beam <NUM>; e.g., between the respective laterally neighboring pair of the slots <NUM>.

Each of the slots <NUM> has a longitudinal length <NUM> and a lateral width <NUM>, where the slot longitudinal length <NUM> is equal to the beam longitudinal length <NUM> and the slot lateral width <NUM> may be equal to or different (e.g., greater or less) than the beam lateral width <NUM>. The slot longitudinal length <NUM> is measured along a longitudinal centerline <NUM> of the respective slot <NUM> from the mount section <NUM> to the support section <NUM>. Each slot longitudinal centerline <NUM> of <FIG> is straight and parallel with the rotational axis <NUM>; however, the present disclosure is not limited to such an exemplary configuration. The slot lateral width <NUM> is measured between opposing lateral sides of the respective slot <NUM>; e.g., between the respective laterally neighboring pair of the beams <NUM>.

The dimensions (e.g., <NUM>, <NUM>, <NUM>, <NUM>) of the beams <NUM> and the slots <NUM> are selected to tune the intermediate section <NUM> to provide the bearing support <NUM> with a certain amount of flexibility. For example, referring to <FIG>, the intermediate section <NUM> and its beams <NUM> may be configured to facilitate a certain degree of twist between the support section <NUM> and the mount section <NUM> about the rotational axis <NUM>. The intermediate section <NUM> and its beams <NUM> may also or alternatively be configured to facilitate a certain degree of radial displacement between the support section <NUM> and the mount section <NUM>. The intermediate section <NUM> may thereby accommodate slight shifts between and/or vibrations in the rotating structure <NUM> and the stationary structure <NUM>.

The support section <NUM> of <FIG> extends axially along the rotational axis <NUM> between and to the intermediate section <NUM> and the support distal end <NUM>. The support section <NUM> of <FIG> extends circumferentially about (e.g., completely around) the rotational axis <NUM>, and may be circumferentially and/or axially uninterrupted. The support section <NUM> of <FIG> includes a support section base <NUM>, a support section shoulder <NUM> and a support section slot <NUM>.

The section base <NUM> extends axially along and circumferentially about (e.g., completely around) the rotational axis <NUM>. The section base <NUM> extends radially between and to an inner side <NUM> of the section base <NUM> (e.g., the intermediate section inner side <NUM>) and the support outer side <NUM>.

The section shoulder <NUM> is connected to the section base <NUM> at the base inner side <NUM>. The section shoulder <NUM> of <FIG> projects radially inward from the section base <NUM> and its base inner side <NUM> to a distal end <NUM> of the section shoulder <NUM>. The section shoulder <NUM> of <FIG> extends axially along the rotational axis <NUM> between and to a first side <NUM> of the section shoulder <NUM> and a second side <NUM> of the section shoulder <NUM>. The section shoulder <NUM> may extend circumferentially about (e.g., completely around) the rotational axis <NUM>.

The section slot <NUM> is arranged at (e.g., on, adjacent or proximate) the support distal end <NUM>. The section slot <NUM> extends circumferentially about (e.g., completely around) the rotational axis <NUM> within the section base <NUM>. Referring to <FIG>, the section slot <NUM> extends axially along the rotational axis <NUM> within the section base <NUM> between and to opposing sides <NUM> and <NUM> of the section slot <NUM>. The section slot <NUM> projects radially into the section base <NUM> from the support inner side <NUM> to an end <NUM> of the section slot <NUM>. Referring again to <FIG>, the section slot <NUM> may be configured as a receptacle for an annular retainer <NUM> (e.g., a split ring).

The fixed support <NUM> may be structurally tied to the stationary structure portion <NUM>. The fixed support <NUM> of <FIG> extends axially along the rotational axis <NUM>. The fixed support <NUM> extends circumferentially about (e.g., completely around) the rotational axis <NUM>. The fixed support <NUM> projects radially inward (e.g., towards the rotational axis <NUM>) to an inner side <NUM> of the fixed support <NUM>. The fixed support <NUM> may project radially outwards (e.g., away from the rotational axis <NUM>) to an outer side <NUM> of the fixed support <NUM>. This fixed support outer side <NUM> may form a (e.g., inner) peripheral boundary of a volume <NUM> outside of a bearing compartment <NUM> housing the bearing <NUM>, which volume <NUM> may be a flowpath <NUM> within the turbine engine.

The bumper <NUM> extends axially along the rotational axis <NUM> between and to opposing ends <NUM> and <NUM> of the bumper <NUM>. Referring to <FIG>, the bumper <NUM> extends circumferentially about (e.g., completely around) the rotational axis <NUM>, thereby providing the bumper <NUM> with a full hoop body. The bumper <NUM> of <FIG> and <FIG> is circumferentially and/or axially uninterrupted, and may be forms as a single unitary (e.g., monolithic) body. The bumper <NUM> of <FIG> extends radially between and to an inner side <NUM> of the bumper <NUM> and an outer side <NUM> of the bumper <NUM>.

Referring to <FIG>, the bumper <NUM> is configured as a (e.g., permanently) deformable body. More particularly, the bumper <NUM> may be configured as a (e.g., radially) crushable body. The bumper <NUM> may have various configurations to tune its deformation (e.g., crushability), various examples of which are described below with reference to <FIG>. The present disclosure, however, is not limited to such exemplary bumper configurations.

The bumper outer side <NUM> of <FIG> may be abutted against and/or otherwise radially engage (e.g., contact) the fixed support <NUM> and its inner side <NUM>. The bumper <NUM> is also mounted to the fixed support <NUM>. The bumper <NUM>, for example, may be fixedly secured to the fixed support <NUM> through a mechanical coupling (e.g., via interference fit, mechanical fastener, etc.), a bond (e.g., weld, braze, adhesive, etc.) joint and/or any other attachment technique.

The bumper <NUM> of <FIG> is radially outboard of and extends circumferentially about (e.g., completely around) each of the turbine engine assembly elements <NUM>, <NUM>, <NUM>, <NUM> and <NUM>. The bumper <NUM> is axially aligned with the bearing support <NUM> and its support section <NUM>. The bumper <NUM> of <FIG>, for example, axially overlaps the support section <NUM> at (or near) the support distal end <NUM>.

The bearing <NUM> may be configured as a roller element bearing. The bearing <NUM> of <FIG>, for example, includes a (e.g., tubular) inner race <NUM>, a (e.g., tubular) outer race <NUM> and a plurality of bearing elements <NUM>. These bearing elements <NUM> are arranged circumferentially about the rotational axis <NUM> in an annular array. The bearing elements <NUM> are located radially between and radially engaged with the inner race <NUM> and the outer race <NUM>.

The inner race <NUM> is mounted to the rotating structure <NUM>. The inner race <NUM> of <FIG>, for example, circumscribes and radially engages (e.g., contacts) the shaft base <NUM> and a surface thereof at its outer side <NUM>. The inner race <NUM> is axially captured and clamped between the shaft shoulder <NUM> and the second component <NUM> of the rotating structure <NUM>. The inner race <NUM> may thereby be fixed to and rotatable with the rotating structure <NUM>.

The outer race <NUM> is mounted to the stationary structure <NUM> and, more particularly, to the support section <NUM> at (e.g., on, adjacent or proximate) the support distal end <NUM>. The outer race <NUM> of <FIG>, for example, is arranged within a bore of the bearing support <NUM> and its support section <NUM>, which support section <NUM> circumscribes and radially engages (e.g., contacts) the outer race <NUM> and an outer surface thereof. The outer race <NUM> is axially captured and clamped between the section shoulder <NUM> and the retainer <NUM>. The outer race <NUM> may also or alternatively be mechanically fixed (e.g., press fit) into the bore of the support section <NUM>. The outer race <NUM> may thereby be fixed to the stationary structure <NUM> and its bearing support <NUM>.

Referring to <FIG>, during a mode of nominal (e.g., normal) turbine engine operation as well as when the turbine engine is non-operational, the bumper <NUM> is radially displaced from the bearing support <NUM> and its support section <NUM> by an (e.g., annular) air gap <NUM>. This air gap <NUM> has a height <NUM> with a first value. This gap height <NUM> extends radially between and to an (e.g., cylindrical) outer surface <NUM> of the support section <NUM> at the support outer side <NUM> and an (e.g., cylindrical) inner surface <NUM> of the bumper <NUM> at the bumper inner side <NUM>. The air gap <NUM> extends axially along the surfaces <NUM> and <NUM> for a (e.g., entire) length <NUM> of the bumper <NUM>, which bumper length <NUM> extends between and to the bumper sides <NUM> and <NUM>. The air gap <NUM> extends circumferentially about (e.g., completely around) the rotational axis <NUM>, thereby forming the air gap <NUM> as an annulus which circumscribes the support section <NUM>.

With the arrangement of <FIG>, the bumper <NUM> is (e.g., completely) structurally disengaged from (e.g., does not contact and/or structurally support) the bearing support <NUM> and its support section <NUM>. The bumper <NUM> also has a height <NUM> with a first value. This bumper height <NUM> extends radially between and to the bumper inner side <NUM> and the bumper outer side <NUM>.

Referring to <FIG>, during a first mode of off-nominal (e.g., abnormal) turbine engine operation, a first (e.g., shock and/or imbalance) load may radially displace the rotating structure <NUM> (see <FIG>). This first load is equal to or greater than a first threshold, but less than a second threshold. The first load may be generated during and/or follow from an off-nominal operating condition and/or event such as, but not limited to, a partial blade off event and/or a relatively large rotating structure imbalance. The radial displacement of the rotating structure <NUM> displaces the bearing <NUM> and the bearing support <NUM> radially outward. The support section <NUM> and its outer surface <NUM> may thereby temporarily radially engage (e.g., contact) the bumper <NUM> and its inner surface <NUM>.

During the first mode of off-nominal turbine engine operation, the bumper <NUM> provides a radial stop (e.g., a bump stop) for the rotating structure radial displacement. While the bumper <NUM> may slightly deform upon initial engagement (e.g., impact) between the surfaces <NUM> and <NUM>, this deformation may be elastic / resilient. Thus, the bumper height <NUM> may have a second value that is substantially (e.g., +/-<NUM>%) or exactly equal to the bumper height first value. A configuration of the bumper <NUM> may thereby remain substantially unchanged between the mode of nominal turbine engine operation and the first mode of off-nominal turbine engine operation.

Referring to <FIG>, during a second mode of off-nominal turbine engine operation, a second (e.g., shock and/or imbalance) load may radially displace the rotating structure <NUM> (see <FIG>). This second load is equal to or greater than the second threshold. The second load may be generated during and/or follow from an off-nominal operating condition and/or event such as, but not limited to, a full blade off event. The radial displacement of the rotating structure <NUM> displaces the bearing <NUM> and the bearing support <NUM> radially outward. The support section <NUM> and its outer surface <NUM> may thereby temporarily radially engage (e.g., contact) the bumper <NUM> and its inner surface <NUM>.

During the second mode of off-nominal turbine engine operation, the bumper <NUM> again provides a radial stop for the rotating structure radial displacement. The bumper <NUM> may also provide a damper (e.g., a shock absorber) for the displaced rotating structure <NUM>. For example, where an impact and/or pressure force of the support section <NUM> against the bumper <NUM> is equal to or greater than a deformation threshold, the bumper <NUM> may (e.g., permanently) deform radially outward. The radial displacement of the rotating structure <NUM>, more particularly, presses the support section <NUM> radially against and at least partially crushes the bumper <NUM>. This crushing may provide a relatively gradual braking effect for the radial rotating structure displacement, as compared to the support section <NUM> hitting against a non-deformable stop. Providing such a gradual braking effect may reduce or prevent further damage to the rotating structure <NUM> and/or other components of the turbine engine. The crushing may also tune a response of the rotating structure <NUM>, for example, by changing rotor-dynamic modes. Following this deformation (e.g., crushing), the bumper height <NUM> has a third value that is less than the bumper height first and second values. The bumper height third value, for example, may be less than four-fifths (<NUM>/<NUM>), two-thirds (<NUM>/<NUM>), one-half (<NUM>/<NUM>), one-third (<NUM>/<NUM>) or otherwise of the bumper height first value. The present disclosure, however, is not limited to the foregoing exemplary dimensional relationship.

Referring to <FIG>, following the second mode of off-nominal turbine engine operation, the bumper <NUM> may remain substantially or completely deformed. The bumper height <NUM>, for example, may have a fourth value that is substantially (e.g., +/-<NUM>%) or exactly equal to the bumper height third value. Thus, when the turbine engine is non-operational for example, the gap height <NUM> has a second value that is greater than the gap height first value (see <FIG>) prior to the deformation (e.g., crushing) of the bumper <NUM>.

Referring to <FIG>, the bumper <NUM> is configured with a porous body. The bumper <NUM> of <FIG>, for example, includes a plurality of internal cavities <NUM> (e.g., pores, chambers, interstices), which cavities <NUM> provide space for the bumper <NUM> to deform; e.g., crush. One or more of the cavities <NUM> may be configured as separate, fluidly discrete cavities. One or more of the cavities <NUM> may also or alternatively be fluidly coupled with another one or more of the cavities <NUM>; e.g., the cavities <NUM> may be interconnected to provide a volume. The bumper <NUM> is constructed from a bumper material such as, but not limited to, a metal, a polymer, a composite material or a combination thereof.

In some embodiments, referring to <FIG>, the bumper <NUM> may be configured with or otherwise include honeycomb <NUM>; e.g., a honeycomb body. Each cavity <NUM> of <FIG>, for example, is configured with a polygonal (e.g., hexagonal) cross-sectional geometry when viewed, for example, in a plane perpendicular to a centerline <NUM> of the respective cavity <NUM>. Referring to <FIG>, the cavity centerline <NUM> may be arranged perpendicular to the bumper inner surface <NUM> / the bumper inner side <NUM>. Each cavity <NUM> of <FIG>, for example, may extends longitudinally along its cavity centerline <NUM> between and to (or about) the bumper inner side <NUM> and the bumper outer side <NUM>.

In some embodiments, referring to <FIG>, the bumper <NUM> may be configured with or otherwise include foam; e.g., a foam body. Referring to <FIG>, the foam may be configured as open cell foam <NUM> where its internal cavities <NUM> (e.g., pores) are interconnected. Referring to <FIG>, the foam may alternatively be configured as closed cell foam <NUM> where its internal cavities <NUM> are discrete.

In some embodiments, referring to <FIG>, the bumper <NUM> may be configured with or otherwise include a lattice structure <NUM>; e.g., a lattice structure body. This lattice structure <NUM> may include one or more repeated cells, where each cell may include a plurality (e.g., a pattern) of interconnected elements <NUM>; e.g., columns.

Referring to <FIG>, the structure / configuration of the bumper <NUM> may be uniform axially across an axial length of the bumper <NUM> between and to the bumper ends <NUM> and <NUM> (see <FIG>). The structure / configuration of the bumper <NUM> may be uniform circumferentially about (e.g., completely around) the rotational axis <NUM>. The structure / configuration of the bumper <NUM> may also be uniform radially across the (e.g., radial) height <NUM> (see <FIG>) of the bumper <NUM> between and to the bumper sides <NUM> and <NUM>. Such an arrangement may provide the bumper <NUM> with a uniform damping characteristic. In other embodiments however, referring to <FIG> and <FIG>, the structure / configuration of the bumper <NUM> may be non-uniform to tailor the bumper <NUM> with a progressive stiffness characteristic and/or a progressive damping characteristic.

Referring to <FIG>, an inner portion 158A (e.g., radial zone) of the bumper <NUM> may be configured with a different stiffness characteristic and/or a different damping characteristic than an outer portion 158B (e.g., radial zone) of the bumper <NUM>. The bumper inner portion 158A is configured to deform (e.g., crush) when subject to an inner portion load. The bumper outer portion 158B is configured to deform (e.g., crush) when subject to an outer portion load, where the outer portion load is different (e.g., greater or less) than the inner portion load. The bumper inner portion 158A, for example, may be configured with an inner portion porosity and an inner portion density. The bumper outer portion 158B may be configured with an outer portion porosity and an outer portion density, where the outer portion porosity is different (e.g., greater or less) than the inner portion porosity and the outer portion density is different (e.g., less or greater) than the inner portion density. For example, the bumper inner portion 158A may be provided with an inner portion number of the internal cavities <NUM>, where each of those internal cavities <NUM> has an inner portion dimension (e.g., diameter, length, etc.). The bumper outer portion 158B may be provided with an outer portion number of the internal cavities <NUM>, where each of those internal cavities <NUM> has an outer portion dimension (e.g., diameter, length, etc.). The inner portion number may be different (e.g., greater or less) than or equal to the outer portion number. The inner portion dimension may be different (e.g., greater or less) than or equal to the outer portion dimension.

For ease of illustration, the bumper inner portion 158A of IFG. <NUM> is shown with a greater density than the bumper outer portion 158B. However, in other embodiments, the bumper outer portion 158B may have a greater density than the bumper inner portion 158A.

The bumper <NUM> is described above as including two (the inner and outer) portions 158A and 158B for tuning the stiffness characteristic and/or the damping characteristic. However, the bumper <NUM> may include more than two bumper portions; e.g., radial zones. For example, referring to <FIG>, the bumper <NUM> may also include an intermediate portion 158C radially between the bumper inner portion 158A and the bumper outer portion 158B. Each of these bumper portions 158A-C (generally referred to as "<NUM>") may be configured with a unique structure. Each of the bumper portions <NUM>, for example, may be configured to deform (e.g., crush) when subject to a different load. Alternatively, some of the bumper portions <NUM> (e.g., 158A and 158B), but not all of the bumper portions <NUM> (e.g., 158C) for example, may be configured with a common structure. Any two of the bumper portions <NUM>, for example, may be configured to deform (e.g., crush) when subject to a first load whereas the remaining bumper portion <NUM> may be configured to deform (e.g., crush) when subject to a different (e.g., larger or small) second load.

In some embodiments, referring to <FIG>, the bumper <NUM> may be further tailored by at least partially or completely filling one or more of the internal cavities <NUM> with filler material <NUM>. The cavities <NUM> in the bumper inner portion 158A of <FIG>, for example, are filled with the filler material <NUM>, whereas the cavities <NUM> in the bumper outer portion 158B are empty. Of course, in other embodiments, the cavities <NUM> in the bumper outer portion 158B may be filled with the filler material <NUM>, and the cavities <NUM> in the bumper inner portion 158A may be empty (or partially or completely filled with the same filler material <NUM> or a different filler material). Examples of the filler material <NUM> include, but are not limited to, a polymer material and a potting material.

For ease of illustration, the bumpers <NUM> of <FIG> are shown with honeycomb cores. However, the foregoing teachings may also be applied to bumpers <NUM> with other configurations. For example, the porosity, the density, the number of internal cavities <NUM>, the dimensions of the internal cavities <NUM> and/or whether or not the internal cavities <NUM> are filled or empty may be tailored for the foam <NUM>, <NUM> or the lattice structure <NUM>. Furthermore, it is also contemplated that the different portions <NUM> of the bumper <NUM> may be tailored with different internal structures. For example, one of the bumper portions <NUM> may have a honeycomb configuration whereas another one of the bumper portions <NUM> may have a foam configuration, etc. The present disclosure therefore is not limited to the foregoing exemplary bumper configurations.

<FIG> illustrates an example of the turbine engine with which the turbine engine assembly <NUM> may be configured. This turbine engine is configured as a turbofan gas turbine engine <NUM>. This turbine engine <NUM> of <FIG> extends along the rotational axis <NUM> between an upstream airflow inlet <NUM> and a downstream airflow exhaust <NUM>. The turbine engine <NUM> includes a fan section <NUM>, a compressor section <NUM>, a combustor section <NUM> and a turbine section <NUM>.

The fan section <NUM> includes a fan rotor <NUM>. The compressor section <NUM> includes a compressor rotor <NUM>. The turbine section <NUM> includes a high pressure turbine (HPT) rotor <NUM> and a low pressure turbine (LPT) rotor <NUM>, where the LPT rotor <NUM> is configured as a power turbine rotor. Each of these rotors <NUM>-<NUM> includes a plurality of rotor blades arranged circumferentially around and connected to one or more respective rotor disks.

The fan rotor <NUM> is connected to the LPT rotor <NUM> through a low speed shaft <NUM>, which provides a low speed rotating structure 22A. The compressor rotor <NUM> is connected to the HPT rotor <NUM> through a high speed shaft <NUM>, which provides a high speed rotating structure 22B. The rotating structure <NUM> of <FIG> may be configured as or otherwise included in either of the low speed rotating structure 22A or the high speed rotating structure 22B, and the shaft <NUM> may be configured as or otherwise included in the respective shaft <NUM>, <NUM>.

During operation, air enters the turbine engine <NUM> through the airflow inlet <NUM>. This air is directed through the fan section <NUM> and into a core flowpath <NUM> (e.g., the flowpath <NUM> of <FIG>) and a bypass flowpath <NUM>. The core flowpath <NUM> extends sequentially through the engine sections <NUM>-<NUM>; e.g., an engine core. The air within the core flowpath <NUM> may be referred to as "core air". The bypass flowpath <NUM> extends through a bypass duct, which bypasses the engine core. The air within the bypass flowpath <NUM> may be referred to as "bypass air".

The core air is compressed by the compressor rotor <NUM> and directed into a combustion chamber <NUM> of a combustor <NUM> in the combustor section <NUM>. This fuel-air mixture is ignited and combustion products thereof flow through and sequentially cause the HPT rotor <NUM> and the LPT rotor <NUM> to rotate. The rotation of the HPT rotor <NUM> drives rotation of the compressor rotor <NUM> and, thus, compression of air received from an inlet into the core flowpath <NUM>. The rotation of the LPT rotor <NUM> drives rotation of the fan rotor <NUM>, which propels bypass air through and out of the bypass flowpath <NUM>. The propulsion of the bypass air may account for a significant portion (e.g., a majority) of thrust generated by the turbine engine <NUM>.

The turbine engine assembly <NUM> and/or its bumper <NUM> may be included in various turbine engines other than the ones described above. The turbine engine assembly <NUM> and/or its bumper <NUM>, for example, may be included in a geared turbine engine where a gear train connects one or more shafts to one or more rotors in a fan section, a compressor section and/or any other engine section. Alternatively, the turbine engine assembly <NUM> and/or its bumper <NUM> may be included in a turbine engine configured without a gear train; e.g., a direct drive turbine engine. The turbine engine assembly <NUM> and/or its bumper <NUM> may be included in a geared or non-geared turbine engine configured with a single spool, with two spools (e.g., see <FIG>), or with more than two spools. The turbine engine may be configured as a turbofan engine, a turbojet engine, a turboprop engine, a turboshaft engine, a propfan engine, a pusher fan engine, an auxiliary power unit (APU) or any other type of turbine engine. The present disclosure therefore is not limited to any particular types or configurations of turbine engines. In addition, while the turbine engine is described above for use in an aircraft application, the present disclosure is not limited to such aircraft applications. For example, the turbine engine may alternatively be configured as an industrial gas turbine engine, for example, for a land based power plant.

Claim 1:
An assembly (<NUM>) for a turbine engine, comprising:
a rotating structure (<NUM>);
a bearing (<NUM>) supporting the rotating structure (<NUM>); and
a stationary structure (<NUM>) including a bearing support (<NUM>) and a bumper (<NUM>);
the bearing support (<NUM>) cantilevered from another portion (<NUM>) of the stationary structure (<NUM>), the bearing support (<NUM>) including a plurality of beams (<NUM>) and a bearing support section (<NUM>), the plurality of beams (<NUM>) distributed circumferentially about an axis (<NUM>) and projecting axially along the axis (<NUM>) to the bearing support section (<NUM>), wherein the bearing (<NUM>) is mounted to the bearing support section (<NUM>) at an unsupported end (<NUM>) of the bearing support (<NUM>); and
the bumper (<NUM>) configured as a deformable body which is configured to deform when the bearing support section (<NUM>) subjects the bumper (<NUM>) to a radial load over a threshold.