阅读说明：本技术 燃气涡轮发动机的旋转鼓形转子的阻尼器组件 (Damper assembly for a rotating drum rotor of a gas turbine engine ) 是由 P·潘卡 N·帕约尔 S·S·普拉尼克 于 2020-11-27 设计创作，主要内容包括：本发明涉及燃气涡轮发动机的旋转鼓形转子的阻尼器组件,具体而言燃气涡轮发动机包括可旋转鼓形转子,其具有固连到其的多个叶片。叶片从可旋转鼓形转子径向地向内延伸。燃气涡轮发动机还包括安装在旋转鼓形转子的径向外侧的支撑框架和转子支撑系统,其具有定位在可旋转鼓形转子和支撑框架之间的轴承组件。轴承组件至少包括固定部件和至少一个可旋转部件。此外,燃气涡轮发动机包括用于固连在支撑框架和可旋转鼓形转子之间的阻尼器组件。此外,阻尼器组件包括至少一个阻尼器,该阻尼器固连在支撑框架和轴承组件的固定部件之间或者固连到可旋转鼓形转子的表面。照此,(多个)阻尼器被构造成在燃气涡轮发动机的操作期间向可旋转鼓形转子提供阻尼。(The present invention relates to a damper assembly for a rotating drum rotor of a gas turbine engine, in particular a gas turbine engine comprising a rotatable drum rotor having a plurality of blades secured thereto. The blades extend radially inwardly from the rotatable drum rotor. The gas turbine engine also includes a support frame mounted radially outward of the rotating drum rotor and a rotor support system having a bearing assembly positioned between the rotatable drum rotor and the support frame. The bearing assembly includes at least a stationary component and at least one rotatable component. Further, the gas turbine engine includes a damper assembly for securing between the support frame and the rotatable drum rotor. Furthermore, the damper assembly comprises at least one damper which is secured between the support frame and a stationary part of the bearing assembly or to a surface of the rotatable drum rotor. As such, the damper(s) is configured to provide damping to the rotatable drum rotor during operation of the gas turbine engine.)

1. A gas turbine engine, comprising:

a rotatable drum rotor comprising a plurality of blades secured thereto, the plurality of blades extending radially inward from the rotatable drum rotor;

a support frame mounted radially outwardly of the rotating drum rotor;

a rotor support system comprising a bearing assembly positioned between the rotatable drum rotor and the support frame, the bearing assembly comprising at least a fixed component and at least one rotatable component; and

a damper assembly secured between the support frame and the rotatable drum rotor, the damper assembly comprising at least one damper secured between the support frame and the stationary component of the bearing assembly or to a surface of the rotatable drum rotor, the at least one damper configured to provide damping to the rotatable drum rotor during operation of the gas turbine engine.

2. The gas turbine engine of claim 1, wherein the at least one damper comprises at least one of a shape memory alloy damper, a metal damper, a fluid-based damper, a spring-type damper, one or more sleeve dampers, or a combination thereof.

3. The gas turbine engine of claim 2, wherein said at least one damper comprises said one or more sleeve dampers comprising a plurality of sleeve dampers arranged in series on an outer or inner surface of said rotatable drum rotor.

4. The gas turbine engine of claim 1, wherein the stationary component and the at least one rotatable component of the bearing assembly each comprise a stationary race and a plurality of roller elements.

5. The gas turbine engine of claim 4, wherein the stationary race corresponds to an outer race of the bearing assembly.

6. The gas turbine engine of claim 4, wherein the stationary race corresponds to an inner race of the bearing assembly.

7. The gas turbine engine of claim 1, wherein the bearing assembly comprises a plurality of roller bearings circumferentially spaced about the rotatable rotor drum and secured to the support frame via a stationary support frame, the stationary and at least one rotatable component of the bearing assembly comprising the stationary support frame and the plurality of roller bearings, respectively.

8. The gas turbine engine of claim 1, wherein the at least one damper of the damper assembly is comprised of one or more annular members, one or more of the annular members being connected via one or more radially extending struts.

9. The gas turbine engine of claim 1, wherein the damper assembly comprises a plurality of circumferentially spaced dampers each comprised of one or more corrugated plates having a leaf spring arrangement.

10. The gas turbine engine of claim 1, wherein the damper assembly comprises a plurality of circumferentially spaced dampers each comprising a box-shaped structure, each of the box-shaped structures defining a stop feature designed to limit deflection of the damper assembly.

Technical Field

The present disclosure relates generally to gas turbine engines and more particularly to damper assemblies for rotatable drum rotors of gas turbine engines.

Background

The gas turbine engine generally includes, in serial flow order, an inlet section, a compressor section, a combustion section, a turbine section, and an exhaust section. In operation, air enters the inlet section and flows to the compressor section where one or more axial compressors progressively compress the air until it reaches the combustion section. Fuel is mixed with the compressed air and combusted within the combustion section to produce combustion gases. The combustion gases flow from the combustion section through a hot gas path defined within the turbine section, and then exit the turbine section via an exhaust section.

In a particular configuration, the compressor section includes, in serial flow order, a Low Pressure Compressor (LPC) and a High Pressure Compressor (HPC). The LPC and HPC may include one or more axially spaced stages. Each stage may include a row of circumferentially spaced stator vanes and a row of circumferentially spaced rotor blades positioned downstream from the row of stator vanes. The stator vanes direct air flowing through the compressor section onto the rotor blades, which transfer kinetic energy into the air to increase its pressure.

The pressurized air exiting the HPC may then flow to a combustor where fuel is injected into the pressurized air stream and the resulting mixture is combusted within the combustor. The high energy combustion products are directed from the combustor along the hot gas path of the engine to a High Pressure Turbine (HPT) for driving the HPC via a high pressure drive shaft, and then to a Low Pressure Turbine (LPT) for driving the LPC. After driving each of the LPT and HPT, the combustion products may be discharged via an exhaust nozzle to provide propulsive jet thrust.

Various rotating drum rotors (e.g., in HPC and LPT) throughout various sections of a gas turbine engine typically experience high deflections at their free ends during bending mode or gyroscopic loading conditions. Accordingly, an improved rotor support system having a damper assembly at the free end of such a rotating drum rotor would be welcomed in the technology.

Disclosure of Invention

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

In one aspect, the present disclosure is directed to a gas turbine engine. The gas turbine engine includes a rotatable drum rotor having a plurality of blades secured thereto. The blades extend radially inwardly from the rotatable drum rotor. The gas turbine engine also includes a support frame mounted radially outward of the rotating drum rotor and a rotor support system having a bearing assembly positioned between the rotatable drum rotor and the support frame. The bearing assembly includes at least a stationary component and at least one rotatable component. In addition, the gas turbine engine includes a damper assembly secured between the support frame and the rotatable drum rotor. Furthermore, the damper assembly comprises at least one damper which is secured between the support frame and a stationary part of the bearing assembly or to a surface of the rotatable drum rotor. As such, the damper(s) is configured to provide damping to the rotatable drum rotor during operation of the gas turbine engine.

In another aspect, the present disclosure is directed to a rotor support system for a gas turbine engine. The gas turbine engine includes a rotatable drum rotor and a support frame. The rotor support system includes a bearing assembly configured for positioning between the rotatable drum rotor and the support frame. The bearing assembly includes at least a stationary component and at least one rotatable component. In addition, the gas turbine engine includes a damper assembly secured between the support frame and the rotatable drum rotor. Furthermore, the damper assembly comprises at least one damper which is secured between the support frame and a stationary part of the bearing assembly or to a surface of the rotatable drum rotor. As such, the damper(s) is configured to provide damping to the rotatable drum rotor during operation of the gas turbine engine.

Technical solution 1. a gas turbine engine, comprising:

a rotatable drum rotor comprising a plurality of blades secured thereto, the plurality of blades extending radially inward from the rotatable drum rotor;

a support frame mounted radially outwardly of the rotating drum rotor;

a rotor support system comprising a bearing assembly positioned between the rotatable drum rotor and the support frame, the bearing assembly comprising at least a fixed component and at least one rotatable component; and

a damper assembly secured between the support frame and the rotatable drum rotor, the damper assembly comprising at least one damper secured between the support frame and the stationary component of the bearing assembly or to a surface of the rotatable drum rotor, the at least one damper configured to provide damping to the rotatable drum rotor during operation of the gas turbine engine.

Solution 2. the gas turbine engine of any of the preceding claims, wherein the at least one damper comprises at least one of a shape memory alloy damper, a metal damper, a fluid-based damper, a spring-type damper, one or more sleeve dampers, or a combination thereof.

Solution 3. the gas turbine engine of any preceding solution, wherein said at least one damper comprises said one or more sleeve dampers comprising a plurality of sleeve dampers arranged in series on an outer or inner surface of said rotatable drum rotor.

Solution 4. the gas turbine engine of any preceding solution, wherein the stationary component and the at least one rotatable component of the bearing assembly each comprise a stationary race and a plurality of roller elements.

Claim 5. the gas turbine engine of any preceding claim, wherein the stationary race corresponds to an outer race of the bearing assembly.

Solution 6. the gas turbine engine of any preceding solution, wherein the stationary race corresponds to an inner race of the bearing assembly.

Solution 7. the gas turbine engine of any preceding solution, wherein the bearing assembly comprises a plurality of roller bearings circumferentially spaced about the rotatable rotor drum and secured to the support frame via a stationary support frame, the stationary and at least one rotatable component of the bearing assembly comprising the stationary support frame and the plurality of roller bearings, respectively.

The gas turbine engine of any preceding claim, wherein the at least one damper of the damper assembly is comprised of one or more ring members, one or more of which are connected via one or more radially extending struts.

Solution 9. the gas turbine engine of any preceding solution, wherein the damper assembly comprises a plurality of circumferentially spaced dampers each comprised of one or more corrugated plates having a leaf spring arrangement.

The gas turbine engine of any preceding claim, wherein the damper assembly comprises a plurality of circumferentially spaced dampers each comprising a box-shaped structure, each of the box-shaped structures defining a stop feature designed to limit deflection of the damper assembly.

The gas turbine engine of any of the preceding claims, wherein the at least one damper of the damper assembly is prestrained.

Solution 12. the gas turbine engine of any preceding solution, wherein the rotatable drum rotor is part of a compressor section, a turbine section or a combustion section of the gas turbine engine.

In accordance with claim 13, a rotor support system for a gas turbine engine, said gas turbine engine including a rotatable drum rotor and a support frame, said rotor support system comprising:

a bearing assembly configured for positioning between the rotatable drum rotor and the support frame, the bearing assembly comprising at least a stationary component and at least one rotatable component; and

a damper assembly for securing between the support frame and the rotatable drum rotor, the damper assembly comprising at least one damper secured between the support frame and the stationary component of the bearing assembly or to a surface of the rotatable drum rotor, the at least one damper configured to provide damping to the rotatable drum rotor during operation of the gas turbine engine.

Solution 14. the rotor support system of any preceding solution, wherein the at least one damper comprises at least one of a shape memory alloy damper, a metal damper, a fluid-based damper, one or more sleeve dampers, a spring-type damper, or a combination thereof.

Solution 15. the rotor support system of any preceding solution, wherein said at least one damper comprises said one or more sleeve dampers, said one or more sleeve dampers comprising a plurality of sleeve dampers arranged in series on an outer or inner surface of said rotatable drum rotor.

The rotor support system of any preceding claim, wherein the stationary component and the at least one rotatable component of the bearing assembly each comprise a stationary race and a plurality of roller elements, and wherein the at least one damper of the damper assembly comprises a spring-like configuration.

The rotor support system of any of the preceding claims, wherein the stationary race corresponds to at least one of an outer race of the bearing assembly or an inner race of the bearing assembly.

The rotor support system of claim 18, wherein the bearing assembly comprises a plurality of roller bearings circumferentially spaced about the rotatable rotor drum and secured to the support frame via a stationary support frame, the stationary and at least one rotatable component of the bearing assembly comprising the stationary support frame and the plurality of roller bearings, respectively.

Solution 19. the rotor support system of any preceding solution, wherein the at least one damper of the damper assembly is comprised of one or more annular members, one or more of which are connected via one or more radially extending struts.

Solution 20. the rotor support system of any preceding solution, wherein the at least one damper of the damper assembly is pre-strained.

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

Drawings

A full and enabling disclosure of the present invention, including the best mode thereof, directed to one of ordinary skill in the art, is set forth in the specification, which makes reference to the appended figures, in which:

FIG. 1 illustrates a cross-sectional view of an embodiment of a gas turbine engine that may be used within an aircraft according to the present disclosure;

FIG. 2 illustrates a cross-sectional view of an embodiment of a section of a gas turbine engine, particularly illustrating a rotor support system having a damper assembly disposed within a bearing assembly positioned between a rotatable drum rotor and a support frame in accordance with the present disclosure;

FIG. 3 illustrates a front view of a bearing assembly of the rotor support system of FIG. 2;

FIG. 4 illustrates a cross-sectional view of another embodiment of a section of a gas turbine engine, particularly illustrating a rotor support system having a damper assembly disposed within a bearing assembly positioned between a rotatable drum rotor and a support frame in accordance with the present disclosure;

FIG. 5 illustrates a front view of the bearing assembly of the rotor support system of FIG. 4;

FIG. 6 illustrates a partial perspective view of an embodiment of one of the bearing assembly and the damper assembly of the rotor support system according to the present disclosure;

FIG. 7 illustrates a partial perspective view of another embodiment of one of the bearing assembly and the damper assembly of the rotor support system according to the present disclosure;

FIG. 8 illustrates a front view of another embodiment of a bearing assembly of the rotor support system according to the present disclosure;

FIG. 9 illustrates a front view of yet another embodiment of a bearing assembly of the rotor support system according to the present disclosure;

FIG. 10 illustrates a front view of yet another embodiment of a bearing assembly of a rotor support system according to the present disclosure;

FIG. 11 illustrates a cross-sectional view of another embodiment of a section of a gas turbine engine, particularly illustrating a damper assembly positioned between a rotatable drum rotor and a support frame according to the present disclosure;

FIG. 12 illustrates a cross-sectional view of another embodiment of a section of a gas turbine engine, particularly illustrating a damper assembly positioned between a rotatable drum rotor and a support frame according to the present disclosure.

Detailed Description

Reference now will be made in detail to embodiments of the invention, one or more examples of which are illustrated in the drawings. Each example is provided by way of explanation of the invention, not limitation of the invention. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made in the present invention without departing from the scope or spirit of the invention. For instance, features illustrated or described as part of one embodiment, can be used with another embodiment to yield a still further embodiment. Thus, it is intended that the present invention cover the modifications and variations of this invention provided they come within the scope of the appended claims and their equivalents.

Referring now to the drawings, FIG. 1 illustrates a cross-sectional view of one embodiment of a gas turbine engine 10 that may be used within an aircraft in accordance with aspects of the present subject matter, the engine 10 being shown with a longitudinal or axial centerline axis 12 extending therethrough for reference purposes. In general, the engine 10 may include a core gas turbine engine (generally indicated by reference numeral 14) and a fan section 16 positioned upstream thereof. The core engine 14 may generally include a substantially tubular outer casing 18 defining an annular inlet 20. Additionally, the outer casing 18 may further enclose and support a low pressure booster compressor 22 for increasing the pressure of the air entering the core engine 14 to a first pressure level. The high pressure multistage axial compressor 24 may then receive pressurized air from the booster compressor 22 and further increase the pressure of such air. The pressurized air exiting the high pressure compressor 24 may then flow to the combustor 26, where fuel is injected into the pressurized air stream, and the resulting mixture is combusted within the combustor 26. The high energy combustion products are directed from the combustion chamber 26 along the hot gas path of the engine 10 to a first (high pressure) turbine 28 for driving the high pressure compressor 24 via a first (high pressure) drive shaft 30, and then to a second (low pressure) turbine 32 for driving the booster compressor 22 and the fan section 16 via a second (low pressure) drive shaft 34, which is generally coaxial with the first drive shaft 30. After driving each of turbines 28 and 32, the combustion products may be discharged from core engine 14 via exhaust nozzle 36 to provide propulsive jet thrust.

Additionally, as shown in FIG. 1, the fan section 16 of the engine 10 may generally include a rotatable axial fan rotor assembly 38 configured to be surrounded by an annular fan casing 40. It should be appreciated by those of ordinary skill in the art that the fan casing 40 may be configured to be supported relative to the core engine 14 by a plurality of substantially radially extending, circumferentially spaced outlet guide vanes 42. As such, the fan housing 40 may enclose the fan rotor assembly 38 and its corresponding fan rotor blades 44. Further, a downstream section 46 of the fan casing 40 may extend over an exterior portion of the core engine 14 to define a secondary or bypass airflow duct 48 that provides additional propulsive jet thrust.

It should be appreciated that, in several embodiments, the second (low pressure) drive shaft 34 may be directly coupled to the fan rotor assembly 38 to provide a direct drive configuration. Alternatively, the second drive shaft 34 may be coupled to the fan rotor assembly 38 via a reduction device 37 (e.g., a reduction gear or gearbox) to provide an indirect drive or geared drive configuration. Such reduction device(s) may also be disposed between any other suitable shaft and/or rotating shaft within the engine as needed or desired.

During operation of engine 10, it should be appreciated that an initial flow of air (indicated by arrow 50) may enter engine 10 through an associated inlet 52 of fan housing 40. The air flow 50 then passes through the fan blades 44 and is split into a first compressed air flow (indicated by arrow 54) moving through the conduit 48 and a second compressed air flow (indicated by arrow 56) entering the booster compressor 22. The pressure of the second compressed air stream 56 then increases and enters the high pressure compressor 24 (indicated by arrow 58). After being mixed with fuel and combusted within the combustor 26, the combustion products 60 exit the combustor 26 and flow through the first turbine 28. Thereafter, the combustion products 60 flow through the second turbine 32 and exit the exhaust nozzle 36 to provide thrust for the engine 10.

Referring now to FIG. 2, a cross-sectional view of an embodiment of a rotor support system 100 suitable for use within gas turbine engine 10 is illustrated, particularly illustrating rotor support system 100 mounted with respect to one of high pressure compressor 24 or low pressure turbine 32 of gas turbine engine 10, in accordance with aspects of the present subject matter. Accordingly, it should be appreciated that the rotor support system 100 may be part of a compressor section, a turbine section, or a combustion section of the gas turbine engine 10. As shown in FIG. 2, the rotor support system 100 may generally include a rotatable drum rotor 102 configured to support a plurality of blades 104 extending radially inward therefrom. Further, as shown, the rotatable drum rotor 102 has a front end 105 and a rear end 107.

Still referring to fig. 2, the rotatable drum rotor 102 may be supported within the engine 10 by one or more bearing assemblies 106 of the rotor support system 100, each bearing assembly 106 being configured to rotatably support the rotatable drum rotor 102 relative to a structural support frame 108 (such as the outer casing 18 of fig. 1) of the gas turbine engine 10 mounted radially outward of the rotatable drum rotor 102. For example, as shown in fig. 2, a bearing assembly 106 may be coupled between the rotatable drum rotor 102 and the support frame 108 of the rotor support system 100.

Referring to fig. 2-5, in several embodiments, the bearing assembly 106 may include at least a stationary component 110 and at least one rotating component 112. Furthermore, as shown, the bearing assembly 106 may be positioned at any suitable axial position along the rotatable drum rotor 102, such as at the trailing end 107, which rotatable drum rotor 102 may be substantially cantilevered. More specifically, as shown in fig. 2 and 3, in one embodiment, the stationary component 110 and the rotatable component(s) 112 of the bearing assembly 106 may include a stationary race 111 and a plurality of roller elements 113, respectively. In such an embodiment, as shown in fig. 3, the stationary race 111 may correspond to an outer race of the bearing assembly 106. In an alternative embodiment, the stationary race 111 may correspond to an inner race of the bearing assembly 106. The roller elements 113 described herein may generally correspond to any suitable bearing element, such as balls or rollers.

Referring to fig. 4-7, various views of additional embodiments of a bearing assembly 106 according to the present disclosure are shown. As shown in each of fig. 5-7, the stationary component 110 and the rotatable component(s) 112 of the illustrated bearing assembly 106 may include a stationary support frame 115 and a plurality of roller bearings 116, respectively. For example, as shown in fig. 5-7, the stationary support frame 115 may extend circumferentially around the rotating drum rotor 102 and through an inner race 119 of each roller bearing 116. Further, as shown, the roller bearings 116 may be circumferentially spaced about the rotatable rotor drum 102 and secured to the support frame 108 via a stationary support frame 115.

Furthermore, as generally shown in fig. 2 and 6-7, the rotor support system 100 may also include a damper assembly 114 secured between the support frame 108 and the stationary member 110 of the bearing assembly 106. Further, damper assembly 114 includes at least one damper 117, which damper 117 is configured to provide damping to rotatable drum rotor 102 during operation of gas turbine engine 10. For example, the damper(s) 117 may include a shape memory alloy damper, a metal damper, a fluid-based damper, one or more sleeve dampers (e.g., such as an annular damper), a spring-type damper, and/or combinations thereof.

Furthermore, in certain embodiments, as shown in fig. 2 and 4, the damping assembly 114 may further comprise a squirrel cage 125 (or spring finger design) for supporting the rotatable drum rotor 102 and providing the desired flexibility/stiffness and also providing centering for the damping assembly. For example, as shown, squirrel cage 125 has a U-shape, but it should be understood that squirrel cage 125 may have any suitable shape in order to provide the desired flexibility/stiffness and/or to accommodate damper assembly 114.

Thus, in several embodiments, as shown in fig. 2, the damper(s) 117 described herein may extend longitudinally between a first end 121 and a second end 123, the first end 121 being coupled to the support frame 108, and the second end 123 being coupled to the stationary member 110 (or directly to the squirrel cage 125). Further, as shown in FIG. 2, the individual dampers 117 of the damper assembly 114 may have a spring-like configuration and/or any suitable shape or configuration that provides the desired flexibility. Thus, in one embodiment, the damper(s) described herein may be pre-strained.

As noted above, in several embodiments, damper(s) 117 described herein may be formed from any suitable material, such as a metal or shape memory alloy, for example, to allow damper(s) 117 to deform during high load events and then return to their original shape during normal load events. For the metal damper(s) 117, the friction (e.g. different E-values) between the metal damper and the surface of the rotatable drum rotor 102 results in damping.

For shape memory alloy damper(s) 117, this material allows the damper(s) to undergo large recoverable deformations without failure when the load transmitted between support frame 108 and rotatable drum rotor 102 exceeds a predetermined load threshold. Such deformation may allow for a reduced support stiffness to be provided between the support frame 108 and the bearing assembly 106 during high load events, thereby allowing for increased loads to be absorbed by the system 100 or providing damping. In certain embodiments, for example, the shape memory alloys described herein can be designed to be strained above the superelastic limit, but less than the plastic limit of the material in order to achieve the desired damping (geometry or pre-strain or both to achieve this). Further, the shape memory alloys described herein provide large hysteresis when operated under cyclic loads above the superelastic limit and within the plastic limit. This energy dissipation capability is the ability to provide damping to the material. Further, it should be appreciated that the design and/or geometry and/or materials of the damper 117 described herein may be optimized based on the particular rotor mode being mitigated. In certain embodiments, the damper(s) 117 may also be formed from a superelastic metal-based shape memory alloy. For example, suitable superelastic metal-based shape memory alloys may include, but are not limited to, nickel-titanium (NiTi) alloys, NiTi-based alloys (e.g., nickel-titanium-hafnium (NiTiHf) alloys, nickel-titanium-vanadium (NiTiVd) alloys, nickel-titanium-palladium (NiTiPd) alloys, nickel-titanium-copper (NiTiCu), nickel-titanium-niobium (NiTiNb) alloys), nickel-aluminum-copper (Ni-Al-Cu) alloys, and other non-nickel-based alloys such as titanium-niobium (Ti-Nb) alloys, copper-zinc-aluminum (CuZnAl) alloys, and copper-aluminum-beryllium (CuAlBe) alloys.

Referring now to fig. 8-12, various views of the bearing assembly 106 of the present disclosure are provided, particularly illustrating different configurations of the damping assembly 114 described herein that provide large hysteresis/damping under certain load conditions. For example, as generally shown in fig. 8-12, in one embodiment, the damper assembly 114 may include a plurality of circumferentially spaced dampers 117, e.g., circumferentially spaced around an outer race of the bearing assembly 106. More specifically, as shown in fig. 8, in one embodiment, damper(s) 117 of damper assembly 114 may include one or more ring members 120, with ring members 120 connected via one or more radially extending struts 122 (also shown in fig. 6 and 7). In such embodiments, the radial strut 122 is configured to provide sufficient stiffness to the damping structure when the damping structure experiences superelastic limits. The annular member(s) 120 are also configured to deflect, providing additional damping and hoop strength to prevent buckling. In such embodiments, the ring member(s) 120 and/or the radial struts 122 may be constructed of a shape memory alloy as described herein.

Referring now to FIG. 9, in another embodiment, each circumferentially spaced damper 117 of the damper assembly 114 may be constructed from one or more corrugated plates 124. For example, as shown, each damper 117 may be constructed from a stack of corrugated plates 124, with each plate 124 constructed from a shape memory alloy as described herein.

In yet another embodiment, as shown in FIG. 10, each circumferentially spaced damper 117 may define a box-like structure 126. Further, each damper 117 may be constructed of a shape memory alloy as described herein. In such embodiments, each box-like structure 126 may further define a stop feature 128, the stop feature 128 designed to limit deflection of the damping assembly 114.

In further embodiments, as shown in fig. 11 and 12, damping assembly 114 may comprise one or more sleeve dampers 117 secured to the inner and/or outer surfaces of rotatable drum rotor 102. Thus, in such embodiments, using such sleeve dampers to control the response of the radial vibration modes of the rotatable drum rotor 102 may be more weight efficient than, for example, adding stiffeners. More specifically, as shown, FIG. 11 corresponds to a low pressure turbine having a plurality of sleeve dampers 117 on the rotatable drum rotor 102, however, such dampers may be used in any module of a gas turbine engine. For example, fig. 12 corresponds to a compressor module having a plurality of sleeve dampers 117 on the rotatable drum rotor 102.

Further, as shown, the damping assembly 114 may comprise a plurality of sleeve dampers 117 arranged in series on the inner and/or outer surface of the rotatable drum rotor 102, for example, to provide external damping due to friction when drum radial vibration modes are excited. In other words, in such embodiments, sleeve damper(s) 117 may be mounted directly on rotatable drum rotor 102 (rather than to any other static support structure), as shown. Further, in such embodiments, the sleeve damper(s) 117 may be rotational, as shown.

Such a sleeve damper 117 may be constructed of any suitable material, such as, for example, a shape memory alloy or a metallic material as described herein. As such, the sleeve damper 117 is configured to provide damping of any radial vibration mode of the rotatable drum rotor 102. For shape memory alloys, sleeve dampers provide hysteretic damping when used during radial vibration modes of the rotatable drum rotor 102. Shape memory alloy based sleeve dampers can also be prestrained to provide high damping. For metallic materials, the friction between the metallic sleeve and the rotatable drum rotor 102 causes damping. Further, the sleeve damper 117 described herein is configured to be elliptical with structural components of the gas turbine engine (e.g., the rotatable drum rotor 102).

Various aspects and embodiments of the invention are defined by the following numbered clauses:

clause 1. a gas turbine engine, comprising:

a rotatable drum rotor comprising a plurality of blades secured thereto, the plurality of blades extending radially inward from the rotatable drum rotor;

a support frame mounted radially outwardly of the rotating drum rotor;

a rotor support system comprising a bearing assembly positioned between the rotatable drum rotor and the support frame, the bearing assembly comprising at least a fixed component and at least one rotatable component; and

a damper assembly secured between the support frame and the rotatable drum rotor, the damper assembly comprising at least one damper secured between the support frame and a stationary component of the bearing assembly or to a surface of the rotatable drum rotor, the at least one damper configured to provide damping to the rotatable drum rotor during operation of the gas turbine engine.

Clause 2. the gas turbine engine of clause 1, wherein the at least one damper comprises at least one of a shape memory alloy damper, a metal damper, a fluid-based damper, a spring-type damper, one or more sleeve dampers, or a combination thereof.

Clause 3. the gas turbine engine of any of the preceding clauses, wherein the at least one damper comprises one or more sleeve dampers comprising a plurality of sleeve dampers arranged in series on an outer or inner surface of the rotatable drum rotor.

Clause 4. the gas turbine engine of any of the preceding clauses, wherein the stationary component and the at least one rotatable component of the bearing assembly each include a stationary race and a plurality of roller elements.

Clause 5. the gas turbine engine of any of the preceding clauses, wherein the stationary race corresponds to an outer race of the bearing assembly.

Clause 6. the gas turbine engine of any of the preceding clauses, wherein the stationary race corresponds to an inner race of the bearing assembly.

Clause 7. the gas turbine engine of any of the preceding clauses, wherein the bearing assembly comprises a plurality of roller bearings circumferentially spaced about the rotatable rotor drum and secured to the support frame via a stationary support frame, the stationary and at least one rotatable component of the bearing assembly comprising the stationary support frame and the plurality of roller bearings, respectively.

Clause 8. the gas turbine engine of any of the preceding clauses, wherein at least one damper of the damper assembly is constructed from one or more annular members, one or more of which are connected via one or more radially extending struts.

Clause 9. the gas turbine engine of any of the preceding clauses, wherein the damper assembly includes a plurality of circumferentially spaced dampers, each damper being constructed of one or more corrugated plates having a leaf spring arrangement.

Clause 10. the gas turbine engine of any of the preceding clauses, wherein the damper assembly includes a plurality of circumferentially spaced dampers, each damper including a box-shaped structure, each box-shaped structure defining a stop feature designed to limit deflection of the damper assembly.

Clause 11. the gas turbine engine of any of the preceding clauses, wherein at least one damper of the damper assembly is prestrained.

Clause 12. the gas turbine engine of any of the preceding clauses, wherein the rotatable drum rotor is part of a compressor section, a turbine section, or a combustion section of the gas turbine engine.

Clause 13. a rotor support system for a gas turbine engine, the gas turbine engine including a rotatable drum rotor and a support frame, the rotor support system comprising:

a bearing assembly configured for positioning between the rotatable drum rotor and the support frame, the bearing assembly comprising at least a stationary part and at least one rotatable part; and

a damper assembly for securing between the support frame and the rotatable drum rotor, the damper assembly comprising at least one damper secured between the support frame and a stationary component of the bearing assembly or to a surface of the rotatable drum rotor, the at least one damper being configured to provide damping to the rotatable drum rotor during operation of the gas turbine engine.

Clause 14. the rotor support system of clause 13, wherein the at least one damper comprises at least one of a shape memory alloy damper, a metal damper, a fluid-based damper, one or more sleeve dampers, a spring-type damper, or a combination thereof.

Clause 15. the rotor support system of clauses 13-14, wherein the at least one damper comprises one or more sleeve dampers comprising a plurality of sleeve dampers arranged in series on an outer or inner surface of the rotatable drum rotor.

Clause 16. the rotor support system of clauses 13-15, wherein the stationary component and the at least one rotatable component of the bearing assembly each comprise a stationary race and a plurality of roller elements, and wherein the at least one damper of the damper assembly comprises a spring-like configuration.

Clause 17. the rotor support system of clauses 13-16, wherein the stationary race corresponds to at least one of an outer race of the bearing assembly or an inner race of the bearing assembly.

Clause 18. the rotor support system of clauses 13-17, wherein the bearing assembly comprises a plurality of roller bearings circumferentially spaced about the rotatable rotor drum and secured to the support frame via a stationary support frame, the stationary and at least one rotatable component of the bearing assembly comprising the stationary support frame and the plurality of roller bearings, respectively.

Clause 19. the rotor support system of clauses 13-18, wherein at least one damper of the damper assembly is comprised of one or more annular members, one or more of which are connected via one or more radially extending struts.

Clause 20. the rotor support system of clauses 13-19, wherein at least one damper of the damper assembly is pre-strained.

This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they include structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal languages of the claims.