US20130294917A1 - Apparatuses including a rotor group and methods of damping the apparatuses - Google Patents

Apparatuses including a rotor group and methods of damping the apparatuses Download PDF

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Publication number
US20130294917A1
US20130294917A1 US13/465,534 US201213465534A US2013294917A1 US 20130294917 A1 US20130294917 A1 US 20130294917A1 US 201213465534 A US201213465534 A US 201213465534A US 2013294917 A1 US2013294917 A1 US 2013294917A1
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United States
Prior art keywords
fluid
supply line
squeeze film
film cavity
damper
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Abandoned
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US13/465,534
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English (en)
Inventor
Mohsiul Alam
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Honeywell International Inc
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Honeywell International Inc
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Publication date
Application filed by Honeywell International Inc filed Critical Honeywell International Inc
Priority to US13/465,534 priority Critical patent/US20130294917A1/en
Assigned to HONEYWELL INTERNATIONAL INC. reassignment HONEYWELL INTERNATIONAL INC. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: ALAM, MOHSIUL
Priority to EP13163590.6A priority patent/EP2662537B1/de
Publication of US20130294917A1 publication Critical patent/US20130294917A1/en
Abandoned legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • F01D25/164—Flexible supports; Vibration damping means associated with the bearing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C27/00—Elastic or yielding bearings or bearing supports, for exclusively rotary movement
    • F16C27/04—Ball or roller bearings, e.g. with resilient rolling bodies
    • F16C27/045—Ball or roller bearings, e.g. with resilient rolling bodies with a fluid film, e.g. squeeze film damping
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/301—Pressure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/304—Spool rotational speed
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C19/00—Bearings with rolling contact, for exclusively rotary movement
    • F16C19/22—Bearings with rolling contact, for exclusively rotary movement with bearing rollers essentially of the same size in one or more circular rows, e.g. needle bearings
    • F16C19/24—Bearings with rolling contact, for exclusively rotary movement with bearing rollers essentially of the same size in one or more circular rows, e.g. needle bearings for radial load mainly
    • F16C19/26—Bearings with rolling contact, for exclusively rotary movement with bearing rollers essentially of the same size in one or more circular rows, e.g. needle bearings for radial load mainly with a single row of rollers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C2360/00—Engines or pumps
    • F16C2360/23—Gas turbine engines
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention generally relates to apparatuses including a rotor group and methods of damping the apparatuses, and more particularly relates to apparatuses and methods in which the rotor group is damped through squeeze film damping.
  • a gas turbine engine may be used to power various types of vehicles and systems.
  • a particular type of gas turbine engine that may be used to power aircraft is a turbofan gas turbine engine.
  • a turbofan gas turbine engine may include, for example, five major sections, a fan section, a compressor section, a combustor section, a turbine section, and an exhaust section.
  • Each section includes rotating components that are coupled to a rotor.
  • the rotating components may be coupled together either by a tie shaft or bolted flange joints to form a rotor group.
  • Two or more bearing assemblies may be employed to support the rotor group.
  • the bearing assemblies may be surrounded by a support housing, which may be connected to an engine case.
  • vibration may occur when the rotor group rotates.
  • the vibration is caused by a rotating mass imbalance, or may occur when a radial deflection of the rotor results in tangential force normal to the deflection.
  • this tangential force excites a fundamental mode of the rotor and creates a non-synchronous vibration (NSV).
  • NSV non-synchronous vibration
  • the magnitude of the tangential force increases with the deflection, resulting in high bearing loads that become unstable and cause damage to the gas turbine engine.
  • a damping system is typically required in the engine to reduce vibration, especially around a critical speed of the rotor group, thereby minimizing bearing loads and safeguarding against potential damage to the bearing assemblies and supports that can be caused by the unstable vibration.
  • a squeeze film damper operates by supplying fluid (usually oil) into a squeeze film cavity formed via a clearance between the support housing and the bearing assemblies.
  • the fluid in the squeeze film cavity is under pressure and damps vibration of the rotor through viscous resistance thereby exerting a damping force on the bearing assembly.
  • Squeeze film dampers are particularly effective for damping synchronous vibration of the rotor group that occurs at the critical speed.
  • squeeze film dampers are relatively useful in reducing synchronous rotor vibration, they may suffer drawbacks.
  • squeeze film dampers are generally effective for damping rotor vibration at a critical speed of the rotor group, where vibration is greatest and where damping is most desired.
  • the critical speed of the rotor group in gas turbine engines is generally relatively low within a range of rotational operating speeds of the gas turbine engines, and the critical speed of the rotor group is often traversed during normal operation of the gas turbine engines.
  • the fluid in the squeeze film damper generally continues to be under pressure once the critical speed is traversed. However, once the critical speed is traversed, synchronous vibration is less than at critical speeds and the need for damping the synchronous vibrations is greatly reduced.
  • damping may even be undesirable once the critical speeds are traversed because the damping force exerted by the pressurized fluid in the squeeze film damper combines with elastic force to create excessively high bearing loads, which leads to excessive engine vibration.
  • FIG. 1 continued damping after traversing the critical speed, while initially decreasing an amplitude of bearing load, causes an increase in bearing load and attendant system vibration at higher rotational operating speeds of the rotor group.
  • Many gas turbine engines that employ squeeze film dampers do not cut off a fluid flow to the squeeze film damper once the critical speed is traversed because cutting off the fluid flow to the squeeze film damper invites NSV, which causes the aforementioned problems.
  • apparatuses including a rotor group that can be damped to minimize bearing loads around a critical speed of the rotor group, but that also exhibits minimized bearing loads upon traversing the critical speed.
  • methods of damping vibration in such apparatuses both around the critical speed of the rotor group and once the critical speed is traversed.
  • an apparatus includes a rotor group that is rotatable within the apparatus and a bearing assembly that supports the rotor group.
  • a support structure supports the bearing assembly and is fixed in the apparatus.
  • the support structure includes a support housing, an anisotropic support that engages the bearing assembly and the support housing, and a squeeze film cavity that is defined between the anisotropic support and the support housing.
  • a damper fluid supply line is in fluid communication with the squeeze film cavity for independently providing a fluid to the squeeze film cavity.
  • a fluid interruption device is disposed in the damper fluid supply line for interrupting a fluid flow to the squeeze film cavity.
  • an apparatus in another embodiment, includes a rotor group that is rotatable within the apparatus and a bearing assembly that supports the rotor group.
  • a support structure supports the bearing assembly and is fixed in the apparatus.
  • the support structure includes a support housing, an anisotropic support that engages the bearing assembly and the support housing, and a squeeze film cavity that is defined between the anisotropic support and the support housing.
  • the anisotropic support includes at least two rings that are connected by asymmetrically-arranged beams.
  • a damper fluid supply line is in fluid communication with the squeeze film cavity for independently providing a fluid to the squeeze film cavity.
  • a fluid reservoir is in fluid communication with the damper fluid supply line for providing the fluid to the damper fluid supply line.
  • a main supply line is disposed between and in fluid communication with the fluid reservoir and the damper fluid supply line, and the damper fluid supply line is split from the main supply line.
  • a bearing fluid supply line is further split from the main supply line for independently providing the fluid to the bearing assembly.
  • a fluid interruption device is disposed in the damper fluid supply line and controlled by an engine control system for interrupting a fluid flow to the squeeze film cavity. The fluid flow to the bearing assembly is uninterrupted when the fluid flow to the squeeze film cavity is interrupted by the fluid interruption device.
  • a method of damping vibration in an apparatus includes providing the apparatus including a rotor group that is rotatable within the apparatus and a bearing assembly that supports the rotor group.
  • a support structure supports the bearing assembly and is fixed in the apparatus.
  • the support structure includes a support housing, an anisotropic support that engages the bearing assembly and the support housing, and a squeeze film cavity that is defined between the anisotropic support and the support housing.
  • a damper fluid supply line is in fluid communication with the squeeze film cavity for independently providing a fluid to the squeeze film cavity.
  • a fluid interruption device is disposed in the damper fluid supply line for interrupting a fluid flow to the squeeze film cavity.
  • the method further includes supplying fluid under pressure to the squeeze film cavity through the damper fluid supply line. Upon surpassing a predetermined value of a variable correlated to rotational speed of the rotor group, the fluid flow to the squeeze film cavity is interrupted with the fluid interruption device.
  • FIG. 1 is a graph showing bearing loads, in pounds-force, as a function of rotational speed of a rotor group within an apparatus as shown in FIG. 2 when a squeeze film damper is employed with fluid in the squeeze film damper pressurized at all rotational speeds;
  • FIG. 2 is a partial cross-sectional side view of an apparatus including a rotor group, a bearing assembly, and a support structure including an anisotropic support in accordance with an exemplary embodiment
  • FIG. 3 is a perspective view of the anisotropic support of FIG. 2 ;
  • FIG. 4 is a graph showing bearing loads, in pounds-force, as a function of rotational speed of the rotor group within the apparatus as shown in FIG. 2 when a squeeze film damper is employed with fluid in the squeeze film damper interrupted once a rigid body critical speed of the rotor group is interrupted.
  • the apparatuses may be further defined as gas turbine engines and include a rotor group, a bearing assembly, and a support structure including a support housing, an anisotropic support, and a squeeze film cavity defined between the anisotropic support and the support housing.
  • the squeeze film cavity When filled with pressurized fluid, the squeeze film cavity functions as a squeeze film damper.
  • the apparatuses and methods employ damping from both the squeeze film damper and the anisotropic support in a way that minimizes bearing loads both around a rigid body critical speed of the rotor group and once the rigid body critical speed is traversed to thereby minimize vibration of the apparatuses in a range of rotational operating speeds of the rotor group.
  • fluid is supplied under pressure to the squeeze film cavity, and a fluid flow to the squeeze film cavity is interrupted upon surpassing a predetermined value of a variable that is correlated to rotational speed of the rotor group, representing traversal of the rigid body critical speed of the rotor group or a speed at which damping with the squeeze film damper begins to create increasing bearing load.
  • a fluid flow to the squeeze film cavity is interrupted, the squeeze film damper effectively ceases damping, thereby reducing the vibration of the rotor group.
  • NSV non-synchronous vibration
  • the anisotropic support is present and provides cross-couple stiffness to protect the rotor group against tangential excitation that creates the NSV. In this manner, high bearing loads attributable to the squeeze film damper at rotational speeds above the rigid body critical speed are minimized, thereby minimizing vibration of the apparatus below vibration that would otherwise be experienced with continued damping by the squeeze film damper.
  • the apparatus 10 is a gas turbine engine, such as an engine of an aircraft.
  • gas turbine engine such as an engine of an aircraft.
  • the apparatuses described herein are not limited to gas turbine engines only and can include any apparatus 10 having a rotor that would benefit from damping of vibration at critical speeds and after traversing the critical speeds.
  • the apparatus 10 includes a rotor group 12 that is rotatable within the apparatus 10 .
  • the rotor group 12 refers to a rotor 14 and any rotatable features within the apparatus 10 that are fixed relative to the rotor 14 .
  • a bearing assembly 16 supports the rotor group 12 within the apparatus 10 .
  • the bearing assembly 16 engages the rotor 14 to support the rotor group 12 .
  • FIG. 2 Although only a single bearing assembly 16 is shown in FIG. 2 for simplicity of illustration, it is to be appreciated that a plurality of bearing assemblies 16 may be included to support the rotor group 12 .
  • the bearing assembly 16 includes bearing elements 18 and an inner race 20 that is fixed on the rotor 14 and that provides a contact surface 22 for the bearing elements 18 .
  • the inner race 20 is also configured to confine the bearing elements 18 within the inner race 20 .
  • a support structure 24 supports the bearing assembly 16 and is fixed in the apparatus 10 , i.e., the support structure 24 does not rotate during operation of the apparatus 10 .
  • each bearing assembly 16 may have its own corresponding support structure 24 .
  • the support structure 24 promotes axial rotation of the rotor 14 , and by extension the rotor group 12 , about an ideal axis during rotation of the rotor group 12 by supporting the rotor 14 through the bearing assembly 16 .
  • the support structure 24 includes a support housing 26 .
  • the support housing 26 is fixed to another non-rotating structure 30 of the apparatus 10 and is fixed to the non-rotating structure 30 of the apparatus 10 , for example, through a flange and bolt connection.
  • the support structure 24 further includes an anisotropic support 28 that engages the bearing assembly 16 and the support housing 26 .
  • the anisotropic support 28 engages the bearing elements 18 of the bearing assembly 16 and provides an outer race 32 that, in cooperation with the inner race 20 , holds the bearing elements 18 in place.
  • the anisotropic support 28 provides support anisotropy, or directionally-dependent, stiffness to the rotor 14 through directly engaging the bearing elements 18 , and the anisotropic support 28 is effective for neutralizing non-synchronous vibration of the rotor group 12 during rotation.
  • FIG. 2 and as best shown in FIG.
  • the anisotropic support 28 includes at least two rings 34 , 36 that are connected by asymmetrically-arranged beams 38 , with the asymmetric arrangement of the beams 38 providing anisotropy to the anisotropic support 28 .
  • one of the at least two rings 36 provides the outer race 32 on an inner surface thereof, and another of the at least two rings 34 provides an inner-circumferential attachment flange 40 for facilitating attachment of the anisotropic support 28 to the apparatus 10 .
  • the anisotropic support 28 can be bolted to the support housing 26 through the inner-circumferential attachment flange 40 .
  • a squeeze film cavity 42 is defined between the anisotropic support 28 and the support housing 26 of the support structure 24 .
  • the squeeze film cavity 42 is defined between one of the at least two rings 36 of the anisotropic support 28 , on an outer surface 44 thereof directly opposite the outer race 32 , and the support housing 26 .
  • the squeeze film cavity 42 extends circumferentially and continuously about the anisotropic support 28 ; however, it is to be appreciated that configurations are possible in which additional features (not shown) are designed into the squeeze film cavity 42 that interrupt continuous circumferential extension of the squeeze film cavity 42 .
  • the anisotropic support 28 includes two grooves 46 that receive piston rings 48 , with the piston rings 48 further defining and sealing the squeeze film cavity 42 .
  • a damper fluid supply line 50 is in fluid communication with the squeeze film cavity 42 for independently providing a fluid to the squeeze film cavity 42 .
  • the damper fluid supply line 50 provides fluid only to the squeeze film cavity 42 or, when the plurality of bearing assemblies 16 and corresponding support structures 24 are included, to each squeeze film cavity 42 .
  • the damper fluid supply line 50 is incorporated into the support housing 26 with a fluid inlet 52 to the squeeze film cavity 42 defined in the support housing 26 adjacent to the squeeze film cavity 42 .
  • a portion of the damper fluid supply line 50 may be disposed outside of the support housing 26 .
  • fluid is supplied under pressure to the squeeze film cavity 42 through the damper fluid supply line 50 .
  • the squeeze film cavity 42 when filled with fluid under pressure, functions as a squeeze film damper and is effective for damping vibration of the rotor group 12 during rotation.
  • the squeeze film damper is effective for damping synchronous vibration of the rotor group 12 , especially at and around a critical speed of the rotor group 12 where synchronous vibration generally peaks.
  • Suitable fluid for filling the squeeze film cavity 42 is not particularly limited and can be any fluid that is capable of flow under pressure, such as engine oil.
  • a fluid reservoir 54 is in fluid communication with the damper fluid supply line 50 for providing the fluid to the damper fluid supply line 50 .
  • the fluid reservoir 54 may be a primary oil supply that collects, filters, and provides oil to various portions of the apparatus 10 , in addition to providing oil to the damper fluid supply line 50 .
  • a main supply line 56 is disposed between and in fluid communication with the fluid reservoir 54 and the damper fluid supply line 50 , and the damper fluid supply line 50 is split from the main supply line 56 .
  • the main supply line 56 supplies fluid to portions of the apparatus 10 beyond the damper fluid supply line 50 , and can be directly attached to the fluid reservoir 54 .
  • a bearing fluid supply line 58 is further split from the main supply line 56 for independently providing the fluid to the bearing assembly 16 .
  • the main supply line 56 may be mounted to the support housing 26 , such as through a flange and bolt connection, with the main supply line 56 including a fluid distributor 60 inserted through the support housing 26 and into a space 62 between the anisotropic support 28 and the rotor 14 .
  • the damper fluid supply line 50 is split from the main supply line 56 in the fluid distributor 60 , with the fluid distributor 60 and the support housing 26 having complementary portions of the damper fluid supply line 50 that align when the fluid distributor 60 is mounted to the support housing 26 .
  • the bearing fluid supply line 58 extends to a distal end 64 of the fluid distributor 60 that is inserted through the support housing 26 to provide fluid into the space 62 between the anisotropic support 28 and the rotor 14 thereby supplying fluid to the bearing elements 18 .
  • the fluid is supplied under pressure to the squeeze film cavity 42 by pressurizing the fluid in the main supply line 56 .
  • a fluid pump 66 is disposed in fluid communication with the main supply line 56 for pressurizing the fluid in the main supply line 56 .
  • the fluid pump 66 thus pressurizes fluid in the main supply line 56 for supplying fluid under pressure to both the squeeze film cavity 42 through the damper fluid supply line 50 and the bearing elements 18 through the bearing fluid supply line 58 .
  • the fluid pump 66 is operated to pressurize the fluid in the main supply line 56 in a range of from about 130 to about 850 KPa.
  • a fluid interruption device 68 is disposed in the damper fluid supply line 50 , which enables a fluid flow to the squeeze film cavity 42 to be interrupted without interrupting a fluid flow to the bearing elements 18 or any other portion of the apparatus 10 .
  • the fluid interruption device 68 is incorporated in the support housing 26 and is disposed in the damper fluid supply line 50 within the support housing 26 , which provides design robustness and enables connections between the damper fluid supply line 50 and the fluid interruption device 68 to be reinforced.
  • the fluid interruption device 68 may be disposed outside of the support housing 26 .
  • Suitable fluid interruption devices 68 include any device that is disposed in the damper fluid supply line 50 and that interrupts or disrupts the fluid flow to the squeeze film cavity 42 .
  • the fluid interruption device 68 may halt the fluid flow to the squeeze film cavity 42 to effectuate interruption of the fluid flow to the squeeze film cavity 42 .
  • the fluid interruption device 68 may release pressure in the damper fluid supply line 50 to effectuate interruption of the fluid flow to the squeeze film damper.
  • the fluid interruption device 68 may reroute the fluid from the damper fluid supply line 50 to other locations within the apparatus 10 to relieve pressure in the damper fluid supply line 50 .
  • the fluid interruption device 68 includes a pressure regulating valve 68 that functions to interrupt the fluid flow to the squeeze film cavity 42 through the influence of pressure on an internal piston (not shown).
  • the fluid interruption device 68 may include a solenoid valve 68 .
  • the fluid interruption device 68 is controlled by an engine control system 70 , with appropriate sensors (not shown) employed to measure variables based upon which a signal can be generated for the fluid interruption device 68 to interrupt the fluid flow to the squeeze film cavity 42 .
  • the fluid interruption device 68 may itself be designed to automatically interrupt the fluid flow to the squeeze film cavity 42 under certain conditions without the need for controlling by the engine control system 70 .
  • the fluid flow to the squeeze film cavity 42 is interrupted with the fluid interruption device 68 upon surpassing a predetermined value of a variable that is correlated to rotational speed of the rotor group 12 .
  • a fluid flow to the bearing assembly 16 is uninterrupted when the fluid flow to the squeeze film cavity 42 is interrupted, thereby enabling fluid flow to continue to the bearing elements 18 .
  • the variable is further defined as fluid pressure in the damper fluid supply line 50
  • the fluid flow to the squeeze film cavity 42 is interrupted by the fluid interruption device 68 upon surpassing a predetermined value of fluid pressure in the damper fluid supply line 50 .
  • the variable is further defined as the actual rotational speed of the rotor group 12
  • the fluid flow to the squeeze film cavity 42 is interrupted by the fluid interruption device 68 upon surpassing a predetermined value of rotational speed of the rotor group 12 .
  • the predetermined value of the variable may correspond to a value of the variable at least at a critical speed of the rotor group 12 .
  • the fluid flow to the squeeze film cavity 42 is interrupted upon surpassing the predetermined value of the variable that is at least at the critical speed of the rotor group 12 .
  • Fluid pressure in the damper fluid supply line 50 can be directly correlated to rotational speed of the rotor group 12 for purposes of identifying rigid body critical speeds at which the fluid flow to the squeeze film cavity 42 is to be interrupted.
  • the predetermined value of the variable corresponds to a value of the variable in a range of from a value of the variable at the critical speed of the rotor group 12 to a value of the variable at about 20 percent above the rigid body critical speed of the rotor group 12 .
  • the simulated apparatus 10 is a gas turbine engine having a rigid body critical speed at about 16,000 rpm.
  • the fluid flow to the squeeze film cavity 42 is halted, thereby resulting in significantly less bearing loads through the remaining range of operating rotational speeds of the rotor group 12 .
  • bearing loads are decreased by at least 30% upon interrupting the fluid flow to the squeeze film cavity 42 , as compared to a simulation in which the fluid flow to the squeeze film cavity 42 is uninterrupted (as represented in FIG. 1 ).

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Support Of The Bearing (AREA)
US13/465,534 2012-05-07 2012-05-07 Apparatuses including a rotor group and methods of damping the apparatuses Abandoned US20130294917A1 (en)

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US13/465,534 US20130294917A1 (en) 2012-05-07 2012-05-07 Apparatuses including a rotor group and methods of damping the apparatuses
EP13163590.6A EP2662537B1 (de) 2012-05-07 2013-04-12 Vorrichtung mit einer Rotorgruppe und Verfahren zum Dämpfen von Schwingungen in einer solchen Vorrichtung

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US13/465,534 US20130294917A1 (en) 2012-05-07 2012-05-07 Apparatuses including a rotor group and methods of damping the apparatuses

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US10641327B2 (en) 2018-07-13 2020-05-05 United Technologies Corporation Oil supply system for fluid film damper
US10697323B2 (en) 2016-07-21 2020-06-30 Raytheon Technologies Corporation Engine bearing damper with interrupted oil film
US10935080B2 (en) * 2019-03-14 2021-03-02 Raytheon Technologies Corporation Extended housing sleeve with stiffening ring feature
US20210180651A1 (en) * 2019-12-11 2021-06-17 United Technologies Corporation Curved beam centering spring for a thrust bearing

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US10465828B2 (en) 2017-02-06 2019-11-05 United Technologies Corporation Tube fitting
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US9695870B2 (en) * 2012-09-25 2017-07-04 United Technologies Corporation Turbomachine bearing support structure
US10697323B2 (en) 2016-07-21 2020-06-30 Raytheon Technologies Corporation Engine bearing damper with interrupted oil film
US10641327B2 (en) 2018-07-13 2020-05-05 United Technologies Corporation Oil supply system for fluid film damper
US10935080B2 (en) * 2019-03-14 2021-03-02 Raytheon Technologies Corporation Extended housing sleeve with stiffening ring feature
US20210180651A1 (en) * 2019-12-11 2021-06-17 United Technologies Corporation Curved beam centering spring for a thrust bearing
US11118629B2 (en) * 2019-12-11 2021-09-14 Raytheon Technologies Corporation Curved beam centering spring for a thrust bearing

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EP2662537B1 (de) 2018-10-24
EP2662537A3 (de) 2017-10-18

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