GB2033024A - Bearing assembly with resilient support means - Google Patents

Bearing assembly with resilient support means Download PDF

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Publication number
GB2033024A
GB2033024A GB7929234A GB7929234A GB2033024A GB 2033024 A GB2033024 A GB 2033024A GB 7929234 A GB7929234 A GB 7929234A GB 7929234 A GB7929234 A GB 7929234A GB 2033024 A GB2033024 A GB 2033024A
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GB
United Kingdom
Prior art keywords
pins
bearing assembly
shaft
recited
annular
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
GB7929234A
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of GB2033024A publication Critical patent/GB2033024A/en
Withdrawn legal-status Critical Current

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Classifications

    • 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
    • F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
    • F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
    • F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
    • F16F15/023—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using fluid means
    • F16F15/0237—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using fluid means involving squeeze-film damping
    • 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
    • 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

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Acoustics & Sound (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Support Of The Bearing (AREA)

Abstract

An improved bearing assembly is provided for supporting a rotating shaft. The improvement is comprised of utilizing a resilient support consisting of a plurality of circumferentially spaced, axially aligned pins 26. A multiple squeeze film damper apparatus 64 provides a large damping force to suppress large vibrations and excessive radial shaft deflections in the event of operation with an abnormally high unbalanced shaft. The resilient support provides a soft spring system as a means for establishing and maintaining the critical rotor speed at a low speed condition, for centering the shaft during normal operation, and for allowing radial deflection during operation with an unbalanced shaft. <IMAGE>

Description

SPECIFICATION Bearing assembly with resilient support means This invention relates to bearing assemblies for supporting rotating shafts and, more particularly, to a resilient support means for such bearing assemblies.
Rotating shafts, and particuiarly rotating shafts in gas turbine engines, can become abnormally unbalanced while operating. For example, a high pressure turbine rotor in a gas turbine engine will become abnormally unbalanced in the event that a turbine blade is lost. The combination of abnormally high unbalance and a critical speed within the operating range of the rotating shaft could result in potentially damaging vibration forces as well as excessive shaft deflections which may result in damaging rubs.
Prior art bearing assemblies control the shaft vibration characteristics by means of critical speed adjustments and damping. The critical speed is usually controlled by adjusting the flexibility of the various members which comprise the engine system, e.g. the rotating shaft itself, the bearing, support structure, etc.
The vibration response at the critical speeds is often suppressed by means of a single squeeze film damper which usually comprises a quantity of oil contained within a small radial gap.
Although the prior art bearing assemblies are generally adequate for achieving smoothness in a moderately unbalanced system during normal operation, they are generally inadequate for an abnormally high unbalanced system. For example, when a prior art bearing assembly is employed with a high pressure turbine rotor in a gas turbine engine, and in the event a turbine blade is lost, the small gap associated with a single squeeze film damper provides a nonlinear hard spring response which tends to raise the critical frequency and negate the advantages derived from the damping.
In addition, when such abnormal conditions exist, the prior art bearing support systems have tended to fail. When such failures have occurred, they have been accompanied by the loss of support system components which have tended to cause extensive secondary damage to the engine.
It is, therefore, an object of the present invention to provide a bearing assembly for supporting a rotating shaft which maintains a soft resilient support system despite abnormal shaft deflections and unbalance forces.
It is a further object of the present invention to provide such a bearing assembly in which failed components are retained in place.
It is yet another object of the present invention to provide such a bearing assembly which maintains the rotating shaft in an assentially centered position.
Briefly stated, these objects as well as additional objects and advantages which will become apparent from the following specification and the appended drawings and claims are accomplished by the present invention which provides a bearing assembly for supporting a rotating shaft. The bearing assembly is comprised of a supporting structure, a bearing including an outer race surrounding the shaft, and a support means surrounding the shaft for resiliently connecting the outer race to the supporting structure. The resilient support means is comprised of an annular support housing which is attached to the supporting structure, an annular bearing housing which is attached to the outer race, and a plurality of circumferentially spaced apart and generally axial aligned pins for connecting the bearing housing to the support housing.A damper apparatus may also be employed with the resilient support means.
Figure 1 is a fragmentary cross-sectional view of a portion of a gas turbine engine including one embodiment of the improved bearing assembly of the present invention.
Figure 2 is a fragmentary cross-sectional view of a different portion of the engine of Fig. 1.
Figure 3 is an enlarged perspective view of a portion of Fig. 1.
Referring to Fig. 1, there is depicted a fragmentary cross section of a portion of a gas turbine engine shown generally as 1 0. The engine. 10 may be of any type, for example a turbofan, a turbojet, a turboshaft, etc., and a detailed description of its major component parts and operation is not deemed to be essential for an understanding of the present invention.
A shaft 12, for example of a turbine rotor, is journaled for rotation within a bearing 14.
The bearing 1 4 may be of any type, for example a roller bearing, and includes an outer race 1 6. The outer race 16 is resiliently connected by a resilient support means, shown generally as 20, to a generally stiff supporting structure 18, for example a bearing sump casing.
The resilient support means 20 is designed as a soft spring system in order to establish and maintain the critical speed of the rotor1 2 at a low percentage of engine speed. The resilient support means 20 also keeps the shaft 1 2 centered during normal operation.
For reasons which will hereinafter become apparent, the resilient nature of the support means 20 allows radial motion of the shaft 1 2 to occur.
The support means 20 of the present embodiment is a so-called "squirrel cage" comprised of an annular cage support housing 22, an annular bearing housing 24 and a plurality of circumferentially spaced apart and generally axially aligned contoured pins, one of which is shown as 26.
The bearing housing 24 is attached to the outer race 1 6 by means of an annular bearing retainer nut 28. The bearing retainer nut 28 is tightened against the outer race 1 6 utilizing threads 30 in the radial interior of the annular bearing housing 24. The initial tightening of the bearing retainer nut 28 puts pressure upon the left side (as viewed in Fig. 1) of the outer race 16, thereby forcing the outer race 1 6 to the right and into abutting engagement with an annular shoulder 32 in the bearing housing 24. Continued tightening of the bearing retainer nut 28 locks the outer race 1 6 in place with respect to the bearing housing 24 as is shown in Fig. 1.
The cage support housing 22 is attached to the supporting structure or sump casing 1 8 by a plurality of bolts and locknuts, a pair of which is shown as 34 and 36 respectively.
The pins connect the cage support housing 22 to the bearing housing 24 (in a manner which will hereinafter be described) in order to provide the desired soft spring support for the bearing 14. In order to avoid unnecessary repetition, the manner of connecting only one pin to the two housings will be described. It is to be understood, however, that all of the pins are connected in the same manner.
The downstream end 38 of a pin 26 is secured by means of an interference press fit within an annular opening 40 extending axially through the cage support housing 22.
(Downstream as used herein means the direction to the right as shown on Fig. 1). The tip of the downstream end 38 of the pin 26 includes a button 42 having an axial crosssectional area which is larger than that of the annular opening 40 and which is disposed within an enlarged diameter opening 44 in the downstream side of the cage support housing 22. The button 42 acts as a positive mechanical stop by abutting against either the upstream side of the sump casing 1 8 or the downstream side of the cage support housing 22, to limit axial motion of the pin 26 in either direction. It also acts as a means to prevent migration or loss of the pin in the event of pin failure.
The upstream end 46 of the pin 26 is similarly secured by means of an interference press fit within an annular opening 48 extending axially through the bearing housing 24.
The upstream end 46 of the pin 26 also includes an extension portion 50 of a diameter smaller than that of the rest of the pin 26.
The pin extension portion 50 extends axially through an annular opening 52 in the bearing housing 24 and through an opening in an anti-rotational lockplate 54. A locknut 56 placed on the threaded end 58 of the pin extension portion 50 is tightened against the lockplate 54 and the bearing housing 24, thereby drawing the pin 26 to the left until an annular shoulder 60 on the pin 26 engages an annular seat 62 within the bearing housing 24 (as is shown in Fig. 1). The locknut 56, in addition to serving as a means for properly positioning the pin 26 within the bearing housing 24 and to retain the lockplate 54 in position, acts as a means to prevent the migration or loss of the pin in the event of pin failure.
The use of individual pins 26 to join the bearing housing 24 and the cage support housing 22 in the above-described manner results in lower pin stress for a given stiffness and rotor deflection. The pins are contoured to provide for constant stresses along the axial length of each pin when radial deflections are imposed upon the bearing housing 24. The lower pin stresses result in an increased capacity for accommodating larger rotor deflections (and therefore higher unbalances) without fatigue failure of the pins 26.
A multiple squeeze film damper apparatus, shown generally as 64, is disposed between the radial exterior of the resilient support means 20 and the radial interior of an annular structural member 66. The structural member 66 is attached to and forms a part of the sump casing 1 8. The damper apparatus 64 is comprised generally of a first annular member of damper housing 68 which, in conjunction with a second annular member or ring member 70 and a portion of the radial exterior of the bearing housing 24, forms an annular damper cavity shown generally as 72.The damper housing 68 is generally comprised of a cylinder 67 having a first annular flange member 69 extending radially inwardly therefrom.The radial exterior of the cylinder 67 generally engages the radial interior of the structural member 66 and is retained in place radially by means of an interference press fit.
A second annular flange member 74 extends radially inwardly from the downstream end 76 of the cylinder 67 and is bolted to the sump casing 1 8 in order to prevent axial movement of the damper housing 68 with respect to the structural member 66.
The annular ring member 70 includes a radially outwardly extending annular flange portion 78 which abuts an annular shoulder 80 on the damper housing 68. An annular spanner nut 82 engages a set of threads 84 within the damper housing 68 and is tightened thereon in order to clamp the ring member 70 in the position as shown in Fig. 1. The spanner nut 82 is specifically designed with a flat portion 86 which engages the radial exterior of the ring member 70 in order to provide a uniform clamping force to keep the ring member 70 from shifting its position under an axial pressure force.
A plurality of nested annular sleeves (shown in the present embodiment as four such sleeves) 88, 90, 92 and 94 are disposed within the annular damper cavity 72. The sleeves are of a precise axial length so that when assembled within the damper cavity a minimal axial clearance exists between the sleeves and the radial walls of the damper cavity 72. In addition, each sleeve includes one or more very shallow projections 1 24 as is shown greatly enlarged in Fig. 3 (only one sleeve being depicted for clarity), creating axial end gaps in order to equalize the pressure on the downstream and upstream ends of the sleeve.
The radially innermost sleeve 88 is associated with the radial exterior of the bearing housing 24, forming an annular space 96 therebetween in a manner which will hereinafter become apparent. The diameters of the annular sleeves 88, 90, 92 and 94 vary from the radially innermost to the radially outermost so as to form annular spaces, 98, 100 and 102 therebetween. For example, the diameter of the radial exterior of sleeve 88 is slightly smaller than the diameter of the radial interior of sleeve 90 thereby forming annular space 98 therebetween. The radially outermost sleeve 94 is associated with the radial interior of the damper housing 68 thereby forming an annular space 104 therebetween.
As is best seen in Fig. 2, a source of viscous fluid under pressure (not shown) is connected (by means which will hereinafter be described) to the damper apparatus 64 in order to maintain a constant supply of pressurized fluid within the annular spaces 96, 98, 100, 102 and 104. The pressurized fluid is supplied via a first fluid conduit 106 disposed within the sump casing 1 8 to an annular fluid supply groove 108 formed between the radial exterior of the damper housing 68 and the sump casing 1 8. The use of an annular supply groove 108 eliminates the need for having a multiplicity of external feed lines. A pair of piston ring seals 110, one of which is located on either side of the supply groove 108, is provided in order to retard fluid leakage from the supply groove 108.
The pressurized fluid within the supply groove 108 flows into the damper cavity 72 via a second conduit 11 2 within the sump housing 68. The axial portion 114 of the second conduit 11 2 includes a means, for example check valve 11 6, for maintaining the pressurized fluid within the damper cavity 72 and to prevent fluid back flow out of the damper 64 during unbalance conditions. Although the foregoing description relates to a single conduit 11 2 for supplying the pressurized fluid from the supply groove 108 to the damper cavity 72, it should be understood that it may be desirable to have more than one such conduit circumferentially spaced apart in order to maintain a proper level of fluid within the damper cavity 72.
Referring now to Figs. 1, 2 and 3, the pressurized fluid enters the damper cavity 72 from the axial portion 114 of conduit 11 2 and forms a hydrodynamic film within the annular spaces 96, 98, 100, 102 and 104.
The movement of the fluid into the annular spaces is facilitated by a plurality of circumferentially spaced apertures or holes 11 8 within the annular sleeves 88, 90, 92 and 94. In the embodiment of the drawing, holes 11 8 in sleeve 94 are alternatingly disposed within two axially spaced apart circumferential rows.
The holes 118 in sleeve 90 are similarly placed. The holes 11 8 in sleeves 92 and 88 are located along a single circumferential row.
The holes are spaced in the described manner to provide progressive fluid communication between the annular spaces 96, 98, 100, 102, 104 in order to maintain an even distribution of the pressurized fluid within the annular spaces 96, 98, 100, 102 or 104.
Referring again to Figs. 1 and 2, a pair of annular piston rings 1 20 or other suitable sealing elements, engage the radial interior of the damper housing 68 with an interference press fit. The piston rings 1 20 are fitted into a pair of annular grooves 1 22 within the radial exterior of the bearing housing 24, in order to retard the leakage of pressurized fluid from the damper cavity 72.
During normal operation, the resilient support means 20 serves as a soft mechanical spring system to keep the shaft 1 2 centered, as well as to establish the critical speed of the shaft 1 2 at a desired level usually below or low in the operating range of the engine. In the event that the shaft 1 2 undergoes a whirl type motion either from abnormally high unbalance forces or from operation at the critical speed, the pins 26 prevent the bearing housing 24 from rotating with the shaft 1 2. Thus, the bearing housing 24 experiences an orbiting type motion which, in turn, imposes an orbiting type motion upon the multiple squeeze film damper apparatus 64.The corresponding displacement squeezes the fluid film in each of the annular spaces 96, 98, 100, 102 and 104, thereby developing hydrodynamic forces therein.
The hydrodynamic forces developed are a function of fluid flow phenomena. It is the nature of the force that the smaller the annular space, the larger the force becomes for a given amount of displacement. Thus, by maintaining small individual annular spaces 96, 98, 100, 102 and 104, rather than one large clearance, the forces may be increased. It is also a characteristic that the forces may be increased by keeping minimal axial clearance between the sleeves 88, 90, 92 and 94 and the walls of the damper cavity 72, thereby constraining the fluid to flow primarily circumferentially, in compliance with the whirl type motion rather than as a free axial expulsion of fluid. The force may be separated into two components, the spring force being the component which is in the direction of the displacement and the damping force being the component which is normal to the direction of the displacement and opposes the whirl motion. It is the increase of this damping force which is desirable to suppress vibration. By increasing the damping force component the spring force component is also increased; however, the multiplicity of annular spaces 96, 98, 100, 102 and 104 combine to provide a larger total radial clearance, resulting in a generally lower overall spring constant combines with the previously described soft mechanical spring system to provide an overall soft support for the shaft 1 2.

Claims (9)

1. An improved bearing assembly for supporting a rotating shaft, said assembly comprising: a supporting structure; and a bearing surrounding said shaft and including an outer race; wherein the improvement comprises resilient support means surrounding said shaft for resiliently connecting said outer race to said supporting structure, said resilient support means including: an annular support housing attached to said supporting structure; an annular bearing housing attached to said outer race; and a plurality of circumferentially spaced apart and axially aligned pins for connecting said bearing housing to said support housing.
2. The improved bearing assembly as recited in claim 1 further comprising a damper apparatus surrounding said shaft for damping vibrations and deflections of said shaft.
3. The improved bearing assembly as recited in claim 1 wherein said pins have a first end and a second end and further including means for retaining said pins in place in the event of a failure of one or more of said pins.
4. The improved bearing assembly as recited in claim 3 further including a plurality of circumferentially apaced apart openings extending axially through said support housing wherein said pin retaining means comprises inserting the first end of each of said pins through said openings, said pins being retained therein by an interference fit.
5. The improved bearing assembly as recited in claim 4 wherein said pin retaining means further comprises a button disposed on the tip of the first end of each of said pins, said button being larger in axial cross section than said openings.
6. The improved bearing assembly as recited in claim 3 further including a plurality of circumferentially spaced apart openings extending axially through said bearing housing wherein said pin retaining means comprises inserting the second end of each of said pins through said openings, said pins being retained therein by an interference fit.
7. The improved bearing assembly as recited in claim 6 wherein said second end of each of said pins includes a threaded portion extending axially out of said openings, said pin retaining means further comprising a locknut installed upon said threaded portion of each of said pins.
8. The improved bearing assembly as recited in claim 1 wherein the pins are contoured to provide for constant stresses along their axial length.
9. A bearing assembly substantially in accordance with any embodiment (or modification thereof) of the invention claimed in Claim 1 and described and/or illustrated herein.
GB7929234A 1978-10-19 1979-08-22 Bearing assembly with resilient support means Withdrawn GB2033024A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US95287278A 1978-10-19 1978-10-19

Publications (1)

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GB2033024A true GB2033024A (en) 1980-05-14

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ID=25493308

Family Applications (1)

Application Number Title Priority Date Filing Date
GB7929234A Withdrawn GB2033024A (en) 1978-10-19 1979-08-22 Bearing assembly with resilient support means

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JP (1) JPS5572910A (en)
DE (1) DE2942000A1 (en)
FR (1) FR2439331A1 (en)
GB (1) GB2033024A (en)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2496169A1 (en) * 1980-12-11 1982-06-18 United Technologies Corp VISCOUS SHOCK ABSORBER WITH ROTOR CENTERING ELEMENT
EP0109346A2 (en) * 1982-11-15 1984-05-23 United Technologies Corporation Viscous damper with rotor centering means
EP0188666A2 (en) * 1985-01-14 1986-07-30 Rockwell International Corporation Drive shaft assembly
GB2240821A (en) * 1990-02-07 1991-08-14 Loehr & Bromkamp Gmbh Vibration damper for drive shaft
US5564903A (en) * 1993-11-23 1996-10-15 Alliedsignal Inc. In-line ram air turbine power system
US7524112B2 (en) 2004-01-12 2009-04-28 Snecma Bearing support with double stiffener
FR3009843A1 (en) * 2013-08-26 2015-02-27 Snecma SUPPORTING COLUMNS OF AN EXTERNAL ROLLING BEARING RING FOR AIRCRAFT TURBOMACHINE, AND METHOD OF MOUNTING THE SAME
WO2015054447A1 (en) * 2013-10-11 2015-04-16 General Electric Company Hermetically sealed damper assembly and method of assembling same
EP3401514A1 (en) * 2017-05-11 2018-11-14 United Technologies Corporation Fluid damping structure ring and method of fluid damping
FR3108688A1 (en) * 2020-03-27 2021-10-01 Safran Aircraft Engines DOWNSTREAM AXIAL STOP FOR EXTERNAL BEARING BUSH

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2504980B1 (en) * 1981-04-29 1985-06-14 Snecma BEARING ASSEMBLY, PARTICULARLY FOR TURBOMACHINES
US4429923A (en) * 1981-12-08 1984-02-07 United Technologies Corporation Bearing support structure
US4453783A (en) * 1981-12-28 1984-06-12 United Technologies Corporation Bearing support structure
JPH028102Y2 (en) * 1985-02-07 1990-02-27
JPH0532653Y2 (en) * 1986-12-02 1993-08-20
DE4002201A1 (en) * 1990-01-23 1991-07-25 Siemens Ag Dual critical speed rotating machine - avoid overloading by actuating hydraulic presses that act as extra supports for one rotor bearing
US5052828A (en) * 1990-05-25 1991-10-01 General Electric Company Bearing assembly for use in high temperature operating environment
DE4019720A1 (en) * 1990-06-21 1992-01-09 Bmw Rolls Royce Gmbh Through-flow calibration for compressed oil damper - is used with turbine and has housing with roller bearing, outer rings, and seals
DE9401510U1 (en) * 1994-01-29 1994-03-10 Schaeffler Waelzlager Kg Rolling bearing with vibration damping
WO2020160734A1 (en) * 2019-02-07 2020-08-13 Gea Process Engineering A/S Rotary bearing with a damper, a motor and a rotary atomizer comprising such bearing, and the use of such bearing

Family Cites Families (6)

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Publication number Priority date Publication date Assignee Title
GB928250A (en) * 1962-01-12 1963-06-12 Rolls Royce Bearing
FR1325291A (en) * 1962-05-28 1963-04-26 Rolls Royce Bearing support structure for turbojet
GB1032185A (en) * 1964-06-30 1966-06-08 Rolls Royce Improvements relating to the detection of vibration in gas turbine engines
FR1424222A (en) * 1965-02-09 1966-01-07 Rolls Royce New type of bearing, especially for gas turbine engines
FR1501477A (en) * 1965-12-16 1967-11-10 Daimler Benz Ag Gas turbine rotor
GB1162900A (en) * 1967-12-29 1969-08-27 Rolls Royce Bearing Assembly

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2496169A1 (en) * 1980-12-11 1982-06-18 United Technologies Corp VISCOUS SHOCK ABSORBER WITH ROTOR CENTERING ELEMENT
EP0109346A2 (en) * 1982-11-15 1984-05-23 United Technologies Corporation Viscous damper with rotor centering means
EP0109346A3 (en) * 1982-11-15 1986-03-12 United Technologies Corporation Viscous damper with rotor centering means
EP0188666A2 (en) * 1985-01-14 1986-07-30 Rockwell International Corporation Drive shaft assembly
EP0188666A3 (en) * 1985-01-14 1987-05-27 Rockwell International Corporation Drive shaft assembly drive shaft assembly
GB2240821A (en) * 1990-02-07 1991-08-14 Loehr & Bromkamp Gmbh Vibration damper for drive shaft
GB2240821B (en) * 1990-02-07 1993-12-22 Loehr & Bromkamp Gmbh Vibration damper for drive shaft
US5564903A (en) * 1993-11-23 1996-10-15 Alliedsignal Inc. In-line ram air turbine power system
US7524112B2 (en) 2004-01-12 2009-04-28 Snecma Bearing support with double stiffener
FR3009843A1 (en) * 2013-08-26 2015-02-27 Snecma SUPPORTING COLUMNS OF AN EXTERNAL ROLLING BEARING RING FOR AIRCRAFT TURBOMACHINE, AND METHOD OF MOUNTING THE SAME
WO2015054447A1 (en) * 2013-10-11 2015-04-16 General Electric Company Hermetically sealed damper assembly and method of assembling same
US9121448B2 (en) 2013-10-11 2015-09-01 General Electric Company Hermetically sealed damper assembly and methods of assembling same
EP3401514A1 (en) * 2017-05-11 2018-11-14 United Technologies Corporation Fluid damping structure ring and method of fluid damping
US10662811B2 (en) 2017-05-11 2020-05-26 Raytheon Technologies Corporation Fluid damping structure ring and method of fluid damping
FR3108688A1 (en) * 2020-03-27 2021-10-01 Safran Aircraft Engines DOWNSTREAM AXIAL STOP FOR EXTERNAL BEARING BUSH

Also Published As

Publication number Publication date
JPS5572910A (en) 1980-06-02
FR2439331A1 (en) 1980-05-16
DE2942000A1 (en) 1980-04-30

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