EP2891873B1 - Trägervorrichtung zur balancekorrektur - Google Patents

Trägervorrichtung zur balancekorrektur Download PDF

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Publication number
EP2891873B1
EP2891873B1 EP13833183.0A EP13833183A EP2891873B1 EP 2891873 B1 EP2891873 B1 EP 2891873B1 EP 13833183 A EP13833183 A EP 13833183A EP 2891873 B1 EP2891873 B1 EP 2891873B1
Authority
EP
European Patent Office
Prior art keywords
mandrel
rotor
outer peripheral
support
aerostatic
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.)
Active
Application number
EP13833183.0A
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English (en)
French (fr)
Other versions
EP2891873A4 (de
EP2891873A1 (de
Inventor
Takeshi Fujimaki
Kazumasa MIYAHARA
Yoshio SHIMOKURA
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.)
IHI Rotating Machinery Engineering Co Ltd
Original Assignee
IHI Compressor and Machinery Co Ltd
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Publication date
Application filed by IHI Compressor and Machinery Co Ltd filed Critical IHI Compressor and Machinery Co Ltd
Publication of EP2891873A1 publication Critical patent/EP2891873A1/de
Publication of EP2891873A4 publication Critical patent/EP2891873A4/de
Application granted granted Critical
Publication of EP2891873B1 publication Critical patent/EP2891873B1/de
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Classifications

    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/027—Arrangements for balancing

Definitions

  • the present invention relates to a support apparatus for balance correction for rotatably supporting a rotating body using a vertical mandrel having an aerostatic bearing in order to correct the balance of the rotating body rotating at high speeds such as a turbocompressor rotor.
  • a support apparatus for balance correction
  • a support apparatus for rotatably supporting the rotor alone using a mandrel having an aerostatic bearing.
  • most of the support apparatuses have a structure such that as the mandrel, there is used a cylindrical mandrel member which is fitted into a support hole with a circular cross section located at a rotation axis portion of the rotor, aerostatic radial bearings (each having radial bearing surface including a jet hole) are provided on an outer peripheral surface of the mandrel member, and aerostatic thrust bearings (each having a thrust bearing surface including a jet hole) are provided on the base end side of the mandrel member.
  • the structure When the mandrel is fitted into the support hole of the rotor, the structure allows the entire rotor to be mounted on the mandrel. Then, compressible fluid (air for aerostatic bearings) is jetted onto internal surfaces of the support hole through the jet holes of the aerostatic radial bearings, and compressible fluid (air for aerostatic bearings) is jetted onto the periphery of the opening (end surface of the rotor) at the lower end of the support hole through the jet holes of the aerostatic thrust bearings, whereby the rotor is rotatably supported around the mandrel in a floating state.
  • compressible fluid air for aerostatic bearings
  • the amount of imbalance is measured by applying rotational force to the rotor in the floating state from outside, such as by jetting air for drive (drive fluid) onto the rotor surface, to rotate the rotor at high speeds, and then using various sensors provided in the balance correction apparatus to measure the behavior of the rotating rotor.
  • Patent Document 1 Japanese Patent Laid-Open No. 2005-172538 ( Figure 5 )
  • the support hole of the rotor is generally a hole having a cylindrical shape with a circular cross section, that is, a circular cross section in an entire axial direction. The reason for this is to fittingly insert the end of the shaft mating with the rotor into the support hole and to couple the shaft with the rotor by bolts or the like.
  • compressible fluid jetted through the jet holes of the aerostatic bearings generally fills between an outer peripheral surface of the mandrel and an inner surface of the support hole serving as a portion supporting the rotor by aerostatic gas.
  • the support hole has the same shape with a circular (perfect circular) cross section as the outer peripheral shape of the mandrel, a rotation of the rotor causes no pressure variation, thereby ensuring high measurement accuracy.
  • the support hole has a polygon-shaped inner hollow portion, squeeze occurs between the polygon-shaped portion and the outer peripheral surface of the mandrel according to the rotation (displacement) of the rotor unlike the case where the support hole has the circular (perfect circular) cross section. The squeeze effect at this time causes pressure to repeatedly increase and decrease between the same.
  • the rotor supported by the mandrel generates hunting vibration due to this pressure variation. This vibration tends to impair the accuracy of measuring the amount of imbalance of the rotor. This vibration also poses a problem in that the rotor is likely to contact the mandrel, which may prevent satisfactory measurement of the amount of imbalance as desired.
  • an object of the present invention is to provide a support apparatus for balance correction capable of measuring the amount of imbalance of a rotating body having a support hole including a polygonal shaped portion with a high accuracy.
  • the present invention provides a support apparatus for balance correction as defined in the claims
  • the variation in pressure occurring in a space between the polygon-shaped cross-section portion of the support hole and the outer peripheral surface of the mandrel is relieved outside through the vent holes.
  • This configuration can suppress the pressure variation in a space between the polygonal shape cross-section portion of the support hole and the outer peripheral surface of the mandrel due to squeeze.
  • the present invention can measure the amount of imbalance of the rotating body having a support hole, part of which is formed in a polygonal shape, with a high accuracy.
  • the present invention can avoid a risk that the rotating body may contact the mandrel. Further, the present invention requires only a simple structure.
  • the present invention can evenly relieve the varied pressure from within a space between the polygonal shape cross-section portion and the outer peripheral surface of the mandrel through a large number of vent holes, thereby further exerting much higher effects.
  • the present invention form the vent holes on the shortest route, which makes it much easier to relieve pressure outside, thereby further exerting much higher effects.
  • FIGS. 1 to 7 an embodiment illustrated in FIGS. 1 to 7 .
  • FIG. 1 illustrates a schematic configuration of a balance correction apparatus for measuring the amount of imbalance (amount of dynamic imbalance) of a rotating body such as a turbocompressor rotor 1 (e.g., compressor rotor), in which reference numeral 2 denotes a base plate of the apparatus, reference numeral 3 denotes a frame body standingly disposed on an upper surface of the base plate 2, and reference numeral 4 denotes a vibration bridge body disposed in front of the frame body 3.
  • a turbocompressor rotor 1 e.g., compressor rotor
  • Each portion of the vibration bridge body 4 is coupled with a plurality of support spring members 5a protruding from the front surface of the frame body 3 and support spring members 5b (only some of them being illustrated) protruding from the upper surface of the base plate 2 so as to displaceably support the entire vibration bridge body 4 leftward and rightward.
  • a support arm body 6 extends in a band shape from a front portion of the vibration bridge body 4.
  • a support apparatus 10 (corresponding to the support apparatus for balance correction of the present application) for supporting the turbocompressor rotor 1 is mounted on a front end portion of the band-shaped support arm body 6.
  • reference numeral 8a denotes a mounting member for mounting the various sensors 8 on the base plate 2
  • reference numeral 9a denotes a mounting member for mounting the jet head portion 9 on the base plate 2.
  • the above support apparatus 10 uses a structure using the vertical mandrel 11 for rotatably supporting the rotor 1 (single body) by aerostatic bearings.
  • the structure of the support apparatus 10 is illustrated in FIG. 2 .
  • the rotor 1 serving as a component to be measured.
  • the rotor 1 includes a rotor body 20 in which a large number of blades 1a are formed on a disc-shaped base surface portion 20a.
  • the rotor body 20 includes a cylindrical boss portion 21 formed at a center portion of the base surface portion 20a.
  • the rotation axis portion of the rotor body 20 and the boss portion 21 of the base surface portion 20a include a support hole 22 having a circular cross section and penetrating the portions in a straight line.
  • the support hole 22 includes therein a shaft 23 having a circular cross section and mating with the rotor 1.
  • an end portion of the shaft 23 is inserted into the support hole 22, and the insertion end is fixed by a fixing member such as a nut member (not illustrated), whereby the rotor 1 is tightened between a receiving portion 23a receiving the end of the boss portion 21, thereby forming a module incorporating the rotor 1, that is, a rotor module.
  • a fixing member such as a nut member (not illustrated)
  • a structure having a polygonal shaped portion constituting part of the shaft 23 and support hole 22 is used (for example, for strong coupling, high precision axis alignment, and other purposes).
  • the support hole 22 including an inner hollow portion having a circular cross section and covering the entire rotor 1 from one end to the other end thereof, and the shaft 23 having a circular cross section and corresponding to the support hole 22 are used.
  • an end constituting part of the support hole 22 specifically, an inner surface of the boss portion 21 serving as the base end of the support hole 22 includes therein a triangular inner surface 26a as a polygon-shaped cross-section portion larger than the other inner hollow with a circular cross section, and the inside of the inner surface 26a is used as the triangular inner hollow portion 26.
  • the shaft 23 includes a triangular flange portion 27 fitted into the triangular inner hollow portion 26. In other words, the rotor 1 and the shaft 23 are coupled with each other using a structure of fitting the triangular inner hollow portion 26 and the flange portion 27 to each other.
  • the support apparatus 10 illustrated in FIGS. 1 and 2 includes a structure for stably supporting the rotor 1 using the support hole 22, part of which is formed in a polygonal shape.
  • Reference numeral 11 denotes the aforementioned mandrel.
  • the mandrel 11 includes a cylindrical mandrel member.
  • the mandrel member is standingly disposed on an upper surface of a front end portion of the support arm body 6 so that the rotor 1 is mounted thereon from above the mandrel 11.
  • the mandrel 11 includes a mounting seat 30 fixed on the support arm body 6, a disk-shaped portion 31 receiving the lower end of the rotor 1 (end of the boss portion 21), and a cylindrical portion 32 insertable into the rotor 1, in the order starting from the lower end thereof, and the mandrel 11 extends by a predetermined amount in the vertical direction from the support arm body 6.
  • a portion on which the rotor body 20 on the front end side is mounted includes a pillar portion 32a with a circular cross section corresponding to the shape of a small diameter hole portion 22d occupying most of the support hole 22 of the rotor body 20. As illustrated in FIG.
  • the portion on which the boss portion 21 on the base end side is mounted includes a pillar portion 32b having a diameter larger than that of the pillar portion 32a so as to fit the shape of a stepped portion 22a of the support hole 22.
  • the portion corresponding to a triangular inner hollow portion 26 includes a pillar portion 32c (having a diameter smaller than that of the inner surface 26a) having a diameter smaller than that of the pillar portion 32b.
  • the rotor 1 can be mounted around the mandrel 11 simply by inserting the mandrel 11 into the rotor 1 from an end (base end) of the support hole 22 without being affected by the presence or absence of the triangular inner hollow portion 26.
  • an outer peripheral surface of the pillar portions 32a and 32b of the mandrel 11 includes aerostatic radial bearing surfaces 34b each having a large number of jet holes 34a to form an aerostatic radial bearing 34 receiving the inner surface of the support hole 22.
  • the upper surface of the disk-shaped portion 31 includes an aerostatic thrust bearing surface 35b having a large number of jet holes 35a around the axis corresponding to the position of the end of the boss portion 21 to form therein an aerostatic thrust bearing 35 receiving the end surface (periphery of the opening of the support hole 22) of the boss portion 21 serving as the lower end of the rotor 1.
  • the jet hole 34a is connected to an outside static pressure bearing gas supply device 37 through a path 36a having various hole diameters and formed along an axial portion of the mandrel 11 and a relay path 36b formed inside the support arm body 6.
  • the jet hole 35a is connected to the aforementioned static pressure bearing gas supply device 37 through a path 38a formed in the disk-shaped portion 31 and a relay path 38b formed inside the support arm body 6.
  • the outer peripheral surface of the pillar portion 32c facing the triangular inner hollow portion 26 (corresponding to the polygon-shaped cross-section portion of the present application) of the rotor 1 includes a vent hole 38.
  • the vent hole 38 comprises a large number of vent holes, that is, here 9 vent holes, which are provided at equal intervals along a circumferential direction of the mandrel 11.
  • any of the vent holes 38 includes a small diameter J-shaped path 39 in which an inlet 39a is opened in a space formed between the pillar portion 32c and the inner surface 26a, and an outlet 39b is opened outside the space.
  • the inlet 39a of the path 39 is opened in an outer peripheral surface portion of the pillar portion 32c located near the lowest position in the space between the pillar portion 32c and the inner surface 26a; and the outlet 39b is opened at a position near and facing outside the aerostatic thrust bearing surface 35b, for example, at a position closer to the bearing surface 35b of the end surface of the disk-shaped portion 31 to form the path 39 by the shortest route.
  • the path 39 formed by the shortest route provides a structure in which when the rotor 1 is rotated, a pressure variation occurring in a space between the triangular inner surface 26a and the outer peripheral surface of the pillar portion 32c with a circular cross section, particularly a rising pressure, is relieved outside.
  • the mandrel 11 standing up in the vertical direction is fitted into the support hole 22 of the rotor 1 thereby to mount the rotor 1 on the mandrel 11.
  • the hole portion 22d of the rotor 1 is disposed on the pillar portion 32a with a circular cross section of the mandrel 11 (including an upper aerostatic radial bearing 34)
  • the stepped portion 22a of the rotor 1 is disposed on the pillar portion 32b (including a lower aerostatic radial bearing 34)
  • the triangular inner hollow portion 26 of the rotor 1 is disposed on the pillar portion 32c.
  • the end of the boss portion 21 of the rotor 1 is disposed on the aerostatic thrust bearing surface 35b.
  • compressed air (compressible fluid) from the static pressure bearing gas supply device 37 is jetted by a predetermined amount through each of the jet holes 34a and 35a.
  • air jetted through the jet hole 34a flows in between the aerostatic radial bearing surface 34b and the inner surface of the hole portion 22d and the inner surface of the stepped portion 22a, whereby the air flow flowing in therebetween rotatably supports the rotor 1 around the mandrel 11.
  • the space (inner hollow portion 26) between the triangular inner surface 26a of the rotor 1 and the pillar portion 32c of the mandrel 11 is filled with air jetted through the jet holes 34a and 35a of the aerostatic bearings 34 and 35.
  • the above described rotor causes no problem because the rotor is mounted on the mandrel with the same circular shape as each other, but the rotor 1 is specified such that the end of the support hole 22 has a polygon shape, specifically, a triangular shape. Therefore, as the rotor 1 is rotated, squeeze occurs between the boss portion 21 having the triangular inner hollow portion 26 and the pillar portion 32c with a circular cross section. For this reason, an increase and a decrease in pressure due to squeeze effect occurs repeatedly in the space between the triangular inner surface 26a and the pillar portion 32c with a circular cross section. Specifically, as illustrated in FIG. 5 , pressure is increased on the front side in the direction of the rotation of the varying triangular inner surface 26a, and pressure is decreased on the rear side in the direction of the rotation thereof.
  • the rotor 1 generates hunting vibration due to the pressure variation. If left in this state, the rotor 1 is affected by the hunting vibration, which impairs the accuracy of measuring the amount of imbalance of the rotor 1.
  • the mandrel 11 includes the vent hole 38 for relieving the pressure varying in the space between the triangular inner surface 26a and the pillar portion 32c with a circular cross section outside. Therefore, as illustrated by the arrows in FIGS. 2 and 5 , the pressure variation occurring in the space, that is, the rising pressure, is relieved out of the space (outside) through the vent hole 38. The falling pressure is compensated by the air of the aerostatic bearings 34 and 35.
  • the amount of imbalance of the rotor 1 (rotating body) can be measured with a high accuracy.
  • the measurement accuracy can be improved simply by forming the vent hole 38 at a position of the outer peripheral surface of the mandrel 11 facing the polygon-shaped cross-section portion of the support hole 22, which requires only a simple structure. Further, this structure can avoid a risk, and concern, that the rotor 1 may contact the mandrel 11.
  • vent holes 38 are provided at equal intervals along a circumferential direction of the mandrel 11, which can evenly relieve the varied pressure outside, thereby further effectively can suppress the pressure variation.
  • vent holes 38 are formed on the shortest route, which makes it easy to relieve the varied pressure outside, thereby more effectively suppress the pressure variation.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Testing Of Balance (AREA)
  • Manufacture Of Motors, Generators (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)

Claims (3)

  1. Stützvorrichtung zur Gleichgewichtskorrektur, Folgendes aufweisend:
    einen drehenden Körper (1), der eine Stützöffnung (22) mit einem kreisförmigen Querschnitt an einem Drehzentrumsabschnitt hat, bei dem eine Endseite der Stützöffnung in einem polygonförmigen Querschnitt ausgebildet ist, und einen vertikalen Dorn (11), an dem der drehende Körper in einer vertikalen Richtung durch Einsetzen in die Stützöffnung angebracht ist, wobei eine Außenumfangsfläche des Dorns ein aerostatisches Radiallager (34) hat, das drehbeweglich eine Innenfläche mit einem kreisförmigen Querschnitt der Stützöffnung aufnimmt, eine Basisendseite ein aerostatisches Drucklager (35) hat, das drehbeweglich einen Umfang einer Öffnung an einem unteren Ende der Stützöffnung aufnimmt, und eine Struktur so ausgebildet ist, dass komprimierbares Fluid zur aerostatischen Lagerung aus dem aerostatischen Radiallager und dem aerostatischen Drucklager ausgestoßen wird, um den drehenden Körper drehbeweglich abzustützen, während der drehende Körper um den Dorn schwebt, um zu ermöglichen, dass der Betrag an Ungleichgewicht gemessen werden kann, indem eine Drehkraft an den drehenden Körper in einem schwebenden Zustand angelegt wird, dadurch gekennzeichnet, dass
    von der Außenumfangsfläche des Dorns ein dem polygonförmigen Querschnittsabschnitt der Stützöffnung zugewandter Außenumfangsflächenabschnitt ein Luftloch (38) hat, um Druck abzubauen, der in einem Raum zwischen dem polygonförmigen Querschnittsabschnitt und der Außenumfangsfläche der Dornaußenseite entsprechend der Drehung des drehenden Körpers variiert.
  2. Stützvorrichtung zur Gleichgewichtskorrektur nach Anspruch 1, dadurch gekennzeichnet, dass das Luftloch (38) eine große Anzahl Luftlöcher hat, die in gleichen Abständen entlang einer Umlaufrichtung der Außenumfangsfläche des Dorns (11) vorgesehen sind.
  3. Stützvorrichtung zur Gleichgewichtskorrektur nach einem der Ansprüche 1 oder 2, dadurch gekennzeichnet, dass es sich bei dem Luftloch (38) um einen Weg handelt, wobei der Weg einen Einlass (39a) nahe einer tiefsten Stelle des Raums zwischen dem polygonförmigen Querschnittsabschnitt des Dorns (11) und der Außenumfangsfläche des Dorns hat, wobei der Weg einen Auslass (39b) an einer nahe der Oberfläche (35b) des aerostatischen Drucklagers nach außen gewandten Stelle hat.
EP13833183.0A 2012-08-30 2013-08-29 Trägervorrichtung zur balancekorrektur Active EP2891873B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2012189633A JP5415601B1 (ja) 2012-08-30 2012-08-30 バランス修正用支承装置
PCT/JP2013/073118 WO2014034769A1 (ja) 2012-08-30 2013-08-29 バランス修正用支承装置

Publications (3)

Publication Number Publication Date
EP2891873A1 EP2891873A1 (de) 2015-07-08
EP2891873A4 EP2891873A4 (de) 2016-04-06
EP2891873B1 true EP2891873B1 (de) 2017-07-26

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EP13833183.0A Active EP2891873B1 (de) 2012-08-30 2013-08-29 Trägervorrichtung zur balancekorrektur

Country Status (6)

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EP (1) EP2891873B1 (de)
JP (1) JP5415601B1 (de)
KR (1) KR101988465B1 (de)
CN (1) CN104769404B (de)
HK (1) HK1212019A1 (de)
WO (1) WO2014034769A1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10054129B2 (en) * 2014-03-24 2018-08-21 Ihi Rotating Machinery Enginering Co., Ltd. Support apparatus for balance correction

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP6830263B2 (ja) * 2016-08-10 2021-02-17 国際計測器株式会社 動釣合い試験機
US20230037942A1 (en) * 2017-06-16 2023-02-09 Trane International Inc. Aerostatic thrust bearing and method of aerostatically supporting a thrust load in a scroll compressor
JP7005372B2 (ja) * 2018-02-09 2022-02-10 三菱電機株式会社 回転電機、電気掃除機、回転電機のバランス試験方法および回転電機の製造方法ならびに電気掃除機の製造方法
CN117072470A (zh) * 2023-09-07 2023-11-17 佛山市南海区绿智电机设备有限公司 一种带定位结构的新风系统离心风扇叶及平衡校正装置

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE59710695D1 (de) * 1997-09-19 2003-10-09 Abb Turbo Systems Ag Baden Verdichterradbefestigung für schnellaufende Turbomaschinen
JP2005172537A (ja) * 2003-12-10 2005-06-30 Ishikawajima Harima Heavy Ind Co Ltd 回転体のバランス修正用支承装置
JP3918809B2 (ja) * 2003-12-10 2007-05-23 石川島播磨重工業株式会社 回転体のバランス修正用支承装置
JP2006316951A (ja) * 2005-05-16 2006-11-24 Valeo Thermal Systems Japan Corp 圧縮機の動力伝達装置
JP2009281462A (ja) * 2008-05-21 2009-12-03 Ntn Corp 静圧気体軸受スピンドル
JP5660292B2 (ja) * 2010-08-09 2015-01-28 株式会社Ihi バランス修正装置と方法
CN203443733U (zh) * 2013-08-15 2014-02-19 甘肃酒钢集团宏兴钢铁股份有限公司 高速线材传动柜冷却风机动平衡校正装置

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10054129B2 (en) * 2014-03-24 2018-08-21 Ihi Rotating Machinery Enginering Co., Ltd. Support apparatus for balance correction

Also Published As

Publication number Publication date
HK1212019A1 (en) 2016-06-03
KR20150047566A (ko) 2015-05-04
EP2891873A4 (de) 2016-04-06
KR101988465B1 (ko) 2019-06-12
EP2891873A1 (de) 2015-07-08
CN104769404A (zh) 2015-07-08
JP2014048091A (ja) 2014-03-17
WO2014034769A1 (ja) 2014-03-06
JP5415601B1 (ja) 2014-02-12
CN104769404B (zh) 2018-02-27

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