EP0211198B1 - Lageranordnung für Turbomaschinen, insbesondere Dampfturbinen - Google Patents

Lageranordnung für Turbomaschinen, insbesondere Dampfturbinen Download PDF

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Publication number
EP0211198B1
EP0211198B1 EP86108226A EP86108226A EP0211198B1 EP 0211198 B1 EP0211198 B1 EP 0211198B1 EP 86108226 A EP86108226 A EP 86108226A EP 86108226 A EP86108226 A EP 86108226A EP 0211198 B1 EP0211198 B1 EP 0211198B1
Authority
EP
European Patent Office
Prior art keywords
bearing
turbine
housing
axial
supporting
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.)
Expired
Application number
EP86108226A
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German (de)
English (en)
French (fr)
Other versions
EP0211198A1 (de
Inventor
Axel Remberg
Detlef Haase
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Publication of EP0211198A1 publication Critical patent/EP0211198A1/de
Application granted granted Critical
Publication of EP0211198B1 publication Critical patent/EP0211198B1/de
Expired legal-status Critical Current

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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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S248/00—Supports
    • Y10S248/901—Support having temperature or pressure responsive feature

Definitions

  • the invention relates to a bearing arrangement for turbomachines, in particular steam turbines, the latter having a plurality of sub-turbines arranged coaxially one behind the other, the shafts of which are rigidly coupled to one another to form a shaft train, as defined in more detail in the preamble of claim 1.
  • the object is achieved by the features specified in the characterizing part of claim 1.
  • Advantageous further developments are given in claims 2 to 12.
  • the advantages that can be achieved with the invention can be seen primarily in the fact that a robust bearing arrangement with large sliding surfaces has been created, in which the coupling of the partial turbine housings to the bearing housings is made possible in a convenient manner, and the partial turbine housings can with their claws from be lowered on top of the support flanges of the bearing housing, the exact height alignment by inserting the adjusting and sliding inserts from the side, i.e. H. easily accessible, done.
  • top surfaces of the support flanges define the horizontal axis plane for the support, it is easy to adapt the support bracket mounting to this reference level, with the height adjustment of the support bracket using the bolts and special adjustment means on these bolts in the form of sliding blocks is secured while allowing sliding play, as explained in claims 2 and 3.
  • the latches are held against the supporting flange by strong, twist-proof anchor bolts and thus in turn secure the supporting claws against lifting.
  • the design of the bearing arrangement as an optional axial fixed point or axial sliding fit as well as other possible variations of the bearing arrangement by design as a single or as a double bearing are dealt with in claims 4 to 9.
  • FIG. 1 and 2 show the outer housing contours of a high-pressure sub-turbine HD and a medium-pressure sub-turbine MD arranged coaxially in the direction of the shaft axis x.
  • the turbine set shown in detail in FIGS. 1 and 2 has two different versions of the bearing arrangement according to the invention in its turbine bearings L1, L2 and L3. Shown are the coaxially arranged housings G1 and G2 of a high-pressure sub-turbine HD and a medium-pressure sub-turbine MD.
  • the turbine bearing L3 is connected to the right end of the latter, followed by or coaxially followed by one or more low-pressure partial turbines, not shown, the illustration of which is not necessary for understanding the invention, although in principle the low-pressure partial turbines with their internal and / or outer housings could be equipped with bearings of the types L1, L2 and L3 according to the invention.
  • the turbine shafts, the shaft couplings and the shaft bearings are not shown in detail in FIGS. 1 and 2, nor are the incoming and outgoing steam lines (only connecting pieces are shown) and the blading inside the partial turbines HD, MD.
  • the coaxial shafts of the partial turbines which cannot be seen from FIGS. 1 and 2, are rigidly coupled to one another to form a shaft train which - apart from the detailed illustration according to FIGS. 10 and 11 - is only indicated by the dash-dotted shaft axis line x.
  • Such foundation bolts are generally formed by the webs of a horizontal table plate made of steel or prestressed concrete that remain between recesses, through the recesses of which the partial turbines protrude with their lower housing halves, the table top supporting the entire turboset being supported by foundation supports on a base plate resting on the building foundation supports how it z.
  • FIGS. 1 and 3 of the article «Deformation behavior of turbine foundations» show.
  • the upper wings of the foundation bolts are at the level n indicated by dashed lines;
  • the bearing housings of the turbine bearings L1, L2 and L3 with their base plates 1.0, which are generally designated by 1 are height-adjusted in these base plates 1.0 by means of jacking screws (not shown) and aligned in the axial direction x, after alignment by means of anchor bolts 1.1 (which are only available in the middle turbine bearing L2 are secured against lifting and poured using in-situ concrete 1.2, whereby in-situ concrete 1.2 the gaps between the base plate 1.0 and a downward rib 1.3 on the base plate on the one hand and the upper edge n of the foundation bolt wings or one receiving the rib 1.3 Rectangular recess 1.4 fills in on the other hand.
  • the foundation bolts FR1 to FR3 can generally be
  • the high-pressure part-turbine HD has a pot housing G1, on which four claws have grown. Of these, only two, namely P11 and P13, can be seen from FIGS. 1 and 2; the other two claws P12 and P14 (not shown) are to be thought of as mirror-symmetrical with respect to the shaft axis x of the claw P11 and claw P13, respectively.
  • the support claw P14 can also be seen in FIG. 10.
  • the housing G1 of the high-pressure turbine part HD also has two molded-on or welded-in, mutually axially opposite inlet connections, of which one EST1 can be seen in FIGS. 1 and 2, and a downflow outlet connection AST1 at the downstream end.
  • the medium-pressure turbine MD has a housing G2, which is divided in the horizontal axis plane xz into an upper housing part G21 and a lower housing part G22, both of which are clamped together with their housing flanges g21 and g22 in the horizontal axis plane xz in a vapor-tight manner (the flange screws are not shown for simplification).
  • a housing G2 which is divided in the horizontal axis plane xz into an upper housing part G21 and a lower housing part G22, both of which are clamped together with their housing flanges g21 and g22 in the horizontal axis plane xz in a vapor-tight manner (the flange screws are not shown for simplification).
  • the upper and lower housing parts G21, G22 of the medium-pressure turbine part MD are each assigned an upstream or downward inlet connection EST2; it is a double-flow medium-pressure turbine section with central inflow (single-flow design is also possible), two bleed steam connections AZ each being provided in the axial direction adjacent to the two inflow connections EST2.
  • the lower housing part G22 has two outflow spigots AST2 which are opposite each other on the same axis and oriented in the axial direction.
  • the bearing principle known in turbomachinery is realized, the housings G1, G2 of the partial turbines HD, MD at their housing ends by means of the claws P11 to P14 or P21 to P24 symmetrically on both sides of the shaft x in horizontal axis planes xz on the bearing housings 1 (or other foundation parts) axially and radially-centric-heat-moveable and adjustable in the x, y and z directions.
  • This heat-moving bearing with adjustment option also includes the axial centering or centering in the vertical axis plane xy.
  • the support and guide surfaces Pxz on the claws which are generally designated P, run in horizontal axis planes (xz), the support and guide surfaces m xy for the axial center guide run on housing forks or spurs, as will be seen below explained, in plane-parallel to the vertical axis plane xy directed vertical planes, and the support and guide surfaces on the claws P for fixing axial fixed points of the thermal expansion of the housing run in axially normal planes yz and are generally designated with py z and in the embodiment according to FIGS. 1 and 2 provided for the middle turbine bearing L2.
  • the two axially normal planes which go through the center of the axially fixed support brackets P13, P14 and P21, P22, are designated in Fig.
  • bearing housing 1 all have a cover plate 1.5 with in the transverse direction extending beyond the span of the opposing support flanges P11-P12, P13-P14 etc., generally designated 2 support flanges, which in detail when they are in the + x direction are oriented or extend in this direction, are labeled 2 + - if they extend in the opposite direction -x -, are labeled 2-.
  • the bearing housing 1 are made of welded steel construction, and their correspondingly strong base or anchor plates 1.0 and cover plates 1.5 are spaced apart from one another in the height direction y by means of end walls 1.6 and side walls 1.7 and connected to form a solid box structure, the anchor plate 1.0 projecting in the axial direction or flanges for anchoring the anchor bolts 1.1, the latter being anchored to corresponding abutment plates (not shown) which penetrate the foundation bolts in cutouts.
  • the turbine bearing L2 (FIG. 3) and the individual representation according to FIGS. 6 to 9 will be discussed first.
  • the support brackets P of the partial turbine housings G1, G2 are each provided with an axially outwardly projecting, step-shaped extension 3 and an axially inwardly adjacent step-up recess 4 .
  • This recess 4 has a horizontal bottom surface 4.1, which serves as a support and guide surface Pxz for the claw P or the associated turbine housing.
  • “Axially inward adjacent” is understood to mean that the recess 4 is axially adjacent in relation to the attachment 3 in the direction of the turbine interior.
  • the associated bearing housing 1 engages according to the position of the support brackets P on both sides of the shaft x with the already mentioned support flanges 2, in particular 2- and 2+, the support brackets P.
  • the support flanges 2 each have a recess 5 for receiving the step-shaped Approach 3 and provided with an axially adjacent step-shaped edge elevation 6 for engagement in the recess 4 of the claw P.
  • adjustment and sliding inserts 8 are inserted into the gap 7.1 between the roof surface 6.1 of the edge elevation 6 and the bottom surface 4.1 of the recess, and their position is secured or can be inserted into this gap 7.1 when the turbo set is installed and can be secured in their inserted position.
  • These adjustment and sliding shims 8 are in particular dimensioned such that the bottom surfaces 4.1 of the claw P are exactly at the level of the horizontal axis plane xz (identical to the horizontal parting joint of the turbine housing) ses G2) are aligned.
  • the adjustment and sliding inserts consist of several layers, as shown in FIG.
  • the bottom surface 4.1 of the recess 4 and also the top surface 3.1 of the axial extension 3 of the support claw P are expediently in the same horizontal plane x-z and can be adjusted to the level of the horizontal axis plane x-z of the turbomachine by means of the adjustment and sliding inserts 8. So that this adjusted position of the claws can be defined in a defined manner while maintaining a slight sliding play, gap-bridging, position-secured sliding blocks 10 are inserted or inserted in gap space 7.2 between the underside of the respective bolt attachment 9.2 and the top surface 3.1 of the axial attachment 3 insertable during assembly.
  • the locking lugs 9.2 penetrating fixing screws 11 are expediently screwed from above into a threaded blind hole 10.1 of the sliding blocks and secured against rotation in the screwed-in position, see anti-rotation device 11.1 on the head of the screw 11.
  • the screws 11 penetrate the bolts in corresponding bores 11.2; they can be seen from the right-hand part of FIG. 7 from above and are assigned in pairs to the respective locking projection 9.2 with corresponding sliding blocks 10.
  • the bars 9 that secure the lifting brackets P against lifting are themselves strong in a thickness of 20 to 30 mm and are held against the suspension flange 2 by correspondingly strong anchor bolts 12, which are screwed into threaded blind holes 2.2 of the suspension flange 2.
  • These are expansion screws with strong heads 12.1 and a thread 12.2 at their lower end, e.g. B. size M52; corresponding to 52 mm.
  • the bars 9 are thus held under the pretension of the expansion screws 12 against the cover surface 2.1 and cannot loosen during vibrations during operation.
  • the middle turbine bearing L2 serves to fix an axial fixed point of thermal expansion or to fix corresponding fixed point planes (yz) and (yz) 2 going through the fixed points.
  • the two gap spaces 7.3a and 7.3b which are formed between the flanks 6.2, 6.3 of the edge elevation 6 of the support flange 2 pointing in the + x and -x direction and the side surfaces 4.2 of the recess 4 of the claw P on the opposite side, Sliding and adjusting inserts in the form of feather keys 13 or 13a, 13b inserted and secured in their position or insertable and securable during assembly.
  • FIG. 9 shows the position of the feather keys 13a, 13b, which grip the edge elevation 6 of the supporting flange 2 with outer angular projections 13.1 and are secured in their inserted position by a cover plate 14, the fastening screws 15 of this cover plate 14, which are screwed into the corresponding threaded blind holes in the edge elevation 6 from the side, are fixed in their screwed-in position by means of an anti-rotation device 16.
  • the latter is designed according to the anti-rotation device 11.1 for the screws 11 as an anti-rotation plate with a flexible flap.
  • the shoe 8.3 of the adjustment and sliding insert arrangement 8 is secured in the lateral direction z, as shown in FIG. 8 in detail.
  • the side surfaces 4.2 correspond to the support and guide surfaces generally designated Py z from FIG. 2.
  • the fixed edge elevations 6 of the support flanges 2 in connection with the inserted feather keys 13a, 13b thus provide fixed stops in the direction x for the side surfaces 4.2 of the support claw recess 4, the axis-normal reference planes of which are shown in dash-dot lines in FIG. 6 and summarized again are referred to as the reference planes (yz) or (yz) 2 already drawn in FIG. 2.
  • This forms the axial fixed points of the housing expansion for the housing G1 of the high-pressure part-turbine HD and the housing G2 of the medium-pressure part-turbine MD, the housing expansions of which originate from these fixed points in the direction -x or + x.
  • the turbine bearing L2 thus forms a double bearing, with four pairs of supports P13-P14 and P21-P22, each supported in pairs and on both sides of the shaft center, i.e. on both sides of the vertical axis plane xy, on a double flange 2- or 2+ of the bearing housing 2 (cf. 10), of which the pair P13-P14 resting on one axial end of the two double flanges to the housing of the high-pressure part-turbine HD and the pair P21-P22 of the claws P resting on the other axial end of the two double flanges to the housing G2 of the axially adjacent medium-pressure turbine MD belongs.
  • axial encoder 22 is fastened to the bearing housing 1, which with its two measuring sensors 22.1, 22.2 faces the two end faces of a shaft collar 17.2 with a narrow gap.
  • they are inductive sensors that are used to control the axial shaft position.
  • Fig. 10 in connection with Fig. 7 shows an advantageous measuring arrangement, wherein on an axially projecting projection 3 of the claws P measuring marks or pointers 28 are attached, to which scales 29 attached in the edge region of the supporting flange 2 for reading the housing expansion in the direction + z or -z are assigned.
  • P measuring marks or pointers 28 are attached, to which scales 29 attached in the edge region of the supporting flange 2 for reading the housing expansion in the direction + z or -z are assigned.
  • the turbine bearing L1 according to FIG. 4 is designed as a single bearing with two support brackets P11 and (not visible) P12 supported individually on each side of the shaft center x on a supporting flange 2 of the bearing housing 1.
  • This housing bearing differs from that according to FIG. 3 in that the feather keys 13a, 13b for defining the axial fixed points are missing here, so that the claws P here in direction -x, starting from the fixed point reference plane (yz) i be able to move freely and without hindrance.
  • the medium-pressure sub-turbine MD extends in the + x direction and then the inner casing of the low-pressure sub-turbines expand in the same direction, which in relation to the axial shaft expansion, which starts from the same turbine bearing L2 in the + x direction, results in very small axial blade clearances.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Magnetic Bearings And Hydrostatic Bearings (AREA)
EP86108226A 1985-06-27 1986-06-16 Lageranordnung für Turbomaschinen, insbesondere Dampfturbinen Expired EP0211198B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3522917 1985-06-27
DE19853522917 DE3522917A1 (de) 1985-06-27 1985-06-27 Lageranordnung fuer turbomaschinen, insbesondere dampfturbinen

Publications (2)

Publication Number Publication Date
EP0211198A1 EP0211198A1 (de) 1987-02-25
EP0211198B1 true EP0211198B1 (de) 1988-05-11

Family

ID=6274284

Family Applications (1)

Application Number Title Priority Date Filing Date
EP86108226A Expired EP0211198B1 (de) 1985-06-27 1986-06-16 Lageranordnung für Turbomaschinen, insbesondere Dampfturbinen

Country Status (6)

Country Link
US (1) US4732533A (enrdf_load_stackoverflow)
EP (1) EP0211198B1 (enrdf_load_stackoverflow)
JP (1) JPS623107A (enrdf_load_stackoverflow)
DE (2) DE3522917A1 (enrdf_load_stackoverflow)
ES (1) ES2000086A6 (enrdf_load_stackoverflow)
IN (1) IN165002B (enrdf_load_stackoverflow)

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5104289A (en) * 1990-10-25 1992-04-14 Westinghouse Electric Corp. Turbine having support arrangement for minimizing humping
US5133641A (en) * 1991-02-01 1992-07-28 Westinghouse Electric Corp. Support arrangement for optimizing a low pressure steam turbine inner cylinder structural performance
RU2154170C1 (ru) * 1999-04-21 2000-08-10 Акционерное общество открытого типа "Ленинградский Металлический завод" Опорный узел цилиндра паровой турбины
US7267319B2 (en) * 2004-11-09 2007-09-11 General Electric Company Low-friction slide-plates for rotary machines
EP1719880A1 (de) * 2005-05-03 2006-11-08 Siemens Aktiengesellschaft Dampfturbine
DE102006027237A1 (de) * 2005-06-14 2006-12-28 Alstom Technology Ltd. Dampfturbine
EP1967702A1 (de) * 2007-03-05 2008-09-10 Siemens Aktiengesellschaft Zapfen für Mittenfixierung
US20110000222A1 (en) * 2007-08-31 2011-01-06 General Electric Company Gas turbine rotor-stator support system
US8047779B2 (en) * 2008-10-23 2011-11-01 General Electric Company Combined axial and transverse constraint and alignment system and method for rotary machines
US8337151B2 (en) * 2009-06-30 2012-12-25 General Electric Company System and method for aligning turbine components
US9157335B2 (en) 2012-03-27 2015-10-13 General Electric Company Side supported turbine shell
JP6694837B2 (ja) 2017-02-27 2020-05-20 三菱日立パワーシステムズ株式会社 蒸気タービン
EP3412877B1 (en) * 2017-06-05 2020-08-19 General Electric Company Bearing bumper for blade out events
CN109113811B (zh) * 2018-07-06 2023-09-08 华电电力科学研究院有限公司 一种汽轮机用基架及其安装方法

Family Cites Families (10)

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Publication number Priority date Publication date Assignee Title
GB777598A (en) * 1954-10-13 1957-06-26 British Thomson Houston Co Ltd Improved mounting for turbine casings
CH334428A (de) * 1954-10-22 1958-11-30 Maschf Augsburg Nuernberg Ag Axialdurchströmte Turbine für heisse Treibmittel, insbesondere Gasturbine
CH426886A (de) * 1965-07-08 1966-12-31 Escher Wyss Ag Turbomaschine mit einem durch eine waagrechte, axiale Ebene geteilten Gehäuse
GB1145612A (en) * 1966-04-12 1969-03-19 Licentia Gmbh Improvements relating to steam turbines
DE1812487A1 (de) * 1968-12-03 1970-08-13 Siemens Ag Gehaeuseanordnung fuer Niederdruckteile von Dampfturbinen in vollstaendig geschweisster mehrschaliger Bauweise
JPS5227282B2 (enrdf_load_stackoverflow) * 1970-11-05 1977-07-19
SU546732A2 (ru) * 1972-05-29 1977-02-15 Предприятие П/Я А-3513 Устройство креплени к фундаменту боковых конденсаторов
CH592268A5 (enrdf_load_stackoverflow) * 1975-07-02 1977-10-14 Bbc Brown Boveri & Cie
FR2411960A1 (fr) * 1977-12-14 1979-07-13 Creusot Loire Fixation sur socle du stator d'une turbomachine
DE3105509A1 (de) * 1981-01-14 1982-08-05 BBC Aktiengesellschaft Brown, Boveri & Cie., 5401 Baden, Aargau Befestigungsvorrichtung fuer ein turbinengehaeuse

Also Published As

Publication number Publication date
JPS623107A (ja) 1987-01-09
EP0211198A1 (de) 1987-02-25
DE3522917A1 (de) 1987-01-08
DE3660189D1 (en) 1988-06-16
IN165002B (enrdf_load_stackoverflow) 1989-07-29
US4732533A (en) 1988-03-22
ES2000086A6 (es) 1987-12-01

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