EP0213297A1 - Moyen de connexion entre les carters d'un groupe de turbines - Google Patents

Moyen de connexion entre les carters d'un groupe de turbines Download PDF

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Publication number
EP0213297A1
EP0213297A1 EP86108225A EP86108225A EP0213297A1 EP 0213297 A1 EP0213297 A1 EP 0213297A1 EP 86108225 A EP86108225 A EP 86108225A EP 86108225 A EP86108225 A EP 86108225A EP 0213297 A1 EP0213297 A1 EP 0213297A1
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EP
European Patent Office
Prior art keywords
turbine
pressure
housing
bearing
low
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.)
Granted
Application number
EP86108225A
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German (de)
English (en)
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EP0213297B1 (fr
Inventor
Axel Remberg
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Siemens AG
Original Assignee
Kraftwerk Union AG
Siemens AG
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Publication of EP0213297A1 publication Critical patent/EP0213297A1/fr
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Expired 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • 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

Definitions

  • the invention relates to a turbo set with at least one low-pressure sub-turbine, which has an outer housing and an inner housing coaxial therewith, and with at least one further high-pressure and / or medium-pressure sub-turbine arranged coaxially and upstream of the low-pressure sub-turbine, the shafts of the sub-turbines are rigidly coupled together to form a shaft train, as further defined in the preamble of claim 1.
  • An axially and radially flexible bellows which is attached to a collar of the coupling rod on the one hand and to the outer housing on the other hand, serves in particular as a sealing element for sealing the bushing. It is therefore subject to relatively large shifts.
  • the seal can also be made by means of a sliding fit, but this is never completely vacuum-tight or requires very precise machining.
  • the turbine type A has an axis-normal reference plane for the axial housing expansion, which is placed in a turbine bearing between the medium-pressure and the first low-pressure part-turbine. This fixes the fixed point of the housing expansion for the inner housing of the low-pressure sub-turbines in the + x direction and for the connected housing of the medium-pressure and high-pressure sub-turbine in the -x direction.
  • the bearing blocks or bearing housings of the high and medium pressure Partial turbines are fixed in each case, but the axial bearing or thrust bearing of the turbine shaft is movable, the housing of which is connected to the housing of the high-pressure subturbine by two horizontal connecting rods and the axial displacement of which follows.
  • the coupling or push rods for the axial displacement of the inner casing of the low-pressure partial turbines in the same direction are only indicated; the turbine bearings for the inner casing are - as in DE-AS 1 216 322 - not shown and not described. It is emphasized, however, that the known turbine type A allows a good adjustment of the axial rotor and housing thermal expansions occurring during operation, particularly in the LP (low pressure) part of the turbine.
  • the object is achieved in a turbo set according to the preamble of claim 1 by the features specified in the characterizing part of claim 1.
  • Advantageous further developments are specified in subclaims 2 to 15.
  • subclaims 2 to 7 and 10 prove to be particularly advantageous for accessibility in the sense of the first subtask.
  • An advantageous embodiment of the sealing membrane is dealt with in claim 8, and in claim 9 a streamlined shape of the support and claw arms is specified.
  • the subject matter of claim 11 proves to be favorable, in that in the area of the thrust-transmitting turbine bearings, by opening a sealing cover, a turnbuckle chamber is accessible from above, in each of which a turnbuckle for axial adjustment or readjustment of the axial alignment of the Coupling rods is housed.
  • the turboset shown in FIGS. 1 and 2 consists of the coaxial to each other in the direction of the shaft axis x arranged partial turbines HD, MD, ND1 and ND2.
  • Each of the low-pressure partial turbines ND1 and ND2, which are constructed identically to one another, has an outer casing nd and - as is shown in particular in FIGS. 10 and 11 - an inner casing 2 coaxial therewith.
  • each of the low-pressure sub-turbines usually has two evaporation flows 3/1, 3/11 and a common central inflow 4 (for which two diametrically opposed pipe sockets are provided), one speaks in a low-pressure sub-turbine of a double-flow design, in two low-pressure sub-turbines of four-flow design, etc.
  • a further high-pressure and / or medium-pressure partial turbine is provided coaxially and upstream of the first or only low-pressure partial turbine ND1 or ND.
  • Partial turbine MD is also essential that a further high-pressure and / or medium-pressure partial turbine is provided coaxially and upstream of the first or only low-pressure partial turbine ND1 or ND.
  • the individual shafts of the partial turbines HD, MD, ND1, ND2 are rigidly coupled together to form a shaft train W, which can be seen in sections from FIGS. 10 and 11, the two-shaft couplings 5.2, 5.3 with their clamped together being particularly clear from FIG. 11 , unspecified coupling flanges and the two the shaft couplings 5.2, 5.3 immediately adjacent bearing positions mw6.2, w6.3 can be seen.
  • the housings hd, md and nd of the partial turbines HD, MD, ND1 and ND2 and the common shaft train W are mounted on turbine bearings, generally designated 6, which are each located in axial gaps between the individual partial turbines, namely the turbine bearings 6.1, 6.2 and 6.3, are located or which are in front of the head of the high-pressure sub-turbine HD or in front of the head of the second low-pressure sub-turbine ND2 and are designated 6.4 or 6.5.
  • the turbine bearings 6.1 to 6.5 are supported on foundation bolts for a table top designated as a whole with FR (see FIGS. 2 and 15) in the axial spaces between the partial turbines and at the ends of the latter.
  • foundation bolts fr are generally formed by the webs of the horizontal table top FR made of prestressed concrete or steel which remain between the cutouts, through the cutouts of which the partial turbines protrude with their lower housing halves, the entire turbo set except for the outer housing 1 of the low-pressure partial turbines ND supporting table top FR over foundation supports (not shown in detail) is supported on a base plate resting on the housing foundation, as described, for. B.
  • Figures 1 and 3 of the article "Deformation behavior of turbine foundations" (magazine VGB-Krafttechnik 59, Issue 10, Oct. 1979, pp. 819 to 833) show.
  • the turbine bearings each comprise housing bearings, which are generally designated in the figures and in particular in FIGS. 1 and 2 with g6.1, g6.2, etc., and shaft bearings, which with w6.1, w6.2, etc. would be designated.
  • These shaft bearings are from Fig. 1, except for the schematically indicated shaft bearing w6.1, with its thrust or axial bearing 7 and its support bearing 8 not visible; 10 and 11, however, one can see the two shaft bearings w6.2 and w6.3 associated with the first low-pressure sub-turbine ND1 with their supporting or radial bearings 8.
  • a first axis-normal reference plane (yz) 0 is defined by the axial bearing 7 (FIG. 1A), from which the axial shaft expansion and displacement in the direction + x (see the coordinate cross shown) and in the direction -x take their output. It is essential for the axial bearing 7 that defines the first axis-normal reference plane that, viewed in the axial direction + x, it is located upstream of the low-pressure part-turbine ND1 and that, even if a medium-pressure part-turbine MD belongs to the turbo set, this part-turbine is also preferably located axially in front. as shown.
  • this axial bearing 7 preferably defines an axial fixed point for the shaft expansion, from which the expansion of the shaft begins when it is heated in the + x and - + direction.
  • the two shaft bundles formed by a shaft constriction lie against fixed thrust block blocks, the blocks of which are individually tiltable, which results in simpler, more manageable ratios of the axial play and the axial shaft expansion for the assembly and operation of the turbo set (not shown in detail).
  • the overall arrangement is first of all based on the perspective, phantom-like overall illustration according to FIG. 15 tion of the turbo set explained. From this one can see the table top FR and the individual partial turbines HD, MD, ND1, MD2 and also coaxially with the outline of the turbogenerator TG coupled to the shaft train with an upstream main exciter machine HE.
  • the high-pressure turbine section HD has two live steam inlet ports hd5, which are diametrically opposed to one another in an axis-transverse plane.
  • valve combinations V1 and V2 are connected to the live steam nozzle hd1 in a symmetrical arrangement, each valve combination consisting of a quick-closing valve V11 or V21 and a control valve V12 or V22 which is perpendicular to it with its valve axis.
  • the high-pressure partial turbine HD is designed in a pot-type construction with the actual housing pot hd1 and the cover hd2, which is tightly clamped with this, as well as the evaporation nozzle hd3 (the evaporation line is not shown in FIG. 1, but from fig. 15 recognizable and labeled there with hd4).
  • FIG. 15 also shows the two valve combinations V3 and V4, each consisting of an interception - quick-closing valve V31 or V41 and an interception control valve V32 or V42, the valve axes of the quick-closing and control valve again being perpendicular to each other.
  • V3 and V4 each consisting of an interception - quick-closing valve V31 or V41 and an interception control valve V32 or V42, the valve axes of the quick-closing and control valve again being perpendicular to each other.
  • the housing divided in the horizontal axis plane is designated by md, its upper housing part by) mdl, its lower part by md2, the tightly clamped housing flanges of upper and Lower part with 9.1 and 9.2, the live steam inlet connection for the central inflow of this double-flow partial turbine with md3 (the latter are each assigned to an upper and lower housing part and are diametrically opposed to each other) opposite), connecting piece for the connection of tapping lines with md4, which are assigned in pairs to the upper or lower part mdl or md2.
  • the outer casing nd of the low-pressure partial turbines is divided in the horizontal axis plane xz into a hood-shaped upper part ndl, the cross-section of which has the shape of a circular segment, and into a box-shaped lower part nd2, which is designed as a frame construction, the upper and lower part having essentially rectangular part-joint flanges 11.1, 11.2 being vacuum-tight are tied together.
  • Upper and lower parts nd1, nd2 are drawn conically inward in the area of the two bushings of the shaft train W, so that there is space for shaft seal arrangements 12, cf. Fig. 11 and Fig. 12, wherein the tapered portions are designated 13.
  • the outer casing nd of the low-pressure partial turbines is connected at a lower rectangular flange to the exhaust pipe part nd3, the latter in turn being connected to the steam condenser C, the latter, as is the case Force arrows a1 make clear that the building foundation F rests.
  • the table top FR (Fig. 16) is thus relieved of the weight of the outer casing nd of the low-pressure partial turbines ND1, ND2.
  • the axial expansion and displacement for the housing hd of the high-pressure sub-turbine HD supported in the region of the housing bearing g6.1 takes its output from the axis-normal reference plane (yx) 11 , and the left end in FIGS. 1A and 2A of the housing hd of the high-pressure sub-turbine HD can expand axially in the direction -x within the housing bearing g6.4, see FIG. 7.
  • the two axis-normal reference planes of the second type namely (yx) 11 and (yz) 12 , to form a common second axis-normal reference plane (yx) 1 , as illustrated in FIGS.
  • this housing and shaft bearing principle has the advantage that the shaft and housing displacement takes place over practically the same axial extension length and in the same direction + x or -x while achieving minimal axial play between adjacent rotor and guide vane rings.
  • the latter can be seen from FIG. 11 and there are designated 17 (rotor blade ring) and 18 (guide blade ring) by way of example for the last blading stage.
  • the axial play between these two blade rings is denoted by lä x 1 .
  • the described thrust transmission is now placed in the area of thrust-transmitting turbine bearings g6.2 and g6.3 by means of the coupling rods 14 (see in particular FIGS. 3, 4, 8 and 9).
  • the vacuum-tight implementation of the coupling rods 14 is structurally combined with a horizontally heat-moveable claw bearing of the inner housing 2 of the low-pressure partial turbines ND1 and ND2 on claw arms 19, cf. see also Fig. 2B and Fig. 10.
  • the claw arms 19 of the inner housing 2 extend in the direction parallel to the shaft, that is parallel to the direction x, and with slidable support and guide surfaces 19.1, 19.2 on the corresponding counter surfaces 20.1, 20.2 are stored and guided by fixed supports of the associated bearing housing 21.
  • the coupling rods 14 are non-positively coupled with the claw arms 19, see coupling points 23.
  • the generally with 24 be signed bushings through the relevant end walls 15 of the outer housing nd on the one hand for the non-positive connection coupling rod 14 - claw arm 19 and on the other hand for the bearing engagement of the claw arm 19 on the support and guide surfaces 20.1, 20.2 of the fixed supports is in a common, .mit the evaporation chamber 2.0 (cf. FIGS. 10 and 11) of the low-pressure sub-turbine ND1 or ND2, communicating vacuum chamber, which is sealed off from the outside by means of the membrane seals 16, cf. 4 and 8 in particular.
  • the membrane seal 16 is designed as an expansion bellows with a double wall 16.1 (outer wall) and 16.2 (inner wall) which is flexible in the axial direction x and is also flexible in the normal axis direction (any direction in the yx plane).
  • the inner wall 16.2 is formed with two expansion folds 25, one at each end of the inner wall 16.2.
  • the outer wall 16.1 can be more rigid and is therefore designed with a somewhat thicker wall.
  • the outer and inner walls 16.1, 16.2 of the sealing membrane 16 are each provided with an annular flange 26.1, 26.2.
  • the sealing membrane 16 With the outer ring flange 26.1, the sealing membrane 16 is screwed onto an end face 15.1 of the outer housing end wall 15, on the inside thereof, in a vacuum-tight manner, and with the inner ring flange 26.2, the sealing membrane 16 is attached to an annular shoulder 27 of the axially projecting support arm 21.1 of the bearing housing. Bracket 21 screwed tight vacuum-tight. Two pairs of ring seats, namely 26.1-15.1 and 26.2-27, are formed, the clamping screws of which are designated by 28.
  • the sealing can take place by means of a metal-rich system or by means of intermediate sealing layers between the ring seats pressed against one another (not specified in more detail); these intermediate layers can consist of plastically deformable metal, klingerite or an aging and temperature-resistant plastic.
  • the external pressure is exerted on the outer parts of the sealing membrane wall 16.1, 16.2, while its interior 2.01 communicates with the vacuum or evaporation space 2.0 of the associated low-pressure partial turbine.
  • the other subspaces that communicate with this space 2.0 include the coupling channel 2.02, through which the coupling rod 14 is guided, and the turnbuckle chamber 2.03, which will be explained further below (FIG. 4).
  • the inner casing 2 of the low-pressure partial turbines ND is axially divided, namely in the axial parting line 29, which coincides with the horizontal axis plane xz of the turboset.
  • the upper part is 2.1, the lower part 2.2.
  • the latter has at its two ends two claw arms 19 protruding symmetrically on both sides of the vertical axis plane xy and protruding in the direction parallel to the shaft, which have already been mentioned, which are in the area or just below the axial parting line 29 and thus in or near the area of the largest inner housing Diameter D 2 are arranged.
  • FIG. 4 show in side view and Fig. 10 in plan view that from the brackets 21.0 of the bearing housing 21 support arms 21.1, in pairs - symmetrically on each end face of the bearing housing 21 - in alignment with the claw arms 19, these each extend through the outer housing end wall 15 through and on the upper and lower sliding support and guide surfaces 20.1, 20.2, which are arranged on the support lugs 20 of the support arms 21.1, from the claw arm ends with through mouth-shaped recesses 19.3 ge formed projections 30.1 (upper projection) and 30.2 (lower projection) over and under.
  • the upper projection 30.1 has on its underside the support and guide surfaces 20.1 already mentioned, the lower projection 30.2 on its upper side the support and guide surfaces 19.2.
  • the lower projection 30.2 is designed as an angled insert, which is fitted into a corresponding angular recess 19.4 on the underside of the support arm 19 and is screwed into it by means of bolts 31, in particular expansion screws. Since the lower projection 30.2 of the support arm 19 has no support function, but only a guide function, this is permissible and useful.
  • the supporting and guiding surfaces also generally include adjusting and sliding inserts, designated by 32, which are inserted between the upper side of the supporting projection 20 and the lower side 19.1 of the upper projection 30.1 or between the upper side of the lower projection 30.2 of the supporting arm 19 and the lower side of the shoulder 20 are inserted.
  • This sliding fit between the support lugs 20 of the support arms 21.1 and the projections 30.1, 30.2 of the claw arms 19 allows the inner housing 2 to be guided on the support arms 21.1 in a horizontally and thermally movable manner, ie a sliding movement in the axial direction x and in a plane that is plane-parallel to the horizontal axis plane xz runs when the inner housing 2 expands radially-centrically in a heat-mobile manner due to the heating or shrinks accordingly when it cools down.
  • the coupling rods 14 penetrate the brackets 21.0 and their support arms 21.1 axially parallel to and above the alignment of the support lugs 20 of the turbine bearing 6.2 or 6.3 in question in the coupling channels 2.02 already mentioned and that the respective claw arm end, ie; its projection 30.1 above the mouth-shaped recess 19.3 with the ends of the coupling rod 14 is non-positively coupled.
  • a favorable design is that the coupling rods 14 are screwed with a threaded end 14.1 into a threaded blind hole 30.2 of the projection 30.1 of the claw arms 19, which threaded blind hole 30.2, as can be seen, above the mouth-shaped recess 19.3 in the as Anchor projection serving projection 30.1 is embedded.
  • the design of the coupling rod shown in Fig. 8 has a reinforced head for the threaded end 14.1, this head is fluted to the side of the shaft of the coupling rod 14, so that a thread of the same strength, the external threads of which bear largely evenly, is achieved . 3 and 4, on the other hand, a simpler design of the coupling rod 14 is shown, the shaft of which there is even slightly larger in diameter than its head 14.1.
  • Fig. 9 shows that the support arms 19 have a circular basic cross-section and that adapted to this, the support projection 20 forms part of a circular cross-section, namely a circular cross-sectional zone.
  • the support arm 21.1 itself then also has a circular basic cross section; with this circular basic cross section, it is guided through the center of the essentially hollow cylindrical membrane seal 16.
  • the basic cross section of the claw arm 19 within the vacuum space 2.0 could also be elliptical (although the circular shape is more favorable for machining on lathes); it is essential that the circular or elliptical outer contour provides a low flow resistance with respect to the steam flow prevailing in the vacuum space 2.0.
  • Fig. 4 and - partially - Fig. 3 show that the coupling rods 14 can be changed in length by turnbuckles 33 and the clutch channel 2.02 in an accessible area of the bearing housing brackets 21.0 is extended to the turnbuckle chamber 2.03, which the latter can be closed vacuum-tight by a sealing cover 33.1.
  • the turnbuckle body 33.0 has a substantially hollow cylindrical shape, it has a thread 33.2 at both ends thereof, one of which is a left-hand thread and the other a right-hand thread.
  • radial bores 33.3 are arranged in a cross shape, which are used for attaching the clamping tool (e.g. insertion pins).
  • the turnbuckle 33 By turning the turnbuckle body 33.0 in one direction of rotation, the turnbuckle 33 can be loosened, tightened by turning in the other direction, so that the axial length of the coupling rod assemblies consisting of the individual coupling rod parts can be changed and adapted to the mounting position of the individual part turbines.
  • the once adjusted coupling rod length is then 34-fixed by the lock nuts. 2B shows the accessibility to the turnbuckle 33 from above.
  • the first axis-normal reference plane (yz) is 0 and the second axis-normal reference plane (yz) 1 placed in the turbine bearing 6.1 between the high-pressure and medium-pressure sub-turbines HD or MD.
  • high-pressure and medium-pressure partial turbines HD, MD with their pairs of claws P 12 and P 21 are attached to this reference bearing 6.1 or to the corresponding housing bearing g6.1 in the area of their horizontal axis planes 35.0 (partial turbine HD) and 9.0 ( Partial turbine MD) axially fixed, but horizontally and radially-centrically heat-moveable
  • the horizontal axis planes 35.0 and 9.0 coincide with the entire horizontal axis plane xz of the turbo set.
  • the support claws each have a block-shaped, step-shaped extension 36 and an adjoining recess 37, which is stepped upwards.
  • the bearing housing 21 is provided with a recess 38 for receiving the extension 36 and with a recess 38 on its strong top-side support flange 21b axially adjacent step-shaped edge elevation 39 for engagement in the recess 37 of the claw P.
  • sliding and adjusting inserts are inserted, which fill the resulting vertical gaps and are labeled 40a and which fill the emerging or remaining axial gaps and are labeled 40b.
  • 21c are end walls of the bearing housing pointing in the x direction, which are welded between the cover-side support flange 21b and the anchor plate 21a, 21d is the side wall facing the observer.
  • 42 is a securing bolt which is arranged in pairs per housing bearing g6.1 on both sides of the vertical axis plane and serves to secure the support brackets P 12 ' P 21 of the turbine parts against lifting forces and moments, and which is provided with strong anchor bolts 43, designed as expansion screws, is attached to the support flanges 21b.
  • High-pressure and medium-pressure partial turbines HD, MD are equipped at their ends facing away from the reference bearing 6.1 with pairs of support brackets P 11 P 11 and P 22 -P 22 (here, too, only one support bracket of the pairs of support brackets can be seen) each axially and radially Centrally and movably supported on the associated turbine bearings 6.4, 6.2 or housing bearings g6.4, g6.2.
  • the support brackets P 11 , P 22 are provided with step-shaped projections 36 and recesses 37, and the support flanges 21b are provided with depressions 38 and raised edges 39; only it is the case that the depressions 38 are larger or wider, so that axially gap spaces 44 remain free for free axial movement of the step-shaped projections 36 of the claws, which is why the end faces of the edge elevations 39 pointing in the direction + x and in the direction -x are not provided with corresponding wedges or adjustment inserts 40b; only the adjustment inserts 40a required for the height alignment are inserted.
  • the safety latches which absorb the lifting forces and moments of the P 111 P 22 claws, are designated here by 42.1. Their axial extent is smaller than that of the locking latch 42 because the latter are used for a double housing bearing.
  • the axially guided sliding and sliding movement of the housing end of the partial turbine MD pointing in the direction x is transmitted, as shown in FIG. 3, through the first of the coupling rods 14 and a turnbuckle 33 to the inner housing 2 of the axially adjacent partial turbine ND1.
  • the partial turbine MD ie its housing md, is provided with a pair of anchoring points, of which the one anchoring point 45 according to FIG. 3 can also be seen from FIG. 2A.
  • the partial turbine MD with two evaporation nozzles md5 that go out laterally below the horizontal axis plane 9.0 of its housing and md5 if the anchoring points 45 are arranged on extensions 46 of the exhaust steam nozzle md5, which extensions are aligned to the coupling rods 14 and claw arms 19 of the inner casing 2 of the adjacent low-pressure turbine section ND1 and extend symmetrically on both sides of the vertical axis plane xy.
  • the coupling channel 2.02 of the coupling rods 14 is sealed towards the side of the medium-pressure turbine MD by a sealing sleeve 47, which evidently surrounds the end 14.2 of the coupling rod 14 protruding from the coupling channel 2.02 and at one end with the opening edge 48 of the coupling channel 2.02 and at their other end with an annular collar 49 surrounding the anchoring point 45 on the extension 46 is connected in a vacuum-tight manner.
  • FIGS. 2A and 2B generally refer to so-called center guides for the housings hd, md and nd of the individual sub-turbines in FIGS. 2A and 2B, which have the task of keeping the individual sub-turbine housings in axial alignment with one another and coaxial with the shaft axis x and for guiding them during thermal movement.
  • the center guides for the housings hd and md as well as for the outer housings nd of the low-pressure partial turbines ND1, ND2 will not be discussed in more detail;
  • the center guide is described in more detail in the aforementioned application P (VPA 85 P 6063) dated 6.1985 by the same applicant.
  • FIGS. 11 and 12 the inner casing 2 of the low-pressure partial turbine ND1 at its two ends and in its lower region where the outflow cross sections 3/1 and 3/11 of the diffusers 1.1 and 1.2 open downwards (this region lies at the same time in the area of the vertical axis plane xy), axial guide bolts 51 connected to the supporting grid construction 2.3 of the inner housing 2 are provided, which (see the section according to FIG.
  • the basic cross-section of the guide pin in the area of the outlet diffuser 1.2 is circular.
  • the circular shape is achieved in the area of the guide spur 53.1 by a cover segment 55 in the form of a segment of a circle, which is only put on after the lower housing part 2.2 has been inserted, that is to say when the fork-like projections 51.2 surround the guide spur 53.1.
  • This cross-sectional shape is aerodynamically favorable and, given the large outlet cross sections available, means that no additional outlet losses can be determined.
  • Fig. 11 and Fig. 12 show that the respective guide rod 53 penetrates the outer housing, ie an end wall 15 of the same, in the lower region of the diffuser outer wall 13 with play 56 in a cylindrical opening 57 delimited by the cylinder wall 57.1, the through the play 56 formed annular space serves as a receiving space for a further sealing membrane 58, which concentrically surrounds the guide rod 53 and is connected on the one hand to the outer housing nd and on the other hand to the guide rod 53 in a vacuum-tight manner.
  • annular seat surface 60 is arranged on an end face of the bushing cylinder wall 57.1, which is welded to the inner circumference of the recess delimiting the opening 57 in the outer housing end wall 15 in general and the diffuser wall 13 in particular.
  • the guide rod 53 is cast by means of in-situ concrete 61 and a corresponding wall pipe 62 in the foundation bolt for or another suitable foundation part and is thereby clearly fixed; the guide pin 51 is screwed to the lattice structure of the inner housing 2 by expansion screws, the axes of which are indicated at 63.
  • corresponding flat mating surfaces 64 are provided between the guide bolt 51 and the lattice structure of the inner housing 2. 11 to 13, the guide rod 53 protrudes through the outer housing end wall 15 into the vacuum space, which is favorable for assembly and adjustment on the one hand and on the other hand eliminates the risk of contamination from dust particles from the outside.
  • FIG. 5 shows a coupling rod-free mounting of the claw arms 19 of an inner housing 2 which leads to the turbine bearing 6.5 or the housing bearing g6.5 (FIG. 2B) belongs. Since no other low-pressure sub-turbine axially adjoins the sub-turbine ND2 in the exemplary embodiment shown, the need for thrust transmission is also eliminated; rather, the axially and horizontally heat-moveable mounting of the claw arms 19 on the corresponding lugs 20 of the support arms 21.1 is sufficient.
  • the leadthrough is sealed with a sealing membrane 65 (of the third type), which is of the same design as the sealing membranes of the first and second types 16 and 58.
  • the inner ring flange 65.1 is again vacuum-tight on a ring seat surface 66 of the support arm 21.1 by means of suitable, not fixed flange screws, the outer ring flange 65.2 in a corresponding manner on an annular seat 660 on the inner end face of a passage through the outer housing end wall 15 limiting cylinder wall 67, which, as with the other bushings of the support arms and guide rods, sealing with the inner circumference the corresponding end wall parts are welded.
  • the claw arms 19 of the inner housing 2 are screwed to their supporting grid construction at several screwing points 68 and with corresponding mutual wing engagement (see FIGS. 8 and 10).
  • a welded connection is also possible here, as is the case with the fastening of the guide bolts 51 to the inner housing 2 according to FIG. 12. From FIG. 10 one can see on the left a somewhat modified sealing sleeve 47 for the coupling rod 14 with regard to position and design, which in this case since there is good accessibility from the outside - could be combined with the turnbuckle 33.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP86108225A 1985-06-27 1986-06-16 Moyen de connexion entre les carters d'un groupe de turbines Expired EP0213297B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19853522916 DE3522916A1 (de) 1985-06-27 1985-06-27 Turbosatz mit wenigstens einer, ein aussengehaeuse und ein dazu koaxiales innengehaeuse aufweisenden niederdruck-teilturbine und mit hochdruck- und/oder mitteldruck-teilturbine
DE3522916 1985-06-27

Publications (2)

Publication Number Publication Date
EP0213297A1 true EP0213297A1 (fr) 1987-03-11
EP0213297B1 EP0213297B1 (fr) 1989-03-15

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EP86108225A Expired EP0213297B1 (fr) 1985-06-27 1986-06-16 Moyen de connexion entre les carters d'un groupe de turbines

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Country Link
US (1) US4744726A (fr)
EP (1) EP0213297B1 (fr)
JP (1) JPS623106A (fr)
DE (3) DE8518569U1 (fr)
ES (1) ES2000180A6 (fr)
IN (1) IN165207B (fr)

Cited By (1)

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US5490386A (en) * 1991-09-06 1996-02-13 Siemens Aktiengesellschaft Method for cooling a low pressure steam turbine operating in the ventilation mode

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DE3742814C2 (de) * 1987-12-17 1996-07-04 Bbc Brown Boveri & Cie Mehrgehäusige Dampfturbine
JPH0742828B2 (ja) * 1989-04-04 1995-05-10 日本板硝子株式会社 複層ガラスのシール構造
US4961310A (en) * 1989-07-03 1990-10-09 General Electric Company Single shaft combined cycle turbine
DE59007880D1 (de) * 1990-12-10 1995-01-12 Asea Brown Boveri Lagerung einer thermischen Turbomaschine.
JPH0591520U (ja) * 1992-05-08 1993-12-14 川嶋工業株式会社 皮引きの刃カバー
DE19629933C1 (de) 1996-07-24 1997-09-04 Siemens Ag Turbinenanlage mit Schubelement sowie Schubelement
US6092986A (en) * 1996-07-24 2000-07-25 Siemens Aktiengesellschaft Turbine plant having a thrust element, and thrust element
EP0952311A1 (fr) 1998-04-06 1999-10-27 Siemens Aktiengesellschaft Turbomachine avec un carter interieur et un carter extérieur
JP3772019B2 (ja) 1998-04-21 2006-05-10 株式会社東芝 蒸気タービン
JP3774321B2 (ja) * 1998-04-24 2006-05-10 株式会社東芝 蒸気タービン
EP1249579A1 (fr) 2001-04-11 2002-10-16 Siemens Aktiengesellschaft Turbine à vapeur
EP1806481B1 (fr) 2006-01-09 2013-12-18 Siemens Aktiengesellschaft Turbine à vapeur ayant des éléments de guidage
JP4991600B2 (ja) * 2008-02-29 2012-08-01 株式会社東芝 蒸気タービン
JP5180652B2 (ja) * 2008-03-31 2013-04-10 三菱重工業株式会社 蒸気タービンの車室構造
US8337151B2 (en) * 2009-06-30 2012-12-25 General Electric Company System and method for aligning turbine components
US20110088379A1 (en) * 2009-10-15 2011-04-21 General Electric Company Exhaust gas diffuser
US8403628B2 (en) 2009-12-16 2013-03-26 General Electric Company Low-pressure steam turbine hood and inner casing supported on curb foundation
US9249687B2 (en) 2010-10-27 2016-02-02 General Electric Company Turbine exhaust diffusion system and method
JP2014514481A (ja) 2011-03-01 2014-06-19 アルストム テクノロジー リミテッド コンバインドサイクル発電プラント
EP2546459A1 (fr) * 2011-07-14 2013-01-16 Siemens Aktiengesellschaft Train de rotor de système de turbines
EP2554801A1 (fr) * 2011-08-02 2013-02-06 Siemens Aktiengesellschaft Système de turbine comprenant un agencement de tige de poussée entre deux carters
DE102012202466B3 (de) * 2012-02-17 2013-07-11 Siemens Aktiengesellschaft Montage einer Strömungsmaschine

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DE520625C (de) * 1928-12-29 1931-03-12 Bbc Brown Boveri & Cie Mehrgehaeuseturbine
FR1332074A (fr) * 1963-12-16
CH385893A (de) * 1959-08-13 1964-12-31 Licentia Gmbh Einrichtung zur Abstützung der beiden Gehäuse von Doppelmantelturbinen
DE1216322B (de) * 1962-05-30 1966-05-12 Creusot Forges Ateliers Dampf- oder Gasturbine mit mehreren, koaxial hintereinander angeordneten Teilturbinen
GB1145612A (en) * 1966-04-12 1969-03-19 Licentia Gmbh Improvements relating to steam turbines
CH502514A (de) * 1969-05-21 1971-01-31 Maschf Augsburg Nuernberg Ag Doppelgehäuse für Dampfturbinen grosser Leistung
DE2200447A1 (de) * 1971-01-13 1972-12-07 Creusot Loire Niederdruck-Teilturbinen von Dampfturbinen
DE3130376A1 (de) * 1981-07-31 1983-02-10 Kraftwerk Union AG, 4330 Mülheim Doppelschaliges dampfturbinengehaeuse

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CH552130A (de) * 1972-11-28 1974-07-31 Bbc Brown Boveri & Cie Turbinengehaeuse.
FR2297999A1 (fr) * 1975-01-16 1976-08-13 Europ Turb Vapeur Fixation d'une piece de guidage d'une enveloppe de machine tournante
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Publication number Priority date Publication date Assignee Title
FR1332074A (fr) * 1963-12-16
DE520625C (de) * 1928-12-29 1931-03-12 Bbc Brown Boveri & Cie Mehrgehaeuseturbine
CH385893A (de) * 1959-08-13 1964-12-31 Licentia Gmbh Einrichtung zur Abstützung der beiden Gehäuse von Doppelmantelturbinen
DE1216322B (de) * 1962-05-30 1966-05-12 Creusot Forges Ateliers Dampf- oder Gasturbine mit mehreren, koaxial hintereinander angeordneten Teilturbinen
GB1145612A (en) * 1966-04-12 1969-03-19 Licentia Gmbh Improvements relating to steam turbines
CH502514A (de) * 1969-05-21 1971-01-31 Maschf Augsburg Nuernberg Ag Doppelgehäuse für Dampfturbinen grosser Leistung
DE2200447A1 (de) * 1971-01-13 1972-12-07 Creusot Loire Niederdruck-Teilturbinen von Dampfturbinen
DE3130376A1 (de) * 1981-07-31 1983-02-10 Kraftwerk Union AG, 4330 Mülheim Doppelschaliges dampfturbinengehaeuse

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5490386A (en) * 1991-09-06 1996-02-13 Siemens Aktiengesellschaft Method for cooling a low pressure steam turbine operating in the ventilation mode

Also Published As

Publication number Publication date
ES2000180A6 (es) 1988-01-01
DE8518569U1 (de) 1988-07-14
JPS623106A (ja) 1987-01-09
US4744726A (en) 1988-05-17
IN165207B (fr) 1989-08-26
DE3662424D1 (en) 1989-04-20
EP0213297B1 (fr) 1989-03-15
DE3522916A1 (de) 1987-01-08

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