EP0566478B2 - Hochdruckdampfturbinengehäuse - Google Patents

Hochdruckdampfturbinengehäuse Download PDF

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Publication number
EP0566478B2
EP0566478B2 EP93400960A EP93400960A EP0566478B2 EP 0566478 B2 EP0566478 B2 EP 0566478B2 EP 93400960 A EP93400960 A EP 93400960A EP 93400960 A EP93400960 A EP 93400960A EP 0566478 B2 EP0566478 B2 EP 0566478B2
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EP
European Patent Office
Prior art keywords
rotor
anterior
high pressure
posterior
pressure module
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 - Lifetime
Application number
EP93400960A
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English (en)
French (fr)
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EP0566478B1 (de
EP0566478A1 (de
Inventor
Jean-Pierre Gros
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Alstom SA
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GEC Alsthom Electromecanique SA
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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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • 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
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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

Definitions

  • the present invention relates to improvements high pressure turbine modules comprising an intake for very high characteristics steam, a steam exhaust, a rotor supporting movable wheels consisting of movable fins and stator parts comprising an external body and an internal body supporting fixed stages arranged between the movable wheels, the internal body being provided with the inlet side of a seal holder ensuring sealing inlet steam (see for example FR-A-1 320 174).
  • High pressure stator parts of turbines in addition to the two envelopes constituted by the internal body and the external body a third intake envelope when pressures and the temperatures are very high.
  • the internal and external bodies are in two parts and have flanges in the plane of horizontal joint to allow bolting.
  • the rotor is provided with discs supporting the fins which results in an increase large transverse dimensions of the finned rotor and therefore stator parts.
  • the turbine module according to the invention of simplified design and whose dimensions have been reduced while ensuring good mechanical behavior and thermal includes an inlet for very high steam features, steam exhaust, rotor supporting wheels movable consisting of movable fins, and stator parts comprising a external body and an internal body supporting fixed parts (diaphragms and fixed guide vanes) constituting with the movable wheels of the stages, the body internal being provided on the intake side with a seal carrier surrounding the rotor and independent of the internal body, i.e.
  • the internal body comprises two bodies, the anterior body is disposed on the inlet side in an anterior area and produced as a single piece and the rear body of which is arranged on the side of the exhaust in a posterior zone of the high pressure module and produced in two parts comprising an upper half-body and a lower half-body united in a diametral joint plane, that the anterior zone comprises a plurality of stages, each stage of which has a diaphragm in the form of monobloc crown or a pair of half-crowns, as the posterior body has a front face located on the border between the areas against which comes lean all of the crowns of the anterior area, as the front of the posterior body is extended by a circular rim which is housed in a groove in the periphery of the anterior body, thus coupling together said two bodies, that the one-piece front body surrounds part of the rotor, and that at least the part of the rotor surrounded by the front body is a rotor drum with
  • the anterior part in which the temperature and the vapor pressure are very high has a inner casing and a seal holder to isotropic admission therefore without bolting.
  • the use of a drum rotor (therefore without discs) inside the anterior internal body reduces the radial dimension of the vein and correlatively that of the envelopes. Furthermore this reduction of the radial dimension of the vein is favorable with the efficiency in particular for the turbines with action.
  • the body no longer comprises on admission that two envelopes, an outer body and an inner body.
  • the grooves of the drum rotor located in the area of the anterior internal body are longitudinal and the wheels mobile are separated by spacers of the same shape that the feet of the fins slipped in the grooves longitudinal and facing the fixed floors which are made up of monoblock diaphragms.
  • This rotor part can also be a drum rotor with circumferential grooves which brings the indicated advantages of the drum rotor.
  • a drum rotor HP module is described in the French patent application No. FR-9104855 in the name of applicant.
  • the posterior internal body for reasons of simplification is in two parts which can either be bolted either fretted.
  • Figure 1 shows a longitudinal half-section of a conventional action turbine HP module.
  • Figure 2 shows in radial half-section the module of figure 1.
  • Figure 3 shows in longitudinal half-section a first embodiment of the turbine module according to the invention.
  • Figure 4 shows a longitudinal section of a variant of FIG. 3.
  • Figure 5 shows a radial section of the figure 4.
  • FIG. 6 represents a second embodiment of the turbine module according to the invention.
  • Figure 7 shows a section of a moving wheel of the module in Figure 6.
  • Figure 8 shows a section through a diaphragm of the module in Figure 6.
  • Figure 9 shows the circumferential arrangement fins.
  • Figures 10, 12, 14 show the three stages of the assembly of the module of figure 3.
  • Figures 11, 13, 15 show the three stages of the assembly of the module of figure 6.
  • FIG. 16 represents a third embodiment of the turbine module according to the invention.
  • Figure 17 is a detailed view of the front in Figure 3.
  • Figure 18 is a detailed view of the front in Figure 6.
  • Figure 19 is a variant of the posterior part of the rotor of Figures 3 and 6.
  • Figure 20 shows the air conditioning of the modules Figures 3 and 6.
  • the conventional action turbine module HP (figure 1) comprises a rotor 1 provided with discs 2 supporting movable fins 3 constituting movable wheels 4 and stator parts 5.
  • Stator parts 5 have an external body 6 in two bolted parts in the horizontal joint plane and an internal body 7 supported by the external body 6 which is also in two parts bolted in the joint plane.
  • diaphragms 8 also in two parts including guide vanes fixed 9 of the vein 10.
  • Each diaphragm 8 constitutes the fixed part of a stage 40 with the movable wheel 4 which follows him.
  • the diaphragms 8 produced in two parts for allow their mounting are the seat of constraints and different deformations depending on the azimuth considered. They must be axially oversized especially for the first floors so as to take into counts this cut at the horizontal joint.
  • the module has intake pipes 11 opening into an internal envelope 12 inside of the internal body used for the distribution of steam in the vein 10 which ends in the exhaust 13.
  • This envelope 12 can be produced in different ways. It can be made in two closed parts to the joint and assembled by bolting or it can be made up of several injection nozzle holders steam fixed to the internal body 7.
  • a packing holder 14 On the internal body 7 around the rotor 1 intake side is mounted at free expansion, a packing holder 14 made in two parts and bolted. It has fittings 15 ensuring the seal between the internal body 7 and rotor 1 on the intake side.
  • the rotor 1 of the module is a drum rotor, that is to say without discs. It has circumferential grooves 16 in which the feet 17 of the movable fins 3. Such a rotor is described in the application FR-A-9104855 in the name of the applicant.
  • the external body 6 of the stator parts 5 of the module is of classical construction and has two bolted parts.
  • the internal body 7 of the stator parts is separated in two bodies coupled a front body 18 on the side admission arranged in the anterior zone (zone A) and a rear body 19 on the side of the exhaust 13 in the posterior zone (zone P).
  • the front body 18 is in one piece, that is to say without radial cut so perfectly isotropic. he comprises two half-crowns 20 provided with grooves 21 in which guide vanes are inserted 9 individually, each set of guide vanes 9 with the movable wheel 4 which follows it constitutes a stage 40.
  • the front body 18 surrounds a packing holder 14 mounted at free expansion which comprises an external tube 22 'monobloc that is to say without radial cut therefore perfectly isotropic which comes to hoop two half-crowns 22 in which seals are mounted retractable 15 each making a half-circumference. There can of course be more than one trim 15 serial. These linings 15 seal with rotor shaft 1.
  • the packing holder 14 with free expansion does not has more than half crowns and is completely piece.
  • the posterior body 19 is made in two parts and coupled to the anterior body 18. It is isotropic and shrunk by frets 39. In this design the hooping is total and easy to carry out since the posterior internal body is fully cylindrical and does not have the steam admissions.
  • the parts vein fixed 10 are guide vanes 9 mounted full hole to the unit at the cut of the horizontal joint in the grooves 23 of the internal body.
  • This rear body 19 has a front face 24 located on the border between zones A and P against which all the half-crowns 20 of zone A comes lean.
  • the front face 24 is extended by a circular rim 25, which is housed in a groove 26 formed in the periphery of the anterior body 18, thus coupling the two bodies 18, 19 together.
  • the half-crowns 20 (fig. 17) have for each stage 40 a sealing segment 41 to prevent or slow the steam flow in the annular space between the crown 20 and the anterior body. This possible leak is immediately recovered upstairs following by holes 42 so as to be sure to have the temperature of the top floor of zone A on the face before 24.
  • zone A has too many floors 40 important (see figures 4 and 5), it is planned to introduce a intermediate support 27 produced by a crown 28 comprising several sectors which are pushed from the outside from the anterior body 18 towards the inside thereof the sectors then being astride a circumferential groove 29 formed inside the anterior body 18 and on a groove 30 formed on the outside of the half crowns 20.
  • the area A comprises a drum rotor 1, the grooves 31 of which are longitudinal.
  • the fins 3 are mounted axially on the rotor 1 in the grooves 31; spacers 32 carrying the seals against the diaphragms ensure filling of the groove between the moving wheels 4. This allows mounting of 8 monobloc diaphragms to the continuation of each movable wheel 4 and spacer 32.
  • Figure 7 there is shown a section aa of movable wheel 4 of zone A.
  • the feet 17 of the fins 3 have at the base a development and are exactly complementary to longitudinal grooves 31.
  • the spacers 32 can be separated or joined in packs of three, four or five. These spacers 32 or packets of spacers are in contact with each other above the grooves 31.
  • the spacers 32 carry the seals 36 opposite hubs 37 of diaphragms 8.
  • Each diaphragm 8 in zone A includes for each stage 40 a sealing segment 41 to prevent or slow down the flow of steam into the annular space between the diaphragm 8 and the anterior body 18. This possible leak is immediately recovered on the next floor by grooves 43 so to be sure to have the temperature of the last stage of zone A on the front face 24 (see fig. 18).
  • the posterior body 19 is constituted like that of figure 3 except that instead of being shrunk it is bolted therefore not isotropic.
  • the diaphragms 8 constituting the fixed parts of the vein 10 are made in two parts and mounted at free expansion. This arrangement makes it possible to better conserve the radial rotor / stator clearances when the latter is not isotropic.
  • the movable fins 3 have a foot 17 in the form of T overturned.
  • the foot 17 of the fin 3 is introduced in the circumferential groove 16 in the shape of an inverted T then swivels.
  • shims 38 are introduced having the same section as foot 17 of fins 3 but much thinner (see figure 9).
  • the last shims 38 are cut in two vertically to be able to be inserted and the last in three.
  • Each movable wheel 4 is assembled in its entirety with its self-tightening on rotor 1 by sliding it axially, between the moving wheels 4 the spacers are mounted 32 in the longitudinal grooves 31 and the monoblock diaphragms 8 (see figures 7 and 8).
  • zone P we have chosen a circumferential arrangement fins 3, the grooves 16 of the drum rotor 1 in this area are therefore circumferential.
  • the assembly takes place as indicated above (see figure 9).
  • zone P we can foresee as described two realizations for the fixed parts of the vein 10, according to that the posterior body 19 is bolted or shrunk and the mounting fixed floors will be different as shown below for mounting the stators.
  • zone A the mounting of the internal body 18 and of the packing holder 14 are identical whatever the mounting principle of the fin (axial or circumferential).
  • the fins 4 and the diaphragms 8 or guide vanes 9 of zone A are mounted on rotor 1 as seen previously.
  • the seal holder 22 ' which has an outer tube fretting two half-crowns 22 carrying the linings retractable 15 is threaded and centered on the body internal 18 by keys external to the internal body 18.
  • This set is then threaded onto the rotor on one side admission.
  • the diaphragms 8 (fig. 13) or the crown 20 bearing the guidelines 9 (fig.12) are then centered from the outside of the anterior body 18 by pawns and are thus mounted at free expansion.
  • the lower front half-body 18 comprising its half-diaphragms 8 (fig. 6) or the guide 9 (fig. 3) is in place in the lower external half-body 6.
  • the upper external half-body is then mounted and bolted.
  • zone P As a variant for action steam turbines we can for zone P take a rotor 1 with discs 2 quite classic.
  • This arrangement makes it possible to reduce the number of floors 4, 8 of zone P.
  • the rotor of zone A is a drum rotor with axial or circumferential mounting; on the figure 16 the fins 3 are shown for mounting axial.
  • the posterior body 19 of the zone P can be as for zone P of the modules already described either bolted to be shrunk.
  • the slots 46 are continued by slots 47 passing through the one-piece anterior body 18 and by pipes 48 crossing the interstatoric space and supplying through slots 49 a floor in zone P, we avoid thus the escape of hot steam from the part front of the anterior body and moreover we work the hot steam escaping.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (11)

  1. Turbinen-Hochdruckmodul, der einen Dampfeinlaß (11) mit sehr hohen Charakteristiken, einen Dampfauslaß (13), einen Rotor (1), der bewegliche Räder (4) trägt, die aus beweglichen Schaufeln (3) bestehen, und Statorbereiche (5) aufweist, die einen äußeren Körper (6) und einen inneren Körper (7, 18, 19) aufweisen, die ortsfeste Teile (Blenden 8 und ortsfeste Leitschaufeln 9) tragen, welche mit den beweglichen Rädern (4) Stufen (40) bilden, wobei der innere Körper (7, 18, 19) auf der Einlaßseite (11) mit einem Dichtungsträger (14) versehen ist, der den Rotor (1) umgibt und vom inneren Körper (7, 18, 19) unabhängig ist, das heißt sich frei bezüglich des Körpers ausdehnen kann, dadurch gekennzeichnet, daß der innere Körper (18, 19) zwei Körper aufweist, nämlich einen vorderen Körper (18), der auf der Seite des Einlasses (11) in einer vorderen Zone (A) angeordnet ist und aus einem Stück besteht, während der hintere Körper (19) auf der Seite des Auslasses (13) in einer hinteren Zone (P) des Hochdruckmoduls angeordnet ist und aus zwei Teilen mit einem oberen und einem unteren Halbkörper besteht, die in einer diametralen Ebene miteinander verbunden sind, daß die vordere Zone (A) mehrere Stufen (40) mit je einer Blende (8) in Form eines einstückigen Kranzes oder in Form zweier Halbkränze (20) aufweist, daß der hintere Körper (19) eine Vorderseite (24) an der Grenze zwischen den Zonen (A und P) enthält, an der sich die Gesamtheit der Kränze (20) der vorderen Zone (A) abstützt, daß die Vorderseite (24) des hinteren Körpers (19) sich in einem ringförmigen Kragen (25) verlängert, der in einer Nut (26) an der Peripherie des vorderen Körpers (18) sitzt und so die beiden Körper (18, 19) miteinander verkoppelt, daß der vordere, einstückige Körper (18) einen Teil des Rotors (1) umgibt und daß mindestens der vom vorderen Körper (18) umgebene Teil des Rotos (1) ein Trommelrotor mit Nuten (16, 31) ist, in denen die Füße (17) der Schaufeln (3) befestigt sind.
  2. Turbinen-Hochdruckmodul nach Anspruch 1, dadurch gekennzeichnet, daß die Turbine eine Aktionsturbine ist, daß die Nuten (31) des Trommelrotors (1), die sich in der Zone des vorderen inneren Körpers (18) befinden, in Längsrichtung liegen und daß die beweglichen Räder (4) durch Zwischenstücke (32) gleicher Form wie die Füße (17) der Schaufeln (3) voneinander getrennt werden, die in die Längsnuten (31) eingeschoben sind und vor den festen Stufen liegen, die aus einstückigen Blenden (8) bestehen.
  3. Hochdruckmodul einer Aktionsturbine nach Anspruch 2, dadurch gekennzeichnet, daß jede Blende (8) einer Stufe (40) mit einem Dichtsegment (41) versehen ist, das die Dichtheit zwischen der Blende (8) und dem vorderen Körper (18) bewirkt, und daß die Blende (8) mit einer Nut (43) versehen ist, die die Weiterleitung des Dampfs gewährleistet, der in die folgende Stufe (40) entweichen könnte.
  4. Turbinen-Hochdruckmodul nach Anspruch 1, dadurch gekennzeichnet, daß die Nuten (16) des vom vorderen inneren Körper (18) umgebenen Trommelrotors in Umfangsrichtung verlaufen und daß der vordere innere Körper (18) zwei Paare von Halbkränzen (20) einspannt, in denen unabhängige Leitschaufeln (9) montiert sind, die die ortsfesten Bereiche der Stufen (40) bilden.
  5. Turbinen-Hochdruckmodul nach Anspruch 4, dadurch gekennzeichnet, daß die Halbkränze (20) für jede Stufe (40) mit Dichtsegmenten (41) versehen sind, die die Dichtheit zwischen diesen Halbkränzen (20) und dem vorderen Körper (18) bewirken, und daß die Halbkränze (20) Löcher (42) aufweisen, die die Weiterleitung des Dampfes bewirken, der in die folgende Stufe (40) entweichen könnte.
  6. Turbinen-Hochdruckmodul nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß der vom hinteren inneren Körper (19) umgebene Bereich des Rotors (1) ein Trommelrotor mit Umfangsnuten (16) ist, in denen die Füße (17) der beweglichen Schaufeln (3) angeordnet sind, die die beweglichen Räder (4) bilden.
  7. Turbinen-Hochdruckmodul nach Anspruch 4, dadurch gekennzeichnet, daß das letzte bewegliche Rad (4) des vom hinteren inneren Körper (19) umgebenen Rotors (1) in Längsnuten (31') montiert ist, die im Rotor (1) vorgesehen sind.
  8. Turbinen-Hochdruckmodul nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, daß die Turbine eine Aktionsturbine ist und daß der Teil des Rotors, der sich in der Zone des hinteren inneren Körpers (19) befindet, mit Scheiben (2) versehen ist, auf denen die beweglichen Schaufeln (3) montiert sind, die die beweglichen Räder (4) bilden.
  9. Turbinen-Hochdruckmodul nach einem der Ansprüche 6 bis 8, dadurch gekennzeichnet, daß der hintere innere Körper (19) aus zwei in der Verbindungsebene durch Bolzen verbundenen Teilen besteht, in denen mit freier Ausdehnung Blenden (8) montiert sind, die in zwei Teilen hergestellt sind und die ortsfesten Stufen bilden.
  10. Turbinen-Hochdruckmodul nach einem der Ansprüche 6 und 8, dadurch gekennzeichnet, daß der hintere innere Körper (19) aus zwei aufgeschrumpften Teilen besteht, in die feste Schaufeln (9) eingesteckt sind, die die ortsfesten Stufen bilden.
  11. Turbinen-Hochdruckmodul nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß er Mittel (46, 47) zur Entnahme von Heißdampf-Leckströmen, die aus dem Dichtungsträger (14) entweichen, und Mittel (48, 49) zur Injektion dieses Heißdampfs ins Innere des hinteren Körpers (19) sowie Mittel zur Entnahme relativ kalten Dampfs im Inneren des hinteren Körpers (19) aufweist, um den Dampf in den Zwischenstatorbereich (44) einzuspeisen, der sich zwischen dem vorderen (18) und dem hinteren Körper (19) einerseits und dem äußeren Körper (6) befindet, wobei der kalte Dampf verwendet werden kann, um den Rotor eines anderen Moduls zu kühlen.
EP93400960A 1992-04-17 1993-04-13 Hochdruckdampfturbinengehäuse Expired - Lifetime EP0566478B2 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9204812A FR2690202B1 (fr) 1992-04-17 1992-04-17 Perfectionnements aux modules haute pression de turbine a rotor tambour avec admission de vapeur a tres hautes caracteristiques.
FR9204812 1992-04-17

Publications (3)

Publication Number Publication Date
EP0566478A1 EP0566478A1 (de) 1993-10-20
EP0566478B1 EP0566478B1 (de) 1996-05-08
EP0566478B2 true EP0566478B2 (de) 2002-07-10

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EP93400960A Expired - Lifetime EP0566478B2 (de) 1992-04-17 1993-04-13 Hochdruckdampfturbinengehäuse

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Country Link
US (1) US5350276A (de)
EP (1) EP0566478B2 (de)
JP (1) JP3529145B2 (de)
DE (1) DE69302520T3 (de)
FR (1) FR2690202B1 (de)

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB9210421D0 (en) * 1992-05-15 1992-07-01 Gec Alsthom Ltd Turbine blade assembly
KR100807886B1 (ko) * 2001-09-24 2008-02-27 에스케이 텔레콤주식회사 직교 주파수 분할 다중화 시스템의 수신 장치
JP2004011609A (ja) * 2002-06-11 2004-01-15 Toshiba Corp 蒸気タービン
EP1744017A1 (de) 2005-07-14 2007-01-17 Siemens Aktiengesellschaft Kombinierte Dampfturbine, Dampf- oder Gas- und Dampf- Turbinenanlage, Verfahren zum Betrieb einer kombinierten Dampfturbine
US7497658B2 (en) * 2005-11-11 2009-03-03 General Electric Company Stacked reaction steam turbine stator assembly
EP2101042A1 (de) * 2008-03-10 2009-09-16 Siemens Aktiengesellschaft Dampfturbine mit Schrumpfringen
EP2101044A1 (de) * 2008-03-13 2009-09-16 Siemens Aktiengesellschaft Dampfturbine mit geteiltem Innengehäuse
EP2119878A1 (de) * 2008-05-15 2009-11-18 Siemens Aktiengesellschaft Dampfturbine mit geteiltem Innengehäuse
US8167566B2 (en) * 2008-12-31 2012-05-01 General Electric Company Rotor dovetail hook-to-hook fit
TWI396261B (zh) * 2009-11-11 2013-05-11 Inotera Memories Inc 堆疊式隨機動態存取記憶體之低寄生電容位元線之製造方法
EP2423454A1 (de) * 2010-08-25 2012-02-29 Siemens Aktiengesellschaft Gehäuse für Strömungsmaschine sowie Verfahren zur Herstellung
US20120067054A1 (en) * 2010-09-21 2012-03-22 Palmer Labs, Llc High efficiency power production methods, assemblies, and systems
US20120189460A1 (en) * 2011-01-21 2012-07-26 General Electric Company Welded Rotor, a Steam Turbine having a Welded Rotor and a Method for Producing a Welded Rotor
FR2975124B1 (fr) * 2011-05-09 2013-05-24 Snecma Virole annulaire de moteur d'aeronef comportant une fenetre d'introduction d'aubes
US8834114B2 (en) * 2011-09-29 2014-09-16 General Electric Company Turbine drum rotor retrofit
CN102562187B (zh) * 2011-12-21 2014-08-06 上海发电设备成套设计研究院 一种空冷式高参数汽轮机的高中压合体缸
US8926273B2 (en) 2012-01-31 2015-01-06 General Electric Company Steam turbine with single shell casing, drum rotor, and individual nozzle rings
US9359913B2 (en) * 2013-02-27 2016-06-07 General Electric Company Steam turbine inner shell assembly with common grooves
CN105507964A (zh) * 2016-01-18 2016-04-20 哈尔滨汽轮机厂有限责任公司 一种700℃超超临界三缸600mw汽轮机
CN105804802A (zh) * 2016-05-18 2016-07-27 哈尔滨汽轮机厂有限责任公司 一种350mw超临界双缸双排汽汽轮机

Family Cites Families (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE38382C (de) * P. HIERONYMUS in Karlsruhe. Nowaksanlage 19 Verfahren und Vorrichtung zur Herstellung von Hohl- und Vollgegenständen aus Papierstoff
CH111845A (de) * 1924-12-17 1926-01-02 Escher Wyss Maschf Ag Dampf- oder Gasturbine mit Leitscheiben, insbesondere für hohe Drücke und Temperaturen.
US2211874A (en) * 1938-08-16 1940-08-20 Westinghouse Electric & Mfg Co Turbine joint seal structure
CH250728A (de) * 1945-12-14 1947-09-15 Sulzer Ag Trommelläufer für Turbomaschinen.
US2467818A (en) * 1947-11-29 1949-04-19 Gen Electric High-temperature turbine casing arrangement
NL72215C (de) * 1949-04-29
FR1085715A (fr) * 1952-11-20 1955-02-07 Escher Wyss Ag Turbine thermique à carters intérieur et extérieur
CH331946A (de) * 1954-03-24 1958-08-15 Westinghouse Electric Corp Dampfturbine für hohe Drücke und Temperaturen mit in ein Aussengehäuse eingesetztem Leitschaufelträger
US2855178A (en) * 1954-07-14 1958-10-07 Vickers Armstrongs Ltd Turbines
US2888240A (en) * 1956-03-07 1959-05-26 Allis Chalmers Mfg Co Fluid cooled barrel cylinder for turbines
FR1201991A (fr) * 1958-09-04 1960-01-07 Napier & Son Ltd Carter de turbine
FR1320174A (fr) * 1962-01-25 1963-03-08 Rateau Soc Perfectionnement des enveloppes de turbomachines, notamment de turbines à vapeur
GB1101305A (en) * 1965-04-06 1968-01-31 Dominion Eng Works Ltd Method of fabricating parts using shrink elements
GB1335939A (en) * 1972-03-06 1973-10-31 Kraftwerk Union Ag Fluid flow machine
DE2218500B2 (de) * 1972-04-17 1974-01-31 Kraftwerk Union AG, 4330 Mülheim Mehrschaliges gehaeuse einer dampfturbine fuer hohe dampfdruecke und dampftemperaturen
US4431373A (en) * 1980-05-16 1984-02-14 United Technologies Corporation Flow directing assembly for a gas turbine engine
US4480957A (en) * 1983-04-14 1984-11-06 General Electric Company Dynamic response modification and stress reduction in dovetail and blade assembly
TR27460A (tr) * 1990-09-12 1995-05-29 United Technologies Corp Gaz türbinli motora mahsus kompresör gövdesi yapimi.

Also Published As

Publication number Publication date
FR2690202B1 (fr) 1995-07-07
DE69302520T2 (de) 1996-09-12
US5350276A (en) 1994-09-27
JPH0658101A (ja) 1994-03-01
EP0566478B1 (de) 1996-05-08
DE69302520T3 (de) 2002-12-05
DE69302520D1 (de) 1996-06-13
EP0566478A1 (de) 1993-10-20
FR2690202A1 (fr) 1993-10-22
JP3529145B2 (ja) 2004-05-24

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