EP2788586B1 - Couronne d'aube pour une turbomachine axiale et procédé d'ajustement de la capacité de débit massique de la couronne d'aube - Google Patents

Couronne d'aube pour une turbomachine axiale et procédé d'ajustement de la capacité de débit massique de la couronne d'aube Download PDF

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Publication number
EP2788586B1
EP2788586B1 EP12786929.5A EP12786929A EP2788586B1 EP 2788586 B1 EP2788586 B1 EP 2788586B1 EP 12786929 A EP12786929 A EP 12786929A EP 2788586 B1 EP2788586 B1 EP 2788586B1
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EP
European Patent Office
Prior art keywords
blade
ring
blade ring
flow rate
adjustment
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.)
Not-in-force
Application number
EP12786929.5A
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German (de)
English (en)
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EP2788586A1 (fr
Inventor
Armin De Lazzer
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Siemens AG
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Siemens AG
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Filing date
Publication date
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Priority to EP12786929.5A priority Critical patent/EP2788586B1/fr
Publication of EP2788586A1 publication Critical patent/EP2788586A1/fr
Application granted granted Critical
Publication of EP2788586B1 publication Critical patent/EP2788586B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/167—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes of vanes moving in translation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2220/00—Application
    • F05B2220/30—Application in turbines
    • F05B2220/301—Application in turbines in steam turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/31—Application in turbines in steam turbines

Definitions

  • the invention relates to a blade ring for an axial turbomachine, an axial turbomachine with the blade ring and a method for adjusting the absorption capacity of the blade ring.
  • the maximum process steam mass flow which can be conveyed by the steam turbine is one of the decisive variables in the design of the steam turbine and is referred to as the steam capacity of the steam turbine.
  • the vane rings of the steam turbine have a plurality of vanes, which are arranged distributed uniformly over the circumference, wherein between the vanes blade channels are formed. Radially, the blade channels are limited on the hub side of a hub contour and the housing side of a housing contour.
  • the absorption capacity of the steam turbine is decisively influenced by the absorption capacity of the first guide vane ring, which is essentially determined by the entirety of all effective cross sections of the vane passages of the first guide vane ring.
  • the invention has for its object to provide a blade ring for an axial turbomachine, the axial turbomachine with the blade ring and a method for adjusting the absorption capacity of the blade ring, wherein the above-mentioned problems are overcome and in particular the absorption capacity of the axial turbomachine is corrected in a corrective manner.
  • the US 5,683,225 includes the features of the preamble of claim 1.
  • the blade ring according to the invention for an axial turbomachine has a radially inwardly facing outer surface arranged on an outer ring and a radially outwardly facing inner surface arranged on an inner ring which delimits an annular flow channel tapering in the main flow direction of the axial turbomachine and arranged concentrically and parallel to one another are, and at least one Justierschaufel, which is arranged in the flow channel by means of a guide device to a surface line of one of the surfaces displaceable parallel and lockable on at least one of the rings in a predetermined position.
  • a generatrix is characterized in that it is arranged on one of the two surfaces and is directed to the imaginary tip of the respective surface.
  • the diameter of the flow channel decreases in the direction of the taper of the inner surface and the outer surface.
  • the at least one adjusting blade displaced in the direction of tapering by means of the guide device its distance decreases in the circumferential direction to the blades arranged adjacent in the blade ring, whereby the obstruction of the flow channel for the fluid flowing through the flow channel increases and decreases the absorption capacity of the blade ring accordingly.
  • the ability to swallow can be increased by displacing the at least one adjusting blade by means of the guide device counter to the direction of tapering.
  • the ability to swallow the blade ring is advantageously easily changed under the operation of the guide device.
  • the inner ring is formed as a disc.
  • the outer surface and the inner surface are preferably conical surfaces.
  • the outer surface and the inner surface alternatively have along the respective surface line in each cross section perpendicular to the axis of the flow channel segmentally equal radii of curvature, so that remain constant when moving the Justierschaufel the extensions of the radial gaps between the Justierschaufel and the surfaces.
  • each of the cross sections of the outer surface and the inner surface is preferably formed perpendicular to the axis of the flow channel in each case by a polygon or by a plurality of immediately adjacent arranged circle segments.
  • the blade ring is preferably a diagonal stage of the axial turbomachine.
  • the diagonal stage advantageously has the flow channel, which is bounded by the two conical surfaces.
  • the blade ring is a vane ring with fixed, non-rotating vanes and a fixed, non-rotating inner surface and outer surface.
  • the blade ring has a plurality of blades, wherein the blades are alternately the Justingschaufeln and fixedly attached to the outer surface and / or on the inner surface blades.
  • Each of the fixed blades is preferably integrally formed with the inner ring and the outer ring or integrally with a segment of the inner ring and a segment of the outer ring. This advantageously results in a high rigidity of the blade ring.
  • the fact that every second blade is firmly attached, results in the manufacture of the blade ring advantageously good accessibility of the blade ring for a production tool.
  • the guide device has a sliding groove in the inner ring and / or in the outer ring as well as on the radially outer side and / or on the radially inner side of the Justierschaufel a pin, wherein the pin engages in the sliding groove.
  • the guide device preferably has, in at least one of the sliding grooves downstream of the main flow direction of the axial turbomachine, a stop with which the adjusting blade can be fixed in the predetermined position. In this case, the adjusting blade is pressed during operation of the axial turbomachine by the fluid flowing in the flow channel against the fluid stop, whereby the determination of the adjusting blade is accomplished.
  • the position of the adjusting blade in the flow channel can be defined for example by introducing a spacer to the stop.
  • the spacer can for example be fixedly mounted by grub screws and / or by welding points on the outer ring and / or on the inner ring.
  • the guide means is arranged such that the at least one adjusting blade is exchangeable with another adjusting blade.
  • the at least one adjusting blade can be exchanged for the other adjusting blade with other aerodynamic properties.
  • An adaptation of the swallowing ability can also be carried out by a suitable exchange, for example by the other adjusting blade having a profile with a shorter or longer chord length.
  • the axial turbomachine according to the invention has the blade ring according to the invention.
  • the absorption capacity of the axial turbomachine is preferably determined by the ability to swallow the blade ring.
  • the method according to the invention for adjusting the buoyancy of the blade ring comprises the following steps: predetermining a desired value of the buoyancy of the blade ring; Determining the actual value of the buoyancy of the blade ring; Comparing the desired value of the buoyancy of the blade ring with the actual value of the buoyancy of the blade ring; Moving the at least one adjusting blade by means of the guide device parallel to the generatrix such that the desired value of the swallowing ability becomes equal to the actual value of the swallowing ability; Locking the adjusting blade with the guide device. If the ability to swallow the axial turbomachine is defined by the ability to swallow the blade ring, the ability to swallow the axial turbomachine can be changed by moving the at least one adjusting blade.
  • FIG. 1 shows a longitudinal section through an axial turbomachine with a preferred embodiment of the blade ring according to the invention.
  • an axial turbomachine 1 comprises a housing 22, a shaft 21 and a plurality of blade rings 11 to 13.
  • a fluid 25 is flowable within the housing 22 with a main flow direction 17.
  • a first vane ring 11, a blade ring 12 and a second vane ring 13 are shown, which are arranged in this order in the main flow direction 17 of the fluid 25.
  • the first vane ring 11 has an outer cone ring 24 fastened to the housing 22 with a conical outer surface 2 facing radially inwards, and an inner conical ring 23 with a conical inner surface 3 facing radially outward within the outer conical ring 24.
  • the cone outer surface 2 and the inner cone surface 3 are arranged concentrically with each other, have a same cone angle 18, are arranged parallel to each other in each axial section and define an annular flow channel 4.
  • the inner cone ring 23 and the outer cone ring 24 are truncated cones. However, it is also conceivable that the inner cone ring 23 includes its conical tip.
  • the cone axes 26 of the cone outer surface 2 and the inner cone surface 3 coincide with the shaft axis 27.
  • the conical surfaces 2, 3 are oriented so that the outer diameter 28 (shown in the figure is half the outer diameter 28) of the flow channel 4 in the main flow direction 17 decreases.
  • the inner cone ring 23 and the outer cone ring 24 are modified such that the cone inner surface 3 and the cone outer surface 2 along the respective surface line 6 and along the width of Justierschaufel 7 in each cross-section perpendicular to the shaft 21 have the same curvature radii, so that when moving the Justierschaufel 7, the extensions of the radial gaps between the Justierschaufel 7 and the conical surfaces 2, 3 remain constant. It is conceivable, for example, that the radii of curvature are infinitely large, so that each of the cross sections of the conical surfaces 2, 3 forms a polygon perpendicular to the shaft 21, wherein a blade is arranged on each of the segments of the polygon. Downstream of the main flow direction 17, the length of each of the path segments of the polygon becomes shorter.
  • each of the cross sections is formed perpendicular to the shaft 21 of a plurality of circle segments.
  • the radii of curvature of the circular segments can be both larger and smaller than the radii of the flow channel 4. Downstream of the main flow direction 17, the extent of each of the circle segments becomes shorter, whereas the radius of curvature remains constant in each case.
  • a Justierschaufel 7 is arranged, which is arranged with its radial outer side 9 on the cone outer surface 2 and with its radially inner side 10 on the inner surface of the cone 3.
  • the Justierschaufel 7 has on its inner radial side 9 and its radial outer side 10 each have a pin 15, wherein the pins 15 each engage in a sliding groove 14 in the inner cone ring 23 and the outer taper ring 24.
  • the slide grooves 14 are arranged parallel to each other and each extend along a surface line 6 of the conical surfaces 2, 3, so that the Justierschaufel 7 is parallel to the generatrices 6 slidably.
  • the adjusting blade 7 When the adjusting blade 7 is displaced in the main flow direction 17, the distance in the circumferential direction of the adjusting blade 7 is reduced to the blades arranged adjacent to it in the first guide blade ring 11, whereby the obstruction for the fluid 25 in the first guide blade ring 11 increases. Increased obstruction reduces the ability of the first vane ring 11 to absorb moisture. Conversely, the ability to swallow can be increased by displacing the adjusting vane 7 upstream of the main flow direction 17.
  • the maximum possible displacement 8 of the adjusting blade 7 is limited by the length of the flow channel 4 in the main flow direction 17 and the length of the Gleitnuten 14. To change the ability to swallow, it is also conceivable that the adjusting blade 7 is replaced by another adjusting blade, which has a shorter or longer chord length.
  • the sliding groove 14 in the tapered inner surface 3 is limited in the main flow direction 17 by a stop 29, i. it is not guided to the downstream end 5 of the flow channel 4, so that during operation of the axial turbomachine 1, the Justierschaufel 7 is pressed by the flow of the fluid 25 to the stop 29. It is also possible to limit the sliding groove 14 in the conical outer surface 2 in the main flow direction 17 of a stop or to limit both Gleitnuten 14 of a stop. Upstream of the main flow direction 17, the sliding grooves 14 are not limited, so that the adjusting blade 7 is removable from the flow channel 4 and exchangeable with another adjusting blade.
  • spacers 16 are provided for detecting the position of the Justierschaufel 7 in the Gleitnuten.
  • the spacers 16 are arranged both on the downstream side of the pins 15, as well as on the upstream side of the pins 15. It is in principle possible to provide no spacers 16 on the upstream side, because the Justierschaufel 7 is pressed in operation against the downstream spacers 16 or against the end of the sliding groove 14. The minimum possible absorption capacity for the adjusting blade 7 is achieved if none of the spacers 16 are provided on the downstream side.
  • All the blades in the first blade ring 11 are designed as adjusting blades 7 and thus designed to be displaceable.
  • the blades could alternately as the adjusting blades 7 are formed and designed to be fixed to the conical surfaces 2, 3.
  • the inner cone ring 23, the outer cone ring 24 and the fixed blades are made of one piece.
  • a fixed blade together with one segment of the inner cone ring 23 and the outer cone ring 24 is made of one piece and thus the first vane ring 11 is composed of a plurality of segments.
  • the Justierschaufeln 7 are also provided for a blade ring.
  • the inner cone ring 23 are fixedly connected to the shaft 21 and the Justierschaufel 7 with its radially inner side 10 slidably disposed on the inner cone ring 23.
  • the inner cone ring 23 and the Justierschaufel 7 are thus rotating components of the axial turbomachine 1.
  • a gap could be provided between the radial outer side 9 of the movable blade 7 and the cone outer surface 2, a gap could be provided.
  • the Justierschaufel 7 could also be with its outer radial side 9 with the outer cone ring 24 in engagement. In the latter case, the outer cone ring 24 would also be a rotating component.
  • the adjustment of the absorption capacity of the first vane ring 11 is to be carried out as follows: predetermining a desired value of the ability to swallow the blade ring 11; Determining the actual value of the swallowability of the blade ring 11; Comparing the target value of the ability to swallow of the blade ring 11 with the actual value of the ability to swallow the blade ring 11; Moving the at least one adjusting blade 7 by means of the guide device parallel to the generating line 6 such that the desired value of the swallowing ability becomes equal to the actual value of the swallowing ability; Detecting the Justierschaufel 7 with the guide device.

Claims (13)

  1. Couronne d'aube pour une turbomachine ( 1 ) axiale, comprenant une surface ( 2 ) extérieure disposée sur un anneau ( 24 ) extérieur et tournée radialement vers l'intérieur et une surface ( 2 ) extérieure disposée sur un anneau ( 24 ) extérieur et tournée radialement vers l'intérieur et une surface ( 3 ) intérieure disposée sur un anneau ( 23 ) intérieur et tournée radialement vers l'extérieur, qui délimitent un canal ( 4 ) d'écoulement de forme annulaire et se rétrécissant dans le sens ( 17 ) principal d'écoulement de la turbomachine ( 1 ) axiale et qui sont disposées concentriquement ainsi que parallèlement l'une à l'autre, caractérisée par au moins une aube ( 7 ) d'ajustement, qui est montée dans le canal ( 4 ) d'écoulement au moyen d'un dispositif ( 14, 15 ) de guidage coulissant parallèlement à une génératrice ( 6 ) de l'une des surfaces ( 2, 3 ) et qui peut être fixée en une position définie à l'avance sur au moins l'un des anneaux ( 23, 24 ).
  2. Couronne d'aube suivant la revendication 1,
    dans laquelle la surface ( 2 ) extérieure et la surface ( 3 ) intérieure sont des surfaces coniques.
  3. Couronne d'aube suivant la revendication 1,
    dans laquelle la surface ( 2 ) extérieure et la surface ( 3 ) intérieure ont, le long de la génératrice ( 6 ) respective, dans chaque section transversale perpendiculairement à l'axe du canal ( 4 ) d'écoulement, segment par segment, des rayons de courbure égaux de sorte que, lorsque l'aube ( 7 ) d'ajustement coulisse, les étendues des intervalles radiaux entre l'aube ( 7 ) d'ajustement et les surfaces ( 2, 3 ) restent constantes.
  4. Couronne d'aube suivant la revendication 3,
    dans laquelle chacune des sections transversales de la surface extérieure et de la surface ( 3 ) intérieure est formée, perpendiculairement à l'axe du canal ( 4 ) d'écoulement, respectivement par un polygone ou par une multiplicité de segments de cercle directement voisins.
  5. Couronne d'aube suivant l'une des revendications 1 à 4,
    dans laquelle la couronne ( 11 ) d'aube est un étage à flux diagonal de la turbomachine ( 1 ) axiale.
  6. Couronne d'aube suivant l'une des revendications 1 à 5,
    dans laquelle la couronne ( 1 ) d'aube a une multiplicité d'aubes,
    les aubes alternant avec les aubes ( 7 ) d'ajustement, ainsi qu'étant mises de manière fixe sur la surface ( 2 ) extérieure et/ou sur la surface ( 3 ) intérieure.
  7. Couronne d'aube suivant la revendication 6,
    dans laquelle chacune des aubes mises de façon fixe est fabriquée d'une pièce ensemble avec l'anneau ( 23 ) intérieur et l'anneau ( 24 ) extérieur ou d'une pièce ensemble avec un segment de l'anneau ( 23 ) intérieur et avec un segment de l'anneau ( 24 ) extérieur.
  8. Couronne d'aube suivant l'une des revendications 1 à 7,
    dans laquelle le dispositif de guidage a une rainure ( 14 ) de glissement dans l'anneau ( 23 ) intérieur et/ou dans l'anneau ( 24 ) extérieur, ainsi qu'un tenon ( 15 ) du côté
    ( 9 ) extérieur radialement et/ou du côté ( 10 ) intérieur radialement de l'aube ( 7 ) d'ajustement, le tenon ( 15 ) pénétrant dans la rainure ( 14 ) de glissement.
  9. Couronne d'aube suivant la revendication 8,
    dans laquelle le dispositif de guidage a, dans au moins l'une des rainure ( 14 ) de glissement, en aval dans le sens ( 17 ) d'écoulement principal de la turbomachine ( 1 ) axiale, une butée ( 29 ) par laquelle l'aube ( 7 ) d'ajustement peut être fixée dans la position définie à l'avance.
  10. Couronne d'aube suivant l'une des revendications 1 à 9,
    dans laquelle le dispositif ( 14, 15 ) de guidage est conçu de manière à ce que la au moins une aube ( 7 ) d'ajustement puisse être remplacée par une autre aube d'ajustement.
  11. Turbomachine axiale ayant une couronne ( 11 ) d'aube suivant l'une des revendications 1 à 10.
  12. Turbomachine axiale suivant la revendication 11,
    dans laquelle le débit de dimensionnement de la turbomachine ( 1 ) axiale est défini par le débit de dimensionnement de la couronne ( 11 ) d'aube.
  13. Procédé d'ajustement du débit de dimensionnement d'une couronne ( 11 ) d'aube suivant l'une des revendications 1 à 10 comprenant les stades :
    - Définition préalable d'une valeur de consigne du débit de dimensionnement de la couronne ( 11 ) d'aube,
    - détermination de la valeur réelle du débit de dimensionnement de la couronne ( 11 ) d'aube,
    - Comparaison de la valeur de consigne du débit de dimensionnement de la couronne ( 11 ) d'aube à la valeur réelle du débit de dimensionnement de la couronne ( 11 ) d'aube,
    - Déplacement de la au moins une aube ( 7 ) d'ajustement au moyen du dispositif ( 14, 15 ) de guidage parallèlement à la génératrice ( 6 ) de manière à ce que la valeur de consigne du débit de dimensionnement soit égale à la valeur réelle du débit de dimensionnement,
    - Fixation de l'aube ( 7 ) d'ajustement par le dispositif ( 14, 15 ) de guidage.
EP12786929.5A 2012-02-02 2012-11-07 Couronne d'aube pour une turbomachine axiale et procédé d'ajustement de la capacité de débit massique de la couronne d'aube Not-in-force EP2788586B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP12786929.5A EP2788586B1 (fr) 2012-02-02 2012-11-07 Couronne d'aube pour une turbomachine axiale et procédé d'ajustement de la capacité de débit massique de la couronne d'aube

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP12153630.4A EP2623717A1 (fr) 2012-02-02 2012-02-02 Couronne d'aube pour une turbomachine axiale et procédé d'ajustement de la capacité de débit massique de la couronne d'aube
EP12786929.5A EP2788586B1 (fr) 2012-02-02 2012-11-07 Couronne d'aube pour une turbomachine axiale et procédé d'ajustement de la capacité de débit massique de la couronne d'aube
PCT/EP2012/071992 WO2013113415A1 (fr) 2012-02-02 2012-11-07 Couronne d'aubes d'une turbomachine axiale et procédé permettant d'ajuster la capacité de débit de la couronne d'aubes

Publications (2)

Publication Number Publication Date
EP2788586A1 EP2788586A1 (fr) 2014-10-15
EP2788586B1 true EP2788586B1 (fr) 2016-01-20

Family

ID=47178653

Family Applications (2)

Application Number Title Priority Date Filing Date
EP12153630.4A Withdrawn EP2623717A1 (fr) 2012-02-02 2012-02-02 Couronne d'aube pour une turbomachine axiale et procédé d'ajustement de la capacité de débit massique de la couronne d'aube
EP12786929.5A Not-in-force EP2788586B1 (fr) 2012-02-02 2012-11-07 Couronne d'aube pour une turbomachine axiale et procédé d'ajustement de la capacité de débit massique de la couronne d'aube

Family Applications Before (1)

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EP12153630.4A Withdrawn EP2623717A1 (fr) 2012-02-02 2012-02-02 Couronne d'aube pour une turbomachine axiale et procédé d'ajustement de la capacité de débit massique de la couronne d'aube

Country Status (5)

Country Link
US (1) US20150030431A1 (fr)
EP (2) EP2623717A1 (fr)
JP (1) JP5855768B2 (fr)
CN (1) CN104105844B (fr)
WO (1) WO2013113415A1 (fr)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
IT201700061762A1 (it) * 2017-06-06 2018-12-06 Ansaldo Energia Spa Gruppo statorico per uno stadio di espansione radiale-assiale di turbina a vapore

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JP5855768B2 (ja) 2016-02-09
EP2623717A1 (fr) 2013-08-07
CN104105844A (zh) 2014-10-15
JP2015506439A (ja) 2015-03-02
CN104105844B (zh) 2016-03-16
US20150030431A1 (en) 2015-01-29
EP2788586A1 (fr) 2014-10-15
WO2013113415A1 (fr) 2013-08-08

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