EP1996796B1 - Dispositif et procédé de support d'une turbomachine - Google Patents

Dispositif et procédé de support d'une turbomachine Download PDF

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Publication number
EP1996796B1
EP1996796B1 EP07704675.3A EP07704675A EP1996796B1 EP 1996796 B1 EP1996796 B1 EP 1996796B1 EP 07704675 A EP07704675 A EP 07704675A EP 1996796 B1 EP1996796 B1 EP 1996796B1
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EP
European Patent Office
Prior art keywords
support
turbine engine
plate elements
base frame
support plate
Prior art date
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Active
Application number
EP07704675.3A
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German (de)
English (en)
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EP1996796A1 (fr
Inventor
Armin Busekros
Olatunde Omisore
Thomas Wilhelm
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Technology GmbH
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Alstom Technology AG
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Publication date
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Publication of EP1996796A1 publication Critical patent/EP1996796A1/fr
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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
    • F01D25/04—Antivibration arrangements
    • 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 device and a method for supporting a flow rotating machine, in particular a gas turbine arrangement, in which a rotor unit is rotatably mounted within a stationary outer housing, with at least two in the axial longitudinal extent to the outer housing spaced supports arranged for weight absorption of the flow rotating machine, on the one hand middle or directly hinged to the outer housing and on the other hand, medium or directly supported on a foundation.
  • Powerful gas turbine assemblies have, depending on the performance, a rotor unit typically with lengths of about 10 m, along which a compressor unit, the combustion chamber and at least one turbine stage are arranged.
  • a second combustion chamber and a further, subsequent turbine blading are additionally provided along the rotor unit.
  • Such, mainly integrally manufactured rotor units are completely enclosed by a stationary housing, which is supported for stable storage of the entire gas turbine assembly via a plurality of supports against a foundation.
  • FIGS. 2a and b To illustrate the previously used bearing concept for gas turbine arrangements is on the FIGS. 2a and b referenced, of which FIG. 2a a schematic cross section through a gas turbine arrangement and FIG.
  • FIG. 2b show a perspective overview of a gas turbine arrangement and the supports required for storage.
  • a substantially tubular gas turbine arrangement 1 a foundation 2 vertically uplifting support struts 3, on the one hand firmly connected to the foundation 2 and on the other hand abut against corresponding Abstützkonturen 4 of the housing 5.
  • the publication DE 43 13 527 A1 describes a support for thermal machines, in which mounted between a base plate and the bearing housing in height aligned sliding blocks.
  • the sliding blocks are used to compensate for thermally induced expansion effects and each form pairs of slides, the placement of the individual sliding blocks is fixed and thus provide no possibility for vibration control. It should also be noted that the vibration problem is not discussed in this document, nor can be found to eliminate the vibration problem recognizable approaches.
  • the publication DE 10 13 466 B describes a support of a machine tool group for a thermal power plant, which has only double-jointed pendulum supports as support devices.
  • the invention is based on the object, a device for supporting a flow rotating machine, in particular a gas turbine arrangement in which a rotor unit is rotatably mounted within a stationary outer housing, with at least two in the axial longitudinal extent to the outer housing spaced from each other supports for weight absorption of the flow rotating machine, on the one hand medium - Or articulated directly on the outer casing and on the other hand medium or directly supported on a foundation supporting base frame, such form that decisive influence on the developing vibrational structural resonance behavior of an operating gas turbine arrangement should be taken, the gas turbine arrangement possible is to store vibration.
  • the measures required for this purpose should be able to be carried out structurally simple and, if possible, after installation of the gas turbine arrangement on site quickly and without great assembly-technical effort.
  • claim 10 is a method for the vibration-reduced storage of a flow rotating machine, in particular a gas turbine arrangement.
  • the concept of the invention advantageously further features are the subject of the dependent claims and the description in particular with reference to the embodiment refer.
  • a device for supporting a flow-rotating machine in particular a gas turbine arrangement according to the features of the preamble of claim 1, is characterized in that at least one support provides at least one support surface, which is supported exclusively in partial areas on at least two support plate elements and the at least one support surface of the Support via the support plate elements with the base frame comes into operative connection, that the support surface is flat and oriented horizontally, that the support plate elements are clamped exclusively by the weight of the flow rotary machine between the support surface and the base frame, and that the support plate elements with mechanical relief of the base frame of the Weight of the flow rotary machine loosely rest on the support surface of the base frame and are laterally displaceable to the support surface.
  • the solution according to the invention allows Nachjustier ashamed the storage of a fully assembled on-site gas turbine arrangement, so that only by targeted placement so-called. Abstützplattenetti over which ultimately at least proportionately the weight of the entire gas turbine arrangement acts on a supporting base frame, the gas turbine individually to own Vibration behavior can be effectively influenced.
  • the inherent inherent elasticity inherent in the support in particular in the area of the support surface which is arranged so as to be cantilevered by the support plate elements, is utilized to determine the resonant vibration behavior of the gas turbine assembly in operation to influence specifically.
  • the stiffness or elasticity of the coupling between the support and the base frame can be varied almost continuously and thus the position of the resonance frequencies of the structure and Rotor unit of the gas turbine engine specifically vary.
  • the replacement or adapted to the respective structural resonances positioning of the respective Abstützplattenimplantation relative to the support surface of the support is made in a short time on site with simple technical means, so that vibration delays in commissioning the gas turbine assembly can be avoided or at least limited to a minimum can.
  • This requires only a suitably trained lifting device which is designed for load-bearing of the gas turbine arrangement and which allows a short-term lifting of the gas turbine arrangement in the region of the support, so that the otherwise loose between the foundation and the support present support plate elements in a suitable manner relative to the support surface of the Support can be moved.
  • the support is to be as elastic as possible, two support plate elements are provided which are to be provided in a suitable manner between the support and the base frame. Further details can be found in the further description with reference to the embodiment. Numerical calculations indicate that the rigidity and thus the elasticity behavior of the support can be varied by approximately +/- 30% with the aid of the support concept according to the solution, which makes it possible to shift the structural resonance of the gas turbine arrangement either above or below the operating speed.
  • the storage according to the solution is based on a solution according to the method for vibration-reduced storage of a flow rotating machine, in particular a gas turbine arrangement in which a rotor unit is rotatably mounted within a stationary outer housing, with at least two axially spaced from each other to the outer housing spaced supports for weight absorption of the flow rotating machine, on the one hand medium - Or articulated directly on the outer casing and on the other hand medium or directly supported on a base frame, which is characterized in that at least one support a flat trained and horizontally oriented support surface is provided, which is supported exclusively in partial areas on at least two support plate elements and the a support surface provided on the base frame is arranged vertically opposite one another.
  • At least two support plate elements arranged laterally spaced from each other are introduced such that the weight of the flow rotation machine proportionally completely acts on the base frame via the support plate elements and the current-operated flow rotating machine supports as little vibration as possible, wherein the support plate elements exclusively by the weight force of the flow rotation machine be clamped between the support surface and the base frame and the support plate elements with mechanical relief of the Base frame of the weight of the flow rotating machine loosely rest on the support surface of the base frame and are displaced laterally to the support surface.
  • the method can be used repeatedly in a suitable manner in order to adapt the bearing to the changed vibration behavior.
  • the support plate elements are introduced according to the number and arrangement between the support and support surfaces such that the support surface of the support provides free and with respect to the support surface spaced surface areas that are suitably dimensioned swinging.
  • the storage as elastic as possible form, so only two small dimensioned support plate elements are provided.
  • the device concept according to the invention is used for the vibration-free or vibration-free mounting of a flow rotary machine, in particular a gas turbine arrangement.
  • a flow rotary machine in particular a gas turbine arrangement.
  • all the system components that are at least substantially determining the vibration behavior of the flow rotary machine can also be mounted in the same way with little vibration in the same way. This concerns in particular attachment parts, which within the shortest time to the Flow rotary machine can be mounted or disassembled from this and lead to a significant change in the rigidity of the machine.
  • FIGS. 1a to c All show schematized cross-sectional views through a gas turbine arrangement as it were the figure representation in FIG. 2a , Unlike the reference to FIG. 2a illustrated, known per se, the solution according to the support concept provides a support 3, which is axially on one side to provide an end portion of the gas turbine assembly or alternatively at both axially opposite end portions of the gas turbine assembly.
  • the solution according to the support 3 has a matched to the outer contour of the outer housing 5 of the gas turbine assembly 1 AufEnglishung 7, via which the support 3 is fixedly connected to the outer housing 5.
  • the connection can usually be made via detachable screw connections in order to ensure easy assembly.
  • the semicircular formed in the embodiment 7 AufEnglishung largely comprises the lower half of the outer casing 5 so that the gas turbine assembly is securely supported by the support 3 in both the horizontal and vertical directions.
  • the support 3 also has a flat and horizontally oriented support surface 8, which is arranged opposite a flat and horizontally oriented support surface 9 of a load-receiving base frame 10 as it were. Between the support surface 8 and the support surface 9 so-called.
  • Support plate elements 11 are provided which the support 3 with respect to the base frame 10 by a gap corresponding to the respective thickness of the support plate elements 11, spaced.
  • the Abstützplattenimplantation 11 serve as spacers and preferably even have only a small surface area, so that their degree of coverage relative to the support surface 8 is as low as possible in order to obtain a high degree of adjustability of the inherent elasticity of the support surface 8. It is still necessary to adjust the rigidity or elasticity of the supports 3 to the vibration behavior of each operating gas turbine assembly 1 with simple technical means to gain influence on the structural resonance.
  • the support surface 8 is formed as a flat surface, mounted horizontally and symmetrically to the center axis M, which also represents a center of gravity line through the gas turbine rotating machine formed. Thus, it is always cut from the center of gravity line, so that a safe storage of the gas turbine arrangement is ensured.
  • the vibration behavior of the support surface 8 of the support 3 can be influenced by the number of introduced between the support 3 and the base frame 10 i Abstützplattenmaschinen 11 and their arrangement. See, for example, according to the embodiment in FIG.
  • FIG. 1 a four support plate elements 11, which are each arranged symmetrically to the center axis M and in the lateral edge regions of the opposing support surface 8 and bearing surface 9, we obtain a high rigidity along the support surface 8 of the support 3.
  • lifting means 12 can be integrated within the foundation base frame 10, which can accommodate the load of the gas turbine arrangement in the region of the support 3 for a short time and raise the support surface 8 relative to the base frame 10. Since the support plate elements 11 rest loosely on the support surface 9 of the base frame 10, they can be manually moved smoothly. It is also possible to adjust the respective support height of each individual support plate element individually by placing additional spacer plates on the respective support plate elements. After appropriate arrangement and adjustment of the individual support plate elements 11, preferably integrated in the base frame 10 lifting means 12 are lowered, so that the proportionate weight of the gas turbine assembly, which rests on the support 3, is introduced via the supporting plate 11 into the base frame 10.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (12)

  1. Dispositif de support d'une turbomachine rotative, en particulier d'un agencement de turbine à gaz dans lequel une unité de rotor (6) est supportée à rotation à l'intérieur d'un boîtier extérieur stationnaire (5), comprenant au moins deux appuis (3) disposés à distance l'un de l'autre dans l'étendue longitudinale axiale du boîtier extérieur (5) pour recevoir le poids de la turbomachine rotative (1), qui sont d'une part articulés de manière directe ou indirecte au boîtier extérieur (5) et s'appuient d'autre part de manière directe ou indirecte sur un cadre de base (10),
    caractérisé en ce qu'au moins un appui (3) prévoit au moins une surface de support (8) qui s'appuie exclusivement dans des régions partielles sur au moins deux éléments de plaque d'appui (11),
    en ce que l'au moins une surface de support (8) de l'appui (3) entre en liaison fonctionnelle par le biais des éléments de plaque d'appui (11) avec le cadre de base (10), en ce que la surface de support (8) est réalisée sous forme plane et est orientée horizontalement,
    en ce que les éléments de plaque d'appui (11) sont serrés exclusivement par la force de pesanteur de la turbomachine rotative (1) entre la surface de support (8) et le cadre de base (10), et
    en ce que les éléments de plaque d'appui (11), lors de la décharge mécanique du cadre de base (10) de la force de pesanteur de la turbomachine rotative (1), reposent librement sur la surface d'appui (9) du cadre de base (10) et peuvent être déplacés latéralement par rapport à la surface d'appui (9).
  2. Dispositif selon la revendication 1, caractérisé en ce que les au moins deux éléments de plaque d'appui (11) sont installés directement entre la surface de support (8) de l'appui (3) et une surface d'appui (9) du cadre de base (10).
  3. Dispositif selon la revendication 1 ou 2, caractérisé en ce qu'un dispositif de levage (12) est prévu, lequel soulève la turbomachine rotative (1) ainsi que son appui (3) par rapport à la surface d'appui (9) du cadre de base (10).
  4. Dispositif selon l'une quelconque des revendications 1 à 3, caractérisé en ce que les éléments de plaque d'appui (11) sont réalisés d'une seule pièce ou présentent plusieurs disques d'espacement individuels disposés en pile.
  5. Dispositif selon l'une quelconque des revendications 1 à 4, caractérisé en ce que l'au moins un appui (3) supporte la turbomachine rotative (1) symétriquement par rapport à l'axe de rotation traversant l'unité de rotor (6), et en ce que la surface de support (8) coupe perpendiculairement une ligne du centre de gravité de la turbomachine rotative (1).
  6. Dispositif selon la revendication 5, caractérisé en ce que la surface de support (8) est réalisée de manière symétrique par rapport à ladite ligne du centre de gravité.
  7. Dispositif selon l'une quelconque des revendications 1 à 6, caractérisé en ce que l'au moins un appui (3) prévoit un évidement (7) de contour conjugué à celui du boîtier extérieur (5) de la turbomachine rotative (1), lequel entoure presque la moitié du boîtier extérieur (5) et par le biais duquel l'appui (3) est connecté fixement au boîtier extérieur (5).
  8. Utilisation du dispositif selon l'une quelconque des revendications 1 à 7 pour le support sans oscillation ou avec peu d'oscillations d'une turbomachine rotative (1) et/ou de composants d'installation connectés à la turbomachine rotative, déterminant conjointement le comportement d'oscillation de la turbomachine rotative (1).
  9. Utilisation selon la revendication 8, caractérisée en ce que les éléments de plaque d'appui (11) sont sélectionnés en termes de leur position, de leur nombre ainsi que de leur épaisseur de plaque en fonction du comportement d'oscillation de la turbomachine rotative (1) en fonctionnement et sont disposés par rapport à la surface de support (8) de l'appui (3) de sorte que la turbomachine rotative (1) soit supportée avec aussi peu d'oscillations que possible.
  10. Procédé pour le support avec oscillation réduite d'une turbomachine rotative (1), en particulier d'un agencement de turbine à gaz dans lequel une unité de rotor (6) est supportée à rotation à l'intérieur d'un boîtier extérieur stationnaire (5), comprenant au moins deux appuis (3) disposés à distance l'un de l'autre dans l'étendue longitudinale axiale du boîtier extérieur (5) pour recevoir le poids de la turbomachine rotative (1), qui sont d'une part articulés de manière directe ou indirecte au boîtier extérieur (5) et s'appuient d'autre part de manière directe ou indirecte sur un cadre de base (10),
    caractérisé en ce que dans le cas d'au moins un appui (3), on prévoit une surface de support (8) réalisée sous forme plane et orientée horizontalement, qui s'appuie exclusivement dans des régions partielles sur au moins deux éléments de plaque d'appui (11), et qui est disposée verticalement à l'opposé d'une surface d'appui (9) prévue sur le cadre de base (10),
    en ce qu'entre la surface de support (8) et la surface d'appui (9) sont introduits au moins deux éléments de plaque d'appui (11) disposés latéralement à distance l'un de l'autre de telle sorte que la force de pesanteur de la turbomachine rotative (1) agisse de manière proportionnée complètement par le biais des éléments de plaque d'appui (11) sur le cadre de base (10) et supporte avec aussi peu d'oscillations que possible la turbomachine rotative (1) en fonctionnement, les éléments de plaque d'appui (11) étant serrés exclusivement par la force de pesanteur de la turbomachine rotative (1) entre la surface de support (8) et le cadre de base (10) et les éléments de plaque d'appui (11), lors de la décharge mécanique du cadre de base (10) de la force de pesanteur de la turbomachine rotative (1), reposant librement sur la surface d'appui (9) du cadre de base (10) et étant déplacés latéralement par rapport à la surface d'appui (9).
  11. Procédé selon la revendication 10, caractérisé en ce que les éléments de plaque d'appui (11) sont introduits entre les surfaces de support (8) et d'appui (9) en fonction de leur nombre et de leur agencement de telle sorte que la surface de support (8) de l'appui (3) prévoie des régions de surface libres et espacées par rapport à la surface d'appui (9).
  12. Procédé selon la revendication 11, caractérisé en ce que pour augmenter la rigidité des régions de surface libres de la surface de support (8), on prévoit plus de deux éléments de plaque d'appui (11).
EP07704675.3A 2006-03-17 2007-02-21 Dispositif et procédé de support d'une turbomachine Active EP1996796B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH4122006 2006-03-17
PCT/EP2007/051649 WO2007107422A1 (fr) 2006-03-17 2007-02-21 Dispositif et procede de montage d'une machine rotative d'ecoulement

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Publication Number Publication Date
EP1996796A1 EP1996796A1 (fr) 2008-12-03
EP1996796B1 true EP1996796B1 (fr) 2016-01-06

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US (1) US8028967B2 (fr)
EP (1) EP1996796B1 (fr)
JP (1) JP2009530525A (fr)
AU (1) AU2007228927B2 (fr)
ES (1) ES2565018T3 (fr)
WO (1) WO2007107422A1 (fr)

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ES2565018T3 (es) 2016-03-30
AU2007228927B2 (en) 2010-07-22
US8028967B2 (en) 2011-10-04
EP1996796A1 (fr) 2008-12-03
JP2009530525A (ja) 2009-08-27
US20090064685A1 (en) 2009-03-12
AU2007228927A1 (en) 2007-09-27

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