EP0491966B1 - Dispositif de support d'une turbomachine thermique - Google Patents

Dispositif de support d'une turbomachine thermique Download PDF

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Publication number
EP0491966B1
EP0491966B1 EP90123734A EP90123734A EP0491966B1 EP 0491966 B1 EP0491966 B1 EP 0491966B1 EP 90123734 A EP90123734 A EP 90123734A EP 90123734 A EP90123734 A EP 90123734A EP 0491966 B1 EP0491966 B1 EP 0491966B1
Authority
EP
European Patent Office
Prior art keywords
bearing
diffuser
turbomachine
housing
inner part
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
EP90123734A
Other languages
German (de)
English (en)
Other versions
EP0491966A1 (fr
Inventor
Kamil Matyscak
Michael Dr. Müller
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.)
ABB Asea Brown Boveri Ltd
ABB AB
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Priority to EP90123734A priority Critical patent/EP0491966B1/fr
Priority to DE59007880T priority patent/DE59007880D1/de
Priority to JP03325482A priority patent/JP3112110B2/ja
Publication of EP0491966A1 publication Critical patent/EP0491966A1/fr
Priority to US08/089,621 priority patent/US5326222A/en
Application granted granted Critical
Publication of EP0491966B1 publication Critical patent/EP0491966B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports

Definitions

  • the invention relates to a thermal turbomachine, in particular an axially flow-through gas turbine, to the outlet rotor blades of which an exhaust gas housing is connected, the boundary walls of which essentially consist of a hub-side annular inner part and an annular outer part, which delimit a diffuser and which are connected to one another via a plurality of ribs distributed uniformly over the circumference are, and wherein the outlet-side bearing of the turbomachine is arranged in the cavity within the inner part.
  • the diffuser In modern machines, the diffuser is no longer supported on the foundation itself, but is flanged to the housing of the gas turbine.
  • the exhaust-side shaft bearing within the diffuser inner ring is in an extremely hot environment during machine operation. Both the positioning of the bearing and the absorption of the usually vertical load are located in the diffuser construction. However, due to the low creep rupture strength of the materials used, the entire supporting structure can deform over time.
  • the invention is therefore based on the object of creating a measure in turbomachines of the type mentioned in which the support of the outlet-side bearing is independent of the influences of thermal stress and thermal expansion of the housing and the diffuser walls.
  • the bearing housing can be positioned in its position with adjusting elements arranged on the inner part of the exhaust gas housing and is supported on the foundation via at least one spring support.
  • the advantage of the invention can be seen in particular in that the deformation of the diffuser due to the wave load is excluded is that the diffuser still positions the rotor in the outer case. As a result, the radial blade clearances in the turbomachine remain unaffected even when the housing is lowered, for example.
  • the thermal turbomachine here a gas turbine, of which the exhaust side and the last four axially flowed stages are shown in FIG. 1, consists essentially of the bladed rotor 1 and the blade carrier 2 equipped with guide vanes.
  • the blade carrier is suspended in the turbine housing 3 .
  • the exhaust gas duct 5 is flanged to the turbine housing, which essentially consists of a hub-side, annular inner part 6 and an annular outer part 7, which delimit the diffuser 9.
  • Both elements 6 and 7 can be half-shells with an axial parting plane (Fig. 2, flanges not shown) or one-piece pot housings. you are interconnected by a plurality of welded radial flow ribs 8, which are arranged evenly distributed over the circumference.
  • the annular outer part 7 is provided on the turbine side with an annular sealing strip 10 which is flush with the contour of the turbine channel on the cylinder side.
  • the outlet-side mounting of the turbomachine is arranged in the cavity within the inner part 6.
  • the rotor 1 lies in a support bearing 4, the bearing housing 11 of which is positioned by means of adjusting elements 12 (FIG. 2), which are part of the inner part 6. Since the flue gas duct flanged onto the turbine housing is to be regarded as a rigid extension of the housing, these adjustment means 12 are sufficient for adjusting the bearing, and there are no additional aids which ensure compliance with the bearing line.
  • the bearing load is no longer absorbed by the diffuser construction, but instead is led out of the hot diffuser area.
  • This is done via a beam 13, which is attached with its upper end to the lower part of the bearing housing 11 by conventional means, for example a joint 14; at its lower end the beam is connected to a commercially available spring support 15 standing on the foundation.
  • the ribs 8 in the diffuser 9 expediently have a wing profile and are hollow. The beam 13 is passed through the lower, vertical rib.
  • This spring support 15 is able to absorb thermal expansion of the beam 13 with constant load. This ensures that the storage line is not affected. Since the load-bearing element of such a spring support is generally a coil spring with a very flat spring characteristic, a certain screw height is required to perform its compensation function. Lack of sufficient space between The exhaust duct and foundation are therefore divided into several, here three spring supports 15, the bearing load, which can be around 30 tons on today's machines.
  • the measure described has the advantage that the diffuser construction flanged to the turbine housing, since it is freed from the bearing load, can now be carried out more easily. In particular, there are savings in costly heat-resistant material.
  • the invention is not limited to the exemplary embodiment shown and described, which has a diffuser with an axial outlet and thus greatly facilitates the arrangement of flow ribs for carrying out the bearing support.
  • the invention is basically applicable wherever a machine element operating in a hot environment has to be fixed in an absolute position.

Claims (2)

  1. Turbomachine thermique, en particulier turbine à gaz à écoulement axial, dont les aubes mobiles de sortie sont raccordées à un corps des gaz d'échappement (5), dont les parois extrêmes se composent essentiellement d'une partie annulaire intérieure (6) située du côté du moyeu et d'une partie annulaire extérieure (7), qui délimitent un diffuseur (9) et qui sont reliées l'une à l'autre par plusieurs ailettes (8) uniformément réparties sur la périphérie, et dans laquelle le palier proche de la sortie (4, 11) de la turbomachine est disposé dans l'espace creux à l'intérieur de la partie intérieure, caractérisée en ce que le corps de palier (11) peut être positionné dans sa place avec des éléments de réglage (12) agencés à la partie intérieure (6) du corps des gaz d'échappement (5) et qu'il est appuyé sur la fondation par au moins un support à ressort (15).
  2. Turbomachine suivant la revendication 1, caractérisée en ce que le corps de palier (11) est relié par une poutre (13) à l'appui à ressort (15), dans laquelle la poutre (13) est conduite hors du corps des gaz d'échappement (5) au travers d'une ailette creuse (8) à travers le diffuseur (9).
EP90123734A 1990-12-10 1990-12-10 Dispositif de support d'une turbomachine thermique Expired - Lifetime EP0491966B1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP90123734A EP0491966B1 (fr) 1990-12-10 1990-12-10 Dispositif de support d'une turbomachine thermique
DE59007880T DE59007880D1 (de) 1990-12-10 1990-12-10 Lagerung einer thermischen Turbomaschine.
JP03325482A JP3112110B2 (ja) 1990-12-10 1991-12-10 熱式タービン機械の支承装置
US08/089,621 US5326222A (en) 1990-12-10 1993-07-12 Bearing arrangement for a thermal turbo machine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP90123734A EP0491966B1 (fr) 1990-12-10 1990-12-10 Dispositif de support d'une turbomachine thermique

Publications (2)

Publication Number Publication Date
EP0491966A1 EP0491966A1 (fr) 1992-07-01
EP0491966B1 true EP0491966B1 (fr) 1994-11-30

Family

ID=8204821

Family Applications (1)

Application Number Title Priority Date Filing Date
EP90123734A Expired - Lifetime EP0491966B1 (fr) 1990-12-10 1990-12-10 Dispositif de support d'une turbomachine thermique

Country Status (4)

Country Link
US (1) US5326222A (fr)
EP (1) EP0491966B1 (fr)
JP (1) JP3112110B2 (fr)
DE (1) DE59007880D1 (fr)

Families Citing this family (19)

* Cited by examiner, † Cited by third party
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DE4232088A1 (de) * 1992-09-25 1994-03-31 Asea Brown Boveri Gasturbine mit Abgasgehäuse und Abgaskanal
DE4232385A1 (de) * 1992-09-26 1994-03-31 Asea Brown Boveri Gasturbine mit angeflanschtem Abgasgehäuse
FR2702243B1 (fr) * 1993-03-03 1995-04-14 Gec Alsthom Electromec Centrale de production d'énergie à turbine à gaz et turbine à vapeur.
US5971702A (en) * 1998-06-03 1999-10-26 Dresser-Rand Company Adjustable compressor bundle insertion and removal system
DE19842811A1 (de) * 1998-09-18 1999-07-15 Siemens Ag Anordnung mit einem Stirnlager in einem axialen Abströmraum, insbesondere einer Dampfturbinenanlage
DE10210174A1 (de) * 2002-03-07 2003-09-25 Alstom Switzerland Ltd Thermische Turbomaschine, insbesondere axialdurchströmte Gasturbine
DE102005052077B4 (de) * 2005-10-28 2016-11-24 Man Diesel & Turbo Se Vorrichtung zur seitlichen Montage und Demontage eines Kompressorbarrels
US8083471B2 (en) * 2007-01-22 2011-12-27 General Electric Company Turbine rotor support apparatus and system
US20110000222A1 (en) * 2007-08-31 2011-01-06 General Electric Company Gas turbine rotor-stator support system
US20110016881A1 (en) * 2009-07-21 2011-01-27 Jose Luis Ruiz Gas turbine with exhaust gas casing and method for producing a gas turbine
US8316523B2 (en) 2009-10-01 2012-11-27 Pratt & Whitney Canada Corp. Method for centering engine structures
JP5554130B2 (ja) 2010-04-14 2014-07-23 三菱重工コンプレッサ株式会社 コンプレッサおよびその組立方法
US8388314B2 (en) * 2011-04-21 2013-03-05 General Electric Company Turbine inlet casing with integral bearing housing
DE102011118735A1 (de) 2011-11-17 2013-05-23 Alstom Technology Ltd. Diffusor, insbesondere für eine axiale strömungsmaschine
US9316117B2 (en) 2012-01-30 2016-04-19 United Technologies Corporation Internally cooled spoke
US10823011B2 (en) 2019-02-07 2020-11-03 Raytheon Technologies Corporation Turbine engine tie rod systems
US11391179B2 (en) 2019-02-12 2022-07-19 Pratt & Whitney Canada Corp. Gas turbine engine with bearing support structure
US11346249B2 (en) 2019-03-05 2022-05-31 Pratt & Whitney Canada Corp. Gas turbine engine with feed pipe for bearing housing
KR102530948B1 (ko) * 2020-12-08 2023-05-09 효성중공업 주식회사 축 발전기용 회전자 지지장치

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US848224A (en) * 1906-03-27 1907-03-26 Edwin S Clough Adjustable bearing.
US1466930A (en) * 1921-12-12 1923-09-04 Cipra Leon Journal bearing
DE768036C (de) * 1937-12-25 1955-05-26 Messerschmitt Boelkow Blohm Befestigung des Endlagers einer Turbinenwelle am Turbinengehaeuse, insbesondere fuer Flugzeugbrennkraftturbinen
US2724621A (en) * 1953-05-26 1955-11-22 Westinghouse Electric Corp Bearing support structure
US2929592A (en) * 1958-02-25 1960-03-22 Theodore W Spaetgens Vibration mounting
US3261587A (en) * 1964-06-24 1966-07-19 United Aircraft Corp Bearing support
US4076452A (en) * 1974-04-09 1978-02-28 Brown, Boveri-Sulzer Turbomaschinen Ag Gas turbine plant
US4150588A (en) * 1976-12-29 1979-04-24 Brewer Engineering Laboratories, Inc. Dynamic vibration absorber
CH619507A5 (fr) * 1977-03-21 1980-09-30 Bbc Brown Boveri & Cie
DE3522916A1 (de) * 1985-06-27 1987-01-08 Kraftwerk Union Ag Turbosatz mit wenigstens einer, ein aussengehaeuse und ein dazu koaxiales innengehaeuse aufweisenden niederdruck-teilturbine und mit hochdruck- und/oder mitteldruck-teilturbine
JPS6453836A (en) * 1987-08-24 1989-03-01 Ibiden Co Ltd Insulating material for high-temperature furnace
FR2646470B1 (fr) * 1989-04-26 1991-07-05 Alsthom Gec Systeme de supportage du rotor dans une turbine a echappement axial avec le palier cote echappement a raideur isotrope, directement flasque sur la fondation
FR2646469B1 (fr) * 1989-04-28 1991-07-05 Alsthom Gec Systeme de supportage du rotor dans une turbine a echappement axial avec le palier cote echappement integre a la fondation
US5178357A (en) * 1989-08-16 1993-01-12 Platus David L Vibration isolation system
FR2651276B1 (fr) * 1989-08-28 1991-10-25 Alsthom Gec Condenseur en beton pour turbine a echappement axial et turbine munie d'un tel condenseur.

Also Published As

Publication number Publication date
EP0491966A1 (fr) 1992-07-01
DE59007880D1 (de) 1995-01-12
JP3112110B2 (ja) 2000-11-27
US5326222A (en) 1994-07-05
JPH04269304A (ja) 1992-09-25

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