EP1342885A1 - Thermal turbomaschine, especially axial gas turbine - Google Patents
Thermal turbomaschine, especially axial gas turbine Download PDFInfo
- Publication number
- EP1342885A1 EP1342885A1 EP03405106A EP03405106A EP1342885A1 EP 1342885 A1 EP1342885 A1 EP 1342885A1 EP 03405106 A EP03405106 A EP 03405106A EP 03405106 A EP03405106 A EP 03405106A EP 1342885 A1 EP1342885 A1 EP 1342885A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- bearing
- spring
- inner part
- exhaust gas
- gas turbine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
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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
-
- 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
- F01D25/243—Flange connections; Bolting arrangements
Definitions
- the present invention relates to the field of technology of thermal turbomachinery. It relates in particular to a thermal turbomachine according to the preamble of claim 1.
- the storage of an axially flowed gas turbine is described and shown in the publication mentioned at the beginning.
- This gas turbine follows whose outlet-side blades on an exhaust gas housing, the boundary walls consist essentially of a hub-side, annular inner part and an annular outer part concentrically surrounding the annular inner part.
- the boundary walls delimit and form a diffuser.
- the outlet-side bearing of the rotor of the gas turbine is arranged in the cavity of the inner part and comprises a bearing housed in a bearing housing.
- the bearing housing can be positioned by adjusting elements arranged on the inner part of the exhaust gas housing and is supported on the foundation of the machine by at least one spring support arrangement.
- the spring support arrangement comprises a bar which is led out of the hot diffuser area to the foundation.
- the object is achieved by the entirety of the features of claim 1.
- the essence of the invention is to provide a spring-loaded screw connection within the bearing, which (due to the contact pressure of the screw springs) restores a rigid connection to the bearing star.
- a first embodiment of the turbomachine according to the invention which is particularly preferred because of its simplicity, is characterized in that the bearing saddle part of a bearing star arranged in the inner part of the exhaust gas housing is separable in a horizontal parting plane, and that the spring-loaded screw connection is arranged in the parting plane.
- the spring-loaded screw connection comprises screw springs, which are designed in total for a force of the same order of magnitude as the spring support.
- connection points of the bearing star with the inner part of the exhaust gas housing are arranged symmetrically to the center of the bearing.
- FIG. 2 of EP-A1-0 491 966 the single figure shows a preferred exemplary embodiment of a turbomachine according to the invention in a cross section through the inner part of the exhaust gas housing.
- FIG. 1 of EP-A1-0 491 966 the cross-section through the outlet-side mounting of a gas turbine 10 according to a preferred exemplary embodiment of the invention is shown in a section restricted to the inner part.
- the position of the inner part 11 of the exhaust gas housing within the gas turbine 10 can basically be found in FIG. 1 of EP-A1-0 491 966.
- the outlet-side bearing 15 for the rotor 16 of the gas turbine 10 is arranged in the interior 13 of the inner part 11.
- the bearing 15 is supported by a horizontally lying bearing saddle 14, which is part of a bearing star 17, 18 that can be separated along a parting plane (contact surfaces 26, 27).
- the bearing saddle 14 is connected to the other elements of the bearing star 17, 18 by a spring-loaded screw connection 19, 20, 21, 22, which comprises corresponding screw bolts and screw springs 21, 22.
- the spring-loaded screw connection 19, .., 22 is preferably provided in the horizontal parting plane.
- the bolts go with sufficient clearance through through holes 23, 24 which are provided on both sides of the bearing saddle 14.
- the bearing saddle 14 is supported against the machine foundation by a spring support 25 which extends downward from the inner part 11 and is described and shown in EP-A1-0 491 966. Outside of the inner part 11, the spring support 25 is surrounded by a support formwork ("strut formwork") 12.
- the spring-loaded screw connection 19, .., 22 within the bearing star 17, 18 restores the rigidity of the bearing support which is impaired by the spring support 25.
- the bearing saddle 14 normally lies movably on the contact surfaces 26, 27 of the bearing star 17, 18, since the latter is exposed to greater thermal expansions. In a springless solution, the entire dead weight of rotor 16 and bearing saddle 14 would be transferred via the contact surfaces 26, 27 of the support. According to older experience, this weight load causes a sufficient rigidity of the support, which is now partially or completely canceled by the spring support (25).
- the spring-loaded screw connection 19, .., 22 now replaces the (missing) weight load on the contact surfaces 26, 27 without impairing the effect of relieving the bearing star structure from the permanent load.
- the screw springs 21, 22 are preferably designed in total for a force which is of the same order of magnitude as that of the spring support 25.
- connection points of the bearing star 17, 18 to the inner part 11 of the exhaust gas housing are preferably arranged symmetrically to the position center 28 of the bearing 15.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Support Of The Bearing (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Die vorliegende Erfindung bezieht sich auf das Gebiet der Technik von thermischen Turbomaschinen. Sie betrifft insbesondere eine thermische Turbomaschine gemäss dem Oberbegriff des Anspruchs 1.The present invention relates to the field of technology of thermal turbomachinery. It relates in particular to a thermal turbomachine according to the preamble of claim 1.
Eine solche Maschine und insbesondere deren austrittsseitige Rotorlagerung sind aus der Druckschrift EP-A1-0 491 966 bekannt, deren gesamter Inhalt ausdrücklich Teil der Offenbarung der vorliegenden Anmeldung ist.Such a machine and in particular its rotor bearing on the outlet side are known from EP-A1-0 491 966, the entire content of which is expressly part of the disclosure of the present application.
In der eingangs genannten Druckschrift wird die Lagerung einer axialdurchströmten Gasturbine beschrieben und gezeigt. Bei dieser Gasturbine schliesst sich an deren austrittsseitige Laufschaufeln ein Abgasgehäuse an, dessen Begrenzungswände im wesentlichen aus einem nabenseitigen, ringförmigen Innenteil und einem das ringförmige Innenteil konzentrisch umgebenden, ringförmigen Aussenteil bestehen. Die Begrenzungswände begrenzen und bilden einen Diffusor. Im Hohlraum des Innenteils ist die austrittsseitige Lagerung des Rotors der Gasturbine angeordnet, die ein in einem Lagergehäuse untergebrachtes Lager umfasst. Um die Abstützung der austrittsseitigen Lagerung von den Einflüssen aus Wärmebeanspruchung und Wärmedehnung des Gehäuses und der Diffusorwandungen unabhängig zu machen, ist das Lagergehäuse durch am Innenteil des Abgasgehäuses angeordnete Verstellelemente positionierbar und über mindestens eine Federstützenanordnung am Fundament der Maschine abgestützt. Die Federstützenanordnung umfasst einen Balken, der aus dem heissen Diffusorbereich zum Fundament hin herausgeführt ist.The storage of an axially flowed gas turbine is described and shown in the publication mentioned at the beginning. This gas turbine follows whose outlet-side blades on an exhaust gas housing, the boundary walls consist essentially of a hub-side, annular inner part and an annular outer part concentrically surrounding the annular inner part. The boundary walls delimit and form a diffuser. The outlet-side bearing of the rotor of the gas turbine is arranged in the cavity of the inner part and comprises a bearing housed in a bearing housing. In order to make the support of the outlet-side bearing independent of the influences of thermal stress and thermal expansion of the housing and of the diffuser walls, the bearing housing can be positioned by adjusting elements arranged on the inner part of the exhaust gas housing and is supported on the foundation of the machine by at least one spring support arrangement. The spring support arrangement comprises a bar which is led out of the hot diffuser area to the foundation.
Nachteilig ist bei dieser bekannten Anordnung, dass die vertikale Abstützung der austrittsseitigen Lagerung für eine Turbomaschinenlagerung viel zu elastisch wird.The disadvantage of this known arrangement is that the vertical support of the outlet-side bearing is much too elastic for a turbomachine bearing.
Es ist daher Aufgabe der Erfindung, eine Turbomaschine mit einer abgasseitigen Lagerabstützung zu schaffen, welche eine gegenüber der bekannten Lagerung wesentlich erhöhte Steifigkeit aufweist, ohne die durch die Federabstützung erreichten Vorteile aufzugeben.It is therefore an object of the invention to provide a turbomachine with a bearing support on the exhaust gas side, which has a significantly increased rigidity compared to the known bearing, without giving up the advantages achieved by the spring support.
Die Aufgabe wird durch die Gesamtheit der Merkmale des Anspruchs 1 gelöst. Der Kern der Erfindung besteht darin, innerhalb der Lagerung eine federbelastete Verschraubung vorzusehen, welche (durch den Anpressdruck der Verschraubungsfedern) eine steife Verbindung mit dem Lagerstern wiederherstellt.The object is achieved by the entirety of the features of claim 1. The essence of the invention is to provide a spring-loaded screw connection within the bearing, which (due to the contact pressure of the screw springs) restores a rigid connection to the bearing star.
Eine erste wegen ihrer Einfachheit besonders bevorzugte Ausgestaltung der Turbomaschine nach der Erfindung ist dadurch gekennzeichnet, dass der Lagersattel in einer horizontalen Trennebene abtrennbarer Teil eines im Innenteil des Abgasgehäuses angeordneten Lagersterns ist, und dass die federbelastete Verschraubung in der Trennebene angeordnet ist.A first embodiment of the turbomachine according to the invention, which is particularly preferred because of its simplicity, is characterized in that the bearing saddle part of a bearing star arranged in the inner part of the exhaust gas housing is separable in a horizontal parting plane, and that the spring-loaded screw connection is arranged in the parting plane.
Besonders günstige Verhältnisse ergeben sich für die erfindungsgemässe Lagerung, wenn die federbelastete Verschraubung Verschraubungsfedern umfasst, welche in der Summe für eine Kraft in gleicher Grössenordnung wie die Federstütze ausgelegt sind.Particularly favorable conditions result for the mounting according to the invention if the spring-loaded screw connection comprises screw springs, which are designed in total for a force of the same order of magnitude as the spring support.
Um Momentenbelastungen bei einem Unwuchtstörfall sicher zu vermeiden, ist es von Vorteil, wenn gemäss einer anderen Ausgestaltung der Erfindung die Verbindungsstellen des Lagersterns mit dem Innenteil des Abgasgehäuses symmetrisch zur Lagermitte des Lagers angeordnet sind.In order to reliably avoid moment loads in the event of an imbalance accident, it is advantageous if, according to another embodiment of the invention, the connection points of the bearing star with the inner part of the exhaust gas housing are arranged symmetrically to the center of the bearing.
Die Erfindung soll nachfolgend anhand von Ausführungsbeispielen im Zusammenhang mit der Zeichnung näher erläutert werden. Die einzige Figur zeigt in Anlehnung an die Fig. 2 der EP-A1-0 491 966 in einem Querschnitt durch den Innenteil des Abgasgehäuses ein bevorzugtes Ausführungsbeispiel einer Turbomaschine nach der Erfindung.The invention will be explained in more detail below on the basis of exemplary embodiments in connection with the drawing. Based on FIG. 2 of EP-A1-0 491 966, the single figure shows a preferred exemplary embodiment of a turbomachine according to the invention in a cross section through the inner part of the exhaust gas housing.
In der Figur ist in einem auf den Innenteil beschränkten Ausschnitt der Querschnitt durch die austrittseitige Lagerung einer Gasturbine 10 gemäss einem bevorzugten Ausführungsbeispiel der Erfindung wiedergegeben. Die Position des Innenteils 11 des Abgasgehäuses innerhalb der Gasturbine 10 kann grundsätzlich der Fig. 1 der EP-A1-0 491 966 entnommen werden.In the figure, the cross-section through the outlet-side mounting of a
Im Innenraum 13 des Innenteils 11 ist das austrittsseitige Lager 15 für den Rotor 16 der Gasturbine 10 angeordnet. Das Lager 15 wird von einem horizontal liegenden Lagersattel 14 getragen, der entlang einer Trennebene (Kontaktflächen 26, 27) abtrennbarer Teil eines Lagersterns 17, 18 ist. Der Lagersattel 14 ist mit den übrigen Elementen des Lagersterns 17, 18 durch eine federbelastete Verschraubung 19, 20, 21, 22 verbunden, die entsprechende Schraubbolzen und Verschraubungsfedern 21, 22 umfasst. Die federbelastete Verschraubung 19,..,22 ist vorzugsweise in der horizontalen Trennebene vorgesehen. Die Schraubbolzen gehen dabei mit ausreichendem Spiel durch Durchgangsbohrungen 23, 24, die auf beiden Seiten des Lagersattels 14 vorgesehen sind. Gleichzeitig ist der Lagersattel 14 durch eine nach unten aus dem Innenteil 11 herausgeführte Federstütze 25, wie sie in der EP-A1-0 491 966 beschrieben und gezeigt ist, gegen das Maschinenfundament abgestützt. Ausserhalb des Innenteils 11 ist die Federstütze 25 von einer Stützenverschalung ("Strutverschalung") 12 umgeben.The outlet-side bearing 15 for the
Durch die federbelastete Verschraubung 19,..,22 innerhalb des Lagersterns 17, 18 wird die durch die Federstütze 25 beeinträchtigte Steifigkeit der Lagerabstützung wiederhergestellt. Normalerweise liegt der Lagersattel 14 beweglich auf den Kontaktflächen 26, 27 des Lagersterns 17, 18 auf, da letzterer grösseren Wärmedehnungen ausgesetzt ist. Über die Kontaktflächen 26, 27 der Auflage würde bei einer federstützenlosen Lösung das ganze Eigengewicht von Rotor 16 und Lagersattel 14 übertragen. Diese Gewichtsbelastung bewirkt nach der älteren Erfahrung eine genügende Steifigkeit der Auflage, welche nun durch die Federstütze (25) teils oder ganz aufgehoben wird. Bei einer Lösung mit Federstütze gemäss der Erfindung ersetzt nun die federbelastete Verschraubung 19,..,22 die (fehlende) Gewichtsbelastung auf den Kontaktflächen 26, 27, ohne die Wirkung der Entlastung der Lagersternstruktur von der Dauerbelastung zu beeinträchtigen. Die Verschraubungsfedern 21, 22 werden dabei vorzugsweise in der Summe für eine Kraft ausgelegt, die in der gleichen Grössenordnung wie die der Federstütze 25 liegt.The spring-loaded
Um Momentenbelastungen bei einem Unwuchtsstörfall zu vermeiden, ist es weiterhin von Vorteil, wenn die Verbindungsstellen des Lagersterns 17, 18 zum Innenteil 11 des Abgasgehäuses vorzugsweise symmetrisch zur Lagemitte 28 des Lagers 15 angeordnet sind.In order to avoid moment loads in the event of an imbalance accident, it is furthermore advantageous if the connection points of the
- 1010
- Gasturbinegas turbine
- 1111
- Innenteil (Abgasgehäuse)Inner part (exhaust housing)
- 1212
- Stützenverschalungsupport casing
- 1313
- Innenrauminner space
- 1414
- Lagersattelbearing saddle
- 1515
- Lagercamp
- 1616
- Rotorrotor
- 17,1817.18
- Lagersternbearing star
- 19, 2019, 20
- Verschraubungscrew
- 21,2221.22
- VerschraubungsfederVerschraubungsfeder
- 23,2423.24
- DurchgangsbohrungThrough Hole
- 2525
- Federstützespring support
- 26,2726.27
- Kontaktfläche (Trennebene)Contact surface (parting plane)
- 2828
- Lagermittebearing center
Claims (4)
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE10210174 | 2002-03-07 | ||
| DE10210174A DE10210174A1 (en) | 2002-03-07 | 2002-03-07 | Thermal turbomachine, in particular gas turbine with axial flow |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP1342885A1 true EP1342885A1 (en) | 2003-09-10 |
| EP1342885B1 EP1342885B1 (en) | 2004-09-29 |
Family
ID=27740695
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP03405106A Expired - Fee Related EP1342885B1 (en) | 2002-03-07 | 2003-02-20 | Thermal turbomaschine, especially axial gas turbine |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US6742985B2 (en) |
| EP (1) | EP1342885B1 (en) |
| CN (1) | CN1325763C (en) |
| DE (2) | DE10210174A1 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8388314B2 (en) * | 2011-04-21 | 2013-03-05 | General Electric Company | Turbine inlet casing with integral bearing housing |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3804475A (en) * | 1971-11-09 | 1974-04-16 | R Brucher | Radial bearing with adjustable shaft support |
| US4331366A (en) * | 1979-10-31 | 1982-05-25 | Bbc Brown, Boveri & Company Limited | Combined thrust and support bearing for turbogenerators |
| US5094588A (en) * | 1989-08-28 | 1992-03-10 | Gec Alsthom Sa | Concrete steam condenser for an axial exhaust turbine and turbine provided with same |
| EP0491966A1 (en) * | 1990-12-10 | 1992-07-01 | Asea Brown Boveri Ag | Support device of a thermal turbomachine |
| DE19842811A1 (en) * | 1998-09-18 | 1999-07-15 | Siemens Ag | Waste-steam outflow zone with end-bearing arrangement esp. for steam-turbine plant |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4076452A (en) * | 1974-04-09 | 1978-02-28 | Brown, Boveri-Sulzer Turbomaschinen Ag | Gas turbine plant |
| FR2646470B1 (en) * | 1989-04-26 | 1991-07-05 | Alsthom Gec | ROTOR SUPPORT SYSTEM IN AN AXIAL EXHAUST TURBINE WITH THE ISOTROPICALLY STRAIGHT EXHAUST BEARING, DIRECTLY FLANGE ON THE FOUNDATION |
-
2002
- 2002-03-07 DE DE10210174A patent/DE10210174A1/en not_active Withdrawn
-
2003
- 2003-02-20 DE DE50300090T patent/DE50300090D1/en not_active Expired - Lifetime
- 2003-02-20 EP EP03405106A patent/EP1342885B1/en not_active Expired - Fee Related
- 2003-03-06 US US10/379,687 patent/US6742985B2/en not_active Expired - Lifetime
- 2003-03-06 CN CNB031199259A patent/CN1325763C/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3804475A (en) * | 1971-11-09 | 1974-04-16 | R Brucher | Radial bearing with adjustable shaft support |
| US4331366A (en) * | 1979-10-31 | 1982-05-25 | Bbc Brown, Boveri & Company Limited | Combined thrust and support bearing for turbogenerators |
| US5094588A (en) * | 1989-08-28 | 1992-03-10 | Gec Alsthom Sa | Concrete steam condenser for an axial exhaust turbine and turbine provided with same |
| EP0491966A1 (en) * | 1990-12-10 | 1992-07-01 | Asea Brown Boveri Ag | Support device of a thermal turbomachine |
| DE19842811A1 (en) * | 1998-09-18 | 1999-07-15 | Siemens Ag | Waste-steam outflow zone with end-bearing arrangement esp. for steam-turbine plant |
Also Published As
| Publication number | Publication date |
|---|---|
| DE10210174A1 (en) | 2003-09-25 |
| CN1443928A (en) | 2003-09-24 |
| US6742985B2 (en) | 2004-06-01 |
| EP1342885B1 (en) | 2004-09-29 |
| DE50300090D1 (en) | 2004-11-04 |
| US20030170118A1 (en) | 2003-09-11 |
| CN1325763C (en) | 2007-07-11 |
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