US20150211385A1 - Fluid dynamics machine comprising a rotor and a housing - Google Patents
Fluid dynamics machine comprising a rotor and a housing Download PDFInfo
- Publication number
- US20150211385A1 US20150211385A1 US14/420,359 US201314420359A US2015211385A1 US 20150211385 A1 US20150211385 A1 US 20150211385A1 US 201314420359 A US201314420359 A US 201314420359A US 2015211385 A1 US2015211385 A1 US 2015211385A1
- Authority
- US
- United States
- Prior art keywords
- bearing
- rotor
- turbomachine
- casing
- guide vane
- 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.)
- Abandoned
Links
Images
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
- F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
-
- 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
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
-
- 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
- F01D9/06—Fluid supply conduits to nozzles or the like
- F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/06—Arrangements of bearings; Lubricating
-
- 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
-
- 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
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/321—Application in turbines in gas turbines for a special turbine stage
- F05D2220/3215—Application in turbines in gas turbines for a special turbine stage the last stage of the turbine
Definitions
- the invention relates to a turbomachine, in particular a steam turbine, comprising a rotor which is mounted rotatably and comprises rotor blades, and a casing which is arranged about the rotor, wherein the casing comprises guide vanes, a first bearing and a second bearing for mounting the rotor.
- turbomachines are among the devices employed in the communal supply of power.
- An example of such a turbomachine is a steam turbine having, in essence, a rotor and a casing arranged about the rotor.
- the rotor is a component which can be several meters long and can weigh several tonnes.
- the rotors are mounted rotatably on two bearings, wherein in operation relatively high rotational speeds such as 50 Hz or 60 Hz or more can be reached. Such high rotational frequencies, together with the weight and the length of the rotors, require precise manufacturing such that safe operation is possible.
- the maximum length of such a rotor is limited by the fact that the stiffness of the turbine section spool is limited and cannot be lengthened in conjunction with the rotor-dynamic properties. Furthermore, the maximum length of the rotor is strongly dependent on the position of the bearing locations and the manner in which the bearing casing is supported.
- An embodiment of the invention has the object of indicating a turbomachine which is improved in terms of rotor dynamics.
- Embodiments of the invention thus proposes displacing at least one bearing such that the rotor-dynamic properties are fundamentally improved. To that end, it is proposed that the bearing is arranged upstream of a guide vane stage, as seen in a flow direction. It is thus proposed that the bearing is not arranged as a separate component at the end of the rotor, but rather that it is integrated into the blade path of the turbomachine. To that end, it is first proposed that the bearing is arranged upstream of a rotor blade stage.
- an embodiment of the invention presents the advantage that the bearing casing can henceforth be borne by a guide vane stage without additional bearing supports.
- the bearing casing is arranged on bearing supports which are formed as guide vanes. That means that the bearing supports fulfill a thermodynamic function, specifically the thermodynamic function of a guide vane. That means that the bearing supports are formed such that they follow a fluid-dynamic profile which is predetermined by a guide vane stage.
- the bearing displaced into the flow path can thus also fulfill thermodynamic properties, in addition to the rotor-dynamic properties, since the bearing supports are also formed as guide vanes.
- a diffuser is preferably arranged downstream of the final rotor blade stage.
- the diffuser advantageously no longer has any disruptive bearing supports in the flow path and can thus carry out the pressure recovery in a more targeted manner.
- the bearing support formed as a guide vane is designed so as to have a device for exchanging energy and signals.
- the invention delivers the advantage that a bearing integrated in the guide vane stage henceforth requires less axial installation space and permits a smaller separation with respect to the condenser. Since the bearing is borne by the guide vane stage, no bearing supports are required, which would lead to material and manufacturing costs and would hinder the exhaust flow to the condenser. Furthermore, the stiffness of the turbine section spool is substantially increased, leading to markedly improved rotor dynamics. This can permit a reduction in radial clearances in order to further improve efficiency.
- an embodiment of the invention presents the advantage that larger exhaust flow cross sections can be realized and longer blade paths can be used.
- the FIGURE shows a cross section view of a steam turbine.
- the FIGURE shows an embodiment of a turbomachine, designed as a steam turbine 1 .
- This steam turbine 1 comprises, in essence, a rotor 3 which is mounted such that it can rotate about an axis of rotation 2 , on which rotor a first rotor blade stage 5 , a second rotor blade stage 6 and a third rotor blade stage 7 are arranged on the rotor surface 4 .
- the steam turbine 1 further comprises a casing (not shown in more detail) which is arranged around the rotatably mounted rotor 3 .
- a first guide vane stage 8 , a second guide vane stage 9 and a third guide vane stage 10 are arranged on the casing.
- a flow path 11 is formed between the first 5 , second 6 and third 7 rotor blade stages and the first 8 , second 9 and third 10 guide vane stages, through which flow path steam flows in operation.
- the rotor 3 is mounted on a base 12 by means of a first bearing 13 and a second bearing 14 .
- the first bearing 13 is arranged at a first end 15 of the rotor 3 .
- the second bearing 14 is arranged at a second end 16 .
- the second bearing 14 is arranged in the flow path 11 upstream of the third rotor blade stage 7 , that is to say consequently the final rotor blade stage.
- the bearing comprises a bearing casing 17 which is arranged around the second bearing 14 .
- a bearing support 19 formed as a guide vane is arranged on the bearing casing. Since the bearing support 19 formed as a guide vane is arranged in the flow path 11 , this bearing support 19 formed as a guide vane participates in the conversion of the energy of the steam in the flow path 11 .
- a diffuser 20 in which a pressure recovery of the steam in the flow path 11 takes place, is arranged downstream of the third rotor blade stage 7 .
- the bearing support 19 formed as a guide vane, with the second bearing 14 can also be arranged upstream of the second rotor blade stage 6 or even further upstream in the flow path 11 .
- Devices 21 for exchanging energy and signals are provided in the bearing support 19 formed as a guide vane.
- the rotor ( 3 ) has, as seen in the flow direction, a first, second, penultimate and final rotor blade row.
- the casing has, as seen in the flow direction, a first, second, penultimate and final guide vane row.
- the second bearing is arranged between the penultimate and the final rotor blade rows.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP12181150.9A EP2700798A1 (de) | 2012-08-21 | 2012-08-21 | Strömungsmaschine umfassend einen Rotor und ein Gehäuse |
EP12181150.9 | 2012-08-21 | ||
PCT/EP2013/065585 WO2014029580A1 (de) | 2012-08-21 | 2013-07-24 | Strömungsmaschine umfassend einen rotor und ein gehäuse |
Publications (1)
Publication Number | Publication Date |
---|---|
US20150211385A1 true US20150211385A1 (en) | 2015-07-30 |
Family
ID=46967941
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US14/420,359 Abandoned US20150211385A1 (en) | 2012-08-21 | 2013-07-24 | Fluid dynamics machine comprising a rotor and a housing |
Country Status (7)
Country | Link |
---|---|
US (1) | US20150211385A1 (de) |
EP (2) | EP2700798A1 (de) |
JP (1) | JP5956077B2 (de) |
KR (1) | KR20150040929A (de) |
CN (1) | CN104583563B (de) |
IN (1) | IN2015DN00390A (de) |
WO (1) | WO2014029580A1 (de) |
Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2919888A (en) * | 1957-04-17 | 1960-01-05 | United Aircraft Corp | Turbine bearing support |
US3327473A (en) * | 1966-01-11 | 1967-06-27 | Gen Motors Corp | Engine support structure |
GB1605252A (en) * | 1976-12-17 | 1986-06-04 | Rolls Royce | Gas turbine engines |
US6030176A (en) * | 1995-07-19 | 2000-02-29 | Siemens Aktiengesellschaft | Structural member for an exhaust-gas connection of a turbomachine, in particular a steam turbine, and set of at least two structural members |
US7523615B2 (en) * | 2005-03-30 | 2009-04-28 | General Electric Company | Telemetry system |
US20110268562A1 (en) * | 2010-04-30 | 2011-11-03 | General Electric Company | Gas turbine engine airfoil integrated heat exchanger |
US20140013771A1 (en) * | 2012-07-13 | 2014-01-16 | United Technologies Corporation | Mid-turbine frame with threaded spokes |
US8641365B2 (en) * | 2007-03-12 | 2014-02-04 | Siemens Aktiengesellschaft | Rotor of a gas turbine |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0591565B1 (de) * | 1992-10-05 | 1996-01-24 | Asea Brown Boveri Ag | Leitschaufeleinhängung für axialdurchströmte Turbomaschine |
JP3772019B2 (ja) * | 1998-04-21 | 2006-05-10 | 株式会社東芝 | 蒸気タービン |
US7513102B2 (en) * | 2005-06-06 | 2009-04-07 | General Electric Company | Integrated counterrotating turbofan |
US7632064B2 (en) * | 2006-09-01 | 2009-12-15 | United Technologies Corporation | Variable geometry guide vane for a gas turbine engine |
EP1930543A1 (de) * | 2006-12-04 | 2008-06-11 | Siemens Aktiengesellschaft | Teilbeaufschlagte Turbine |
US8511986B2 (en) * | 2007-12-10 | 2013-08-20 | United Technologies Corporation | Bearing mounting system in a low pressure turbine |
-
2012
- 2012-08-21 EP EP12181150.9A patent/EP2700798A1/de not_active Withdrawn
-
2013
- 2013-07-24 US US14/420,359 patent/US20150211385A1/en not_active Abandoned
- 2013-07-24 KR KR1020157003908A patent/KR20150040929A/ko not_active Application Discontinuation
- 2013-07-24 CN CN201380044360.5A patent/CN104583563B/zh not_active Expired - Fee Related
- 2013-07-24 JP JP2015527827A patent/JP5956077B2/ja not_active Expired - Fee Related
- 2013-07-24 WO PCT/EP2013/065585 patent/WO2014029580A1/de active Application Filing
- 2013-07-24 EP EP13745011.0A patent/EP2852743A1/de not_active Withdrawn
-
2015
- 2015-01-16 IN IN390DEN2015 patent/IN2015DN00390A/en unknown
Patent Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2919888A (en) * | 1957-04-17 | 1960-01-05 | United Aircraft Corp | Turbine bearing support |
US3327473A (en) * | 1966-01-11 | 1967-06-27 | Gen Motors Corp | Engine support structure |
GB1605252A (en) * | 1976-12-17 | 1986-06-04 | Rolls Royce | Gas turbine engines |
US6030176A (en) * | 1995-07-19 | 2000-02-29 | Siemens Aktiengesellschaft | Structural member for an exhaust-gas connection of a turbomachine, in particular a steam turbine, and set of at least two structural members |
US7523615B2 (en) * | 2005-03-30 | 2009-04-28 | General Electric Company | Telemetry system |
US8641365B2 (en) * | 2007-03-12 | 2014-02-04 | Siemens Aktiengesellschaft | Rotor of a gas turbine |
US20110268562A1 (en) * | 2010-04-30 | 2011-11-03 | General Electric Company | Gas turbine engine airfoil integrated heat exchanger |
US20140013771A1 (en) * | 2012-07-13 | 2014-01-16 | United Technologies Corporation | Mid-turbine frame with threaded spokes |
Also Published As
Publication number | Publication date |
---|---|
JP5956077B2 (ja) | 2016-07-20 |
IN2015DN00390A (de) | 2015-06-19 |
CN104583563B (zh) | 2016-09-28 |
EP2700798A1 (de) | 2014-02-26 |
JP2015526639A (ja) | 2015-09-10 |
EP2852743A1 (de) | 2015-04-01 |
WO2014029580A1 (de) | 2014-02-27 |
CN104583563A (zh) | 2015-04-29 |
KR20150040929A (ko) | 2015-04-15 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: SIEMENS AKTIENGESELLSCHAFT, GERMANY Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:SEILER, MARCEL;REEL/FRAME:034912/0989 Effective date: 20150113 |
|
STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |