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US20150211385A1 - Fluid dynamics machine comprising a rotor and a housing - Google Patents

Fluid dynamics machine comprising a rotor and a housing Download PDF

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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
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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
Application number
US14/420,359
Inventor
Marcel Seiler
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: Seiler, Marcel
Publication of US20150211385A1 publication Critical patent/US20150211385A1/en
Abandoned 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
    • F01D25/28—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)

Abstract

A steam turbine having a rotor and a housing is provided herein, wherein the bearing for supporting the rotor is arranged in front of the last vane stage.

Description

    CROSS REFERENCE TO RELATED APPLICATIONS
  • This application is the U.S. National Stage of International Application No. PCT/EP2013/065585 filed Jul. 24, 2013, and claims the benefit thereof. The International Application claims the benefit of European Application No. EP12181150 filed Aug. 21, 2012. All of the applications are incorporated by reference herein in their entirety.
    • FIELD OF INVENTION
  • 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.
    • BACKGROUND OF INVENTION
  • Relatively long 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. In this case, the rotor is a component which can be several meters long and can weigh several tonnes. In general, 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.
  • In known turbomachines, current turbine section spools are mounted at the shaft ends. To that end, the bearings must frequently be arranged in the steam space. Furthermore, such bearings must be designed such that the bearing casing is connected via struts with the diffuser supported on the base. Constructions of this type are also termed star bearings.
    • SUMMARY OF INVENTION
  • An embodiment of the invention has the object of indicating a turbomachine which is improved in terms of rotor dynamics.
  • This object is achieved with a turbomachine as claimed.
  • It has been recognized, according to embodiments of the invention, that the optimal bearing positions, in terms of stiffness, lie in the case of an evenly loaded shaft at what is termed the Bessel points. These Bessel points are located, following calculations, at approx. 22% of the shaft length from the shaft ends. 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. Inter alia, 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.
  • Advantageous refinements are indicated in the subclaims.
  • It is thus proposed to arrange the second bearing upstream of a final rotor blade stage. That means that the bearing is arranged in the flow duct such that the bearing is arranged upstream of the final rotor blade stage.
  • In a further advantageous embodiment, 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. Henceforth, 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.
  • Advantageously, 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.
  • Furthermore, an embodiment of the invention presents the advantage that larger exhaust flow cross sections can be realized and longer blade paths can be used.
    • BRIEF DESCRIPTION OF THE DRAWINGS
  • Aspects of the invention will be explained in more detail with reference to an exemplary embodiment.
  • The FIGURE shows a cross section view of a steam turbine.
    •  DETAILED DESCRIPTION OF INVENTION
  • 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.
  • In this context, 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.
  • In alternative embodiments, 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.

Claims (5)

1. A turbomachine, 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,
wherein the rotor has, as seen in a flow direction, a first, second, penultimate and a final rotor blade row and the casing has a first, second, penultimate and a final guide vane row, and
wherein the second bearing is arranged in the flow direction between the penultimate and the final rotor blade rows.
2. The turbomachine as claimed in claim 1, wherein the second bearing has a bearing casing and a bearing support formed as guide vanes.
3. The turbomachine as claimed in claim 1, wherein a diffuser is arranged downstream of the final rotor blade row, as seen in the flow direction.
4. The turbomachine as claimed in claim 1, wherein devices for exchanging energy and signals are provided in the bearing support formed as a guide vane.
5. The turbomachine of claim 1, wherein the turbomachine comprises a steam turbine.
US14/420,359 2012-08-21 2013-07-24 Fluid dynamics machine comprising a rotor and a housing Abandoned US20150211385A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP12181150.9A EP2700798A1 (en) 2012-08-21 2012-08-21 Turbomachine comprising a rotor and a casing
EP12181150.9 2012-08-21
PCT/EP2013/065585 WO2014029580A1 (en) 2012-08-21 2013-07-24 Fluid dynamics machine comprising a rotor and a housing

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 (en)
EP (2) EP2700798A1 (en)
JP (1) JP5956077B2 (en)
KR (1) KR20150040929A (en)
CN (1) CN104583563B (en)
IN (1) IN2015DN00390A (en)
WO (1) WO2014029580A1 (en)

Citations (8)

* Cited by examiner, † Cited by third party
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)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0591565B1 (en) * 1992-10-05 1996-01-24 Asea Brown Boveri Ag Stator blade fastening for axial through-flow turbomachines
JP3772019B2 (en) * 1998-04-21 2006-05-10 株式会社東芝 Steam turbine
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 (en) * 2006-12-04 2008-06-11 Siemens Aktiengesellschaft Partial admission turbine
US8511986B2 (en) * 2007-12-10 2013-08-20 United Technologies Corporation Bearing mounting system in a low pressure turbine

Patent Citations (8)

* Cited by examiner, † Cited by third party
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
IN2015DN00390A (en) 2015-06-19
EP2852743A1 (en) 2015-04-01
CN104583563A (en) 2015-04-29
JP5956077B2 (en) 2016-07-20
WO2014029580A1 (en) 2014-02-27
CN104583563B (en) 2016-09-28
EP2700798A1 (en) 2014-02-26
KR20150040929A (en) 2015-04-15
JP2015526639A (en) 2015-09-10

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Legal Events

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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