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US20150003965A1 - Turbomachine for generating power having a temperature measurement device in a region of the rotor - Google Patents

Turbomachine for generating power having a temperature measurement device in a region of the rotor Download PDF

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Publication number
US20150003965A1
US20150003965A1 US14/241,172 US201214241172A US2015003965A1 US 20150003965 A1 US20150003965 A1 US 20150003965A1 US 201214241172 A US201214241172 A US 201214241172A US 2015003965 A1 US2015003965 A1 US 2015003965A1
Authority
US
United States
Prior art keywords
rotor
turbomachine
region
temperature measurement
retaining element
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
US14/241,172
Other languages
English (en)
Inventor
Guido Ahaus
Ingo Balkowski
Patrick Ronald Flohr
Waldemar Heckel
Harald Hoell
Christian Lyko
Oliver Ricken
Uwe Sieber
Sebastian Stock
Vyacheslav Veitsman
Frank Woditschka
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: FLOHR, PATRICK RONALD, Ricken, Oliver, Heckel, Waldemar, Stock, Sebastian, HOELL, HARALD, SIEBER, UWE, VEITSMAN, VYACHESLAV, AHAUS, GUIDO, Balkowski, Ingo, Lyko, Christian, WODITSCHKA, FRANK
Publication of US20150003965A1 publication Critical patent/US20150003965A1/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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/02—Arrangement of sensing elements
    • F01D17/08—Arrangement of sensing elements responsive to condition of working-fluid, e.g. pressure
    • F01D17/085—Arrangement of sensing elements responsive to condition of working-fluid, e.g. pressure to temperature
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/003—Arrangements for testing or measuring
    • 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
    • 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
    • F01D5/10—Anti- vibration means
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
    • G01K1/00—Details of thermometers not specially adapted for particular types of thermometer
    • G01K1/16—Special arrangements for conducting heat from the object to the sensitive element
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
    • G01K13/00—Thermometers specially adapted for specific purposes
    • G01K13/04—Thermometers specially adapted for specific purposes for measuring temperature of moving solid bodies
    • G01K13/08—Thermometers specially adapted for specific purposes for measuring temperature of moving solid bodies in rotary movement

Definitions

  • the invention relates to a turbomachine having a rotor, wherein the rotor comprises a central retaining element and rotor elements arranged thereon.
  • a turbomachine is a fluid energy machine in which energy is transferred between fluid and machine in an open space by means of a flow according to the laws of fluid dynamics via kinetic energy. Energy is normally transferred by means of rotor blades which are shaped such that the flow around them produces a pressure difference between the front and back sides (wing profile).
  • a turbomachine typically consists of a rotating part, the rotor, and a stationary part, the stator.
  • a gas turbine is a turbomachine in which a gas under pressure expands. It consists of a turbine or expander, a compressor connected upstream thereof, and a combustor connected between the two.
  • the working principle is based on the cyclic process (Joule process): this compresses air by means of the blading of one or more compressor stages, then mixes this air with a gaseous or liquid fuel in the combustor and ignites and combusts the mixture.
  • the air is used for cooling, in particular of components subjected to high thermal stresses.
  • the rotor of a turbomachine is a component which is subjected to high thermal and mechanical stresses. It conventionally consists of a central retaining element, a shaft or axle, to which are attached the remaining rotating elements such as disks and rotor blades. In particular in the case of a cold start of the turbomachine, the rotor disks are in this case subjected to very high stresses. On one hand, the rotors experience considerable heating in the region of the blade roots, and on the other hand cooling air flows through the rotor so that the temperature of the material does not exceed the strength limits.
  • FEM finite element method
  • the boundary conditions are determined using individual prototype measurements. Sample measurements of the temperature of individual rotor components are also carried out here in part.
  • the data obtained in this manner are used, on one hand, to estimate the maximum number of start cycles that a rotor can withstand before it has to be replaced and, on the other hand, to estimate a rotor preheat time, which is necessary in certain cases in order to reduce thermal stresses to an acceptable level and to keep the number of permitted start cycles high enough.
  • waiting a certain time before commencement of operation of the rotor always implies increased energy consumption and a longer startup time for the turbomachine, which is undesirable, particularly for example in the case of gas turbine and steam turbine power plants, as these often have to cover peak power requirements of the electrical grid at short notice.
  • a contact element being arranged in a region of the rotor between the retaining element and the rotor element, wherein the contact element comprises a temperature measurement device.
  • the invention thus proceeds from the consideration that faster startup and better estimation of the lifespan would be possible in particular if especially precise and up-to-date data on the temperature behavior of the rotor of a turbomachine for generating power were made available.
  • An estimation of this kind must, however, always be conservative with respect to operational safety and lifespan. This can for example have the consequence that, during startup, there is an unnecessarily long wait for the corresponding temperature conditions or even that the process of starting the turbomachine is locked, even though the required material temperature has been reached, as the temperature formula has estimated the temperature as too low.
  • the temperature must be determined still more precisely. This can be achieved by directly measuring the temperature in that region of the rotor which is of interest. This is however problematic in that certain regions of the rotor, in particular the disk hubs subjected to particularly high thermal stresses, are arranged inside the turbomachine and access to these is therefore difficult.
  • a means should be found to measure the material temperature using an appropriate arrangement of a temperature measurement device. This can be achieved by the temperature measurement device being arranged in a contact element between the rotor element to be measured and the retaining element of the rotor. This can be effected with the aid of temperature converters such as resistance sensors or thermocouples. The contact element is then pressed against the retaining element by centrifugal force during rotation of the rotor, thus ensuring good contact and good heat transfer.
  • the central rotor element is a tie rod and/or the rotor element is a rotor disk, i.e. the contact element is located between the tie rod and the rotor disks attached thereto.
  • Contact elements can thus be attached to all disks over the entire axial length and the temperature of these can thus be detected.
  • said region of the rotor is the region which is subjected to the highest thermal loads in comparison to other regions. Indeed, not all regions of the rotor of the turbomachine are subjected to the same level of load in operation. Thus, for example, the disk hubs of the rotor are comparatively highly loaded parts. In order that a temperature measurement does not need to be carried out in all regions, it should be ensured that in every case the highly loaded regions which are critical for calculating the lifespan are precisely measured.
  • the contact element is mounted rotatably on an axle, wherein the axle is attached to the central retaining element.
  • the contact element is configured as a pawl which is attached to the central retaining element, in particular the tie rod.
  • this pawl moves, under the effect of centrifugal force, outward on the side facing away from the axle and wedges the surrounding rotor component, in particular the rotor disk.
  • the pawl thus serves two purposes: on one hand to attach and centrally and symmetrically secure the rotor disk, and on the other hand in the chain of transmitting the signal of the disk temperature to the pawl temperature, data transmission and monitoring.
  • the pawls may also be used to damp oscillations in the rotor.
  • An advantageous embodiment of the pawl is in this case such that even at turning rotational speed, i.e. when the turbomachine is started up, it bears against the disk with sufficient force and such that at operating speed it allows a relative expansion of the rotor components.
  • the contact element advantageously comprises a thermally conductive material on its side facing the rotor element. This ensures a particularly good transfer of heat from the region to be measured on the rotor disk to the temperature measurement device, which improves the quality of the temperature determination.
  • the contact element comprises an insulating material on its side facing the central retaining element. This prevents an input of heat or a loss of heat in the direction of the central tie rod. This also improves the quality of the temperature determination.
  • the central retaining element advantageously comprises, in the region of a bearing assigned to it, a transmitter connected to the temperature measurement device on the data side and serving to transmit the temperature data.
  • the data line from the temperature measurement device thus runs on or in the central retaining element, e.g. the tie rod to the bearing, which is typically arranged in an outer region.
  • the transmitter can for example be designed according to the inductive principle or by means of sliding contacts and thus allows signals to be transmitted to the stationary components.
  • An embodiment of this type can be operationally active for long periods of operation. For reasons of good accessibility, positioning the transmitter on a bearing also makes it possible to carry out maintenance without dismantling the rotor.
  • a plurality of contact elements is arranged symmetrically about the central retaining element. This avoids imbalances and allows temperature measurement over the entire circumference.
  • the turbomachine is advantageously a gas turbine. Specifically in gas turbines, whose components, in particular the rotor, are subjected to the highest thermal and mechanical stresses, the described configuration is of considerable advantage with respect to determining lifespan and reduces the startup time without sacrificing operational safety or lifespan.
  • a turbomachine of this type is advantageously used in a power plant.
  • the advantages achieved with the invention are in particular that, by virtue of measuring over the entire lifespan of the turbomachine, up-to-date data on the temperature behavior of the rotor are available. With the aid of these data, substantially more precise lifespan estimates for rotors can be made, and the number of permissible starts, corresponding to physical actualities, can be adapted in an up-to-date manner. This is an immediate industrial advantage for the operator, in particular in the case of installations with frequent cold starts.
  • continuous temperature measurement permits a better estimation of the rotor lifespan and a shortening of the startup process without reducing the lifespan. In addition to the time saving and thus increased flexibility, less energy is also used for startup. Direct temperature measurement, together with the signal line in the region of the bearings, further presents a particularly maintenance-friendly system for continuous temperature measurement.
  • FIG. 1 shows an axial section through a gas turbine
  • FIG. 2 shows an axial section through a partial region of the rotor of the gas turbine of FIG. 1 .
  • FIG. 3 shows a radial section through a contact element of the gas turbine.
  • a gas turbine 101 as shown in FIG. 1 is a turbomachine. It has a compressor 102 for combustion air, a combustor 104 and a turbine unit 106 for driving the compressor 102 and a generator (not shown) or a work machine. To that end, the turbine unit 106 and the compressor 102 are arranged on a common turbine shaft 108 , also termed the turbine rotor, to which the generator or, as the case may be, the work machine is also connected, and which is mounted rotatably about its central axis 109 . These units form the rotor of the gas turbine 101 .
  • the combustor 104 which is embodied as an annular combustor, is equipped with a number of burners 110 for burning a liquid or gaseous fuel.
  • the turbine unit 106 has a number of rotary rotor blades 112 which are connected to the turbine shaft 108 .
  • the rotor blades 112 are arranged in a ring shape on the turbine shaft 108 and thus form a number of rotor blade rings or rows.
  • the turbine unit 106 further comprises a number of stationary guide vanes 114 which are attached, also in a ring shape, to a guide vane carrier 116 of the turbine unit 106 so as to form guide vane rows.
  • the rotor blades 112 serve in this context to drive the turbine shaft 108 by impulse transfer from the working medium M which flows through the turbine unit 106 .
  • the guide vanes 114 serve, on the other hand, to guide the flow of the working medium M between in each case two successive—as seen in the direction of flow of the working medium M—rotor blade rows or rotor blade rings.
  • Each guide vane 114 has a platform 118 which is arranged as a wall element for fixing the respective guide vane 114 to a guide vane carrier 116 of the turbine unit 106 .
  • the platform 118 is in this context a component which is subjected to comparatively high thermal loads and which forms the outer limit of a hot gas channel for the working medium M which flows through the turbine unit 106 .
  • Each rotor blade 112 is, in analogous fashion, attached to the turbine shaft 108 by means of a platform 119 , also termed the blade root.
  • a ring segment 121 is in each case arranged on a guide vane carrier 116 of the turbine unit 106 between the spaced apart platforms 118 of the guide vanes 114 of two adjacent guide vane rows.
  • the outer surface of each ring segment 121 is in this context also exposed to the hot working medium M flowing through the turbine unit 106 , and is separated in the radial direction from the outer end of the rotor blades 112 located opposite by a gap.
  • the ring segments 121 arranged between adjacent guide vane rows serve in this context in particular as covering elements which protect the interior housing in the guide vane carrier 116 , or other integrated housing parts, from thermal overloading caused by the hot working medium M which is flowing through the turbine 106 .
  • the combustor 104 is configured as what is termed an annular combustor, wherein a multiplicity of burners 110 , arranged around the turbine shaft 108 in the circumferential direction, open into a common combustor space. To that end, the combustor 104 is configured in its entirety as an annular structure which is positioned around the turbine shaft 108 .
  • the gas turbine 101 is configured for a temperature measurement in the rotor. This is shown in FIG. 2 , which represents an enlarged section through the rotor of the gas turbine 101 .
  • FIG. 1 This shows the more detailed construction of the rotor in axial section: the already-described rotor blades 112 of the turbine unit 106 are in each case attached, together with the platforms 119 , to one rotor disk 122 per rotor blade row.
  • the rotor disks 122 are attached to a tie rod 124 .
  • a pawl 126 which is rotatably attached to an axle 128 by means of nuts 130 , is arranged in the region subjected to the greatest thermal load.
  • a data line 132 leads to a temperature measurement device 134 in the pawl 126 .
  • FIG. 3 shows a radial section through the rotor, wherein the shape of the pawl 126 can be seen.
  • the temperature measurement device 134 is arranged in the region facing the rotor disk 122 . A material with good thermal conductivity is applied on top of it and an insulator underneath it.
  • the data line 132 leads from the temperature measurement device 134 to a bearing (not shown) of the rotor, where it leads into a transmitter which transmits the temperature data to stationary components.
  • the pawl 126 When the tie rod 124 rotates with the rotor, the pawl 126 is pressed against the rotor disk 122 such that there exists a good transfer of heat to the temperature measurement device 134 .
  • the pawl 126 thus fulfills multiple functions: on one hand it secures the rotor disk and provides radial equalization, on the other hand it serves as a transmission member in the temperature measurement. In addition, the pawl 126 serves to damp oscillations.
  • the startup time of the gas turbine 101 is on one hand reduced.
  • temperature data for the rotor are available, which permits particularly precise predictions with respect to the lifespan of the gas turbine 101 .

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US14/241,172 2011-08-29 2012-08-02 Turbomachine for generating power having a temperature measurement device in a region of the rotor Abandoned US20150003965A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP11179152.1 2011-08-29
EP11179152A EP2565605A1 (de) 2011-08-29 2011-08-29 Strömungsmaschine mit einer Temperaturmesseinrichtung in einem Bereich des Rotors
PCT/EP2012/065098 WO2013029908A1 (de) 2011-08-29 2012-08-02 Strömungsmaschine zur energierzeugung mit einer temperaturmesseinrichtung in einem bereich des rotors

Publications (1)

Publication Number Publication Date
US20150003965A1 true US20150003965A1 (en) 2015-01-01

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US14/241,172 Abandoned US20150003965A1 (en) 2011-08-29 2012-08-02 Turbomachine for generating power having a temperature measurement device in a region of the rotor

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US (1) US20150003965A1 (de)
EP (2) EP2565605A1 (de)
WO (1) WO2013029908A1 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150016949A1 (en) * 2013-07-09 2015-01-15 Rolls-Royce Plc Tip clearance control method
US20180343259A1 (en) * 2017-04-21 2018-11-29 InfoSci, LLC Systems and methods for device verification and authentication

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3062050A (en) * 1959-04-15 1962-11-06 Napier & Son Ltd Gas turbines
US4426161A (en) * 1981-12-22 1984-01-17 Westinghouse Electric Corp. Turbine disc cavity temperature sensing arrangement
US4455530A (en) * 1982-03-30 1984-06-19 Westinghouse Electric Corp. Conductivity sensor for use in steam turbines
US5080496A (en) * 1990-06-25 1992-01-14 General Electric Company Method and apparatus for compensated temperature prediction
US5537864A (en) * 1993-12-10 1996-07-23 Solar Turbines Incorporated Apparatus and method for determining and controlling combustor primary zone temperature
US6109783A (en) * 1997-08-21 2000-08-29 Abb Research Ltd. Optic pyrometer for gas turbines
US20090121896A1 (en) * 2007-11-08 2009-05-14 Siemens Power Generation, Inc. Instrumented Component for Wireless Telemetry
US7582359B2 (en) * 2002-09-23 2009-09-01 Siemens Energy, Inc. Apparatus and method of monitoring operating parameters of a gas turbine
US20110133950A1 (en) * 2007-11-08 2011-06-09 Ramesh Subramanian Instrumented component for wireless telemetry
US20110133949A1 (en) * 2007-11-08 2011-06-09 Ramesh Subramanian Instrumented component for wireless telemetry

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5560610A (en) * 1978-10-27 1980-05-07 Toshiba Corp Apparatus for reducing thermal stress produced in rotor of steam turbine
JPS5783611A (en) * 1980-11-14 1982-05-25 Hitachi Ltd Method and device for monitoring temperature of turbine rotor
DE19857453B4 (de) * 1998-12-12 2008-03-20 Pfeiffer Vacuum Gmbh Temperaturüberwachung an Rotoren von Vakuumpumpen
US8221057B2 (en) * 2008-06-25 2012-07-17 General Electric Company Method, system and controller for establishing a wheel space temperature alarm in a turbomachine
ITMI20101918A1 (it) * 2010-10-20 2012-04-21 Ansaldo Energia Spa Impianto a turbina a gas per la produzione di energia elettrica, provvisto di un'apparecchiatura per il monitoraggio di parti rotanti

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3062050A (en) * 1959-04-15 1962-11-06 Napier & Son Ltd Gas turbines
US4426161A (en) * 1981-12-22 1984-01-17 Westinghouse Electric Corp. Turbine disc cavity temperature sensing arrangement
US4455530A (en) * 1982-03-30 1984-06-19 Westinghouse Electric Corp. Conductivity sensor for use in steam turbines
US5080496A (en) * 1990-06-25 1992-01-14 General Electric Company Method and apparatus for compensated temperature prediction
US5537864A (en) * 1993-12-10 1996-07-23 Solar Turbines Incorporated Apparatus and method for determining and controlling combustor primary zone temperature
US6109783A (en) * 1997-08-21 2000-08-29 Abb Research Ltd. Optic pyrometer for gas turbines
US7582359B2 (en) * 2002-09-23 2009-09-01 Siemens Energy, Inc. Apparatus and method of monitoring operating parameters of a gas turbine
US20090121896A1 (en) * 2007-11-08 2009-05-14 Siemens Power Generation, Inc. Instrumented Component for Wireless Telemetry
US20110133950A1 (en) * 2007-11-08 2011-06-09 Ramesh Subramanian Instrumented component for wireless telemetry
US20110133949A1 (en) * 2007-11-08 2011-06-09 Ramesh Subramanian Instrumented component for wireless telemetry

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150016949A1 (en) * 2013-07-09 2015-01-15 Rolls-Royce Plc Tip clearance control method
US20180343259A1 (en) * 2017-04-21 2018-11-29 InfoSci, LLC Systems and methods for device verification and authentication

Also Published As

Publication number Publication date
EP2565605A1 (de) 2013-03-06
EP2724131A1 (de) 2014-04-30
WO2013029908A1 (de) 2013-03-07
EP2724131B1 (de) 2016-03-23

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