EP1900907A2 - System zur Turbinenschaufelspitzen-Abstandsreduktion für einen Turbinenmotor - Google Patents

System zur Turbinenschaufelspitzen-Abstandsreduktion für einen Turbinenmotor Download PDF

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Publication number
EP1900907A2
EP1900907A2 EP07113096A EP07113096A EP1900907A2 EP 1900907 A2 EP1900907 A2 EP 1900907A2 EP 07113096 A EP07113096 A EP 07113096A EP 07113096 A EP07113096 A EP 07113096A EP 1900907 A2 EP1900907 A2 EP 1900907A2
Authority
EP
European Patent Office
Prior art keywords
turbine
turbine blade
ring segments
tips
vane carrier
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.)
Withdrawn
Application number
EP07113096A
Other languages
English (en)
French (fr)
Other versions
EP1900907A3 (de
Inventor
Gennadiy Afanasiev
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 Energy Inc
Original Assignee
Siemens Energy Inc
Siemens Power Generations Inc
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 Energy Inc, Siemens Power Generations Inc filed Critical Siemens Energy Inc
Publication of EP1900907A2 publication Critical patent/EP1900907A2/de
Publication of EP1900907A3 publication Critical patent/EP1900907A3/de
Withdrawn legal-status Critical Current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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/22—Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2250/00—Geometry
    • F05D2250/40—Movement of components

Definitions

  • This invention is directed generally to turbine engines, and more particularly to systems for reducing the gap between the tips of rotatable turbine blades attached to a rotary turbine blade assembly and ring segments attached to a vane carrier when the turbine engine is operating at steady state conditions.
  • gas turbine engines typically include a compressor for compressing air, a combustor for mixing the compressed air with fuel and igniting the mixture, and a turbine blade assembly for producing power.
  • Combustors often operate at high temperatures that may exceed 2,500 degrees Fahrenheit.
  • Typical turbine combustor configurations expose turbine blade assemblies to these high temperatures.
  • turbine blades must be made of materials capable of withstanding such high temperatures.
  • Turbine blades and other components often contain cooling systems for prolonging the life of the blades and reducing the likelihood of failure as a result of excessive temperatures.
  • Turbine blades typically extend radially from a rotor assembly and terminate at a tip within close proximity of the ring segments attached to a vane carrier.
  • the ring segments may be exposed to the hot combustion gases and, similar to the turbine blades, the ring segments often rely on internal cooling systems to reduce stress and increase the life cycle.
  • the ring segments are spaced radially from the turbine blade tips to create a gap therebetween to prevent contact of the turbine blade tips with the ring segments as a result of thermal expansion of the turbine blades.
  • turbine blades and ring segments pass through a pinch point at which the gap between the turbine blade tips and the ring segments is at a minimal distance due to thermal expansion.
  • the turbine blade tips of many conventional configurations contact or nearly contact the ring segments. Contact of the turbine blade tips may cause damage to the blades. Furthermore, designing the gap between the turbine blade tips and the ring segments for the pinch point often results in a gap at steady state conditions that is larger than desired because the gap and combustion gases flowing therethrough adversely affect performance and efficiency.
  • One conventional system includes moving the rotor axially to reduce the gap. however, moving the rotor axially within the turbine engine causes an increase in the gaps at the compressor blade tips, thereby increasing inefficiencies in the compressor. Thus, a need exists for a more effective way of enabling turbine blade tips to pass through the pinch point without contacting the ring segments, yet reduce the size of the gap at steady state operating conditions.
  • This invention is directed to a turbine blade gap control system for reducing a gap formed between turbine blades and ring segments in turbine engines. Reducing the gap increases the efficiency of the turbine engine by reducing the amount of combustion gases flowing around the turbine blades rather than through the blades.
  • the turbine blade gap control system may be configured to enable the turbine engine to go through start up conditions, through a pinch point in the start up process before steady state operation where the tips of the turbine blades are closest to the ring segments and into a steady state condition.
  • the turbine blade gap control system may be configured to reduce the size of the gap at steady state operating conditions by moving a vane carrier to which the ring segments are attached axially. Such axial movement may reduce the gap between the tips of turbine blades and ring segments in turbine engines in which the tips of the turbine blades are positioned at an acute angle relative to a rotational axis and the ring segments are positioned in a similar manner.
  • the turbine engine may include a turbine blade assembly formed from a plurality rows of turbine blades extending radially from a rotor. Each row may be formed from a plurality of turbine blades. The turbine blades may have tips positioned at an acute angle relative to a rotational axis of the turbine blade assembly.
  • the turbine engine may also include a vane carrier concentric with the rotor and positioned radially outward from the turbine blades.
  • a plurality of ring segments may be attached to the vane carrier and positioned between the vane carrier and the tips of the turbine blades in each row. An inner surface of each of the ring segments may be offset radially outward from the tips of the turbine blades creating gaps so that the turbine blades may rotate without contact.
  • the ring segments may be positioned at an acute angle substantially equal to the acute angle at which the turbine blade tips are positioned.
  • the turbine engine may also include a turbine blade gap control system configured to move the vane carrier and attached ring segments axially relative to the turbine blade assembly to reduce the gaps between the tips of the turbine blades and the ring segments.
  • the turbine blade gap control system may include one or more hydraulic arms attached to the vane carrier for moving the vane carrier axially relative to the turbine blade assembly.
  • the hydraulic arm may be attached to an outer cylinder or other turbine engine support structure positioned radially outward from the vane carrier.
  • the hydraulic arm may be formed from four hydraulic arms positioned around the outer cylinder. The hydraulic arms may be positioned generally 90 degrees from each other around the outer cylinder.
  • the invention may also include a method of reducing gaps between tips of turbine blades in a turbine engine and adjacent ring segments.
  • the method may include operating a turbine engine by bringing the turbine engine to a steady state operating condition and reducing the gaps between the tips of the turbine blades and the ring segment by using the turbine blade gap control system to move the vane carrier axially relative to the turbine blade assembly.
  • Operating a turbine engine may include using a turbine blade gap control system including one or more hydraulic arms attached to the vane carrier for moving the vane carrier axially relative to the turbine blade assembly.
  • the hydraulic arm may be attached to an outer cylinder or other turbine engine support structure positioned radially outward from the vane carrier.
  • the hydraulic arm may include four hydraulic arms positioned around the outer cylinder and may be spaced generally 90 degrees from each other around the outer cylinder.
  • the turbine engine may be started and brought up to a steady state operating condition.
  • the turbine blade gap control system may have the carrier vane and attached ring segments moved axially away from the tips of the turbine blades. In this position, the turbine engine may go from start up through a pinch point at which the turbine blade tips are closest to the ring segments without contact occurring.
  • the turbine blades and other turbine engine components may heat up to a steady state operating temperature at which the turbine blades have ceased growing due to thermal expansion.
  • the turbine blade gap control system may be used to reduce the size of the gap by moving the vane carrier axially along the rotational axis relative to the turbine blade assembly.
  • the hydraulic arms may be used to move the vane carrier axially relative to the turbine blade assembly.
  • An advantage of this invention is that the turbine blade gap control system enables turbine blades to be brought through a pinch point without the turbine blade tips contacting the ring segments and enables the gaps between the turbine blades tips and the ring segments to be reduced at steady state operating conditions to increase the efficiency of the engine.
  • Another advantage of this invention is that the turbine blade gap control system enables the gaps between the turbine blades tips and the ring segments to be reduced at steady state operating conditions to increase the efficiency of the engine without negatively affecting the compressor.
  • the net effect on the turbine engine is an increase in efficiency.
  • this invention is directed to a turbine blade gap control system 10 for reducing a gap 12 formed between turbine blades 14 and ring segments 16 in turbine engines 18. Reducing the gap 12 increases the efficiency of the turbine engine 18 by reducing the amount of combustion gases flowing around the turbine blades 14 rather than through the blades 14.
  • the turbine blade gap control system 10 may be configured to enable the turbine engine 18 to go through start up conditions, through a pinch point in the start up process before steady state operation where the tips 20 of the turbine blades 14 are closest to the ring segments 16 and into a steady state condition.
  • the turbine blade gap control system 10 may be configured to reduce the size of the gap 12 at steady state operating conditions by moving a vane carrier 22 to which the ring segments 16 are attached axially.
  • Such axial movement may reduce the gap 12 between the tips 20 of turbine blades 14 and ring segments 16 in turbine engines 18 in which the tips 20 of the turbine blades 14 are positioned at an acute angle 24 relative to a rotational axis 26 and the ring segments 16 are positioned in a similar manner.
  • the turbine engine 18 may include a turbine blade assembly 28 formed from a plurality rows 30 of turbine blades 14 extending radially outward from a rotor 32.
  • the rotor 32 may be any conventional rotor configured to rotate about the rotational axis 26.
  • Each row 30 may be formed from a plurality of turbine blades 14 extending radially outward from the rotor 32.
  • the turbine blades 14 of a row may all extend substantially equal distances from the rotor 32 such that the tips 20 are positioned within close proximity of the ring segments 16, yet offset to form the gap 12.
  • the rotor 32 rotates as combustion gases pass by the turbine blades 14.
  • the turbine blades 14 may have tips 20 positioned at an acute angle 24 relative to a rotational axis 26 of the turbine blade assembly 28. In at least one embodiment, as shown in Figures 1, 4 and 5, the tips 20 of the turbine blades 14 may be positioned at an acute angle 24 of about 20 degrees.
  • the ring segments 16 may include inner surfaces 34 that are positioned at substantially at the acute angle 24 relative to the rotational axis 26.
  • the ring segments 16 may be positioned between the vane carrier 22 and the tips 20 of the turbine blades 14 in each row, wherein an inner surface 34 of each of the ring segments 16 is offset radially outward from the tips 20 of the turbine blades 14.
  • the ring segments 16 may be attached to the vane carrier 22.
  • the vane carrier 22 may be concentric with the rotor 32 and positioned radially outward from the turbine blades 14. In such a position, axial movement of the vane carrier 22 causes a reduction in the size of the gap 12. In at least one embodiment, the vane carrier 22 may be move axially between about 4 millimeters and about 5 millimeters, which results in a reduction of the gap 12 of about 1 millimeter.
  • the turbine blade gap control system 10 may be configured to move the vane carrier 22 and attached ring segments 16 axially relative to the turbine blade assembly 28 to reduce the size of the gaps 12 between the tips 20 of the turbine blades 14 and the ring segments 16.
  • the turbine blade gap control system 10 may be formed from any device capable of moving the vane carrier 22 relative to the turbine blade assembly 28, and in particular, relative to the tips 20 of the turbine blades 14.
  • the turbine blade gap control system 10 may comprise at least one hydraulic arm 36 attached to the vane carrier 22 for moving the vane carrier 22 axially relative to the turbine blade assembly 28.
  • the hydraulic arm 36 may be attached to an outer cylinder 38 or other support structure positioned radially outward from the vane carrier 22.
  • the hydraulic arm 36 may include four hydraulic arms 36 positioned around the outer cylinder 38.
  • the hydraulic arms 36 may be positioned generally 90 degrees from each other around the outer cylinder 38.
  • the turbine blade gap control system 10 may include other numbers of hydraulic arms 36, and the hydraulic arms may be positioned in other configurations.
  • the turbine engine 18 may be started and brought up to a steady state operating condition.
  • the turbine blade gap control system 10 may have the carrier vane 22 and attached ring segments 16 positioned axially away from the tips 20 of the turbine blades 14. In this position, the turbine engine 18 may go from start up through a pinch point at which the turbine blade tips 20 are closest to the ring segments 16 without contact occurring.
  • the turbine blades 14 and other turbine engine components may heat up to a steady state operating temperature at which the turbine blades 14 have ceased thermal expansion.
  • the turbine blade gap control system 10 may be used to reduce the size of the gap 12 by moving the vane carrier 22 axially along the rotational axis 26 relative to the turbine blade assembly 28.
  • the hydraulic arms 36 may be used to move the vane carrier 22 axially relative to the turbine blade assembly 28.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP07113096A 2006-09-08 2007-07-25 System zur Turbinenschaufelspitzen-Abstandsreduktion für einen Turbinenmotor Withdrawn EP1900907A3 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11/518,018 US20080063513A1 (en) 2006-09-08 2006-09-08 Turbine blade tip gap reduction system for a turbine engine

Publications (2)

Publication Number Publication Date
EP1900907A2 true EP1900907A2 (de) 2008-03-19
EP1900907A3 EP1900907A3 (de) 2009-12-16

Family

ID=38776301

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07113096A Withdrawn EP1900907A3 (de) 2006-09-08 2007-07-25 System zur Turbinenschaufelspitzen-Abstandsreduktion für einen Turbinenmotor

Country Status (3)

Country Link
US (1) US20080063513A1 (de)
EP (1) EP1900907A3 (de)
CA (1) CA2600788A1 (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2233701A1 (de) * 2009-03-26 2010-09-29 Siemens Aktiengesellschaft Axialturbomaschine mit axial verschiebbarem Leitschaufelträger
DE102009023062A1 (de) * 2009-05-28 2010-12-02 Mtu Aero Engines Gmbh Spaltkontrollsystem, Strömungsmaschine und Verfahren zum Einstellen eines Laufspalts zwischen einem Rotor und einer Ummantelung einer Strömungsmaschine
US8186945B2 (en) 2009-05-26 2012-05-29 General Electric Company System and method for clearance control
EP2369141A3 (de) * 2010-03-22 2014-09-17 General Electric Company Aktive Kopfspielsteuerungsanordnung für ummantelte Gasturbinenschaufeln und zugehöriges Verfahren

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8550785B2 (en) 2010-06-11 2013-10-08 Siemens Energy, Inc. Wire seal for metering of turbine blade cooling fluids
US9488062B2 (en) * 2012-05-10 2016-11-08 General Electric Company Inner turbine shell axial movement
US20130315716A1 (en) * 2012-05-22 2013-11-28 General Electric Company Turbomachine having clearance control capability and system therefor
US9435218B2 (en) * 2013-07-31 2016-09-06 General Electric Company Systems relating to axial positioning turbine casings and blade tip clearance in gas turbine engines
US9441499B2 (en) * 2013-07-31 2016-09-13 General Electric Company System and method relating to axial positioning turbine casings and blade tip clearance in gas turbine engines
US9683453B2 (en) * 2013-09-11 2017-06-20 General Electric Company Turbine casing clearance management system
US9593589B2 (en) * 2014-02-28 2017-03-14 General Electric Company System and method for thrust bearing actuation to actively control clearance in a turbo machine
US10323536B2 (en) * 2015-04-09 2019-06-18 United Technologies Corporation Active clearance control for axial rotor systems
US10697241B2 (en) * 2015-10-28 2020-06-30 Halliburton Energy Services, Inc. Downhole turbine with an adjustable shroud
CN109751131A (zh) * 2019-03-29 2019-05-14 国电环境保护研究院有限公司 一种提升燃气轮机效率和功率的调整方法
CN110725722B (zh) * 2019-08-27 2022-04-19 中国科学院工程热物理研究所 一种适用于叶轮机械的动叶叶顶间隙动态连续可调结构

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1249577A1 (de) * 2001-04-12 2002-10-16 Siemens Aktiengesellschaft Gasturbine mit axial verschiebbaren Gehäuseteilen
EP1676978A2 (de) * 2004-12-29 2006-07-05 United Technologies Corporation Vorrichtung sowie Verfahren zur Regelung des Schaufelspitzenspiels in einer Gasturbine

Family Cites Families (5)

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Publication number Priority date Publication date Assignee Title
US3520635A (en) * 1968-11-04 1970-07-14 Avco Corp Turbomachine shroud assembly
US5203673A (en) * 1992-01-21 1993-04-20 Westinghouse Electric Corp. Tip clearance control apparatus for a turbo-machine blade
DE10060740A1 (de) * 2000-12-07 2002-06-13 Alstom Switzerland Ltd Vorrichtung zur Spaltmasseinstellung für eine Strömungsmaschine
GB2374123B (en) * 2001-04-05 2004-09-08 Rolls Royce Plc Gas turbine engine system
US7407369B2 (en) * 2004-12-29 2008-08-05 United Technologies Corporation Gas turbine engine blade tip clearance apparatus and method

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1249577A1 (de) * 2001-04-12 2002-10-16 Siemens Aktiengesellschaft Gasturbine mit axial verschiebbaren Gehäuseteilen
EP1676978A2 (de) * 2004-12-29 2006-07-05 United Technologies Corporation Vorrichtung sowie Verfahren zur Regelung des Schaufelspitzenspiels in einer Gasturbine

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2233701A1 (de) * 2009-03-26 2010-09-29 Siemens Aktiengesellschaft Axialturbomaschine mit axial verschiebbarem Leitschaufelträger
WO2010108876A1 (de) * 2009-03-26 2010-09-30 Siemens Aktiengesellschaft Axialturbomaschine mit axial verschiebbarem leitschaufelträger
CN102365426A (zh) * 2009-03-26 2012-02-29 西门子公司 具有可轴向移动的导向叶片支架的轴流式涡轮机
US9057281B2 (en) 2009-03-26 2015-06-16 Siemens Aktiengesellschaft Axial turbomachine having an axially displaceable guide-blade carrier
CN102365426B (zh) * 2009-03-26 2015-09-02 西门子公司 具有可轴向移动的导向叶片支架的轴流式涡轮机
US8186945B2 (en) 2009-05-26 2012-05-29 General Electric Company System and method for clearance control
DE102009023062A1 (de) * 2009-05-28 2010-12-02 Mtu Aero Engines Gmbh Spaltkontrollsystem, Strömungsmaschine und Verfahren zum Einstellen eines Laufspalts zwischen einem Rotor und einer Ummantelung einer Strömungsmaschine
US9068471B2 (en) 2009-05-28 2015-06-30 Mtu Aero Engines Gmbh Clearance control system, turbomachine and method for adjusting a running clearance between a rotor and a casing of a turbomachine
EP2369141A3 (de) * 2010-03-22 2014-09-17 General Electric Company Aktive Kopfspielsteuerungsanordnung für ummantelte Gasturbinenschaufeln und zugehöriges Verfahren
US8939715B2 (en) 2010-03-22 2015-01-27 General Electric Company Active tip clearance control for shrouded gas turbine blades and related method

Also Published As

Publication number Publication date
EP1900907A3 (de) 2009-12-16
US20080063513A1 (en) 2008-03-13
CA2600788A1 (en) 2008-03-08

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