EP2674580A1 - Procédé et appareil pour atténuer les effets des déviations de la rondeur au niveau d'une turbine - Google Patents

Procédé et appareil pour atténuer les effets des déviations de la rondeur au niveau d'une turbine Download PDF

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Publication number
EP2674580A1
EP2674580A1 EP13171178.0A EP13171178A EP2674580A1 EP 2674580 A1 EP2674580 A1 EP 2674580A1 EP 13171178 A EP13171178 A EP 13171178A EP 2674580 A1 EP2674580 A1 EP 2674580A1
Authority
EP
European Patent Office
Prior art keywords
turbine shell
turbine
shell
ring insert
degrees
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Withdrawn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
EP13171178.0A
Other languages
German (de)
English (en)
Inventor
Steven Christopher Pisarski
Kenneth Damon Black
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of EP2674580A1 publication Critical patent/EP2674580A1/fr
Withdrawn legal-status Critical Current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
    • 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
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49229—Prime mover or fluid pump making
    • Y10T29/49231—I.C. [internal combustion] engine making
    • Y10T29/49234—Rotary or radial engine making

Definitions

  • the subject matter disclosed herein relates to an apparatus and method for mitigating out-of-roundness effects at an inner turbine shell of a gas turbine.
  • turbine section designs include an inner turbine shell that provides a flow path for a working gas through the turbine and an outer turbine shell that surrounds the inner turbine shell.
  • a rotor having a plurality of blades is disposed within the inner turbine shell and rotates as a result of the working gas passing through the turbine.
  • the clearance between the inner turbine shell and the plurality of turbine blades determines turbine efficiency and power production and can be affected by a deviation of the inner turbine shell from a circular cross-section, also known as out-of-roundness.
  • the present disclosure provides a method and apparatus that reduces load transfer between outer turbine shell and inner turbine shell to reduce out-of-roundness effects.
  • the present invention resides in a method of mitigating out-of-roundness effects at a turbine, the method including: providing an inner turbine shell of the turbine within an outer turbine shell of the turbine; and coupling the inner turbine shell to the outer turbine shell using a ring insert that is segmented into a plurality of ring insert segments that reduce a transfer of load from the outer turbine shell to the inner turbine shell to mitigate out-of-roundness of the inner turbine shell.
  • the present invention resides in a turbine including an outer turbine shell; an inner turbine shell; and a ring insert configured to couple the inner turbine shell to the outer turbine shell and segmented into a plurality of ring insert segments to reduce a load transfer from the outer turbine shell to the inner turbine shell.
  • FIG. 1 shows a side view cross-section of an exemplary inner turbine shell 100 of a gas turbine in one embodiment of the present disclosure.
  • the exemplary inner turbine shell 100 provides a hollow casing extending along a longitudinal axis 102 and having an inlet 104 at a first end of the longitudinal axis and an outlet 106 at a second end of the longitudinal axis.
  • the turbine shell is substantially rotationally symmetric about its longitudinal axis 102.
  • a rotor having a plurality of turbine blades (not shown) is disposed substantially along the longitudinal axis 102 within the inner turbine shell 100.
  • a working gas injected into the inner turbine shell 100 at the inlet 104 displaces the turbine blades to cause the turbine blades to rotate, thereby causing the rotor to rotate to generate power.
  • the inner turbine shell 100 is composed of two or more sections, also referred to herein as shell sectors, that are mated together to form the inner turbine shell 100.
  • An exemplary shell sector generally spans a selected azimuthal angle around the longitudinal axis 102.
  • the two or more shell sectors are mated together at interfaces 110 via bolts 112.
  • the mated shell sectors provide a cooling hole or air passage 114 passing through the inner turbine shell 100 that provides air to nozzles (not shown) that are assembled at the inner turbine shell.
  • the inner turbine shell is coupled to the outer turbine shell at a thrust collar 116 of the inner turbine shell 100.
  • the inner turbine shell includes a thrust collar 116.
  • FIG. 2 shows a section of the inner turbine shell of FIG. 1 that includes a thrust collar 116.
  • the thrust collar 116 is segmented.
  • the segmented thrust collar 116 of the inner turbine shell includes a slot 118 into which a ring insert can be inserted.
  • the ring insert couples the inner turbine shell to the outer turbine shell to provide support for the inner turbine shell.
  • the ring insert provides an area of contact between the outer turbine shell and the inner turbine shell.
  • the ring insert is segmented into a plurality of ring insert segments that are separated from each other to provide gaps between them along the circumference. Thus, the total angle subtended by the plurality of ring insert segments is less than 360 degrees.
  • FIG. 3 shows a profile view of a shell sector in an exemplary embodiment of the present disclosure.
  • the exemplary inner turbine shell is composed of four shell sectors, each of which forms a quadrant of the inner turbine shell 300.
  • Exemplary shell sector 315 is shown.
  • a ring insert segment 302 is shown on the exemplary shell sector 315.
  • the ring insert segment 302 extends from a first azimuthal location 304 to a second azimuthal location 306 along a circumference of sector 315 to subtend angle 320.
  • angle 320 is less than 90 degrees.
  • angle 320 is between about 15 degrees and 85 degrees.
  • angle 320 is between about 30 degrees and about 70 degrees.
  • the ring insert segment 302 is disposed evenly between the first mating interface 310 and second mating interface 312 of shell sector 315 such that a distance between the first azimuthal location 304 and the first mating interface 310 is substantially the same as a distance between the second azimuthal location 306 and the second mating interface 312.
  • the area of contact between the outer turbine shell and the inner turbine shell is less than 360 degrees. This reduced contact area reduces a load transfer area between the outer turbine shell and the inner turbine shell.
  • the exemplary shell sector 315 can include two or more ring segments separated from each other.
  • the length of the ring insert segment can be determined using a processor.
  • the exemplary processor can run a simulation to determine the length of the ring insert segment at which an out-of-roundness of the inner turbine shell meets a selected criterion.
  • the processor can simulate various operating cycles of the turbine and determine out-of-roundness of the inner turbine shell at various times during the cycle.
  • a turbine having the exemplary ring insert segments can be constructed and operated. Sensors can be disposed at various locations of the inner turbine shell and the out-of-roundness of the inner turbine shell can be observed as the turbine is run through various operational cycles. A ring insert segment length and spacing can thereby be determined by observing an effectiveness of the various ring insert segment lengths with respect to mitigating out-of-roundness effects.
  • the length of the ring segment is selected at which the out-of roundness meets a selected criterion.
  • the right segment is selected when a length of the ring segment keeps the out-of-roundness of the inner turbine shell within an acceptable tolerance level.
  • the selected criterion can be an out-of-roundness tolerance over a selected time frame.
  • FIG. 4 shows a plot of a circumference of an exemplary inner turbine shell of the present disclosure at various times during operation of an exemplary turbine.
  • the plot of FIG. 4 is output from an analytical model in measurements of radial displacement of the circumference are obtained at approximately every 5 degrees around the circumference.
  • a plot may alternatively be obtained for a test of a constructed shell, generally using about 10 sensors placed around the circumference. Radial measurements are obtained at various times, as indicated by reference numbers 401 (1654 seconds after start-up), 402 (2374 seconds), 403 (2874 seconds), 404 (4174 seconds), 405 (100000 seconds) and 406 (100967 seconds).
  • FIG. 5 shows a plot of the circumference of the exemplary inner turbine shell of FIG. 4 at later times.
  • the exemplary inner turbine shell is generally run through one or more cycles of increasing and decreasing power output.
  • the circumference of the inner turbine shell generally increases with heating and decreases with cooling.
  • Early times i.e., time 401 show an inner turbine shell that has a substantially round cross-section.
  • the turbine operating at high output levels i.e. times 404, 405 and 406) are shown.
  • Time 404 in particular shows an inner turbine shell with large out-of roundness effects at high output levels.
  • Times 503 and 504 shown the circumference as the operation cycle is lowered to a lower output levels.
  • Time 506 shows the circumference as the operation cycle is raised again to high output levels. As seen in FIG. 5 , the degree of out-of-roundness of the shell at time 506 is relatively little. When the out-of-roundness effects are within an acceptable tolerance an operator can select the ring segment for use in a turbine.
  • the present disclosure provides a method of mitigating out-of-roundness effects at a turbine, the method including: providing an inner turbine shell of the turbine within an outer turbine shell of the turbine; and coupling the inner turbine shell to the outer turbine shell using a ring insert that is segmented into a plurality of ring insert segments that reduce a transfer of load from the outer turbine shell to the inner turbine shell to mitigate out-of-roundness of the inner turbine shell.
  • the plurality of ring insert segments includes four ring insert segments.
  • At least one of the ring insert segments subtends an angle measured from a longitudinal axis of the inner turbine shell selected from the group consisting of: (i) less than 90 degrees; (ii) between about 15 degrees and about 85 degrees; and (iii) between about 30 degrees and about 70 degrees.
  • a processor can be used to determine a length and position of the ring insert segments at which an out-of-roundness of the inner turbine shell meets a selected criterion.
  • the length of a ring insert segment is selected to reduce a load path between the outer turbine shell and the inner turbine shell.
  • the load is a result of a thermal stress at the outer turbine shell.
  • the ring insert segments are disposed at a thrust collar of the inner turbine shell at equidistant locations around a circumference of the inner turbine shell.
  • the inner turbine shell is formed of at least two azimuthal shell sectors.
  • a turbine including an outer turbine shell; an inner turbine shell; and a ring insert configured to couple the inner turbine shell to the outer turbine shell and segmented into a plurality of ring insert segments to reduce a load transfer from the outer turbine shell to the inner turbine shell.
  • the ring insert is segmented into four ring insert segments.
  • An angle subtended by at least one of the ring insert segments is selected from the group consisting of: (i) less than 90 degrees; (ii) between about 15 degrees and 85 degrees; and (iii) between about 30 degrees and about 70 degrees.
  • a processor running a program of a model of the turbine can be used to determine a length of the ring insert.
  • the length of the ring insert segments is generally selected to reduce a load path between the outer turbine shell and the inner turbine shell.
  • the load is generally related to thermal stress at the outer turbine shell.
  • the ring insert segments are evenly spaced around a circumference of the inner turbine shell.
  • the inner turbine shell is formed of at least two shell sectors extending over a selected azimuthal angle.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP13171178.0A 2012-06-11 2013-06-10 Procédé et appareil pour atténuer les effets des déviations de la rondeur au niveau d'une turbine Withdrawn EP2674580A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/493,435 US20130330187A1 (en) 2012-06-11 2012-06-11 Method and apparatus for mitigating out of roundness effects at a turbine

Publications (1)

Publication Number Publication Date
EP2674580A1 true EP2674580A1 (fr) 2013-12-18

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP13171178.0A Withdrawn EP2674580A1 (fr) 2012-06-11 2013-06-10 Procédé et appareil pour atténuer les effets des déviations de la rondeur au niveau d'une turbine

Country Status (5)

Country Link
US (1) US20130330187A1 (fr)
EP (1) EP2674580A1 (fr)
JP (1) JP2013256945A (fr)
CN (1) CN103485844B (fr)
RU (1) RU2013126491A (fr)

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB229627A (en) * 1924-02-19 1926-01-14 Jan Kieswetter Improvements relating to turbine casings having transverse partitions and the like therein
US1873743A (en) * 1930-11-15 1932-08-23 Gen Electric Elastic fluid turbine
US4078812A (en) * 1975-07-04 1978-03-14 Bbc Brown Boveri & Company Limited Combined seal and guide arrangement for two coaxially arranged machine parts
EP2378088A2 (fr) * 2010-04-15 2011-10-19 General Electric Company Turbine à carter double

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3892497A (en) * 1974-05-14 1975-07-01 Westinghouse Electric Corp Axial flow turbine stationary blade and blade ring locking arrangement
DE4136408A1 (de) * 1991-11-05 1993-05-06 Siemens Ag, 8000 Muenchen, De Waermebewegliche anordnung zur abdichtung eines zwischenraumes, insbesondere fuer dampfleitungen bei dampfturbinen
US6733233B2 (en) * 2002-04-26 2004-05-11 Pratt & Whitney Canada Corp. Attachment of a ceramic shroud in a metal housing
US7617602B2 (en) * 2005-08-18 2009-11-17 General Electric Company Method of servicing a turbine
US7686575B2 (en) * 2006-08-17 2010-03-30 Siemens Energy, Inc. Inner ring with independent thermal expansion for mounting gas turbine flow path components
US8152446B2 (en) * 2007-08-23 2012-04-10 General Electric Company Apparatus and method for reducing eccentricity and out-of-roundness in turbines
US8177483B2 (en) * 2009-05-22 2012-05-15 General Electric Company Active casing alignment control system and method

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB229627A (en) * 1924-02-19 1926-01-14 Jan Kieswetter Improvements relating to turbine casings having transverse partitions and the like therein
US1873743A (en) * 1930-11-15 1932-08-23 Gen Electric Elastic fluid turbine
US4078812A (en) * 1975-07-04 1978-03-14 Bbc Brown Boveri & Company Limited Combined seal and guide arrangement for two coaxially arranged machine parts
EP2378088A2 (fr) * 2010-04-15 2011-10-19 General Electric Company Turbine à carter double

Also Published As

Publication number Publication date
JP2013256945A (ja) 2013-12-26
RU2013126491A (ru) 2014-12-20
US20130330187A1 (en) 2013-12-12
CN103485844B (zh) 2017-04-12
CN103485844A (zh) 2014-01-01

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