EP1744014A1 - Agencement de montage des aubes d'entrée d'une turbine à gaz - Google Patents

Agencement de montage des aubes d'entrée d'une turbine à gaz Download PDF

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Publication number
EP1744014A1
EP1744014A1 EP05015235A EP05015235A EP1744014A1 EP 1744014 A1 EP1744014 A1 EP 1744014A1 EP 05015235 A EP05015235 A EP 05015235A EP 05015235 A EP05015235 A EP 05015235A EP 1744014 A1 EP1744014 A1 EP 1744014A1
Authority
EP
European Patent Office
Prior art keywords
turbine
transition tubes
hot gas
turbine plant
plant according
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Withdrawn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
EP05015235A
Other languages
German (de)
English (en)
Inventor
Gregor Frank
Joachim Krützfeldt
Kai-Uwe Rogos
Axel Dr. Schaberg
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
Priority to EP05015235A priority Critical patent/EP1744014A1/fr
Publication of EP1744014A1 publication Critical patent/EP1744014A1/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Withdrawn legal-status Critical Current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
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • 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
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • 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
    • F05D2240/55—Seals

Definitions

  • the present invention relates to a turbine installation having a turbine section, at least one flame chamber, which leads to a hot gas and has a hot gas outlet opening facing the turbine section and a number of guide vanes arranged in the region of the hot gas outlet opening or the hot gas outlet openings.
  • a turbine system in particular a gas turbine plant, is a turbomachine that essentially comprises a compressor section, a turbine section and a burner section arranged between the turbine section and the compressor section with one or more combustion chambers or flame tubes.
  • a gas turbine plant is for example in US 4,787,208 described.
  • transition tubes which are arranged circumferentially around the turbine runner and burner arrangements of the burner section connect to the turbine section.
  • the hot gas produced by the burners is directed from the transition tubes towards the turbine section and exits the hot gas outlets of the transition tubes into the turbine section.
  • the hot gas outlet openings is fluidly downstream of a number of vanes, which lead the exiting hot gas flow and deflect such that its kinetic energy can be effectively transferred to the turbine runner.
  • the turbine vanes are disposed around the turbine runner, extend substantially in the radial direction of the turbine runner and each have a mounting portion at its radially inner end and radially outer end. While the radially inner mounting portion is fixed to a component surrounding the turbine runner, the so-called shaft cover, the radially outer mounting portion is fixed to a vane support.
  • the described manner of mounting the vanes causes them to oscillate due to the different thermal expansions of the vane carrier and the shaft cover.
  • the vane carrier expands against the flow direction of the hot gas, whereas the shaft cover expands in the flow direction.
  • This pendulum movement can lead to high wear and deformation of the seals between the transition tubes and vane mounting.
  • If the transition tubes are fixed to the guide blade carrier, there is a relative movement between the burner and transition tube due to the thermal expansion of the transition tube. In the area of the burner and in the region of the transition between the transition tubes and the turbine section, therefore, complex sealing systems are necessary which take into account the movement of the turbine guide vanes and of the transition tube.
  • Object of the present invention is to provide a comparison with the cited prior art improved turbine system.
  • the fastening of both the inner and the outer attachment portion on the guide vane carrier can be made directly or indirectly, ie via the interposition of further construction elements.
  • At least one bracket is present, which is a fixed to the guide blade carrier first bracket end and a remote from the guide blade carrier and compared to the first end radially inwardly lying second Has temple end.
  • the inner attachment portion is attached in this embodiment, the second bracket end.
  • the stems When the flame spaces are formed as a number of transition tubes annularly distributed around the axial direction, the stems may be guided between adjacent transition tubes to the inner attachment portion.
  • the space between the transition tubes depends mainly on the number of transition tubes.
  • the distance of the bracket to the respective transition tubes can be adapted to the cooling air requirement of the transition tubes.
  • the dimensions of the brackets should be chosen in particular with regard to the required rigidity of the construction.
  • this spacer can likewise be fastened to the stirrup, in order to avoid that it behaves differently under thermal expansion than the inner attachment section the vanes.
  • a shaft cover surrounding the turbine rotor is present.
  • the inner fixing portion is fixed to the shaft cover in this embodiment.
  • the shaft cover is movably arranged relative to the compressor and fixed via the ribs on the guide blade carrier, so that the inner ring is indirectly secured to the guide blade carrier.
  • the shaft cover is fixed via a rib by a so-called. Diffuser on the compressor housing.
  • the fins may be passed between any two adjacent transition tubes.
  • the space between the transition tubes depends mainly on their number, and the distance of the ribs to the transition tubes should be based on the cooling air requirement of the transition tubes.
  • the dimensions of the ribs are chosen in view of the required rigidity of the construction and the available space.
  • flame spaces are in the form of a number of annular transition pipes distributed annularly about the axial direction available.
  • a cage fixedly connected to the guide blade carrier is present, which has receptacles for the hot gas outlet openings having ends of the transition tubes. Both the outer mounting portion and the inner mounting portion of the vanes are secured to the cage.
  • transition tubes are arranged to be movable relative to the guide blade carrier and merely inserted into the receptacles. As a result, movement of the transition tubes relative to the cage upon thermal expansion becomes possible.
  • a seal is arranged between the cage and the shaft cover.
  • the gas turbine plant comprises a compressor section 1, a burner section 3 and a turbine section 5.
  • a shaft 10 which carries on the one hand the turbine blades 30, 32 and on the other hand, the compressor blades 50.
  • a series of blades are each arranged along a circumferential line of the shaft 10 and form a blade ring.
  • the shaft 10 with the turbine blades 30, 32 and compressor blades 50 is also called a turbine runner or rotor.
  • vanes 40, 42 are provided, which are arranged between the blade rings.
  • compressor vanes 60 are disposed between the compressor blade rings 50.
  • the vanes 60 are arranged in a ring shape and form Leitschaufelkränze.
  • the burner section 3 comprises a large chamber, the so-called.
  • Brennerplenum 7 in which emerges from the compressor compressed air.
  • the burners 9 are fluidically connected to the turbine section 5 via transition tubes 13.
  • the guide vanes 40 of the first vane ring can only absorb the flow forces, but no mechanical forces. They are therefore held both at its radially outer end relative to the shaft 10 and at its radially inner end. They are attached on the one hand to a vane support 44 and on the other hand to a shaft cover 46. However, this type of attachment causes the vanes 40 to oscillate due to the differential thermal expansion of the vane support 44 and shaft cover 46. Namely, the vane support 44 expands against the flow direction and the shaft cover 46 in the flow direction.
  • the pendulum movement has a high wear of the vanes and can lead to deformations.
  • complex sealing systems are necessary in order to be able to reliably ensure a sealing of the burner plenum 7 against the flowing hot gases despite the pendulum movement.
  • FIG. 2 and 3 show a section of a gas turbine plant.
  • a burner 9 transition tubes 13
  • a section of the turbine section 5 of the gas turbine plant to recognize.
  • the guide vane carrier 44 and a vane 40 of the first vane ring are shown.
  • the shaft cover 46 is shown.
  • the outer shell 64 of the compressor section 1 is shown. A gap between the compressor outer shell 64 and the shaft cover 46 forms the outlet 2 of the compressor.
  • the vanes 40 of the first vane ring each have an airfoil 41 which, at its radially inner end with respect to the shaft 10, opens into an inner vane ring 47 extending around the shaft 10 as an inner attachment portion.
  • the radially outer end opens into an outer vane ring 48, which is also referred to as an outer attachment portion. While the inner vane ring 47 is fixed to the shaft cover 46, the radially outer vane ring 48 is fixed to the vane support 44.
  • the shaft cover 46 is secured in the present embodiment via a number of ribs 49 on the vane support 44.
  • the ribs 49 are passed between adjacent transition tubes 13.
  • the radially inner vane ring 47 is also indirectly attached to the vane carrier 44.
  • the ribs ensure that any relative movement between the vane support 44 and the shaft cover 46 can be effectively suppressed.
  • the pendulum movement of the vanes 40 of the first vane ring can thereby be effectively reduced.
  • the sealing of the shaft cover to the compressor side is also much easier to accomplish.
  • the side surfaces of the ribs 49 can serve as guide surfaces, which increasingly direct compressor air into the region of the transition tubes 13, in which the hot gas outlet openings 14 are arranged. As a result, the cooling of the transition tubes 13 can be improved.
  • connecting ribs connecting the compressor outer shell 64 with the shaft cover 46 can be omitted, whereby the flow area of the compressor outlet 2 can be increased.
  • FIGS. 2 and 3 show a section of a gas turbine plant, which corresponds to the detail shown in Figures 2 and 3.
  • Elements corresponding to the elements shown in FIGS. 2 and 3 are denoted by the same reference numerals as in FIG. 2 and FIG. 3 and will not be explained again in order to avoid unnecessary repetition.
  • brackets 149 are present, which have approximately the shape of a lying on the side "U" and are passed between adjacent transition tubes 13.
  • the outer end 150 of the brackets 149 is secured to the turbine vane support 44.
  • the free inner end 152 of the bracket 149 is the fixed to the guide rail carrier 44 end 150 in relation to the shaft 10 radial direction opposite. At the free end 152 of the inner vane ring 47 is fixed.
  • the shaft cover 46 is not connected to the turbine vane support 44. Instead, it is attached to the compressor outer shell 64 via ribs 66.
  • the free ends 152 of the bracket 149 form ring segments which together form a ring cover 46 surrounding the ring. Between this ring and the shaft cover 46, a seal 45 is arranged to seal the turbine section 5 against the Brennschplenum 7.
  • vanes 40 of the first vane ring are fixed only to the turbine vane support 44, a pendulum motion due to thermal expansion can be effectively reduced. Due to the reduced pendulum movement, the sealing effort can be greatly reduced.
  • FIG. 4b shows a modification of the second exemplary embodiment.
  • a spacer 43 is additionally provided between the outlet 14 of the transition tube 13 and the turbine vane 40. This spacer 43 is also attached to the bracket 149.
  • a spacer can also be present in the two other exemplary embodiments and fastened there to the rib or cage (third exemplary embodiment, which is described below).
  • FIGS. 6 and 7. show the transition region between the transition tubes 13 and the turbine section 5.
  • the guide vane carrier 44, the shaft cover 46, a vane 40 with airfoil 41, inner vane ring 47 and outer vane ring 48 can be seen.
  • a transition tube 13 is indicated.
  • a cage 100 is disposed. This has a cage outer ring 102 and a cage inner ring 104.
  • the cage outer ring 102 and the cage inner ring 104 are connected to each other via a number of cage webs 106.
  • the spaces between two adjacent cage webs form receptacles 108, in which the hot gas outlet openings 14 having ends of the transition tubes 13 are inserted.
  • the cage 100 has no rigid connection to the shaft cover 46, but a seal 101. In this way, a relative movement between the cage 100 and turbine vane support 44 on the one hand and the shaft cover 46 on the other hand due to thermal expansion is possible.
  • the cage outer ring 102 has a holding region, in which the guide vane outer ring is inserted.
  • the cage inner ring 104 has a holding region in which the guide blade inner ring 47 is inserted.
  • the vane ring is therefore completely held by the cage 100.
  • the vanes 40 of the first vane ring are attached only to the turbine vane support 44.
  • the holding areas of the cage rings 102, 104 may be provided, for example, in the form of annular grooves. Due to the attachment of the first vane ring alone to the cage 100, the vanes 40 no longer perform a pendulum motion due to thermal expansion.
  • the cage 100 is designed as a separate component which is only on the turbine vane carrier 44 is preferably releasably fixed.
  • the cage 100 can then be removed from the turbine guide vane carrier 44, which significantly simplifies assembly and disassembly.
  • the transition tubes 13 can be fixed to the cage 100 and thus to the turbine guide vane carrier 44. In this case, the transition tubes 13 may move due to the thermal expansion of the vane support 44 relative to the burners 9. Between the burners 9 and the transition tubes 13, therefore, sliding seals are arranged. In addition, there is a flexible support of the transition tubes near the burner.
  • the transition tubes 13 it is also possible to fasten the transition tubes 13 to the burners 9 or to the housing and to insert the transition tubes 13 only into the receptacles 108 in the cage 100 so that they can be displaced within the receptacles 108.
  • the sealing concept between the burners 9 and the transition tubes 13 can be simplified, since there is no longer any relative movement between the burners 9 and the transition tubes 13.
  • the mere insertion of the transition tubes 13 in the receptacles 108 of the cage 100 allows a relative movement between the cage 100 and the transition tubes 13. With this configuration, the wear caused by sliding movements of the seal between the burner 9 and transition tube 13 can be reduced.
  • the assembly and disassembly of the transition tubes 13 is simplified to the burners 9, since no complicated sealing system must be installed.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP05015235A 2005-07-13 2005-07-13 Agencement de montage des aubes d'entrée d'une turbine à gaz Withdrawn EP1744014A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP05015235A EP1744014A1 (fr) 2005-07-13 2005-07-13 Agencement de montage des aubes d'entrée d'une turbine à gaz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP05015235A EP1744014A1 (fr) 2005-07-13 2005-07-13 Agencement de montage des aubes d'entrée d'une turbine à gaz

Publications (1)

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EP1744014A1 true EP1744014A1 (fr) 2007-01-17

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EP05015235A Withdrawn EP1744014A1 (fr) 2005-07-13 2005-07-13 Agencement de montage des aubes d'entrée d'une turbine à gaz

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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2402659A1 (fr) * 2010-07-01 2012-01-04 Siemens Aktiengesellschaft Coque extérieure pour chambre de combustion
WO2013130148A1 (fr) * 2011-12-05 2013-09-06 Siemens Energy, Inc. Carter circulaire pour un cadre intermédiaire de turbine à gaz industrielle
US9492780B2 (en) 2014-01-16 2016-11-15 Bha Altair, Llc Gas turbine inlet gas phase contaminant removal
US10502136B2 (en) 2014-10-06 2019-12-10 Bha Altair, Llc Filtration system for use in a gas turbine engine assembly and method of assembling thereof
US10883375B2 (en) * 2016-04-08 2021-01-05 Ansaldo Energia Switzerland AG Turboengine, and vane carrier unit for turboengine
US11873738B2 (en) 2021-12-23 2024-01-16 General Electric Company Integrated stator-fan frame assembly

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE440143C (de) * 1924-01-10 1927-02-05 Escher Wyss Maschf Ag Leitvorrichtung fuer Dampf- oder Gasturbinen
US2625013A (en) * 1948-11-27 1953-01-13 Gen Electric Gas turbine nozzle structure
US4776765A (en) * 1985-07-29 1988-10-11 General Electric Company Means and method for reducing solid particle erosion in turbines
US4787208A (en) 1982-03-08 1988-11-29 Westinghouse Electric Corp. Low-nox, rich-lean combustor
DE3913223A1 (de) * 1988-04-21 1989-11-02 Nuovo Pignone Spa Vorrichtung zum staendigen halten der ringfoermigen auslassmuendung des gasausstroemraums zentriert um die duesenanordnung in einer gasturbine

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE440143C (de) * 1924-01-10 1927-02-05 Escher Wyss Maschf Ag Leitvorrichtung fuer Dampf- oder Gasturbinen
US2625013A (en) * 1948-11-27 1953-01-13 Gen Electric Gas turbine nozzle structure
US4787208A (en) 1982-03-08 1988-11-29 Westinghouse Electric Corp. Low-nox, rich-lean combustor
US4776765A (en) * 1985-07-29 1988-10-11 General Electric Company Means and method for reducing solid particle erosion in turbines
US4776765B1 (fr) * 1985-07-29 1992-06-30 Gen Electric
DE3913223A1 (de) * 1988-04-21 1989-11-02 Nuovo Pignone Spa Vorrichtung zum staendigen halten der ringfoermigen auslassmuendung des gasausstroemraums zentriert um die duesenanordnung in einer gasturbine

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2402659A1 (fr) * 2010-07-01 2012-01-04 Siemens Aktiengesellschaft Coque extérieure pour chambre de combustion
WO2013130148A1 (fr) * 2011-12-05 2013-09-06 Siemens Energy, Inc. Carter circulaire pour un cadre intermédiaire de turbine à gaz industrielle
CN104114819A (zh) * 2011-12-05 2014-10-22 西门子能源有限公司 用于工业燃气涡轮发动机的中间框架的全环式壳体
US9200565B2 (en) 2011-12-05 2015-12-01 Siemens Energy, Inc. Full hoop casing for midframe of industrial gas turbine engine
US9492780B2 (en) 2014-01-16 2016-11-15 Bha Altair, Llc Gas turbine inlet gas phase contaminant removal
US10502136B2 (en) 2014-10-06 2019-12-10 Bha Altair, Llc Filtration system for use in a gas turbine engine assembly and method of assembling thereof
US10883375B2 (en) * 2016-04-08 2021-01-05 Ansaldo Energia Switzerland AG Turboengine, and vane carrier unit for turboengine
US11873738B2 (en) 2021-12-23 2024-01-16 General Electric Company Integrated stator-fan frame assembly

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