EP3244022A1 - Turbinenanordnung, turbineninnenwandanordnung und turbinenanordnungsverfahren - Google Patents

Turbinenanordnung, turbineninnenwandanordnung und turbinenanordnungsverfahren Download PDF

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Publication number
EP3244022A1
EP3244022A1 EP17169742.8A EP17169742A EP3244022A1 EP 3244022 A1 EP3244022 A1 EP 3244022A1 EP 17169742 A EP17169742 A EP 17169742A EP 3244022 A1 EP3244022 A1 EP 3244022A1
Authority
EP
European Patent Office
Prior art keywords
rotary component
wall
wall segments
turbine
segments
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Withdrawn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
EP17169742.8A
Other languages
English (en)
French (fr)
Inventor
James Zhang
James Tyson Balkcum III
John Mcconnell Delvaux
Matthew Troy Hafner
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 EP3244022A1 publication Critical patent/EP3244022A1/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Withdrawn legal-status Critical Current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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • F01D1/04—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines traversed by the working-fluid substantially axially
    • 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
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • F05D2240/00—Components
    • F05D2240/55—Seals

Definitions

  • the present embodiments are directed to turbine assemblies, turbine inner wall assemblies, and turbine assembly methods. More specifically, the present embodiments are directed to turbine inner wall assemblies with nozzles forming a seal with inner wall segments.
  • a gas turbine generally includes a main flow path intended to confine a main working fluid therein, namely the hot combustion gases. Additionally, a cooling fluid that is independent of the main working fluid may be supplied to adjacent turbine rotor structural components. Sealing devices thus may be used to shield the rotor components from direct exposure to the main working fluid driving the turbine and to prevent the cooling fluid from escaping with the main working fluid. Typical sealing devices may reduce the efficiency and performance of a turbine due to leakage. For example, leakage in sealing devices, such as inter-stage seals, may require an increase in the amount of parasitic fluid needed for cooling purposes. The use of the parasitic cooling fluid decreases the overall performance and efficiency of a gas turbine engine.
  • a near-flow-path seal is a sealing device that is conventionally positioned about a nozzle and in between buckets of a turbine.
  • a NFPS is typically intended to form an outer boundary for the flow of combustion gases, so as to prevent the flow of combustion gases from migrating therethrough.
  • Ceramic matrix composite (CMC) materials include compositions having a ceramic matrix reinforced with coated fibers.
  • the composition provides strong, lightweight, and heat-resistant materials with possible applications in a variety of different systems.
  • the manufacture of a CMC part typically includes laying up pre-impregnated composite fibers having a matrix material already present (prepreg) to form the shape of the part (pre-form), autoclaving and burning out the pre-form, infiltrating the burned-out pre-form with the melting matrix material, and any machining or further treatments of the pre-form.
  • Infiltrating the pre-form may include depositing the ceramic matrix out of a gas mixture, pyrolyzing a pre-ceramic polymer, chemically reacting elements, sintering, generally in the temperature range of 925 to 1650 °C (1700 to 3000 °F), or electrophoretically depositing a ceramic powder.
  • CMC materials include, but are not limited to, carbon-fiber-reinforced carbon (C/C), carbon-fiber-reinforced silicon carbide (C/SiC), silicon-carbide-fiber-reinforced silicon carbide (SiC/SiC), alumina-fiber-reinforced alumina (Al 2 O 3 /Al 2 O 3 ), or combinations thereof.
  • the CMC may have increased elongation, fracture toughness, thermal shock, dynamic load capability, and anisotropic properties as compared to a monolithic ceramic structure.
  • a turbine assembly includes a rotary component rotatable about an axis of a turbine, a plurality of inner wall segments coupled to the rotary component circumferentially around the rotary component and rotatable with the rotary component, a non-rotary component circumferentially surrounding the rotary component, a plurality of outer wall segments coupled to the non-rotary component and disposed to extend toward the rotary component, and a plurality of nozzles extending from each of the outer wall segments, each nozzle having a distal tip, the distal tips forming a seal with the inner wall segments at an inner flow path of the turbine.
  • an inner wall assembly in another embodiment, includes a rotary component rotatable about an axis of a turbine and a plurality of inner wall segments coupled to the rotary component circumferentially around the rotary component and rotatable with the rotary component.
  • a turbine assembly method in another embodiment, includes coupling a plurality of inner wall segments circumferentially to a rotary component and mounting a plurality of outer wall segments to a non-rotary component and disposed to extend toward the rotary component.
  • a plurality of nozzles extend from each outer wall segment toward one of the plurality of inner wall segments. The nozzles form a seal with the inner wall segments at an inner flow path of the turbine.
  • a turbine assembly with composite turbine nozzles and integrated rotating end wall segments forming a seal with the nozzles.
  • Embodiments of the present disclosure for example, in comparison to concepts failing to include one or more of the features disclosed herein, save cooling flow, increase efficiency, reduce loss due to gaps between a cantilevered airfoil, eliminate the need for separate near flow path seals (NFPSs), reduce the number of gaps at the inner flow path, reduce the amount of pull load, reduce the cooling flow needed, or combinations thereof.
  • NFPSs near flow path seals
  • FIG. 1 shows a turbine assembly 10 including a rotary component 12, an inner wall segment 16, a set of nozzles 18, and an outer wall segment 20.
  • the rotary component 12 is rotatable about a central axis of the turbine.
  • the inner wall segments 16 are coupled circumferentially around and surround the rotary component 12 and are rotatable with the rotary component 12.
  • the outer wall segments 20 are mounted to a non-rotary component (not shown) circumferentially surrounding the rotary component and disposed to extend toward the rotary component 12.
  • a set of nozzles 18 extend from the outer wall segment 20 toward the inner wall segment 16 and form a seal with the inner wall segment 16 at the inner flow path of the turbine.
  • the nozzles 18 are attached by nozzle pins 22 to the outer wall segment 20 and extend in a cantilevered fashion therefrom.
  • the rotary component 12 is a single piece that is a dedicated rotor wheel 13 that is free from physical attachment to either the upstream or the downstream bucket wheel.
  • FIG. 2 shows a turbine assembly 10 including a rotary component 12 including a rotor wheel 13 and a near flow path seal segment 14, an inner wall segment 16, a set of nozzles 18, and an outer wall segment 20.
  • the rotary component 12 is rotatable about a central axis of the turbine.
  • a plurality of the near flow path seal segments 14 are mounted circumferentially around the rotor wheel 13 and rotate with the rotor wheel 13.
  • the near flow path seal segments 14 are connected by a dovetail to the rotor wheel 13.
  • the inner wall segments 16 are coupled to the near flow path seal segments 14 and are rotatable with the rotor wheel 13 and the near flow path seal segments 14.
  • the outer wall segments 20 are mounted to a non-rotary component (not shown) circumferentially surrounding the rotary component and disposed to extend toward the rotary component 12.
  • a set of nozzles 18 extend from each outer wall segment 20 toward the inner wall segment 16 and form a seal with the inner wall segment 16 at the inner flow path of the turbine.
  • the nozzles 18 are attached by nozzle pins 22 to the outer wall segment 20 and extend in a cantilevered fashion. An end of a near flow path seal segment 14 is visible in FIG. 2 .
  • FIG. 3 shows a perspective partial cross sectional view of the coupling of the inner wall segment 16 to the rotary component 12 of the embodiment of FIG. 1 .
  • the rotary component 12 includes a rotary coupler 30.
  • the rotary coupler 30 includes a pair of outwardly-extending mounting flanges.
  • the inner wall segment 16 includes an inner wall coupler 36 complementary to the rotary coupler 30.
  • the inner wall coupler 36 includes a pair of wall flanges extending from the lower surface of the inner wall segment 16 to sit adjacent to the outwardly-extending mounting flanges of the rotary component 12.
  • the inner wall segments 16 are fastened to the rotary component 12 by way of wall pins 38 extending into holes in the outwardly-extending mounting flanges and holes in the wall flanges to mount the inner wall segments 16 to the rotary component 12.
  • FIG. 4 shows a coupling of the inner wall segment 16 to the near flow path seal segment 14 of the rotary component 12.
  • the rotary coupler 30 includes a pair of axially-extending mounting flanges.
  • the inner wall coupler 36 includes a pair of L-shaped flanges extending from the lower surface of the inner wall segment 16 to engage the axially-extending mounting flanges of the near flow path seal segment 14 of the rotary component 12 that serve as a hook to connect the near flow path seal segment 14 to the inner wall segment 16, thereby mounting the inner wall segment 16 to the near flow path seal segment 14 of the rotary component 12.
  • FIG. 5 shows another alternate coupling of the inner wall segment 16 to the near flow path seal segment 14 of the rotary component 12.
  • the rotary coupler 30 includes an outwardly-extending tenon of a dovetail.
  • the inner wall coupler 36 includes a mortise between two extensions from the lower surface of the inner wall segment 16 to engage the outwardly-extending tenon of the near flow path seal segment 14 of the rotary component 12, thereby mounting the inner wall segment 16 to the near flow path seal segment 14 of the rotary component 12.
  • the tenon may be formed by the inner wall segment 16 and the mortise may be formed by the near flow path seal segment 14 of the rotary component 12 to achieve the dovetail coupling.
  • the pinning, hooking, and dovetailing couplings may be used with either a singular rotary component 12 or with a rotary component 12 including near flow path seal segments 14.
  • the rotary couplers 30 may continue around the entire circumference without a gap. In hooking or dovetailing embodiments, however, some sort of gap is needed to allow the inner wall couplers 36 to engage the rotary coupler 30.
  • the gap may be included in the rotary coupler 30 at a location around the rotary component 12 permitting the inner wall coupler 36 to slidingly engage the rotary couplers 30, thereby coupling the inner wall segment 16 to the rotary component 12.
  • the inner wall segments 16 may alternatively be coupled to the near flow path seal segments 14 without a gap in the rotary couplers 30 if the inner wall segments 16 are first coupled to the near flow path seal segments 14 and then the near flow path seal segments 14 are attached to the rotor wheel 13 and there is a gap allowing coupling of the near flow path seal segments 14 to the rotor wheel 13.
  • the composite turbine nozzle assembly includes an outer wall segment 20 as a one-piece segment of an outer side wall to support multiple nozzles 18 as singlet cantilevered composite airfoils.
  • the number of nozzles 18 supported by each one-piece outer wall segment 20 may be two, alternatively at least two, alternatively in the range of two to six, alternatively four, alternatively at least four, alternatively six, alternatively at least six, or any number, range, or sub-range therebetween.
  • the airfoils are attached only to the outer wall segments 20, leaving a small gap between the tip 34 and the inner flow path defined by the upper surface 32 of the inner wall segment 16.
  • the inner wall segments 16 have an arc length greater than the nozzle pitch of the nozzles 18. In some embodiments, the arc length of the inner wall segments 16 is similar to the arc length of the outer wall segments 20.
  • the number of nozzles 18 sealing with each one-piece inner wall segment 16 may be two, alternatively at least two, alternatively in the range of two to six, alternatively four, alternatively at least four, alternatively six, alternatively at least six, or any number, range, or sub-range therebetween.
  • the rotary component 12 is the rotating rotor wheel 13.
  • each inner wall segment 16 may be made as a one-piece inner flow path segment and may be attached to the rotor wheel 13 directly.
  • the rotary component 12 includes a plurality of near flow path seal segments 14 attached to the rotor wheel 13.
  • the inner wall segment 16 is indirectly attached to the rotor wheel 13, the inner wall segment 16 being attached to a near flow path seal segment 14, which is attached to the rotor wheel 13.
  • the inner wall segments 16 are coupled to the rotary component 12.
  • the inner wall segment 16 is pinned to the rotary component 12.
  • the inner wall segment 16 is hooked to the rotary component 12.
  • the inner wall segment 16 is dovetailed to the rotary component 12.
  • a preferred design accommodates nozzles 18 that are high-temperature composite airfoils that tolerate higher temperatures with less cooling flow needed, thereby increasing the efficiency of the turbine.
  • the rotating inner flow path defined by the inner wall segment 16 eliminates the need for separate NFPSs, thereby saving cooling flow and increasing efficiency.
  • the rotating inner flow path defined by the inner wall segment 16 also reduces the efficiency loss caused by a gap between the cantilevered airfoil and the inner flow path.
  • the inner wall segments 16 defining the rotating inner flow path are made of lightweight high-temperature ceramic matrix composite (CMC) materials, thereby reducing the pull load and the cooling flow needed.
  • CMC ceramic matrix composite
  • the inner wall segments 16 are effectively pinned to the rotating rotary component 12 due to the relative light weight of the CMC material.
  • the nozzles 18 are made of lightweight high-temperature ceramic matrix composite (CMC) materials, thereby reducing the cooling flow needed.
  • CMC ceramic matrix composite
  • the length of the inner wall segments 16 is greater than one nozzle 18 or blade pitch, which reduces the number of segment gaps to seal.
  • the inner wall segments 16 defining the CMC inner flow path are attached to a dedicated rotor wheel 13, which is free from physical attachment to either the upstream or the downstream bucket wheel.
  • a bayonet-style design includes a one-piece outer wall segment 20 and multiple cantilevered CMC airfoils for a stage-2 nozzle 18 of a turbine.
  • An outer wall segment 20 accommodates two cantilevered CMC airfoils as nozzles 18, alternatively at least two cantilevered CMC airfoils, alternatively in the range of two to six cantilevered CMC airfoils, alternatively four cantilevered CMC airfoils, alternatively at least four cantilevered CMC airfoils, alternatively six cantilevered CMC airfoils, alternatively at least six cantilevered CMC airfoils, or any number, range, or sub-range therebetween.
  • a lightweight, high-temperature CMC material of an inner wall segment 16 defining a rotating inner flow path minimizes the pull load and cooling flow needed.
  • the lightweight material permits a pinned attachment of the inner wall segment 16 to the rotary component 12, which may be a rotating rotor wheel 13.
  • the length of the inner wall segments 16 may be greater than one nozzle 18 or blade pitch, which reduces the number of segment gaps to seal.
  • the inner wall segments 16 are preferably attached to a dedicated rotor wheel 13 and not to the upstream or downstream bucket wheels.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP17169742.8A 2016-05-10 2017-05-05 Turbinenanordnung, turbineninnenwandanordnung und turbinenanordnungsverfahren Withdrawn EP3244022A1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US15/150,573 US20170328203A1 (en) 2016-05-10 2016-05-10 Turbine assembly, turbine inner wall assembly, and turbine assembly method

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Publication Number Publication Date
EP3244022A1 true EP3244022A1 (de) 2017-11-15

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EP17169742.8A Withdrawn EP3244022A1 (de) 2016-05-10 2017-05-05 Turbinenanordnung, turbineninnenwandanordnung und turbinenanordnungsverfahren

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US (1) US20170328203A1 (de)
EP (1) EP3244022A1 (de)
JP (1) JP2017207061A (de)

Citations (8)

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GB706730A (en) * 1951-04-11 1954-04-07 Vickers Electrical Co Ltd Improvements relating to turbine rotors
GB1524108A (en) * 1975-12-12 1978-09-06 Mtu Muenchen Gmbh Rotor for fluid flow machine
EP1557536A1 (de) * 2004-01-22 2005-07-27 Siemens Aktiengesellschaft Strömungsmaschine mit einem axial verschiebbaren Rotor
EP2208860A2 (de) * 2009-01-14 2010-07-21 General Electric Company Dichtung zwischen Stufen einer Gasturbine und zugehörige Gasturbine
US20140069101A1 (en) * 2012-09-13 2014-03-13 General Electric Company Compressor fairing segment
WO2014107217A1 (en) * 2012-12-21 2014-07-10 General Electric Company Hybrid turbine nozzle
EP2784269A1 (de) * 2013-03-28 2014-10-01 Rolls-Royce plc Wandabschnitt für den Arbeitsgaskanal eines Gasturbinenmotors, zugehörige Mantelring und Gasturbinenmotor
EP2884051A1 (de) * 2013-12-13 2015-06-17 Siemens Aktiengesellschaft Rotor für eine Strömungsmaschine, Strömungsmaschine, Axialverdichter, Gasturbine und Verfahren zum Herstellen eines Rotors einer Strömungsmaschine

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US2793832A (en) * 1952-04-30 1957-05-28 Gen Motors Corp Means for cooling stator vane assemblies
US2859011A (en) * 1953-07-27 1958-11-04 Gen Motors Corp Turbine bucket and liner
US3042365A (en) * 1957-11-08 1962-07-03 Gen Motors Corp Blade shrouding
US2972470A (en) * 1958-11-03 1961-02-21 Gen Motors Corp Turbine construction
US4655683A (en) * 1984-12-24 1987-04-07 United Technologies Corporation Stator seal land structure
US4869640A (en) * 1988-09-16 1989-09-26 United Technologies Corporation Controlled temperature rotating seal
US5154577A (en) * 1991-01-17 1992-10-13 General Electric Company Flexible three-piece seal assembly
US5232339A (en) * 1992-01-28 1993-08-03 General Electric Company Finned structural disk spacer arm
US6709230B2 (en) * 2002-05-31 2004-03-23 Siemens Westinghouse Power Corporation Ceramic matrix composite gas turbine vane
US7600970B2 (en) * 2005-12-08 2009-10-13 General Electric Company Ceramic matrix composite vane seals
US7470113B2 (en) * 2006-06-22 2008-12-30 United Technologies Corporation Split knife edge seals
GB2462810B (en) * 2008-08-18 2010-07-21 Rolls Royce Plc Sealing means
FR2972877B1 (fr) * 2011-03-15 2013-03-22 Cassidian Sas Procede d'encodage correcteur d'erreur, procede de decodage et dispositifs associes.
US9938846B2 (en) * 2014-06-27 2018-04-10 Rolls-Royce North American Technologies Inc. Turbine shroud with sealed blade track

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB706730A (en) * 1951-04-11 1954-04-07 Vickers Electrical Co Ltd Improvements relating to turbine rotors
GB1524108A (en) * 1975-12-12 1978-09-06 Mtu Muenchen Gmbh Rotor for fluid flow machine
EP1557536A1 (de) * 2004-01-22 2005-07-27 Siemens Aktiengesellschaft Strömungsmaschine mit einem axial verschiebbaren Rotor
EP2208860A2 (de) * 2009-01-14 2010-07-21 General Electric Company Dichtung zwischen Stufen einer Gasturbine und zugehörige Gasturbine
US20140069101A1 (en) * 2012-09-13 2014-03-13 General Electric Company Compressor fairing segment
WO2014107217A1 (en) * 2012-12-21 2014-07-10 General Electric Company Hybrid turbine nozzle
EP2784269A1 (de) * 2013-03-28 2014-10-01 Rolls-Royce plc Wandabschnitt für den Arbeitsgaskanal eines Gasturbinenmotors, zugehörige Mantelring und Gasturbinenmotor
EP2884051A1 (de) * 2013-12-13 2015-06-17 Siemens Aktiengesellschaft Rotor für eine Strömungsmaschine, Strömungsmaschine, Axialverdichter, Gasturbine und Verfahren zum Herstellen eines Rotors einer Strömungsmaschine

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US20170328203A1 (en) 2017-11-16
JP2017207061A (ja) 2017-11-24

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