EP2743454A1 - Turbinenkomponente mit Kühlbohrungen mit variierendem Durchmesser - Google Patents

Turbinenkomponente mit Kühlbohrungen mit variierendem Durchmesser Download PDF

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Publication number
EP2743454A1
EP2743454A1 EP13195501.5A EP13195501A EP2743454A1 EP 2743454 A1 EP2743454 A1 EP 2743454A1 EP 13195501 A EP13195501 A EP 13195501A EP 2743454 A1 EP2743454 A1 EP 2743454A1
Authority
EP
European Patent Office
Prior art keywords
turbine
cooling passage
section
diameter
elongated cooling
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Withdrawn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
EP13195501.5A
Other languages
English (en)
French (fr)
Inventor
Xiuzhang James Zhang
Adebukola Oluwaseun Benson
Richard Ryan Pilson
Stephen William Tesh
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 EP2743454A1 publication Critical patent/EP2743454A1/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Withdrawn legal-status Critical Current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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • 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
    • F05D2230/10—Manufacture by removing material
    • F05D2230/11—Manufacture by removing material by electrochemical methods
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/232—Three-dimensional prismatic conical
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/25—Three-dimensional helical
    • 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
    • F05D2250/30—Arrangement of components
    • F05D2250/32—Arrangement of components according to their shape
    • F05D2250/323—Arrangement of components according to their shape convergent

Definitions

  • the subject matter disclosed herein relates to cooling passages in turbine components, more specifically, to turbine nozzles, shrouds, and/or buckets having shaped tube electrochemical machined (STEM) cooling holes with a varying diameter (e.g., a convergent shape, a divergent shape, etc.) therein.
  • STEM shaped tube electrochemical machined
  • efficiencies are directly proportional to the temperature of turbine gases flowing along the hot gas path and driving the turbine blades.
  • These gas turbines typically have operating temperatures on the order of approximately 2700 degrees Fahrenheit (1482 degrees Celsius), a temperature which may stress and/or damage turbine components (e.g., turbine buckets, shrouds, nozzles, etc.).
  • the components are manufactured from advanced materials and typically include smooth bore cooling passages with a constant diameter for flowing a cooling medium, typically compressor discharge air, through the buckets. These passages also typically extend from the radially inner bucket root to the radially outer bucket tip with a consistent diameter.
  • STEM Shaped Tube Electrochemical Machining
  • STEM is used for non-contact drilling of small, deep holes in electrically conductive materials, with high aspect ratios (e.g., a ratio of the length or depth of the hole to the largest lateral dimension (e.g., diameter of the hole), which in certain specific applications can be as small as a few millimeters) such as 300:1.
  • the STEM process removes stock by electrolytic dissolution, utilizing a flow of electric current between an electrode and the workpiece through an electrolyte flowing in the intervening space to form the radial cooling flow passages.
  • turbulence promoters are also used in many gas turbine buckets to enhance the internal heat transfer coefficient. This heat transfer enhancement may increase the heat transfer coefficient to more than two times greater than smooth-bore passages for the same cooling flow rate.
  • Turbulators conventionally comprise internal ridges or roughened surfaces along the interior surfaces of the cooling passages.
  • formation of these smooth-bore passages and/or turbulators may be limited by wall thickness requirements within the turbine bucket, particularly in proximity to a tip and/or trailing edge of the turbine bucket which typically has very small/thin dimensions.
  • Turbine components e.g., turbine nozzles, shrouds, and/or buckets having shaped tube electrochemical machined (STEM) cooling holes with a varying diameter (e.g., a convergent shape, a divergent shape, etc.) are disclosed.
  • STEM shaped tube electrochemical machined
  • a first aspect of the invention includes: a turbine component including: at least one elongated cooling passage extending from a root of the bucket to a tip of the bucket, wherein the elongated cooling passage has a variable diameter along a length of the bucket.
  • a second aspect of the invention includes: turbine bucket including: a root configured to connect to a turbine; a base disposed on the root and configured to extend into a turbine flowpath, the base having an airfoil shape and including a tip; and at least one elongated cooling passage formed in the root and the base, the at least one elongated cooling pass including: a first section disposed proximate the root and including an aperture at a terminus of the at least one elongated cooling passage, the first section extending into the base, and a second section fluidly connected to the first section and disposed proximate the tip, wherein a second diameter of the second section is smaller than a first diameter of the first section.
  • a third aspect of the invention includes: a turbine including: a stator; a working fluid passage substantially surrounded by the stator; a rotor disposed radially inboard of the stator and in the working fluid passage; and a turbine bucket connected to the rotor, the turbine bucket including: at least one elongated cooling passage extending from a root of the turbine bucket to a tip of the turbine bucket, wherein the elongated cooling passage has a variable diameter along a length of the turbine bucket.
  • FIGS. 1-12 are not necessarily to scale. The drawings are intended to depict only typical aspects of the invention, and therefore should not be considered as limiting the scope of the invention. It is understood that elements similarly numbered between the FIGURES may be substantially similar as described with reference to one another. Further, in embodiments shown and described with reference to FIGS. 1-12 , like numbering may represent like elements. Redundant explanation of these elements has been omitted for clarity. Finally, it is understood that the components of FIGS. 1-12 and their accompanying descriptions may be applied to any embodiment described herein.
  • turbine components e.g., nozzles, shrouds, buckets, etc.
  • STEM shaped cooling passages with a varying diameter e.g., convergent, divergent, etc.
  • cooling passages through turbine components are conventionally cylindrical passageways with a substantially constant diameter from root to tip.
  • the diameter of the coolant passages is constant and is therefore limited by the thinnest part of the turbine component (e.g., the blade tip, the trailing edge, the nozzle trailing edge, etc.).
  • aspects of the invention include a turbine component (e.g., turbine bucket, turbine nozzle, nozzle trailing edge, shroud, etc.) having cooling passages with a varying diameter (e.g., a cooling passage which has a first diameter in one portion of the turbine bucket which varies in dimensional size from a second diameter of the cooling passage in a second portion of the turbine bucket, convergent cooling passages, divergent cooling passages, etc.).
  • the cooling passage diameter may decrease/diminish (e.g., gradually, telescopically, stepwise, etc.) across a length of the cooling passage in a convergent manner.
  • the varying diameter of the cooling passage has a larger dimension proximate a root of a turbine component (e.g., bucket) relative to a diameter of the cooling passage proximate a tip of the turbine bucket (e.g., a small diameter cooling passage proximate the tip of the turbine bucket which has an increasingly larger diameter as the cooling passage extends through mid and lower points of an airfoil span of the turbine bucket).
  • the thickness/diameter of the cooling passage may be greater at the turbine bucket root where a cooling fluid flow may be introduced, this thickness increasing the sectional area proximate the root and increasing flow of the cooling fluid there through.
  • the cooling passage may include an aperture (e.g., metering feature) through the nozzle trailing edge configured to manipulate/control characteristics of a cooling flow through the cooling passage.
  • Turbine bucket 100 includes a base (e.g., an airfoil) 130 connected to a root 120 which is configured to connect to a turbine system.
  • set of cooling passages 110 may be formed/shaped through shaped tube electrochemical machining (STEM).
  • Set of cooling passages 110 extend substantially radially from root 120 toward a tip 132 of base 130.
  • Base 130 is shaped as an airfoil and includes a trailing edge 134 with a relatively thin thickness.
  • Set of cooling passages 110 may enable a cooling flow 70 to pass through turbine component 100 and may include a varying diameter (e.g., convergent, divergent, etc.).
  • a diameter of set of cooling passages 110 may vary in proportion/relation to a thickness of turbine bucket 100.
  • Cooling passages 110 are defined by an interior surface of turbine bucket 100 and may include an aperture 118 which allows cooling flow 70 to enter a flow path of a turbine.
  • the terms “axial” and/or “axially” refer to the relative position/direction of objects along axis A, which is substantially perpendicular to the axis of rotation of the turbomachine (in particular, the rotor section).
  • the terms “radial” and/or “radially” refer to the relative position/direction of objects along axis (r), which is substantially perpendicular with axis A and intersects axis A at only one location.
  • the terms “circumferential” and/or “circumferentially” refer to the relative position/direction of objects along a circumference which surrounds axis A but does not intersect the axis A at any location.
  • FIG. 2 a portion of a rotor 10 is shown including a first wheel 12 and a second wheel 14.
  • Each of the wheels 12 and 14 carries a circumferential array of buckets 16 and 18, respectively.
  • Circumferential arrays of first and second-stage nozzle vanes 20 and 22 are also shown. It will be appreciated that the buckets 16 and 18 and nozzle vanes 20 and 22 lie in the working fluid flowpath 21 of the turbine.
  • Nozzle vane 22 is carried by an inner shell 24 which disposes nozzle vanes 20 and 22 in the flowpath.
  • the trailing edges of the nozzle vanes 20 and 22 are cooled by a flow of liquid (e.g., air, compressor discharge, etc.) into a trailing edge cavity 26 for flow through cooling passages 110 through the trailing edge tip 34 into the flowpath.
  • set of cooling passages 110 may extend to a nozzle trailing edge 34, a diameter of the cooling passages 110 decreasing relative to a proximity to the trailing edge 34 (e.g., convergently, divergently, etc.).
  • cooling passage 210 with a set of sections 220, 230, and 240, with varied diameter in accordance with embodiments of the invention.
  • Cooling passage 210 is defined by an inner surface 280 of turbine component 200.
  • cooling passage 210 includes a first section 220 fluidly connected to a second section 230 and a third section 240.
  • first section 220 may include a first diameter A
  • second section 230 may include a second diameter B
  • third section 240 may include a third diameter C.
  • first section 220, second section 230, and third section 240 may form a step (e.g., incremental, tiered, telescoped, etc.) shaped cooling passage 210, whereby a diameter of cooling passage 210 decreases incrementally/stepwise as cooling passage 210 extends (e.g., radially) through turbine component 200.
  • cooling flow 70 may flow in a convergent direction through first section 220 to second section 230 and/or third section 240.
  • Diameter A of first section 220 may be greater than diameter B of second section 230, and diameter B of second section 230 may be greater than diameter C of third section 240.
  • inner surface 280 may have a substantially uniform material composition (e.g., metal, ceramic, etc.) throughout cooling passage 210.
  • inner surface 280 comprises a machined surface of turbine component 200. It is understood that while embodiments are described with reference to particular cooling passages, these embodiments may be combinable and/or applicable to any cooling passages described herein, including cooling passages 110, 210, 310, 410, etc.
  • Cooling passage 310 has a diameter D which varies gradually (e.g., from a dimension D 1 , D 2 , etc.) in a convergent fashion from a base 302 of turbine component 300 toward a tip 304 of turbine component 300.
  • An interior surface of cooling passage 310 may be angled and have a substantially coned/frusto-conical shape.
  • Cooling passage 410 may include a first section 420 with a substantially coned shape fluidly connected to a second section 430 with a reduced diameter 'G.
  • First section 420 may have a diameter E which gradually diminishes (e.g., from E 1 , to E 2 , to E 1+N ) between a root 402 of turbine component 400 and second section 430. It is understood that the descriptions and/or combinations of cooling passage sections described herein are merely exemplary, and that any combination, modification, orientation, and/or arrangement of cooling passage sections may be included in accordance with embodiments.
  • Cooling passage 510 may have a coned/frusto-conical shape and include a turbulator 550 disposed on a surface 518 of cooling passage 510.
  • Turbulator 550 may extend into a flow path of cooling flow 70 and may be configured to induce and/or enhance turbulent flow.
  • turbulator 550 may include a set of sections (e.g., rings, tabs, protrusions, etc.) disposed within cooling passage 510.
  • the set of sections of turbulator 550 may be disposed at a proximity relative one another which is in a range of about 7 to about 13 times a relative protrusion height (e.g., how far each section protrudes into cooling passage 510) of each of the sections of turbulator 550.
  • the set of sections may be disposed at a substantially regular interval relative to one another.
  • a portion of a turbine component 600 may include a cooling passage 610 as shown in accordance with embodiments. Cooling passage 610 may include a turbulator 650 disposed on a surface of cooling passage 610 with a substantially swirl shaped configuration.
  • Turbulator 650 may include a first end 622 disposed proximate a root portion 612 of turbine component 600, and second end 624 disposed proximate a tip portion 614 of turbine component 600. Turbulator 650 may be disposed circumferentially about cooling passage 610 while extending radially outward through cooling passage 610. In an embodiment, flow 70 may travel through cooling passage 610 in a divergent direction (e.g., from a first section of cooling passage 610 with a first diameter to a second section of cooling passage 610 with a second diameter which is greater than the first diameter) from tip portion 614 toward root portion 612. It is understood that cooling flow 70 as described in embodiments herein may flow in any direction, and that the embodiments described herein are merely exemplary.
  • cooling passage 710 includes a first portion 714 which is fluidly connected to a metering feature 712.
  • Metering feature 712 includes an aperture 716 disposed at a terminus of cooling passage 710.
  • a flow 70 e.g., air
  • Metering feature 712 may fluidly connect cooling passage 710 to a fluid passage of a turbine.
  • metering feature 712 and/or aperture 716 may be adjustable/variable in diameter.
  • Metering feature 712 and/or aperture 716 may control/meter cooling flow 70 in and/or through cooling passage 710 and may be modified/machined by a technician to adjust flow characteristics through cooling passage 710 (e.g., during maintenance, diagnostics, testing, cold flows, etc.).
  • aperture 716 and/or metering feature 712 may be machined to tune cooling passage 710 to meet design/nominal amounts and flow results.
  • aperture 716 and/or metering feature 712 may be adjusted (e.g., increased, drilled out, etc,) during cold testing of the component to correct manufacturing irregularities/errors.
  • a technician may increase (e.g., drill, bore, STEM, etc.) a diameter of metering feature 712 and/or aperture 716 in order to adjust the heat transfer coefficient within cooling passage 710.
  • a turbine component 800 may include a cooling passage 810 with a telescoping (e.g., incremental, stepped, etc.) shape and a metering feature 812.
  • Cooling passage 810 may include a first section 814 with a diameter which is greater than a diameter of a second section 818.
  • cooling passage 810 may include a metering feature 812 which is fluidly connected to second section 818.
  • Metering feature 812 may include an aperture 816 and enable cooling flow 70 to enter and/or exit cooling passage 810.
  • a turbine component 850 may include a cooling passage 870 with a substantially constant diameter and a set of turbulators 880 disposed on a surface thereof.
  • Turbine component 850 may include a metering feature 874 with an aperture 878 configured to meter/control cooling flow 70 through cooling passage 870.
  • Combined cycle power plant 900 may include, for example, a gas turbine 980 operably connected to a generator 970.
  • Generator 970 and gas turbine 980 may be mechanically coupled by a shaft 915, which may transfer energy between a drive shaft (not shown) of gas turbine 980 and generator 970.
  • a heat exchanger 986 operably connected to gas turbine 980 and a steam turbine 992. Heat exchanger 986 may be fluidly connected to both gas turbine 980 and a steam turbine 992 via conventional conduits (numbering omitted).
  • Gas turbine 980 and/or steam turbine 992 may include component 100 and/or set of cooling passages 110 of FIG. 1 or other embodiments described herein.
  • Heat exchanger 986 may be a conventional heat recovery steam generator (HRSG), such as those used in conventional combined cycle power systems. As is known in the art of power generation, HRSG 986 may use hot exhaust from gas turbine 980, combined with a water supply, to create steam which is fed to steam turbine 992.
  • Steam turbine 992 may optionally be coupled to a second generator system 970 (via a second shaft 915). It is understood that generators 970 and shafts 915 may be of any size or type known in the art and may differ depending upon their application or the system to which they are connected.
  • a single shaft combined cycle power plant 990 may include a single generator 970 coupled to both gas turbine 980 and steam turbine 992 via a single shaft 915.
  • Steam turbine 992 and/or gas turbine 980 may include set of cooling passages 110 of FIG. 1 or other embodiments described herein.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Electrical Discharge Machining, Electrochemical Machining, And Combined Machining (AREA)
EP13195501.5A 2012-12-11 2013-12-03 Turbinenkomponente mit Kühlbohrungen mit variierendem Durchmesser Withdrawn EP2743454A1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/711,241 US20140161625A1 (en) 2012-12-11 2012-12-11 Turbine component having cooling passages with varying diameter

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Publication Number Publication Date
EP2743454A1 true EP2743454A1 (de) 2014-06-18

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EP13195501.5A Withdrawn EP2743454A1 (de) 2012-12-11 2013-12-03 Turbinenkomponente mit Kühlbohrungen mit variierendem Durchmesser

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US (1) US20140161625A1 (de)
EP (1) EP2743454A1 (de)
JP (1) JP2014114816A (de)
CN (1) CN203835473U (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3306036A1 (de) * 2016-10-04 2018-04-11 Honeywell International Inc. Turbinenschaufel mit einem kühlkanal und einer durchflusskontrolle
EP3081754B1 (de) * 2015-04-13 2021-06-02 General Electric Company Turbinenschaufel
DE102014103007B4 (de) 2013-03-14 2024-05-16 General Electric Technology Gmbh Kühlkanäle für Turbinenschaufeln einer Gasturbine

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US10247099B2 (en) * 2013-10-29 2019-04-02 United Technologies Corporation Pedestals with heat transfer augmenter
EP2918782A1 (de) * 2014-03-11 2015-09-16 United Technologies Corporation Bauteil mit Kühlungsloch mit Wendelnut und zugehöriges Gasturbinenkraftwerk
EP2990605A1 (de) * 2014-08-26 2016-03-02 Siemens Aktiengesellschaft Turbinenschaufel
US10137499B2 (en) * 2015-12-17 2018-11-27 General Electric Company Method and assembly for forming components having an internal passage defined therein
US10851663B2 (en) * 2017-06-12 2020-12-01 General Electric Company Turbomachine rotor blade
US10989070B2 (en) * 2018-05-31 2021-04-27 General Electric Company Shroud for gas turbine engine
US11339668B2 (en) * 2018-10-29 2022-05-24 Chromalloy Gas Turbine Llc Method and apparatus for improving cooling of a turbine shroud
JP6637630B1 (ja) * 2019-06-05 2020-01-29 三菱日立パワーシステムズ株式会社 タービン翼およびタービン翼の製造方法並びにガスタービン
KR102630916B1 (ko) * 2019-06-05 2024-01-29 미츠비시 파워 가부시키가이샤 터빈 날개 및 터빈 날개의 제조 방법 및 가스 터빈
CN114776403B (zh) * 2021-12-29 2023-12-26 东方电气集团东方汽轮机有限公司 一种适用于大焓降小流量透平进气结构及其方法

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Publication number Priority date Publication date Assignee Title
DE102014103007B4 (de) 2013-03-14 2024-05-16 General Electric Technology Gmbh Kühlkanäle für Turbinenschaufeln einer Gasturbine
EP3081754B1 (de) * 2015-04-13 2021-06-02 General Electric Company Turbinenschaufel
EP3306036A1 (de) * 2016-10-04 2018-04-11 Honeywell International Inc. Turbinenschaufel mit einem kühlkanal und einer durchflusskontrolle
US10683763B2 (en) 2016-10-04 2020-06-16 Honeywell International Inc. Turbine blade with integral flow meter

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US20140161625A1 (en) 2014-06-12
JP2014114816A (ja) 2014-06-26
CN203835473U (zh) 2014-09-17

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