EP2620595A1 - Turbinenabdichtungsabweiser - Google Patents

Turbinenabdichtungsabweiser Download PDF

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Publication number
EP2620595A1
EP2620595A1 EP13152139.5A EP13152139A EP2620595A1 EP 2620595 A1 EP2620595 A1 EP 2620595A1 EP 13152139 A EP13152139 A EP 13152139A EP 2620595 A1 EP2620595 A1 EP 2620595A1
Authority
EP
European Patent Office
Prior art keywords
inner band
directors
array
flow path
rotor
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Withdrawn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
EP13152139.5A
Other languages
English (en)
French (fr)
Inventor
Modachur Krishnan Prabakaran
Moorthi Subramaniyan
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 EP2620595A1 publication Critical patent/EP2620595A1/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Withdrawn legal-status Critical Current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
    • F01D11/001—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
    • 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
    • F05D2240/12—Fluid guiding means, e.g. vanes

Definitions

  • the subject matter disclosed herein relates to turbine engines.
  • the flowpath through a turbine along the root radius is defined in part by the inner bands or rings of the nozzles and flow surfaces along the platforms at the roots of the buckets on the rotor. Any fluid flow leakage exiting the flowpath along the root radii bypasses the buckets and nozzles, and directly decreases the performance of the turbine stage. Teeth arranged on the rotor adjacent to the fluid flow leakage increase the swirl of the fluid flow leakage.
  • a typical nozzle and bucket design of, for example, a steam turbine stage includes a nozzle root diameter equal to the bucket root diameter, resulting in a significant probability of an upstream facing step, which disturbs the streamline characteristics of the fluid flow in the flowpath. Radial reentry flows cause fluid flow random mixing along the flowpath with consequent aerodynamic efficiency losses.
  • an inner band of turbine nozzle array includes a leading portion and a trailing portion, and an array of directors arranged on the inner band, the array of directors operative to direct a flow path of fluid, the flow path of fluid partially defined by a rotor and the inner band.
  • a turbo machine includes a rotor being rotatable about an axis, a circumferential array of nozzles having circumferentially spaced airfoils and inner and outer bands disposed at opposite ends thereof, the inner band having a leading portion and a trailing portion, and an array of directors arranged on the inner band, the array of directors operative to direct a flow path of fluid, the flow path of fluid partially defined by the rotor and the inner band.
  • an array of directors includes a plurality of fins extending from a guide surface of an inner band portion of a turbine, the inner band portion arranged at an end portion of an array of nozzles, the plurality of fins being operative to direct a flow path of a fluid, the flow path partially defined by the inner band portion and a portion of a rotor having an axis of rotation.
  • FIG. 1 illustrates a portion of an exemplary embodiment of a turbo machine 100.
  • the turbine defines an inner or root region of a flowpath, indicated by the arrow and generally designated 10.
  • Energetic fluid e.g., steam
  • the turbo machine 100 includes a rotor 102 rotatable about a horizontal axis and a plurality of axially spaced rotor wheels 104, each carrying a plurality of circumferentially spaced buckets 106.
  • FIG. 1 includes a stationary component 108 of the turbine, including axially spaced arrays of nozzles 110.
  • Each array of nozzles 110 has circumferentially spaced stationary airfoils 112 mounted between inner bands or rings 114 and outer bands or rings 116.
  • the inner bands 114 include leading portions 203 and trailing portions 204, where the leading portion 203 is upstream of the flowpath 10 relative to the trailing portions 204.
  • the inner bands 114 each define a plane normal to the axis of rotation of the rotor 102.
  • Each nozzle 110 and a downstream array of buckets 106 form a turbine stage, there being a plurality of stages within the turbine section of the turbine.
  • Packing rings (packing ring segments) 118 are provided between the stationary component 108, e.g., inner bands 114, and the rotor surface 120 between the rotor wheels 104 for sealing leakage flowpaths between the stationary and rotary components.
  • Teeth 122 are arranged on the rotor surface 120 proximate to and corresponding with an inner surface 124 of the inner band 114.
  • the teeth 122 and the inner surface 124 of the inner bands 114 define gaps 101.
  • the gap 101 defines a leakage flow path of energetic fluid indicated by the arrows 11. The leakage flow path results in an aerodynamic inefficiency when the fluid reenters the root region of the flow path.
  • a plurality of directors (diverters) 126 are arranged at the trailing portions 204 of the inner bands 114 and in the leakage flow path.
  • the directors 126 in the illustrated embodiment are operative to direct the leakage flow into the root region of the main flow path while reducing the aerodynamic inefficiency of the introduction of the leakage flow path into the root region of the flow path.
  • the directors 126 may include fins or other similar structures extending from the inner bands 114.
  • the directors 126 may include fins having opposing planar profiled sides or fins having arcuate shaped opposing sides.
  • FIG. 2 illustrates a partial view of the region 2 (of FIG. 1 ).
  • the director 126 is arranged proximate to the trailing portion 204 of the inner band 114.
  • the trailing portion 204 includes a surface portion 206 that is substantially perpendicular to the axis of rotation of the rotor 102 and a guide surface portion 202 that is arranged at an angle ( ⁇ ) relative to the axis of rotation of the rotor 102.
  • the line 201 is shown parallel to the axis of rotation of the rotor 102.
  • the surface portion 206 and the guide surface portion 202 define an angle ( ⁇ ). In the illustrated embodiment the angle ⁇ is greater than 90° while the angle ⁇ is less than 90°.
  • angles ⁇ and ⁇ may include any number of degrees, for example the angles ⁇ and ⁇ may each be 90° or greater than or less than 90°.
  • the angles ⁇ and ⁇ may be selected in the design process to reduce the aerodynamic inefficiency of the introduction of the leakage flow path into the root region of the flow path.
  • the angles ⁇ and ⁇ may depend on the pressure and flow rate of the fluid at a particular nozzle stage and the geometry of the nozzle stage.
  • the position of the tooth 122 relative to the position of the directors 126 (as shown by the indicated distance x) may be chosen to direct the leakage flow path to generally follow along the surface 208, which is arranged generally coaxially with the rotor 102.
  • the distance x may be determined partially by the distance y, which is defined by the surface portion 206 and a surface 220 of the rotor wheel 104.
  • the ratio of x:y should between 0.3 to 1, where x ⁇ y.
  • the desired value of the ratio may be determined by considering the axial movement of the rotor 104 during transient conditions (i.e., startup and shutdown conditions).
  • FIG. 3 illustrates a perspective partially transparent view of the region 2 (of FIG. 1 ) with the leakage flow path indicated by the arrow 11.
  • the leakage flow path is diverted by the directors 126 and the guide surface portion 202 (of FIG. 2 ) such that the leakage flow path flows more efficiently and less randomly into the root region of the flow path.
  • the leakage flow path is partially defined by the guide surface portion 202, the directors 126, and a leading edge surface 220 of the rotor wheel 104.
  • FIG. 4 illustrates a perspective, partially cut-away view of a portion of an exemplary embodiment of the turbo machine 100.
  • the directors 126 are shown arranged radially on the guide surface 202.
  • the directors 126 are arranged substantially parallel to each other.
  • Each director 126 is partially defined by opposing linear surfaces that are substantially parallel to each other.
  • the directors 126 are arranged such that the linear axis of the directors 126 illustrated by line 401 and a line 403 perpendicular to the axis of rotation of the rotor 102 defines an angle ( ⁇ ).
  • the angle ⁇ may be selected during the design of the turbo machine 100 to reduce the aerodynamic inefficiency of the introduction of the leakage flow path into the root region of the flow path and may include any angle between, for example, 0°-180°.
  • FIG. 5 illustrates a perspective, partially cut-away view of a portion of another exemplary embodiment of the turbo machine 100.
  • the directors 126 are formed in an arcuate shape.
  • the leading and trailing edges of the directors 126 define a chord line 501 the chord line and a line 503 perpendicular to the axis of rotation of the rotor 102 define the angle ⁇ .
  • the angle ⁇ may include any angle that reduces aerodynamic inefficiency of the introduction of the leakage flow path into the root region of the flow.
  • FIG. 6 illustrates an exemplary embodiment of the turbo machine 100, where the directors 126 are arranged on a base portion 602 that is secured to the inner band 114.
  • the base portion 602 may be secured to the inner band 114 by any suitable method including, fasteners, welding, or brazing.
  • FIG. 7 illustrates another exemplary embodiment of the turbo machine 100, wherein the directors 126 are arranged on a base portion 702 that slidably engages a portion of inner band 114.
  • FIG. 8 illustrates an exemplary embodiment of a turbine machine compressor 800.
  • the compressor 800 includes diverters 126 arranged on inner bands 114. Teeth 122 are arranged on the rotor surface 120.
  • the main flow path 802 is generally designated by the arrow 80.
  • the inner bands 114 and the teeth 122 define a leakage flow path 81 generally designated by the arrow 81.
  • the diverters 126 are arranged proximate to an upstream portion 805 of the inner bands 114.
  • the leakage flow path 81 flows generally from a down stream portion 803 of the inner bands 114 to the up stream portion 805 where the diverters 126 induce effects to the leakage flow path 81 as described above in the turbo machine 100.
  • FIG. 9 illustrates another exemplary embodiment of a turbo machine 900.
  • the a plurality of directors (diverters) 126 are arranged between the leading portions 203 and trailing portions 204 of the inner bands 114 and in the leakage flow path indicated by the arrows 11.
  • the directors 126 are disposed between two of the teeth 122 however, in alternate embodiments, the directors 126 may be arranged before or after the teeth 122 relative to the flow path 10.
  • the embodiments described above increase the efficiency of a turbine machine by reducing the mixing losses and randomness of the introduction of leakage flows into root regions of the main flow path.
  • the increased efficiency is realized by the use of diverters arranged on inner rings proximate to the trailing edges of the turbine nozzles.
  • the diverters reduce the aerodynamic inefficiency of the introduction of the leakage flow into the root region of the main flow path.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
EP13152139.5A 2012-01-24 2013-01-22 Turbinenabdichtungsabweiser Withdrawn EP2620595A1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/356,840 US20130189107A1 (en) 2012-01-24 2012-01-24 Turbine Packing Deflector

Publications (1)

Publication Number Publication Date
EP2620595A1 true EP2620595A1 (de) 2013-07-31

Family

ID=47631295

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13152139.5A Withdrawn EP2620595A1 (de) 2012-01-24 2013-01-22 Turbinenabdichtungsabweiser

Country Status (5)

Country Link
US (1) US20130189107A1 (de)
EP (1) EP2620595A1 (de)
JP (1) JP2013151935A (de)
CN (1) CN103216276A (de)
RU (1) RU2013102781A (de)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP5591042B2 (ja) * 2010-09-17 2014-09-17 三菱重工業株式会社 タービン
EP3147460A1 (de) * 2015-09-23 2017-03-29 General Electric Technology GmbH Axialturbine
US10822977B2 (en) * 2016-11-30 2020-11-03 General Electric Company Guide vane assembly for a rotary machine and methods of assembling the same
FR3099788B1 (fr) * 2019-08-06 2021-09-03 Safran Aircraft Engines Abradable de turbine de turbomachine comprenant une face d’usure pourvue de redresseurs de flux
IT202000013609A1 (it) * 2020-06-08 2021-12-08 Ge Avio Srl Componente di un motore a turbina con un insieme di deflettori
US11692451B1 (en) * 2022-03-28 2023-07-04 Pratt & Whitney Canada Corp. Aircraft engine with radial clearance between seal and deflector

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0894944A1 (de) * 1997-07-29 1999-02-03 Siemens Aktiengesellschaft Turbinenbeschaufelung
GB2417053A (en) * 2004-08-11 2006-02-15 Rolls Royce Plc A turbine comprising baffles situated between turbine blades and guide vanes
US20080056895A1 (en) * 2006-08-31 2008-03-06 Shigeki Senoo Axial turbine

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US881474A (en) * 1906-08-14 1908-03-10 Belliss & Morcom Ltd Turbine-motor.
US4370094A (en) * 1974-03-21 1983-01-25 Maschinenfabrik Augsburg-Nurnberg Aktiengesellschaft Method of and device for avoiding rotor instability to enhance dynamic power limit of turbines and compressors
JP2002285802A (ja) * 2001-03-26 2002-10-03 Toshiba Corp 回転機械のラビリンスシール装置
US7549835B2 (en) * 2006-07-07 2009-06-23 Siemens Energy, Inc. Leakage flow control and seal wear minimization system for a turbine engine
US8419356B2 (en) * 2008-09-25 2013-04-16 Siemens Energy, Inc. Turbine seal assembly
US8282346B2 (en) * 2009-04-06 2012-10-09 General Electric Company Methods, systems and/or apparatus relating to seals for turbine engines

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0894944A1 (de) * 1997-07-29 1999-02-03 Siemens Aktiengesellschaft Turbinenbeschaufelung
GB2417053A (en) * 2004-08-11 2006-02-15 Rolls Royce Plc A turbine comprising baffles situated between turbine blades and guide vanes
US20080056895A1 (en) * 2006-08-31 2008-03-06 Shigeki Senoo Axial turbine

Also Published As

Publication number Publication date
US20130189107A1 (en) 2013-07-25
JP2013151935A (ja) 2013-08-08
RU2013102781A (ru) 2014-07-27
CN103216276A (zh) 2013-07-24

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