EP2581555A1 - Composant de turbomachine présentant une caractéristique de contour d'écoulement - Google Patents

Composant de turbomachine présentant une caractéristique de contour d'écoulement Download PDF

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Publication number
EP2581555A1
EP2581555A1 EP12187836.7A EP12187836A EP2581555A1 EP 2581555 A1 EP2581555 A1 EP 2581555A1 EP 12187836 A EP12187836 A EP 12187836A EP 2581555 A1 EP2581555 A1 EP 2581555A1
Authority
EP
European Patent Office
Prior art keywords
gas path
turbomachine
flow contour
contour feature
wheelspace
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Withdrawn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
EP12187836.7A
Other languages
German (de)
English (en)
Inventor
Alexander Stein
Clint Luigie Ingram
Bradley Taylor Boyer
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 EP2581555A1 publication Critical patent/EP2581555A1/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Withdrawn legal-status Critical Current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
    • 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
    • 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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations

Definitions

  • the subject matter disclosed herein relates to the art of turbomachines and, more particularly, to turbomachine components having a flow contour feature.
  • gas turbomachines include a combustor assembly within which a fuel/air mixture is combusted to release heat energy.
  • the heat energy forms a high temperature gas stream that is channeled to a turbine portion via a hot gas path.
  • the turbine portion converts thermal energy from the high temperature gas stream to mechanical energy that rotates a turbine shaft.
  • the turbine portion may be used in a variety of applications, such as for providing power to a pump or an electrical generator.
  • the high temperature gas stream passes over vanes and blades arranged in sequential stages along the hot gas path.
  • a first stage of the turbine portion includes first stage vanes including an airfoil that is configured to direct the high temperature gas stream tangentially toward first stage blades.
  • the high temperature gas stream aerodynamically interacts with and induces rotation of the first stage blades.
  • the first turbine stages exhibit strong secondary flows in which high energy and high temperature fluids flow in a direction transverse to a main flow direction. That is, if the main flow direction is presumed to be axial, the secondary flows propagate circumferentially or radially.
  • the secondary flows can negatively impact the stage efficiency and has led to development of non-axisymetric endwall contouring (EWC), which has been effective in reducing secondary flow losses for turbines.
  • EWC non-axisymetric endwall contouring
  • Current EWC is, however, only geared towards gas path surfaces.
  • a turbomachine component includes a main body having a gas path surface configured to be exposed to gases passing along a turbomachine gas path, a non gas path surface configured to be arranged in a turbomachine wheelspace outside the turbomachine gas path, and a non-axisymetric flow contour feature extending from the gas path surface to the non gas path surface.
  • a turbomachine bucket includes an airfoil portion, and a base portion supporting the airfoil portion.
  • the base portion includes one or more gas path surfaces configured to be exposed to gases passing along a turbomachine gas path, one or more non gas path surfaces configured to be arranged outside the turbomachine gas path, and a non-axisymetric flow contour feature extending from at least one of the one or more gas path surfaces to at least one of the one or more non gas path surfaces.
  • a turbomachine includes a housing, a gas path extending through the housing, a wheelspace arranged within the housing and substantially fluidly separated from the gas path, and at least one turbomachine component arranged in the housing.
  • the turbomachine component includes at least one gas path surface arranged within the gas path, at least one non gas path surface arranged within the wheelspace, and a non-axisymetric flow contour feature extending from the at least one gas path surface to the at least one non gas path surface.
  • Turbomachine 2 includes a compressor portion 4 and a turbine portion 6.
  • Compressor portion 4 is fluidly coupled to turbine portion 6 through a combustor assembly 8.
  • Compressor portion 4 is also mechanically linked to turbine portion 6 via a common compressor/turbine shaft 10.
  • Turbine portion 6 includes a plurality of stages 14 that extend along a hot gas path 15. Stages 14 include a first stage 16, a second stage 18, and a third stage 20. The number of stages for turbine portion 6 could of course vary.
  • First stage 16 includes a plurality of stationary vanes one of which is indicated at 22 and a plurality of rotating airfoil members or buckets one of which is indicated at 24.
  • second stage 18 includes a plurality of second stage stationary vanes one of which is indicated at 26 and second stage rotating airfoil members or buckets one of which is indicated at 28.
  • Third stage 20 includes a plurality of third stage stationary vanes one of which is indicated at 30 and a plurality of third stage rotating airfoil members or buckets one of which is indicated at 32.
  • second stage bucket 28 includes an airfoil portion 40 and a base portion 44.
  • Airfoil portion 40 extends from base portion 44 and includes a pressure side 47, a suction side 48, a leading edge 49, and a trailing edge 50. Airfoil portion 40 is exposed to combustion gases flowing along a hot gas path (not separately labeled) of turbine portion 6.
  • Base portion 44 includes a main body 52 having a front face 54, an aft face 55, and an airfoil support surface 57 and a connection member (not shown). Airfoil support surface 57 supports airfoil portion 40 while the connection member provides an interface to a second stage turbine wheel or rotor (also not shown).
  • Second stage bucket 28 includes a gas path portion 61 that includes airfoil portion 40 and portions of base portion 44 above a point denoted by a line 64, and a non-gas path portion 68 that includes portions of base portion 44 below line 64.
  • Gas path portion 61 includes all portions of second stage blade 28 that are exposed to combustion gases flowing along the hot gas path.
  • Non-gas path portion 68 includes all surfaces of base portion 44 that are arranged in a wheelspace (not shown) of turbine portion 6.
  • Base portion 44 includes a first gas path surface 71 that includes airfoil support surface 57 and a second gas path surface 73 that includes a portion of front face 54 above line 64.
  • Base portion 44 also includes non-gas path surfaces 77 that include a trench surface portion 79, a buffer surface portion 81, an upper angel wing 83 and a lower angel wing 85.
  • non-gas path surfaces 77 that include a trench surface portion 79, a buffer surface portion 81, an upper angel wing 83 and a lower angel wing 85.
  • aft face 55 also includes gas path and non-gas path surfaces (not separately labeled).
  • second stage bucket 28 includes a flow contour feature 94.
  • Flow contour feature 94 is shown positioned on front face 54 and extends from first gas path surface 71 onto non-gas path surfaces 77.
  • flow contour feature 94 takes the form of a non-axisymetric feature including a trough/depression 100 and a protrusion 102 formed in base portion 44.
  • Flow contour feature is positioned so as to alter local pressures at circumferential locations within the turbine portion wheelspace. More specifically, flow contour feature 94 creates an elevation in wheelspace static pressure at particular circumferential locations that generally experience high pressures at a wheelspace/gas path border due to wakes, bow waves shocks and the like.
  • flow contour feature 94 increases local backflow margins that prevent localized hot gas ingestions from the gas path to the wheelspace thereby reducing the need for additional purge flows in the wheelspace while also maintaining cooler wheelspace temperatures.
  • Second stage bucket 101 includes an airfoil portion 102 and a base portion 103.
  • Airfoil portion 102 extends from base portion 103 and includes a pressure side 104, a suction side 105, a leading edge 106, and a trailing edge 107.
  • Airfoil portion 102 is exposed to combustion gases flowing along the hot gas path (not separately labeled) of turbine portion 6.
  • Base portion 103 includes a main body 110 having a front face 111, an aft face (not shown), an airfoil support surface 113, and a connection member (also not shown).
  • Airfoil support surface 113 supports airfoil portion 102 while the connection member provides an interface to a second stage turbine wheel or rotor (also not shown).
  • Second stage bucket 101 includes a gas path portion 120 that includes airfoil portion 102 and portions of base portion 103 above a point denoted by a line 124, and a non-gas path portion 128 that includes portions of base portion 103 below line 124.
  • Gas path portion 120 includes all portions of second stage blade 101 that are exposed to combustion gases flowing along the hot gas path.
  • Non-gas path portion 128 includes all surfaces of base portion 103 that are arranged in a wheelspace (not shown) of turbine portion 6.
  • Base portion 103 includes a first gas path surface 131 that includes airfoil support surface 113 and a second gas path surface 133 that includes a portion of front face 111 above line 124.
  • Base portion 103 also includes non-gas path surfaces 140 that include a trench surface portion 141, a buffer surface portion 142, an upper angel wing 143 and a lower angel wing 145.
  • non-gas path surfaces 140 that include a trench surface portion 141, a buffer surface portion 142, an upper angel wing 143 and a lower angel wing 145.
  • the aft face also includes gas path and non-gas path surfaces (not separately labeled).
  • second stage bucket 101 includes a flow contour feature 150.
  • Flow contour feature 150 is shown positioned on front face 111 extending from first gas path surface 131 onto non-gas path surfaces 140.
  • flow contour feature 150 takes the form of non-axisymetric trench or depression 160 formed in base portion 103.
  • flow contour feature 150 is positioned so as to alter local pressures at circumferential locations within the turbine portion wheelspace. More specifically, flow contour feature 150 creates an elevation in wheelspace static pressure at particular circumferential locations that generally experience high pressures at a wheelspace/gas path border due to wakes, bow waves shocks and the like.
  • flow contour feature 150 increases local backflow margins that prevent localized hot gas ingestions from the gas path to the wheelspace thereby reducing the need for additional purge flows in the wheelspace while also maintaining cooler wheelspace temperatures.
  • Second stage bucket 180 includes an airfoil portion 185 and a base portion 186.
  • Airfoil portion 185 extends from base portion 186 and includes a pressure side 188, a suction side 189, a leading edge 190, and a trailing edge 191.
  • airfoil portion 185 is exposed to combustion gases flowing along a hot gas path (not separately labeled) of turbine portion 6.
  • Base portion 186 includes a main body 187 having a front face 193, an aft face (not shown), an airfoil support surface 195, and a connection member (also not shown).
  • Airfoil support surface 195 supports airfoil portion 185 while the connection member provides an interface to a second stage turbine wheel or rotor (also not shown).
  • Second stage bucket 180 includes a gas path portion 211 that includes airfoil portion 185 and portions of base portion 186 above a point denoted by a line 214, and a non-gas path portion 218 that includes portions of base portion 190 below line 214.
  • Gas path portion 211 includes all portions of second stage bucket 180 that are exposed to combustion gases flowing along the hot gas path.
  • Non-gas path portion 218 includes all surfaces of base portion 190 that are arranged in a wheelspace (not shown) of turbine portion 6.
  • base portion 186 includes a first gas path surface 221 that includes airfoil support surface 195 and a second gas path surface 223 that includes a portion of front face 193 above line 214.
  • Base portion 186 also includes non-gas path surfaces 227 that include a trench surface portion 229, a buffer surface portion 231, an upper angel wing 233 and a lower angel wing 235.
  • non-gas path surfaces 227 that include a trench surface portion 229, a buffer surface portion 231, an upper angel wing 233 and a lower angel wing 235.
  • aft face also includes gas path and non-gas path surfaces (not separately labeled).
  • second stage bucket 180 includes a flow contour feature 244.
  • Flow contour feature 244 is shown positioned on front face 193 extending from first gas path surface 221 onto non-gas path surfaces 227.
  • flow contour feature 244 takes the form of a non-axisymetric ridge or raised area 250 formed on base portion 190.
  • flow contour feature is positioned so as to alter local pressures at circumferential locations within the turbine portion wheelspace. More specifically, flow contour feature 244 creates an elevation in wheelspace static pressure at particular circumferential locations that generally experience high pressures at a wheelspace/gas path border due to wakes, bow waves shocks and the like.
  • flow contour feature 244 increases local backflow margins that prevent localized hot gas ingestions from the gas path to the wheelspace thereby reducing the need for additional purge flows in the wheelspace while also maintaining cooler wheelspace temperatures.
  • the exemplary embodiments flow contour features for turbine buckets that enhance back flow margins to limit the need for additional purge flows from the compressor to the wheelspace. By limiting purge flows to the wheelspace, more compressor flow can be passed to the turbine portion to generate shaft work.
  • the flow contour features are not only positioned on surfaces exposed to combustion gases but also on surfaces that are arranged in the wheelspace. Positioning the flow contour feature on surfaces exposed to the wheelspace creates localized pressure increases at points which experience higher combustion gas pressures. In this manner, the flow contour features limit ingestion of combustion gases to the wheelspace.
  • the flow contour feature in accordance with the exemplary embodiments could also be provided on stationary turbomachine components.
  • the flow contour feature is not limited to any one physical location and may be arranged on other surfaces.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP12187836.7A 2011-10-11 2012-10-09 Composant de turbomachine présentant une caractéristique de contour d'écoulement Withdrawn EP2581555A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/270,377 US20130089430A1 (en) 2011-10-11 2011-10-11 Turbomachine component having a flow contour feature

Publications (1)

Publication Number Publication Date
EP2581555A1 true EP2581555A1 (fr) 2013-04-17

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EP12187836.7A Withdrawn EP2581555A1 (fr) 2011-10-11 2012-10-09 Composant de turbomachine présentant une caractéristique de contour d'écoulement

Country Status (3)

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US (1) US20130089430A1 (fr)
EP (1) EP2581555A1 (fr)
CN (1) CN103046965A (fr)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130272884A1 (en) * 2012-04-13 2013-10-17 Mtu Aero Engines Gmbh Blade for a turbomachine, blade arrangement, and turbomachine
EP2806103A1 (fr) * 2013-05-24 2014-11-26 MTU Aero Engines GmbH Grille d'aubes, aubes et turbomachine
EP3064709A1 (fr) * 2015-03-02 2016-09-07 General Electric Company Plate-forme d'aube de turbine pour influencer les pertes d'incursion de gaz chaude
US10544695B2 (en) 2015-01-22 2020-01-28 General Electric Company Turbine bucket for control of wheelspace purge air
US10590774B2 (en) 2015-01-22 2020-03-17 General Electric Company Turbine bucket for control of wheelspace purge air
US10619484B2 (en) 2015-01-22 2020-04-14 General Electric Company Turbine bucket cooling
US10626727B2 (en) 2015-01-22 2020-04-21 General Electric Company Turbine bucket for control of wheelspace purge air
US10815808B2 (en) 2015-01-22 2020-10-27 General Electric Company Turbine bucket cooling

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9644483B2 (en) * 2013-03-01 2017-05-09 General Electric Company Turbomachine bucket having flow interrupter and related turbomachine
EP2986823B1 (fr) * 2013-04-18 2017-11-08 United Technologies Corporation Composant avec profil d'aube
DE102022117268A1 (de) 2022-07-12 2024-01-18 MTU Aero Engines AG Laufschaufel und Laufschaufelanordnung für eine Strömungsmaschine

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2003052240A2 (fr) * 2001-12-14 2003-06-26 Alstom Technology Ltd Systeme de turbine a gaz
US20060269399A1 (en) * 2005-05-31 2006-11-30 Pratt & Whitney Canada Corp. Deflectors for controlling entry of fluid leakage into the working fluid flowpath of a gas turbine engine
EP2138727A2 (fr) * 2008-06-23 2009-12-30 Rolls-Royce Deutschland Ltd & Co KG Bande de recouvrement d'aube dotée d'un passage
US20100074734A1 (en) * 2008-09-25 2010-03-25 Siemens Energy, Inc. Turbine Seal Assembly

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7465152B2 (en) * 2005-09-16 2008-12-16 General Electric Company Angel wing seals for turbine blades and methods for selecting stator, rotor and wing seal profiles
US8721291B2 (en) * 2011-07-12 2014-05-13 Siemens Energy, Inc. Flow directing member for gas turbine engine

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2003052240A2 (fr) * 2001-12-14 2003-06-26 Alstom Technology Ltd Systeme de turbine a gaz
US20060269399A1 (en) * 2005-05-31 2006-11-30 Pratt & Whitney Canada Corp. Deflectors for controlling entry of fluid leakage into the working fluid flowpath of a gas turbine engine
EP2138727A2 (fr) * 2008-06-23 2009-12-30 Rolls-Royce Deutschland Ltd & Co KG Bande de recouvrement d'aube dotée d'un passage
US20100074734A1 (en) * 2008-09-25 2010-03-25 Siemens Energy, Inc. Turbine Seal Assembly

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130272884A1 (en) * 2012-04-13 2013-10-17 Mtu Aero Engines Gmbh Blade for a turbomachine, blade arrangement, and turbomachine
US9359904B2 (en) * 2012-04-13 2016-06-07 Mtu Aero Engines Gmbh Blade for a turbomachine, blade arrangement, and turbomachine
EP2806103A1 (fr) * 2013-05-24 2014-11-26 MTU Aero Engines GmbH Grille d'aubes, aubes et turbomachine
US10544695B2 (en) 2015-01-22 2020-01-28 General Electric Company Turbine bucket for control of wheelspace purge air
US10590774B2 (en) 2015-01-22 2020-03-17 General Electric Company Turbine bucket for control of wheelspace purge air
US10619484B2 (en) 2015-01-22 2020-04-14 General Electric Company Turbine bucket cooling
US10626727B2 (en) 2015-01-22 2020-04-21 General Electric Company Turbine bucket for control of wheelspace purge air
US10815808B2 (en) 2015-01-22 2020-10-27 General Electric Company Turbine bucket cooling
EP3064709A1 (fr) * 2015-03-02 2016-09-07 General Electric Company Plate-forme d'aube de turbine pour influencer les pertes d'incursion de gaz chaude

Also Published As

Publication number Publication date
US20130089430A1 (en) 2013-04-11
CN103046965A (zh) 2013-04-17

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