EP3358135A1 - Contournage d'une plate-forme de grille d'aube - Google Patents

Contournage d'une plate-forme de grille d'aube Download PDF

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Publication number
EP3358135A1
EP3358135A1 EP17154853.0A EP17154853A EP3358135A1 EP 3358135 A1 EP3358135 A1 EP 3358135A1 EP 17154853 A EP17154853 A EP 17154853A EP 3358135 A1 EP3358135 A1 EP 3358135A1
Authority
EP
European Patent Office
Prior art keywords
blade
platform
segment
elevation
grid
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.)
Granted
Application number
EP17154853.0A
Other languages
German (de)
English (en)
Other versions
EP3358135B1 (fr
Inventor
Markus Brettschneider
Inga Mahle
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines 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 MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to EP17154853.0A priority Critical patent/EP3358135B1/fr
Priority to ES17154853T priority patent/ES2857568T3/es
Priority to US15/886,977 priority patent/US10590773B2/en
Publication of EP3358135A1 publication Critical patent/EP3358135A1/fr
Application granted granted Critical
Publication of EP3358135B1 publication Critical patent/EP3358135B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
    • 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
    • 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
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence
    • 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
    • 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
    • F05D2240/123—Fluid guiding means, e.g. vanes related to the pressure side of a stator vane
    • 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
    • F05D2240/124—Fluid guiding means, e.g. vanes related to the suction side of a stator vane
    • 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
    • F05D2240/129—Cascades, i.e. assemblies of similar profiles acting in parallel
    • 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
    • F05D2240/80—Platforms for stationary or moving blades

Definitions

  • the publication US 2012/051 900 A1 discloses a vane grille with sidewall contouring in which a platform surface between the pressure side of one of the airfoils and the suction side of another of the airfoils each has a protrusion and a recess which together form an axially extending arcuate channel.
  • the second airfoil may be partially based on the further survey.
  • An embodiment has proved to be advantageous in which the further elevation has its highest point (s) on a borderline between the second blade (or its suction side) and the platform surface.
  • the platform surface may be convex or concave.
  • FIG. 1 is schematically illustrated in plan view (with radial viewing direction) an exemplary, developed embodiment of a blade grid segment 1 according to the invention. It comprises airfoils 20, 30, which each have a pressure side and a suction side, and a platform 10 according to the invention with a platform edge 10a (with respect to the intended main flow direction X) and a downstream platform edge 10b.
  • the platform may be formed in one piece or, for example, in two parts (not shown), in particular it may comprise two parts, of which in each case one of the blades 20, 30 protrudes.
  • the blades 20, 30 define an axial grid width g by the distance, measured in the axial main flow direction X, of their leading edges 23, 33 from their trailing edges 24, 34 on the platform surface.
  • the platform surface has one extending to the suction side 31 of the other (second) airfoil 30, in the FIG. 1 Again, illustrated by contour lines depression 13 with a lowest point 14.
  • the airfoil 30 is partially (namely in its front region) in the recess 13th
  • the highest point 12 and the lowest point 14 lie in an intermediate strip Z of the platform surface.
  • the inflow-side and the outflow-side boundary of the intermediate strip Z run parallel to the inflow-side platform edge 10a.
  • FIG. 2 shows an alternative embodiment of an unwrapped blade grid segment according to the invention 1 'in plan view (with a radial viewing direction). It includes like that in FIG. 1 shown blade airfoils 20, 30 and a platform 10 according to the invention with a platform surface and a (based on the intended, axial main flow direction X) upstream platform edge 10a and a downstream platform edge 10b.
  • blade grid segment 1 also has the platform surface of in FIG. 2 shown blade lattice segment 1 'extending to the pressure side 21 of the one (first) blade 20 elevation 11' with a highest point 12 'and extending to the suction side 31 of the other (second) blade 30 recess 13' with a lowest point 14th '.
  • the highest point 12 'of the elevation and the deepest point 14' of the depression are both in the intermediate strip Z, which is defined by the distances a, b as described above, ie at least 30% and at most 60% of the axial grid width g downstream of Leading edges 23, 33 of the blades 20, 30 arranged.
  • the inflow-side platform edge 10a covers the elevation 11 'in a section 11'a.
  • the inflow-side platform edge 10a therefore also has a (in the FIG. 2 not shown) contour by (as a graph of a one-dimensional function) in the area 11 'a has a local maximum.
  • a blade lattice segment 1, 1 'of a blade lattice of a turbomachine which comprises at least two airfoils g defining a blade widths 20, 30 and a platform 10 with a platform surface and an upstream platform edge 10a.
  • the platform surface has a raised to the pressure side 21 of a first of the blades 20 elevation 11, 11 'and extending to the suction side 32 of the other of the blades 30 recess 13, 13'.
  • At least one highest point 12, 12 'of the elevation 11, 11' and at least one lowest point 14, 14 'of the recess 13, 13' lie at least 30% and at most 60% of the axial grid width g downstream of the Leading edges 23, 33 of the blades 20, 30.
  • the elevation 11, 11 'and the recess 13, 13' each zoom up to the upstream platform edge 10a zoom.

Landscapes

  • 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)
EP17154853.0A 2017-02-06 2017-02-06 Contournage d'une plate-forme de grille d'aube Active EP3358135B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP17154853.0A EP3358135B1 (fr) 2017-02-06 2017-02-06 Contournage d'une plate-forme de grille d'aube
ES17154853T ES2857568T3 (es) 2017-02-06 2017-02-06 Contorneo de una plataforma de una rejilla de paletas
US15/886,977 US10590773B2 (en) 2017-02-06 2018-02-02 Contouring a blade/vane cascade stage

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP17154853.0A EP3358135B1 (fr) 2017-02-06 2017-02-06 Contournage d'une plate-forme de grille d'aube

Publications (2)

Publication Number Publication Date
EP3358135A1 true EP3358135A1 (fr) 2018-08-08
EP3358135B1 EP3358135B1 (fr) 2021-01-27

Family

ID=57965850

Family Applications (1)

Application Number Title Priority Date Filing Date
EP17154853.0A Active EP3358135B1 (fr) 2017-02-06 2017-02-06 Contournage d'une plate-forme de grille d'aube

Country Status (3)

Country Link
US (1) US10590773B2 (fr)
EP (1) EP3358135B1 (fr)
ES (1) ES2857568T3 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ES2819128T3 (es) * 2017-03-03 2021-04-15 MTU Aero Engines AG Contorneo de una plataforma de una rejilla de paletas
JP7232034B2 (ja) * 2018-12-18 2023-03-02 三菱重工業株式会社 タービン翼及びこれを備えた蒸気タービン
US11639666B2 (en) * 2021-09-03 2023-05-02 Pratt & Whitney Canada Corp. Stator with depressions in gaspath wall adjacent leading edges

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060233641A1 (en) 2005-04-14 2006-10-19 General Electric Company Crescentic ramp turbine stage
US20080232968A1 (en) * 2006-02-27 2008-09-25 Honeywell International, Inc. Non-axisymmetric end wall contouring for a turbomachine blade row
US20120051900A1 (en) 2010-08-31 2012-03-01 General Electric Company Turbine nozzle with contoured band
NO20130204A1 (no) * 2012-02-29 2013-08-30 Gen Electric Turbintrinn med bølgete overflate og spylekanal
EP2487329B1 (fr) 2011-02-08 2013-11-27 MTU Aero Engines GmbH Canal d'aube doté d'une définition de contour de la paroi latérale et turbomachine associé
EP2787172A2 (fr) 2012-08-02 2014-10-08 MTU Aero Engines GmbH Grille d'aubes avec définition de contour de la paroi latérale et turbomachine
EP2696029B1 (fr) 2012-08-09 2015-10-07 MTU Aero Engines AG Grille d'aube avec définition de contour de la paroi latérale et turbomachine
WO2015195112A1 (fr) * 2014-06-18 2015-12-23 Siemens Energy, Inc. Configuration de paroi d'extrémité pour moteur de turbine à gaz

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8459956B2 (en) * 2008-12-24 2013-06-11 General Electric Company Curved platform turbine blade
US9194235B2 (en) * 2011-11-25 2015-11-24 Mtu Aero Engines Gmbh Blading
EP2746533B1 (fr) * 2012-12-19 2015-04-01 MTU Aero Engines GmbH Grille d'aube et turbomachine
US9376927B2 (en) * 2013-10-23 2016-06-28 General Electric Company Turbine nozzle having non-axisymmetric endwall contour (EWC)
DE102015224420A1 (de) * 2015-12-07 2017-06-08 MTU Aero Engines AG Ringraumkonturierung einer Gasturbine
DE102016211315A1 (de) * 2016-06-23 2017-12-28 MTU Aero Engines AG Lauf- oder Leitschaufel mit erhabenen Bereichen

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060233641A1 (en) 2005-04-14 2006-10-19 General Electric Company Crescentic ramp turbine stage
US20080232968A1 (en) * 2006-02-27 2008-09-25 Honeywell International, Inc. Non-axisymmetric end wall contouring for a turbomachine blade row
US20120051900A1 (en) 2010-08-31 2012-03-01 General Electric Company Turbine nozzle with contoured band
EP2487329B1 (fr) 2011-02-08 2013-11-27 MTU Aero Engines GmbH Canal d'aube doté d'une définition de contour de la paroi latérale et turbomachine associé
NO20130204A1 (no) * 2012-02-29 2013-08-30 Gen Electric Turbintrinn med bølgete overflate og spylekanal
EP2787172A2 (fr) 2012-08-02 2014-10-08 MTU Aero Engines GmbH Grille d'aubes avec définition de contour de la paroi latérale et turbomachine
EP2696029B1 (fr) 2012-08-09 2015-10-07 MTU Aero Engines AG Grille d'aube avec définition de contour de la paroi latérale et turbomachine
WO2015195112A1 (fr) * 2014-06-18 2015-12-23 Siemens Energy, Inc. Configuration de paroi d'extrémité pour moteur de turbine à gaz

Also Published As

Publication number Publication date
EP3358135B1 (fr) 2021-01-27
US10590773B2 (en) 2020-03-17
ES2857568T3 (es) 2021-09-29
US20180223670A1 (en) 2018-08-09

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