EP2221454A1 - Gasturbinenschaufel mit Deckbandteile - Google Patents

Gasturbinenschaufel mit Deckbandteile Download PDF

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Publication number
EP2221454A1
EP2221454A1 EP09153485A EP09153485A EP2221454A1 EP 2221454 A1 EP2221454 A1 EP 2221454A1 EP 09153485 A EP09153485 A EP 09153485A EP 09153485 A EP09153485 A EP 09153485A EP 2221454 A1 EP2221454 A1 EP 2221454A1
Authority
EP
European Patent Office
Prior art keywords
chord
normalized
span
gas turbine
airfoil
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Withdrawn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
EP09153485A
Other languages
English (en)
French (fr)
Inventor
Willy Heinz Hofmann
Bruno Stephan
Christian Walter Sommer
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 Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Priority to EP09153485A priority Critical patent/EP2221454A1/de
Publication of EP2221454A1 publication Critical patent/EP2221454A1/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Withdrawn legal-status Critical Current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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • 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
    • F05D2250/70—Shape
    • F05D2250/74—Shape given by a set or table of xyz-coordinates

Definitions

  • the invention relates generally to gas turbine blades and more specifically to low pressure gas turbine shrouded blades.
  • Gas turbine blades are rotating airfoil shaped components designed to convert thermal energy from a combustor into mechanical work in order to turn a shaft. Performance of a turbine can be enhanced by sealing the outer edge of the blade tip to prevent combustion gases from escaping from the flow path to the gaps between the blade tip and the outer casing. A common manner of sealing the gap between the blade tips and the turbine casing is through shrouds fitted to the tip of the airfoil of the blade.
  • blade design is a compromise between aerodynamic efficiency and mechanical integrity
  • a blades design is not defined solely by design limits.
  • the designer has a limited freedom to influence the final design.
  • a designer to address the above problem, may specify a partial shroud having reduced weight. While partial shrouds are less aerodynamically efficient than full shrouds in certain blade arrangements and for certain conditions a partially shrouded blade may produce an optimised design point during the iterative design process.
  • the invention is intended to provide an improved blade design with improved aerodynamic efficiency that addresses the problems of shroud weight.
  • the invention provides a blade design that enables a blade to have a full shroud where otherwise a partial shroud maybe favoured.
  • the invention is based on the idea of shortening the chord length towards the airfoil end distal to the hub so as to reduce the weight of the shroud. In this way the blade has the aerodynamic benefits of a full shroud together with the benefit of reduced shroud weight.
  • An aspect provides a gas turbine blade comprising a hub with an airfoil, extending radially from the hub.
  • the airfoil having a leading edge; a trailing edge; a span defined by the radial height of the airfoil, normalized by the airfoil radial length between the hub and an airfoil end radially distal from the hub; and an axial chord normalized along the span by the axial chord at the hub to form a normalized axial chord.
  • the blade further comprises a full shroud at the radially distal end of the airfoil.
  • the gas turbine blade is characterized by a normalized axial chord at 100% span that is between about 4% to about 10% shorter than the normalized axial chord at 90% span.
  • the normalized axial chord at 100% span is limited to being about 6% shorter than the normalized axial chord at about 90% span. In a yet further aspect the normalized axial chord at 100% span is limited to being about 6% shorter than the normalized axial chord at about 90% span while at the same time normalized chord at 100% span is limited to being about 6% shorter than the normalized chord at about 90% span.
  • a further aspect derived directly from 3D simulation, provides a gas turbine blade earlier described having a chord normalized by the chord at the hub wherein the normalized axial chord carried to +/- 1 % and the normalized chord carried to +/-1 %, at different spans conform to Table 1.
  • the previously described gas turbine blade is a stage 2 or stage 3 gas turbine blade of a low pressure turbine.
  • the axial chord 21 and chord 22 can be normalized by using reference lengths at 0% span 30, as shown in FIG. 4 where the span 30 of the airfoil 25 is defined as the radial extension of the airfoil 25 from the hub 28 to the full shroud 27. That is 0% span 30 corresponds to the point at which the airfoil 25 extends from the hub 28 and 100% span 30 is the point where a shroud 27 is fitted to the airfoil 25.
  • FIG. 4 shows a side view of an exemplary embodiment of a blade 5.
  • the blade 5 has a hub 28. Extending radially, that is normal from the turbine axis 18, from the hub 28 is an airfoil 25 with a leading edge 26 and a trailing edge 23. At the end of the airfoil 25, radially distal from the hub 28, is a full shroud 27.
  • a full shroud 27 is a shroud that is capable of covering the throat 20 between two fitted airfoils 25 as shown in FIG. 3 .
  • the normalized axial chord 21 reduces between 90% span 30 to 100% span 30 by about 6% while the normalized chord 22 between the same span 30 range reduces by about 6%.
  • the reduced axial chord 21 results in an overall reduced radially distal end size of the airfoil 25. As a result a smaller full shroud 27 can be fitted than may otherwise be the case resulting in improved blade 5 aerodynamic efficiency.
  • a more detailed exemplary embodiment corresponding to an arrangement for a particular gas turbine 1 machine optimised by 3D aerodynamic and lifetime simulation, has a normalized axial chord 21 carried to +/- 1 % and normalized chord 22, carried to +/- 1%, at different spans 30 as tabulated in Table 1.
  • any of the exemplary embodiments may be stage 3 two or stage 3 three blades 5, as shown on FIG. 2 , of a low pressure turbine 14. This location is the region of a turbine most likely to benefit from the invention due to the combination of blade 5 size, blade 5 cooling requirements and blade 5 service. Blades 5 having any of the configurations of the exemplary embodiments could however be suitable for use in other turbine services and locations dependant on the particular turbine and stage operating conditions.

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP09153485A 2009-02-24 2009-02-24 Gasturbinenschaufel mit Deckbandteile Withdrawn EP2221454A1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP09153485A EP2221454A1 (de) 2009-02-24 2009-02-24 Gasturbinenschaufel mit Deckbandteile

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09153485A EP2221454A1 (de) 2009-02-24 2009-02-24 Gasturbinenschaufel mit Deckbandteile

Publications (1)

Publication Number Publication Date
EP2221454A1 true EP2221454A1 (de) 2010-08-25

Family

ID=40834391

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09153485A Withdrawn EP2221454A1 (de) 2009-02-24 2009-02-24 Gasturbinenschaufel mit Deckbandteile

Country Status (1)

Country Link
EP (1) EP2221454A1 (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2505780A1 (de) * 2011-04-01 2012-10-03 MTU Aero Engines GmbH Schaufelanordnung für eine Turbomaschine
WO2013191877A1 (en) * 2012-06-19 2013-12-27 United Technologies Corporation Airfoil including adhesively bonded shroud
US9416671B2 (en) 2012-10-04 2016-08-16 General Electric Company Bimetallic turbine shroud and method of fabricating
US11035238B2 (en) 2012-06-19 2021-06-15 Raytheon Technologies Corporation Airfoil including adhesively bonded shroud

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2355413A (en) * 1942-01-21 1944-08-08 Gen Electric Elastic fluid turbine blading
US5156529A (en) * 1991-03-28 1992-10-20 Westinghouse Electric Corp. Integral shroud blade design
US6491498B1 (en) 2001-10-04 2002-12-10 Power Systems Mfg, Llc. Turbine blade pocket shroud
US20050214120A1 (en) * 2004-03-26 2005-09-29 The Boeing Company High speed rotor assembly shroud
EP1612372A1 (de) * 2004-07-01 2006-01-04 Alstom Technology Ltd Turbinenschaufel mit einem Hinterschnitt am Schaufelfuss oder an der Schaufelspitze
EP1707742A1 (de) * 2005-03-09 2006-10-04 ABB Turbo Systems AG Turbinenschaufel mit Schmutzfänger

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2355413A (en) * 1942-01-21 1944-08-08 Gen Electric Elastic fluid turbine blading
US5156529A (en) * 1991-03-28 1992-10-20 Westinghouse Electric Corp. Integral shroud blade design
US6491498B1 (en) 2001-10-04 2002-12-10 Power Systems Mfg, Llc. Turbine blade pocket shroud
US20050214120A1 (en) * 2004-03-26 2005-09-29 The Boeing Company High speed rotor assembly shroud
EP1612372A1 (de) * 2004-07-01 2006-01-04 Alstom Technology Ltd Turbinenschaufel mit einem Hinterschnitt am Schaufelfuss oder an der Schaufelspitze
EP1707742A1 (de) * 2005-03-09 2006-10-04 ABB Turbo Systems AG Turbinenschaufel mit Schmutzfänger

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2505780A1 (de) * 2011-04-01 2012-10-03 MTU Aero Engines GmbH Schaufelanordnung für eine Turbomaschine
WO2012130341A1 (en) * 2011-04-01 2012-10-04 Mtu Aero Engines Gmbh Blade arrangement for a turbo engine
WO2013191877A1 (en) * 2012-06-19 2013-12-27 United Technologies Corporation Airfoil including adhesively bonded shroud
US11035238B2 (en) 2012-06-19 2021-06-15 Raytheon Technologies Corporation Airfoil including adhesively bonded shroud
US9416671B2 (en) 2012-10-04 2016-08-16 General Electric Company Bimetallic turbine shroud and method of fabricating

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