EP1767746A1 - Rotor- bzw. Leitschaufel einer Turbine sowie Turbinenstufe mit einer Anzahl solcher Rotor- bzw. Leitschaufeln - Google Patents

Rotor- bzw. Leitschaufel einer Turbine sowie Turbinenstufe mit einer Anzahl solcher Rotor- bzw. Leitschaufeln Download PDF

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Publication number
EP1767746A1
EP1767746A1 EP05020703A EP05020703A EP1767746A1 EP 1767746 A1 EP1767746 A1 EP 1767746A1 EP 05020703 A EP05020703 A EP 05020703A EP 05020703 A EP05020703 A EP 05020703A EP 1767746 A1 EP1767746 A1 EP 1767746A1
Authority
EP
European Patent Office
Prior art keywords
turbine
blade
vane
cavity
section
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Withdrawn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
EP05020703A
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English (en)
French (fr)
Inventor
Jan Dr. Walkenhorst
Armin Dr. De Lazzer
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP05020703A priority Critical patent/EP1767746A1/de
Publication of EP1767746A1 publication Critical patent/EP1767746A1/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Withdrawn legal-status Critical Current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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • 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
    • F05D2240/126—Baffles or ribs
    • 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 present invention relates to a turbine blade/vane comprising a blade/vane airfoil mounted on a base platform and extending along an elongation axis, said base platform in a first basal direction extending between an upstream surface and a downstream surface.
  • the invention further relates to a turbine section comprising a plurality of such turbine blades/vanes and a steam turbine or a gas turbine comprising a number of turbine sections of this type.
  • Both gas turbines and steam turbines are employed in many fields for driving generators or machinery.
  • the energy content of a working medium is used to generate a rotational motion of a turbine shaft.
  • hot steam is used as working medium which expands during its passage through turbine sections of the steam turbine.
  • fuel is burned in a combustion chamber, with compressed air being supplied from an air compressor.
  • the working medium in this case is generated at high pressure and at high temperature in the combustion chamber by the combustion of the fuel and then is conducted to a number of turbine sections connected downstream of the combustion chamber, where the gas expands with an output of work.
  • a number of rotor blades together with a number of guide vanes is provided in the respective turbine section.
  • the rotor blades which are usually combined into blade groups or blade rows are arranged on the turbine shaft and drive the turbine shaft by means of a transfer of inertia from the working medium.
  • guide vanes connected to the turbine casing are usually arranged in rows between adjacent rotor blade rows.
  • the rotor blades as well as the guide vanes each typically comprise a blade/vane airfoil mounted on a base platform.
  • the base platform then is mounted onto the rotor shaft (in case of a rotor blade) or to the casing of the turbine section (in case of a guide vane).
  • a header element may be provided at the free end or tip of the blade/vane airfoil.
  • the header or blade/vane tip is positioned at a certain distance from its respective counter part in the turbine section, i. e. the turbine inner casing for the rotor blade or the rotor shaft surface for the guide vane, in any case resulting in a certain radial gap of the respective turbine blade row or guide vane row.
  • the header or blade/vane tip is positioned at a certain distance from its respective counter part in the turbine section, i. e. the turbine inner casing for the rotor blade or the rotor shaft surface for the guide vane, in any case resulting in a certain radial gap of the respective turbine blade row or guide vane row.
  • leakage of the working medium may occur, resulting in a certain small fraction of the working medium bypassing the respective blade row or guide vane row.
  • this object is achieved with a cavity provided in the upstream surface of the base platform of the turbine blade or turbine vane, said cavity extending along a second basal direction approximately perpendicular to the elongation axis of the blade/vane airfoil.
  • the invention is based upon the concept that even though the leakage effects in the radial gaps in the respective turbine section may not be entirely avoidable, among other things their negative influence on the flow dynamics of the main flow of the working medium should be minimized.
  • the effects of re-admixing the leakage flows into the main flow of the working medium should be minimized by establishing a particularly smooth flow path for the partial flows to be re-admixed.
  • Such a smooth flow path may be achieved by designing the structural components in the vicinity of the respective radial gaps such that the leakage flows are smoothly guided back into the main flow.
  • the leakage flows typically tend to have a flow component in circumferential direction in the turbine, and this component is not significantly reduced by the respective seals or gaskets, and in order to avoid re-admixing losses, in particular these components and their effect on the flow dynamics should be minimized.
  • the invention provides for means for gathering the leakage flows and to dissipate the undesired flow components before re-admixing occurs.
  • the upstream surface of the base plate of the turbine blade or turbine vane is provided with an appropriate surface cavity that in response to incoming leakage flows of the working medium generates vortices and turbulences which in turn are used to smoothly guide further inflowing leakage flows back into the main flow of the working medium.
  • the cavity may be restricted to a part of the width of the respective blade. In order to provide for a particularly beneficial way of conducting the leakage flows, however, in a preferred embodiment the cavity extends over the entire width of the upstream surface of the respective base blade.
  • the cross section of the cavity may be chosen appropriately in order to optimize the desired influence on the flow dynamics. Among other design choices, the cross section may be polygonal or have other curvatures. In a preferred embodiment, however, the cross section of the cavity is semicircular, allowing for a particularly simplified manufacturing of the respective parts.
  • the radius of this semicircle preferably is chosen comparable to the extension of the respective radial gap.
  • the cavity has an open width of approximately 6 mm to 12 mm and an axial depth of approximately 3 mm to 10 mm.
  • the object identified above is achieved with a plurality of turbine blades and/or turbine vanes according to the invention, which respectively are combined to form a blade row and/or a vane row.
  • the design is chosen such that the cavities of the turbine blades or turbine vanes forming one of said blade/ vane rows jointly form an annular cavity ring circumvening the turbine rotor.
  • the turbine section is part of either a steam turbine or a gas turbine.
  • FIG 1 the invention is referred to in the embodiment of a gas turbine 1. However, it is well understood that the invention may also be incorporated into a steam turbine in an entirely analogous manner.
  • the gas turbine 1 has a compressor 2 for combustion air, a combustion chamber 4, and a turbine section 6 for driving the compressor 2 and a generator or a power machine (not shown).
  • the turbine section 6 and the compressor 2 are arranged on a common turbine shaft 8, also designated a turbine rotor to which the generator or this power machine is also connected and which is rotatably supported about its center line 9.
  • the combustion chamber 4 is equipped with a number of burners 10 for the combustion of the liquid or gaseous fuel. It is, in addition, provided with heat-shield elements (not shown in anymore detail) on its inner wall.
  • the turbine section 6 has a number of rotor blades 12 which can rotate and which are connected to the turbine shaft 8.
  • the rotor blades 12 are arranged as a as number of rings on the turbine shaft 8 and therefore form a number of rotor blade rows.
  • the turbine section 6 also comprises a number of stationary guide vanes 14 which are likewise fastened rings with the formation of guide vane rows on an inner casing 16 of the turbine section 6.
  • the rotor blades 12 are used for driving the turbine shaft 8 by use of a transfer of inertia from the working medium M flowing through the turbine section 6 in a main flow direction as indicated by the arrow 17.
  • the guide vanes 14, are used for conducting the flow of the working medium M between each two rotor blade rows or rotor blade rings, which follow one another viewed in the flow direction of the working medium M.
  • Each guide vane 14 has a base platform 18 which is also designated a vane root and which is arranged for fixing the respective guide vane 14 as a wall element on the inner casing 16 of the turbine section 6.
  • the platform 18 is a thermally comparatively strongly stressed component which forms the outer boundary of a hot gas duct for the working medium M flowing through the turbine section 6.
  • Each rotor blade 12 is fastened, in an analogous manner, by a platform 20, also designated as a blade root, to the turbine shaft 8.
  • a guide ring 21 is respectively arranged on the inner casing 16 of the turbine section 6 between the platforms 18 which are arranged at a distance from one another, of the guide vanes 14 of the adjacent guide vane rows.
  • each guide ring 21 is at a distance in the radial direction from the outer end 22 of the rotor blade 12 located opposite to it, forming a radial gap 24.
  • the outer surface of the turbine shaft 8 is at a distance in the radial direction from the outer end 26 of the guide vane 14 located opposite to it, forming a radial gap 28.
  • the radial gaps 24, 28, will cause partial leakage flows of the working medium M as indicated by the arrows 30. Even though the main flow of the working medium M will still be conducted through the respective rows of rotor blades 12 and guide vanes 14, these leakage flows still will occur and reduce the efficiency of the turbine section 6. Beyond potentially limiting these leakage flows by applying appropriate gaskets or the like in order to close the gaps 24, 28, the turbine section 6 is designed in order to minimize the negative effects of the leakage flows on the flow dynamics of the working medium M within the turbine section 6.
  • the rotor blades 12 and the guide vanes 14 with respect to their structure are designed such that a particularly smooth flow profile of the leakage flows is achieved and losses due to re-admixing the leakage flows into the main flow of the working medium M are minimized.
  • both the rotor blades 12 and the guide vanes 14 comprise a blade airfoil 40 or a vane airfoil 42, respectively, mounted on the respective base platform 20, 18.
  • the blade airfoil 40/the vane airfoil 42 extends along an elongation axis as indicated by the respective arrow 44.
  • the respective base platform 20, 18 furthermore in first basal direction extends between an upstream surface 46, 48 respectively, and a downstream surface 50, 52 respectively, wherein the designations "upstream” and "downstream” refer back to the main flow direction of the working medium M as indicated by the arrow 17.
  • the platforms 20, 18 on their surfaces facing the inflowing respective leakage flow i. e. their upstream surfaces 46, 48 are provided with a cavity 60, 62.
  • the cavity 60, 62 is designed in order to catch incoming leakage flow from the preceding gap 28, 24 respectively, and to controllably create turbulences or vortices in the flow medium as indicated by lines 64, 66. These turbulences or vortices will create gas cushions in front of the respective upstream surfaces 46, 48, effectively smoothening the flow dynamics of the leakage flows as indicated by arrows 30. In these vortices or turbulences, an additional mixing process is taking place, efficiently absorbing energy of the respective leakage flow and accordingly minimizing re-admixing losses when the leakage flow re-enters the main flow of the working medium M.
  • the cavities 66, 62 each have approximately semicircular cross section. However, cross section may be varied according to specific design goals and may have any appropriately chosen curvature.
  • the cavities 60, 62 both extend over the entire width of the respective base platform 20, 18. Consequently, since the turbine blades 12 form a closed ring around the turbine shaft 8, the cavities 60 in this particular blade row also form an annular cavity ring circumvening the turbine rotor 8. Analogously, the cavity 62 of the guide vanes 14 forming a guide vane ring also form an annular cavity ring circumvening the turbine shaft 8.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP05020703A 2005-09-22 2005-09-22 Rotor- bzw. Leitschaufel einer Turbine sowie Turbinenstufe mit einer Anzahl solcher Rotor- bzw. Leitschaufeln Withdrawn EP1767746A1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP05020703A EP1767746A1 (de) 2005-09-22 2005-09-22 Rotor- bzw. Leitschaufel einer Turbine sowie Turbinenstufe mit einer Anzahl solcher Rotor- bzw. Leitschaufeln

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP05020703A EP1767746A1 (de) 2005-09-22 2005-09-22 Rotor- bzw. Leitschaufel einer Turbine sowie Turbinenstufe mit einer Anzahl solcher Rotor- bzw. Leitschaufeln

Publications (1)

Publication Number Publication Date
EP1767746A1 true EP1767746A1 (de) 2007-03-28

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EP05020703A Withdrawn EP1767746A1 (de) 2005-09-22 2005-09-22 Rotor- bzw. Leitschaufel einer Turbine sowie Turbinenstufe mit einer Anzahl solcher Rotor- bzw. Leitschaufeln

Country Status (1)

Country Link
EP (1) EP1767746A1 (de)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2055901A1 (de) * 2007-10-31 2009-05-06 Siemens Aktiengesellschaft Schaufel mit einem Fußbereich für Turbine in einem Kraftwerk
EP2055902A1 (de) * 2007-10-31 2009-05-06 Siemens Aktiengesellschaft Turbine für ein Wärmekraftwerk mit einer Laufschaufel und einer Leitschaufel
EP2096262A1 (de) * 2008-02-26 2009-09-02 Siemens Aktiengesellschaft Axialturbine mit geringen Leckageverlusten
WO2013009449A1 (en) * 2011-07-12 2013-01-17 Siemens Energy, Inc. Flow directing member for gas turbine engine
US20150132114A1 (en) * 2013-11-08 2015-05-14 Mitsubishi Hitachi Power Systems, Ltd. Axial turbine
JP2018105297A (ja) * 2016-12-26 2018-07-05 富士電機株式会社 タービン
WO2021020518A1 (ja) * 2019-07-31 2021-02-04 三菱パワー株式会社 軸流タービン

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5728810A (en) * 1980-07-28 1982-02-16 Hitachi Ltd Fluid turbine
US5167486A (en) * 1990-05-14 1992-12-01 Gec Alsthom Sa Turbo-machine stage having reduced secondary losses
DE4220961A1 (de) * 1992-06-25 1994-01-05 Turbowerke Meisen Ventilatoren Axialarbeitsmaschine
JPH08121106A (ja) * 1994-10-26 1996-05-14 Mitsubishi Heavy Ind Ltd タービン動翼
EP1001138A1 (de) * 1998-11-10 2000-05-17 Asea Brown Boveri AG Spitzendichtung für Turbinenlaufschaufeln
US20020136638A1 (en) * 2001-02-16 2002-09-26 Siemens Westinghouse Power Corporation Pre-segmented squealer tip for turbine blades

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5728810A (en) * 1980-07-28 1982-02-16 Hitachi Ltd Fluid turbine
US5167486A (en) * 1990-05-14 1992-12-01 Gec Alsthom Sa Turbo-machine stage having reduced secondary losses
DE4220961A1 (de) * 1992-06-25 1994-01-05 Turbowerke Meisen Ventilatoren Axialarbeitsmaschine
JPH08121106A (ja) * 1994-10-26 1996-05-14 Mitsubishi Heavy Ind Ltd タービン動翼
EP1001138A1 (de) * 1998-11-10 2000-05-17 Asea Brown Boveri AG Spitzendichtung für Turbinenlaufschaufeln
US20020136638A1 (en) * 2001-02-16 2002-09-26 Siemens Westinghouse Power Corporation Pre-segmented squealer tip for turbine blades

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 006, no. 093 (M - 133) 29 May 1982 (1982-05-29) *
PATENT ABSTRACTS OF JAPAN vol. 1996, no. 09 30 September 1996 (1996-09-30) *

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2055901A1 (de) * 2007-10-31 2009-05-06 Siemens Aktiengesellschaft Schaufel mit einem Fußbereich für Turbine in einem Kraftwerk
EP2055902A1 (de) * 2007-10-31 2009-05-06 Siemens Aktiengesellschaft Turbine für ein Wärmekraftwerk mit einer Laufschaufel und einer Leitschaufel
EP2096262A1 (de) * 2008-02-26 2009-09-02 Siemens Aktiengesellschaft Axialturbine mit geringen Leckageverlusten
WO2013009449A1 (en) * 2011-07-12 2013-01-17 Siemens Energy, Inc. Flow directing member for gas turbine engine
US8864452B2 (en) 2011-07-12 2014-10-21 Siemens Energy, Inc. Flow directing member for gas turbine engine
US20150132114A1 (en) * 2013-11-08 2015-05-14 Mitsubishi Hitachi Power Systems, Ltd. Axial turbine
JP2018105297A (ja) * 2016-12-26 2018-07-05 富士電機株式会社 タービン
WO2021020518A1 (ja) * 2019-07-31 2021-02-04 三菱パワー株式会社 軸流タービン
JP2021025432A (ja) * 2019-07-31 2021-02-22 三菱パワー株式会社 軸流タービン
CN114127389A (zh) * 2019-07-31 2022-03-01 三菱动力株式会社 轴流涡轮
CN114127389B (zh) * 2019-07-31 2023-11-03 三菱重工业株式会社 轴流涡轮
US11898461B2 (en) 2019-07-31 2024-02-13 Mitsubish Heavy Industries, Ltd. Axial flow turbine

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