EP1907671B1 - Gasturbinenschaufelkranz - Google Patents

Gasturbinenschaufelkranz Download PDF

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Publication number
EP1907671B1
EP1907671B1 EP06764202A EP06764202A EP1907671B1 EP 1907671 B1 EP1907671 B1 EP 1907671B1 EP 06764202 A EP06764202 A EP 06764202A EP 06764202 A EP06764202 A EP 06764202A EP 1907671 B1 EP1907671 B1 EP 1907671B1
Authority
EP
European Patent Office
Prior art keywords
platform
blade
gas turbine
vane
root
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.)
Not-in-force
Application number
EP06764202A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1907671A1 (de
Inventor
Alexander Ralph Beeck
Stefan Irmisch
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to PL06764202T priority Critical patent/PL1907671T3/pl
Publication of EP1907671A1 publication Critical patent/EP1907671A1/de
Application granted granted Critical
Publication of EP1907671B1 publication Critical patent/EP1907671B1/de
Not-in-force 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • 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
    • F05D2250/71—Shape curved
    • 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
    • F05D2250/71—Shape curved
    • F05D2250/711—Shape curved convex
    • 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
    • F05D2250/71—Shape curved
    • F05D2250/712—Shape curved concave

Definitions

  • the invention relates to a gas turbine blade having a profiled in cross-section blade root, followed successively by a platform and thereon a longitudinally curved blade profile, wherein the blade root extends in the longitudinal direction of the blade profile and the platform has two longitudinally extending curved longitudinal platform edges.
  • the invention relates to a platform element for a gas turbine blade ring of a gas turbine, with a profiled platform foot and a platform plate having two curved longitudinal edges and in which the platform plate and the platform foot extend in a longitudinal direction.
  • the invention relates to a support structure for mounting arranged in a ring gas turbine blades, in which blade holding grooves are provided, in each of which the blade root of the gas turbine blade can be inserted.
  • the invention relates to a gas turbine blade ring for a gas turbine having a support structure and with gas turbine blades and the use of such a gas turbine blade ring.
  • Gas turbine blades with straight blade roots and platforms as well as curved blade profiles are known from the prior art.
  • the pressure-side and suction-side platforms run with widely varying platform overhangs.
  • platform overhangs For example, on the pressure side, in the middle region between leading edge and trailing edge, such gas turbine blades on large overhangs, which are steadily smaller towards the trailing edge and leading edge. These large overhangs are poorly coolable and reduce the fatigue life of the gas turbine blade.
  • a turbine blade assembly for a gas turbine known.
  • the gas turbine blade having a straight blade root is positively inserted in a retaining groove provided on the outer circumference of a turbine disk.
  • the gas turbine blades only have platform stubs whose longitudinal edges are curved in the axial direction of the turbine. Between two adjacent gas turbine blades, a separate platform is connected to the turbine disk by means of an additional support. Due to the comparatively lightweight, because platformless gas turbine blade radial extension of the blade profiles is possible.
  • each platform element by means of a separate holding element or a separate holder to be attached to the turbine disk muse.
  • Another turbine blade assembly is of the WO 01/59263 known.
  • the object of the invention is to specify a simplified system for fastening gas turbine blades and platform elements to a support structure for forming a gas turbine blade ring for a gas turbine.
  • the object directed to the system is achieved by providing a gas turbine blade ring with the features of claim 1.
  • the simplified system is composed at least of a support structure with axially curved retaining grooves, are fixed to the gas turbine blades with analogous to the retaining grooves curved blade roots.
  • the system includes further retaining grooves in the support structure for attachment of Platform elements with correspondingly convex or concave curved longitudinal edges.
  • the gas turbine blades are mounted in the support structure to a gas turbine blade ring.
  • vane holding grooves are provided into which the vane feet of the gas turbine blade are insertable, the vane holding grooves corresponding to the vane roots of the gas turbine blades, i. H.
  • Each blade retaining groove is curved (curved) in the longitudinal direction or in the axial direction in the same way as the blade root and profiled in cross-section.
  • platform elements are mounted in the same manner as the gas turbine blade. Due to the use of approximately platformless gas turbine blades in the support structure, in each case a platform retention groove is provided in the support structure between two adjacent blade retaining grooves, which are arched to an identical extent as the platform feet. In this platform holding grooves, the platform elements are inserted in a direction of their curvature corresponding movement direction, since both the longitudinal edges of the platform elements and the platform longitudinal edges of the platform of the gas turbine blade and their (platform and blade) feet are curved in the same direction.
  • a particularly small platform of the gas turbine blade is achieved in that the suction-side and / or pressure-side platform overhang is designed as a platform stub with a comparatively short platform width.
  • the gas turbine blade is almost platformless, which significantly simplifies their structural design.
  • the simplification leads to a cost reduction in the design of the gas turbine blade and in their manufacture.
  • the invention is based on the recognition that the platform base and the blade root of the gas turbine blade as well as their retaining grooves of the support structure must be similarly shaped in the longitudinal direction or axial direction in order to achieve a particularly simple, even individual assembly.
  • the platform longitudinal edges are curved in the axial direction
  • the blade root extends in a straight line in the axial direction. Since the gas turbine blade thereof known is inserted in a purely translational movement due to the rectilinear blade root, and whose platform longitudinal edges are curved, the intermediate platform elements must be radially introduced into their operating position, then with an additional, mounted in a rectilinear direction of movement bracket on the rotor disk to be attached.
  • the platform foot is now shaped such that it runs convexly or concavely in accordance with the platform longitudinal edges. All geometric surfaces influencing the assembly are then curved in the same direction, so that all components forming the gas turbine blade ring can be individually assembled in a direction of movement corresponding to their curvature.
  • Compliance with this geometric condition also allows the provision of gas turbine blades with a pressure-side platform and a suction-side platform, each along the profile wall has an approximately equal platform width as a platform overhang.
  • the platform width is the distance from the pressure-side or suction-side profile wall to the nearest platform longitudinal edge.
  • the almost constant platform width allows one much easier and more efficient cooling of the platform. This results in a more uniform distribution of temperature along the platform during use in a gas turbine, which in turn prolongs the life of the gas turbine due to lower material stresses.
  • the gas turbine blade according to the invention has a blade root surface on which all curvature lines extending in the longitudinal direction extend parallel to the curved platform longitudinal edges on a circular arc.
  • the suction-side and the pressure-side blade root surfaces could also be curved in such a way that the blade root becomes sharpened from an oncoming-edged end face to a downstream-edged end face, i. wedge-shaped shrinking its cross section in the longitudinal direction, tapers.
  • such a gas turbine blade would be pressed into a correspondingly shaped retaining a support structure due to the thrust forces occurring in the hot gas and axially fixed.
  • a suction-side or pressure-side platform projection projects from the suction-side profile wall to the suction-side platform longitudinal edge and / or from the pressure-side profile wall to the pressure-side platform longitudinal edge, whose platform width is approximately constant over 30% of its longitudinal length. Due to the almost constant platform width, the transition of platform and blade profile is in operation more uniform thermal and mechanical stresses. Such a designed platform is particularly good and uniformly cool and avoids non-uniform, because substantially different width wide platform projections along the blade profile. In addition, due to the now uniformized stresses, an increase in the fatigue life can be achieved.
  • the gas turbine blade is designed as a gas turbine blade, the blade root is formed in cross-section dovetailed, hammer-shaped or fir-tree-like.
  • the preferably cast gas turbine blade is coolable.
  • the platform foot is shaped in the longitudinal direction in such a way that all the longitudinally extending curvature lines of the platform foot surface extend parallel to the longitudinal edges on a circular arc.
  • the platform foot is thus curved to the same extent as the blade root of the gas turbine blade. Both feet thus have identical circular arcs or radii, so that each element can be mounted individually in the support structure.
  • this consists at least partially of ceramic.
  • the platform cooling can be reduced thereby, which has an efficiency-enhancing effect on a gas turbine equipped therewith.
  • the support structure is designed as a rotor disk, in which the blade retaining grooves are provided in the axial direction of the rotor disk extending in its outer periphery.
  • the upstream and / or pressure-side platform or their overhangs Due to the approximately constant width of the upstream and / or pressure-side platform or their overhangs, they can be cooled easier and more efficiently.
  • the use of Cooling air can be reduced.
  • the saved cooling air can be supplied in the stationary gas turbine to increase the efficiency of the combustion.
  • the platform element is provided as a ceramic or with a ceramic thermal barrier coating, it may even be possible to dispense with the platform cooling, which has an efficiency-increasing effect on a gas turbine equipped therewith.
  • FIG. 1 shows a gas turbine 1 in a longitudinal partial section. It has inside a rotatably mounted about a rotation axis 2 rotor 3, which is also referred to as a turbine runner. Along the rotor 3 successive an intake 4, a compressor 5, a toroidal annular combustion chamber 6 with a plurality of rotationally symmetrical to each other arranged burners 7, a turbine unit 8 and an exhaust housing 9.
  • the annular combustion chamber 6 forms a combustion chamber 17 which communicates with an annular hot gas channel 18.
  • There four successive turbine stages 10 form the turbine unit 8. Each turbine stage 10 is formed of two blade rings.
  • one row of guide vanes 13 follows one out Gas turbine blades 15 formed row 14.
  • the vanes 12 are attached to the stator, whereas the gas turbine blades 15 of a row 14 are mounted by means of a turbine disk 19 on the rotor 3.
  • a generator or a working machine (not shown) is coupled.
  • FIG. 2 shows a gas turbine blade according to the invention designed as a gas turbine blade 50 with a blade root 52, on which a platform 54 and a blade profile 56 is successively provided.
  • the blade profile 56 is curved in the longitudinal direction L, ie in the installed position in a gas turbine 1 in the axial direction A.
  • the blade profile 56 is not shown in its full height, but it ends comparatively close to the platform 54th
  • the blade profile 56 has a pressure-side profile wall 62 and a suction-side profile wall 64, which extend from a front edge 66 of the blade profile 56 to a trailing edge 68.
  • the hot gas 11 flows around the gas turbine blade 50. It flows along the profile walls 62, 64, from the front edge 66 in the direction of the trailing edge 68.
  • the platform 54 is curved along the longitudinal direction L, the longitudinal edges 55 of the platform 54 do not run in a straight line but on an arc.
  • the suction side platform longitudinal edge 55a is convex and the pressure side platform longitudinal edge 55b is concavely curved.
  • the platform 54 has, in each case in the region of the front edge 66 and in the region of the rear edge 68, a cross-platform transverse edge 53 running transversely on the front side.
  • the blade root 52 is curved in the same manner as the longitudinal edges 55 of the platform 54.
  • the suction-side blade root surface 72b is longitudinal curved convexly and the pressure-side blade root surface 72a in the longitudinal direction concave.
  • the blade root 52 is also shaped in the embodiment shown in such a way that all extending in the longitudinal direction L lines of curvature 70 of Schaufelfußober Design 72 extend parallel to the platform longitudinal edge 55 on a circular arc.
  • the curved lines 70 of the platform longitudinal edges 55 and of the blade root 52 can run on a circular arc, so that they are particularly easy to insert into a support structure 80 (FIG. FIG. 4 ) can be successively inserted into blade holding grooves 82.
  • thermomechanical tension reducing platform overhangs 75 that extend approximately uniformly along the longitudinal axis L over at least 30% of the length of the platform 54 (longitudinally), both on the suction side and on the pressure side.
  • An inventive platform element 74 is in a perspective view in FIG FIG. 3 shown.
  • the platform element 74 has a platform plate 76 and a platform foot 78, both of which extend in the longitudinal direction L.
  • the platform plate 76 of the platform element 74 has a platform longitudinal edge 79a that is convexly curved in the longitudinal direction L, and a concavely curved platform longitudinal edge 79b.
  • the platform foot 78 is curved to the platform longitudinal edges 79 in the longitudinal direction L correspondingly.
  • Like all longitudinally L extending curvature lines 70 of the Schaufelfußober Design 72 of the gas turbine blade 50 according to the invention all extend in the longitudinal direction L.
  • FIG. 4 shows a perspective view of a section of a gas turbine blade ring 90 according to the invention for a gas turbine 1.
  • the gas turbine blade ring 90 is held by a support structure 80, in particular a rotor disk 19.
  • a support structure 80 in particular a rotor disk 19.
  • profiled retaining grooves are provided in the axial direction A, relative to the axis of rotation of the rotor 3.
  • the retaining grooves serve to receive and secure gas turbine blades 50 and platform elements 74 according to the present invention.
  • the retaining grooves provided for attaching gas turbine blades 50 have the blade retaining grooves 92 profiled in a fir-tree cross section, whereas the platform retaining grooves 93 provided for holding and securing platform elements 74 are dovetail-shaped in cross-section are formed or may have other foot shapes.
  • Each blade root 52 is seated in the blade retaining groove 92 in a positive fit, as well as each platform root 78 in the platform retaining groove 93.
  • Both the blade retaining grooves 92 and the platform retaining grooves 93 are curved in the axial direction A in such a way that their axial direction A extending curvature lines of the groove surface run parallel on a circular arc and thereby correspond to the curvature of the blade root 52 and the platform foot 78.
  • a more consistent platform width can generally be provided on both sides of the blade profile, i. on the suction side and on the pressure side.
  • the pressure-side as well as the suction-side platform overhangs can thus be approximately the same size and thus comparatively symmetrical, which avoids one-sided platform overhangs and correspondingly locally varying mass accumulations. Varying mass accumulations have a negative effect on the voltage distributions and thus on the service life of the gas turbine blade.
  • the unilaterally occurring in sections platform overhangs are difficult to cool, which also has a negative impact on the life of the gas turbine blade. Fatigue symptoms appear delayed.
  • the design with curved blade root and curved platform longitudinal edges can be a design simplification of the gas turbine blade and thus a more efficient cooling brought about, which advantageously also allows the introduction of provided between the gas turbine blades platform elements or intermediate platforms.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Low-Molecular Organic Synthesis Reactions Using Catalysts (AREA)
EP06764202A 2005-07-25 2006-07-19 Gasturbinenschaufelkranz Not-in-force EP1907671B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL06764202T PL1907671T3 (pl) 2005-07-25 2006-07-19 Wieniec łopatkowy turbiny gazowej

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US70235805P 2005-07-25 2005-07-25
US11/214,303 US7300253B2 (en) 2005-07-25 2005-08-29 Gas turbine blade or vane and platform element for a gas turbine blade or vane ring of a gas turbine, supporting structure for securing gas turbine blades or vanes arranged in a ring, gas turbine blade or vane ring and the use of a gas turbine blade or vane ring
PCT/EP2006/064400 WO2007012587A1 (de) 2005-07-25 2006-07-19 Gasturbinenschaufel und plattformelement für einen gasturbinenschaufelkranz, tragstruktur zu deren befestigung, gasturbinenschaufelkranz und seine verwendung

Publications (2)

Publication Number Publication Date
EP1907671A1 EP1907671A1 (de) 2008-04-09
EP1907671B1 true EP1907671B1 (de) 2008-12-31

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ID=37054737

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06764202A Not-in-force EP1907671B1 (de) 2005-07-25 2006-07-19 Gasturbinenschaufelkranz

Country Status (9)

Country Link
US (1) US7300253B2 (pl)
EP (1) EP1907671B1 (pl)
JP (1) JP2009503330A (pl)
CN (1) CN101233299B (pl)
AT (1) ATE419451T1 (pl)
DE (1) DE502006002518D1 (pl)
ES (1) ES2317560T3 (pl)
PL (1) PL1907671T3 (pl)
WO (1) WO2007012587A1 (pl)

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JP2009503330A (ja) 2009-01-29
EP1907671A1 (de) 2008-04-09
CN101233299A (zh) 2008-07-30
US20070020102A1 (en) 2007-01-25
DE502006002518D1 (de) 2009-02-12
WO2007012587A1 (de) 2007-02-01
PL1907671T3 (pl) 2009-06-30
US7300253B2 (en) 2007-11-27
ATE419451T1 (de) 2009-01-15
CN101233299B (zh) 2011-06-15
ES2317560T3 (es) 2009-04-16

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