WO2009100795A1 - Aube mobile pour une turbomachine - Google Patents

Aube mobile pour une turbomachine Download PDF

Info

Publication number
WO2009100795A1
WO2009100795A1 PCT/EP2008/067741 EP2008067741W WO2009100795A1 WO 2009100795 A1 WO2009100795 A1 WO 2009100795A1 EP 2008067741 W EP2008067741 W EP 2008067741W WO 2009100795 A1 WO2009100795 A1 WO 2009100795A1
Authority
WO
WIPO (PCT)
Prior art keywords
blade
rotor
teeth
end faces
along
Prior art date
Application number
PCT/EP2008/067741
Other languages
German (de)
English (en)
Inventor
Fathi Ahmad
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Publication of WO2009100795A1 publication Critical patent/WO2009100795A1/fr

Links

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
    • 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
    • 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

Definitions

  • the invention relates to a blade for a turbomachine, with a blade root, at its upper side adjoined by a working fluid aerodynamically curved blade, wherein the blade foot along a longitudinal extent between two end sides rectilinearly and the two end sides laterally connecting side walls each at least one extending along the longitudinal extension extending and extending transversely thereof tooth for positive attachment to a rotor.
  • Blades for turbomachinery with a hammer-shaped or fir tree-shaped blade root seen in cross-section have long been known from the state of the art.
  • Each of these blade feet comprises two side walls connecting the two end sides laterally, on which - depending on the cross-sectional shape - each one or more, along the longitudinal extent and transversely protruding tooth resp. Teeth is or are arranged.
  • each side wall comprises only one protruding tooth.
  • each side wall comprises two or more adjacent teeth. Relative to the mounting position of the blade in a rotor of the turbomachine with a machine axis, the rectilinear one extends
  • the teeth protrude transversely therefrom with respect to an imaginary sidewall plane of the blade root, which is spanned by the machine axis radial direction and an axially extending auxiliary axis, and are provided with a plurality of teeth on a side wall of the blade root relative to the blade root Machine axis - spaced apart in the radial direction.
  • rotor blades of steam turbines are known from the state of the art, whose blade roots run uniformly curved along their length between the two end faces, ie along the machine axis.
  • Runner mounting for compressor blades known.
  • the hook-like feet of the blades are curved convexly along their extension.
  • the curvature of the feet is chosen so that points at the rotor-mounted blade whose convex hook surface to the rotor center.
  • the holding grooves in the rotor which are necessary for entanglement, are correspondingly shaped to the hook-like feet and open into the lateral surface of the rotor.
  • Blade holding in contrast it is executed non-arched.
  • the object underlying the invention is inventively achieved in that the teeth of the blade root are curved along the rectilinear longitudinal extension of the blade root to the top.
  • the teeth have a substantially constant tooth height along their longitudinal extent.
  • the tooth height is determined by the vertical distance from an imaginary side wall level to the tooth tip.
  • a curvature directed to the top arises in that each tooth has a supporting flank facing the airfoil and a bottom flank facing away from the airfoil, wherein the support flank is convexly curved along the longitudinal extent of the teeth and the lower flanks are concavely curved along the longitudinal extension of the teeth.
  • the rotor on which the object is based has a shaft collar in which retaining grooves extending in the axial direction are provided for accommodating rotor blades, which-seen in cross section-are hammer-shaped or fir-tree-shaped with the formation of pockets are bounded radially outwardly from a first side surface and radially inwardly from a second side surface, wherein the retaining grooves are formed corresponding to the blade roots of blades according to the invention, such that the first side surface is concavely curved along the longitudinal extent of the retaining groove and along the second side surface the longitudinal extent of the retaining groove is convexly curved.
  • the retaining grooves comprise, in addition to a groove base, two lateral groove flanks in which pockets corresponding to the teeth of the blade roots are provided, in which the teeth generally engage in a form-fitting manner when the blade is inserted into the retaining groove. Due to the curvature of the teeth and the compulsorily corresponding pockets, the contact surface against which the blade rests under the action of centrifugal force in the retaining groove can be increased in relation to non-curved teeth. The contact area between the blade and the rotor is increased by the proposed curvature. The centrifugal force acting on the blade during operation of the turbomachine can thus be absorbed by a larger contact surface, which leads to lower bearing stresses in the rotor material surrounding the blade root.
  • the load perpendicular to the contact surface thus has both an axial and a radial component with respect to the machines of the rotor, which leads to a lower CF load (cycle fatigue).
  • the curvature of the teeth leads to a shift of the center of gravity of the rotor blade to the machine axis.
  • the curvatures of the teeth and the underside follow in each case a circular arc, wherein the respective centers of the different circular arcs coincide in one point.
  • the blade is the blade of the last turbine stage of a gas turbine or steam turbine, this can also be removed from the rotor, if the housing of the corresponding turbine is closed. All that is required for this is that the exhaust gas diffuser, which usually adjoins the last turbine stage of a turbine, is accessible to an installer and the rotor blade can not be removed counter to the flow direction of the working medium, but rather in the direction of flow.
  • the teeth are arched along their longitudinal extension to the upper side.
  • an underside of the blade root connecting the two end faces is arched over at least 80% of its longitudinal extent to an identical extent as the teeth.
  • the blade root on one of the two end faces on a connecting the two end faces underside to the top extending first foot height, which first foot height of the correspondingly determined second foot height of the other of the two end faces is different.
  • the blade root has a foot height which is identical to both end faces and in each case extends from a lower side connecting the two end faces to the upper side.
  • the shaft collar may be formed by a rotor disk or by a shaft portion. If, according to a further advantageous embodiment, the width of the teeth and / or the height of the teeth diverges along their longitudinal extension, the use of curved teeth on a rectilinear blade root can achieve an axial securing of the blade against displacement along the retaining groove, whereby further constructive effort can be avoided.
  • FIG. 1 shows a schematic side view of a rotor blade according to the invention for a turbomachine in a first embodiment
  • FIG. 3 shows a rotor blade according to the invention according to a second embodiment in a side view
  • FIG 4 shows the blade according to FIG 3 in one
  • FIG. 5 shows a detail of a rotor disk with a holding groove for receiving a moving blade according to the first embodiment
  • FIG. 6 shows the detail of a rotor disk with a holding groove for receiving a blade according to the second embodiment.
  • a rotor blade 10 according to the invention for a turbomachine is shown in FIG. 1 in a side view and in FIG. 2 in a front view according to a first embodiment.
  • the blade 10 is preferably designed as a turbine blade of a steam turbine or a gas turbine. Of course, it can also be the moving blade of a compressor.
  • the generally cast, one-piece blade 10 includes an aerodynamically curved blade 12, which is flowed around by a working fluid in a turbomachine when operating. At the root of the blade 12, a platform 16 connects as part of a blade root 14.
  • the platform 16 also has, as part of the blade root 14, its upper side 18, on which the blade leaf 12 adjoins.
  • the blade root 14 further comprises two flat, opposite end faces 20, 21, between which the blade root 14 extends in a straight line.
  • the two opposite end faces 20, 21 are connected laterally by two likewise opposite side walls 22.
  • the two opposite end faces 20, 21 are connected by an underside 24 of the blade root 14.
  • rotor blade 10 as shown in FIG. 2, is fir-tree-shaped, so that each of the two side walls 22 in each case comprises two teeth 28, 30 spaced apart from one another.
  • the teeth 28, 30 extend over the longitudinal extent of the blade root 14 from the first end face 20 to the second end face 21. Both the bottom 24 and the teeth 28, 30 arch along their Lijnserstre- ckung of the first end face 20 to the second end face 21st
  • Each tooth 28, 30 comprises a supporting flank 37 facing the blade leaf 12.
  • a supporting flank 37 is to be understood as meaning in particular that part of the relevant tooth 28, 30 which is pressed against a claw during centrifugal force.
  • the teeth have a lower edge 39 facing away from the blade. This is to be understood in particular as that part of the relevant tooth 28, 30, which the support flank 37 is opposite.
  • Both support flank 37 and lower flank 39 are arched towards the upper side 18. This results in that the surface having the support flank 37 is convexly curved and the surface having the lower flank 39 is concavely curved.
  • the machine axis is provided with the reference numeral 46, wherein the representation of the rotor blade 10 in FIG. 1 takes place in such a way as is later arranged opposite the machine axis 46 in the installed state.
  • the machine axis 46 is identical to the axis of rotation of the rotor.
  • the side walls 22 connecting the two end faces 20, 21 can also be understood as imaginary sidewall planes 26, 29, which sidewall planes 26, 29 can be clamped, for example, by a radius of the machine axis 46 and an auxiliary axis extending in the axial direction. Other lying, thereby not significantly tilted reference levels are also conceivable.
  • the vertical distance between the associated side wall plane 26, respectively. 29 and the farthest point of the outer contour of the corresponding tooth 28, 30 understood.
  • a width B of the teeth 28, 30 is determined by the distance of the crossing points
  • Both the first end face 20 and the second end face 21 have a foot height 23, 25.
  • the foot height 23, 25 is detected in each case frontally between the top 18 and the bottom 24.
  • the foot height 23 of the first end face 20 is smaller than the foot height 25 of the second end face 21.
  • the curvature of the bottom 24 is circular arc-shaped with a first radius Rl.
  • the curvature of the first teeth 28 have a radius R2, the curvature of the second teeth 30 have a Radius R3 on.
  • the centers of the radii Rl, R2, R3 lie on a point 27th
  • FIG. 5 shows a perspective view of a detail of a rotor disk 40, which is designed as part of the rotor of a turbomachine.
  • the rotor disk 40 has a retaining groove 42, which is suitable for receiving the rotor blade 10 according to the first embodiment.
  • the retaining groove 42 is formed fir-tree-shaped in plan view in a corresponding manner to the blade root 14 of the rotor blade 10.
  • the retaining groove 42 at the mutually opposite groove flanks 44, whose groove flank planes can be defined in an analogous manner to the sidewall planes, in each case two along the and tangential to the axis of rotation 46 extending Nutenför-mige pockets 48, 50.
  • Each pocket 48, 50 is bounded by a radially outwardly disposed first side surface 57, which is part of a pocket 48, 50 externally adjacent claw 49, 51.
  • each pocket 48, 50 is bounded radially inwardly by a second side surface 59, which is part of the pocket 50 to the inside adjacent claw 49 or part of the groove bottom of the retaining groove 42.
  • the correspondingly formed teeth 28, 30 of the blade root 14 can be inserted in a form-fitting manner.
  • the first side surfaces 57 which are arranged radially on the outside of the relevant pocket 48, 50, are concavely curved and the second side face 59 arranged radially inward relative to the relevant pocket 48, 50 are convexly curved.
  • the curvature of the first and second side surfaces 57, 59 corresponds to the Wölbungsutz the support flanks 37 and lower edges 39.
  • the teeth 28, 30 engage behind by the Bags 48, 50 formed claws 49, 51, so that under centrifugal force, the blade 10 can be held securely radially from these.
  • the assembly of the rotor blade 10 according to the first embodiment in the retaining groove 42 of the rotor disk 40 takes place such that the second end 21 is inserted into the front opening 52 of the retaining groove 42 according to FIG. 5 and by a subsequent pivoting movement to the rear opening 54 of the retaining groove 52 is moved until the first end face 20, the front opening 52 and the second end 21 closes the rear opening 54.
  • the height H of the teeth 28, 30 and accordingly also the corresponding height of the pockets 48, 50 and / or the width B of the teeth 28, 30 and the width B corresponding width of the pockets 48, 50 may additionally divergent in the axial direction of the rotor so that a self-clamping effect can be achieved in Einschwenk- direction.
  • an additional device for securing the blade 10 can be dispensed with against a further axial displacement, which would otherwise be required if the width B of the teeth 28, 30 and the constant height H of the teeth 28, 30 remain the same in the axial direction.
  • the end faces 20, 21 of the blade root 14 according to FIG 3 are the same height. Consequently, they have an identical foot height 23, 25 between top 18 and bottom 24.
  • the along the longitudinal extension extending teeth 28, 30 are curved to the top 18 of the blade root 14 out. This results in that the front ends 32 of the teeth 28, 30 are further away from the upper side 18 of the blade root 14 than the central portion 34 thereof.
  • the underside 24 of the blade root is forcibly curved to the same extent as the teeth 28 arranged on the side walls 22 , 30, so that the rotor 10 is mountable.
  • the teeth 28, 30 according to the second embodiment can be inserted into a holding groove 42 of a rotor disk 40 shown in FIG.
  • the retaining groove 42 is along her Longitudinal extent in the direction of the machine axis 46 in a manner corresponding to the teeth 28, 30 curved manner.
  • the measure provides for a blade 10 with a rectilinear, cross-sectionally hammer-shaped or fir-tree-shaped blade root 14, that the hammer shape or the Christmas tree-forming teeth 28, 30 of the blade root 14, which are provided at its also in the longitudinal direction rectilinear side walls 22, between the end faces 20, 21 of the blade root 14 are curved to extend when installed in the rotor state that contact surface 56 between the blade root 14 and rotor to which the blade 14 rests under centrifugal force.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne une mesure pour allonger la durée de vie d’une aube mobile (10). Cette mesure prévoit, pour une aube mobile (10) ayant un pied d’aube (14) rectiligne, à section en forme de marteau ou de sapin, que : les dents (28, 30) du pied d’aube (14), qui constituent la forme de marteau ou de sapin et qui sont prévues sur les parois latérales rectilignes (22) - s’étendant elles aussi en direction longitudinale - du pied d’aube (14), s’étendent de manière incurvée entre les côtés frontaux (20, 21) du pied d’aube (14), afin d’agrandir, dans l’état installé dans le rotor, la surface de contact (56) entre le pied d’aube (14) et le rotor sur laquelle le pied d’aube (14) s’applique sous l’action de la force centrifuge.
PCT/EP2008/067741 2008-02-15 2008-12-17 Aube mobile pour une turbomachine WO2009100795A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP08002849.1 2008-02-15
EP08002849A EP2090751A1 (fr) 2008-02-15 2008-02-15 Aube pour turbomachine

Publications (1)

Publication Number Publication Date
WO2009100795A1 true WO2009100795A1 (fr) 2009-08-20

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PCT/EP2008/067741 WO2009100795A1 (fr) 2008-02-15 2008-12-17 Aube mobile pour une turbomachine

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EP (1) EP2090751A1 (fr)
WO (1) WO2009100795A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3789586A1 (fr) * 2019-09-05 2021-03-10 Raytheon Technologies Corporation Montage d'élément aérodynamique pour un moteur à turbine à gaz
US11959399B2 (en) * 2021-08-11 2024-04-16 MTU Aero Engines AG Blade root receptacle for receiving a rotor blade

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9777575B2 (en) * 2014-01-20 2017-10-03 Honeywell International Inc. Turbine rotor assemblies with improved slot cavities
FR3042825B1 (fr) * 2015-10-27 2019-09-06 Safran Aircraft Engines Aube et disque de soufflante

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3378230A (en) * 1966-12-16 1968-04-16 Gen Electric Mounting of blades in turbomachine rotors
US4169694A (en) * 1977-07-20 1979-10-02 Electric Power Research Institute, Inc. Ceramic rotor blade having root with double curvature
GB2021700A (en) * 1978-05-20 1979-12-05 Rolls Royce Rotor for bladed fluid-flow machines
SU757747A1 (ru) * 1978-11-03 1980-08-23 Viktor V Darovskikh Рабочее колесо осевой турбомашины 1 2
JPS59108805A (ja) * 1982-12-15 1984-06-23 Toshiba Corp タ−ビン動翼の固定装置
US4483054A (en) * 1982-11-12 1984-11-20 United Technologies Corporation Method for making a drum rotor
DE19705323A1 (de) * 1997-02-12 1998-08-27 Siemens Ag Reduzierung von lokalen Spannungen in Schaufelfußnuten
US6244822B1 (en) * 1998-12-04 2001-06-12 Glenn B. Sinclair Precision crowning of blade attachments in gas turbines

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3378230A (en) * 1966-12-16 1968-04-16 Gen Electric Mounting of blades in turbomachine rotors
US4169694A (en) * 1977-07-20 1979-10-02 Electric Power Research Institute, Inc. Ceramic rotor blade having root with double curvature
GB2021700A (en) * 1978-05-20 1979-12-05 Rolls Royce Rotor for bladed fluid-flow machines
SU757747A1 (ru) * 1978-11-03 1980-08-23 Viktor V Darovskikh Рабочее колесо осевой турбомашины 1 2
US4483054A (en) * 1982-11-12 1984-11-20 United Technologies Corporation Method for making a drum rotor
JPS59108805A (ja) * 1982-12-15 1984-06-23 Toshiba Corp タ−ビン動翼の固定装置
DE19705323A1 (de) * 1997-02-12 1998-08-27 Siemens Ag Reduzierung von lokalen Spannungen in Schaufelfußnuten
US6244822B1 (en) * 1998-12-04 2001-06-12 Glenn B. Sinclair Precision crowning of blade attachments in gas turbines

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
DATABASE WPI Week 198119, Derwent World Patents Index; AN 1981-E3096D *

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3789586A1 (fr) * 2019-09-05 2021-03-10 Raytheon Technologies Corporation Montage d'élément aérodynamique pour un moteur à turbine à gaz
US11203944B2 (en) 2019-09-05 2021-12-21 Raytheon Technologies Corporation Flared fan hub slot
US11959399B2 (en) * 2021-08-11 2024-04-16 MTU Aero Engines AG Blade root receptacle for receiving a rotor blade

Also Published As

Publication number Publication date
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