WO2001071166A1 - Aube mobile de turbine - Google Patents

Aube mobile de turbine Download PDF

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Publication number
WO2001071166A1
WO2001071166A1 PCT/EP2001/002629 EP0102629W WO0171166A1 WO 2001071166 A1 WO2001071166 A1 WO 2001071166A1 EP 0102629 W EP0102629 W EP 0102629W WO 0171166 A1 WO0171166 A1 WO 0171166A1
Authority
WO
WIPO (PCT)
Prior art keywords
blade
turbine
recess
blade root
axis
Prior art date
Application number
PCT/EP2001/002629
Other languages
German (de)
English (en)
Inventor
Peter Tiemann
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 WO2001071166A1 publication Critical patent/WO2001071166A1/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

Definitions

  • the invention relates to a turbine blade arrangement with several m circumferential circumferences of a turbine disk, with a blade root which is staggered, each having a blade root, which has two longitudinal sides and end faces, has longitudinal teeth on its longitudinal sides and which in a turbo person is longitudinally slidable and there through groove. slow tooth, which engages behind its longitudinal tooth, is held radially against extraction.
  • Turbine impeller blades with grooves in a Turbmen disc are severely stressed in their groove areas by the centrifugal forces acting on the turbine blade when the turbine disc rotates.
  • the holding devices of the foot in the groove are designed as slanted longitudinal teeth.
  • the centrifugal forces, which point radially outwards, are introduced through the longitudinal tooth in the longitudinal tooth of the groove. Since the longitudinal teeth are in contact, this introduction deflects some of the centrifugal force.
  • the forces introduced are very stressful for the groove area, since they rise abruptly there. This creates a particularly heavy load in the lower groove area, which can lead to cracks.
  • the object is achieved in that the blade root has local material monitoring on its end face.
  • the invention has the advantage that fl enicra-induced voltage peaks are caught and are therefore not introduced into the end soapy area into the surrounding longitudinal slot teeth, but rather further inside, in the middle of the blade root.
  • This advantage is achieved in that the material is locally weakened on the front side. A material weakening is present if the surrounding areas have a greater rigidity, for example because the material is thinner at the weakening. Thus, the GESAM ⁇ te is reduced resulting stiffness of this area. Because when a load is applied, the soft, weakened area is deformed first. The material is no longer as rigid. In this way, only a reduced transmission of force to the surrounding groove can take place in this area.
  • the normally very rigid end faces of the blade root are made more resilient to stresses by the proposed arrangement.
  • the proposed arrangement prevents such high voltages from attacking on the end faces of the longitudinal tooth that damage occurs entstenen. In this way, for example, stress peaks due to fit failures, such as occur even with very careful post-machining of the turbine blade root, can be compensated for. As a result of the proposed arrangement, the service life of the turbine blade arrangement is increased and fewer faults occur during operation.
  • Material monitoring that is easy to calculate and reproducible is provided if the blade root has a recess on its end face.
  • the recess softens the forehead region of the foot against the attacking centrifugal force, so that it can be elastically compressed under the application of force. A smaller proportion of the force is introduced into the end region of the groove, and thus a larger proportion into the region of the center of the foot.
  • the recess on the end face of the blade root can be made during the casting by inserting a casting core from the outside or subsequently by mechanical processing.
  • the recess is a wedge-shaped notch on the end face of the blade root in the area between the longitudinal teeth closest to the axis of the turbine disc and the recess is open at an end of the blade root on the disc axis side, forces can be caused by elastic bending of the side flanks of the wedge-shaped notch be caught softly in this area. A smaller proportion of the force is transferred to the surrounding groove area. The load capacity is thus diverted to an area in the direction of the center of the blade root.
  • This spring-like folding of the wedge-shaped notch is limited by the fact that no permanent plastic deformations may occur. This can be achieved, for example, by maintaining the dimensions and shapes of the recess, in particular a certain width and depth, which, for example, depend on the bucket weight, but also on the opening flap in the groove and the manufacturing tolerances observed.
  • the recess has a maximum depth decreasing in the direction of the blade platform, the recess is softest in the end area on the disc side and becomes increasingly hard from there towards the center of the blade root with decreasing width.
  • the maximum notch depth can moreover be easily adapted in this way to a possible helix angle of the blade root by increasing the depth with increasing helix angle.
  • the recess has a rounded contour, it is ensured that the contact forces can be derived more smoothly. This prevents crack peaks from forming in the recess, for example in the event of changes in force and changes in the direction of force, which lead to damage to the material.
  • each of the two end faces of the blade root has local material monitoring, on both end faces the similar and with symmetrical design of the blade have the same voltage increases, to obtain similar or the same advantageous effects.
  • Coolant can be penetrated through the blade root and at the same time an efficiency improvement can take place due to an inclined position if the blade root has a cavity which has an access at the end of the blade root on the axis of the blade and the local material monitoring has such a distance from the access that under the operating load of the Turbine rotor blade the required stability is guaranteed.
  • coolant can be passed through the blade root and through the blade profile.
  • the local centrifugal force distributes the attacking centrifugal force towards the center of the blade root.
  • the strength of the blade root is also given in the forehead area in that a sufficient wall thickness on the front side of the blade root is ensured in spite of the local material monitoring. All of the advantages of the invention can thus be used and at the same time an internal cooling of the blade profile or a weight reduction can be carried out due to the hollowing out of the blade root.
  • the cavity at the end of the disk axis has a plurality of accesses which are arranged offset on a longitudinal axis and the local material monitoring on the end face is also at least partially on the longitudinal axis, a stress distribution is achieved centrally along the longitudinal axis.
  • the voltage is thus diverted symmetrically to the two flanks of the groove.
  • the forces are evenly distributed on both sides of the groove, thereby avoiding any excessive tension in the center area.
  • Several entrances ensure stabilization in the walls between the entrances, thereby evening out the force distribution. In particular, sufficient stability the distance from the local material monitoring to the access closest to the recess.
  • the blade root which starts from the disk axis in a star shape and is rotated through the radial axis through the blade root, is rotated through the turret disk, a strongly asymmetrical power transmission and an associated increase in Soannurgs are observed in the area of the ends of the lowermost slot teeth.
  • the groove ends which encompass the forehead areas of the feet, are subjected to a strong asymmetrical load due to the forces transmitted to them.
  • This asymmetrical load in the end area due to the bending stresses that arise and the associated crack nucleation, is a limit for the improvement of the effective cross-section due to the inclined position of the blade root ⁇ ar.
  • the local material monitoring according to the invention acts in particular against the recess in that the material of the foot behaves softer in this weakened forehead region.
  • the main load absorption of the component lying in the circumferential direction of the turbine disk of the contact pressure which arises under centrifugal force loading takes place at the further inner regions of the groove. Bending of the asymmetrically loaded groove is thus prevented even at steep angles of the blade root. In this way, a very large improvement in efficiency can take place by inserting blades which are inclined under large outflow angles without loss of strength, for example due to crack nucleation due to bending stresses in the end regions of the grooves.
  • the softness of the end face of the foot can be individually adapted to the needs caused by the inclination of the blade root if the width, the depth and the shape of the recess are matched to the angle and the spacing of the turbine blade root.
  • a softening of the entire front side of the blade root is ⁇ adurcn that the recess runs from the end of the blade root on the disk side to between the two opposite longitudinal teeth of the platform. In this way, force vertexes with large maxima can be compensated.
  • FIG. 1 is a perspective view of a turbine blade with a recess
  • FIG. 4 shows a schematic view of the turbine blade root in view II-II
  • FIG. 5 shows a schematic plan view of a circumferential area of a turbine disk with turbine blades
  • FIG. 6 shows a side view of the foot with a recess.
  • Fig.l shows a perspective view of a turbine blade 2.
  • the turbine blade 2 consists of a blade profile 10, which is adjacent to a parallelogrammfor ig beveled blade platform 11, which forms the conclusion of the underlying blade root 3.
  • the blade root 3 likewise has a parallelogram-shaped cross section parallel to the blade platform 11.
  • the platform 11 has a helix angle 24 relative to the vertical 14 on an end face 8 of the blade root 3.
  • the blade root 3 has a fir-tree-shaped cross section parallel to its end face 8, which has projecting longitudinal teeth 5 running parallel to one another along the two parallel longitudinal sides 4 of the blade root 3 and tapering 3 mm narrower towards an end 17 of the base on the disc axis side.
  • the longitudinal teeth 5 are related to a longitudinal axis of the blade 23 undercuts forming radial contact.
  • the blade foot 3 is inserted into a correspondingly negatively shaped turbomachine disc 6 with longitudinal teeth 5 receiving longitudinal cutouts 15 along its longitudinal sides 4 and decogenous elements on the axis of the turbine disk 1 are held radially by means of slot teeth 7 corresponding to the longitudinal teeth 5 ,
  • the region 26 of the turbine disk 1 lying parallel to the surface and lying between two blades 2 and parallel to the surface is thus stressed by the two adjacent turbine blades 2 in opposite directions.
  • the forces represented by the force vector arrows 30, n circumferential ⁇ chtung the Turmnenrise 1 cancel each other in the central region 28 mutually Anna nernd on ⁇ e indicated in Fig.5.
  • the blade root 3 has a local material monitoring in the form of a recess 9 on the end face 8.
  • the recess 9 is located approximately centrally between the longitudinal axis teeth 5 next to the disc axis tapered to the other end face 8 hm, rounded edges 12.
  • the recess 9 is open to the end 17 of the foot 3 hm on the disc axis side.
  • the recess 9 has its greatest height 27 directly on the end face 8 and falls rounded off towards the center of the blade root 3.
  • FIG. 3a, b, c show cross sections parallel to the blade platform 11 through the foot area with the outer dimension 9 along the section lines III a, b, c from FIG.
  • the cross sections have a maximum depth 18 which is at a distance from the end 17 on the disc axis side and with an approach to the blade platform 11.
  • the maximum width 16 of the recess 9 increases at a distance from the end 17 on the disc side.
  • the slope of the flanks 12 of the recesses 9 is adapted to this decrease, but is essentially constant.
  • Fig. Shows a top view II-II of the disc axis end 17 of the foot 3 from Fig.l.
  • the foot 3 has four approaches 19 of approximately the same elliptical cross section to an internal cavity, which is not shown.
  • the accesses 19 are separated from one another by central walls 22.
  • Both the accesses 19 and the recesses 9 lie with their longitudinal extensions along a longitudinal axis 21 of the foot, which runs parallel to the longitudinal sides 4 of the foot 3 in the middle between them.
  • the recesses 9 are at a distance 20 from the adjacent accesses 19.
  • the blade profile 10 of the turbine blade 2 can be supplied with coolant.
  • the Middle Iwan de 22 strengthen the disc area on the side of the disc axis and ensure sufficient resistance to the stress caused by the attacking forces of the flies.
  • FIG. 5 shows a plan view of a circumference of a turbine disk 1 with grooves 6 of turbine blades 2 inserted, which are at a distance 25 from one another between corresponding longitudinal sides.
  • the platforms 11 and with them the feet have an angle 24 to a perpendicular 14 on the front side of the turbine disk.
  • the front region 8 has an elongated recess 9.
  • the recess 9 is open at the disk-side end region 17 of the foot 3 and extends from the sheath-side end region 17 to between the uppermost long teeth 5.
  • the areas between the middle and the upper, opposite foot longitudinal teeth 5 can also be resiliently loaded. Voltage peaks in the forehead area 8 can be compensated for more effectively.

Abstract

L'invention concerne un système d'aubes mobiles de turbine comprenant plusieurs aubes mobiles de turbine (2) décalées dans le sens périphérique d'un disque de turbine (1) et pourvues chacune d'une emplanture d'aube (3) qui peut être insérée en long dans une rainure (6) du disque de turbine et y est maintenue radialement, sans possibilité d'extraction, par des dents longitudinales de rainure (7) s'accrochant avec liaison de forme derrière ses dents longitudinales d'emplanture (5). L'invention vise à réaliser des aubes mobiles de turbine (2) pouvant être utilisées sous des angles d'hélice supérieurs à ceux atteints jusqu'à présent. A cet effet, l'emplanture d'aube (3) présente sur sa face frontale (8) un affaiblissement de matériau local.
PCT/EP2001/002629 2000-03-21 2001-03-08 Aube mobile de turbine WO2001071166A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP00106142.3 2000-03-21
EP00106142A EP1136654A1 (fr) 2000-03-21 2000-03-21 Aube rotorique de turbine

Publications (1)

Publication Number Publication Date
WO2001071166A1 true WO2001071166A1 (fr) 2001-09-27

Family

ID=8168183

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2001/002629 WO2001071166A1 (fr) 2000-03-21 2001-03-08 Aube mobile de turbine

Country Status (2)

Country Link
EP (1) EP1136654A1 (fr)
WO (1) WO2001071166A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2442968A (en) * 2006-10-20 2008-04-23 Rolls Royce Plc Turbomachine rotor and rotor blade mounting thereon
CN104265377A (zh) * 2014-09-16 2015-01-07 上海金通灵动力科技有限公司 一种降低纵树型轮毂型线处应力的结构
US9777575B2 (en) 2014-01-20 2017-10-03 Honeywell International Inc. Turbine rotor assemblies with improved slot cavities

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6786696B2 (en) * 2002-05-06 2004-09-07 General Electric Company Root notched turbine blade
FR2903138B1 (fr) * 2006-06-28 2017-10-06 Snecma Aube mobile et disque de rotor de turbomachine, et dispositif d'attache d'une telle aube sur un tel disque
FR2995343B1 (fr) * 2012-09-11 2018-05-25 Safran Aircraft Engines Aube de turbine, turbine, et procede de fabrication
GB2529681B (en) 2014-08-29 2019-02-20 Rolls Royce Plc Gas turbine engine rotor arrangement
US10400784B2 (en) 2015-05-27 2019-09-03 United Technologies Corporation Fan blade attachment root with improved strain response
US20180112544A1 (en) * 2016-10-26 2018-04-26 Siemens Aktiengesellschaft Turbine rotor blade, turbine rotor arrangement and method for manufacturing a turbine rotor blade
CN109030012B (zh) * 2018-08-24 2024-01-23 哈尔滨电气股份有限公司 一种带有冷却通道的透平叶根疲劳试验模拟件及试验方法
FR3087479B1 (fr) 2018-10-23 2022-05-13 Safran Aircraft Engines Aube de turbomachine

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2643853A (en) * 1948-07-26 1953-06-30 Westinghouse Electric Corp Turbine apparatus
US4480957A (en) * 1983-04-14 1984-11-06 General Electric Company Dynamic response modification and stress reduction in dovetail and blade assembly
US5104290A (en) * 1989-11-09 1992-04-14 Rolls-Royce Plc Bladed rotor with axially extending radially re-entrant features
US5314307A (en) * 1992-12-18 1994-05-24 Alliedsignal Inc. Gas turbine test airfoil
EP0874136A2 (fr) * 1997-04-24 1998-10-28 United Technologies Corporation Aube de soufflante frangible
EP0906514A1 (fr) * 1996-06-21 1999-04-07 Siemens Aktiengesellschaft Rotor pour une turbomachine avec des pales a monter dans des rainures et pales pour un rotor

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2643853A (en) * 1948-07-26 1953-06-30 Westinghouse Electric Corp Turbine apparatus
US4480957A (en) * 1983-04-14 1984-11-06 General Electric Company Dynamic response modification and stress reduction in dovetail and blade assembly
US5104290A (en) * 1989-11-09 1992-04-14 Rolls-Royce Plc Bladed rotor with axially extending radially re-entrant features
US5314307A (en) * 1992-12-18 1994-05-24 Alliedsignal Inc. Gas turbine test airfoil
EP0906514A1 (fr) * 1996-06-21 1999-04-07 Siemens Aktiengesellschaft Rotor pour une turbomachine avec des pales a monter dans des rainures et pales pour un rotor
EP0874136A2 (fr) * 1997-04-24 1998-10-28 United Technologies Corporation Aube de soufflante frangible

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2442968A (en) * 2006-10-20 2008-04-23 Rolls Royce Plc Turbomachine rotor and rotor blade mounting thereon
GB2442968B (en) * 2006-10-20 2009-08-19 Rolls Royce Plc A turbomachine rotor blade and a turbomachine rotor
US7874806B2 (en) 2006-10-20 2011-01-25 Rolls-Royce Plc Turbomachine rotor blade and a turbomachine rotor
US9777575B2 (en) 2014-01-20 2017-10-03 Honeywell International Inc. Turbine rotor assemblies with improved slot cavities
CN104265377A (zh) * 2014-09-16 2015-01-07 上海金通灵动力科技有限公司 一种降低纵树型轮毂型线处应力的结构
CN104265377B (zh) * 2014-09-16 2016-01-20 上海金通灵动力科技有限公司 一种降低纵树型轮毂型线处应力的结构

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Publication number Publication date
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