EP3425162A1 - Aube de turbine et évidemment de fixation pour une turbomachine et procédé de fabrication associé - Google Patents

Aube de turbine et évidemment de fixation pour une turbomachine et procédé de fabrication associé Download PDF

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Publication number
EP3425162A1
EP3425162A1 EP17180253.1A EP17180253A EP3425162A1 EP 3425162 A1 EP3425162 A1 EP 3425162A1 EP 17180253 A EP17180253 A EP 17180253A EP 3425162 A1 EP3425162 A1 EP 3425162A1
Authority
EP
European Patent Office
Prior art keywords
tooth flank
anchoring
recess
elevation
anchoring tooth
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Withdrawn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
EP17180253.1A
Other languages
German (de)
English (en)
Inventor
Balazs Janos Becs
Ricardo NILSSON
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 EP17180253.1A priority Critical patent/EP3425162A1/fr
Publication of EP3425162A1 publication Critical patent/EP3425162A1/fr
Withdrawn legal-status Critical Current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
    • F01D5/30—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
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material

Definitions

  • the invention relates to a turbine blade for a turbomachine, a mounting recess for a turbomachine and method for producing a turbine blade of a turbomachine and a mounting recess of a turbomachine.
  • a turbine blade for a turbomachine such as a gas turbine
  • a turbomachine such as a gas turbine
  • the blade attachment section serves to secure the turbine blade in the fastening recess provided for it in all phases of operation.
  • the operating phases include a full load of the gas turbines, a stoppage of the gas turbine and all areas in between.
  • the various operating phases cause different loads to be absorbed by the blade attachment portion and the attachment recess.
  • the blade attachment portion usually has a profile shape which forms a positive connection with the mounting recess, whereby an unwanted movement of the turbine blade is counteracted.
  • the blade attachment portion has in the joining direction a first edge region disposed at the beginning of the blade attachment portion and a second edge region disposed at the end of the blade attachment portion. These edge areas are under high load particularly high loads, so-called edge stresses exposed. These loads lead to very high mechanical stresses in these edge areas. Due to the fact that the edge regions are exposed to particularly high voltages, under full load, for example, voltage peaks can occur which exceed the material limits of the material used. If the stress spikes exceed the material limits, unwanted deformations or even material fractures can occur which can damage the blade attachment section, the turbine blade and the entire turbomachine.
  • the object of the invention is therefore to provide a turbine blade for a turbomachine, a mounting recess for a turbomachine and method for producing a turbine blade of a turbomachine and a mounting recess of a turbomachine, in their blade mounting portion or in the mounting recess an occurrence of voltage peaks that the material boundaries of the material used to prevent, whereby the turbine blade and the mounting recess have a long life.
  • the turbomachine blade according to the invention for a turbomachine has a blade attachment section which has at least one anchoring tooth which is designed for installation in a corresponding attachment recess, wherein the at least one anchoring tooth has at least one anchoring tooth flank whose surface extends from two edges extending in the joining direction and from an initial edge and is delimited by an end edge whose direction of extension deviates from the joining direction, wherein one of the anchoring tooth flanks has at least one elevation along the joining direction extending edges, the elevation having a maximum extension in a region of the anchoring tooth flank extending from the leading edge and the end edge of the anchoring tooth flank is spaced at least greater than zero, whereby at least one defined engagement point or at least one defined engagement region with a voltage applied to the anchoring tooth flank Befest onlysausEnglishungszahnflanke of the mounting recess can be formed.
  • the anchoring tooth flanks Due to the fact that at least one of the anchoring tooth flanks has an increase along the edges extending in the joining direction, in the region of the elevation the defined engagement point or the defined engagement region forms with the adjoining fastening recess tooth flank of the fastening recess.
  • a turbomachine is a fluid energy machine that allows energy transfer between a fluid and a machine by the laws of fluid dynamics.
  • the blade attachment portion is formed, for example, with a profile which is formed symmetrically on its two profile sides, a first profile side and a second profile side.
  • the blade attachment section can have, for example, more than one of the anchoring teeth on each of the profile sides.
  • each of the profile sides can have more than one of the anchoring teeth
  • each of the profile sides also has more than one of the anchoring tooth flanks.
  • each of the anchoring teeth usually has two anchoring tooth flanks, it must be distinguished in which direction the anchoring tooth flanks are oriented. In most cases, one of the anchoring tooth flanks of the anchoring tooth is oriented substantially radially outwardly and the other of the anchoring tooth flanks of the anchoring tooth is oriented substantially radially inwards.
  • edges which extend in the joining direction preferably run in the axial direction of the flow machine, but may, for example, also deviate therefrom and run along a curve.
  • the edges which extend in the joining direction preferably run along this curve insofar as the fastening recess in which the blade fastening section is inserted along the same curve or along the same curves.
  • the leading edge connects the two edges extending in the joining direction on a front edge-side end face of the blade fastening section, and the end edge connects the edges extending in the joining direction on a trailing edge-side end face of the blade fastening section.
  • one of the leading edges, one of the edges extending in the joining direction, one of the end edges and one of the other edges extending in the joining direction forms one of the anchoring tooth flanks.
  • the edges extending in the joining direction can be arranged at different positions on the anchoring tooth.
  • the anchoring tooth flank is formed by the surrounding edges, it has a flat geometric surface, which is formed by the geometric shape of the edges.
  • the geometric surface of the anchoring tooth flanks does not have to be flat, but can be curved by way of example or have a different geometric shape.
  • the elevation arranged on a curved geometrical surface can, for example, be formed as a slightly more outwardly curved surface. Because the slightly more outwardly curved surface forms an elevation, a defined engagement point or a defined engagement edge or a defined engagement region forms with the adjacent engagement surface of the attachment recess.
  • the attachment recess has, for example, an inwardly curved geometric surface which is a negative of the outwardly directed curved geometric Surface of the anchoring tooth flank without the increase represents.
  • the increase may, for example, also be only a very locally positioned elevation or a bead-like thickening.
  • the anchoring tooth flank elastically deforms with the increase under load, as a result of which the anchoring tooth flank conforms to the raised engagement surface of the fastening recess.
  • the fact that the anchoring tooth flank conforms to the fastening recess increases the area of the anchoring tooth flank which absorbs the stresses, as a result of which the stresses are distributed over a larger area, as a result of which local voltage peaks decrease.
  • the entire surface of the anchoring tooth flank rests against the engagement surface of the fastening recess with the elevation only under a relatively high load.
  • the engagement surface of the fastening recess bears against the entire surface of the anchoring tooth flank with the elevation only under full load of the turbomachine.
  • the anchoring tooth flank also plastically deforms with the increase, whereby an optimal fitting to the engagement surface of the fastening recess can be realized for a longer period of time.
  • the anchoring tooth flank has at least one elevation
  • the entire stresses occurring on the profile can be influenced. It can be influenced in which areas the highest voltages and in which areas the smallest voltages occur. Depending on requirements, this can be influenced by the positioning of at least one increase the stress distribution, whereby the life of the turbine blade can be positively influenced.
  • the increase with the anchoring tooth is usually made of the same material, but it is also conceivable that the increase may be formed of a different material. Furthermore, the increase may be integrally formed with the anchoring tooth.
  • the blade attachment portion of the turbine blade on two or more anchoring teeth, each having the increase.
  • the blade attachment portion has two or more anchoring teeth, each having the increase, formed on each of the anchoring teeth of the defined engagement point or the defined engagement region with the voltage applied to the respective anchoring tooth flank Befest onlysausEnglishungszahnflanke of the mounting recess.
  • the blade attachment section has three anchoring teeth, each with two anchoring tooth flanks, on each of the profile sides, it may be advantageous to equip the two outwardly oriented anchoring tooth flanks of the two anchoring teeth of the two profile sides arranged radially further in each case with the elevation.
  • the stress peaks at the edge regions of the anchoring tooth flanks and / or notches occurring at the anchoring tooth valleys can be reduced or even avoided at several or all of the anchoring tooth flanks.
  • the greatest stresses along the anchoring tooth flanks and / or the largest notch stresses occur over the entire blade attachment portion only in the region spaced from the starting edges and the end edges of the anchoring tooth flanks. The fact that this area absorbs the greatest stresses, and not the edge areas, increases the service life of the blade attachment section.
  • the anchoring tooth flank has an anchoring tooth flank center point, wherein the elevation of the anchoring tooth flank has its maximum extent in a region of the anchoring tooth flank center point.
  • the anchoring tooth flank center For example, is the geometric center of the surface of the anchoring tooth flank.
  • the defined engagement point or defined engagement area with the anchoring tooth flank engaging securement tooth flank of the mounting recess forms at the region of the anchoring tooth flank center point, whereby the forces occurring under load are first in the range engage the Anank fürszahnflankenstoffticians and increases with increasing load due to the elastic and / or plastic deformation of the Anank fürszahnflanke or the mounting recess, the area extending from Verank fürszahnflankenstoff Vietnamese up to the edge regions of the Verank fürs leopardflanke, whereby the edge areas, for example, only under full load must absorb relatively low forces. Because the edge regions only have to absorb relatively small forces under full load, relatively low stresses arise in the edge regions, which in turn lead to relatively low edge stresses, which is why the blade fastening section according to the invention has the longer service life.
  • the elevation has an elevation profile extending from the start edge to the end edge or extending in a region portion between the start edge and the end edge.
  • the elevation profile is essentially formed following the edges extending in the joining direction.
  • the elevation can extend, for example, along the entire anchoring tooth flank, from the starting edge to the end edge, or extend only in an area section between the starting edge and the end edge. Due to the fact that the elevation profile can extend completely or only in sections along the entire anchoring tooth flank, it is possible, depending on the requirements, to position the elevation at the desired position along the anchoring tooth flank.
  • the increase profile can be continuous or discontinuous or regionally continuous and / or regionally discontinuous.
  • the elevation profile is formed at least in regions of at least one higher-order curve, a sinusoidal curve or at least one higher-order curve segment, a sinusoidal curve segment or a straight line segment.
  • a particularly advantageous nestling of the anchoring tooth flank can be realized with the increase of the engagement surface of the mounting recess . It is also conceivable, for example, that a plurality of maximum expansions of the elevation form along the anchoring tooth flank. Because the elevation profile along the joining edges extends, for example, along the straight line section, a relatively simple production of the elevation is possible.
  • the elevation profile is composed along the edges extending in the joining direction from the straight line section, the higher-order curve section and the sinusoidal curve section.
  • the elevation profile has a plurality of the maximum dimensions and a plurality of minimum dimensions.
  • the elevation profile should be selected according to the requirements and essentially serves to enable optimal transmission of forces from the anchoring tooth flank to an engagement surface of the fastening recess.
  • a plurality of the anchoring tooth flanks or each of the anchoring tooth flanks have a different elevation profile.
  • the elevation profile changes along the edges extending in the joining direction and changes along the leading edge and / or the trailing edge.
  • the elevation profile can be freely designed.
  • the maximum extent of the elevation is preferably arranged in a region of the anchoring tooth flank which is spaced from at least one of the edges of the anchoring tooth flank which extends in the joining direction. Characterized in that the maximum extent of the increase in a region of the anchoring tooth flank is arranged, which is spaced from at least one of the joining direction extending edges of the anchoring tooth flank, the defined engagement point or the defined engagement portion of the anchoring tooth flank with the adjacent Befest
  • This elevation profile along the leading edge and / or along the end edge may be constructed from the same curve sections as the elevation profile along one of the edges extending in the joining direction. It is also possible that the elevation profile extends along the start edge and / or along the end edge along the entire leading edge and / or along the entire end edge, from one joining edge to the other joining edge, or only partially formed between them. Likewise, the elevation profile may vary along the leading edge and / or along the end edge along one of the edges extending in the joining direction.
  • the surface of the elevation is thus formed in the joining direction from the elevation profile of extending in the joining direction edges and deviating from the joining direction of the elevation profile of the leading edge and / or end edge.
  • the surface of the increase can be wavy or wavy, smooth or partially smooth, curved or wavy partially curved, continuous or regionally continuous, unsteady or regionally discontinuous and even or regionally flat.
  • the blade attachment portion is formed as a fir tree blade attachment portion. Characterized in that the blade attachment portion is formed as a fir tree blade attachment portion, the blade attachment portion has at least two anchoring teeth per profile side, wherein the radially inner anchoring tooth preferably has the smaller anchoring tooth flank than the radially outer anchoring tooth.
  • the fir tree blade attachment portions preferably have a V-shape that is substantially tapered from outside to inside.
  • the anchoring tooth disposed radially further inwards preferably has the smaller anchoring tooth flank than the anchoring tooth arranged radially further, and due to the V-shape of the fir tree blade mounting section, it may be advantageous for the elevation to be arranged on the anchoring tooth arranged radially further inwards. Due to the V-shape and the smaller surface of the radially inner anchoring tooth flank arranged this anchoring tooth flank is easily elastically deformable, which is why it advantageously conforms to the engagement surface of the mounting recess and thereby advantageously transfers the forces occurring. Why the blade attachment portion has the longer life.
  • At least one of the edges extending in the joining direction and / or the starting edge and / or the end edge has a curvature.
  • the fastening recess into which the blade attachment section must be inserted has a curvature, thus it is necessary for a positive connection that the blade attachment section also has the same curvature.
  • the blade attachment section has the curvature, most of them also extend in the joining direction Edges of the anchoring tooth flank on this curvature.
  • the anchoring tooth flank may merge along the joining edge via another curvature into another region of the anchoring tooth such as, for example, an anchoring tooth tip or an anchoring tooth tip.
  • the increase has a maximum extension of 0.2mm.
  • the maximum extent of the increase is the difference between the point of engagement or the engagement region with the engagement surface of the attachment recess and the anchorage side without elevation which bears against the anchoring tooth flank.
  • the machining may include, by way of example, milling, grinding, planing or other machining methods.
  • the method according to the invention for producing a turbine blade comprises the steps of: a) providing a turbine blade having a blade attachment portion with at least one anchoring tooth adapted for installation in a corresponding attachment recess, the anchor tooth having at least one anchoring tooth flank; b) Irregular application of material to the anchoring tooth flank of the anchoring tooth along one of the joining edges, whereby at least one elevation is formed on the anchoring tooth flank compared to the unprocessed anchoring tooth flank, whereby at least one defined engagement point or at least one defined engagement region with one on the Anchoring tooth flank adjacent Befest onlysaus predominantlyungszahnflanke the mounting recess is formed.
  • the irregular application of material to the anchoring tooth flank is realized by means of additive manufacturing methods. It is also conceivable that the entire turbine blade or parts of the turbine blade, such as, for example, the blade attachment section, can be manufactured using additive manufacturing methods. If the blade attachment section is produced by methods of additive manufacturing, it is possible to realize a provision of one of the anchoring tooth flanks with the increase in a particularly advantageous manner.
  • a mounting recess for a turbomachine has at least one fastening recess tooth, which is designed to receive a blade mounting section of a turbine blade, wherein the at least one fastening recess tooth has at least one Befest onlyungszahnflanke having at least one increase along a joining direction extending edge, the increase a maximum Expansion in a region of the Befest onlysausEnglishungszahnflanke, which is spaced from a leading edge and an end edge of the Befest onlysaus fundamentalungszahnflanke at least greater than zero, whereby at least one defined engagement point or at least one defined engagement region can be formed with a voltage applied to the Befest onlysausnaturalungszahnflanke Anank ceremoniesszahnflanke the blade attachment portion.
  • the elevation is not arranged on the blade attachment section but on the attachment recess.
  • the mounting recess has a profile of a negative of the blade attachment portion and thus also has at least one Befest onlyungszahnflanke, which could have an increase. It should be noted, however, that it may be advantageous to arrange the increase on one of the Befest onlysaus simplifiedungszahnflanken the mounting recess, which are oriented substantially radially inwardly.
  • the mounting recess has two or more Befest onlyungszähne, each having the increase in at least one of Befest onlystsEnglishungszahnflanken. It is also conceivable that the mounting recess has the increase at several or all of the Befest onlysausnaturalungszahnflanken.
  • the elevation has an elevation profile that extends along the entire attachment recess tooth flank in the joining direction or that extends in a region section of the attachment recess tooth flank in the joining direction.
  • the elevation profile is at least partially formed of at least one higher-order curve, a sinusoidal curve or at least one higher-order curve segment, a sinusoidal curve segment or a straight line segment.
  • the elevation profile of the fastening recess tooth flank of the fastening recess can have the same geometric surface shapes as the elevation of the anchoring tooth flanks of the blade fastening portion.
  • the method according to the invention for producing a fastening recess comprises the following steps: a) providing a fastening recess having at least one fastening recess tooth, which is designed to receive a blade fastening section of a turbine blade, wherein the fastening recess tooth has at least one fastening recess tooth flank; b) Abrasive removal of material from the attachment recess tooth flank of the attachment recess tooth, thereby forming at least one elevation on the attachment recess tooth flank compared to the unmachined attachment recess tooth flank, thereby forming at least one defined engagement point or at least one defined engagement portion with an anchoring tooth flank of the blade attachment portion abutting the attachment recess tooth flank.
  • the machining may include, by way of example, milling, grinding, planing or other machining methods.
  • the method according to the invention for producing a fastening recess comprises the following steps: a) providing a fastening recess having at least one fastening recess tooth, which is designed to receive a blade fastening section of a turbine blade, wherein the fastening recess tooth has at least one fastening recess tooth flank; b) Irregular application of material from the attachment recess tooth flank of the attachment recess tooth, thereby forming at least one elevation on the attachment recess tooth flank compared to the unprocessed fastener recess tooth flank, whereby at least one defined engagement point or at least one defined engagement portion adjoins the attachment recess tooth flank An anchoring tooth flank of the blade mounting portion is formed.
  • a turbomachine preferably has such a turbine blade and / or a blade attachment section. It is conceivable, by way of example, that the blade attachment section and the attachment recess have the same, a similar or a different elevation. As a result, the desired effect, for example, be particularly enhanced.
  • FIG. 1 shows a turbine blade 1 for a turbomachine, which has an airfoil 2, a platform 3 and a blade attachment portion 4.
  • the airfoil 2 has a front edge 5 and a trailing edge 6, wherein the front edge 5 is arranged upstream relative to the trailing edge 6.
  • FIG. 2 shows the blade attachment portion 4 of in FIG. 1 shown blade 1.
  • the blade attachment section 4 has a front edge-side end face 7, a trailing edge-side end face 8, a bottom side 9, a first profile side 13 and a second profile side 14.
  • the front edge-side end face 7 is arranged substantially on the same side as the front edge 5 and the trailing edge-side end face 8 is arranged substantially on the same side as the trailing edge 6.
  • the bottom face 9 is oriented substantially radially inward, the first profile side 13 is arranged in relation to the blade 1 substantially on the pressure side and the second profile side 14 is arranged with respect to the blade 1 substantially suction side.
  • the blade attachment portion 4 is formed as a symmetrical Tannenbaumprofil.
  • the first profile page 13 is explained below. Due to the symmetry, the second profile side 14 has all the features of the first profile side 13.
  • the first profile side 13 has a first anchoring tooth 10, a second anchoring tooth 11 and a third anchoring tooth 12. These three anchoring teeth 10, 11, 12 together with a platform flank 31 and the bottom 9, the first profile side 13 of the blade mounting portion 4.
  • the anchoring tooth 10 and the anchoring tooth 11 have an anchoring tooth valley 18, a first anchoring tooth flank 15, an anchoring tooth tip 17 and a second anchoring tooth flank 16.
  • the third anchoring tooth 12 is formed by means of the anchoring tooth valley 18, the first anchoring tooth flank 15, the anchoring tooth tip 17 and the underside 9.
  • the anchoring teeth 10, 11, 12 extend from the front edge-side end face 7 up to the rear edge-side end face 8.
  • the third anchoring tooth 12 has an elevation 38 on its first anchoring tooth flank 15.
  • the first anchoring tooth 10 and the second anchoring tooth 11 do not have the elevation 38 on any of their anchoring tooth flanks 15, 16.
  • the other anchoring teeth 10, 11 also have the elevation 38.
  • the maximum extent of the elevation 38 on the third anchoring tooth 12 is arranged centrally on its first anchoring tooth flank 15.
  • first auxiliary level 19 and a second auxiliary level 20 are shown.
  • the first auxiliary plane 19 is drawn along an imaginary edge of the first anchoring tooth flank 15 of the second anchoring tooth 11 that extends in the joining direction.
  • first auxiliary plane 19 along the entire first anchoring tooth flank 15 of the second anchoring tooth 11 intersects this imaginary edge.
  • the second auxiliary plane 20 is arranged parallel to the first auxiliary plane 19 and intersects an imaginary substantially in the joining direction extending edge of the first anchoring tooth flank 15 of the third anchoring tooth 12 only in the region of the maximum extent of the elevation 38 of the third anchoring tooth 12.
  • the profile of the elevation 38 is formed along a sinusoidal curve and extends along the entire first anchoring tooth flank 15 of the third anchoring tooth 12. It is also conceivable, for example, that the profile is formed following another curve section and / or a straight line section and extends only over a region of the first anchoring tooth flank 15.
  • the FIG. 4 shows a diagram of occurring mechanical notch stresses along the anchoring tooth 18 of the third anchoring tooth 12.
  • the diagram has an abscissa 23, an ordinate 24, a first auxiliary line 28, a second auxiliary line 29 and an arrow 27.
  • the abscissa 23 represents the extension of the Anank fürszahntals 18 of the third anchoring tooth 12, starting at the front edge side end side 7 to the trailing edge side end 8.
  • the ordinate 24 represents the notch stresses occurring under load.
  • the notch stresses occur shown under load over the extension of the first anchoring tooth flank 15 of the third anchoring tooth 12.
  • a first curve 25 shows the notch stresses of the Anank fürszahntals 18 of the third anchoring tooth 12, which has the increase 38 and a second curve 26, the notch stresses occurring the same Anank fürszahntals 18, which does not have the increase 38.
  • FIG. 4 It can be clearly seen that the notch stresses occurring in the region of the maximum extent of the elevation 38 differ only insignificantly, but that the notch stresses occurring in the edge regions of the anchoring tooth valley 18, which are the increase 38, are less than the notch stresses of the same Anank fürs leopardtals 18, 38 do not have the increase.
  • the voltage peaks of the notch stresses shown in the upper right area of the diagram differ by about 25 percent.
  • the auxiliary line 28, the auxiliary line 29 and the arrow 27 represent the difference between the voltage peaks of the notch stresses between the first curve 25 and the second curve 26.
  • the FIG. 5 shows a mounting recess 32, in which the blade attachment portion 4 is inserted, whereby a positive connection between the two components, which can absorb the forces occurring arises.
  • the attachment recess 32 has a first attachment recess tooth 33, a second attachment recess tooth 34 and a third attachment recess tooth 35.
  • Each of the mounting recess teeth 33, 34, 35 has a first radially outwardly oriented first mounting recessed tooth flank 36 and a second generally radially inwardly oriented second mounting recessed tooth flank 37.
  • the Befest Trentauersaus Principleungszähne 33, 34, 35 form with the anchoring teeth 10, 11, 12 the positive connection and thereby allow an advantageous transfer of the forces occurring.
  • the elevation 38 is arranged on the substantially outwardly oriented anchoring tooth flank 15 of the fastening portion 4 or on the substantially inwardly oriented second Befest onlysaus predominantlyungszahnflanke 37 of the mounting recess 32 is arranged. Due to the fact that the elevation 38 is arranged on one of these two flanks, the occurring forces first of all come into contact with the region at which the elevation 38 has its maximum extent and distribute with increasing load to further regions of the flanks up to edge regions of the fastening recess tooth flank 37th

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP17180253.1A 2017-07-07 2017-07-07 Aube de turbine et évidemment de fixation pour une turbomachine et procédé de fabrication associé Withdrawn EP3425162A1 (fr)

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Application Number Priority Date Filing Date Title
EP17180253.1A EP3425162A1 (fr) 2017-07-07 2017-07-07 Aube de turbine et évidemment de fixation pour une turbomachine et procédé de fabrication associé

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP17180253.1A EP3425162A1 (fr) 2017-07-07 2017-07-07 Aube de turbine et évidemment de fixation pour une turbomachine et procédé de fabrication associé

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EP3425162A1 true EP3425162A1 (fr) 2019-01-09

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Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6397803A (ja) * 1986-10-13 1988-04-28 Hitachi Ltd タ−ビン翼の固定部構造
EP0431766A1 (fr) * 1989-11-30 1991-06-12 ROLLS-ROYCE plc Fixage amélioré d'une aube de turbine à gaz sur un disque de rotor de turbine
WO2006124615A1 (fr) * 2005-05-16 2006-11-23 General Electric Company Coupe arriere d'ailette/disque en queue d'aronde destinee a reduire les contraintes d'ailette/disque (7fa+e, etape 1)
DE102007051838A1 (de) * 2007-10-30 2009-05-07 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenschaufelfuß
EP2546465A1 (fr) * 2011-07-14 2013-01-16 Siemens Aktiengesellschaft Pied d'aube, aube, disque de rotor et ensemble de turbomachine associés
US20130195669A1 (en) * 2012-01-31 2013-08-01 James R. Murdock Fan blade attachment of gas turbine engine
EP2626516A1 (fr) * 2012-02-10 2013-08-14 General Electric Company Agencement de turbine et procédé pour modifier une fréquence de résonance
EP3098388A1 (fr) * 2015-05-28 2016-11-30 Siemens Aktiengesellschaft Aube pour une turbine à gaz

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6397803A (ja) * 1986-10-13 1988-04-28 Hitachi Ltd タ−ビン翼の固定部構造
EP0431766A1 (fr) * 1989-11-30 1991-06-12 ROLLS-ROYCE plc Fixage amélioré d'une aube de turbine à gaz sur un disque de rotor de turbine
WO2006124615A1 (fr) * 2005-05-16 2006-11-23 General Electric Company Coupe arriere d'ailette/disque en queue d'aronde destinee a reduire les contraintes d'ailette/disque (7fa+e, etape 1)
DE102007051838A1 (de) * 2007-10-30 2009-05-07 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenschaufelfuß
EP2546465A1 (fr) * 2011-07-14 2013-01-16 Siemens Aktiengesellschaft Pied d'aube, aube, disque de rotor et ensemble de turbomachine associés
US20130195669A1 (en) * 2012-01-31 2013-08-01 James R. Murdock Fan blade attachment of gas turbine engine
EP2626516A1 (fr) * 2012-02-10 2013-08-14 General Electric Company Agencement de turbine et procédé pour modifier une fréquence de résonance
EP3098388A1 (fr) * 2015-05-28 2016-11-30 Siemens Aktiengesellschaft Aube pour une turbine à gaz

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