EP4134523A2 - Logement de pied d'aube permettant de loger une aube mobile - Google Patents

Logement de pied d'aube permettant de loger une aube mobile Download PDF

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Publication number
EP4134523A2
EP4134523A2 EP22188295.4A EP22188295A EP4134523A2 EP 4134523 A2 EP4134523 A2 EP 4134523A2 EP 22188295 A EP22188295 A EP 22188295A EP 4134523 A2 EP4134523 A2 EP 4134523A2
Authority
EP
European Patent Office
Prior art keywords
blade root
blade
flank
receptacle
section
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP22188295.4A
Other languages
German (de)
English (en)
Other versions
EP4134523A3 (fr
Inventor
Kilian Bayer
David Koch
Susanne Pösl
Markus ZEIS
Andreas Hieber
Jens Trübenbach
Dieter Freno
Hermann Nachtigall
Miriam Rimke
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines 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 MTU Aero Engines AG filed Critical MTU Aero Engines AG
Publication of EP4134523A2 publication Critical patent/EP4134523A2/fr
Publication of EP4134523A3 publication Critical patent/EP4134523A3/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Withdrawn legal-status Critical Current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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/14—Two-dimensional elliptical
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/24—Three-dimensional ellipsoidal
    • 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
    • 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
    • F05D2260/00—Function
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction

Definitions

  • the present invention relates to a blade root receptacle for receiving a blade root of a rotating blade of a turbomachine.
  • a turbomachine is functionally divided into compressor, combustion chamber and turbine, whereby in the case of an aircraft engine, intake air is compressed in the compressor and burned in the downstream combustion chamber with added kerosene. The resulting hot gas, a mixture of combustion gas and air, flows through the downstream turbine and is expanded in the process.
  • the turbine and the compressor are each constructed in multiple stages, with each stage comprising a ring of guide vanes and a rotor blade ring. Each blade ring is made up of a plurality of peripherally consecutive blades around which the compressor gas or the hot gas flows, depending on the application.
  • a rotor blade ring can have, for example, a rotor disk on which the rotor blades are successively mounted circumferentially in a form-fitting manner.
  • the rotor disk can be provided with a blade root receptacle at different circulation positions, namely an axially extending profile groove.
  • a blade root can be inserted into each profile groove, the outer wall surface of which then forms a form fit with the flanks of the blade root receptacle that delimit the profile groove. Because of this profiling, the rotor blade is held in a form-fitting manner in the radial direction, in particular against the centrifugal forces during operation.
  • the present invention is based on the technical problem of specifying a particularly advantageous blade root receptacle.
  • the bulge or convex shape is not only related to the circumferential or radial extension of the supporting flank (perpendicular section), but also in terms of its longitudinal extension, ie in the axial direction (paraxial section).
  • This convexity or crowning which is formed in two directions, can e.g. B. be advantageous in terms of structural mechanics, for example, as a result, enable a more uniform load transfer between the blade root and the supporting flank.
  • z. B. can result in different contact areas due to production, can with the convex training z. B. a reproducible contact surface can be created.
  • smaller tolerances can only be provided locally in the area of the bulges and/or the influence of deviations outside of the bulges can be reduced.
  • axial refers to the axis of rotation around which the blade root receptacle with the rotor blade, and in particular the disk or the rotor blade ring, rotate during operation .
  • the perpendicular section is perpendicular to the axis of rotation; the axially parallel sectional plane is parallel thereto, and it can in particular be perpendicular to the supporting flank.
  • the bearing flank is "facing radially inwards at least in part", so a surface normal on the bearing flank has at least one radial component directed inwards. Depending on the specific configuration, it can also have a circulation component, ie lie at an angle. Viewed in the perpendicular section, the support flank can extend, for example, between a concave curved section, which leads radially inward into a radially inner free flank or the groove base, and a convex curvature, which leads into a radially outer free flank or, for example, the disk circumference.
  • the blade root receptacle can form a so-called fir tree profile, for example, but this is only one possibility.
  • the blade root in particular a bulge thereof that is essentially complementary to the blade root receptacle, is pressed against the support flank during operation.
  • the blade root receptacle can also have more than one bearing flank, for example a further bearing flank offset in the direction of rotation and/or one or more bearing flanks radially inside or outside.
  • more than one bearing flank can then also be formed with a bulge; a corresponding design of all bearing flanks of the blade root receptacle or only a subset thereof is possible.
  • the convex curvature can also extend axially over the entire support flank. In a preferred embodiment, it goes in the paraxial Viewed in section, however, in the direction of a first axial end of the supporting flank into a concave profile, ie the profile between the first end and the convex curvature is concave at least in sections.
  • the transition from the convex to the concave profile can be spaced, for example, by at least 5% of an axial length of the support flank from the first axial end, with further possible lower limits of, for example, at least 10% or 15% (and theoretical upper limits of 70% , 50% or 30%).
  • a certain distance between the convex shape and the (first) axial end of the supporting flank can be advantageous in terms of structural mechanics, for example.
  • the support flank runs straight into the first end, adjoining the concave profile in the direction of the first axial end, viewed in the axially parallel section.
  • the straight section can in particular lie parallel to the axis.
  • the “first end” can be located axially in front or axially behind in relation to the arrangement in the turbomachine, ie upstream or downstream.
  • the convex shape viewed in the axially parallel section, also transitions into a concave profile in the direction of a second axial end, which is axially opposite to the first, ie a concave profile adjoins the convex shape axially on both sides.
  • the concave profile can also be followed by a straight line in the direction of the second axial end, which runs into the second end of the supporting flank, in particular parallel to the axis (alternatively, however, another bulge can also follow, see below in detail).
  • a further preferred embodiment relates to the profile of the support flank in the section perpendicular to the axis, namely in this section the convex shape changes into a concave profile, preferably on both sides.
  • the latter means that in relation to a width direction of the supporting flank, in which its width is taken in the axially perpendicular section (and which, depending on the orientation of the supporting flank, has a circumferential and possibly a radial component), on both sides a concave course to the convex shape connects.
  • the concave course can be followed by a rectilinear course, to one or to both sides.
  • a further bulge is formed in the supporting flank, that is to say there are a total of at least two bulges in the supporting flank.
  • the further bulge can also have a convex shape when viewed both in a section perpendicular to the axis and in a section parallel to the axis.
  • the (first) and the further bulge are offset from one another in the axial direction; alternatively or additionally, they can be offset from one another in the width direction of the supporting flank. In the latter case, they can be offset with a rotating component and, depending on the orientation of the support flank (see above), with a radial component.
  • a large number of bulges can also be formed in the supporting flank, with possible upper limits being, for example, at most 30, 20 or 10 bulges, but in principle an even larger number is also possible.
  • exactly three bulges are provided in the supporting flank, which together form a reproducible abutment for the associated surface or flank of the blade root.
  • the three bulges are therefore preferably offset in the bearing flank in such a way that they define a plane with one another (that is to say they do not lie on a common straight line).
  • the number of bulges on one or each supporting flank of the blade root receptacle is in the range from 1 to 10 per supporting flank, preferably 2 to 7 per supporting flank, in particular 3 to 4 per supporting flank.
  • the bulge (40), in particular each of the bulges has a profile with a continuously differentiable course in each section perpendicular to the support flank through the bulge.
  • the progression in these configurations is soft and free of jags, cracks and/or edges. This enables a defined, to a certain extent areal and stress-technically particularly advantageous system.
  • the ratio H/D of the height H of the bulge to the smallest transverse dimension D of the bulge within the support flank is in the range of 1:2 to 1:500, in particular for each of the bulges 1:10 to 1:200 or 1:100 to 1:500. This enables a particularly advantageous system in terms of voltage.
  • the invention also relates to a blade arrangement with a blade root receptacle disclosed in the present case and a moving blade, the blade root of which is arranged in the blade root receptacle.
  • the blade root lies against the support flank, during operation it is pressed against it by centrifugal force.
  • the invention relates to a rotor disk for a rotor blade ring of a turbomachine, in particular an aircraft engine.
  • the rotor disk which can have a ring shape overall, for example, has a plurality of blade root receptacles distributed circumferentially, each of which is preferably designed with a supporting flank according to the present disclosure.
  • the invention relates to a method for producing a blade root receptacle disclosed in the present case or the blade arrangement or rotor disk, the support flank being machined from a solid material by removing material. This is preferably done by electrochemical removal (Electro Chemical Machining , ECM), with which the desired surface contour can be achieved particularly well.
  • ECM Electro Chemical Machining
  • FIG 1 shows a turbomachine 1, specifically a turbofan engine, in an axial section.
  • the turbomachine 1 is functionally divided into a compressor 1a, a combustion chamber 1b and a turbine 1c. Both the compressor 1a and the turbine 1c are each constructed of multiple stages. Each of the stages consists of a vane ring and a rotor blade ring. For the sake of clarity, for the turbine 1c only one of the stages of the guide blade ring 3 and the associated rotor blade ring 4 are referenced with reference symbols.
  • the intake air is compressed in the compressor 1a and then burned in the downstream combustion chamber 1b with added kerosene.
  • the hot gas flows through the hot gas duct and drives the moving blade rings, which rotate about the axis of rotation 2 .
  • the rotor blade ring 4 comprises a rotor disk 4.1, in which a plurality of rotor blades 4.2 are used, distributed circumferentially.
  • FIG. 2 shows a section of the running disk 4.1 in an axial view, ie looking at it along the axis of rotation 2.
  • a blade root receptacle 20 is provided in the running disk 4.1, which is introduced in the form of a profiled groove which penetrates the running disk 4.1 axially.
  • a blade root 21 indicated here only schematically, of the respective rotor blade 4 . In operation, it is pressed against bearing flanks 25 of the blade root receptacle, one of which is referenced here with a reference number and will be discussed in further detail.
  • the supporting flank 25 extends between a convex curvature section 26 and a concave curvature section 27, as shown in FIG figure 2 is to recognize their width 28. Perpendicular thereto, ie in the axial direction 32, the supporting flank 25 has its longitudinal extension. In the present case, it is oriented in such a way that it partially runs in the radial direction 22 and also in the circumferential direction 33 .
  • figure 3 shows the supporting flank 25 in a detailed view, namely in a section perpendicular to the axial direction 32 .
  • This reveals a bulge 40 which has a convex shape 41 .
  • the convex shape 41 merges into a concave profile 42 on both sides.
  • figure 4 shows the bulge 40 in a sectional plane perpendicular thereto, namely an axis-parallel section AA (cf figure 2 to the position of the cutting plane).
  • the bulge 40 also has a convex shape 51 in this section, which in the present example transitions first into a concave profile 52 and then into a straight line 53 both in the direction of a first axial end 61 and in the direction of a second axial end 62 .
  • a transition 56 between convex/concave extension is about 30% away from the first axial end 61 in this example (which applies in mirror image to the other transition and the second axial end 62).
  • figure 5 shows a supporting flank 25 in a schematic top view, in which, in addition to the (first) bulge 40, a further bulge 70 is provided, which is offset axially and also circumferentially or radially with respect to the first bulge 40.
  • a total of three bulges 71 are provided in the support flank 25, which together form a defined contact surface.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP22188295.4A 2021-08-11 2022-08-02 Logement de pied d'aube permettant de loger une aube mobile Withdrawn EP4134523A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102021120876.9A DE102021120876A1 (de) 2021-08-11 2021-08-11 Schaufelfussaufnahme zum aufnehmen einer laufschaufel

Publications (2)

Publication Number Publication Date
EP4134523A2 true EP4134523A2 (fr) 2023-02-15
EP4134523A3 EP4134523A3 (fr) 2023-03-08

Family

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EP22188295.4A Withdrawn EP4134523A3 (fr) 2021-08-11 2022-08-02 Logement de pied d'aube permettant de loger une aube mobile

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US (1) US11959399B2 (fr)
EP (1) EP4134523A3 (fr)
DE (1) DE102021120876A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US12305533B2 (en) 2023-06-23 2025-05-20 Pratt & Whitney Canada Corp. Turbine rotor dovetail structure with splines

Citations (2)

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Publication number Priority date Publication date Assignee Title
WO2009100795A1 (fr) * 2008-02-15 2009-08-20 Siemens Aktiengesellschaft Aube mobile pour une turbomachine
US20150098832A1 (en) * 2013-10-09 2015-04-09 General Electric Company Method and system for relieving turbine rotor blade dovetail stress

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US3378230A (en) * 1966-12-16 1968-04-16 Gen Electric Mounting of blades in turbomachine rotors
US3809495A (en) 1973-03-27 1974-05-07 Westinghouse Electric Corp Turbine rotor having cushioned support surfaces for ceramic blades mounted thereon
US4169694A (en) * 1977-07-20 1979-10-02 Electric Power Research Institute, Inc. Ceramic rotor blade having root with double curvature
GB2238581B (en) * 1989-11-30 1994-01-12 Rolls Royce Plc Improved attachment of a gas turbine engine blade to a turbine rotor disc
US6764282B2 (en) * 2001-11-14 2004-07-20 United Technologies Corporation Blade for turbine engine
US7306434B2 (en) * 2004-02-12 2007-12-11 Rolls-Royce Plc Reduction of co-efficient of friction to reduce stress ratio in bearings and gas turbine parts
US7442007B2 (en) * 2005-06-02 2008-10-28 Pratt & Whitney Canada Corp. Angled blade firtree retaining system
US20080050238A1 (en) * 2006-08-24 2008-02-28 Pratt & Whitney Canada Corp. Disc firtree slot with truncation for blade attachment
US9174292B2 (en) * 2008-04-16 2015-11-03 United Technologies Corporation Electro chemical grinding (ECG) quill and method to manufacture a rotor blade retention slot
US8734112B2 (en) * 2010-11-30 2014-05-27 United Technologies Corporation Asymmetrical rotor blade slot attachment
EP2546465A1 (fr) * 2011-07-14 2013-01-16 Siemens Aktiengesellschaft Pied d'aube, aube, disque de rotor et ensemble de turbomachine associés
US9297265B2 (en) * 2012-12-04 2016-03-29 General Electric Company Apparatus having engineered surface feature and method to reduce wear and friction between CMC-to-metal attachment and interface
US20160305259A1 (en) 2015-04-13 2016-10-20 Charles Evans Turbine blade retention configuration
CN205172641U (zh) 2015-11-30 2016-04-20 中航商用航空发动机有限责任公司 榫连结构以及航空发动机
FR3054855B1 (fr) 2016-08-08 2020-05-01 Safran Aircraft Engines Disque de rotor de turbomachine
FR3075255B1 (fr) 2017-12-14 2020-06-12 Safran Aircraft Engines Aube de turbomachine
DE102019210699A1 (de) 2019-07-19 2021-01-21 MTU Aero Engines AG Zwischenelement für eine Schaufel-Rotorscheiben-Verbindung bei einem Rotor einer Strömungsmaschine und Rotor für eine Strömungsmaschine

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009100795A1 (fr) * 2008-02-15 2009-08-20 Siemens Aktiengesellschaft Aube mobile pour une turbomachine
US20150098832A1 (en) * 2013-10-09 2015-04-09 General Electric Company Method and system for relieving turbine rotor blade dovetail stress

Also Published As

Publication number Publication date
US11959399B2 (en) 2024-04-16
DE102021120876A1 (de) 2023-02-16
EP4134523A3 (fr) 2023-03-08
US20230046019A1 (en) 2023-02-16

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