EP3399151A1 - Tôle de protection d'usure pour une aube mobile d'une turbine à gaz - Google Patents

Tôle de protection d'usure pour une aube mobile d'une turbine à gaz Download PDF

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Publication number
EP3399151A1
EP3399151A1 EP18162095.6A EP18162095A EP3399151A1 EP 3399151 A1 EP3399151 A1 EP 3399151A1 EP 18162095 A EP18162095 A EP 18162095A EP 3399151 A1 EP3399151 A1 EP 3399151A1
Authority
EP
European Patent Office
Prior art keywords
axial
blade root
base
rotor
securing
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.)
Granted
Application number
EP18162095.6A
Other languages
German (de)
English (en)
Other versions
EP3399151B1 (fr
Inventor
Martin Pernleitner
Rudolf Stanka
Manfred Dopfer
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 EP3399151A1 publication Critical patent/EP3399151A1/fr
Application granted granted Critical
Publication of EP3399151B1 publication Critical patent/EP3399151B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/322—Blade mountings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/24—Rotors for turbines
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the present invention relates to a wear apron for a blade root of a blade of a gas turbine, in particular aircraft gas turbine, with a base and two base connected to the side walls, wherein the side walls are opposite and are shaped so that they substantially to an outer contour of a respective blade root are formed complementary, and wherein the wear guard is adapted to be received in an installed state between the respective blade root and a blade root receiving a rotor, in particular between the respective blade root and arranged in the blade root receiving axial securing element.
  • the provision of a wear guard between a blade root and a blade root receiving a rotor is known per se.
  • the wear guard plate is used in particular to avoid wear on the blade root and on the blade root receiving, so that after a certain period of the gas turbine usually only the wear plates must be replaced.
  • WO2016059338A1 is a wear protection film for a compressor blade is known, which is placed in the circumferential direction on a blade root and protrudes in the mounted state both in the circumferential direction and in the axial direction over the blade root.
  • the object of the invention is to provide a wear guard in which the installation is improved, so that damage to the wear guard can be prevented.
  • the sidewalls protrude at least one of their axial ends with a respective side end portion over an axial end portion of the base, and a guide portion adjoins the axial end portion of the base, starting from the base in the direction of axial side end portion of the side walls is bent.
  • the guide section facilitates insertion into the blade foot receptacle.
  • the side walls at least one of its axial ends, preferably the one with the bent guide portion projecting with a respective side end portion of an axial end portion of the base, also an axial protrusion of the wear guard plate on the rotor disk and / or in a groove, in particular Axial groove, the rotor disc recorded blade foot can be prevented.
  • the wear guard can be completely disposed within the disc groove and at the same time the blade end on one or both sides axially flush with the rotor disc, without the wear guard also only partially over the blade root and / or over the rotor disc.
  • the guide section be bent in such a way that it has substantially the same curvature as a blade root area which comes into contact or is in contact with the guide section.
  • the guide portion may have a projected length corresponding to about 0.75 to 1.0 times a radius with respect to a projection in the axial direction the guide section is bent. As a result, the guide portion does not protrude beyond the axial ends of the side end portions in the axial direction.
  • the guide portion may be disposed on an axial insertion end of the blade root, such that the wear guard plate and the associated blade root in the axial insertion direction are displaceable relative to the relevant rotor blade root receptacle of the rotor.
  • the wear guard plate is taken during insertion of the blade from the blade root.
  • the guide portion acts as a kind of tab, which rests on the blade root, so that the entire wear guard can be moved when the blade root is inserted in the axial direction.
  • the guide portion is particularly adapted to act during installation of the blade in the rotor. When removing a blade from the rotor of the guide section has no effect and the blade root can be moved separately from the wear plate in the axial direction of removal.
  • a rotor for a gas turbine in particular aircraft gas turbine, with a rotor body, in particular a blade disc, in which at least one blade root receptacle is formed, in which a blade root of an associated blade is arranged and secured by an axial securing element, and with a wear guard having a base and two side walls joined to the base, the side walls being circumferentially opposed and shaped to be substantially complementary to an outer contour of the blade root, and wherein the wear guard is configured to be in one installed state between the respective blade root and the axial securing element, wherein it is proposed that the side walls of the wear plate at least one of its axial ends with a respective Se That is, the end portion projecting beyond an axial end portion of the base and that adjoins the axial end portion of the base, a guide portion which is bent from the base in the direction of the axial side end portions of the side walls, in particular in the radial direction bent outward.
  • the axial securing element may comprise a first securing portion and a second securing portion, which are interconnected by a securing base, wherein the first securing portion is formed such that it forms a first stop for the Forming blade root in the axial direction, wherein the first securing portion and the securing base are interconnected by a curved portion, and wherein the guide portion is disposed in the region of the curvature portion between the blade root and the axial securing element.
  • the first securing portion and the securing base are aligned substantially orthogonal to each other, so that the curvature portion has an arc length substantially equal to ⁇ / 2 rad, wherein the arc length of the guide portion of the wear guard plate smaller than ⁇ / 2 rad and greater than or equal to ⁇ / 4 rad.
  • the second securing portion of the axial securing element may be formed such that it forms a second stop for the axial securing element on the rotor base body.
  • the axial securing element in the axial direction of installation can be inserted up to the second stop in the blade foot receptacle.
  • the first securing portion may extend radially outward and the second securing portion may extend radially inward.
  • the invention further relates to a gas turbine, in particular aircraft gas turbine with at least one rotor described above.
  • the rotor may be assigned to the compressor or the turbine, in particular a high-speed turbine or low-pressure turbine.
  • High-speed means that the turbine is coupled to the fan via a gearbox and rotates faster than the fan during operation.
  • Low pressure means that there is at least one additional turbine downstream of the combustion chamber, which is located upstream of the low-pressure turbine.
  • Fig. 1 shows in a schematic and highly simplified sectional view in the plane defined by the radial direction RR and circumferential direction UR cutting plane a blade root 10 of a blade otherwise not shown.
  • the blade root 10 is received in a blade foot receptacle 12 of a rotor 14.
  • the rotor 14 may be formed as a rotor disk and along its outer periphery a plurality of blade root receivers 12 may be formed, so that an entire blade ring for the gas turbine can be provided.
  • the blade root 10 has an outer contour 16, which is arranged in an inner contour 18 of the blade foot receptacle.
  • the outer contour 16 and the inner contour 18 are formed substantially complementary to each other.
  • the blade root 10 is inserted into the blade root receiver 12 in the axial direction AR (substantially orthogonal to the cutting plane of the Fig. 1 ) or taken out of this.
  • the axial direction AR corresponds to the direction of the rotor axis of rotation.
  • the illustrated shapes of the outer contour 16 and the inner contour 18 are purely qualitative. In particular, illustrated distances or gaps between these two contours 16, 18 can also be designed differently, for example, smaller than shown.
  • a wear apron 20 may be disposed between the blade root 10 and the blade receiving 12.
  • Fig. 1 is such a wear guard 20 indicated by a dashed line purely qualitatively. It should be noted that the dashed line is not to be understood so that the wear plate 20 is a component with interruptions. Rather, the wear guard has based on the sectional view of Fig. 1 usually an uninterrupted volume of material.
  • the wear protection plate 20 has a shape that is formed substantially complementary to the blade root 10, in particular complementary to a radially inwardly disposed portion of the blade root 10. From the schematic sectional view of Fig. 1 It can also be seen that the wear guard plate 20 is generally not formed along an entire radial height of the blade root 10.
  • Fig. 2 shows in a simplified and schematic perspective view of an embodiment of a wear protection plate 20.
  • the wear plate comprises a base 22 and two side walls 24a, 24b.
  • the base 22 and the side walls 24a, 24b may be integrally formed with each other.
  • the wear protection plate 20 may in particular be formed from a single machined, for example stamped and bent, metal piece.
  • the side walls 24a, 24b are formed or have an outer shape which is adapted to an outer contour of a blade root, not shown here. Purely schematic is in this respect again on the Fig. 1 in which the side walls 24a, 24b and the base 22 are also designated for the sake of completeness, even if the Fig. 1 not exactly the embodiment of Fig. 2 shows.
  • the base 22 extends substantially in the axial direction AR and in the circumferential direction UR.
  • the base 22 is formed as an area in the plane defined by the axial direction AR and the circumferential direction UR (or a tangential direction to the circumferential direction).
  • the base 22 does not necessarily have to be a flat surface, it may also partially or in total have a curvature, for example it may have a radially inwardly convex shape.
  • a guide portion 28 is arranged.
  • the guide portion 28 may also be formed integrally with the base 22.
  • the guide portion 28 has a bent or curved shape. The curvature is concave on the blade side facing the blade.
  • the guide section 28 is in the direction of the side walls 24a, 24b, in particular bent in the direction of the side end portions 30a, 30b. Based on an installation position on a rotor, the guide section 28 is bent radially outward.
  • the side end portions 30 a, 30 b protrude in the axial direction AR beyond the end portion 26 of the base 22.
  • Fig. 3 which shows a lateral plan view of the side wall 24b.
  • the guide portion 28 can be seen. Since the side end portions 30a, 30b protrude beyond the base 22 in the axial direction, it is possible to deform, particularly bend, the guide portion 28, which also forms a kind of free end of the base 20. From the Fig. 3 It can also be seen that the guide section 28 is provided in the embodiment only at one axial end of the wear guard plate 20. This axial end may also be referred to as insertion end 32. The opposite axial end may be referred to as a performer 34 of the wear guard plate 20.
  • Fig. 4 is an enlarged view of the guide portion 28 can be seen approximately corresponding to the in Fig. 3 marked IV area.
  • the blade foot 10 is indicated by hatching.
  • the guide portion 28 is bent so that its inner radius IR substantially corresponds to an outer radius of the blade root 10 in this area.
  • the blade root 10 rests directly on the guide section 28 of the wear protection plate 20 in the manner of a positive connection.
  • the length of the guide section 28 is in a range which is greater than or equal to 75% of the inner radius IR but smaller than the inner radius IR or equal to the inner radius IR.
  • Fig. 5 shows a sectional view of the blade root 10, which is arranged or installed in the blade foot receptacle 12 of the rotor 14. Between the blade foot 12 and the blade root 10, the wear plate 20 is arranged. Furthermore, an axial securing element 40 is shown in this example. The axial securing element 40 is arranged between the wear protection plate 20 and the blade foot receptacle 12. The axial securing element 40 may also be referred to as an axial securing plate. It comprises a first securing section 42, which is set up to serve as the first axial stop or axial contact surface for the blade root 10. The first securing portion 42 is bent radially outward.
  • the axial securing element 40 further comprises a second securing portion 44, which serves in particular to form a second axial stop on the rotor 14.
  • the second securing portion 44 is bent radially outward. It should be noted that the second securing portion 44 in the Fig. 5 is illustrated for purposes of clarity, without it being understood that the second securing portion 44 must have exactly the shape shown. Rather, other embodiments of the second securing portion 44 are conceivable.
  • the axial securing member 40 further includes a securing base 46 extending between the first securing portion 42 and the second securing portion 44, substantially along the axial direction AR.
  • the first securing portion 42 is substantially orthogonal to the securing base 46, in particular it extends substantially in the radial direction RR.
  • a transition between the first securing portion 42 and the securing base 46 is formed by a curved portion 48.
  • the curvature portion 48 has an arc length substantially equal to ⁇ / 2 rad.
  • the guide portion 28 of the wear guard plate is arranged or received.
  • the arc length of the guide section 28 of the wear protection plate 20 is less than ⁇ / 2 rad and greater than or equal to ⁇ / 4 rad.
  • the guide portion 28 is so dimensioned or bent or curved that its free end 52 does not project beyond the axial end 32 of the blade root 10. This will ensure that the Guide portion 28 of the wear plate 20 is not arranged or clamped in the region extending substantially in the radial direction RR between the first securing portion 42 and the blade root 10. Furthermore, it can be seen that the guide section 28 is dimensioned or curved or curved in such a way that a sufficient positive locking is ensured with the blade root 10 so that the wear protection plate 20, if appropriate with the blade root 10, is inserted when the blade root 10 is inserted into the blade root receptacle 12 in the axial direction until his in the Fig. 5 shown end position is moved, in particular relative to the axial securing element 40 is moved.
  • the insertion direction runs from right to left.
  • the guide section 28 therefore serves, in particular, to ensure that the wear protection plate 20 can be automatically brought into a desired or correct position relative to the blade foot receptacle 12 or the axial securing element 40 when the blade root 10 is inserted. Accordingly, it can be prevented that the position of the wear protection plate 20 after insertion of the blade root 10 must be corrected, whereby the risk of damage to the wear plate 20 can be minimized and possibly even excluded.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP18162095.6A 2017-05-03 2018-03-15 Tôle de protection d'usure pour une aube mobile d'une turbine à gaz Active EP3399151B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102017207445.0A DE102017207445A1 (de) 2017-05-03 2017-05-03 Verschleißschutzblech für eine Laufschaufel einer Gasturbine

Publications (2)

Publication Number Publication Date
EP3399151A1 true EP3399151A1 (fr) 2018-11-07
EP3399151B1 EP3399151B1 (fr) 2020-01-29

Family

ID=61683700

Family Applications (1)

Application Number Title Priority Date Filing Date
EP18162095.6A Active EP3399151B1 (fr) 2017-05-03 2018-03-15 Tôle de protection d'usure pour une aube mobile d'une turbine à gaz

Country Status (4)

Country Link
US (1) US10753213B2 (fr)
EP (1) EP3399151B1 (fr)
DE (1) DE102017207445A1 (fr)
ES (1) ES2775064T3 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
FR3136507A1 (fr) * 2022-06-13 2023-12-15 Safran Aircraft Engines Dispositif de retenue axiale des aubes mobiles d’une turbine BP dans les alvéoles d’un disque de rotor de la turbine BP et procédé de montage de ces aubes mobiles
FR3139361A1 (fr) * 2022-09-01 2024-03-08 Safran Aircraft Engines Clinquant pour aube mobile de turbomachine, ensemble pour rotor comportant un tel clinquant et procédé de montage d’un tel ensemble

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE889160C (de) * 1950-03-25 1953-09-07 Armstrong Siddeley Motors Ltd Schaufelbefestigung fuer Laeuferscheiben von Kreiselradmaschinen
US4207029A (en) * 1978-06-12 1980-06-10 Avco Corporation Turbine rotor assembly of ceramic blades to metallic disc
EP2042689A1 (fr) * 2007-09-25 2009-04-01 Snecma Clinquant pour aube de turbomachine
FR2951494A1 (fr) * 2009-10-15 2011-04-22 Snecma Clinquant pour aube de turbomachine.
WO2016059338A1 (fr) * 2014-10-13 2016-04-21 Snecma Procede d'intervention sur un rotor et clinquant associe

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6431835B1 (en) 2000-10-17 2002-08-13 Honeywell International, Inc. Fan blade compliant shim
EP2719865A1 (fr) 2012-10-12 2014-04-16 MTU Aero Engines GmbH Insert pour connexions aube-disque de turbomachines
EP2719864A1 (fr) 2012-10-12 2014-04-16 MTU Aero Engines GmbH Insert pour une connexion aube-disque pour un rotor d'une turbomachine et un rotor d'une turbomachine associé
WO2014143318A1 (fr) * 2013-03-13 2014-09-18 United Technologies Corporation Patins d'usure d'aubes et procédés de fabrication
DE102013214933A1 (de) 2013-07-30 2015-02-26 MTU Aero Engines AG Verfahren zum Montieren einer Gasturbinenschaufel in einer zugeordneten Aufnahme eines Rotorgrundkörpers
DE102013223583A1 (de) 2013-11-19 2015-05-21 MTU Aero Engines AG Schaufel-Scheiben-Verbund, Verfahren und Strömungsmaschine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE889160C (de) * 1950-03-25 1953-09-07 Armstrong Siddeley Motors Ltd Schaufelbefestigung fuer Laeuferscheiben von Kreiselradmaschinen
US4207029A (en) * 1978-06-12 1980-06-10 Avco Corporation Turbine rotor assembly of ceramic blades to metallic disc
EP2042689A1 (fr) * 2007-09-25 2009-04-01 Snecma Clinquant pour aube de turbomachine
FR2951494A1 (fr) * 2009-10-15 2011-04-22 Snecma Clinquant pour aube de turbomachine.
WO2016059338A1 (fr) * 2014-10-13 2016-04-21 Snecma Procede d'intervention sur un rotor et clinquant associe

Also Published As

Publication number Publication date
EP3399151B1 (fr) 2020-01-29
ES2775064T3 (es) 2020-07-23
US10753213B2 (en) 2020-08-25
US20180320535A1 (en) 2018-11-08
DE102017207445A1 (de) 2018-11-08

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