US20090060745A1 - Shim for a turbomachine blade - Google Patents

Shim for a turbomachine blade Download PDF

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Publication number
US20090060745A1
US20090060745A1 US12/171,736 US17173608A US2009060745A1 US 20090060745 A1 US20090060745 A1 US 20090060745A1 US 17173608 A US17173608 A US 17173608A US 2009060745 A1 US2009060745 A1 US 2009060745A1
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US
United States
Prior art keywords
shim
operating temperature
turbomachine
branches
layer
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.)
Abandoned
Application number
US12/171,736
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English (en)
Inventor
Charles Jean-Pierre Douguet
Christophe Jacq
Jean-Pierre Francois LOMBARD
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Assigned to SNECMA reassignment SNECMA ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: Douguet, Charles, JACQ, CHRISTOPHE, LOMBARD, JEAN-PIERRE
Publication of US20090060745A1 publication Critical patent/US20090060745A1/en
Abandoned legal-status Critical Current

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Classifications

    • 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
    • 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
    • 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
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/501—Elasticity
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/506—Hardness
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to shim for a turbomachine blade, the shim being of the type comprising two branches that are to come against the bearing surfaces of a blade root, together with a base part interconnecting the branches.
  • the shim can be used with any type of turbomachine whether terrestrial or for aviation purposes (turbojet, turboprop, terrestrial gas turbine, etc.).
  • turbomachine whether terrestrial or for aviation purposes (turbojet, turboprop, terrestrial gas turbine, etc.).
  • the shim of the invention can be used for the fan blades, or for the moving blades of the low pressure compressor (or “booster”), or for the high pressure compressor, or for the high pressure turbine, or for the low pressure turbine of the turbojet.
  • the axial direction corresponds to the direction of the axis A of the rotor of the turbomachine
  • the radial direction is a direction perpendicular to the axis A.
  • adjectives such as “inner” and “outer” are used relative to a radial direction in such a manner that the (radially) inner portion of an element is closer to the axis A than is the (radially) outer portion of the same element.
  • a rotor disk i.e. a disk secured to the rotor
  • the (moving) blades are fastened to the disk by attachment systems, which may be constituted by shank-type fasteners that may be rectilinear or curvilinear, hammerhead-shaped, or Christmas-tree-shaped.
  • attachment systems may be constituted by shank-type fasteners that may be rectilinear or curvilinear, hammerhead-shaped, or Christmas-tree-shaped.
  • Such fastener systems can be described as devices in which the blade roots form the male portions of the system and are held radially in the female portions of the system that are formed in the outer periphery of the disk and that are commonly known as “slots”.
  • the blades When the rotor is set into rotation, the blades are subjected mainly to centrifugal forces and also to axial aerodynamic forces, and the blade roots are pressed in abutment against portions of the disk lying on either side of the outer opening of each slot, under the effect of centrifugal forces.
  • the surfaces of the blade roots and of the disks that come into abutment against each other are commonly referred to as “bearing surfaces”. These bearing surfaces are subjected to pressure (as a result of said forces applied to said bearing surfaces). To a first approximation, it can be estimated that this pressure depends on the square of the speed of rotation of the rotor.
  • anti-wear solutions can be adopted, i.e. solutions that slow down the appearance of wear at the contact interfaces, and these solutions include those based on inserting a third body, referred to as “shim”, between the blade roots and the disk.
  • the shim serves in particular to double the number of contact interfaces (going from a single blade/disk interface to a pair of interfaces, blade/shim and shim/disk), and to reduce the relative movements between the parts that are in contact, thus enabling wear to be reduced in operation.
  • shim of the above-mentioned type is described in document FR 2 890 684. That shim is made entirely out of metal, and it is constituted by a sheet of metal that is folded appropriately.
  • An object of the invention is to provide a shim that is more effective than the above-mentioned known shim in terms of performing the “anti-wear” function, so as to provide better protection to the bearing surfaces of the blades and of the disk.
  • a shim for a turbomachine blade comprising two branches for coming against bearing surfaces of the blade rotor, and a base part interconnecting the branches, the shim being characterized in that it presents, at least in its branches, a multilayer structure having at least three layers that are fastened to one another and superposed in the following order: a first layer of a first material; a second layer of a second material; and a third layer of a third material that is optionally different from the first material, said first and third materials presenting respective first and third Young's moduluses of values E and E′ at any arbitrary operating temperature in the operating temperature range of the shim, and said second material presenting a second Young's modulus of value lying in the range E/20 to E/5 and in the range E′/20 to E′/5 at said operating temperature.
  • operating temperature is used to mean the temperature to which the shim is subjected while the turbomachine is in operation under normal conditions of use.
  • the relationship between said first, second, and third Young's moduluses, as defined above, needs to be satisfied for all of the temperatures in the range of operating temperatures of the shim.
  • the shim belongs to the fan or to the low pressure compressor of a bypass two-spool airplane turbojet
  • its operating temperature lies in the range 20° C. to 150° C.
  • the high pressure compressor of a bypass two-spool airplane turbojet its operating temperature lies in the range 150° C. to 500° C.
  • the high pressure turbine of a bypass two-spool airplane turbojet its operating temperature lies in the range 400° C. to 700° C.
  • the present invention thus relates to adopting said multilayer structure in which the (isotropic or anisotropic) elasticity characteristics of the second material are better than the (isotropic or anisotropic) elasticity characteristics of the first and third materials in the desired operating temperature range.
  • said first and third materials are the same or different metal alloys or organic matrix composite materials, while said second material is non-metallic.
  • the second material may be made of rubber, of silicone, of polyimide, of glass, or of epoxy resin.
  • the invention also provides a turbomachine rotor assembly comprising: a rotor disk presenting slots in its outer periphery; blades fastened via their roots in said slots; and shims according to the invention, each branch of each shim being disposed between the bearing surface of a blade root and the corresponding bearing surface of the disk.
  • the invention also provides a turbomachine including such a rotor assembly.
  • FIG. 1 is a fragmentary exploded and diagrammatic view of a turbomachine rotor assembly comprising a rotor disk, an example of shim of the invention, and a blade root;
  • FIG. 2 is a radial section view on plane II-II showing the FIG. 1 assembly once it has been assembled;
  • FIG. 3 is a section view analogous to that of FIG. 2 , showing another example of shim of the invention.
  • FIG. 4 is a section view analogous to that of FIG. 2 , showing another example of shim of the invention, placed between two adjacent slots.
  • FIGS. 1 and 2 show: a rotor disk 2 having numerous grooves or “slots” 4 in its periphery that define housings, each suitable for receiving the root 16 of a blade 14 , the root 16 being surrounded by a shim 20 .
  • the blade root 16 and the fan disk 2 are made out of titanium alloy, for example.
  • assemblies also exist (not shown) that have a spacer placed between the blade root 16 and the bottom of the slot 4 .
  • the blades 14 When the disk 2 is set into rotation, the blades 14 are subjected to centrifugal forces, and the bearing surfaces 16 A on the blade root 16 become pressed against bearing surfaces 22 A of the disk 2 .
  • the surfaces 16 A constitute the flanks of the blade root 16
  • the surfaces 22 A constitute the bottom faces of the lip-shaped portions 22 of the disk that extend on either side of the outer opening of each slot 4 .
  • the shim 20 comprises two side branches 20 A for coming against the bearing surfaces 16 A of the blade root 16 , and a base part 20 B, here a base plate, interconnecting the branches and extending under the blade root 16 .
  • the shim 20 constitutes a wear piece and its main function is to limit wear of the blade root 16 and of the fan disk 2 .
  • the shim 20 presents a multilayer structure in its branches 20 A and its base part 20 B, which structure comprises three layers 31 , 32 , 33 that adhere to one another. These three layers are superposed in the following order going from the blade root 16 towards the disk 2 : a first layer 31 of a first material; a second layer 32 of a second material; and a third layer 33 of a third material.
  • the third material is identical to the first material, so that they present the same first Young's modulus.
  • the first Young's modulus has a corresponding value E
  • said second material presents a second Young's modulus with a value lying in the range E/20 to E/5.
  • the shim 20 must present a certain amount of stiffness in order to perform its mechanical function and its anti-wear function, such that the value of E is preferably greater than or equal to 110,000 megapascals (MPa) for metal shim (e.g. 210,000 MPa for shim made of a nickel-based superalloy, of the type sold under the name “Inconel”), and greater than or equal to 70,000 MPa for shim made of organic matrix composite material.
  • MPa megapascals
  • the rotor assembly belongs to the fan or the low pressure compressor of a bypass two-spool airplane turbojet, it is subjected to operating temperatures lying in the range 20° C. to 150° C.
  • the first material can be selected as a Ni-based superalloy with more than 15% by weight Fe and Cr, such as the superalloy sold under the name “Inconel 718”; while the second material can be rubber (natural or synthetic).
  • the first material it is also possible for the first material to be a composite material using an epoxy resin matrix with reinforcing fibers, e.g. made of carbon; the second material could then be an epoxy resin on its own (with the difference in Young's modulus between the first and second materials being associated with the absence of fibers).
  • the assembly belongs to the high pressure compressor of a bypass two-spool airplane turbojet, it is subjected to operating temperatures lying in the range 150° C. to 500° C. Under such circumstances, and by way of example, it is possible to select for the first material a Ni-based superalloy having more than 15% by weight of Fe and Cr, such as the superalloy sold under the name “Inconel 718”; the second material could be a silicone or polyimide.
  • the assembly belongs to the high pressure turbine of a bypass two-spool airplane turbojet, it is subjected to operating temperatures lying in the range 400° C. to 700° C.
  • the first material to be selected as an Ni-based superalloy with more than 15% by weight Fe and Cr, such as the superalloy sold under the name “Inconel 718”; the second material may be glass (which in this operating temperature range presents viscoelastic behavior).
  • said layers 31 , 32 , 33 can be fastened to one another in various ways, and in particular:
  • Said layers may be integral with one another to form said multilayer structure, and the fastening that is obtained must naturally be sufficiently secure to prevent the structure becoming delaminated in operation and to prevent the layer 32 from creeping.
  • FIG. 3 is a section view analogous to that of FIG. 2 showing another element of a shim 120 of the invention. Elements or element portions that are analogous between FIGS. 2 and 3 are identified by the same reference numerals plus 100 .
  • FIG. 3 differs from that of FIG. 2 in that the base part 120 B of the shim 120 is formed by the first and second layers 131 and 133 joined to each other. Only the branches 120 A of the shim present a multilayer structure made up of the first, second, and third layers 131 , 132 , and 133 of the invention. It should be observed that the base part 120 B of the shim could also be formed solely by the third layer 133 , or indeed solely by the first layer 131 .
  • FIG. 4 is a section view analogous to that of FIG. 2 showing another example of a shim 220 of the invention. Elements or element portions analogous between FIGS. 2 and 4 are identified with the same numerical references plus 200 .
  • FIG. 4 differs from that of FIG. 2 in that the base part 220 B of the shim 220 extends over the outer periphery of the rotor disk 202 between two adjacent slots 204 , with each branch 220 A of the shim penetrating into a slot 204 and being housed between the bearing surface 216 A of the blade root 216 and the corresponding bearing surface 222 A of the disk 202 .
  • the shim 220 presents a multilayer structure analogous to that of the shim 20 in FIG. 2 , having three layers 231 , 232 , 233 that are fastened to one another and superposed.

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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)
  • Gasket Seals (AREA)
  • Laminated Bodies (AREA)
US12/171,736 2007-07-13 2008-07-11 Shim for a turbomachine blade Abandoned US20090060745A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0756466A FR2918702B1 (fr) 2007-07-13 2007-07-13 Clinquant pour aube de turbomachine
FR0756466 2007-07-13

Publications (1)

Publication Number Publication Date
US20090060745A1 true US20090060745A1 (en) 2009-03-05

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ID=39166321

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Application Number Title Priority Date Filing Date
US12/171,736 Abandoned US20090060745A1 (en) 2007-07-13 2008-07-11 Shim for a turbomachine blade

Country Status (10)

Country Link
US (1) US20090060745A1 (ru)
EP (1) EP2014873B1 (ru)
JP (1) JP2009019629A (ru)
CN (1) CN101344015A (ru)
CA (1) CA2636922A1 (ru)
DE (1) DE602008002486D1 (ru)
ES (1) ES2352583T3 (ru)
FR (1) FR2918702B1 (ru)
RU (1) RU2472945C2 (ru)
UA (1) UA96589C2 (ru)

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WO2010125089A1 (fr) * 2009-04-29 2010-11-04 Snecma Cale d'aube de soufflante renforcee
US20110033302A1 (en) * 2009-08-05 2011-02-10 Ventura Peter D Fan blade dovetail with compliant layer
US20110206530A1 (en) * 2008-08-06 2011-08-25 Snecma Vibration damper device for turbomachine blade attachments, associated turbomachine and associated engines
US20120263596A1 (en) * 2011-04-14 2012-10-18 Rolls-Royce Plc Annulus filler system
US8398298B2 (en) * 2010-12-14 2013-03-19 William H. Swader Automatic pot stirrer
GB2506225A (en) * 2012-06-04 2014-03-26 Snecma Turbine wheel and associated turbine engine
WO2014100193A1 (en) * 2012-12-18 2014-06-26 United Technologies Corporation Rotor blade root spacer with a fracture feature
WO2014143318A1 (en) 2013-03-13 2014-09-18 United Technologies Corporation Blade wear pads and manufacture methods
US20140294597A1 (en) * 2011-10-10 2014-10-02 Snecma Cooling for the retaining dovetail of a turbomachine blade
US20140341739A1 (en) * 2013-05-17 2014-11-20 Snecma Propeller blade pivot
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US20150192144A1 (en) * 2014-01-08 2015-07-09 United Technologies Corporation Fan Assembly With Fan Blade Under-Root Spacer
US20150322796A1 (en) * 2012-09-03 2015-11-12 Snecma Turbine rotor for a turbomachine
GB2528759A (en) * 2014-06-24 2016-02-03 Rolls Royce Plc Rotor blade manufacture
US20160237835A1 (en) * 2013-10-11 2016-08-18 United Technologies Corporation Compressible fan blade with root spacer
US9422819B2 (en) 2012-12-18 2016-08-23 United Technologies Corporation Rotor blade root spacer for arranging between a rotor disk and a root of a rotor blade
EP3075958A1 (en) * 2015-03-30 2016-10-05 United Technologies Corporation Fan blade and method of covering a fan blade root portion
US9506356B2 (en) 2013-03-15 2016-11-29 Rolls-Royce North American Technologies, Inc. Composite retention feature
US20170107999A1 (en) * 2015-10-19 2017-04-20 Rolls-Royce Corporation Rotating structure and a method of producing the rotating structure
US9745856B2 (en) 2013-03-13 2017-08-29 Rolls-Royce Corporation Platform for ceramic matrix composite turbine blades
US10047614B2 (en) * 2014-10-09 2018-08-14 Rolls-Royce Corporation Coating system including alternating layers of amorphous silica and amorphous silicon nitride
WO2019083595A1 (en) * 2017-10-24 2019-05-02 General Electric Company CONNECTING ASSEMBLIES BETWEEN TURBINE ROTOR BLADES AND ROTOR WHEELS
US10577961B2 (en) 2018-04-23 2020-03-03 Rolls-Royce High Temperature Composites Inc. Turbine disk with blade supported platforms
US10767498B2 (en) 2018-04-03 2020-09-08 Rolls-Royce High Temperature Composites Inc. Turbine disk with pinned platforms
US10890081B2 (en) 2018-04-23 2021-01-12 Rolls-Royce Corporation Turbine disk with platforms coupled to disk
CN113833691A (zh) * 2020-06-08 2021-12-24 中国航发商用航空发动机有限责任公司 一种风扇组件及涡轮风扇发动机
US11346363B2 (en) 2018-04-30 2022-05-31 Raytheon Technologies Corporation Composite airfoil for gas turbine
US11555407B2 (en) 2020-05-19 2023-01-17 General Electric Company Turbomachine rotor assembly
EP4202187A1 (en) * 2021-12-23 2023-06-28 Rolls-Royce plc Bladed disc for a rotating machine, gas turbine engine and method of reducing the low-cycle fatigue of a blade within a bladed gas turbine engine

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JP5725849B2 (ja) * 2010-12-27 2015-05-27 三菱日立パワーシステムズ株式会社 固定治具
JP6085096B2 (ja) * 2012-04-05 2017-02-22 三菱日立パワーシステムズ株式会社 燃料ガス圧縮機の動翼取り外し方法
EP3059033A4 (en) * 2013-10-15 2017-06-21 IHI Corporation Method for bonding metal powder injection molded bodies
US9970297B2 (en) * 2014-08-29 2018-05-15 Rolls-Royce Corporation Composite fan slider with nano-coating
KR102142141B1 (ko) * 2018-08-17 2020-08-06 두산중공업 주식회사 터빈, 가스 터빈, 및 터빈 블레이드 분리 방법
FR3093533B1 (fr) 2019-03-06 2022-04-15 Safran Aircraft Engines dispositif d’amortissement pour rotor de turbomachine
FR3139363A1 (fr) * 2022-09-01 2024-03-08 Safran Aircraft Engines Clinquant pour disque de turbine de turbomachine, ensemble pour rotor comportant un tel clinquant et procédé de montage d’un tel ensemble

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US2874932A (en) * 1952-02-25 1959-02-24 Maschf Augsburg Nuernberg Ag Steel turbine rotors with ceramic blades
US5087174A (en) * 1990-01-22 1992-02-11 Westinghouse Electric Corp. Temperature activated expanding mineral shim
US5160243A (en) * 1991-01-15 1992-11-03 General Electric Company Turbine blade wear protection system with multilayer shim
US5240375A (en) * 1992-01-10 1993-08-31 General Electric Company Wear protection system for turbine engine rotor and blade
US5365545A (en) * 1992-04-24 1994-11-15 Universal Data Systems, Inc. MODEM-channel bank converter
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US6290466B1 (en) * 1999-09-17 2001-09-18 General Electric Company Composite blade root attachment
US20020044870A1 (en) * 2000-10-17 2002-04-18 Honeywell International, Inc. Fan blade compliant layer and seal
US6832896B1 (en) * 2001-10-24 2004-12-21 Snecma Moteurs Blade platforms for a rotor assembly
US20040151590A1 (en) * 2003-01-31 2004-08-05 Forrester James Michael Snap on blade shim

Cited By (52)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110206530A1 (en) * 2008-08-06 2011-08-25 Snecma Vibration damper device for turbomachine blade attachments, associated turbomachine and associated engines
US8801385B2 (en) * 2008-08-06 2014-08-12 Snecma Vibration damper device for turbomachine blade attachments, associated turbomachine and associated engines
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DE602008002486D1 (de) 2010-10-28
CA2636922A1 (fr) 2009-01-13
RU2472945C2 (ru) 2013-01-20
EP2014873A1 (fr) 2009-01-14
FR2918702B1 (fr) 2009-10-16
EP2014873B1 (fr) 2010-09-15
UA96589C2 (ru) 2011-11-25
JP2009019629A (ja) 2009-01-29
RU2008128378A (ru) 2010-01-20
FR2918702A1 (fr) 2009-01-16
ES2352583T3 (es) 2011-02-21
CN101344015A (zh) 2009-01-14

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