US20130101422A1 - Fastening assembly for blades of turbomachines having axial flow and method for producing such an assembly - Google Patents

Fastening assembly for blades of turbomachines having axial flow and method for producing such an assembly Download PDF

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Publication number
US20130101422A1
US20130101422A1 US13/696,618 US201113696618A US2013101422A1 US 20130101422 A1 US20130101422 A1 US 20130101422A1 US 201113696618 A US201113696618 A US 201113696618A US 2013101422 A1 US2013101422 A1 US 2013101422A1
Authority
US
United States
Prior art keywords
blade
underside
fastening assembly
groove
channel
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
US13/696,618
Other languages
English (en)
Inventor
Patrick Bullinger
Marco Link
Nicolas Savilius
Uwe Sieber
Hubertus Michael Wigger
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
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BULLINGER, PATRICK, SAVILIUS, NICOLAS, Link, Marco, SIEBER, UWE, Wigger, Hubertus Michael
Publication of US20130101422A1 publication Critical patent/US20130101422A1/en
Abandoned 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
    • 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
    • F01D5/3053—Fixing blades to rotors; Blade roots ; Blade spacers by means of pins
    • 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
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/90—Mounting on supporting structures or systems
    • F05B2240/94—Mounting on supporting structures or systems on a movable wheeled structure
    • 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
    • F05D2230/60—Assembly methods
    • 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
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • 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
    • F05D2230/70—Disassembly methods
    • 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
    • F05D2240/90—Mounting on supporting structures or systems
    • F05D2240/91—Mounting on supporting structures or systems on a stationary structure
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member

Definitions

  • the invention relates to a fastening assembly according and further relates to a method for producing such a fastening assembly.
  • the present invention concerns the mechanical connection of stationary or rotating blades of the flow path of a turbomachine having axial flow.
  • these blades are guide blades, which are fastened to the housing or to a corresponding guide blade support, or are moving blades, which are arranged on the rotor of the turbomachine.
  • guide blades of a blade ring are assembled in a groove running in a peripheral direction.
  • moving blades are each inserted into a respective groove running in the axial direction.
  • a resilient fastening of moving blades in a peripheral groove in the turbine rotor is known from U.S. Pat. No. 6,761,538 B2, said moving blades being pressed against the known hammer-shaped latching with the aid of a tubular spring element that is slitted both longitudinally and transversely.
  • a further type of fastening of moving blades in a compressor to a rotor disk is known from U.S. Pat. No. 2,753,149.
  • a double-headed bolt connection is provided between the base of the axial groove and the underside of the blade root. So as to nevertheless allow slight movement of the moving blade in a compressor in the retaining groove, the bolt sits in its receptacle with a small amount of play.
  • the blades tend to clatter in constructions of this type, particularly when the compressor is started, and this generates wear.
  • a fastening assembly is known from U.S. Pat. No. 4,836,749, in which a shaft made of a superelastic material is used to bias a moving blade.
  • the shaft which is intrinsically hollow, is filled with a material that melts at a low temperature and with an electric heating element. The heat generated by the current flow then leads to radial expansions of the shaft, thus generating pressure.
  • This assembly is complex, however, susceptible to failure and associated with operational costs.
  • the object of the present invention is to disclose an alternative fastening assembly for blades of turbomachines having axial flow.
  • a further object of the invention is to provide a corresponding production method.
  • the fastening assembly according to the invention for blades of turbomachines having axial flow comprises a blade support with a central axis and a lateral surface concentric therewith, in which retaining grooves distributed along the periphery and extending axially are provided, and comprises blades, of which the blade roots are inserted into these retaining grooves, wherein each retaining groove has a groove base, which is located opposite an underside of the respective blade root, and in each case has a resilient tensioning element, which is arranged between each groove base and the opposed underside and is supported in a biased manner at the respective underside and at the respective groove base, wherein, in each of the undersides of the blades, a channel is provided, in which the respective tensioning element rests flat, that is to say along its longitudinal extent.
  • a suitable channel for guidance of the tensioning element is preferably also arranged in the groove base.
  • the invention is based on the knowledge that the blade can be pressed into the retaining groove in an improved manner if a channel is provided at least in the underside of the blade root, the tensioning element resting over its entire length in said channel with a positive fit.
  • the blade is thus pressed in uniformly over the length of the latching region of the undercut, which is not the case in the closest prior art.
  • increased process quality is achieved when the blade is assembled in the retaining groove, since individual adaptation of blades is not necessary in order to press in and fix said blades.
  • the blades and the blade support are produced inclusive of all retaining grooves.
  • a blade is then inserted into its respective retaining groove.
  • the blade is then fixed temporarily in the retaining groove.
  • the two mutually opposed channels are then produced in pairs, that is to say at the same time, by means of a single drilling process.
  • the bore runs along the underside/groove base plane and cuts into the blade foot and into the blade support at a respective halfway point.
  • the tensioning element is then inserted into the bore.
  • the temporary fixing is preferably released again either before or after the insertion of the tensioning element.
  • Both channels can be produced at the same time in a relatively simple manner and without excessive effort with the aid of this first method according to the invention. Since both channels are produced in just one drilling process, a very high precision of the positioning of both channels can be assumed, which results in a particularly reliable fit of the spring element in the corresponding channels. This results in the fact that the blades can be pressed into their retaining groove against the undercuts with predefined tensioning forces, in particular over the entire length of the undercuts.
  • a second method according to the invention comprises the following steps: the blade support is first produced, but without the respective retaining grooves.
  • the blade support is then drilled, wherein the bores are each placed in such a way that merely part of the material surrounding the respective bore is removed subsequently during production of one of the retaining grooves.
  • the retaining grooves are then produced in the blade support, wherein, in each case, merely part of the material surrounding the respective bore is removed during this process, such that the rest of the material surrounding the respective bore forms the groove-base channel Blades are then inserted, each having underside channels already provided, and the tensioning element is inserted into the space defined by the mutually opposed channels.
  • This production method has the advantage that the channel arranged in the blade support can be produced beforehand in a relatively simple manner and without particular effort, in particular if the longitudinal directions of the channel and retaining groove are different.
  • both channels extend parallel to the longitudinal extension of the retaining groove.
  • the channels may extend at an incline to the longitudinal extension of the retaining groove.
  • the latter variant has the advantage that a positive fit between the blade root and the groove is produced with the aid of the tensioning element due to the mutually inclined direction of displacement of the moving blades (along the retaining groove) and the tensioning element (along the channel), and is simultaneously used to provide axial security against displacement of the blades along the retaining groove.
  • the tensioning element thus simultaneously performs the function of an axial displacement safeguard.
  • the shear forces acting from the blades onto the tensioning elements prevent said tensioning elements from being released from the channels.
  • the longitudinal extension of the retaining grooves is expediently inclined with respect to the central axis and the channels expediently extend parallel to the central axis.
  • the groove-base channel discharges into at least one of the two end faces of the blade support, which border the lateral surface.
  • the underside channel discharges into at least one of the two end faces of the blade root, which border the underside. Lateral accessibility of the channels can accordingly be assumed for assembly of the tensioning element, which is preferably designed as a tensioning pin.
  • the proposed fastening assembly can be used both for rotating and static systems.
  • the blade is formed as a moving blade with axial roots and the blade support is formed as a rotor element, wherein at least part of the radially outer lateral surface of the rotor element forms the respective lateral surface of the blade support comprising the corresponding retaining grooves.
  • each blade is formed as a guide blade with axial roots and the blade support is formed as an annular guide blade support element, wherein at least part of the radially inner lateral surface of the guide blade support forms the respective lateral surface of the blade support.
  • FIG. 1 shows the perspective view of a root of a blade for the fastening assembly according to the invention
  • FIG. 2 shows a perspective illustration of a portion of the fastening assembly according to the invention with a retaining groove and a blade fitted therein;
  • FIG. 3 shows a sectional view through a blade support of a fastening assembly
  • FIG. 4 shows a blade according to a second embodiment
  • FIG. 5 shows a blade support according to a second embodiment, suitable for receiving the blade illustrated in FIG. 4 .
  • FIG. 1 shows a perspective illustration of a blade 10 formed as a compressor blade.
  • the compressor blade comprises a blade face 12 , illustrated merely in part, to which a blade root 14 adjoins.
  • the blade root 14 has a dovetail-shaped outer contour so as to be held with a positive fit in a blade support (not illustrated in FIG. 1 ).
  • the blade root 14 has an underside 16 , in which a channel 18 is arranged.
  • the channel 18 will also be referred to hereinafter as an underside channel 18 .
  • the underside channel 18 extends over the entire longitudinal extension of the blade root 14 , such that it ends at the end faces of the blade root 14 contoured in a dovetail-shaped manner.
  • the channel 18 is U-shaped in this case, that is to say groove-shaped with a semi-circular basic contour, and is of such a depth that it can almost, but not fully, receive a tensioning element formed as a tensioning pin (not illustrated). It is thus possible, with the aid of the tensioning pin, to fasten the blade 10 in a biased manner in a retaining groove that does not have a channel at the base thereof.
  • FIG. 2 shows a perspective illustration of a blade support 20 of a fastening assembly 8 .
  • a retaining groove 22 is provided in the blade support 20 and has a contour corresponding to the blade foot 14 of the blade 10 .
  • the contour of the retaining groove 22 does not correspond to the blade root, but is different therefrom.
  • a groove-base channel 26 is provided in the base 24 of the retaining groove 22 .
  • the blade 10 illustrated in FIG. 2 differs from the blade 10 illustrated in FIG. 1 in that the channel 18 is not U-shaped, but is merely approximately semi-circular.
  • the openings of both channels 18 , 26 point toward one another. Viewed in cross section, both channels 18 , 26 form an approximately circular contour. They also always lie against one another along their longitudinal extension and are thus suitable for receiving a tensioning element 28 , which is generally formed as a tensioning pin.
  • both channels 18 , 26 extend over the entire axial extension of the retaining groove 22 , such that the tensioning element 28 can be inserted at the end face ( FIG. 3 ). It should be noted that the tensioning element 28 is only shown schematically in FIG. 3 , in which the cross section of said tensioning element is illustrated rotated through 90°.
  • the channels 18 , 26 extend transversely, that is to say at an incline, to the longitudinal extension of the retaining groove 22 .
  • the underside channel 18 now does not discharge at the end face of the blade root 14 , but at the supporting flank ( FIG. 4 ).
  • the groove-base channel 26 now does not discharge in the region of the contour of the retaining groove 22 , but outside said region, in the form of a bore opening. This is illustrated in FIG. 5 .
  • the discharge 34 of the groove-base channel 26 is outside the discharge 38 of the retaining groove 22 .
  • the longitudinal displacement of the blade 10 along the retaining groove 22 is prevented, since the tensioning element 28 rests with a positive fit in the bore or channel 26 and also engages in the underside channel 18 in the blade root 14 . Due to the different directions of displacement of the blade 10 (along the retaining groove 22 ) and of the tensioning element 28 (along the channels 18 , 26 ), the blade 10 is simultaneously secured against displacement along the retaining groove 22 with insertion of the tensioning element.
  • a fastening assembly 8 for blades 10 of turbomachines having axial flow, preferably compressors, is disclosed by the invention, said assembly comprising a blade support 20 with a lateral surface, in which retaining grooves 22 distributed along the periphery are provided and in which blades 10 are inserted, wherein a resilient tensioning element 28 is provided between each groove base 24 and the opposed underside 16 of the respective blade root 14 and is supported in a biased state at the respective groove base 24 , wherein a channel 18 , 26 , in which the tensioning element 28 rests, is provided both in the groove base 24 and in the underside 16 .

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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)
US13/696,618 2010-05-14 2011-05-11 Fastening assembly for blades of turbomachines having axial flow and method for producing such an assembly Abandoned US20130101422A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP10005079A EP2386721A1 (fr) 2010-05-14 2010-05-14 Dispositif de fixation pour pales de turbomachines pouvant s'écouler axialement et son procédé de fabrication
EP10005079.8 2010-05-14
PCT/EP2011/057628 WO2011141514A1 (fr) 2010-05-14 2011-05-11 Agencement de fixation pour aubes de turbomachines à circulation axiale et procédé de fabrication d'un tel agencement

Publications (1)

Publication Number Publication Date
US20130101422A1 true US20130101422A1 (en) 2013-04-25

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ID=43017149

Family Applications (1)

Application Number Title Priority Date Filing Date
US13/696,618 Abandoned US20130101422A1 (en) 2010-05-14 2011-05-11 Fastening assembly for blades of turbomachines having axial flow and method for producing such an assembly

Country Status (6)

Country Link
US (1) US20130101422A1 (fr)
EP (2) EP2386721A1 (fr)
JP (1) JP5596223B2 (fr)
CN (1) CN102906375A (fr)
RU (1) RU2012154199A (fr)
WO (1) WO2011141514A1 (fr)

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US20130333173A1 (en) * 2012-06-15 2013-12-19 Mitsubishi Heavy Industries, Ltd. Blade root spring insertion jig and insertion method of blade root spring
US20140072419A1 (en) * 2012-09-13 2014-03-13 Manish Joshi Rotary machines and methods of assembling
US20160040541A1 (en) * 2013-04-01 2016-02-11 United Technologies Corporation Lightweight blade for gas turbine engine
US20160348689A1 (en) * 2015-05-27 2016-12-01 United Technologies Corporation Fan blade attachment root with improved strain response
US10309240B2 (en) 2015-07-24 2019-06-04 General Electric Company Method and system for interfacing a ceramic matrix composite component to a metallic component
US11401945B2 (en) * 2020-08-19 2022-08-02 Doosan Enerbility Co., Ltd. Compressor blade assembly structure, gas turbine having same, and compressor blade assembly method
CN117145800A (zh) * 2023-09-27 2023-12-01 杭州汽轮动力集团股份有限公司 一种压气机叶片减振锁紧结构及装配方法

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FR2990462B1 (fr) * 2012-05-14 2014-05-30 Snecma Dispositif d'attache d'aubes sur un disque de rotor de turbomachine
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JP6118104B2 (ja) * 2012-12-26 2017-04-19 川崎重工業株式会社 プロペラ翼固定機構
US10287903B2 (en) * 2016-04-06 2019-05-14 General Electric Company Steam turbine drum nozzle having alignment feature, related assembly, steam turbine and storage medium
CN108050101A (zh) * 2017-12-19 2018-05-18 哈尔滨广瀚燃气轮机有限公司 一种舰船燃气轮机高压比压气机叶片连接外环
KR101950922B1 (ko) * 2018-09-06 2019-02-21 터보파워텍(주) 가스터빈용 베인조립체
CN110397625A (zh) * 2019-08-15 2019-11-01 上海电气燃气轮机有限公司 一种新型叶片锁紧装置
CN110439858B (zh) * 2019-09-09 2024-10-18 上海电气燃气轮机有限公司 一种具有减振效果的叶片锁紧结构
CN112128040B (zh) * 2020-09-23 2022-05-24 国家电网有限公司 立轴混流式水轮机上下止漏环检查工法
KR20230091604A (ko) 2021-12-16 2023-06-23 한화에어로스페이스 주식회사 보호심을 구비하는 로터 어셈블리 및 이를 포함하는 가스 터빈 엔진
US12286903B2 (en) 2023-02-24 2025-04-29 General Electric Company Turbine engine including a composite airfoil assembly having a dovetail portion
US12241383B2 (en) 2023-02-24 2025-03-04 General Electric Company Turbine engine with a composite-airfoil assembly having a dovetail portion
DE102023207197A1 (de) 2023-07-27 2025-01-30 Siemens Energy Global GmbH & Co. KG Schaufel mit vereinfachter Fußgeometrie

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RU2012154199A (ru) 2014-06-20
JP2013526667A (ja) 2013-06-24
EP2386721A1 (fr) 2011-11-16
WO2011141514A1 (fr) 2011-11-17
EP2569514A1 (fr) 2013-03-20
EP2569514B1 (fr) 2014-04-02
JP5596223B2 (ja) 2014-09-24

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