US3567337A - Rotor for turboengines - Google Patents

Rotor for turboengines Download PDF

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Publication number
US3567337A
US3567337A US779374A US3567337DA US3567337A US 3567337 A US3567337 A US 3567337A US 779374 A US779374 A US 779374A US 3567337D A US3567337D A US 3567337DA US 3567337 A US3567337 A US 3567337A
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US
United States
Prior art keywords
slot
blades
rotor
blade
foot
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.)
Expired - Lifetime
Application number
US779374A
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English (en)
Inventor
Ferdinand Zerlauth Herb Flegel
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.)
Sulzer AG
Original Assignee
Sulzer 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 Sulzer AG filed Critical Sulzer AG
Application granted granted Critical
Publication of US3567337A publication Critical patent/US3567337A/en
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • 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
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides

Definitions

  • This invention relates to a rotor for turboengines.
  • the rotors of turboengines require significant strength properties, that is, as far as mechanical and thermal properties are concerned.
  • additional stresses are superimposed on the rotors due to an expansion differential resulting from temperature differences particularly upon starting and stopping of the rotors.
  • Such superimposed stresses can, however, reach the admissible limit at unfavorable points and occasionally exceed the admissible limit.
  • the alternating thermal stress and vibration stress which are likely to be added thereon can rapidly result in fatigue phenomena as has been repeatedly confirmed by blade ruptures.
  • the rotors and especially the blades require a high degree of precision during manufacture. For example, not only must the profiles be complied With exactly but also must be set in proper position in order to assure a flow with minimum losses. Accordingly, the corinection of the blades with the rotor is subjected to maximum stress.
  • the blades have had feet which have been form-locked upon insertion in slots of a rotor.
  • the foot of such blades has been shaped substantially like a hammer head or, as in other instances, with tuber heads, pine cones or other configurations with wave-shaped slots.
  • considerable demands have been made on the precision of the blade profiles as well as the slot profiles.
  • the insertion of the blades through one fitting site extending over a part of the slot circumference has caused considerable work.
  • the recesses required for the formation of the fitting site has weakened the rotor body.
  • the invention provides a rotor which is manufactured with a continuous slot having surfaces disposed coaxially of the rotor axis to receive a plurality of blades.
  • the surfaces of the slot include at least one lateral surface which is sloped so as to engage the blades in opposition to the centrifugal force exerted on the blades.
  • the blades are further provided with feet which are dimensioned relative to the slot so as to permit insertion of a blade foot into the slot when positioned in one direction and to allow locking of the blade foot in the slot when rotated
  • a spring foot is placed in the slot below each blade to bias the blade outwardly of the slot against the sloped surface of the slot. Further, the blades are spaced apart within the slot by the use of individual spacers.
  • the shape of the blade feet is such as to allow insertion of all the blades and respective spring mounted feet as well as most of the spacers into the rotor slot without the need of recesses in the slot while also permitting displacement of the blade feet with sufiicient clearance at their respective sites in the rotor circumference. Since only a few open spaces exist between some of the blades which are uniformly distributed about the rotor, an intermediary locking layer is used to fill up these remaining spaces after all the blades have been positioned. As these intermediary locking layers are subjected to loading to a much less extent than the circumference of the rotor body or blade feet, where formed multi-sectionally in order to form a closure, there is no danger such as that frequently arising at the closing points of the rotor.
  • FIG. 1 illustrates a view taken on line II of 'FIG. 4 of a blade abutted against the slot of a rotor according to the invention
  • FIG. 2 illustrates a view taken on line IIII of FIG. 4 of a spacer within the rotor slot according to the invention
  • FIG. 3 illustrates a view taken on line IIIIII of FIG. 4 of an intermediary locking layer according to the invention
  • FIG. 4 illustrates a fragmentary plan view of a rotor according to the invention.
  • FIG. 5 illustrates a view taken on line VV of FIG. 4.
  • the rotor has a rotor body 1 which receives a plurality of blades 2 in a circumferential slot 3 having two symmetrically disposed tapered lateral surfaces 4, 5 and a flat base surface 6; the surfaces 4, 5, 6 of the slot 3 being disposed on axes coincident to the rotor axis.
  • the slot surfaces 4, 5, 6 are uninterrupted by recesses throughout their circumference so as to prevent the tension stresses in the rotor from reaching peak values at any point. Thus, a uniform tension stress pattern is obtained along the slot surfaces which is readily controlled by appropriate shaping of the rotor body and blade feet.
  • the blades 2 are dimensioned to seat against contact strips on the tapered surfaces 4, of the slot 3 by means ofcounterfitting surfaces 7, 8. Thus, the centrifugal force of each blade 2 is transmitted to the rotor body 1 at these contact strips while the blades 2 are held in equilibrium by the rotor body 1. 7
  • the mouth of the slot 3 and the length 1 of the blade foot with respect to the periphery of the rotor are so dimensioned as to allow insertion of the blade foot into the slot 3 when turned 90 with respect to the final blade position in the slot 3. Further, the depth 1 of the slot 3 and the slope of the surfaces 7, 8 of the blade foot are such that the maximum diagonal d of the blade foot remains smaller than the Width of the slot base surface 6.
  • the blade 2 in order to insert a blade 2 in the slot 3, the blade 2 is inserted into the slot 3 in a position as shown in dotted line in FIG. 2 approximately perpendicular to the final position in the slot 3. Next, the blade 2 is rotated 90 about its axis into the position shown in FIG. 1. Thereafter, the blade 2 is lifted to engage the lateral surfaces 4, 5 of the slot 3.
  • spacer layers 9 are disposed between each pair of adjacent blades 2.
  • the spacers 9 which are disposed in a major part of the rotor circumference consist of individual plates 10 which are inserted in identical manner to the blades longitudinally into the blade slot down to the base surface 6 and then turned against the side faces of the blade feet.
  • the shape of these plates 10 completely fills out the space of the complete profile of the slot 3 so that the plates 10 are held captive in position, practically without any clearance, by the lateral surfaces 4, 5 and the slot base surface 6.
  • each spring foot 11 is arranged beneath each blade 2 within a spring groove 12.
  • Each spring foot 11 consists of a prismatic foot element 13, for example, of rectangular or square cross section, which has a bore in which a cup spring 14 carrying a pressure plate 15 is mounted. Following insertion of a blade 2 into operative position, a spring foot 11 is pushed as an assembly into the spring groove 12 beneath the blade foot so that, even at stoppage and without the effect of centrifugal forces,
  • the length of the spring foot 11 is selected in such a manner as to be held with a slight clearance by the spacer layers 9 at either side of the blade supported by the spring foot 11 (FIG. 5).
  • intermediary layers are radially inserted individually into the spaces between the already inserted blades so as to act as a closure or lock.
  • These intermediary layers substantially comprise two shaped plates 16, 17 of substantially identical configuration of which each one bears with one shaped edge 18 on a repsective contact strip 4, 5 of the slot and with one shaped edge 19- on the slot base surface 6.
  • the intermediary layers also have a compartment between the inner edges 20 of two adjoining shaped plates 16, 17, defined by parallel walls. This compartment 21 is filled by two hook-shaped locking elements 22, 23 and a filler 24 between the locking elements.
  • Each of the locking elements 22, 23 has the lower hooked end disposed in the groove 12 under a respective plate 16, 17 so that owing to the inserting of the filler 24, the two locking elements 22, 23 are held against the shaped elements 16, 17 with a sufi'icient force to prevent removal.
  • the longer locking element 2 is bent over the filler 24 so that the intermediary layer is secured against falling out.
  • a rotor for a turboengine comprising:
  • a rotor body having a peripheral circumferential slot of smooth uninterrupted surfaces therein, said slot having a pair of lateral surfaces sloped toward the the interior of said slot and a a base surface;
  • each blade having a blade foot engaging said lateral surfaces of said slot to transfer the centrifugal force exerted on said blade to said lateral surface and being spaced from said base surface, each blade foot being dimensioned to pass radially into and out of said slot in a position transverse to the mounted position of said blade foot in said slot and to be rotated within said slot into said mounted position;
  • each said blade foot has an outer dimension less than the mouth of said slot and a diagonal length less than the Width of the base of said slot.
  • each said lateral surface includes at least one contact strip thereon abutting said blades.
  • said spacing means includes a plurality of fiat plates having profiled edges fitting against the surfaces of said slot.
  • a rotor for a turboengine comprising:
  • a rotor body having a circumferential slot of smooth uninterrupted surfaces therein, said slot having at least one lateral surface sloped toward the interior of said slot;
  • each blade having a blade foot engaging said lateral surface of said locking elements having an end bent over said said slot to transfer the centrifugal force exerted on filler to lock said filler in said compartment.
  • said blade to said lateral surface, each blade foot being dimensioned to pass into and out of said slot in a References Cited position transverse to the mounting position of said 5 UNIT D STAT S PAT S blade P slot; 2,595,829 5/1952 Dean 253-77(C-2)UX spring means in said slot biasing each said blade agalnst 3 216 700 11/1965 Bostock said lateral surface of said slot; and spacing means in said slot between each pair of adjacent F REI N PATENTS blades, said spacing means including at least one in- 10 1,634,439 4/1953 France 416 215 termediary locking layer of multi-sectional compo- 59 592 10 1951 Great Britain nents of a Width less than the width of said slot, said 7 0 334 11

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)
  • Centrifugal Separators (AREA)
US779374A 1968-07-26 1968-11-27 Rotor for turboengines Expired - Lifetime US3567337A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH1127568A CH494341A (de) 1968-07-26 1968-07-26 Rotor für Turbomaschinen

Publications (1)

Publication Number Publication Date
US3567337A true US3567337A (en) 1971-03-02

Family

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Application Number Title Priority Date Filing Date
US779374A Expired - Lifetime US3567337A (en) 1968-07-26 1968-11-27 Rotor for turboengines

Country Status (8)

Country Link
US (1) US3567337A (https=)
JP (1) JPS4924485B1 (https=)
BE (1) BE736540A (https=)
CH (1) CH494341A (https=)
DE (1) DE1751819B1 (https=)
FR (1) FR2013754A1 (https=)
GB (1) GB1274547A (https=)
NL (1) NL6811392A (https=)

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3954350A (en) * 1974-06-14 1976-05-04 Motoren-Und Turbinen-Union Munchen Gmbh Rotor having means for locking rotor blades to rotor disk
US3955898A (en) * 1974-08-13 1976-05-11 Motoren- Und Turbinen-Union Munchen Gmbh Locking device for the rotor blades of a flow machine
US3986779A (en) * 1974-05-27 1976-10-19 Brown Boveri-Sulzer Turbomaschinen Aktiengesellschaft Locking device for releasably fastening parts to rotors of fluid flow machines
US4500255A (en) * 1981-04-24 1985-02-19 United States Of America As Represented By The Secretary Of The Air Force Spacer structure
US4820127A (en) * 1988-01-29 1989-04-11 Westinghouse Electric Corp. Blade support and blade assembly
US5090198A (en) * 1990-05-04 1992-02-25 Rolls-Royce Inc. & Rolls-Royce Plc Mounting assembly
US5100292A (en) * 1990-03-19 1992-03-31 General Electric Company Gas turbine engine blade
US20040037703A1 (en) * 2001-12-21 2004-02-26 Paolo Arinci System for connecting and locking rotor blades of an axial compressor
US20050265846A1 (en) * 2004-06-01 2005-12-01 Przytulski James C Balance assembly for rotary turbine component and method for installing and/or adjusting balance weight
US20070280831A1 (en) * 2006-06-05 2007-12-06 United Technologies Corporation Rotor disk and blade arrangement
CN101550936A (zh) * 2008-04-04 2009-10-07 通用电气公司 压缩机叶片的轴向保持
DE102010053141A1 (de) 2009-12-07 2011-06-09 Alstom Technology Ltd. Turbinenaggregat
US20140199172A1 (en) * 2013-01-11 2014-07-17 General Electric Company Turbomachine and method of handling turbomachine components
US20150118055A1 (en) * 2013-10-31 2015-04-30 General Electric Company Gas turbine engine rotor assembly and method of assembling the same
US20150139808A1 (en) * 2013-11-19 2015-05-21 MTU Aero Engines AG Rotor of a turbomachine
US10145382B2 (en) 2015-12-30 2018-12-04 General Electric Company Method and system for separable blade platform retention clip
CN115822730A (zh) * 2022-12-08 2023-03-21 杭州中能汽轮动力有限公司 一种汽轮机叶轮结构及其设计安装方法
RU230892U1 (ru) * 2024-09-09 2024-12-24 Акционерное общество "Объединенная двигателестроительная корпорация" (АО "ОДК") Устройство фиксации лопаток рабочего колеса компрессора газотурбинного двигателя

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2119026B (en) * 1981-03-25 1984-06-20 Rolls Royce Aerofoil blade mounting
GB2156908A (en) * 1984-03-30 1985-10-16 Rolls Royce Bladed rotor assembly for gas turbine engine
EP1130217B1 (de) * 2000-03-01 2005-05-18 ALSTOM Technology Ltd Befestigung von Laufschaufeln in einer Turbomaschine
DE10120532A1 (de) * 2001-04-26 2002-10-31 Alstom Switzerland Ltd Vorrichtung und Verfahren zur Befestigung einer Laufschaufel längs einer innerhalb eines Rotors einer axial durchströmten Turbomaschine verlaufenden Umfangsnut
US6761538B2 (en) * 2002-10-31 2004-07-13 General Electric Company Continual radial loading device for steam turbine reaction type buckets and related method
EP1698758B1 (de) * 2005-02-23 2015-11-11 Alstom Technology Ltd Axial getrennter Rotor-Schluss
FR2897099B1 (fr) * 2006-02-08 2012-08-17 Snecma Roue de rotor de turbomachine
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
KR101884712B1 (ko) * 2016-12-21 2018-08-03 두산중공업 주식회사 로터 블레이드용 로킹 스페이서
KR101920070B1 (ko) * 2016-12-23 2018-11-19 두산중공업 주식회사 로터 블레이드용 로킹 스페이서

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH349624A (de) * 1957-03-05 1960-10-31 Oerlikon Maschf Axiale Strömungsmaschine
DE1269137B (de) * 1960-01-07 1968-05-30 Prvni Brnenska Strojirna Turbomaschinenlaeufer
NL123379C (https=) * 1963-11-01

Cited By (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3986779A (en) * 1974-05-27 1976-10-19 Brown Boveri-Sulzer Turbomaschinen Aktiengesellschaft Locking device for releasably fastening parts to rotors of fluid flow machines
US3954350A (en) * 1974-06-14 1976-05-04 Motoren-Und Turbinen-Union Munchen Gmbh Rotor having means for locking rotor blades to rotor disk
US3955898A (en) * 1974-08-13 1976-05-11 Motoren- Und Turbinen-Union Munchen Gmbh Locking device for the rotor blades of a flow machine
US4500255A (en) * 1981-04-24 1985-02-19 United States Of America As Represented By The Secretary Of The Air Force Spacer structure
JP2879794B2 (ja) 1988-01-29 1999-04-05 ウエスチングハウス・エレクトリック・コーポレーション ブレード支持体・ブレード組立体
US4820127A (en) * 1988-01-29 1989-04-11 Westinghouse Electric Corp. Blade support and blade assembly
JPH01224402A (ja) * 1988-01-29 1989-09-07 Westinghouse Electric Corp <We> ブレード支持体・ブレード組立体
US5100292A (en) * 1990-03-19 1992-03-31 General Electric Company Gas turbine engine blade
US5090198A (en) * 1990-05-04 1992-02-25 Rolls-Royce Inc. & Rolls-Royce Plc Mounting assembly
US20040037703A1 (en) * 2001-12-21 2004-02-26 Paolo Arinci System for connecting and locking rotor blades of an axial compressor
US6981847B2 (en) * 2001-12-21 2006-01-03 Nuovo Pignone Holding S.P.A. System for connecting and locking rotor blades of an axial compressor
US20050265846A1 (en) * 2004-06-01 2005-12-01 Przytulski James C Balance assembly for rotary turbine component and method for installing and/or adjusting balance weight
US20070280831A1 (en) * 2006-06-05 2007-12-06 United Technologies Corporation Rotor disk and blade arrangement
US8608446B2 (en) 2006-06-05 2013-12-17 United Technologies Corporation Rotor disk and blade arrangement
EP1865153A3 (en) * 2006-06-05 2011-01-12 United Technologies Corporation Rotor disk and blade arrangement and method of assembly thereof
US20090252611A1 (en) * 2008-04-04 2009-10-08 General Electric Company, Axial compressor blade retention
CN101550936B (zh) * 2008-04-04 2013-11-20 通用电气公司 压缩机叶片的轴向保持
CN101550936A (zh) * 2008-04-04 2009-10-07 通用电气公司 压缩机叶片的轴向保持
US8267664B2 (en) * 2008-04-04 2012-09-18 General Electric Company Axial compressor blade retention
US8851852B2 (en) 2009-12-07 2014-10-07 Alstom Technology Ltd. Turbine assembly
US20110200441A1 (en) * 2009-12-07 2011-08-18 David Paul Blatchford Turbine assembly
DE102010053141A1 (de) 2009-12-07 2011-06-09 Alstom Technology Ltd. Turbinenaggregat
DE102010053141B4 (de) 2009-12-07 2018-10-11 General Electric Technology Gmbh Turbinenaggregat mit möglicher Überdrehung des Fußes einer Schaufel bis zum Einbau einer letzten Schaufel
US20140199172A1 (en) * 2013-01-11 2014-07-17 General Electric Company Turbomachine and method of handling turbomachine components
US20150118055A1 (en) * 2013-10-31 2015-04-30 General Electric Company Gas turbine engine rotor assembly and method of assembling the same
US9896946B2 (en) * 2013-10-31 2018-02-20 General Electric Company Gas turbine engine rotor assembly and method of assembling the same
US20150139808A1 (en) * 2013-11-19 2015-05-21 MTU Aero Engines AG Rotor of a turbomachine
US10066493B2 (en) * 2013-11-19 2018-09-04 MTU Aero Engines AG Rotor of a turbomachine
US10145382B2 (en) 2015-12-30 2018-12-04 General Electric Company Method and system for separable blade platform retention clip
CN115822730A (zh) * 2022-12-08 2023-03-21 杭州中能汽轮动力有限公司 一种汽轮机叶轮结构及其设计安装方法
RU230892U1 (ru) * 2024-09-09 2024-12-24 Акционерное общество "Объединенная двигателестроительная корпорация" (АО "ОДК") Устройство фиксации лопаток рабочего колеса компрессора газотурбинного двигателя

Also Published As

Publication number Publication date
JPS4924485B1 (https=) 1974-06-24
NL6811392A (https=) 1970-01-29
DE1751819B1 (de) 1971-01-21
CH494341A (de) 1970-07-31
GB1274547A (en) 1972-05-17
BE736540A (https=) 1970-01-26
FR2013754A1 (https=) 1970-04-10

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