EP0202531B1 - Bindung von Laufschaufeln einer thermischen Turbomaschine - Google Patents

Bindung von Laufschaufeln einer thermischen Turbomaschine Download PDF

Info

Publication number
EP0202531B1
EP0202531B1 EP86106150A EP86106150A EP0202531B1 EP 0202531 B1 EP0202531 B1 EP 0202531B1 EP 86106150 A EP86106150 A EP 86106150A EP 86106150 A EP86106150 A EP 86106150A EP 0202531 B1 EP0202531 B1 EP 0202531B1
Authority
EP
European Patent Office
Prior art keywords
blades
button
tying
conical
blade
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
Application number
EP86106150A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0202531A1 (de
Inventor
Hans-Joachim Herrmann
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.)
MAN Gutehoffnungshutte GmbH
Original Assignee
MAN Gutehoffnungshutte GmbH
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 MAN Gutehoffnungshutte GmbH filed Critical MAN Gutehoffnungshutte GmbH
Publication of EP0202531A1 publication Critical patent/EP0202531A1/de
Application granted granted Critical
Publication of EP0202531B1 publication Critical patent/EP0202531B1/de
Expired legal-status Critical Current

Links

Images

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
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations

Definitions

  • the invention relates to a binding of rotor blades of a thermal turbomachine by means of extensions which extend in the circumferential direction and are rigidly connected in pairs to the associated rotor blade and which are supported at least during operation of the turbine or the compressor via flat contact surfaces.
  • the natural frequency is increased by such a binding of the rotor blades on the circumference in the upper part of the blades; in addition, the excitability of a bound blade ring is significantly lower.
  • Known bindings of the rotor blades or rotor blade groups of steam turbines and compressors are cover plates which have a certain excess in the circumferential direction, as a result of which a tangential preload is created between the cover plates when the blades are installed, or arcuate elements, so-called arcades, in the form of pairs on the rotor blade attached steel arches, the V-shaped ends of two adjacent steel arches intermeshing and under pressure in the circumferential direction, or supporting wings, d. H. in the circumferential direction extending lugs on the blades with a streamlined profile. - Shifts between these circumferentially braced binding elements - z. B.
  • the invention has for its object to provide a binding of the type mentioned, which ensures for all operating areas of the machine and for a sufficient time a defined, independent of manufacture, material and operating behavior, flat contact between the binding elements.
  • the constancy of the frictional relationships between the binding elements should be ensured in order to protect individual tunnels from being overstressed as a result of instability and evasion processes and to minimize fretting wear.
  • one or both contact surfaces per adjacent pair of lugs are formed by the one or more flat end faces of one or two pressure bodies each having a conical seat, that each pressure body in a neck recess with a conical seat, the The inclination is steeper than the inclination of the pressure body seat, is mounted such that it can be tilted, and that each pressure body receives its final placement and bedding as a result of the moment F T contact m, as well as the F T hurling, and the bending moment F T.
  • e transmits self-locking, where F T is the circumferential force component and e is the eccentric position or m is the distance from the pressure body edge to the pressure body axis of symmetry.
  • the conical seat of the pressure body enables the rotary movement required for parallel adjustment to the support surface through the angle difference ⁇ , as well as the notch-free introduction of moments and pressures, also from the centrifugal force, which ensures the fatigue strength of the connection.
  • the pressure bodies receive their final placement and bedding with an approximately uniform surface pressure distribution over the contact surface by local flow of the pressure body seat up to the annular support in the seat of the projections; Since the conical section, which deviates from the ideal ring surface, becomes force-fit and form-fitting due to the unique plasticization and elastic bedding, self-locking bending moments from the coupling vibration can be transmitted to a large extent from the pressure bodies under pressure due to the ratio e / p. - Due to the loose attachment of the pressure body, their interchangeability is relatively easy and independent of location, so that there is also interchangeability in the power plant.
  • each pressure body is beveled conically at the front end.
  • each pressure element has a cylindrical section between its conical seat and its front part, and that pressure elements with different heights of the cylindrical section are used.
  • the pressure bodies In order to be able to fasten the pressure bodies in the binding elements by loose caulking, the pressure bodies each have a conical section between the cylindrical section and the conical front part in particular.
  • the pressure bodies consist of a material with little differences between static and sliding friction, little or no porosity, high pressure and bending strength, high corrosion resistance and - if necessary - high abrasion resistance.
  • the manufacture of the pressure hull with a relatively free choice of material, an optimal selection of sliding partners with the desired constant friction coefficient as possible, i. H. Sliding partner with slight differences between static and sliding friction, without seizing and taking corrosion protection into account, whereby the binding function, and thus the desired vibration behavior, is ensured.
  • defined contact relationships between the binding elements are ensured for the desired, relatively long time, so that the binding according to the invention can be used especially in steam turbines and compressors, that is to say machines with a long service life.
  • each front, cylindrical wall part in the associated attachment has a corresponding opening at the bottom and / or top.
  • each pressure body is cut off laterally symmetrically to its longitudinal median plane, such that the distance between the straight side surfaces is slightly less than the width of the opening or openings in the extension wall part.
  • the twisted, radially mountable rotor blades are numbered 1, to which two steel lugs 2, each pointing in the circumferential direction, are rigidly fastened - one lug each on different sides of the airfoils.
  • the lugs 2 are preferably an integral part of the associated moving blade.
  • the approaches 2 are shown in the example shown as a support wing with a streamlined profile 3; but they can also be cover plates or other binding elements.
  • the free ends of the lugs 2 have flat, sloping surfaces; the plane through this surface - seen in plan view - is rotated by such an angle with respect to the circumferential direction that the previously mentioned displacement movements between the later-mentioned contact surfaces 6e are possible, and the blades are not prevented from rotating by self-locking.
  • the lugs 2 have recesses on their flat end faces, each with a conical seat 4 and a concave wall part 5 adjoining the conical seat 4 for loosely receiving pressure bodies 6.
  • the pressure bodies 6 consist of a material which is as low as possible porosity, high pressure and bending strength, high corrosion resistance and high abrasion resistance, which is the case with certain sintered hard metals, certain hard metals produced in the so-called HIP process - compression under high pressure and high temperature or given certain ceramic plates with a high surface quality.
  • Each one-piece pressure body 6 has a plurality of sections, namely a frustoconical seat 6a, a cylindrical intermediate part 6b with a differently selectable height h, a frustoconical intermediate part 6c with a cone, which is used for mounting in the neck cavity by loose caulking, and a frustoconical front part 6d with a cone with a flat circular contact surface 6e, which are provided with the correspondingly high surface quality by appropriate processing methods such as grinding or the like.
  • the inclination of the conical seat 6a of the pressure body 6 is smaller by the angle ⁇ than the inclination of the conical seat 4 in the neck 2; in addition, the diameter of the wall part 5 of the neck 2 is larger than the largest diameter of the pressure body 6, so that the required tiltable mounting of the pressure body 6 is available for self-adjustment.
  • the largest diameter of the pressure body 6 and the corresponding diameter in the extension 2 is greater than the greatest height H of the extension profile, so that the wall part 5 has openings 7a, 7b at the top and bottom.
  • the largest diameter of the pressure body 6, however, is smaller than the maximum height H of the neck profile, a free milling is at least on the underside of the wall part 5 is advantageous for the simple replacement or removal of the pressure element 6, because then there is an engagement surface for a tool or the like.
  • the pressure bodies 6 protrude with their contact surfaces 6e from the end faces of the approaches 2 in the circumferential direction.
  • the pressure bodies 6 made of the corresponding hard metal are applied in pairs to two adjacent approaches 2. - In principle, however, it is also conceivable to use only one pressure element on one of the lugs 2 and its interaction with the flat end face of the adjacent lug on the next blade. For this purpose, however, it is necessary to choose a suitable material for the pressure body, which interacts with the steel attachment end face, without tending to eat or the like. A suitable material for the pressure body would be, for. B. certain bronzes.
  • corresponding pressure elements 6 with different height h are selected such that after the introduction of the pressure elements 6 into the openings 7 in the approaches 2 Gap widths are approximately the same over the circumference. - After the radial installation of the blades, there is no tangential preload in the preferred application example.
  • the pressure elements 6 can be prevented from falling out by two light mounting locks 8 which do not hinder the self-adjustment of the pressure elements if rotor blades have to be removed again after the initial installation.
  • the pressure elements 6 are self-adjusting because when the blade ring is rotated as a result of the moment F T - m - where F T is the circumferential force component and m is the distance between the pressure element edge and the pressure element symmetry axis 9 - the pressure element rotates up to the angular difference resulting from the different inclination of the seats ⁇ - which is in the order of 15 'to 30' (angular minutes) in the case of precise production - so that the deviations from the parallel position (eccentricity e) which are always present for production reasons are compensated for.
  • the contact surfaces are, as previously mentioned, so inclined to the circumferential direction that self-locking with displacements of two adjacent circular contact surfaces 6e are avoided with certainty.
  • the conical shape of the seat which deviates from the ideal ring surface, becomes non-positive and form-fitting due to the unique plasticization and elastic bedding.
  • the blades 1 can also be equipped with such pressure bodies by selecting appropriate heights h that the gap between the pressure bodies 6 is zero when installing, or that there is a tangential oversize, so that after the installation of the blades a desired tangential already with the turbine blade ring at rest Bias is present between the lugs 2 with the pressure bodies 6, the bias being increased in the operating state of the turbine.
  • the binding according to the invention can also be used with straight blades; only appropriate measures must be taken to ensure that the contact surfaces or the lugs with pressure bodies are supported against one another with appropriate circumferential force both at rest and in the course of the turbines or compressor blades.
  • the pressure hulls can be used without assembly-related restriction of the friction angle ⁇ , even after assembly of the blades in the wheel rim. If the gap between the lugs for the assembly is not large enough and the blades cannot be pressed apart far enough, the pressure bodies in the upper area must be cut off on opposite sides, such that the width of the pressure body between the cut, straight, parallel ones Areas is slightly less than the width of the opening in the neck 2. The cut pressure body is inserted radially, perpendicular to the turbine axis through the opening and then rotated by 90 °, so that the round sections are opposite the corresponding round sections of the wall part 5. Incidentally, as can be seen from FIG. 2, there also need not be two opposite openings 7, but an opening is also sufficient, which will preferably be provided at the base 2 in its outer area.
  • binding according to the invention are end blades in the low-pressure part of large steam turbines.
  • the binding according to the invention can also be used in the case of blade rings of other steam turbine stages, in the case of blade rings of compressors, gas turbines and the like.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP86106150A 1985-05-14 1986-05-06 Bindung von Laufschaufeln einer thermischen Turbomaschine Expired EP0202531B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19853517283 DE3517283A1 (de) 1985-05-14 1985-05-14 Bindung von laufschaufeln einer thermischen turbomaschine
DE3517283 1985-05-14

Publications (2)

Publication Number Publication Date
EP0202531A1 EP0202531A1 (de) 1986-11-26
EP0202531B1 true EP0202531B1 (de) 1988-08-17

Family

ID=6270660

Family Applications (1)

Application Number Title Priority Date Filing Date
EP86106150A Expired EP0202531B1 (de) 1985-05-14 1986-05-06 Bindung von Laufschaufeln einer thermischen Turbomaschine

Country Status (6)

Country Link
EP (1) EP0202531B1 (enrdf_load_stackoverflow)
CS (1) CS271330B2 (enrdf_load_stackoverflow)
DE (1) DE3517283A1 (enrdf_load_stackoverflow)
IN (1) IN167677B (enrdf_load_stackoverflow)
YU (1) YU44289B (enrdf_load_stackoverflow)
ZA (1) ZA863523B (enrdf_load_stackoverflow)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4798519A (en) * 1987-08-24 1989-01-17 United Technologies Corporation Compressor part span shroud
US5695323A (en) * 1996-04-19 1997-12-09 Westinghouse Electric Corporation Aerodynamically optimized mid-span snubber for combustion turbine blade
DE10328310A1 (de) 2003-06-23 2005-01-13 Alstom Technology Ltd Verfahren zum Modifizieren der Kopplungsgeometrie bei Deckbandsegmenten von Turbinenlaufschaufeln
DE10342207A1 (de) 2003-09-12 2005-04-07 Alstom Technology Ltd Laufschaufelbindung einer Turbomaschine
EP1944466A1 (de) * 2007-01-10 2008-07-16 Siemens Aktiengesellschaft Kopplung zweier Laufschaufeln
EP2116693A1 (de) * 2008-05-07 2009-11-11 Siemens Aktiengesellschaft Rotor für eine Strömungsmaschine
EP2669477B1 (en) * 2012-05-31 2017-04-05 General Electric Technology GmbH Shroud for airfoils

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE818806C (de) * 1949-02-17 1951-10-29 Escher Wyss Ag Beschaufelung an Rotoren von axial durchstroemten, stark verwundene Schaufeln aufweisenden Kreiselmaschinen, insbesondere von Dampf-, Gasturbinen und Verdichtern
US2957675A (en) * 1956-05-07 1960-10-25 Gen Electric Damping means
US2942843A (en) * 1956-06-15 1960-06-28 Westinghouse Electric Corp Blade vibration damping structure
CH418360A (de) * 1962-11-21 1966-08-15 Ass Elect Ind Turbomaschine
AT252962B (de) * 1964-09-25 1967-03-10 Elin Union Ag Abstützung von Turbinenschaufeln
GB1121194A (en) * 1967-05-01 1968-07-24 Rolls Royce Bladed rotor for a fluid flow machine
US3719432A (en) * 1971-04-23 1973-03-06 Gen Electric Articulated sleeve for turbine bucket lashing
JPS5632441B2 (enrdf_load_stackoverflow) * 1973-11-30 1981-07-28
FR2329845A1 (fr) * 1975-10-28 1977-05-27 Europ Turb Vapeur Disposition de liaison continue des aubes mobiles d'une turbo-machine
FR2337251A1 (fr) * 1975-12-29 1977-07-29 Europ Turb Vapeur Etage mobile de turbomachine
JPS54125307A (en) * 1978-03-24 1979-09-28 Toshiba Corp Connecting device for turbine movable blades
GB2033492A (en) * 1978-11-08 1980-05-21 Northern Eng Ind Interconnecting turbine blades
JPS572405A (en) * 1980-06-05 1982-01-07 Hitachi Ltd Rotary blade connector of axial-flow rotary machine
GB2105414B (en) * 1981-09-08 1985-02-13 Northern Eng Ind Axial-flow steam turbine wheel

Also Published As

Publication number Publication date
IN167677B (enrdf_load_stackoverflow) 1990-12-08
ZA863523B (en) 1987-01-28
YU44289B (en) 1990-04-30
DE3517283C2 (enrdf_load_stackoverflow) 1988-05-19
CS271330B2 (en) 1990-09-12
DE3517283A1 (de) 1986-11-20
CS348486A2 (en) 1990-02-12
YU78686A (en) 1989-10-31
EP0202531A1 (de) 1986-11-26

Similar Documents

Publication Publication Date Title
EP0635623B1 (de) Laufrad einer Turbomaschine
EP0118020B1 (de) Keramische Turbinenschaufel mit metallenem Stützkern
EP1636462B1 (de) Schaufel und gasturbine
EP2719484B1 (de) Bauteil für eine strömungsmachine
DE69616460T2 (de) Rotor aus thermostrukturellem Verbundmaterial, insbesondere mit grossem Diameter und sein Herstellungsverfahren
EP2094946B1 (de) Schaufelanordnung
EP1254301A2 (de) Turbinenschaufelanordnung
EP0629770A2 (de) Verfahren zur Herstellung eines Schaufelringes für trommelartige Rotoren von Turbomaschinen
EP0202531B1 (de) Bindung von Laufschaufeln einer thermischen Turbomaschine
DE4432999C2 (de) Laufrad einer Turbomaschine, insbesondere einer axial durchströmten Turbine eines Gasturbinentriebwerks
WO2011141514A1 (de) Befestigungsanordnung für schaufeln von axial durchströmten turbomaschinen sowie verfahren zum herstellen einer solchen
DE2834843A1 (de) Zusammengesetzte keramik-gasturbinenschaufel
WO2016116105A1 (de) Lageranordnung und abgasturbolader
EP3070278A2 (de) Schutzeinrichtung für eine strömungsmaschine
DE3601911C2 (de) Schaufelreihe
EP3988767A1 (de) Radialgasturbine mit stützlager
DE3500692A1 (de) Axial- oder radiallaufschaufelgitter mit einrichtungen zur konstanthaltung des schaufelspitzenspiels
EP2394028A1 (de) Abdichtvorrichtung an dem schaufelschaft einer rotorstufe einer axialen strömungsmaschine
DE102008048261A1 (de) Axialturbomaschinenrotor mit einem Schaufelschloss und Verfahren zum Herstellen desselben
DE102017204243A1 (de) Dichtfin mit zumindest einer gewölbten Seitenflanke
WO2020212039A1 (de) Resonator, verfahren zur herstellung eines solchen sowie mit einem solchen versehene brenneranordnung
DE919802C (de) Einrichtung zur Befestigung von Laufschaufeln fuer axial durchstroemte Kreiselradmaschinen
DE102021201821B4 (de) Turboladereinrichtung für einen Abgasturbolader eines Verbrennungsmotors
WO2017174355A1 (de) Rotorscheibenanordnung mit zweiteiliger dichtung
EP3292928A1 (de) Verfahren zur herstellung einer turbinenschaufel

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): CH FR GB IT LI SE

17P Request for examination filed

Effective date: 19870520

17Q First examination report despatched

Effective date: 19880119

ITF It: translation for a ep patent filed
GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): CH FR GB IT LI SE

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)
ET Fr: translation filed
PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
ITTA It: last paid annual fee
EAL Se: european patent in force in sweden

Ref document number: 86106150.5

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 19980414

Year of fee payment: 13

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 19980417

Year of fee payment: 13

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: SE

Payment date: 19980423

Year of fee payment: 13

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: CH

Payment date: 19980430

Year of fee payment: 13

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 19990506

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 19990507

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 19990531

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 19990531

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 19990506

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

EUG Se: european patent has lapsed

Ref document number: 86106150.5

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20000131

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES;WARNING: LAPSES OF ITALIAN PATENTS WITH EFFECTIVE DATE BEFORE 2007 MAY HAVE OCCURRED AT ANY TIME BEFORE 2007. THE CORRECT EFFECTIVE DATE MAY BE DIFFERENT FROM THE ONE RECORDED.

Effective date: 20050506