EP0707136B1 - Rotor à tambour pour une turbomachine à écoulement axial - Google Patents

Rotor à tambour pour une turbomachine à écoulement axial Download PDF

Info

Publication number
EP0707136B1
EP0707136B1 EP95810615A EP95810615A EP0707136B1 EP 0707136 B1 EP0707136 B1 EP 0707136B1 EP 95810615 A EP95810615 A EP 95810615A EP 95810615 A EP95810615 A EP 95810615A EP 0707136 B1 EP0707136 B1 EP 0707136B1
Authority
EP
European Patent Office
Prior art keywords
groove
blade
radii
blade groove
drum rotor
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
EP95810615A
Other languages
German (de)
English (en)
Other versions
EP0707136A1 (fr
Inventor
Flemming Christensen
Uy-Liem Dr. Nguyen
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.)
ABB AG Germany
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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 ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Publication of EP0707136A1 publication Critical patent/EP0707136A1/fr
Application granted granted Critical
Publication of EP0707136B1 publication Critical patent/EP0707136B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D5/30—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

  • the invention relates to a drum rotor for an axial flowed through turbomachine, in which the blades with their feet in rows in circumferential blade grooves lateral tines are attached.
  • Such drum rotors are known from EP 0 520 260 B1.
  • the rotating ones change Blade grooves have their axial dimension with every rotor revolution. Due to the resulting changing voltages, damage to the rotor turns.
  • damage to the rotor turns.
  • at Temperature changes for example in operational Fluctuations in the first blade groove are strong asymmetrical Shifts occur.
  • To avoid damage usually becomes one before the first blade groove empty, circumferential pre-groove arranged. This pre-groove however, weakens the drum rotor and disrupts the flow of the Work equipment.
  • the lead groove is therefore mostly with Lock segments equipped. The Vornut and the Closure segments create additional work production and assembly, as well as an additional one Material consumption.
  • the invention is based, with one Drum rotor of the type mentioned at the outset and asymmetrical deformations of the first blade groove one calculated using the finite element method Avoid geometrical shaping of the blade groove.
  • the advantages of the invention are among them see that the rotor properties remain unchanged.
  • the Flow of the work equipment is not affected.
  • the Blade groove can be manufactured and without significant additional effort all conventional parts, such as blades, can be used without Adjustments are used.
  • Blade grooves corresponding to the first blade groove be shaped asymmetrically to include in them Axial shifts and asymmetrical deformations too avoid.
  • FIG. 1 shows the first three rows of a high-pressure rotor 1.
  • the individual blades consisting of blade 2 and Blade root 3, are in circumferential blade grooves 10, 11 and 12 used.
  • the blade groove 10 is there on the steam inlet side, the blade groove 12 on the steam outlet side.
  • the flow-limiting contour 4 of the not shown Cylinder is shown in dash-dot lines.
  • Fig. 2 shows the hammer head shape of the blade root 3 in Detail. The forces occurring during operation are over Carrying teeth 5 of the blade groove 10 are introduced into the rotor 1.
  • the previous groove contour 6 is shown in dashed lines on the steam inlet side.
  • the previous groove contour is retained on the steam outlet side.
  • the asymmetrical shape of the blade groove 10 is described by a plurality of successive radii R1, R2, R3 and R4.
  • the radius R1 is larger than R2, R2 is larger than R3 and R3 is larger than R4.
  • Points A, B, C, D and E are defined on the contour of the part of the blade groove 10 which is described by the radii R1 to R4. These points divide the contour on the steam inlet side into circular arcs 21, 22, 23 and 24 described by the radii R1 to R4.
  • Circular arc 21 goes from point A to point B
  • circular arc 22 goes from point B to point C, and so on.
  • the points AE are locations of common tangents of the partial curves touching each other there.
  • a straight line T through the point C is a tangent to the circular arc 22 described by the radius R2
  • the straight line T is also a tangent to the circular arc 23 described by the radius R3.
  • the centers of the circular arcs 22 and 23 are perpendicular to the tangent T through point C. The same applies to the centers of the other arcs.
  • the groove is returned to the previous groove contour by an essentially arbitrarily shaped curve 25 at point F.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (1)

  1. Rotor à tambour (1) pour une turbomachine à écoulement axial, dans lequel les aubes avec leurs bases (3) sont fixées en rang dans des rainures d'aubes périphériques (10, 11, 12) avec des dents de support latérales, caractérisé en ce qu'au moins la première rainure d'aube (10) du côté de l'entrée du fluide de travail est asymétrique, et en ce que le contour de la rainure d'aube (10), du côté de l'entrée du fluide de travail, est formé par plusieurs rayons (R1-R4), les rayons des arcs de cercle successifs de la rangée diminuant encore depuis la base de la rainure d'aube (10), et les arcs de cercle (21-24) formés par les rayons (R1-R4) possèdent une tangente commune (T) à leurs points de contact.
EP95810615A 1994-10-14 1995-10-03 Rotor à tambour pour une turbomachine à écoulement axial Expired - Lifetime EP0707136B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4436727 1994-10-14
DE4436727A DE4436727A1 (de) 1994-10-14 1994-10-14 Trommelrotor für eine axial durchströmte Turbomaschine

Publications (2)

Publication Number Publication Date
EP0707136A1 EP0707136A1 (fr) 1996-04-17
EP0707136B1 true EP0707136B1 (fr) 1998-11-25

Family

ID=6530754

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95810615A Expired - Lifetime EP0707136B1 (fr) 1994-10-14 1995-10-03 Rotor à tambour pour une turbomachine à écoulement axial

Country Status (4)

Country Link
US (1) US5575623A (fr)
EP (1) EP0707136B1 (fr)
JP (1) JP3665394B2 (fr)
DE (2) DE4436727A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100074754A1 (en) * 2008-09-19 2010-03-25 Thunder Tiger Corporation Securing Device For Connecting Blades To Blade-Root Attachment Of Remote-Control Helicopters
CH702204A1 (de) * 2009-11-10 2011-05-13 Alstom Technology Ltd Rotor für eine axial durchströmte turbomaschine sowie gasturbine für solchen rotor.
US8734112B2 (en) 2010-11-30 2014-05-27 United Technologies Corporation Asymmetrical rotor blade slot attachment

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4191509A (en) * 1977-12-27 1980-03-04 United Technologies Corporation Rotor blade attachment
JPS58167807A (ja) * 1982-03-29 1983-10-04 Hitachi Ltd タ−ボ機械のブレ−ド取付構造
RU1784065C (ru) * 1989-05-31 1992-12-23 О.И. Довгаус Диск турбомашины
US5141401A (en) * 1990-09-27 1992-08-25 General Electric Company Stress-relieved rotor blade attachment slot
EP0520259B1 (fr) * 1991-06-28 1994-09-21 Asea Brown Boveri Ag Fixation d'aubes de rotor
EP0520260B1 (fr) * 1991-06-28 1994-04-13 Asea Brown Boveri Ag Rotor à tambour pour turbine axiale
US5474423A (en) * 1994-10-12 1995-12-12 General Electric Co. Bucket and wheel dovetail design for turbine rotors

Also Published As

Publication number Publication date
EP0707136A1 (fr) 1996-04-17
US5575623A (en) 1996-11-19
JPH08200006A (ja) 1996-08-06
DE4436727A1 (de) 1996-04-18
JP3665394B2 (ja) 2005-06-29
DE59504324D1 (de) 1999-01-07

Similar Documents

Publication Publication Date Title
DE602004011859T2 (de) Vorrichtung für die Regelung von Spalten in einer Gasturbine
DE10059997B4 (de) Kühlbare Schaufel für eine Gasturbinenkomponente
EP0799973B1 (fr) Contour de paroi pour une turbomachine axiale
EP0916812B1 (fr) Etage final pour turbine axial
EP1836401B1 (fr) Méthode pour modifier un compresseur multi-étages
EP0705959A2 (fr) Configuration du pied d'aube de turbomachine
DE2060123A1 (de) Turbinenrotorschaufel mit vom Schaufelfuss zum Schaufelende verlaufenden Kuehlkanaelen
EP1293644A1 (fr) Support pour aubes statoriques et segment d'accumulation de chaleur
DE3541330A1 (de) Plattformdichtung fuer eine turbomaschine
EP1515000A1 (fr) Aubage d'une turbomachine avec un carenage contouré
CH698342A2 (de) Verfahren zur Reparatur einer Laufscheibe für eine Gasturbine sowie Laufscheibe.
DE102009044812A1 (de) Hohlkanäle
EP1703080A1 (fr) Machine tournante
EP2179143A2 (fr) Installation de turbine à gaz
DE10244038A1 (de) Einlaufbelag für Axialverdichter von Gasturbinen, insbesondere von Gasturbinentriebwerken
DE102014205226A1 (de) Schaufelreihengruppe
EP3064706A1 (fr) Rangée d'aubes directrices pour une turbomachine traversée axialement
DE102017209658A1 (de) Einlaufstruktur für eine Strömungsmaschine, Strömungsmaschine mit einer Einlaufstruktur und Verfahren zum Herstellen einer Einlaufstruktur
EP1079070A2 (fr) Bouclier thermique pour un rotor de turbine
EP0707136B1 (fr) Rotor à tambour pour une turbomachine à écoulement axial
EP2805017B1 (fr) Stator pour une turbomachine axiale et procédé de dimensionnement du stator
DE102004020377A1 (de) Verfahren zur Bearbeitung von Dichtungen nach Art der Lamellendichtungen
EP0707135A2 (fr) Rotor avec aubes
EP0844367A1 (fr) Rotor soudé pour une turbomachine
DE69816947T2 (de) Gasturbinenschaufel

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): DE FR GB IT

17P Request for examination filed

Effective date: 19960920

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: ASEA BROWN BOVERI AG

17Q First examination report despatched

Effective date: 19970710

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB IT

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 FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 19981125

REF Corresponds to:

Ref document number: 59504324

Country of ref document: DE

Date of ref document: 19990107

ITF It: translation for a ep patent filed

Owner name: DE DOMINICIS & MAYER S.R.L.

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 19990128

EN Fr: translation not 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
PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20000915

Year of fee payment: 6

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: 20011003

REG Reference to a national code

Ref country code: GB

Ref legal event code: IF02

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

Effective date: 20011003

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 59504324

Country of ref document: DE

Representative=s name: ROESLER, UWE, DIPL.-PHYS.UNIV., DE

Effective date: 20120621

Ref country code: DE

Ref legal event code: R081

Ref document number: 59504324

Country of ref document: DE

Owner name: ALSTOM TECHNOLOGY LTD., CH

Free format text: FORMER OWNER: ALSTOM, PARIS, FR

Effective date: 20120621

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

Ref country code: DE

Payment date: 20141022

Year of fee payment: 20

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

Ref country code: IT

Payment date: 20141030

Year of fee payment: 20

REG Reference to a national code

Ref country code: DE

Ref legal event code: R071

Ref document number: 59504324

Country of ref document: DE