EP0707136A1 - Rotor à tambour pour une turbomachine à écoulement axial - Google Patents

Rotor à tambour pour une turbomachine à écoulement axial Download PDF

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Publication number
EP0707136A1
EP0707136A1 EP95810615A EP95810615A EP0707136A1 EP 0707136 A1 EP0707136 A1 EP 0707136A1 EP 95810615 A EP95810615 A EP 95810615A EP 95810615 A EP95810615 A EP 95810615A EP 0707136 A1 EP0707136 A1 EP 0707136A1
Authority
EP
European Patent Office
Prior art keywords
radii
blade
groove
points
blade groove
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.)
Granted
Application number
EP95810615A
Other languages
German (de)
English (en)
Other versions
EP0707136B1 (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 Management 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 ABB Management AG filed Critical ABB Management AG
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

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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
    • F01D5/3023—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 axially flowed through turbomachine, in which the blades are fastened in rows with their feet in circumferential blade grooves with lateral support teeth.
  • Such drum rotors are known from EP 0 520 260 B1.
  • the rotating blade grooves change their axial dimension with each rotor revolution.
  • the resulting alternating voltages can damage the rotor rotations.
  • strong asymmetrical displacements can occur with temperature changes, for example with operational fluctuations in the first blade groove.
  • an unpopulated, circumferential pre-groove is usually arranged in front of the first blade groove.
  • this preliminary groove weakens the drum rotor and disrupts the flow of the working fluid.
  • the lead groove is therefore mostly with Lock segments equipped.
  • the pre-groove and the locking segments generate additional work in production and assembly, as well as additional material consumption.
  • the object of the invention is to avoid axial displacements and asymmetrical deformations of the first vane groove in a drum rotor of the type mentioned at the outset by means of a geometric shape of the vane groove calculated using the finite element method.
  • this is achieved in that at least the first blade groove on the working medium inlet side is formed axially asymmetrically by a plurality of radii, the preceding radius being larger than the following radius and the circular arcs formed by the radii having a common tangent at their points of contact.
  • the advantages of the invention can be seen, inter alia, in the fact that the rotor properties remain unchanged.
  • the flow of the work equipment is not affected.
  • the blade groove can be manufactured without significant additional effort and all conventional parts, such as moving blades, can be used without adjustments.
  • the further blade grooves are shaped asymmetrically in accordance with the first blade groove in order to avoid axial displacements and asymmetrical deformations in them as well.
  • 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 inserted in peripheral blade grooves 10, 11 and 12.
  • the blade groove 10 is on the steam inlet side, the blade groove 12 on the steam outlet side.
  • the flow-limiting contour 4 of the cylinder, not shown, is indicated by dash-dotted lines.
  • Fig. 2 shows the hammer head shape of the blade root 3 in detail. The forces that occur during operation are introduced into the rotor 1 by way of carrying tines 5 of the blade groove 10.
  • 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)
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
DE4436727A DE4436727A1 (de) 1994-10-14 1994-10-14 Trommelrotor für eine axial durchströmte Turbomaschine
DE4436727 1994-10-14

Publications (2)

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

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH702204A1 (de) * 2009-11-10 2011-05-13 Alstom Technology Ltd Rotor für eine axial durchströmte turbomaschine sowie gasturbine für solchen rotor.

Families Citing this family (2)

* 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
US8734112B2 (en) 2010-11-30 2014-05-27 United Technologies Corporation Asymmetrical rotor blade slot attachment

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2011552A (en) * 1977-12-27 1979-07-11 United Technologies Corp 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
EP0478234A1 (fr) * 1990-09-27 1992-04-01 General Electric Company Fixation d'aube de rotor avec fente déchargée de constraintes
RU1784065C (ru) * 1989-05-31 1992-12-23 О.И. Довгаус Диск турбомашины
EP0520259A1 (fr) * 1991-06-28 1992-12-30 Asea Brown Boveri Ag Fixation d'aubes de rotor
EP0520260A1 (fr) * 1991-06-28 1992-12-30 Asea Brown Boveri Ag Rotor à tambour pour turbine axiale

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5474423A (en) * 1994-10-12 1995-12-12 General Electric Co. Bucket and wheel dovetail design for turbine rotors

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2011552A (en) * 1977-12-27 1979-07-11 United Technologies Corp 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
EP0478234A1 (fr) * 1990-09-27 1992-04-01 General Electric Company Fixation d'aube de rotor avec fente déchargée de constraintes
EP0520259A1 (fr) * 1991-06-28 1992-12-30 Asea Brown Boveri Ag Fixation d'aubes de rotor
EP0520260A1 (fr) * 1991-06-28 1992-12-30 Asea Brown Boveri Ag Rotor à tambour pour turbine axiale

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 008, no. 005 (M - 267) 11 January 1984 (1984-01-11) *
SOVIET INVENTIONS ILLUSTRATED Section PQ Week 9402, 2 March 1994 Derwent World Patents Index; Class Q51, AN 94-015166 *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH702204A1 (de) * 2009-11-10 2011-05-13 Alstom Technology Ltd Rotor für eine axial durchströmte turbomaschine sowie gasturbine für solchen rotor.

Also Published As

Publication number Publication date
DE59504324D1 (de) 1999-01-07
DE4436727A1 (de) 1996-04-18
US5575623A (en) 1996-11-19
EP0707136B1 (fr) 1998-11-25
JPH08200006A (ja) 1996-08-06
JP3665394B2 (ja) 2005-06-29

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