EP1686241A2 - Rotor de turbine à gaz - Google Patents

Rotor de turbine à gaz Download PDF

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Publication number
EP1686241A2
EP1686241A2 EP06000976A EP06000976A EP1686241A2 EP 1686241 A2 EP1686241 A2 EP 1686241A2 EP 06000976 A EP06000976 A EP 06000976A EP 06000976 A EP06000976 A EP 06000976A EP 1686241 A2 EP1686241 A2 EP 1686241A2
Authority
EP
European Patent Office
Prior art keywords
rotor
blade
groove
blades
rotor according
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.)
Withdrawn
Application number
EP06000976A
Other languages
German (de)
English (en)
Inventor
Hermann Klingels
Klaus Peter Rued
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines 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 MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP1686241A2 publication Critical patent/EP1686241A2/fr
Withdrawn legal-status Critical Current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
    • F01D5/3046—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses the rotor having ribs around the circumference

Definitions

  • the invention relates to a rotor of a turbomachine, in particular a gas turbine rotor, according to the preamble of patent claim 1.
  • Rotors of a turbomachine such as gas turbine rotors
  • the blades can either be an integral part of the rotor body or be anchored via blade roots in one or more grooves of the rotor body.
  • Rotors with integral blading are referred to as blisk or bling, depending on whether a disk-shaped or an annular rotor body is present.
  • blisk or bling depending on whether a disk-shaped or an annular rotor body is present.
  • rotors in which the blades are anchored via blade roots in a groove a distinction is made between rotors in which the blade roots of the blades are mounted either in so-called axial grooves of the rotor body or in a circumferential groove thereof.
  • the present invention relates to a rotor of a turbomachine, in particular a gas turbine rotor, in which the rotor blades are fastened via their blade roots in a circumferential groove of the rotor base body, that is in a circumferential groove.
  • the circumferential grooves In rotors in which the blades are fixed with their blade roots in so-called circumferential grooves, the circumferential grooves have at least two uniformly distributed over the circumference of filling openings to introduce the blade roots of the blades in the corresponding circumferential groove.
  • the filling openings are formed according to the prior art by constrictions in the region of two opposing, profiled Nutwandschenkeln the circumferential groove, which lie in operation, the blade feet with profiled support flanks on the two profiled Nutwandschenkeln. Notches are formed at the portions of the groove wall limbs by the filling openings, which are exposed during operation of the rotor to a relatively high voltage level. As a result, the life of the rotor is reduced.
  • the blade roots of the blades have circumferentially only approximately half the width of blade platforms of the blades. This also limits the forces that can be absorbed by the blade roots during operation of the rotor.
  • the present invention based on the problem to provide a novel rotor of a turbomachine.
  • the groove has a profiled groove wall limb exclusively on one side, against which the blade roots of the rotor blades or of the rotor blade segments bear with correspondingly profiled support flanks.
  • a rotor of a turbomachine in which the rotor blades or rotor blade segments are anchored in a circumferential groove, wherein the circumferential groove has a profiled Nutwandschenkel only on one side, against which the blade roots with correspondingly profiled support flanks.
  • the circumferential groove has a profiled Nutwandschenkel only on one side, against which the blade roots with correspondingly profiled support flanks.
  • the design principle according to the invention allows tension-optimized and weight-optimized anchoring of blade segments, which have a plurality of blades, in a circumferential groove of a rotor.
  • blades with outer shrouds can be dispensed with a so-called Z-latching, resulting in a much simpler installation of the rotor.
  • the inventive design principle of a rotor allows cost-effective production and easy assembly of rotors, so that there are cost advantages over the prior art.
  • the blade roots of the blades or the blade segments on at least two different diameters each have at least one projection, wherein the projections secure the blade roots in the groove on the one hand in its axial position and on the other hand against tilting positively.
  • At least one securing element cooperates with projections of the blade feet, wherein the or each securing element secures the blades or the blade segments in the circumferential direction in a form-fitting manner in the groove.
  • FIG. 1 Before describing the present invention in greater detail below with reference to FIGS. 2 to 8b, it will be described in advance, with reference to FIG. 1, a prior art gas turbine rotor having blades guided in a circumferential groove.
  • FIG. 1 shows a detail of a gas turbine rotor 10 according to the prior art, the gas turbine rotor 10 being formed by a rotor main body 11 and a plurality of rotor blades 12.
  • the rotor blades 12 each have an airfoil 13 and a blade root 14, wherein a blade platform 15 is formed between the airfoil 13 and the blade root 14.
  • the rotor blades 12 are fastened or guided in a circumferentially extending groove 16 of the rotor base body 11 via their blade roots 14.
  • the circumferentially extending groove 16 is radially outwardly open and is bounded by two opposing, profiled groove wall limbs 17 and 18, respectively.
  • the Nutwandschenkel 17, 18 recesses or indentations 19 introduced according to the prior art form the filling openings for the blade roots 14.
  • the notches 19 are formed on portions of the Nutwandschenkel 17, 18, which are exposed during operation of the gas turbine rotor 10 to a relatively high voltage level.
  • the blades 12 are threaded through their blade roots 14 in the region of the notches 19 in the circumferential groove 16 and then moved in the circumferential direction.
  • the entire set of blades 12 is displaced by half a blade pitch in the circumferential direction, so that all contact surfaces of the blade roots 14 below the supporting Nutwandschenkel 17th and 18 are therefore not in the region of a recess or notch 19 of the groove wall legs 17, 18. It follows immediately that the blade roots 14 seen in the circumferential direction have only approximately half the width of the blade platforms 15.
  • FIG. 2 shows a section of a gas turbine rotor 20 designed according to the invention, the gas turbine rotor 20 of the embodiment shown comprising a rotor main body 21 and a plurality of rotor blade segments 22, and wherein the rotor blade segments 22 are anchored with blade roots 23 in a circumferential groove 24 of the rotor main body 21.
  • Each of the blade segments 22 has next to the blade root 23 via two blades 25, wherein between the two blades 25 and the blade root 23 of each blade segment 22, a platform 26 of the blade segment 22 is formed.
  • 6a and 6b show such a blade segment 22 in isolation in two different perspective views, namely Fig. 6a in the direction of the so-called inlet side of the blade segment 22 and Fig. 6b in the direction of the so-called exit side of the same.
  • the circumferential groove 24 of the rotor base body 21 exclusively on one side via a profiled Nutwandschenkel 27, against which the blade roots 23 of the blade segments 22 abut with correspondingly profiled support flanks 28.
  • the blade roots 23 of the blade segments 22 are therefore equipped only on one side with profiled support flanks 28, which are profiled fir-tree-like in the illustrated embodiment.
  • On the profiled Nutwandschenkel 27 opposite side of the rotor body 21 has a circumferential rib 29, which has a much smaller radius than a radially outer rib 30 of the Fig. 4 shows the rotor body 21 of the gas turbine rotor 20 according to the invention fragmentary in a solo view.
  • the blade roots 23 of the blade segments 22 are positively secured in the circumferential groove 24 of the rotor base body 21 via projections 31 and 32, wherein the projections 31 and 32 each overlap one of the two ribs 29 and 30 or engage behind.
  • the two projections 31 and 32 of the blade roots 23 of the blade segments 22 are positioned at two different diameters, wherein the projection 32 is arranged on a larger diameter than the projection 31.
  • the projection 31 can therefore as radially inward projection and the projection 32 as a radially outer Projection of a blade root 23 may be referred to.
  • the radially inner projection 31 is in the assembled state (see Fig. 2) with the rib 29 of the rotor body 21 in overlap.
  • the radially outer projection 32 overlaps or engages behind the radially outer rib 30 of the profiled Nutwandschenkels 27.
  • the projections 31 and 32 secure the blade roots 23 of the blade segments 22 in the circumferential groove 24 on the one hand in its axial position and on the other hand against tilting.
  • the rotor base body 21 has at least one threading, in the embodiment of Figs. 2 to 6b via two threading openings 33 and 34, on different diameters and at about the same circumferential position of the rotor body 21 are arranged.
  • a threading opening 33 is integrated in the rib 29 and a further threading opening 34 in the rib 30 of the groove wall leg 27.
  • the gas turbine rotor 20 according to the invention furthermore has a securing element 35.
  • FIG. 5 shows the securing element 35 in detail in a single representation.
  • the securing element 35 is formed as a circumferential, closed ring having a plurality of recesses 37 on a radially outer rib 36. In the assembled state engage in the recesses 37 of the securing element 35, the radially outer projections 32 of the Blade feet 23 of the blade segments 22 in the sense of a toothing and thus secure the blade segments 22 positively in its circumferential position.
  • the securing element 35 is preferably fastened to the rotor base body in order to fix the relative position between the securing element 35 and the rotor base body 21.
  • FIG. 3a shows the blade segment 22 before the axial insertion thereof into the circumferential groove 24 of the rotor main body 21;
  • 3b shows the blade segment 22, however, after the axial insertion into the circumferential groove 24.
  • the same as shown in FIG. 3c is displaced in the circumferential direction, so the threading openings 33 and 34 for to enable the threading of the next blade segment 22.
  • FIGS. 3d and 3e show the threading of a second blade segment 22 into the peripheral groove 24 of the rotor base body 21, wherein in turn a displacement of the two blade segments in the circumferential direction is performed in order to successively fill the circumferential groove 24 with blade segments 22.
  • FIG. 3f shows a detail of a rotor base body 21 filled with blade segments 22 over the entire circumference in a view of the outlet side of the blade segments 22 and thus of the gas turbine rotor 20;
  • Fig. 3g shows a view of the entrance side thereof.
  • FIG. 3h shows that a securing element 35 is brought from the inlet side of the gas turbine rotor 20 forth to the rotor body 21, wherein the circumferential locking of the blade segments 22 engage the radially outer projections 32 of the blade roots 23 in the recesses 37 of the fuse element 35 in the sense of a toothing
  • FIG. 3i shows the securing element 35 in the position meshed with the blade segments 22, with the securing element 35 preferably being screwed to the rotor base body 21, about the axial position of the securing element 35 relative to the rotor main body 21 to secure.
  • the securing element 35 is preferably designed in the preferred embodiment as a sealing ring of a so-called inner air seal seal.
  • the threading openings 33 and 34 are preferably uniformly distributed over the circumference of the rotor base body 21.
  • the rotor base body 21 may have two or even four radially inner filler openings 33 and two or four radially outer filler openings 34, which are diametrically opposed in each case.
  • the threading openings 33 and 34 are respectively integrated into sections of the rotor main body 21, namely the ribs 29 and 30 thereof, which are exposed to a relatively low or low voltage level during operation of the gas turbine rotor.
  • the ribs 29 and 30, in which the Einfädelötechnisch 33 and 34 are integrated, are therefore only slightly loaded during operation of the gas turbine rotor. This makes it possible that the blade roots 23 in the circumferential direction have a width which corresponds approximately to a width of the platforms 26 of the blade segments 22. This makes it possible for the first time to store or secure blade segments in circumferential grooves of a gas turbine rotor with optimum tension and optimum weight.
  • the threading openings 33 and 34 can either remain open in the assembled state of the gas turbine rotor or be closed by additional securing elements.
  • FIGS. 2 to 6b show an exemplary embodiment of a gas turbine rotor 20 according to the invention, in which the rotor base body 21 has threading openings 33 and 34 on two different diameters, around the blade feet 23 of the blade segments 22 or on different ones Diameters positioned projections 31 and 32 of the blade roots 23 to thread into the circumferential groove 24.
  • the rotor base body can also have threading openings for the projections of the blade roots only on a diameter.
  • Fig. 7a shows a rotor body 21 having a circumferential groove 24, wherein only the radially outer rib 30 of the profiled Nutwandschenkels 27 has at least one Einfädelö réelle 34 for the radially outer projection 32 of the blade root 23 of a blade segment 22 (see Fig. 7b).
  • a plurality of such threading openings 34 can be symmetrically integrated into the encircling rib 30 over the circumference.
  • the dimensions of the threading openings 34 on the radially outer rib 30 are then in turn adapted to the dimensions of the radially outer projections 32 of the blade roots 23 of the blade segments 22.
  • the radially inner projection 31 of the blade root 23 may extend over the entire circumferential extent of the blade root 23.
  • At least one filling opening 33 may also be present in the region of the radially inner rib 29 of the rotor main body 21, whereas in the region of the radially outer rib 30 of the groove wall leg 27 of the rotor main body 21 no threading opening is present.
  • the inventive principle of a gas turbine rotor is particularly advantageous in the attachment of blade segments in a circumferential groove of a rotor body of the gas turbine rotor. It is, however possible to fasten in the manner of the invention individual blades in a circumferential groove of a gas turbine rotor. In the circumferential direction, a width of the blade roots of the blades or the blade segments is approximately equal to a width of platforms thereof. For blades or blade segments with outer shrouds can be dispensed with the known from the prior art Z-latch, resulting in a simpler installation for a gas turbine rotor.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP06000976A 2005-01-26 2006-01-18 Rotor de turbine à gaz Withdrawn EP1686241A2 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102005003511A DE102005003511A1 (de) 2005-01-26 2005-01-26 Rotor einer Turbomaschine, insbesondere Gasturbinenrotor

Publications (1)

Publication Number Publication Date
EP1686241A2 true EP1686241A2 (fr) 2006-08-02

Family

ID=35735291

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06000976A Withdrawn EP1686241A2 (fr) 2005-01-26 2006-01-18 Rotor de turbine à gaz

Country Status (3)

Country Link
US (2) US7284959B2 (fr)
EP (1) EP1686241A2 (fr)
DE (1) DE102005003511A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2010149146A3 (fr) * 2009-06-25 2011-07-21 Mtu Aero Engines Gmbh Dispositif de fixation d'une ailette de turbine ou de compresseur

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8814524B2 (en) * 2008-12-11 2014-08-26 Rolls-Royce Corporation Wheel formed from a bladed ring and disk
FR2941487B1 (fr) * 2009-01-28 2011-03-04 Snecma Aube de turbomachine en materiau composite a pied renforce
US8608447B2 (en) * 2009-02-19 2013-12-17 Rolls-Royce Corporation Disk for turbine engine
DE102009052305A1 (de) 2009-11-07 2011-05-12 Mtu Aero Engines Gmbh Blisk, Gasturbine und Verfahren zur Herstellung einer derartigen Blisk
JP5450176B2 (ja) * 2010-03-10 2014-03-26 株式会社東芝 タービン動翼翼列および蒸気タービン
DE102010025238A1 (de) 2010-06-26 2011-12-29 Mtu Aero Engines Gmbh Rotor und Schaufelsegment für eine Strömungsmaschine
US8491267B2 (en) 2010-08-27 2013-07-23 Pratt & Whitney Canada Corp. Retaining ring arrangement for a rotary assembly
US9097131B2 (en) 2012-05-31 2015-08-04 United Technologies Corporation Airfoil and disk interface system for gas turbine engines
US9140136B2 (en) 2012-05-31 2015-09-22 United Technologies Corporation Stress-relieved wire seal assembly for gas turbine engines
EP2818638B1 (fr) 2013-06-27 2016-04-27 MTU Aero Engines GmbH Assemblage aubes-disque, procédé et turbomachine
DE102013223583A1 (de) 2013-11-19 2015-05-21 MTU Aero Engines AG Schaufel-Scheiben-Verbund, Verfahren und Strömungsmaschine

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US747523A (en) * 1903-09-15 1903-12-22 Wilkinson Steam Turbine Company Elastic-fluid-turbine wheel.
US1345678A (en) * 1918-06-25 1920-07-06 Westinghouse Electric & Mfg Co Mounting for turbine-buckets
US1366605A (en) * 1919-06-27 1921-01-25 Gen Electric Blade-securing means and method of making the same
US1347327A (en) * 1920-01-15 1920-07-20 Gen Electric Elastic-fluid turbine
US1466324A (en) * 1922-06-07 1923-08-28 Gen Electric Elastic-fluid turbine
US1640451A (en) * 1926-05-15 1927-08-30 Gen Electric Elastic-fluid turbine
FR2695433B1 (fr) * 1992-09-09 1994-10-21 Snecma Joint annulaire d'étanchéité disposé à une extrémité axiale d'un rotor et recouvrant des brochages d'aubes.

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2010149146A3 (fr) * 2009-06-25 2011-07-21 Mtu Aero Engines Gmbh Dispositif de fixation d'une ailette de turbine ou de compresseur

Also Published As

Publication number Publication date
DE102005003511A1 (de) 2006-07-27
US7306433B2 (en) 2007-12-11
US20060188376A1 (en) 2006-08-24
US20070059181A1 (en) 2007-03-15
US7284959B2 (en) 2007-10-23

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