US20110200440A1 - Blade cluster having an offset axial mounting base - Google Patents

Blade cluster having an offset axial mounting base Download PDF

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Publication number
US20110200440A1
US20110200440A1 US12/998,388 US99838809A US2011200440A1 US 20110200440 A1 US20110200440 A1 US 20110200440A1 US 99838809 A US99838809 A US 99838809A US 2011200440 A1 US2011200440 A1 US 2011200440A1
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US
United States
Prior art keywords
blade
blades
stage
recited
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.)
Abandoned
Application number
US12/998,388
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English (en)
Inventor
Frank Stiehler
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
Individual
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 Individual filed Critical Individual
Assigned to MTU AERO ENGINES GMBH reassignment MTU AERO ENGINES GMBH ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: STIEHLER, FRANK
Publication of US20110200440A1 publication Critical patent/US20110200440A1/en
Abandoned 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/025—Fixing blade carrying members on shafts
    • 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
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding

Definitions

  • the present invention relates to a blade.
  • Turbine stages which are built for turbines that are subject to relatively high loads, and also compressor stages are generally equipped with individual blades that are each hooked via a profiled root into a disk having grooves and are fixed in position therein.
  • the related art in accordance with the German Patent Application DE 198 58 702 A1 describes the blade of a turbine machine that is mounted on a rotor or stator via an axially oriented dovetail root in the form of a fir tree.
  • the disk-shaped rotor in the form of a disk has a number of axially extending grooves on its radial peripheral surface which, in the aforementioned form, form a plurality of radially spaced apart undercuts in the direction of the groove base.
  • the root is composed of a fir tree-shaped projection, on which a number of peripherally extending undercuts are formed in such a way that the root can be inserted into the groove in the axial direction of the rotor and fixed in position therein.
  • the rotors of compressor and turbine stages that are built in accordance with the BLISK design principle offer one approach for partially resolving the aforementioned problem.
  • the basis for a BLISK is preferably a forged disk, out of whose outer contour, the blade profiles are machined, for example. This means that the disk and the blades are fabricated from one part.
  • blade clusters are integral components composed of at least two blades that are equipped with one (single) shared blade mount for mounting the cluster on the rotor or stator.
  • the blade mount is designed as an axially extending dovetail connection having at least one undercut (on each lateral face). This type of connection may be produced with high precision and assembled inexpensively.
  • the dovetail connection is advantageously configured in a decentralized location between the blades, preferably offset circumferentially. This allows the loads acting on the blades to be introduced to each dovetail contact surface as distributed loads, instead of as centrally consolidated loads, thereby reducing the high stress concentration loads that form in the process. This makes it possible for the dovetail connection to have a less massive design, respectively for it to transmit higher forces. In this context, with respect to the introduction of force, it proves to be especially beneficial when the circumferential offset is equal to approximately one half of a blade pitch.
  • the groove, respectively the recess of the dovetail connection be formed on the side of the blade cluster, and that the root, respectively the projection be formed on the side of the rotor or stator. This reduces the weight of the cluster and thus the force load of the connection.
  • FIG. 1 shows the radially outer circumferential portion of a turbine or compressor disk having the blade cluster mounted thereon in accordance with one preferred exemplary embodiment of the present invention
  • FIG. 2 shows the blade cluster in the uninstalled state
  • FIG. 3 shows an alternate embodiment of the blade cluster
  • FIG. 4 shows an alternate embodiment of the dovetail joint of FIG. 2 .
  • a blade cluster 1 of a turbine or compressor stage is composed of a pair of blades 2 which, at the radially inner ends thereof, are joined to a shared blade root 3 .
  • the radially outer ends are coupled to one another via a flat band 4 (referred to by experts as a “plain shroud”).
  • Blade cluster 1 having the preceding components is formed in an integral type of construction, for example by friction welding or inductive high-frequency pressure welding, and also preferably in one piece.
  • blade root 3 is composed of a root plate 5 , to whose radial upper side the two radially inner blade ends are attached and on whose radial bottom side a root base 6 is formed in such a way that root plate 5 has a strip-shaped overhang relative to base 6 .
  • a groove 7 Machined into this root base 6 in the present case is a groove 7 , which extends right through in the axial direction of the stage relative to the row of blades.
  • Groove 7 is produced in the form of a dovetail and thus forms an undercut at each groove side.
  • groove 7 is not centrally located in the middle between the two blades 2 , respectively the inner blade ends thereof, but rather, in the present case, is configured so as to be offset by approximately one half of a blade pitch in the circumferential direction, namely in accordance with FIG. 1 , in the direction of the action of force of blades 2 .
  • FIG. 1 shows a portion of a disk (rotor) 8 of the stage. Accordingly, disk 8 is axially widened at the radially outer periphery thereof to form what is generally known as a fillet interface 9 , on whose radial outer side, a number of tongue-type strips 10 are formed in one piece with disk 8 in the axial direction of the stage. Tongues 10 are spaced uniformly apart in the circumferential direction.
  • tongues 10 form a dovetail shape and thus form the mating component to grooves 7 on the side of blade cluster 1 .
  • Grooves 7 and tongues 10 are dimensioned in such a way that a press-fit connection is formed when they are joined together.
  • blade roots 3 are slid onto disk-side tongues 10 in the axial direction until a burr-free transition is formed between disk 8 and root 3 .
  • individual blade clusters 1 are assembled to form a complete blade ring.
  • a blade cluster 1 may also have more than two blades, for example three blades, as shown in FIG. 3 with blades 2 a, 2 b, 2 c on base 6 .
  • blade root 3 is not limited to a simple dovetail shape. As is also known from the related art, it may be designed in the shape of a fir tree having a plurality of undercut edges per side face, as shown in FIG. 4 with groove 7 a in base 6 a. Finally, it is not absolutely necessary that groove 7 be designed to be through-extending. Rather, it may be closed on one side, thereby forming a predefined limit stop for mounting blade cluster 1 .

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US12/998,388 2008-11-13 2009-11-07 Blade cluster having an offset axial mounting base Abandoned US20110200440A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102008057190A DE102008057190A1 (de) 2008-11-13 2008-11-13 Schaufelcluster mit versetztem axialem Montagefuß
PCT/DE2009/001579 WO2010054632A2 (fr) 2008-11-13 2009-11-07 Groupe d'aubes avec pied de montage axial décalé

Publications (1)

Publication Number Publication Date
US20110200440A1 true US20110200440A1 (en) 2011-08-18

Family

ID=42105017

Family Applications (1)

Application Number Title Priority Date Filing Date
US12/998,388 Abandoned US20110200440A1 (en) 2008-11-13 2009-11-07 Blade cluster having an offset axial mounting base

Country Status (4)

Country Link
US (1) US20110200440A1 (fr)
EP (1) EP2344722A2 (fr)
DE (1) DE102008057190A1 (fr)
WO (1) WO2010054632A2 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170002659A1 (en) * 2015-07-01 2017-01-05 United Technologies Corporation Tip shrouded high aspect ratio compressor stage
US20200063575A1 (en) * 2018-08-24 2020-02-27 Rolls-Royce North American Technologies Inc. Turbine blade comprising ceramic matrix composite materials

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ES2532582T3 (es) * 2012-08-09 2015-03-30 Mtu Aero Engines Gmbh Método para fabricar un segmento de corona de álabes de TiAl para una turbina de gas, así como un correspondiente segmento de corona de álabes
ES2640263T3 (es) 2012-11-09 2017-11-02 MTU Aero Engines AG Conjunto de palas para una turbina
WO2015047445A2 (fr) 2013-03-05 2015-04-02 Freeman Ted J Pale de moteur à turbine à gaz composite avec de multiples surfaces portantes
WO2020099184A1 (fr) * 2018-11-15 2020-05-22 Rolls-Royce Deutschland Ltd & Co Kg Procédé de fabrication d'un composant pour une turbomachine

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2221685A (en) * 1939-01-18 1940-11-12 Gen Electric Elastic fluid turbine bucket unit
US2277484A (en) * 1939-04-15 1942-03-24 Westinghouse Electric & Mfg Co Turbine blade construction
US3597109A (en) * 1968-05-31 1971-08-03 Rolls Royce Gas turbine engine axial flow multistage compressor
US3902820A (en) * 1973-07-02 1975-09-02 Westinghouse Electric Corp Fluid cooled turbine rotor blade
US5743713A (en) * 1995-09-21 1998-04-28 Ngk Insulators, Ltd. Blade, turbine disc and hybrid type gas turbine blade
US6416276B1 (en) * 1999-03-29 2002-07-09 Alstom (Switzerland) Ltd Heat shield device in gas turbines
US6616408B1 (en) * 1998-12-18 2003-09-09 Mtu Aero Engines Gmbh Blade and rotor for a gas turbine and method for linking blade parts
US7037078B2 (en) * 2003-02-13 2006-05-02 Snecma Moteurs Turbomachine turbines with blade inserts having resonant frequencies that are adjusted to be different, and a method of adjusting the resonant frequency of a turbine blade insert

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE679926C (de) * 1935-12-21 1939-08-17 Gustav Koehler Dipl Ing Befestigung von radial beaufschlagten Doppelschaufeln
CH305819A (de) * 1951-02-26 1955-03-15 Power Jets Res & Dev Ltd Verfahren zur Herstellung eines Schaufelrotors einer Turbomaschine und nach diesem Verfahren hergestellter Schaufelrotor.
CH335695A (de) * 1955-12-06 1959-01-31 Bbc Brown Boveri & Cie Fuss zur Befestigung von Schaufeln in Läufern von Turbomaschinen
GB2401655A (en) * 2003-05-15 2004-11-17 Rolls Royce Plc A rotor blade arrangement
DE10337868A1 (de) * 2003-08-18 2005-03-17 Mtu Aero Engines Gmbh Rotor für eine Gasturbine sowie Gasturbine
WO2006060012A1 (fr) * 2004-12-01 2006-06-08 United Technologies Corporation Moteur de turbine a pression d’entree comprenant des groupes de pales de turbine et procede de montage

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2221685A (en) * 1939-01-18 1940-11-12 Gen Electric Elastic fluid turbine bucket unit
US2277484A (en) * 1939-04-15 1942-03-24 Westinghouse Electric & Mfg Co Turbine blade construction
US3597109A (en) * 1968-05-31 1971-08-03 Rolls Royce Gas turbine engine axial flow multistage compressor
US3902820A (en) * 1973-07-02 1975-09-02 Westinghouse Electric Corp Fluid cooled turbine rotor blade
US5743713A (en) * 1995-09-21 1998-04-28 Ngk Insulators, Ltd. Blade, turbine disc and hybrid type gas turbine blade
US6616408B1 (en) * 1998-12-18 2003-09-09 Mtu Aero Engines Gmbh Blade and rotor for a gas turbine and method for linking blade parts
US6416276B1 (en) * 1999-03-29 2002-07-09 Alstom (Switzerland) Ltd Heat shield device in gas turbines
US7037078B2 (en) * 2003-02-13 2006-05-02 Snecma Moteurs Turbomachine turbines with blade inserts having resonant frequencies that are adjusted to be different, and a method of adjusting the resonant frequency of a turbine blade insert

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170002659A1 (en) * 2015-07-01 2017-01-05 United Technologies Corporation Tip shrouded high aspect ratio compressor stage
US20200063575A1 (en) * 2018-08-24 2020-02-27 Rolls-Royce North American Technologies Inc. Turbine blade comprising ceramic matrix composite materials
US10934859B2 (en) * 2018-08-24 2021-03-02 Rolls-Royce North American Technologies Inc. Turbine blade comprising ceramic matrix composite materials

Also Published As

Publication number Publication date
DE102008057190A1 (de) 2010-05-20
EP2344722A2 (fr) 2011-07-20
WO2010054632A2 (fr) 2010-05-20
WO2010054632A3 (fr) 2010-12-29

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Legal Events

Date Code Title Description
AS Assignment

Owner name: MTU AERO ENGINES GMBH, GERMANY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:STIEHLER, FRANK;REEL/FRAME:026206/0374

Effective date: 20110318

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION