EP2460979A1 - Segment d'aube d'une turbomachine avec de surfaces d'appui - Google Patents

Segment d'aube d'une turbomachine avec de surfaces d'appui Download PDF

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Publication number
EP2460979A1
EP2460979A1 EP10193687A EP10193687A EP2460979A1 EP 2460979 A1 EP2460979 A1 EP 2460979A1 EP 10193687 A EP10193687 A EP 10193687A EP 10193687 A EP10193687 A EP 10193687A EP 2460979 A1 EP2460979 A1 EP 2460979A1
Authority
EP
European Patent Office
Prior art keywords
blade
abutment surface
shroud
blade segment
counter
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
EP10193687A
Other languages
German (de)
English (en)
Other versions
EP2460979B1 (fr
Inventor
Alexander Böck
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
Priority to EP10193687A priority Critical patent/EP2460979B1/fr
Priority to ES10193687T priority patent/ES2401350T3/es
Priority to US13/310,939 priority patent/US20120141259A1/en
Publication of EP2460979A1 publication Critical patent/EP2460979A1/fr
Application granted granted Critical
Publication of EP2460979B1 publication Critical patent/EP2460979B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12Blades
    • F01D5/22Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225Blade-to-blade connections, e.g. for damping vibrations by shrouding

Definitions

  • the present invention relates to a blade segment and a turbomachine.
  • the object of the present invention is to provide an alternative or complementary approach, which provides a coupling between at least two blades of a blade segment in order to achieve a favorable damping behavior.
  • a vane segment for a turbomachine comprising: a first vane; a first shroud connected to the tip of the first blade and having a bearing surface; a second blade; and a second, connected to the tip of the second blade second shroud, which has a counter-contact surface for a concern of the contact surface of the first shroud in the radial direction such that a frictional engagement between the contact surface and the counter-contact surface can be generated; provided.
  • turbomachine in particular turbomachine, is provided with the blade segment according to the invention.
  • the idea underlying the present invention is to arrange the shrouds of the respective blades in a roof tile, so that the shrouds in the radial direction against each other so that at least during operation of the blade segment (or even at a standstill) formed a frictional engagement between overlapping shrouds becomes.
  • the frictional engagement ensures a coupling of the shrouds or the blades with each other, which is favorable in terms of a damping behavior.
  • circumferential direction means a direction along a circular line which has the axis of rotation of the blade segment in the turbomachine as the central axis.
  • radial refers to a direction perpendicular to the axis of rotation of the blade segment in the turbomachine.
  • axial refers to a direction along the axis of rotation of the blade segment in the turbomachine.
  • the center of gravity of the first shroud is circumferentially spaced from a central axis of the first blade so that the first blade flexes under the action of the centrifugal forces during operation of the blade segment to produce the frictional engagement between the abutment surface and the opposing abutment surface.
  • a bending moment thus arises under the action of the centrifugal forces which tends to tip the blade together with the shroud in the circumferential direction. But this tilting is prevented by means of the contact surface of the first shroud and the counter-bearing surface of the second shroud.
  • the contact surface presses in the radial direction against the counter-contact surface in such a way that frictional engagement occurs between the contact surface and the counter-contact surface.
  • central axis herein is meant the axis of the first blade positioned such that, if the center of gravity of the first shroud were coincident therewith, no or only a negligible bending moment would be introduced from the shroud into the first blade. The same applies to the central axis of the second blade.
  • the contact surface of the first shroud and / or the counter-bearing surface of the second shroud with a pressing dimension formed in the radial direction for bending the first blade about its base in the circumferential direction, thereby generating the frictional engagement between the abutment surface and the counter abutment surface.
  • a pressing dimension is meant that the contact surface and / or counter-contact surface is thickened in the radial direction, thereby generating a surface pressure and thus a frictional engagement between the contact surface and the counter-contact surface.
  • the frictional engagement is designed to generate a torsional reaction torque in one direction about the central axis of the first and the second blade. This is favorable for compensating for the tendency to unwind of radially twisted blade profiles.
  • the first and / or second blade on a basic inclination in the axial direction which is defined by a base inclination axis, wherein the contact surface and counter-bearing surface obliquely, in particular at an angle between 45 and 135 degrees, with respect Base pitch axis in the axial direction of the first and the second blade are arranged.
  • the basic inclination is also called “lean”.
  • the basic inclination usually serves to largely compensate for the gas forces which occur during operation of the turbomachine and which generate corresponding bending moments on the blades, at least in certain operating regions of the turbomachine.
  • the base inclination is usually between 0 and 2 degrees depending on the configuration of the turbomachine.
  • the oblique arrangement of contact surface and counter-bearing surface causes a torsional moment about the central axis of a respective blade is created, which can counteract a unwinding of a respective blade.
  • This torsional moment increases, the more the contact surface presses against the counter-contact surface.
  • the abutment surfaces and counter abutment surfaces on an engagement element and a receiving element which engage in one another in the circumferential direction.
  • this embodiment prevents unwinding of the blades when no frictional engagement is generated (For example, at standstill of the blade segment in the embodiment with the offset in the circumferential direction center of gravity of the shroud).
  • the first and / or second blade is torsionsvorgespannt. If the blades engage with each other by means of the above-described engaging and receiving elements, it is possible, for example, to bias the blades torsionally so that sufficient coupling between the blades is achieved even at low rotational speeds, which brings about a favorable damping behavior. The frictional engagement due to the offset of the center of gravity of a respective shroud may not be sufficient at the low speeds to achieve such sufficient coupling between the shrouds.
  • the first and second blades are designed as moving blades.
  • the first and second blades are made of a strong creeping material.
  • strong creeping materials are meant those materials that crawl more than current nickel materials.
  • FIG. 1 As seen in the axial direction, schematically shows a blade segment 1 according to an embodiment of the present invention.
  • the blade segment 1 is part of a turbomachine, in particular a turbomachine, which is generally designated 2.
  • the turbomachine is preferably an aircraft engine.
  • the blade segment 1 has two blades 3 and 3 'on the blades 3, 3' are preferably formed as blades.
  • the blades 3, 3 ' are with their respective feet 4, 4' in a rotor 5, see FIG. 4 , For example by means of a Christmas tree connection, attached.
  • the rotor 5 rotates about an axis 6, wherein the blades 3, 3 'interact with a fluid flowing through the turbomachine 2.
  • the terms "in the circumferential direction”, “in the radial direction” and “in the axial direction” refer hereinafter to the axis 6. It should be noted that the axis 6 is located in reality much further away from the blades 3, 3 ', as in FIG. 1 shown.
  • the blades 3, 3 ' are each connected to shrouds 7, 7'.
  • the shrouds 7, 7 'each have a center of gravity S, S', which has a distance D, D 'on a central axis M, M' of a respective blade 3, 3 '.
  • the central axes M, M 'each extend through the axis 6, which due to the highly schematic representation in FIG. 1 is not recognizable.
  • the central axis M extends through a center of gravity SB of the blade 3, see FIG. 2 ,
  • the center of gravity SB is the center of gravity of the profile of the blade 3. The same applies to the central axis M 'of the blade 3'.
  • a respective shroud 7, 7 ' has a contact surface 11, 11' and a counter-contact surface 12, 12 'lying opposite it.
  • the contact surfaces 11, 11 'and counter-contact surfaces 12, 12' may each be formed at the ends of the shrouds 7, 7 'in the circumferential direction U.
  • FIG. 2 shows a section A-A from FIG. 1.
  • FIG. 3 shows a section B-B from FIG. 1.
  • "Sloping" means an angle W 'other than 90 degrees and preferably between 45 and 135 Degree.
  • the base inclination axis G 'of the blade 3' may be inclined for example by 1 degree in the direction of the axis of rotation 6.
  • a contact pressure AK results between the contact surface 11 and the counter-contact surface 12 '. Due to the oblique arrangement of the contact surface 11 and the counter-contact surface 12 ', the contact force AK results in a reaction force RK1 and a reaction force RK2, which act on the blade 3. RK2 acts along the base pitch axis G 'and RK1 perpendicular thereto.
  • RK1 is also in FIG. 2 shown. Here it can be seen that RK1 generates an additional torsional moment TR about the center of gravity SB or the center axis M of the blade 3, which counteracts a winding E of the blade 3.
  • FIG. 4 1 shows the vane segment FIG. 1 in a perspective view obliquely from below.
  • the shrouds 7, 7 'at their opposite ends preferably in the region of the contact surfaces 11, 11' and counter-bearing surfaces 12, 12 'engaging elements 13, 13' and receiving elements 14, 14 'on.
  • the engagement element 13 'of the shroud 7' engages in the circumferential direction in the receiving element 14 of the shroud 7 a. This results in a form fit in the axial direction, which unwinding of the blades 3, 3 'at a standstill of the blade segment 1 or at low speeds, where the frictional engagement RF is still too low to couple the blades 3, 3' together prevented ,
  • Fig. 5 As seen in the axial direction, schematically shows a blade segment 1 according to another embodiment of the present invention.
  • the blade segment 1 differs from that according to the Fig. 1 to 4 only in the way the friction fit RF is generated. Incidentally, therefore, the comments on the Fig. 1 to 4 according to the blade segment Fig. 5 ,
  • the frictional engagement RF in the embodiment according to Fig. 5 is advantageous not or only slightly dependent on speed.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP10193687A 2010-12-03 2010-12-03 Segment d'aube d'une turbomachine avec des surfaces d'appui Not-in-force EP2460979B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP10193687A EP2460979B1 (fr) 2010-12-03 2010-12-03 Segment d'aube d'une turbomachine avec des surfaces d'appui
ES10193687T ES2401350T3 (es) 2010-12-03 2010-12-03 Segmento de paletas y turbina con superficies de asiento radiales
US13/310,939 US20120141259A1 (en) 2010-12-03 2011-12-05 Blade segment and fluid flow machine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP10193687A EP2460979B1 (fr) 2010-12-03 2010-12-03 Segment d'aube d'une turbomachine avec des surfaces d'appui

Publications (2)

Publication Number Publication Date
EP2460979A1 true EP2460979A1 (fr) 2012-06-06
EP2460979B1 EP2460979B1 (fr) 2013-02-13

Family

ID=43754720

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10193687A Not-in-force EP2460979B1 (fr) 2010-12-03 2010-12-03 Segment d'aube d'une turbomachine avec des surfaces d'appui

Country Status (3)

Country Link
US (1) US20120141259A1 (fr)
EP (1) EP2460979B1 (fr)
ES (1) ES2401350T3 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2023247857A1 (fr) * 2022-06-22 2023-12-28 Safran Aircraft Engines Ensemble aubage de turbomachine comportant des moyens de limitations de vibrations entre plateformes

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB861728A (en) * 1958-09-29 1961-02-22 Parsons & Marine Eng Turbine Improvements in and relating to elastic fluid turbines
GB2139295A (en) * 1983-05-05 1984-11-07 Tuomo Kaivola Thermal joint e.g. for a turbine
US20060127221A1 (en) * 2002-09-02 2006-06-15 Yutaka Yamashita Turbine moving blade
JP2007154695A (ja) 2005-12-01 2007-06-21 Toshiba Corp タービン動翼および蒸気タービン
US20070224043A1 (en) * 2006-03-27 2007-09-27 Alstom Technology Ltd Turbine blade and diaphragm construction
EP1840333A1 (fr) * 2006-03-31 2007-10-03 ALSTOM Technology Ltd Aube de turbine ayant des portions de bande de renforcement
EP1873355A1 (fr) * 2006-06-27 2008-01-02 Siemens Aktiengesellschaft Aube de turbine
WO2008084038A1 (fr) * 2007-01-12 2008-07-17 Alstom Technology Ltd Diaphragme pour turbomachines et procédé de production

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1033197A (fr) * 1951-02-27 1953-07-08 Rateau Soc Amortisseurs de vibrations pour aubages mobiles de turbo-machines
GB1194061A (en) * 1968-01-17 1970-06-10 Rolls Royce Improvements relating to Pressure Exchanger Rotors
JP2001248404A (ja) * 2000-03-01 2001-09-14 Hitachi Ltd タ一ビン動翼
JP2002371802A (ja) * 2001-06-14 2002-12-26 Mitsubishi Heavy Ind Ltd ガスタービンにおけるシュラウド一体型動翼と分割環
US20080145227A1 (en) * 2006-12-19 2008-06-19 Mark Stefan Maier Methods and apparatus for load transfer in rotor assemblies

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB861728A (en) * 1958-09-29 1961-02-22 Parsons & Marine Eng Turbine Improvements in and relating to elastic fluid turbines
GB2139295A (en) * 1983-05-05 1984-11-07 Tuomo Kaivola Thermal joint e.g. for a turbine
US20060127221A1 (en) * 2002-09-02 2006-06-15 Yutaka Yamashita Turbine moving blade
JP2007154695A (ja) 2005-12-01 2007-06-21 Toshiba Corp タービン動翼および蒸気タービン
US20070224043A1 (en) * 2006-03-27 2007-09-27 Alstom Technology Ltd Turbine blade and diaphragm construction
EP1840333A1 (fr) * 2006-03-31 2007-10-03 ALSTOM Technology Ltd Aube de turbine ayant des portions de bande de renforcement
EP1873355A1 (fr) * 2006-06-27 2008-01-02 Siemens Aktiengesellschaft Aube de turbine
WO2008084038A1 (fr) * 2007-01-12 2008-07-17 Alstom Technology Ltd Diaphragme pour turbomachines et procédé de production

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2023247857A1 (fr) * 2022-06-22 2023-12-28 Safran Aircraft Engines Ensemble aubage de turbomachine comportant des moyens de limitations de vibrations entre plateformes
FR3137120A1 (fr) * 2022-06-22 2023-12-29 Safran Aircraft Engines Ensemble aubagé de turbomachine comportant des moyens de limitations de vibrations entre plateformes

Also Published As

Publication number Publication date
EP2460979B1 (fr) 2013-02-13
US20120141259A1 (en) 2012-06-07
ES2401350T3 (es) 2013-04-18

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