EP2310634B1 - Système d'aubes mobiles pour une rangée d'aubes mobiles d'une turbomachine - Google Patents

Système d'aubes mobiles pour une rangée d'aubes mobiles d'une turbomachine Download PDF

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Publication number
EP2310634B1
EP2310634B1 EP09776055A EP09776055A EP2310634B1 EP 2310634 B1 EP2310634 B1 EP 2310634B1 EP 09776055 A EP09776055 A EP 09776055A EP 09776055 A EP09776055 A EP 09776055A EP 2310634 B1 EP2310634 B1 EP 2310634B1
Authority
EP
European Patent Office
Prior art keywords
rotating
blade
blades
row
segments
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.)
Not-in-force
Application number
EP09776055A
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German (de)
English (en)
Other versions
EP2310634A2 (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
Publication of EP2310634A2 publication Critical patent/EP2310634A2/fr
Application granted granted Critical
Publication of EP2310634B1 publication Critical patent/EP2310634B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/16—Form or construction for counteracting blade vibration
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/50—Building or constructing in particular ways
    • F05D2230/51—Building or constructing in particular ways in a modular way, e.g. using several identical or complementary parts or features
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/314—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being inclined in relation to each other
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member

Definitions

  • the invention relates to a blade system referred to in the preamble of claim 1. Art for a blade row of a turbomachine.
  • the invention further relates to a turbomachine specified in the preamble of claim 7 and a method for mounting a blade row for a turbomachine.
  • the blade system comprises two or more blade segments, of which each blade segment has at least two blades, which are arranged at least predominantly radially between a radially inner and a radially outer shroud and coupled to the Deckbändem with respect to a rotational axis of the blade row, at least the radially outer shrouds of Blade segments include mutually corresponding contact surfaces over which the blade segments abut each other.
  • the fan blade segments so-called clusters
  • the number of joints and gaps of the rotor blade system can be considerably reduced compared to blade systems made of individual rotor blades.
  • fewer attack surfaces provide for guided by the associated turbomachine gases, whereby the durability of such blade systems or blade rows can be increased.
  • the blade segments also form mechanically relatively stable units in the mounted state, whereby relative movements during operation and the associated wear are advantageously reduced.
  • a disadvantage of the known blade systems is the fact that the blade segments, unlike blade systems from individual blades no longer by torsion of the blades of a row of blades against each other can be tightened. As a result, the rotor clusters are mechanically decoupled from one another and are difficult to control in terms of vibration mechanics.
  • Object of the present invention is therefore to provide a blade system of the type mentioned, which has improved vibration mechanical properties.
  • An inventive blade system for a blade row of a turbomachine having improved vibration mechanical properties is provided in that radial equilibrium axes of adjacent blades of the at least two blade segments are each axially tilted at an angle to their respective base pitch, the angles having opposite signs relative to the ground tilt , In other words, it is provided that adjacent blades of the at least two blade segments are arranged starting from their respective base inclination tilted like a scissor.
  • the basic inclination which is also called “lean” is usually used during the operation of the associated turbomachine gas forces that generate corresponding bending moments on the blades, at least in certain operating areas of the turbomachine largely compensate.
  • the basic inclination, about which the equilibrium axes of the rotor blades are tilted, is in this case usually between 0 ° and 2 °, depending on the configuration of the turbomachine.
  • the equilibrium axis can run coaxially or axially parallel to a threading axis of the blade profiles depending on the geometries of the rotor blades.
  • the blades are cast in the inner shroud and / or in the outer shroud. This allows a cost-effective manner a mechanically stable and reliable connection of the blades to the relevant shroud.
  • the contact surfaces are designed as a mechanical latch.
  • the pressing forces achievable with the aid of the rotor blade system according to the invention can be distributed over a wide area, so that in contrast to the prior art, no elastic deformations occur, but the resulting forces in the area of the contact surfaces can be discontinued as contact forces.
  • This will be a mechanically particularly stable coupling of the at least two blade segments achieved, so that the blade system is not critical vibration mechanics.
  • an amount of the angle between 0.1 ° and 10 °, in particular between 0.1 ° and 5 °, and preferably between 0.1 ° and 2 °.
  • a turbomachine in particular a thermal gas turbine, with a blade row, which comprises a blade system of at least two blade segments, each of which blade segment at least two blades, with respect to a rotational axis of the blade row at least predominantly radially between a radially inner and a radially outer shroud and are coupled to the Deckbändem, wherein at least the radially outer shrouds of the two blade segments comprise mutually corresponding application areas, via which the blade segments are coupled together.
  • radial equilibrium axes of adjacent blades of the at least two blade segments are each tilted axially at an angle to their respective base pitch, wherein the angles have opposite signs with respect to the base pitch.
  • the blade row is arranged in a turbine region, in particular a low-pressure turbine region of the turbomachine.
  • a turbine region in particular a low-pressure turbine region of the turbomachine.
  • Another aspect of the invention relates to a method for mounting a blade row for a turbomachine, in particular for a thermal gas turbine, wherein at least two blade segments of a blade system according to one of the preceding embodiments provided and those blades of the at least two blade segments, each axially at an angle ( ⁇ a , ⁇ b ) are tilted relative to their respective base pitch, are arranged adjacent to each other, wherein the angles with respect to the base pitch of the blades have opposite signs.
  • This allows a mechanically stable and vibration-mechanically uncritical assembly of the blade row, whereby a significant reduction in manufacturing costs is given at the same time increased durability.
  • Another advantage is that the bracing contact forces between the blade segments only occur speed-dependent during operation of the turbomachine, so that the blade segments are particularly easy to assemble or disassemble in the state.
  • Further advantages arise when the connection areas of the blade segments are coupled together without deformation. In contrast to the prior art, in which due to the torsion of the blade profiles over the shrouds, the contact force must be generated at the connection areas by elastic deformation and also in the state, can with the aid of the inventive method and the center of gravity displacement of the blades during operation, a bias and thus a vibration mechanical uncritical coupling of the at least two blade segments are achieved without deformation.
  • the single figure shows a schematic perspective view of two coupled blade segments of a blade system for a blade row for arrangement in a low-pressure turbine section of a thermal gas turbine.
  • FIGURE is a schematic perspective view of two coupled blade segments 10a, 10b of a blade row blade system formed from a plurality of blade segments 10 for placement in a low pressure turbine section of a thermal gas turbine (not shown).
  • Each blade segment 10a, 10b comprises in the present embodiment in each case four blades 12 (Airfoils), which are arranged with respect to a rotation axis of the blade row mounted in the turbomachine predominantly radially between a radially inner shroud 14a, 14a 'and a radially outer shroud 14b, 14b' and the shrouds 14a, 14b and 14a ', 14b' are coupled.
  • Airfoils Airfoils
  • the radially outer shrouds 14b, 14b 'of the two blade segments 10a, 10b comprise mutually correspondingly formed contact surfaces 16a, 16b, with a Z-shaped profile (so-called Z-shroud).
  • the contact surfaces 16a, 16b which are arranged at an angle to one another are designed as mechanical latches.
  • the blades 12 are respectively cast into the inner and outer shrouds 14a, 14a ', 14b, 14b' to achieve a mechanically stable, lightweight connection.
  • As the several rotor blades 12 comprehensive blade segments 10 a, 10 b (so-called.
  • a adjacent blades 12 of at least two blade segments 10a, 10b are each axially by an angle ⁇ a, ⁇ b compared to their respective baseline slope (so-called. Lean) are arranged tilted.
  • the angles ⁇ a, ⁇ b are selected such that adjacent rotor blades 12 with respect to its respective base to tilt mutually opposite, but in amount equal angles ⁇ a and ⁇ b tilted like scissors.
  • a blade 12 is tilted rearward relative to the lean relative to a rotational axis of the blade system and the adjacent blade 12 is tilted forward accordingly.
  • a center of gravity displacement of the blades concerned 12 is achieved, which due to the centrifugal forces during operation of the associated turbomachine speed-dependent righting forces arise that settle according to the arrows 18a, 18b in the contact surfaces 16a, 16b as contact forces.
  • the blade segments 10a, 10b are mechanically coupled during operation, so that the entire blade system or the blade row is vibration-mechanically uncritical.
  • the contact forces increase with the speed.
  • angles ⁇ a , ⁇ b are in the illustrated embodiment about ⁇ 1 °. In principle, however, deviating angles ⁇ or, in terms of magnitude, different angles ⁇ a , ⁇ b can be selected. It is preferably contemplated that the marginal blades 12 of each blade segment 10 are also tilted about opposing angles ⁇ with respect to their respective base pitch. Alternatively or additionally, it may also be provided that inner rotor blades 12 of the respective blade segments 10 are tilted by an angle ⁇ relative to their respective base inclination.

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

Claims (10)

  1. Système d'aubes mobiles pour une rangée d'aubes mobiles d'une turbomachine, en particulier d'une turbine à gaz thermique, comportant au moins deux segments d'aubes mobiles (10a, 10b), dont chaque segment d'aubes mobiles (10a, 10b) comprend au moins deux aubes mobiles (12), qui sont disposées au moins essentiellement radialement par rapport à un axe de rotation de la rangée d'aubes mobiles, entre un anneau de renforcement radialement intérieur et un anneau de renforcement radialement extérieur (14a, 14a', 14b, 14b'), et sont couplées avec les anneaux de renforcement (14a, 14a', 14b, 14b'), dans lequel les anneaux de renforcement radialement extérieurs (14b, 14b') des deux segments d'aubes mobiles (10a, 10b) comprennent des faces de contact (16a, 16b) qui se correspondent mutuellement, caractérisé en ce que des axes d'équilibre radiaux (A) d'aubes mobiles voisines (12) des au moins deux segments d'aubes mobiles (10a, 10b) sont disposés respectivement en position inclinée axialement d'un angle (αa, αb) par rapport à leur inclinaison de base, dans lequel les angles (αa, αb) présentent des signes contraires par rapport à l'inclinaison de base.
  2. Système d'aubes mobiles selon la revendication 1, caractérisé en ce que les angles (αa, αb) sont de valeur égale.
  3. Système d'aubes mobiles selon la revendication 1 ou 2, caractérisé en ce que les aubes mobiles (12) d'au moins un segment d'aubes mobiles (10a, 10b) sont réalisées d'une seule pièce avec l'anneau de renforcement intérieur (14a, 14a') et/ou avec l'anneau de renforcement extérieur (14b, 14').
  4. Système d'aubes mobiles selon l'une quelconque des revendications 1 à 3, caractérisé en ce que les aubes mobiles (12) sont venues de fonderie avec l'anneau de renforcement intérieur (14a, 14a') et/ou avec l'anneau de renforcement extérieur (14b, 14b').
  5. Système d'aubes mobiles selon l'une quelconque des revendications 1 à 4, caractérisé en ce que les faces de contact (16a, 16b) se présentent sous la forme d'un encliquetage mécanique.
  6. Système d'aubes mobiles selon l'une quelconque des revendications 1 à 5, caractérisé en ce que la valeur des angles (αa, αb) est comprise entre 0,1° et 10 ° , en particulier entre 0,1° et 5 ° , et de préférence entre 0,1° et 2°.
  7. Turbomachine, en particulier turbine à gaz thermique, comportant une rangée d'aubes mobiles, qui comporte un système d'aubes mobiles selon l'une quelconque des revendications 1 à 6.
  8. Turbomachine selon la revendication 7, caractérisée en ce que la rangée d'aubes mobiles est disposée dans une zone de turbine, en particulier dans une zone de turbine basse pression, de la turbomachine.
  9. Procédé de montage d'une rangée d'aubes mobiles pour une turbomachine, en particulier pour une turbine à gaz thermique, dans lequel on prépare au moins deux segments d'aubes mobiles (10a, 10b) d'un système d'aubes mobiles selon l'une quelconque des revendications 1 à 6 et on dispose au voisinage l'une de l'autre les aubes mobiles (12) des au moins deux segments d'aubes mobiles (10a, 10b), qui sont respectivement inclinées axialement d'un angle (αa, αb) par rapport à leur inclinaison de base, dans lequel les angles (αa, αb) présentent des signes contraires par rapport à l'inclinaison de base des aubes mobiles (12).
  10. Procédé selon la revendication 9, caractérisé en ce que l'on couple les uns aux autres et sans déformation les segments d'aubes mobiles (10a, 10b).
EP09776055A 2008-08-16 2009-08-01 Système d'aubes mobiles pour une rangée d'aubes mobiles d'une turbomachine Not-in-force EP2310634B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102008038038A DE102008038038A1 (de) 2008-08-16 2008-08-16 Laufschaufelsystem für eine Laufschaufelreihe einer Strömungsmaschine
PCT/DE2009/001094 WO2010020210A2 (fr) 2008-08-16 2009-08-01 Système d'aubes mobiles pour une rangée d'aubes mobiles d'une turbomachine

Publications (2)

Publication Number Publication Date
EP2310634A2 EP2310634A2 (fr) 2011-04-20
EP2310634B1 true EP2310634B1 (fr) 2012-03-14

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP09776055A Not-in-force EP2310634B1 (fr) 2008-08-16 2009-08-01 Système d'aubes mobiles pour une rangée d'aubes mobiles d'une turbomachine

Country Status (7)

Country Link
US (1) US8684659B2 (fr)
EP (1) EP2310634B1 (fr)
AT (1) ATE549487T1 (fr)
CA (1) CA2734071A1 (fr)
DE (1) DE102008038038A1 (fr)
ES (1) ES2381817T3 (fr)
WO (1) WO2010020210A2 (fr)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8888459B2 (en) * 2011-08-23 2014-11-18 General Electric Company Coupled blade platforms and methods of sealing
EP2639004B1 (fr) * 2012-03-15 2016-05-11 MTU Aero Engines GmbH Segment de couronne d'aubes avec surface de limitation de l'espace annulaire à profil en hauteur ondulé et procédé de fabrication
ITTO20120517A1 (it) * 2012-06-14 2013-12-15 Avio Spa Schiera di profili aerodinamici per un impianto di turbina a gas
US10774661B2 (en) 2017-01-27 2020-09-15 General Electric Company Shroud for a turbine engine
CN114233399B (zh) * 2022-02-23 2022-05-17 成都中科翼能科技有限公司 一种用于控制涡轮转子叶片叶冠接触面接触应力的方法

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2215407A (en) * 1988-03-05 1989-09-20 Rolls Royce Plc A bladed rotor assembly
GB2251034B (en) * 1990-12-20 1995-05-17 Rolls Royce Plc Shrouded aerofoils
EP0528138B1 (fr) * 1991-08-08 1995-05-17 Asea Brown Boveri Ag Anneau d'aube de turbine axiale
FR2851285B1 (fr) 2003-02-13 2007-03-16 Snecma Moteurs Realisation de turbines pour turbomachines ayant des aubes a frequences de resonance ajustees differentes et procede d'ajustement de la frequence de resonance d'une aube de turbine
AU2003266505A1 (en) * 2003-09-10 2005-04-06 Hitachi, Ltd. Turbine rotor blade
CA2633337C (fr) * 2005-12-29 2014-11-18 Rolls-Royce Power Engineering Plc Profil d'une aube de guidage de tuyere de second etage

Also Published As

Publication number Publication date
DE102008038038A1 (de) 2010-02-18
WO2010020210A3 (fr) 2010-11-18
WO2010020210A2 (fr) 2010-02-25
ES2381817T3 (es) 2012-05-31
EP2310634A2 (fr) 2011-04-20
US8684659B2 (en) 2014-04-01
US20110142652A1 (en) 2011-06-16
CA2734071A1 (fr) 2010-02-25
ATE549487T1 (de) 2012-03-15

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