EP2789800B1 - Assortiment des tôles de serrage, moteur à turbine à gaz et procédé de montage associés - Google Patents

Assortiment des tôles de serrage, moteur à turbine à gaz et procédé de montage associés Download PDF

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Publication number
EP2789800B1
EP2789800B1 EP13162839.8A EP13162839A EP2789800B1 EP 2789800 B1 EP2789800 B1 EP 2789800B1 EP 13162839 A EP13162839 A EP 13162839A EP 2789800 B1 EP2789800 B1 EP 2789800B1
Authority
EP
European Patent Office
Prior art keywords
lock plates
coding
different
lock
assortment
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.)
Active
Application number
EP13162839.8A
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German (de)
English (en)
Other versions
EP2789800A1 (fr
Inventor
Martin Pernleitner
Rudolf Stanka
Manfred Schill
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
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MTU Aero Engines AG
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Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to ES13162839.8T priority Critical patent/ES2630046T3/es
Priority to EP13162839.8A priority patent/EP2789800B1/fr
Priority to US14/248,067 priority patent/US9695699B2/en
Publication of EP2789800A1 publication Critical patent/EP2789800A1/fr
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Publication of EP2789800B1 publication Critical patent/EP2789800B1/fr
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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
    • F01D5/32—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
    • 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
    • F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor
    • 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

Definitions

  • the present invention relates to a securing plate assortment for a blade arrangement of a gas turbine with a plurality of different locking plates, a gas turbine with such a securing plate assortment and a method for assembling such a blade arrangement.
  • An object of an embodiment of the present invention is to improve the assembly of blade assemblies with safety plates.
  • Claim 9 is directed to a gas turbine with such a safety plate assortment, claim 10 to a method for assembling blade assemblies.
  • Advantageous embodiments of the invention are the subject of the dependent claims.
  • the invention consists in a safety plate assortment according to claim 1. This can advantageously be achieved in one embodiment, that during mounting of the gas turbine different locking plates with a lower error rate or error-free the associated blade assembly can be assigned. As a result, in particular an advantageous increase in safety can be achieved.
  • the geometric codes differ in number and / or shape and / or size of, in particular based on the mounting state axial and / or radial, recesses and / or elevations.
  • a haptic and / or low-wear differentiation of the different locking plates is made possible.
  • an optical differentiation of the different locking plates can be made possible.
  • an assembly process can be at least partially automated by such a geometric coding.
  • An encoding may have one, two or more recesses and / or elevations.
  • the recesses may differ in their shape; In particular, different codes may alternatively have round holes, grooves, indentations and / or similar recesses.
  • the surveys may differ in their form; it can be provided webs, pins and / or similar surveys. Additionally or alternatively, elevations and / or recesses may have maximum dimensions, for example diameters, which differ by at least 5 mm, in particular at least 10 mm. Additionally or alternatively, elevations and / or recesses of different locking plates may be arranged at different points of the locking plates, for example (relative to the mounting position) offset in the circumferential direction.
  • the locking plates have a functional area for supporting or securing the blade arrangement and a coding area on, wherein the geometric coding of the locking plates is arranged in the coding area.
  • the coding of the securing plates does not or only slightly influences the function of the securing plate and / or the function of the turbine component to be secured.
  • a functional area is to be understood in particular to mean a region of the securing plate which, in particular by means of positive and / or frictional contact with the blade arrangement to be secured, limits, in particular prevents, an undesired, in particular axial, movement of the blade arrangement.
  • a coding region is to be understood as meaning, in particular, a region of the securing plate in which different recesses and / or elevations are arranged, which in their combination represent the geometric coding of the securing plate.
  • the geometric coding of the securing plate is formed by the combination of recesses and / or elevations of at least two coding region.
  • the locking plates on a first flange, a second flange and a connecting web at least one of the flanges and / or the connecting web on a functional area, which is designed differently than a functional area of the other locking plates.
  • connecting webs of different locking plates have different longitudinal extents and / or widths.
  • the longitudinal extension of a securing plate is in particular that which is axial in relation to the gas turbine State to understand.
  • the longitudinal extent of various locking plates of the securing plate assortment differ by at most 10 mm, in particular by at most 1 mm, which is difficult to distinguish with the naked eye in the mounting situation.
  • the first flange and / or the second flange of the locking plates in particular in each case, at least one coding region.
  • This can be arranged in an embodiment on a surface of the flange facing the blade arrangement, on a surface of the flange facing away from the blade arrangement and / or an edge of the flange connecting these two surfaces.
  • a geometric coding in a near-end, even in the assembled state accessible or visible area of the locking plate are arranged, which in particular a better haptic distinction of different or differently coded locking plates can be done.
  • the connecting web of the locking plates on a coding area is advantageously advantageously an improved optical differentiation of the different locking plates before or during assembly is made possible and a larger space can be used for coding.
  • different locking plates have mutually correspondingly arranged coding regions whose coding differs in number and / or shape and / or size of recesses.
  • the coding region is different from the functional region, in particular disposed of.
  • the invention further consists in a gas turbine according to claim 9. This can be achieved in particular advantageously that when mounting each turbine stage easy and / or little error-prone the appropriate locking plates can be arranged.
  • the invention further consists in an assembly method according to claim 10. This can be achieved in particular advantageously that when mounting the gas turbine different locking plates with a lower error rate or error-free the associated blade assemblies can be assigned. As a result, in particular an advantageous reduction of the error rate during assembly can be achieved.
  • first locking plate first and blade assemblies are mounted on a turbine stage, the blade assemblies and the locking plate are not yet fixed to each other. This determination can be made in particular by deforming, in particular bending over a flange, of the securing plate.
  • each turbine stage is assigned a securing plate of the securing plate assortment.
  • Fig. 1 shows a trained according to an embodiment of the present invention safety plate assortment 1 a number of different locking plates 10, 20 and 30th
  • the locking plates 10, 20, 30 each have a first flange 11, 21, 31 and a second flange 12, 22, 32.
  • the first flange 11, 21, 31 is connected to the second flange 12, 22, 32 by means of a connecting web 13, 23, 33.
  • This connecting webs 13, 23, 33 differ slightly in their longitudinal extent L 13 , L 23 , L 33 , whereby the locking plates 10, 20, 30 have a different longitudinal extent.
  • first flanges 11, 21, 31 are arranged here for axial securing functional areas 14.2, 24.2, 34.2, which are in contact with the blade feet.
  • a coding region 15 is additionally arranged in the functional region 14.2, in which a geometric coding of the securing plate 10 by means of two, formed as round holes, recesses 16 and 17 is formed.
  • a geometric coding of the securing plate 10 by means of two, formed as round holes, recesses 16 and 17 is formed.
  • no recesses are provided, so that the locking plate 10, despite its only slight difference in length haptically and wear-resistant from the locking plates 20, 30 to differentiate and assign the respective turbine stage or blade assembly.
  • a coding region 25 or 35 is formed, which is spaced from the functional areas 24.2 and 34.2, so as not to function in particular, not to weaken the surface.
  • the coding regions 25 and 35 are arranged at mutually corresponding positions of the respective securing plate 20 and 30, respectively.
  • the coding areas of all locking plates are arranged at mutually corresponding positions of the respective locking plate, for example, in the areas 14.2, 24.2 and 34.2 axial recesses in a different number, shape and / or arrangement are formed and / or on the edges (left in Fig. 1 ) Radial elevations and / or recesses in a different number, shape and / or arrangement are formed.
  • the coding region 25 of the securing plate 20 has a, here in part substantially part-circular, radial (relative to the mounting state) elevation 26.
  • the coding region 35 of the securing plate 30 has a, here part-circular, radial recess.
  • each locking plate 10, 20, 30 Due to the different positioning, number, shape and / or size of the recesses and elevations in the respective coding region 15, 25, 35, compared With the other coding areas, each locking plate 10, 20, 30 has a different geometric coding.
  • a geometric encoding, as in FIG. 1 is shown in particular allows wear-free a haptic distinction of the three locking plates 10, 20 and 30, which is difficult for an assembly worker due to the only slightly different longitudinal extent L 13 , L 23 , L 33 of the connecting webs 13, 23, 33 without this geometric coding would prove.

Landscapes

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

Claims (13)

  1. Assortiment de tôles de sûreté (1) pour un agencement de pales d'une turbine à gaz, avec une pluralité de différentes tôles de sûreté (10, 20, 30), dans lequel les tôles de sûreté présentent une première aile (11, 21, 31), une seconde aile (12, 22, 32) et une barrette de liaison (13, 23, 33) entre la première et la deuxième aile et dans lequel diverses tôles de sûreté présentent respectivement des codages géométriques différents, caractérisé en ce que la première aile (11, 21, 31) et/ou la seconde aile (12, 22, 32) des tôles de sûreté (10, 20, 30) présente(nt) une zone de codage (15, 25, 35), dans lequel le codage géométrique des tôles de sûreté est agencé dans la zone de codage et dans lequel la zone de codage (15, 25, 35) est agencée sur une surface de l'aile opposée à la barrette de liaison et/ou sur une arête, qui relie la surface opposée à la surface tournée vers la barrette de liaison.
  2. Assortiment de tôles de sûreté selon la revendication 1, dans lequel les codages géométriques se distinguent par le nombre et/ou la forme et/ou la grandeur de cavités (16, 17, 36) et/ou de protubérances (26).
  3. Assortiment de tôles de sûreté selon l'une quelconque des revendications précédentes, dans lequel les tôles de sûreté présentent une zone fonctionnelle (14, 24, 34) pour étayer ou sécuriser l'agencement de pales.
  4. Assortiment de tôles de sûreté selon l'une quelconque des revendications précédentes, dans lequel au moins l'une des ailes et/ou de la barrette de liaison d'une tôle de sûreté présente(nt) une zone fonctionnelle qui est autrement conçue que la zone fonctionnelle correspondante d'une autre tôle de sûreté.
  5. Assortiment de tôles de sûreté selon la revendication précédente, dans lequel les barrettes de liaison (13, 23, 33) de différentes tôles de sûreté (10, 20, 30) présentent des extensions longitudinales (L13, L23, L33) et/ou des largeurs différentes.
  6. Assortiment de tôles de sûreté selon l'une quelconque des revendications précédentes, dans lequel la barrette de liaison (13, 23, 33) des tôles de sûreté présente une zone de codage.
  7. Assortiment de tôles de sûreté selon la revendication précédente, dans lequel différentes tôles de sûreté présentent des zones de codage agencées de manière correspondante l'une de l'autre, dont le codage se distingue par le nombre et/ou la forme et/ou la grandeur de cavités et/ou de protubérances.
  8. Assortiment de tôles de sûreté selon l'une quelconque des revendications précédentes, dans lequel la zone de codage est agencée différemment de la zone fonctionnelle, en particulier à distance de celle-ci ou dans celle-ci.
  9. Turbine à gaz comprenant un assortiment de tôles de sûreté selon l'une quelconque des revendications précédentes avec au moins deux étages de turbine, dans lesquels sont agencées différentes tôles de sûreté (10, 20, 30) qui présentent différents codages géométriques.
  10. Procédé de montage d'un agencement de pales d'une turbine à gaz, dans lequel une tôle de sûreté (10, 20, 30) est choisie dans un assortiment de tôles de sûreté selon l'une quelconque des revendications 1 à 8 sur la base de son codage géométrique et est reliée à l'agencement de pales.
  11. Procédé selon la revendication 10, dans lequel :
    - à différents points de montage de la turbine sont affectées des tôles de sûreté (10, 20, 30) avec un codage géométrique différent et
    - des tôles de sûreté (10, 20, 30) sont choisies sur la base de leur codage géométrique et sont reliées au point de montage affecté sur la turbine.
  12. Procédé selon l'une quelconque des revendications 10 à 11, dans lequel, avant une localisation mutuelle de l'agencement de pales et de la tôle de sûreté (10, 20, 30), on vérifie si une tôle de sûreté (10,20, 30) affectée à cet agencement de pales a été montée.
  13. Procédé selon l'une quelconque des revendications 10 à 12, dans lequel la turbine à gaz présente au moins deux étages de turbine, auxquels différentes tôles de sûreté (10,20,30) sont affectées.
EP13162839.8A 2013-04-09 2013-04-09 Assortiment des tôles de serrage, moteur à turbine à gaz et procédé de montage associés Active EP2789800B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
ES13162839.8T ES2630046T3 (es) 2013-04-09 2013-04-09 Surtido de chapas de sujeción, turbina de gas correspondiente y método de ensamblaje
EP13162839.8A EP2789800B1 (fr) 2013-04-09 2013-04-09 Assortiment des tôles de serrage, moteur à turbine à gaz et procédé de montage associés
US14/248,067 US9695699B2 (en) 2013-04-09 2014-04-08 Securing blade assortment

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13162839.8A EP2789800B1 (fr) 2013-04-09 2013-04-09 Assortiment des tôles de serrage, moteur à turbine à gaz et procédé de montage associés

Publications (2)

Publication Number Publication Date
EP2789800A1 EP2789800A1 (fr) 2014-10-15
EP2789800B1 true EP2789800B1 (fr) 2017-06-14

Family

ID=48049874

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13162839.8A Active EP2789800B1 (fr) 2013-04-09 2013-04-09 Assortiment des tôles de serrage, moteur à turbine à gaz et procédé de montage associés

Country Status (3)

Country Link
US (1) US9695699B2 (fr)
EP (1) EP2789800B1 (fr)
ES (1) ES2630046T3 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102013205948B4 (de) * 2013-04-04 2015-03-12 MTU Aero Engines AG Sicherungssystem und Verfahren zur Sicherung eines Befestigungsbereichs wenigstens einer Rotorschaufel oder eines Rotorschaufelsegments in einem Montagebereich eines Rotorgrundkörpers
US11339674B2 (en) 2018-08-14 2022-05-24 Rolls-Royce North American Technologies Inc. Blade retainer for gas turbine engine
US11702211B2 (en) * 2021-04-15 2023-07-18 B/E Aerospace, Inc. Headrest tilt mechanism utilizing gear reduction

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB691380A (en) * 1950-07-01 1953-05-13 Power Jets Res & Dev Ltd Improvements relating to bladed rotors for compressors, turbines or like apparatus
US2761648A (en) * 1951-09-18 1956-09-04 A V Roe Canada Ltd Rotor blade locking device
US2994507A (en) * 1959-01-23 1961-08-01 Westinghouse Electric Corp Blade locking structure
US3076634A (en) * 1959-06-12 1963-02-05 Ass Elect Ind Locking means for compressor and turbine blades
US3248081A (en) * 1964-12-29 1966-04-26 Gen Electric Axial locating means for airfoils
US3395891A (en) * 1967-09-21 1968-08-06 Gen Electric Lock for turbomachinery blades
US4846628A (en) * 1988-12-23 1989-07-11 United Technologies Corporation Rotor assembly for a turbomachine
DE4300773C1 (de) * 1993-01-14 1993-11-18 Mtu Muenchen Gmbh Einrichtung zur axialen Laufschaufelsicherung und zur Beseitigung von Rotorunwuchten für axial durchströmte Verdichter oder Turbinen
US5350279A (en) * 1993-07-02 1994-09-27 General Electric Company Gas turbine engine blade retainer sub-assembly
DE4430636C2 (de) * 1994-08-29 1997-01-23 Mtu Muenchen Gmbh Einrichtung zur Laufschaufelfixierung und zur Beseitigung von Rotorunwuchten bei axial durchströmten Verdichtern oder Turbinen von Gasturbinentriebwerken
GB2408296A (en) * 2003-11-22 2005-05-25 Rolls Royce Plc Compressor blade root retainer with integral sealing means to reduce axial leakage
US7806662B2 (en) * 2007-04-12 2010-10-05 Pratt & Whitney Canada Corp. Blade retention system for use in a gas turbine engine
EP2088287A1 (fr) * 2008-02-08 2009-08-12 Siemens Aktiengesellschaft Dispositif de sécurité axiale sur aubes mobiles d'un rotor d'une turbine à gaz

Non-Patent Citations (1)

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Title
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Also Published As

Publication number Publication date
EP2789800A1 (fr) 2014-10-15
US20140301853A1 (en) 2014-10-09
ES2630046T3 (es) 2017-08-17
US9695699B2 (en) 2017-07-04

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