EP2520767A1 - Dispositif d'équilibrage d'une turbine à gaz - Google Patents

Dispositif d'équilibrage d'une turbine à gaz Download PDF

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Publication number
EP2520767A1
EP2520767A1 EP12003249A EP12003249A EP2520767A1 EP 2520767 A1 EP2520767 A1 EP 2520767A1 EP 12003249 A EP12003249 A EP 12003249A EP 12003249 A EP12003249 A EP 12003249A EP 2520767 A1 EP2520767 A1 EP 2520767A1
Authority
EP
European Patent Office
Prior art keywords
annular groove
balancing
rotor
tool
turbine
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
EP12003249A
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German (de)
English (en)
Other versions
EP2520767B1 (fr
Inventor
Sacha Pichel
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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.)
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Publication date
Application filed by Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2520767A1 publication Critical patent/EP2520767A1/fr
Application granted granted Critical
Publication of EP2520767B1 publication Critical patent/EP2520767B1/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
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • 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
    • F01D5/027—Arrangements for balancing

Definitions

  • the invention relates to a balancing device, in particular to a gas turbine balancing device, by means of which it is possible to make a balancing of the intermediate or high-pressure shaft in the mounted state of the gas turbine.
  • the balancing of the high and low pressure waves takes place in different steps.
  • the individual rotor drums are gewuchet.
  • material is generally taken at predetermined locations on the drum.
  • the balancing of the assembled individual drums takes place.
  • small corrections are then made on the low pressure shaft, e.g. by attaching weights to the freely accessible fan (fan). This is due to the lack of accessibility, not readily possible on the high pressure shaft.
  • the US 5,545,010 A describes a method of incorporating or removing weights from an additionally attached ring. Accessibility is established via the gas path.
  • the US 4,803,893 A describes a method in which in the disk contour of a turbine disk, an additional recess is provided in the special Balancing weights are mountable. Accessibility is not described here.
  • the invention has for its object to provide a gas turbine balancing device, which ensures a high degree of efficiency with a simple design and simple, reliable operation.
  • At least one annular groove extending in a radial plane to an engine axis is provided.
  • at least one balancing body is arranged in this at least one annular groove which is formed on the outer circumference of at least one high-pressure rotor of a high-pressure compressor.
  • the one or more balancing body according to the invention in the circumferential direction along the annular groove slidably and fixed in the respective desired position by means of a fixing device.
  • several such balancing bodies are used in order to be able to produce, for example, with two balancing bodies of the same mass by displacement, a counter imbalance of any size and direction.
  • the fixing device which is designed for example in the form of a screw (grub screw) or the like, can be actuated by means of a tool in the installed state of the gas turbine.
  • an access opening (borescope opening, mounting opening or the like) is particularly preferably used, so that additional adjustments of the engine housing are not or only to a limited extent required.
  • both the balancing body and the parts used for the fixing are designed to be captive.
  • the balancing body and the parts used for the fixing are designed to be captive.
  • the balancing device according to the invention can thus be formed in a preferred manner, without significant changes to existing components are required.
  • the annular groove can either be additionally introduced, but it is also possible to use an already existing groove, which is used for example for air extraction, with.
  • the inventive design it is also possible to pre-install balancing weights so that they must be moved only for fine balancing after assembly of the engine.
  • the balancing device according to the invention is thus repeatedly used and can be adjusted at any time. This proves to be particularly advantageous even if during operation of the Engine, for example, by wear or damage, imbalances occur that are to be compensated.
  • the Fig. 1 shows a schematic representation of a gas turbine engine according to the present invention.
  • the gas turbine engine 10 is an example of a turbomachine to which the invention may find application. However, it will be understood from the following that the invention can be used with other turbomachinery as well.
  • the engine 10 is conventionally formed and includes in the flow direction one after another an air inlet 11, a fan 12 circulating in a housing, an intermediate pressure compressor 13, a high pressure compressor 14, combustion chambers 15, a high pressure turbine 16, an intermediate pressure turbine 17 and a low pressure turbine 18 and an exhaust nozzle 19, which are all arranged around a central engine axis 1.
  • the intermediate pressure compressor 13 and the high pressure compressor 14 each include a plurality of stages, each of which includes a circumferentially extending array of fixed stationary vanes 20, commonly referred to as stator vanes, that radially inwardly from the engine casing 21 in an annular flow passage through the compressors 13, 14 protrude.
  • the compressors further include an array of compressor blades 22 projecting radially outwardly from a rotatable drum or disc 26 coupled to hubs 27 of the high pressure turbine 16 and the intermediate pressure turbine 17, respectively.
  • the turbine sections 16, 17, 18 have similar stages, comprising an array of fixed vanes 23 projecting radially inward from the housing 21 into the annular flow passage through the turbines 16, 17, 18, and a downstream array of turbine blades 24 projecting outwardly from a rotatable hub 27.
  • the compressor drum or compressor disk 26 and the vanes 22 disposed thereon and the turbine rotor hub 27 and the turbine blades 24 disposed thereon rotate about the engine axis 1 during operation.
  • a high-pressure rotor 31 comprises a profiled annular groove 29, which extends around its circumference and in which one or more balancing bodies 30 are inserted. These are displaceable along the annular groove 29.
  • the balancing body 30 comprises an internal thread 36, in which a clamping screw 32 (grub screw) is screwed.
  • a clamping screw 32 grub screw
  • FIGS. 2 and 3 also show an inner housing 38, which supports stator blades 40, and an outer housing 39.
  • Rotor blades 32 are mounted on the rotor 31 in the usual way, as known from the prior art.
  • the outer housing 39 has at least one access opening 35, through which a tool 33 can be inserted.
  • the tool 33 is formed, for example in the form of a screwdriver, to rotate the clamping screw 32.
  • an auxiliary tool 42 is provided, which is inserted into the access opening 35 and is supported in an opening 43 of the inner housing 38 to guide the tool 33.
  • the Fig. 3 shows a state in the balanced, mounted state in which the tool 33 and the auxiliary tool 42 have been removed.
  • a closure element 34 is inserted.
  • the Fig. 4 shows an embodiment in which the introduction of the tool 33 is effected by a slot 44, which is provided in the inner housing 38 for air extraction and can be shared.
  • the Fig. 5 shows a further embodiment in which the annular groove 29 at a joining region of two components 31 a, 31 b of the high-pressure rotor 31 is formed.
  • the annular groove 29 is in communication with an air removal opening 45, for example for turbine cooling, so that, apart from the structuring of the cross section of the annular groove 29, no further changes must be performed.
  • the invention thus provides a groove or an annular gap in the high pressure rotor of a turbine engine, in which the groove adapted balancing body are used.
  • the annular gap can in particular be combined with any required air withdrawals in the compressor rotor (eg for turbine cooling), as is often the case in modern compressors available. These are most easily realized by an annular gap that arises between two bolted parts (eg front and rear rotor drum).
  • the balancing bodies comprise an internal thread, in which a grub screw is screwed in to secure, which is supported against the rotor. The falling out of the screws can be prevented by a self-assurance or appropriate geometry.
  • these balancing bodies are then displaced or rotated in the circumferential direction in order to produce a suitable counterbalance.
  • the rotation of the balancing body takes place, for example. by retaining the same and relative rotation of the rotor.
  • auxiliary tool can be used. After mounting the grub screws, the auxiliary tool and the tool are removed and the cavity is closed with a plug (closure element), so that the tightness of the inner and outer housing is ensured.
  • the radially far outward and preferably centered between the bearings position of the balancing body used is vorteihaft to compensate for the residual imbalance. Even a small change in position leads to a relatively large influence on the imbalance at comparatively low mass of the balancing body.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP12003249.5A 2011-05-06 2012-05-03 dispositif de correction de balourd d'un rotor d'une turbine à gaz Active EP2520767B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102011100783A DE102011100783A1 (de) 2011-05-06 2011-05-06 Gasturbinenauswuchtvorrichtung

Publications (2)

Publication Number Publication Date
EP2520767A1 true EP2520767A1 (fr) 2012-11-07
EP2520767B1 EP2520767B1 (fr) 2018-02-14

Family

ID=46178382

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12003249.5A Active EP2520767B1 (fr) 2011-05-06 2012-05-03 dispositif de correction de balourd d'un rotor d'une turbine à gaz

Country Status (3)

Country Link
US (1) US9017029B2 (fr)
EP (1) EP2520767B1 (fr)
DE (1) DE102011100783A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015112344A1 (fr) * 2014-01-21 2015-07-30 United Technologies Corporation Structure et procédé d'équilibrage de moteur à turbine
EP3587733A1 (fr) * 2018-06-21 2020-01-01 United Technologies Corporation Système et procédé d'équilibrage d'un rotor dans un moteur assemblé

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB201409245D0 (en) * 2014-05-23 2014-07-09 Rolls Royce Plc Rotor balancing
GB201409242D0 (en) * 2014-05-23 2014-07-09 Rolls Royce Plc Screw tool
US10087785B2 (en) * 2015-02-09 2018-10-02 United Technologies Corporation Mid-turbine frame assembly for a gas turbine engine
US11105203B2 (en) * 2018-01-29 2021-08-31 Carrier Corporation High efficiency centrifugal impeller with balancing weights
DE102019111211A1 (de) * 2019-04-30 2020-11-05 Rolls-Royce Deutschland Ltd & Co Kg Vorrichtung zur Einstellung eines Wuchtzustandes eines rotierenden Teils eines Gasturbinentriebwerkes, ein Wuchtkörper und ein Gasturbinentriebwerk für ein Luftfahrzeug
JP7196120B2 (ja) * 2020-02-10 2022-12-26 三菱重工業株式会社 タービンホイール
FR3115823B1 (fr) * 2020-11-04 2022-09-30 Safran Aircraft Engines Modularite d’une turbomachine d’aeronef
US11732585B2 (en) * 2021-01-28 2023-08-22 General Electric Company Trapped rotatable weights to improve rotor balance
FR3135110A1 (fr) * 2022-04-29 2023-11-03 Safran Aircraft Engines Turbomachine aéronautique à dispositif d’équilibrage amélioré et procédé d’équilibrage de la turbomachine

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3985465A (en) * 1975-06-25 1976-10-12 United Technologies Corporation Turbomachine with removable stator vane
US4064762A (en) * 1975-04-28 1977-12-27 Stal-Laval Turbin Ab Method and apparatus for balancing a rotor
JPS5572937A (en) * 1978-11-29 1980-06-02 Hitachi Ltd Balance weight for rotary body
US4803893A (en) 1987-09-24 1989-02-14 United Technologies Corporation High speed rotor balance system
US4856964A (en) * 1988-06-03 1989-08-15 Westinghouse Electric Corp. Method and apparatus for balancing a turbine rotor
FR2630496A1 (fr) * 1988-04-20 1989-10-27 Snecma Dispositif de correction de balourd d'un rotor de turbomachine
US4898514A (en) 1987-10-27 1990-02-06 United Technologies Corporation Turbine balance arrangement with integral air passage
US5545010A (en) 1993-05-13 1996-08-13 Solar Turbines Incorporated Method and apparatus for trim balancing a gas turbine engine
US6279420B1 (en) * 1999-08-18 2001-08-28 General Electric Co. Balance weight for a rotary component in turbomachinery, methods of installation and installation tools
EP1602855A2 (fr) * 2004-06-01 2005-12-07 General Electric Company Dispositif de correction de balourd d'un rotor de turbine
EP1726780A2 (fr) * 2005-05-26 2006-11-29 Rolls-Royce Deutschland Ltd & Co KG Dispositif pour une correction de balourd de précision pour rotors de turbomachines

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3736811A (en) * 1971-08-19 1973-06-05 Gen Electric Balance weight attachment for turbine wheels
PL314191A1 (en) 1993-11-02 1996-09-02 Neurobiological Technologies Method of treating rheumatoid artritis
US8348616B2 (en) * 2009-06-16 2013-01-08 General Electric Company Trapped spring balance weight and rotor assembly
EP2397651A1 (fr) 2010-06-17 2011-12-21 Siemens Aktiengesellschaft Poids de correction de l'équilibre fournissant une masse constante

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4064762A (en) * 1975-04-28 1977-12-27 Stal-Laval Turbin Ab Method and apparatus for balancing a rotor
US3985465A (en) * 1975-06-25 1976-10-12 United Technologies Corporation Turbomachine with removable stator vane
JPS5572937A (en) * 1978-11-29 1980-06-02 Hitachi Ltd Balance weight for rotary body
US4803893A (en) 1987-09-24 1989-02-14 United Technologies Corporation High speed rotor balance system
US4898514A (en) 1987-10-27 1990-02-06 United Technologies Corporation Turbine balance arrangement with integral air passage
FR2630496A1 (fr) * 1988-04-20 1989-10-27 Snecma Dispositif de correction de balourd d'un rotor de turbomachine
US4856964A (en) * 1988-06-03 1989-08-15 Westinghouse Electric Corp. Method and apparatus for balancing a turbine rotor
US5545010A (en) 1993-05-13 1996-08-13 Solar Turbines Incorporated Method and apparatus for trim balancing a gas turbine engine
US6279420B1 (en) * 1999-08-18 2001-08-28 General Electric Co. Balance weight for a rotary component in turbomachinery, methods of installation and installation tools
EP1602855A2 (fr) * 2004-06-01 2005-12-07 General Electric Company Dispositif de correction de balourd d'un rotor de turbine
EP1726780A2 (fr) * 2005-05-26 2006-11-29 Rolls-Royce Deutschland Ltd & Co KG Dispositif pour une correction de balourd de précision pour rotors de turbomachines

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015112344A1 (fr) * 2014-01-21 2015-07-30 United Technologies Corporation Structure et procédé d'équilibrage de moteur à turbine
US10544679B2 (en) 2014-01-21 2020-01-28 United Technologies Corporation Turbine engine balancing structure and method
EP3587733A1 (fr) * 2018-06-21 2020-01-01 United Technologies Corporation Système et procédé d'équilibrage d'un rotor dans un moteur assemblé
US10954793B2 (en) 2018-06-21 2021-03-23 Raytheon Technologies Corporation System and method for balancing a rotor in an assembled engine

Also Published As

Publication number Publication date
EP2520767B1 (fr) 2018-02-14
US9017029B2 (en) 2015-04-28
US20120282082A1 (en) 2012-11-08
DE102011100783A1 (de) 2012-11-08

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