EP0609979A1 - Rotor équilibré pour une turbine à gaz - Google Patents

Rotor équilibré pour une turbine à gaz Download PDF

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Publication number
EP0609979A1
EP0609979A1 EP94300104A EP94300104A EP0609979A1 EP 0609979 A1 EP0609979 A1 EP 0609979A1 EP 94300104 A EP94300104 A EP 94300104A EP 94300104 A EP94300104 A EP 94300104A EP 0609979 A1 EP0609979 A1 EP 0609979A1
Authority
EP
European Patent Office
Prior art keywords
rotor
plates
retention
retention plates
balanced 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.)
Withdrawn
Application number
EP94300104A
Other languages
German (de)
English (en)
Inventor
Roy Talbot Hirst
Peter Broadhead
Mark Halliwell
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 PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Publication of EP0609979A1 publication Critical patent/EP0609979A1/fr
Withdrawn legal-status Critical Current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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • 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

  • This invention relates to a balanced rotor which is suitable for use in a gas turbine engine.
  • Gas turbine engines commonly include an axial flow turbine having at least one rotor which comprises a disc, the radially outer periphery of which carries a plurality of aerofoil blades.
  • Each aerofoil blade has a root portion, often of fir-tree type cross-sectional configuration, which locates in a correspondingly shaped, axially extending slot provided in the disc periphery.
  • balance weights are attached to a suitable support structure which is itself either attached to the disc or is an integral part of the disc.
  • balance weights While the use of such balance weights is effective in achieving rotor balance, it does of course result in the rotor being more expensive to manufacture and slightly heavier than it would otherwise be the case were balancing not required.
  • a balanced rotor suitable for a gas turbine engine comprises a disc carrying an annular array of radially extending aerofoil blades on its periphery, each of said blades having a root portion slidingly located in a correspondingly shaped generally axially extending retention groove provided in said disc periphery, said rotor additionally including a plurality of generally similar retention plates so located thereon and attached thereto as to provide axial retention of said aerofoil blades on said disc, the majority of said plates being substantially equal in weight to each other, each of the remaining plates being of different weight to each of said plates in the majority, said plates of different weight being so distributed on said rotor as to ensure its balance.
  • Fig 1 is a schematic sectioned side view of a ducted fan gas turbine engine which incorporates a balanced rotor in accordance with the present invention.
  • Fig 2 is a sectioned side view of a portion of a balanced rotor in accordance with the present invention.
  • Fig 3 is a partially exploded view of a balanced rotor in accordance with the present invention.
  • a ducted fan gas turbine engine generally indicated at 10 is of conventional configuration. It comprises, in axial flow series, an air inlet 11, a fan 12 contained within a duct 13, an intermediate pressure compressor 14, a high pressure compressor 15, combustion equipment 16, high, intermediate and low pressure turbines 17, 18 and 19 respectively and an exhaust nozzle 20.
  • the turbines 19, 18 and 17 respectively drive the fan 12, intermediate pressure compressor 14 and high pressure compressor 15 by concentric shafts extending along the central axis of the engine 10.
  • Air drawn in through the air inlet 11 by the fan 12 is divided into two flows.
  • the first flow is exhausted from the fan duct 13 to provide propulsive thrust.
  • the second flow is directed into the intermediate pressure compressor 14 where compression of the air takes place.
  • the air is then directed into the high pressure compressor 15 where further compression of the air takes place before it is directed into the combustion equipment 16.
  • There the air is mixed with fuel and the mixture combusted.
  • the resultant hot gaseous combustion products then expand through, and thereby drive, the high, intermediate and low pressure turbines 17, 18 and 19 respectively.
  • the combustion products are exhausted through the nozzle 20 to provide additional propulsive thrust.
  • the intermediate pressure turbine 18 includes a rotor 21, part of which can be seen more clearly if reference is now made to Figs 2 and 3.
  • the rotor 21 comprises a disc 22 which carries an annular array of similar aerofoil blades 23.
  • Each aerofoil blade 23 comprises an aerofoil portion 24 which is acted upon by the gaseous flow through the intermediate pressure turbine 18.
  • each aerofoil portion 24 there is provided a shroud 25.
  • the shrouds 25 of adjacent aerofoil blades abut each other so that they cooperate to define an annular barrier to inhibit gas leakage over the radially outer extents of the blades 23.
  • each aerofoil blade 23 there is provided a platform 26.
  • the platforms 26 of adjacent aerofoil blades cooperate to define an annular portion of the radially inner boundary of the gaseous flow through the intermediate pressure turbine 18.
  • each platform 26 Radially inwardly of each platform 26 there is provided a root 27 which is of the so-called fir-tree cross-section configuration.
  • Each blade root 27 locates in a correspondingly shaped axially extending retention groove 28 provided in the periphery of the disc 22.
  • a step (not shown) provided at one end of each groove 28 prevents axial movement of the aerofoil blades 23 in one axial direction. Movement in the opposite direction is prevented by a plurality of generally similar circumferentially arcuate retention plates 29.
  • the retention plates 29 are arranged in an annular array to cover the ends of the blade roots 27. Each retention plate 29 is maintained in position on the disc 22 by its location in grooves provided in the disc 22 and the blade platforms 26.
  • each retention plate 29 locates in a radially outwardly directed annular groove 30 provided in an annular axially extending flange 31 on the disc 22.
  • the radially outer edge of each retention plate 29 locates in a radially inwardly directed annular groove 32 defined by individual grooves in each blade platform 26.
  • the majority of the retention plates 29, for instance 36, are planar and can be readily manoeuvred into position in the grooves 30 and 32. This can be achieved, for instance, by leaving out some of the aerofoil blades 23 and sliding the retention plates 29 along the grooves 30 and 32. However the remainder of the retention plates 29 cannot be so positioned once all of the aerofoil blades 23 are correctly positioned on the disc 22.
  • the remaining retention plates 29, which may amount to nine plates are not flat but are of slightly curved configuration as can be seen from the floating plate 29 shown in Fig 3. This slight curving of these retention plates 29 enables them to be positioned with their radially inner and outer edges adjacent the grooves 30 and 32. They are then flattened, by for instance hammering, so that their radially inner and outer edges enter and are engaged within the grooves 30 and 32.
  • Each of the retention plates is approximately 3 cms wide radially and 5 cms long circumferentially. Those retention plates 29 which are in the majority are approximately 1.5 mm thick. However the retention plates 29 which are in the minority, that is the slightly curved plates 29, are only 1 mm thick. They are, therefore slightly lighter than the majority of the retention plates 29. This feature of the thinner plates 29 is put to use in the balancing of the rotor 21.
  • the whole assembly is put on a suitable balancing machine.
  • the slightly thinner retention plates 29 are then temporarily positioned on the disc 22, by for instance the use of adhesive tape. Balancing is then carried out; the retention plates 29 being moved around the disc 22 periphery until balance is achieved.
  • the slightly thinner retention plates 29 are then fixed in their appropriate positions by being flattened as described earlier.
  • retention plates 29 in the minority have been described as being slightly thinner than the remainder, it will be appreciated that this need not necessarily be the only way of achieving weight variation in the plates 29. Thus other material or configurational changes could be utilised. Moreover the retention plates 29 in the minority could be heavier, not lighter than the remaining plates 29.
  • the important feature of the retention plates 29 in the minority is that they should be of different weight to the majority of the retention plates 29 to permit the achievement of balance.
  • the present invention provides a balanced rotor 21 without the need for the disc 22 to be adapted to carry dedicated balance weights. Such adaptation increases manufacturing costs and adds undesirable weight to the whole rotor assembly 21.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP94300104A 1993-02-03 1994-01-07 Rotor équilibré pour une turbine à gaz Withdrawn EP0609979A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB939302064A GB9302064D0 (en) 1993-02-03 1993-02-03 Balanced rotor
GB9302064 1993-02-03

Publications (1)

Publication Number Publication Date
EP0609979A1 true EP0609979A1 (fr) 1994-08-10

Family

ID=10729742

Family Applications (1)

Application Number Title Priority Date Filing Date
EP94300104A Withdrawn EP0609979A1 (fr) 1993-02-03 1994-01-07 Rotor équilibré pour une turbine à gaz

Country Status (3)

Country Link
EP (1) EP0609979A1 (fr)
JP (1) JPH06280502A (fr)
GB (1) GB9302064D0 (fr)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0761930A1 (fr) * 1995-08-24 1997-03-12 ROLLS-ROYCE plc Segments d'étanchéité et de rétention pour les aubes d'une turbomachine
GB2396389A (en) * 2002-12-20 2004-06-23 Rolls Royce Plc Blade arrangement for a gas turbine engine
WO2007014543A1 (fr) * 2005-07-30 2007-02-08 Mtu Aero Engines Gmbh Element de fixation d'aubes mobiles
WO2012028653A3 (fr) * 2010-09-03 2012-04-26 Siemens Aktiengesellschaft Joints de blocage axiaux pour pale de turbine arrière amovible
GB2506712A (en) * 2013-05-14 2014-04-09 Rolls Royce Plc Static balancing of retaining plates using dedicated weighing disc
GB2511584A (en) * 2013-05-31 2014-09-10 Rolls Royce Plc A lock plate
EP2792849A1 (fr) * 2014-05-30 2014-10-22 Rolls-Royce plc Perfectionnements à ou se rapportant à l'équilibrage d'un rotor
EP2940249A1 (fr) * 2014-04-29 2015-11-04 Siemens Aktiengesellschaft Agencement de disque de roue et procédé de montage d'un agencement de disque de roue
US9624775B2 (en) 2014-05-30 2017-04-18 Rolls-Royce Plc Developments in or relating to rotor balancing

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1916389A1 (fr) * 2006-10-26 2008-04-30 Siemens Aktiengesellschaft Assemblage d'aubes de turbine
FR2918106B1 (fr) * 2007-06-27 2011-05-06 Snecma Dispositif de retenue axiale d'aubes montees sur un disque de rotor de turbomachine.

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3077811A (en) * 1960-08-08 1963-02-19 Ca Nat Research Council Continuous retaining ring adapted for radial expansion
GB1095830A (en) * 1966-09-13 1967-12-20 Rolls Royce Bladed rotor for a fluid flow machine such as a gas turbine engine
DE1928184A1 (de) * 1968-06-24 1970-01-08 Westinghouse Electric Corp Befestigungs- und Kuehlanordnung fuer Laufschaufelkraenze von Turbomaschine,vorzugsweise Gasturbinen
US3888601A (en) * 1974-05-23 1975-06-10 Gen Electric Turbomachine with balancing means
GB2105790A (en) * 1981-09-15 1983-03-30 Rolls Royce Balanced bladed rotor

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3077811A (en) * 1960-08-08 1963-02-19 Ca Nat Research Council Continuous retaining ring adapted for radial expansion
GB1095830A (en) * 1966-09-13 1967-12-20 Rolls Royce Bladed rotor for a fluid flow machine such as a gas turbine engine
DE1928184A1 (de) * 1968-06-24 1970-01-08 Westinghouse Electric Corp Befestigungs- und Kuehlanordnung fuer Laufschaufelkraenze von Turbomaschine,vorzugsweise Gasturbinen
US3888601A (en) * 1974-05-23 1975-06-10 Gen Electric Turbomachine with balancing means
GB2105790A (en) * 1981-09-15 1983-03-30 Rolls Royce Balanced bladed rotor

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0761930A1 (fr) * 1995-08-24 1997-03-12 ROLLS-ROYCE plc Segments d'étanchéité et de rétention pour les aubes d'une turbomachine
GB2396389A (en) * 2002-12-20 2004-06-23 Rolls Royce Plc Blade arrangement for a gas turbine engine
US6971855B2 (en) 2002-12-20 2005-12-06 Rolls-Royce Plc Blade arrangement for gas turbine engine
GB2396389B (en) * 2002-12-20 2006-01-18 Rolls Royce Plc Blade arrangement for gas turbine engine
WO2007014543A1 (fr) * 2005-07-30 2007-02-08 Mtu Aero Engines Gmbh Element de fixation d'aubes mobiles
US8128374B2 (en) 2005-07-30 2012-03-06 Mtu Aero Engines Gmbh Securing element for fastening rotor blades
WO2012028653A3 (fr) * 2010-09-03 2012-04-26 Siemens Aktiengesellschaft Joints de blocage axiaux pour pale de turbine arrière amovible
US9109457B2 (en) 2010-09-03 2015-08-18 Siemens Energy, Inc. Axial locking seals for aft removable turbine blade
EP2803867A3 (fr) * 2013-05-14 2015-06-17 Rolls-Royce plc Procédé d'équilibrage
GB2506712A (en) * 2013-05-14 2014-04-09 Rolls Royce Plc Static balancing of retaining plates using dedicated weighing disc
GB2506712B (en) * 2013-05-14 2018-05-02 Rolls Royce Plc Balancing method
EP2808489A1 (fr) * 2013-05-31 2014-12-03 Rolls-Royce plc Plaque de verrouillage
GB2511584B (en) * 2013-05-31 2015-03-11 Rolls Royce Plc A lock plate
GB2511584A (en) * 2013-05-31 2014-09-10 Rolls Royce Plc A lock plate
US9695700B2 (en) 2013-05-31 2017-07-04 Rolls-Royce Plc Lock plate
EP2940249A1 (fr) * 2014-04-29 2015-11-04 Siemens Aktiengesellschaft Agencement de disque de roue et procédé de montage d'un agencement de disque de roue
EP2792849A1 (fr) * 2014-05-30 2014-10-22 Rolls-Royce plc Perfectionnements à ou se rapportant à l'équilibrage d'un rotor
US9624775B2 (en) 2014-05-30 2017-04-18 Rolls-Royce Plc Developments in or relating to rotor balancing

Also Published As

Publication number Publication date
GB9302064D0 (en) 1993-03-24
JPH06280502A (ja) 1994-10-04

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Inventor name: HALLIWELL, MARK

Inventor name: BROADHEAD, PETER

Inventor name: HIRST, ROY TALBOT