EP2011966A2 - Luftzuführvorrichtung für die Belüftung von Laufradschaufeln einer Niederdruckturbine eines Gasturbinenmotors - Google Patents

Luftzuführvorrichtung für die Belüftung von Laufradschaufeln einer Niederdruckturbine eines Gasturbinenmotors Download PDF

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Publication number
EP2011966A2
EP2011966A2 EP08159726A EP08159726A EP2011966A2 EP 2011966 A2 EP2011966 A2 EP 2011966A2 EP 08159726 A EP08159726 A EP 08159726A EP 08159726 A EP08159726 A EP 08159726A EP 2011966 A2 EP2011966 A2 EP 2011966A2
Authority
EP
European Patent Office
Prior art keywords
turbine
segments
drum
rim
ventilation air
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
EP08159726A
Other languages
English (en)
French (fr)
Other versions
EP2011966A3 (de
EP2011966B1 (de
Inventor
Didier Escure
Jacques Bart
Stéphane Rousselin
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Publication of EP2011966A2 publication Critical patent/EP2011966A2/de
Publication of EP2011966A3 publication Critical patent/EP2011966A3/de
Application granted granted Critical
Publication of EP2011966B1 publication Critical patent/EP2011966B1/de
Active 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
    • 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
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • 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

Definitions

  • the present invention relates to the field of turbomachines. It is aimed at ventilating low pressure turbine blades in a double-body gas turbine engine.
  • turbomachinery it is common to use air taken from the high-pressure compressor, HP, to cool rooms in a warmer environment.
  • HP high-pressure compressor
  • This can be HP turbine blade, disk bores, etc.
  • the low-pressure turbine, BP is part of the ventilated zones: in particular it is made that air comes to cool the blade attachments circulating between the blade root, its attachment and the rim of the disk.
  • the turbine section of a double-body gas turbine engine comprises a stage 2 of HP turbine and a set of LP turbines downstream of a distributor 4 disposed between the stage 2 and the first stage of the LP turbine.
  • the entire LP turbine is composed here of four disks bolted to form a module. Each disc has a ferrule on both sides of its plane. The ferrules of two adjacent discs are bolted together. Rectifiers 5 are interposed between the different stages.
  • the cells 31 are machined peripherally on the rim of the discs in which vanes 6 are slid and axially locked by an axial retention segment 8.
  • the segments have an arcuate shape and are arranged in abutment against a face of the disc rim between a hook 61 and the face 62 of the blade roots to which the hook is attached. They hold the blades against any axial displacement.
  • the segments are scalloped and slid into a peripheral groove 32.
  • the segment is first angularly offset to allow the blade roots to be inserted into their cell and then the segment is angularly displaced so that the peaks of the festooned portion are engaged between the face of the foot and the hook. each dawn. As the segment is retained in the groove, the assembly is immobilized axially.
  • the circulation of the ventilation air represented on the Figures 3 and 4 , which illustrate two different architectures of the prior art, comprises an air flow, illustrated by the arrow F, from the DBP1 distributor upstream of the first LP turbine stage which, for each stage, is guided between the shell V1 of the disc and the VE sealing ring, bypasses the axial retention segments 8 and reaches the fasteners of the turbine blades.
  • a drum is composed of two disks 11 and 12 connected by a shell 13 on which are formed the sealing elements 13E.
  • a ferrule 14 is secured to the downstream disc 12 and includes orifices 14A for the passage of fastening means, bolts not shown in the figure, to another group or adjacent disc.
  • ferrules for the sealing elements are not necessary since they are integrated with the drum.
  • the disks also have the same structure as in previous achievements and the assembly of the blades of the second stage of the group of this figure is also the same.
  • the applicant has set a goal to find a solution that would allow in the case of drum disks to perform the ventilation of the fasteners and the axial retention of the blades.
  • a ventilation air supply device in a turbine rotor of a gas turbine engine comprising a first and a second turbine disc and a ferrule downstream of the second disc together forming a one-piece drum, the second turbine disk comprising cells for housing the turbine blades, and the vanes being axially retained by axial retaining segments.
  • the device is characterized in that at least one hole is made in said ferrule placing the inside of the drum in communication with at least a portion of the cells by a passage through the segments.
  • the axial retaining segments comprise an annular channel open laterally on said bore and on the cells.
  • the segments comprise radial channels made in particular not machining.
  • the monobloc drum 10 comprises the discs 11 and 12 connected by a ferrule 13 and with a rear ferrule 14.
  • the elements are monoblock in that they are either machined to form a drum in one piece, or welded together.
  • the rim 12J of the disc 12 has axial recesses in which the feet 6P of the vanes 6 are slid axially. To wedge them axially, the blades comprise a hook 6B downstream of the rear transverse face 6A of the foot 6P.
  • a 12P bore is provided in the downstream wall of the disk rim 12J through the downstream ferrule 14. This drilling is radial, it puts in communication the internal drum volume and the bottom of a groove 12R '. This groove is open radially. It is formed between the rim 12J and a transverse flange parallel to the rim 12J.
  • the axial retention segments 18 are housed in this groove 12R '. These arcuate segments extend radially along the downstream face of the rim and mask the downstream faces 6A of the blade feet 6P. The segments are slid between the downstream face 6A 6P feet and their corresponding downstream hook. They block the feet of dawn in this way against any axial displacement.
  • the base 18B of the segments is thick and occupies in width the groove 12R '.
  • an annular channel 18C is machined in the thickness of the base 18B. This channel communicates the holes 12P with the bottom of the cells and thus forms a radial passage 18P and axial.
  • the air flows from the upstream zone of the turbine rotor. It passes through the stator 20 through a passage 20P and is divided into several streams.
  • the flow F1 is guided towards the passage formed between the shell and a flange for attaching the ferrule to the first disk 11 to ventilate the cells of the disk 11.
  • Another portion F2 of the flow passes between the central openings of two disks 11 and 12 , and the stator 20, goes up along the downstream face of the disk 12 and engages in the holes 12P.
  • the holes communicating with the bottom of the groove in line with the channel 18C, the air is found in the annular channel 18C where it is distributed in the existing spaces between the blade roots and the bottom of the cells. Leaving this space, the air is then guided into the gas vein.
  • the cost in mass is low or non-existent on the thickness of the base 18B.
  • the segment performs its function of axial retention without loss of efficiency.
  • This segment 18 ' instead of a continuous channel formed in the base 18'B, comprises a plurality of blind 18'C blinds machined in the mass of the base 18'B. These radial lunulas communicate on one side with the holes 12P and are open axially on the side of the face bearing against the rim 12J at the cell bottom. They form the passages 18'P. The ventilation of the blades of the blades is provided in the same way as before. The air from the upstream turbine distributor circulates inside the drum; part of this flow is driven through the holes 12P and is guided by the axial retention segments in the free spaces between the cell bottoms and the blade roots.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP08159726A 2007-07-06 2008-07-04 Luftzuführvorrichtung für die Belüftung von Laufradschaufeln einer Niederdruckturbine eines Gasturbinenmotors Active EP2011966B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0704918A FR2918414B1 (fr) 2007-07-06 2007-07-06 Dispositif d'alimentation en air de ventilation des aubes de turbine basse pression d'un moteur a turbine a gaz ; segment pour l'arret axial et la ventilation des aubes de turbine basse pression

Publications (3)

Publication Number Publication Date
EP2011966A2 true EP2011966A2 (de) 2009-01-07
EP2011966A3 EP2011966A3 (de) 2010-03-03
EP2011966B1 EP2011966B1 (de) 2012-03-28

Family

ID=39052417

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08159726A Active EP2011966B1 (de) 2007-07-06 2008-07-04 Luftzuführvorrichtung für die Belüftung von Laufradschaufeln einer Niederdruckturbine eines Gasturbinenmotors

Country Status (6)

Country Link
US (1) US8157506B2 (de)
EP (1) EP2011966B1 (de)
JP (1) JP5035146B2 (de)
CA (1) CA2636665C (de)
FR (1) FR2918414B1 (de)
RU (1) RU2481481C2 (de)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2965291A1 (fr) * 2010-09-27 2012-03-30 Snecma Ensemble unitaire de disques de rotor pour une turbomachine
FR2973433A1 (fr) * 2011-04-04 2012-10-05 Snecma Rotor de turbine pour une turbomachine
FR2995021A1 (fr) * 2012-09-04 2014-03-07 Snecma Dispositif d'alimentation en air pour turbines de moteurs d'aeronefs
EP3026217A1 (de) * 2014-11-07 2016-06-01 United Technologies Corporation Segmentierte turbinenrotor/stator-seitenplatten mit drehverhinderung
EP3075952A1 (de) * 2015-03-31 2016-10-05 United Technologies Corporation Sicherungsringe für turbomaschinenplatte und abdeckplattenanordnungen
EP3124742A1 (de) * 2015-07-28 2017-02-01 MTU Aero Engines GmbH Gasturbine
FR3062677A1 (fr) * 2017-02-07 2018-08-10 Safran Aircraft Engines Turboreacteur a double flux comprenant un distributeur precedant deux etages de turbines basse pression qui sont ventiles par de l'air de refroidissement du distributeur

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2958322B1 (fr) * 2010-04-01 2013-03-15 Snecma Rotor de moteur a turbine a gaz comprenant un tambour de rotor et une couronne de rotor
FR2963806B1 (fr) * 2010-08-10 2013-05-03 Snecma Dispositif de blocage d'un pied d'une aube de rotor
US10001061B2 (en) * 2014-06-06 2018-06-19 United Technologies Corporation Cooling system for gas turbine engines
EP3141698A1 (de) * 2015-09-10 2017-03-15 Siemens Aktiengesellschaft Anordnung für eine gasturbine
JP6554736B2 (ja) 2015-10-23 2019-08-07 三菱日立パワーシステムズ株式会社 ガスタービンロータ、ガスタービン、及びガスタービン設備
JP6773404B2 (ja) 2015-10-23 2020-10-21 三菱パワー株式会社 圧縮機ロータ、これを備えるガスタービンロータ、及びガスタービン
FR3062415B1 (fr) * 2017-02-02 2019-06-07 Safran Aircraft Engines Rotor de turbine de turbomachine a ventilation par lamage

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GB612097A (en) * 1946-10-09 1948-11-08 English Electric Co Ltd Improvements in and relating to the cooling of gas turbine rotors
US3356339A (en) * 1966-12-12 1967-12-05 Gen Motors Corp Turbine rotor
JPH07324632A (ja) * 1994-05-30 1995-12-12 Mitsubishi Heavy Ind Ltd ガスタービン動翼の冷却空気シール装置
US5932940A (en) * 1996-07-16 1999-08-03 Massachusetts Institute Of Technology Microturbomachinery
DE19950109A1 (de) * 1999-10-18 2001-04-19 Asea Brown Boveri Rotor für eine Gasturbine
FR2825748B1 (fr) * 2001-06-07 2003-11-07 Snecma Moteurs Agencement de rotor de turbomachine a deux disques aubages separes par une entretoise
RU2230195C2 (ru) * 2002-05-30 2004-06-10 Открытое акционерное общество "Авиадвигатель" Ротор многоступенчатой турбины
US7192244B2 (en) * 2004-02-23 2007-03-20 Grande Iii Salvatore F Bladeless conical radial turbine and method
GB2420155B (en) * 2004-11-12 2008-08-27 Rolls Royce Plc Turbine blade cooling system
FR2892454B1 (fr) * 2005-10-21 2008-01-25 Snecma Sa Dispositif de ventilation de disques de turbine dans un moteur a turbine a gaz
GB0603030D0 (en) * 2006-02-15 2006-03-29 Rolls Royce Plc Gas turbine engine rotor ventilation arrangement

Non-Patent Citations (1)

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Title
None

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2965291A1 (fr) * 2010-09-27 2012-03-30 Snecma Ensemble unitaire de disques de rotor pour une turbomachine
FR2973433A1 (fr) * 2011-04-04 2012-10-05 Snecma Rotor de turbine pour une turbomachine
US9920690B2 (en) 2012-09-04 2018-03-20 Snecma Air supply device for aircraft engine turbines
FR2995021A1 (fr) * 2012-09-04 2014-03-07 Snecma Dispositif d'alimentation en air pour turbines de moteurs d'aeronefs
WO2014037664A1 (fr) * 2012-09-04 2014-03-13 Snecma Dispositif d'alimentation en air pour turbines de moteurs d'aeronefs
GB2520212A (en) * 2012-09-04 2015-05-13 Snecma Air supply device for aircraft engine turbines
GB2520212B (en) * 2012-09-04 2017-06-28 Snecma Air supply device for aircraft engine turbines
EP3026217A1 (de) * 2014-11-07 2016-06-01 United Technologies Corporation Segmentierte turbinenrotor/stator-seitenplatten mit drehverhinderung
US10408087B2 (en) 2014-11-07 2019-09-10 United Technologies Corporation Turbine rotor segmented sideplates with anti-rotation
EP3075952A1 (de) * 2015-03-31 2016-10-05 United Technologies Corporation Sicherungsringe für turbomaschinenplatte und abdeckplattenanordnungen
US9732619B2 (en) 2015-03-31 2017-08-15 United Technologies Corporation Retaining rings for turbomachine disk and coverplate assemblies
EP3124742A1 (de) * 2015-07-28 2017-02-01 MTU Aero Engines GmbH Gasturbine
US10428656B2 (en) 2015-07-28 2019-10-01 MTU Aero Engines AG Gas turbine
FR3062677A1 (fr) * 2017-02-07 2018-08-10 Safran Aircraft Engines Turboreacteur a double flux comprenant un distributeur precedant deux etages de turbines basse pression qui sont ventiles par de l'air de refroidissement du distributeur

Also Published As

Publication number Publication date
RU2481481C2 (ru) 2013-05-10
FR2918414B1 (fr) 2013-04-12
EP2011966A3 (de) 2010-03-03
JP5035146B2 (ja) 2012-09-26
US8157506B2 (en) 2012-04-17
CA2636665A1 (fr) 2009-01-06
RU2008127152A (ru) 2010-01-10
CA2636665C (fr) 2015-02-24
FR2918414A1 (fr) 2009-01-09
US20090304495A1 (en) 2009-12-10
JP2009013981A (ja) 2009-01-22
EP2011966B1 (de) 2012-03-28

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