EP1749970B1 - Extension de plateforme d'aube de turbine ayant une faible contrainte au niveau de son contrefort - Google Patents

Extension de plateforme d'aube de turbine ayant une faible contrainte au niveau de son contrefort Download PDF

Info

Publication number
EP1749970B1
EP1749970B1 EP20060252876 EP06252876A EP1749970B1 EP 1749970 B1 EP1749970 B1 EP 1749970B1 EP 20060252876 EP20060252876 EP 20060252876 EP 06252876 A EP06252876 A EP 06252876A EP 1749970 B1 EP1749970 B1 EP 1749970B1
Authority
EP
European Patent Office
Prior art keywords
platform
thickness
point
buttress
blade
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
EP20060252876
Other languages
German (de)
English (en)
Other versions
EP1749970A2 (fr
EP1749970A3 (fr
Inventor
Bryan P. Dube
Randall J. Butcher
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.)
Raytheon Technologies Corp
Original Assignee
United Technologies Corp
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 United Technologies Corp filed Critical United Technologies Corp
Publication of EP1749970A2 publication Critical patent/EP1749970A2/fr
Publication of EP1749970A3 publication Critical patent/EP1749970A3/fr
Application granted granted Critical
Publication of EP1749970B1 publication Critical patent/EP1749970B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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
    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow 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
    • 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
    • F05D2250/70—Shape

Definitions

  • the present invention relates to a turbine blade having a platform provided with additional material for reducing stress acting on the blade by distributing loads away from a buttress portion of the turbine blade.
  • the turbine blade 30 has a platform 32, an airfoil portion 34 (only a portion of which is shown) radially extending from the platform 32, and an attachment portion 36.
  • the attachment portion typically includes a dovetail portion 38 for connecting the blade 30 to a rotating disk (not shown), a neck portion 40, and a buttress portion 42 which extends between the neck portion 40 and an underside 44 of the platform 32.
  • the lower speeds and temperatures faced by certain blades allow the airfoil portion to have short root necks and buttresses that adjoin to serrations.
  • the buttress portion 42 serves to minimize secondary flow leakage. Blades which face higher stress and temperature have airfoils which use side plates to cover the leakage area between the buttress and the serrations.
  • Some turbine blades have a relatively large leading edge platform which is necessary to minimize flowpath leakage between the blade and vane.
  • the large overhang of the platform, high rotor speed, short root neck, and relatively high temperature create a stress concentration where the upper serration meets the suction side and pressure side buttresses.
  • a turbine blade having the features of the preamble of claim 1 is disclosed in US-B1-6506016 .
  • a turbine blade of the present invention is provided with a system for redistributing a load path away from the buttress portion of the turbine blade.
  • the turbine blade 100 has a platform 102, an airfoil portion 104 radially extending from a first side 106 of the platform 102, and an attachment portion 108 extending from a second side or underside 110 of the platform 102.
  • the attachment portion 108 includes a dovetail portion 112 for securing the turbine blade 100 in a slot (not shown) in a rotor (not shown), such as a disk.
  • the attachment portion 108 further includes a neck portion 114 between the dovetail portion 112 and the second side 110 of the platform 102.
  • the attachment portion 108 has a buttress 116 between the second side 110 of the platform 102 and the leading end of the neck portion 114. During operation, the buttress 116 as previously discussed is subject to stress.
  • the platform 102 has a leading edge 120, a suction side 122, a leading edge root face 123, and a pressure side 124.
  • the platform leading edge 120 has a thickness T1.
  • the suction side 122 and the pressure side 124 each have a thickness T2.
  • the platform further has a central longitudinal axis 126.
  • the leading edge of the platform 102 is provided with additional material 140 so as to redistribute the load away from the buttress 116 towards the center of the leading edge root face 123.
  • This additional material 140 is preferably the same material that is being used to form the platform 102 and the turbine blade 100.
  • the additional material 140 may be formed during the casting of the turbine blade 100.
  • the additional material 140 has a shape similar to that of a platypus bill.
  • FIG. 8 there is shown a contour map of an exemplary additional material formation which comprises a system for redistributing the loads away from the buttress 116.
  • the thicknesses of the additional material 140 for the various points 1 - 24 shown in FIG. 8 are listed in Table I. The thicknesses are given as normalized percentages with the largest thickness at the thickest point 5 being 100%.
  • TABLE I PT NO. 1 2 3 4 5 6 7 8 THICKNESS 41.8 53.8 70.6 93.5 100 73.5 57.1 45.3 PT NO. 9 10 11 12 13 14 15 16 THICKNESS 34.1 43.5 52.4 57.7 55.9 48.2 38.8 31.2 PT NO. 17 18 19 20 21 22 23 24 THICKNESS 30.0 34.7 38.9 40.6 38.8 34.1 30.0 27.1
  • the thicknesses 1 - 24 are taken along three lines A, B, and C in the region between the front root face 121 and the leading edge 120.
  • Line A is located closest to the buttress 116 at a normalized distance of about 13.51% from the front root face 121.
  • Line B is located at a normalized distance of about 47.30% from the front root face 121 and line C is located at a normalized distance of about 88.59% from the front root face 121.
  • the thickness of the additional material 140 on the second side 110 gradually increases from both the suction side 122 and the pressure side 124 towards a maximum point 5 (on line A), 13 (on line B), and 21 (on line C), which maximum point is preferably offset from the central longitudinal axis 126.
  • the thickness of the platform 102 on the second side 110 gradually increases from points along line C, nearest to the leading edge 120, to the point 5.
  • the additional material 140 is advantageous in that it distributes loads, both stress and strain, away from the buttress 116 towards the center of leading edge root face 123. This is different from conventional blades where the loads are funneled into the middle and distributed along the entire width of the leading edge of the platform.

Landscapes

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

Claims (15)

  1. Aube (100) utilisée dans un moteur de turbine à gaz, comprenant :
    une plateforme (102), une partie formant un profilé (104) s'étendant radialement à partir d'un premier côté (106) de la plateforme (102), et une partie de fixation (108) s'étendant à partir d'un deuxième côté (110) de la plateforme (102), ladite plateforme (102) présentant un côté de pression (124), un côté d'aspiration (122), un bord d'attaque (120) et une épaisseur (T1) au niveau dudit bord d'attaque (120) ;
    ladite partie de fixation (108) comprenant un contrefort (116) qui vient buter contre ledit deuxième côté (110) de la plateforme (102) ; et
    caractérisée par :
    ledit deuxième côté (110) comprend un moyen (140) pour redistribuer la charge à l'écart du contrefort (116), ledit moyen comprenant une configuration délimitée où une épaisseur augmente d'un côté de pression ou d'une aspiration de la plateforme et comprenant une première région ayant une première épaisseur supérieure à ladite épaisseur (T1) au niveau dudit bord d'attaque et une deuxième région ayant une deuxième épaisseur supérieure à ladite première épaisseur.
  2. Aube selon la revendication 1, dans laquelle ladite plateforme (102) a un côté d'aspiration (122) et un côté de pression (124), et où ledit moyen (140) de redistribution des charges comprend un moyen servant à diriger la charge vers l'extérieur vers un centre d'une face d'embase de bord d'attaque (123).
  3. Aube selon la revendication 1 ou 2, dans laquelle ladite plateforme (102) a un axe central longitudinal (126) et où lesdites première et deuxième régions sont décalées de l'axe central longitudinal (126).
  4. Aube selon la revendication 3, dans laquelle ladite première région est proche du bord d'attaque (120) de ladite plateforme et où ladite deuxième région vient en butée contre ledit contrefort (116).
  5. Aube selon l'une quelconque des revendications précédentes, dans laquelle le côté d'aspiration (122) a une épaisseur (T2) et où ledit moyen de redistribution de ladite charge comprend une troisième région décalée d'un point central dudit contrefort (116) et où ladite épaisseur de ladite troisième région est supérieure à ladite épaisseur (T2) au niveau dudit côté d'aspiration (122).
  6. Aube selon la revendication 5, dans laquelle ladite plateforme (102) a une épaisseur qui augmente du côté d'aspiration (122) à ladite troisième région.
  7. Aube selon la revendication 5 ou 6, dans laquelle ledit côté de pression (124) a une épaisseur (T2) et où ladite épaisseur au niveau de ladite troisième région est supérieure à ladite épaisseur (T2) au niveau dudit côté de pression (124).
  8. Aube selon la revendication 7, dans laquelle ladite épaisseur de ladite plateforme (102) augmente du côté de pression (124) à ladite troisième région.
  9. Aube selon l'une quelconque des revendications précédentes, dans laquelle ledit moyen de redistribution des charges comprend un matériau supplémentaire (140) situé sur le deuxième côté (110) de la plateforme (102).
  10. Aube selon l'une quelconque des revendications précédentes, dans laquelle ledit deuxième côté (110) est un côté inférieur de ladite plateforme (102).
  11. Aube selon la revendication 1, dans laquelle
    ladite partie de fixation (108) comprend une partie à collet (114) s'étendant à partir du deuxième côté (110) de ladite plateforme (102) ; et
    ledit contrefort (116) est positionné à côté d'une intersection de ladite partie à collet (114) et dudit deuxième côté (110) ;
    et ledit moyen de redistribution des charges comprend un matériau supplémentaire (140) formé sur le deuxième côté (110) de ladite plateforme (102).
  12. Aube de turbine selon la revendication 11, comprenant en outre :
    ledit matériau supplémentaire (140) commençant en un premier point à proximité dudit bord d'attaque (120) et dont l'épaisseur augmente vers un deuxième point venant en butée contre ledit contrefort (116) ;
    ledit matériau supplémentaire (140) commençant en un troisième point adjacent audit côté d'aspiration (122) et augmentant en épaisseur dudit troisième point audit deuxième point ; et
    ledit matériau supplémentaire (140) commençant en outre au niveau d'un quatrième point adjacent audit côté de pression (124) et augmentant en épaisseur dudit quatrième point audit deuxième point.
  13. Aube de turbine selon la revendication 12, comprenant en outre le fait que ladite plateforme (102) comporte un axe longitudinal central (126) et ledit deuxième point étant décalé dudit axe longitudinal central (126).
  14. Aube de turbine selon la revendication 13, dans laquelle ledit premier point est décalé dudit axe longitudinal central (126).
  15. Aube de turbine selon l'une quelconque des revendications 11 à 14, dans lequel ladite partie de profilé (104) est une partie de profilé en surplomb.
EP20060252876 2005-08-03 2006-06-02 Extension de plateforme d'aube de turbine ayant une faible contrainte au niveau de son contrefort Active EP1749970B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11/197,162 US20070031260A1 (en) 2005-08-03 2005-08-03 Turbine airfoil platform platypus for low buttress stress

Publications (3)

Publication Number Publication Date
EP1749970A2 EP1749970A2 (fr) 2007-02-07
EP1749970A3 EP1749970A3 (fr) 2010-05-26
EP1749970B1 true EP1749970B1 (fr) 2015-05-13

Family

ID=37387422

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20060252876 Active EP1749970B1 (fr) 2005-08-03 2006-06-02 Extension de plateforme d'aube de turbine ayant une faible contrainte au niveau de son contrefort

Country Status (6)

Country Link
US (1) US20070031260A1 (fr)
EP (1) EP1749970B1 (fr)
JP (1) JP2007040295A (fr)
CN (1) CN1908379A (fr)
SG (1) SG130114A1 (fr)
TW (1) TW200710319A (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010004854A1 (de) * 2010-01-16 2011-07-21 MTU Aero Engines GmbH, 80995 Laufschaufel für eine Strömungsmaschine und Strömungsmaschine
US9976433B2 (en) * 2010-04-02 2018-05-22 United Technologies Corporation Gas turbine engine with non-axisymmetric surface contoured rotor blade platform
WO2019136672A1 (fr) * 2018-01-11 2019-07-18 贵州智慧能源科技有限公司 Plaque à rebord de pale de turbine basée sur une conception de courbe spline
FR3107301B1 (fr) * 2020-02-19 2022-03-11 Safran Aircraft Engines aube pour roue aubagée mobile de turbomachine d’aéronef comprenant un becquet d’étanchéité à section évolutive optimisée

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2807436A (en) * 1952-03-25 1957-09-24 Gen Motors Corp Turbine wheel and bucket assembly
US4259037A (en) * 1976-12-13 1981-03-31 General Electric Company Liquid cooled gas turbine buckets
GB2228541B (en) * 1989-02-23 1993-04-14 Rolls Royce Plc Device for damping vibrations in turbomachinery blades
US5302085A (en) * 1992-02-03 1994-04-12 General Electric Company Turbine blade damper
FR2712631B1 (fr) * 1993-11-19 1998-08-21 Gen Electric Ailette de rotor et ensemble ailettes-disque de rotor comportant une telle ailette.
FR2743845B1 (fr) * 1996-01-23 1998-02-20 Snecma Aube mobile de soufflante a profil de securite
US6158962A (en) * 1999-04-30 2000-12-12 General Electric Company Turbine blade with ribbed platform
US6511294B1 (en) * 1999-09-23 2003-01-28 General Electric Company Reduced-stress compressor blisk flowpath
US6561761B1 (en) * 2000-02-18 2003-05-13 General Electric Company Fluted compressor flowpath
US6422820B1 (en) * 2000-06-30 2002-07-23 General Electric Company Corner tang fan blade
US6506016B1 (en) * 2001-11-15 2003-01-14 General Electric Company Angel wing seals for blades of a gas turbine and methods for determining angel wing seal profiles
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

Also Published As

Publication number Publication date
SG130114A1 (en) 2007-03-20
TW200710319A (en) 2007-03-16
US20070031260A1 (en) 2007-02-08
EP1749970A2 (fr) 2007-02-07
JP2007040295A (ja) 2007-02-15
CN1908379A (zh) 2007-02-07
EP1749970A3 (fr) 2010-05-26

Similar Documents

Publication Publication Date Title
US7549846B2 (en) Turbine blades
EP1726782B1 (fr) Configuration de l'arête aval d'une aube de turbine
US7845906B2 (en) Dual cut-back trailing edge for airfoils
US7351035B2 (en) Hollow rotor blade for the turbine of a gas turbine engine, the blade being fitted with a “bathtub”
US6669445B2 (en) Endwall shape for use in turbomachinery
JP4179921B2 (ja) 根元ノッチ付きタービンブレード
EP1561900B1 (fr) Circuit de refroidissement pour plate-forme d'aube de turbine
US7059834B2 (en) Turbine blade
EP1605137B1 (fr) Aube de rotor refroidie
EP1561904B1 (fr) Aube de turbine avec arêtes coupantes sur le talon
US20090257875A1 (en) Platformless turbine blade
US20020194733A1 (en) Method for repairing cracks in a turbine blade root trailing edge
EP2022941B1 (fr) Aube de turbine d'un moteur à turbine à gaz
EP1749970B1 (fr) Extension de plateforme d'aube de turbine ayant une faible contrainte au niveau de son contrefort
US7686582B2 (en) Radial split serpentine microcircuits
CA2746415A1 (fr) Aube de turbine avec plate-forme courbe
EP1887186B1 (fr) Refroidissement de bord d'attaque avec dispositif anti-coriolis à microcircuit
EP1262635B1 (fr) Aube variable pour turbo machines
US20050191182A1 (en) Turbine blade shroud cutter tip
US7399163B2 (en) Rotor blade for a compressor or a gas turbine
US7708528B2 (en) Platform mate face contours for turbine airfoils
CA2466797A1 (fr) Plate-forme d'aube de turbine pour un rendement ameliore en cas de detachement de l'aube
EP1234949A2 (fr) Configuration des entrées d'air de refroidissement dans le pied d'une aube
EP1618287B1 (fr) Aube de turbine avec parois de support arriere incurvees pour reduction de contrainte
KR20070016928A (ko) 낮은 버팀벽 응력을 위한 터빈 에어포일 플랫폼 플래티퍼스

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK YU

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK YU

17P Request for examination filed

Effective date: 20101125

AKX Designation fees paid

Designated state(s): DE GB

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20141215

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE GB

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602006045413

Country of ref document: DE

Effective date: 20150625

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602006045413

Country of ref document: DE

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20160216

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 602006045413

Country of ref document: DE

Representative=s name: SCHMITT-NILSON SCHRAUD WAIBEL WOHLFROM PATENTA, DE

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20190521

Year of fee payment: 14

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 602006045413

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210101

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20240521

Year of fee payment: 19