EP1749970A2 - 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: EP1749970A2
Authority: EP; European Patent Office
Prior art keywords: platform; thickness; blade; buttress; point
Prior art date: 2005-08-03
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

EP06252876A

Other languages

German (de)

English (en)

Other versions

EP1749970B1 (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.)

RTX 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.)

2005-08-03

Filing date

2006-06-02

Publication date

2007-02-07

2006-06-02 Application filed by United Technologies Corp filed Critical United Technologies Corp

2007-02-07 Publication of EP1749970A2 publication Critical patent/EP1749970A2/fr

2010-05-26 Publication of EP1749970A3 publication Critical patent/EP1749970A3/fr

2015-05-13 Application granted granted Critical

2015-05-13 Publication of EP1749970B1 publication Critical patent/EP1749970B1/fr

Status Active legal-status Critical Current

2026-06-02 Anticipated expiration legal-status Critical

Links

210000003739 neck Anatomy 0.000 description 6
241000289371 Ornithorhynchus anatinus Species 0.000 description 2
230000015572 biosynthetic process Effects 0.000 description 1
238000005266 casting Methods 0.000 description 1
238000010276 construction Methods 0.000 description 1

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 of the present invention is provided with a system for redistributing a load path away from the buttress portion of the turbine blade.
a blade which broadly comprises a platform, an airfoil portion extending radially from a first side of the platform, and an attachment portion extending from a second side of the platform.
the attachment portion includes a buttress which abuts said second side of the platform.
the blade is provided with means for redistributing loads away from the buttress.
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)

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 true EP1749970A2 (fr)	2007-02-07
EP1749970A3 EP1749970A3 (fr)	2010-05-26
EP1749970B1 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)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
EP2372102A3 (fr) *	2010-04-02	2014-11-05	United Technologies Corporation	Plate-forme des pales de rotor d'une turbine à gaz
EP2396515B1 (fr) *	2010-01-16	2016-07-20	MTU Aero Engines GmbH	Aube mobile pour une turbomachine et turbomachine

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
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

Citations (1)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
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

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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
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

2005
- 2005-08-03 US US11/197,162 patent/US20070031260A1/en not_active Abandoned
2006
- 2006-04-24 TW TW095114575A patent/TW200710319A/zh unknown
- 2006-05-29 JP JP2006147671A patent/JP2007040295A/ja active Pending
- 2006-06-02 EP EP20060252876 patent/EP1749970B1/fr active Active
- 2006-06-02 CN CNA2006100887133A patent/CN1908379A/zh active Pending
- 2006-08-02 SG SG200605221-1A patent/SG130114A1/en unknown

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
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

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
EP2396515B1 (fr) *	2010-01-16	2016-07-20	MTU Aero Engines GmbH	Aube mobile pour une turbomachine et turbomachine
EP2372102A3 (fr) *	2010-04-02	2014-11-05	United Technologies Corporation	Plate-forme des pales de rotor d'une turbine à gaz
US9976433B2 (en)	2010-04-02	2018-05-22	United Technologies Corporation	Gas turbine engine with non-axisymmetric surface contoured rotor blade platform

Also Published As

Publication number	Publication date
US20070031260A1 (en)	2007-02-08
EP1749970B1 (fr)	2015-05-13
EP1749970A3 (fr)	2010-05-26
CN1908379A (zh)	2007-02-07
TW200710319A (en)	2007-03-16
JP2007040295A (ja)	2007-02-15
SG130114A1 (en)	2007-03-20

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2007-01-05	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
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2007-02-07	AX	Request for extension of the european patent	Extension state: AL BA HR MK YU
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2011-01-05	17P	Request for examination filed	Effective date: 20101125
2011-02-02	AKX	Designation fees paid	Designated state(s): DE GB
2014-12-15	GRAP	Despatch of communication of intention to grant a patent	Free format text: ORIGINAL CODE: EPIDOSNIGR1
2015-01-14	INTG	Intention to grant announced	Effective date: 20141215
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