EP3018290A1 - Aube de turbine à gaz - Google Patents

Aube de turbine à gaz Download PDF

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Publication number
EP3018290A1
EP3018290A1 EP15190456.2A EP15190456A EP3018290A1 EP 3018290 A1 EP3018290 A1 EP 3018290A1 EP 15190456 A EP15190456 A EP 15190456A EP 3018290 A1 EP3018290 A1 EP 3018290A1
Authority
EP
European Patent Office
Prior art keywords
blade
groove
trailing edge
gas turbine
platform
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
EP15190456.2A
Other languages
German (de)
English (en)
Other versions
EP3018290B1 (fr
Inventor
Luc Gooren
Alwin Grijseels
Pim Goedhart
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.)
Sulzer Turbo Services Venlo BV
Original Assignee
Sulzer Turbo Services Venlo BV
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 Sulzer Turbo Services Venlo BV filed Critical Sulzer Turbo Services Venlo BV
Priority to EP15190456.2A priority Critical patent/EP3018290B1/fr
Publication of EP3018290A1 publication Critical patent/EP3018290A1/fr
Application granted granted Critical
Publication of EP3018290B1 publication Critical patent/EP3018290B1/fr
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
    • F01D5/30—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
    • F05D2260/00—Function
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction

Definitions

  • the invention relates to a gas turbine blade in accordance with the preamble of claim 1.
  • a gas turbine blade is described in US 6,390,775 B1 .
  • the said gas turbine blade comprises a blade platform having a blade trailing edge side, a blade convex side, a blade concave side and a blade leading edge side.
  • a blade profile portion is connected to the blade platform.
  • a groove is formed in the blade trailing edge side of the blade platform, wherein the groove runs form the blade concave side to the blade trailing edge side.
  • Such grooves are normally called an "undercut”.
  • the said groove begins on the blade concave side und exits on the blade trailing edge side.
  • the groove runs along a straight line and is at an angle of 90 degrees with respect to a mean camber line of a trailing edge of the blade profile portion.
  • the said groove results in a reduced mechanical and thermal stress condition in a root trailing edge of the blade profile portion and a higher stressed condition in the groove. This is possible because the groove is located in a region of cooler metal temperature having greater material fatigue strength.
  • the gas turbine blade comprises a blade platform having a blade trailing edge side, a blade convex side, a blade concave side and a blade leading edge side.
  • a blade profile portion is connected to the blade platform.
  • a groove is formed in the blade trailing edge side of the blade platform, wherein the groove runs form the blade concave side to the blade trailing edge side.
  • the groove comprises a first portion which is curved with respect to a mean camber line of a trailing edge of the blade profile portion. This leads advantageously to a very effective transfer of stress to the groove and so to a very low trailing edge stress.
  • the first portion of the groove in particular runs in a plane parallel to the surface of the blade platform. But it is also possible that the groove is inclined to said surface. Often the groove comprises not only the first portion, but also a second and perhaps a third portion. But it's also possible that the groove consists only of the first portion.
  • the first portion of the groove runs along a circular arc.
  • the radius of the circular arc in particular is between5 and 20 mm. This leads to a particularly low trailing edge stress.
  • the groove comprises a second portion which runs from the blade convex side to the blade concave side of the blade platform.
  • the second portion of the groove in particular is straight and has a constant depth between 2 and 15 mm.
  • the combination of the first and second portion of the groove leads to a particularly low trailing edge stress. It's also possible that the second portion of the groove is curved.
  • the second portion of the groove in particular has a constant height between 4 and 10 mm.
  • the second portion of the groove in particular runs in the same plane as the first portion of the groove. It's also possible that there is an third, intermediate section which connects the first and the second portion of the groove.
  • An inner part of the groove has for example a substantially round or elliptical cross-section
  • an outer part of the groove has for example a rectangular cross-section, whereby the outer and inner part of the groove merge into each other.
  • other forms of cross sections are also possible.
  • a gas turbine blade 10 comprises a blade platform 11 having a blade trailing edge side 12, a blade convex side 13 (not visible in Fig. 1 , see Fig. 2 ), a blade concave side 14 and a blade leading edge side 15.
  • a blade profile portion 16 is connected to the blade platform 11.
  • the sides of the blade platform 11 are labeled according to their position relative to the blade profile portion 16.
  • a groove 17 is provided in the blade platform 11, such that the groove runs from the blade concave side 14 to the blade convex side 13.
  • the groove 17 runs in a plane parallel to a surface 18 (see also Fig. 2 ) of the blade platform 11.
  • the groove 17 (indicated as a dotted line) comprises a first portion 19 and a second portion 20.
  • the first portion of the groove 19 begins at the blade concave side 14 and runs along a circular arc, so it is curved with respect to a mean camber line 21 of a trailing edge 22 of the blade profile portion 16.
  • the said circular arc has a radius R (see Fig. 3 ).
  • the radius R is for example between 5 and 20 mm.
  • the first portion of the groove 19 merges into the second portion of the groove 20 which ends at the blade convex side 13.
  • the second portion of the groove 20 runs in the same plane as the first portion of the groove 19. It has a depth t (see Fig. 3 or 4 ) which lies for example between 2 and 15 mm.
  • the second portion of the groove 20 has a cross-section which comprises an inner part 23 with a round cross-section and an outer part 24 with a rectangular cross section. It's also possible that the inner part of the cross section of the second portion of the groove has an elliptical cross section.
  • the second portion of the groove 20 has a height h in the direction of the blade profile portion 16) which lies for example between 4 and 10 mm.
  • the first portion of the groove 19 has similar cross sections, whereby different cross sections has different depths. The different depths are caused by different outer parts of the groove.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP15190456.2A 2014-11-05 2015-10-19 Aube de turbine à gaz Active EP3018290B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP15190456.2A EP3018290B1 (fr) 2014-11-05 2015-10-19 Aube de turbine à gaz

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP14191932 2014-11-05
EP15190456.2A EP3018290B1 (fr) 2014-11-05 2015-10-19 Aube de turbine à gaz

Publications (2)

Publication Number Publication Date
EP3018290A1 true EP3018290A1 (fr) 2016-05-11
EP3018290B1 EP3018290B1 (fr) 2019-02-06

Family

ID=51846553

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15190456.2A Active EP3018290B1 (fr) 2014-11-05 2015-10-19 Aube de turbine à gaz

Country Status (1)

Country Link
EP (1) EP3018290B1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2020153320A (ja) * 2019-03-20 2020-09-24 三菱日立パワーシステムズ株式会社 タービン翼およびガスタービン
CN114080489A (zh) * 2019-06-14 2022-02-22 赛峰飞机发动机公司 用于涡轮发动机的具有优化的根部的桨叶以及用于优化桨叶轮廓的方法

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6390775B1 (en) 2000-12-27 2002-05-21 General Electric Company Gas turbine blade with platform undercut
US20080063529A1 (en) * 2006-09-13 2008-03-13 General Electric Company Undercut fillet radius for blade dovetails
US20120251331A1 (en) * 2011-04-01 2012-10-04 Alstom Technology Ltd. Turbine Blade Platform Undercut

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6390775B1 (en) 2000-12-27 2002-05-21 General Electric Company Gas turbine blade with platform undercut
US20080063529A1 (en) * 2006-09-13 2008-03-13 General Electric Company Undercut fillet radius for blade dovetails
US20120251331A1 (en) * 2011-04-01 2012-10-04 Alstom Technology Ltd. Turbine Blade Platform Undercut

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2020153320A (ja) * 2019-03-20 2020-09-24 三菱日立パワーシステムズ株式会社 タービン翼およびガスタービン
KR20210124423A (ko) * 2019-03-20 2021-10-14 미츠비시 파워 가부시키가이샤 터빈 날개 및 가스 터빈
US20220154581A1 (en) * 2019-03-20 2022-05-19 Mitsubishi Power Ltd. Turbine blade and gas turbine
US11788417B2 (en) * 2019-03-20 2023-10-17 Mitsubishi Heavy Industries, Ltd. Turbine blade and gas turbine
JP7406920B2 (ja) 2019-03-20 2023-12-28 三菱重工業株式会社 タービン翼およびガスタービン
CN114080489A (zh) * 2019-06-14 2022-02-22 赛峰飞机发动机公司 用于涡轮发动机的具有优化的根部的桨叶以及用于优化桨叶轮廓的方法

Also Published As

Publication number Publication date
EP3018290B1 (fr) 2019-02-06

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