EP1898049A1 - Turbinenschaufel - Google Patents

Turbinenschaufel Download PDF

Info

Publication number: EP1898049A1
Authority: EP; European Patent Office
Prior art keywords: section; turbine blade; root; platform; leading
Prior art date: 2006-09-11
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

EP06019003A

Other languages

English (en)

French (fr)

Other versions

EP1898049B1 (de

Inventor

Adrian Brathwaite

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.)

Siemens AG

Original Assignee

Siemens AG

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.)

2006-09-11

Filing date

2006-09-11

Publication date

2008-03-12

2006-09-11 Application filed by Siemens AG filed Critical Siemens AG

2006-09-11 Priority to EP20060019003 priority Critical patent/EP1898049B1/de

2008-03-12 Publication of EP1898049A1 publication Critical patent/EP1898049A1/de

2012-05-23 Application granted granted Critical

2012-05-23 Publication of EP1898049B1 publication Critical patent/EP1898049B1/de

Status Expired - Fee Related legal-status Critical Current

2026-09-11 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
- 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
- F05D2250/71—Shape curved
- 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 present invention relates to a turbine blade comprising a platform section, an airfoil section and a root section.
the platform section has a first side, a second side opposite the first side, and, extending from the first side to the second side, a leading side, a trailing side and peripheral sides extending from the leading side to the trailing side.
An airfoil section extends from the platform section's first side, and a root section extends from the platform section's second side. The root section and the peripheral sides of the platform section follow a curved path.
the inventive turbine blade comprises a platform section, an airfoil section and a root section.
the platform section has a first side, a second side opposite to the first side, and, extending from the first side to the second side, a leading side, a trailing side and peripheral sides.
the peripheral sides extend along a curved path from the leading side to the trailing side.
an airfoil section extends from the first side of the platform section and a root section extends from the second side of the platform section.
the root section of the turbine blade extends along a path from the leading side to the trailing side that is straight or has a curvature which is different to the curvature of said curved path.
the centrifugal force is not strong enough to hold the roots tight in the notches. With turbine blades according to the state of the art this may lead to small movements between the roots and the notches which can cause wear.
the movement of a root in the notch can be in a longitudinal direction of the notch or in a direction perpendicular thereto.
the interlocking of neighbouring turbine blades can be achieved due to the fact that the root extends straight while the peripheral sides extend along a curved path. Hence, a longitudinal movement of the blade in a notch will be restricted by the difference in the curvatures of the peripheral sides of the platform section and the root section.
the difference in the curvature of the platform's peripheral sides and the root section provides a better strength of the blade and increases the stress/strain distribution during gas turbine operation.
the root portion may, in particular, extend along a path that is perpendicular to the leading side of the platform section.
the leading side and the trailing side may be parallel to each other.
the root portion's cross section may have, e.g., a fir tree shape, a bulb shape or a hammer shape.
the inventive turbine blade may be, in particular, a gas turbine blade or a steam turbine blade.
Figure 1 shows the inventive turbine blade from the leading edge.
Figure 2 shows the inventive turbine blade from the airfoil section.
Figure 3 shows the inventive turbine blade in a perspective view onto the root section and the peripheral side of the platform section.
Figure 4 shows an alternative embodiment of the inventive turbine blade in a perspective view onto the root section and the peripheral side of the platform section.
the turbine blade comprises a platform section 1, an airfoil section 3 and a root section 5 and is made from a nickel (Ni) based alloy or a cobalt (Co) based alloy.
the surface of the airfoil section 3 and parts of the surface of the platform section 1 may be provided with a coating, such as a so-called MCrAlY where M stands for an element of the group consisting of iron (Fe), cobalt (Co) and nickel (Ni), Y stands for yttrium and/or silicon and/or at least one element of the rare earths or hafnium (Hf).
thermal barrier coating may, e.g., comprise ZrO 2 or Y 2 O 3 -ZrO 2 , i.e. Zirconium dioxide coating which is not stabilised, partly stabilised or fully stabilised by yttrium oxide and/or calcium oxide and/or magnesium oxide.
the turbine blade may be solid or hollow. If the turbine blade is to be cooled during operation of the gas turbine engine, it is hollow and comprises cooling film openings where applicable in order to allow for the production of a cooling air film over the surface of the turbine blade.
the platform section 1 of the turbine blade comprises a first side, a second side opposite the first side, a leading side 14, a trailing side 16 and two peripheral sides 15 which extend from the leading side 14 to the trailing side 16.
the platform section 1 shows a curvature in its peripheral sides 15 whereas the root section extends along a straight line from the leading side 14 of the platform to the trailing side 16 of the platform.
the root section 5 is shown to extend straight, it may as well be curved, as it is shown in Figure 4 for a bulb shaped root section 105. If the root section 105 extends along a curved path from the leading side 14 to the trailing side 16, the curvature of the root section 105 is, however, different to the curvature of the peripheral sides 15. The curvature may, e.g., have a different value for the radius or, like it is shown in Figure 4, may have the opposite orientation with respect to the curvature of the peripheral sides 15 of the platform section 1, i.e. one is curved to the right while the other is curved to the left.
the cross-sectional shape of the root section is, in the present embodiments, a fir tree shape 51 ( Figures 1 and 3) and a bulb shape 151 ( Figure 4), respectively.
the root section may also have a different cross-sectional shape which is suitable for allowing the turbine blade to be held tight in a notch of a rotor during operation of a gas turbine engine.
leading side 14 of the platform section 1 is parallel to the trailing side 16 in the shown embodiments this does not necessarily need to be so. Instead, the sides 14, 16 could include an angle relative to each other. Moreover, the centre line of a straight root section 5 as described with respect to Figures 1 to 3 does not need to be perpendicular to the leading and/or trailing side of the platform.

Landscapes

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

EP20060019003 2006-09-11 2006-09-11 Turbinenschaufel Expired - Fee Related EP1898049B1 (de)

Priority Applications (1)

Application Number	Priority Date	Filing Date	Title
EP20060019003 EP1898049B1 (de)	2006-09-11	2006-09-11	Turbinenschaufel

Applications Claiming Priority (1)

Application Number	Priority Date	Filing Date	Title
EP20060019003 EP1898049B1 (de)	2006-09-11	2006-09-11	Turbinenschaufel

Publications (2)

Publication Number	Publication Date
EP1898049A1 true EP1898049A1 (de)	2008-03-12
EP1898049B1 EP1898049B1 (de)	2012-05-23

Family

ID=37102205

Family Applications (1)

Application Number	Title	Priority Date	Filing Date
EP20060019003 Expired - Fee Related EP1898049B1 (de)	2006-09-11	2006-09-11	Turbinenschaufel

Country Status (1)

Country	Link
EP (1)	EP1898049B1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
CN101782080A (zh) *	2008-12-31	2010-07-21	通用电气公司	关于频率调谐的涡轮叶片的方法、***和/或设备
WO2010088881A1 (de) *	2009-02-05	2010-08-12	Mtu Aero Engines Gmbh	Abdichtvorrichtung an dem schaufelschaft einer rotorstufe einer axialen strömungsmaschine
WO2013110140A1 (en) *	2012-01-24	2013-08-01	Aquaglobe Pty Ltd	A variable output generator and water turbine

Citations (7)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
US1719415A (en) *	1927-09-14	1929-07-02	Westinghouse Electric & Mfg Co	Turbine-blade attachment
US3986793A (en) *	1974-10-29	1976-10-19	Westinghouse Electric Corporation	Turbine rotating blade
US3986739A (en)	1972-09-18	1976-10-19	Francois Guiraud	Retractable safety bolt for door leaf
US5160242A (en)	1991-05-31	1992-11-03	Westinghouse Electric Corp.	Freestanding mixed tuned steam turbine blade
US5242270A (en)	1992-01-31	1993-09-07	Westinghouse Electric Corp.	Platform motion restraints for freestanding turbine blades
JPH07310502A (ja)	1994-05-19	1995-11-28	Toshiba Corp	タービン動翼
EP1124038A1 (de)	2000-02-09	2001-08-16	Siemens Aktiengesellschaft	Turbinenschaufelanordnung

2006
- 2006-09-11 EP EP20060019003 patent/EP1898049B1/de not_active Expired - Fee Related

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
US1719415A (en) *	1927-09-14	1929-07-02	Westinghouse Electric & Mfg Co	Turbine-blade attachment
US3986739A (en)	1972-09-18	1976-10-19	Francois Guiraud	Retractable safety bolt for door leaf
US3986793A (en) *	1974-10-29	1976-10-19	Westinghouse Electric Corporation	Turbine rotating blade
US5160242A (en)	1991-05-31	1992-11-03	Westinghouse Electric Corp.	Freestanding mixed tuned steam turbine blade
US5242270A (en)	1992-01-31	1993-09-07	Westinghouse Electric Corp.	Platform motion restraints for freestanding turbine blades
JPH07310502A (ja)	1994-05-19	1995-11-28	Toshiba Corp	タービン動翼
EP1124038A1 (de)	2000-02-09	2001-08-16	Siemens Aktiengesellschaft	Turbinenschaufelanordnung

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
CN101782080A (zh) *	2008-12-31	2010-07-21	通用电气公司	关于频率调谐的涡轮叶片的方法、***和/或设备
WO2010088881A1 (de) *	2009-02-05	2010-08-12	Mtu Aero Engines Gmbh	Abdichtvorrichtung an dem schaufelschaft einer rotorstufe einer axialen strömungsmaschine
US8870542B2 (en)	2009-02-05	2014-10-28	Mtu Aero Engines Gmbh	Sealing apparatus at the blade shaft of a rotor stage of an axial turbomachine
WO2013110140A1 (en) *	2012-01-24	2013-08-01	Aquaglobe Pty Ltd	A variable output generator and water turbine
AU2013212537B2 (en) *	2012-01-24	2017-06-01	Aquaglobe Pty Ltd	A variable output generator and water turbine

Also Published As

Publication number	Publication date
EP1898049B1 (de)	2012-05-23

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