EP2320030A1 - Rotor et aube de rotor pour une turbomachine axiale - Google Patents

Rotor et aube de rotor pour une turbomachine axiale Download PDF

Info

Publication number: EP2320030A1
Authority: EP; European Patent Office
Prior art keywords: rotor; blade; hammer head; axial; predetermined
Prior art date: 2009-11-10
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

EP10189854A

Other languages

German (de)

English (en)

Other versions

EP2320030B1 (fr

Inventor

Erich Kreiselmaier

Kurt Rubischon

Christoph Nagler

Herbert Brandl

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.)

GE Vernova GmbH

Original Assignee

Alstom Technology 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.)

2009-11-10

Filing date

2010-11-03

Publication date

2011-05-11

2009-11-10 Priority claimed from CH01724/09A external-priority patent/CH702204A1/de

2009-11-10 Priority claimed from CH01723/09A external-priority patent/CH702203A1/de

2010-11-03 Application filed by Alstom Technology AG filed Critical Alstom Technology AG

2011-05-11 Publication of EP2320030A1 publication Critical patent/EP2320030A1/fr

2012-12-19 Application granted granted Critical

2012-12-19 Publication of EP2320030B1 publication Critical patent/EP2320030B1/fr

Status Active legal-status Critical Current

2030-11-03 Anticipated expiration legal-status Critical

Links

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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
- F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
- F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
- F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
- 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
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
- F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
- 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
- F05D2250/10—Two-dimensional
- F05D2250/14—Two-dimensional elliptical
- 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
- F05D2250/10—Two-dimensional
- F05D2250/14—Two-dimensional elliptical
- F05D2250/141—Two-dimensional elliptical circular
- 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
- 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 the art of axial flow turbomachinery. It relates to a rotor for an axial flow turbine engine according to the preamble of claim 1 and a blade for such a rotor.
FIG. 1 shows a perspective, partially sectioned view of an example of such a gas turbine, which is offered by the Applicant and is known under the type designation GT26 ® .
the gas turbine 10 of Fig. 1 is equipped with a so-called sequential combustion. It comprises a multi-stage compressor 12, which draws and compresses air via an air inlet 15. The compressed air is used in a subsequent first annular combustion chamber 14a partially for the combustion of a injected fuel. The resulting hot gas flows through a first turbine 13a and then enters a second combustion chamber 14b, where the remaining air is used to burn a re-injected fuel. The hot gas stream coming from the second combustion chamber 14b is expanded under operating power in a second turbine 13b and exits the gas turbine 10 through an exhaust gas outlet 16 to be discharged to the outside or used to generate steam in a combined cycle power plant.
the compressor 12 and the two turbines 13a, 13b have sets of blades rotating about the axis 30 which, together with stator vanes secured to the surrounding stator, form the blading of the machine. All blades are arranged on a common, rotatable about the axis of the rotor 11 and releasably secured to the rotor shaft by means provided therefor rotor grooves. Particular attention is paid to the last stages 12a of the compressor 12, in which the compressed air reaches temperatures of several hundred degrees Celsius.
An increase in power of the gas turbine is associated with an increase in mass flow through the compressor resulting in a higher gas temperature in the last compressor stages 12a.
the contemporary, advanced aerodynamic design of the blades of the compressor requires greater axial chord lengths, resulting in a greater distance between the rotor grooves 19.
a rotor groove formed in this way has at its bottom a reduced bottom section 23 with a continuously curved cross-sectional contour, which is characterized by a large radius of curvature in the region of the median plane 33 and is mirror-symmetrical to the median plane 33 for reducing thermal stresses.
the object is solved by the entirety of the features of claims 1 and 8.
the basic idea of the invention is that the rotor groove at its bottom for reducing thermal stresses in a conventional manner has an extended in the axial and radial directions bottom area with a continuously curved cross-sectional contour, and the blade root of the blades is adapted in the radial direction to the extended bottom area ,
the widened floor area is mirror-symmetrical to a central plane passing through the rotor groove and perpendicular to the axis, and the radius of curvature of the cross-sectional contour of the floor area decreases starting from the median plane towards the edge.
Another embodiment of the invention is characterized in that the extended bottom portion in the axial direction has a predetermined maximum width, that the radial abutment surfaces in the axial direction have a predetermined minimum distance, and that the ratio of minimum distance to maximum width between 0.1 and 0.6, ie 0.1 ⁇ d 5 / d 1 ⁇ 0.6.
the extended bottom region has a predetermined first maximum depth relative to the radial abutment surfaces
the extended bottom region has a predetermined second maximum depth relative to the inner edges of the axial abutment surfaces
the ratio of second maximum depth to first maximum Depth is between 0.4 and 0.9, ie 0.4 ⁇ d 3 / d 4 ⁇ 0.9.
the blade root is extended below the hammer head for bridging the radial extension of the extended bottom region in the radial direction.
an extension bolt extending in the radial direction is provided for extending the blade root.
the comparatively Slim extension studs bridge the gap without adding bulk to the bucket.
extension bolt is formed on the hammer head.
a curved transition surface is provided at the transition between the extension bolt and the hammer head to ensure a steady transition.
extension bolt as a separate part and to connect this with the hammer head.
the mass of the blade can be further reduced if mass-reducing recesses are provided in the blade root.
the recesses extend over the hammer head and the extension bolt.
these recesses may extend in other, for example, radial direction.
An embodiment of the rotor according to the invention is characterized in that between the lower end of the extension bolt and the bottom of the extended bottom portion, a gap remains free, and that in the free space, a spring is arranged, which the blade with the blade root in the radial direction against presses the radial abutment surfaces.
Another embodiment is characterized in that the hammer head has a predetermined height, that the extension bolt has a predetermined radial length, and that the height to length ratio is between 0.2 and 0.8, ie 0.2 ⁇ d 2 / d 1 ⁇ 0.8.
a further embodiment is characterized in that the hammer head has a predetermined first axial width, that the extension bolt has a predetermined second axial width, and that the ratio of the second to the first axial width is between 0.2 and 0.6, ie 0 , 2 ⁇ d 4 / d 3 ⁇ 0.6.
Fig. 4 shows that too Fig. 2 comparable longitudinal section through the rotor 11 of a gas turbine in the region of the last stages of the compressor according to the invention.
a comparison of Fig. 2 and 4 shows that the upper portion of the rotor groove 21 with respect to the known Rotornutgeometrie from Fig. 2 remains unchanged. Accordingly, the radial and axial abutment surfaces 25 and 20 remain virtually unchanged. Thus, the proven design can be used in this area.
the widened floor area 23 of the rotor groove 21 is characterized in that the cross-sectional contour of the floor area 23 is continuously curved, and that the radius of curvature of the cross-sectional contour of the floor area 23 is very large in the area of the median plane and starts from the median plane decreases sharply towards the edge.
the cross-sectional contour is mirror-symmetrical to the median plane.
the extended bottom portion 23 extends immediately below the axial abutment surfaces 20 on both sides in the axial direction in the manner of an undercut. He shows how Fig. 3 shows, in the axial direction, a predetermined maximum width d 1 , while the radial stop surfaces 25 in the axial direction a given minimum distance d 5 have. It is particularly favorable if the ratio of minimum distance d 5 to maximum width d 1 is between 0.1 and 0.6, ie if the inequality 0.1 ⁇ d 5 / d 1 ⁇ 0.6 applies.
the extended bottom portion 23 has a predetermined first maximum depth d 4 .
the extended bottom portion 23 has a predetermined second maximum depth d 3 . It is particularly favorable if the ratio of the second maximum depth d 3 to the first maximum depth d 4 is between 0.4 and 0.9, ie if the inequality 0.4 ⁇ d 3 / d 4 ⁇ 0.9 applies.
Another inequality relates to the offset of the rotor grooves to each other. If a plurality of similar rotor slots 21 are provided offset from each other by a predetermined distance d 2 in the axial direction, it is advantageous if the ratio of maximum width d 1 to distance d 2 is between 0.5 and 0.8, ie the inequality 0 , 5 ⁇ d 1 / d 2 ⁇ 0.8.
the blade 26 of the Fig. 5 and 6 has a blade root 27, which is formed in the upper portion, which extends to the axial abutment surfaces, substantially the same as the blade root 18 from Fig. 2 ,
the hammer head 32 attached radial extension downwards by means of an integrally formed on the hammer head 32 extension bolt 29, which is narrower (width d 4 ) than the hammer head 32 (width d 3 ).
the radial length (d 1 ) of the Extension bolt 29 is significantly larger than the height (d 2 ) of the hammer head 32nd
a curved transition surface 28 is preferably provided at the transition between the extension bolt 29 and the hammer head 32 to ensure a steady transition.
the extension pin 29 As a cost-effective alternative for the axial extension of the blade root 18, it is advisable to form the extension pin 29 as a separate part and to connect that with the hammer head 32. As the requirements of practical operation sufficient connection method have thereby screwing or welding proven.
the hammer head 32 may be provided at the bottom 34 in the region of the median plane 33 with a threaded bore 35. With the help of an integrally formed threaded bolt 36 of the extension bolt 29 is screwed into the blade root 18, as in Fig. 7 outlined as an example.
one or more mass-reducing recesses 31 are provided in the blade root 18, 27, which can be designed as a circular, elliptical or otherwise shaped hole or slot in a single or multiple design.
the recess (s) 31 extend or extend in the radial direction, preferably via the hammer head 32 and the extension bolt 29. In this case, this recess (s) 31 extends or runs preferably, but not necessarily, in the circumferential direction, as in FIG Fig. 5 . 6 and 7 shown.
other suitable directional curves and embodiments of mass-reducing recesses 31 are likewise conceivable, for example in the form of bores introduced radially into the blade root 27.
the ratio of height (d 2 ) of the hammer head 32 to length (d 1 ) of the extension bolt 29 is preferably between 0.2 and 0.8, ie the inequality 0.2 ⁇ d 2 / d 1 ⁇ 0.8 applies.
the ratio of the axial width (d 4 ) of the extension bolt 29 to the axial width (d 3 ) of the hammer head 32 is preferably between 0.2 and 0.6, ie, the inequality 0.2 ⁇ d 4 / d 3 ⁇ 0, 6th

Landscapes

Engineering & Computer Science (AREA)
Mechanical Engineering (AREA)
General Engineering & Computer Science (AREA)
Structures Of Non-Positive Displacement Pumps (AREA)
Turbine Rotor Nozzle Sealing (AREA)

EP10189854A 2009-11-10 2010-11-03 Rotor et aube de rotor pour une turbomachine axiale Active EP2320030B1 (fr)

Applications Claiming Priority (2)

Application Number	Priority Date	Filing Date	Title
CH01724/09A CH702204A1 (de)	2009-11-10	2009-11-10	Rotor für eine axial durchströmte turbomaschine sowie gasturbine für solchen rotor.
CH01723/09A CH702203A1 (de)	2009-11-10	2009-11-10	Rotor für eine axial durchströmte turbomaschine sowie laufschaufel für einen solchen rotor.

Publications (2)

Publication Number	Publication Date
EP2320030A1 true EP2320030A1 (fr)	2011-05-11
EP2320030B1 EP2320030B1 (fr)	2012-12-19

Family

ID=43587536

Family Applications (1)

Application Number	Title	Priority Date	Filing Date
EP10189854A Active EP2320030B1 (fr)	2009-11-10	2010-11-03	Rotor et aube de rotor pour une turbomachine axiale

Country Status (4)

Country	Link
US (1)	US8770938B2 (fr)
EP (1)	EP2320030B1 (fr)
JP (1)	JP5765918B2 (fr)
CN (1)	CN102121400B (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
EP2873808A1 (fr) *	2013-11-19	2015-05-20	MTU Aero Engines GmbH	Composé aubes-disques, procédé et turbomachine
EP2956626B1 (fr) *	2013-02-12	2019-11-20	United Technologies Corporation	Aube de soufflante comprenant des cavités extérieures
US12110809B1 (en)	2023-04-04	2024-10-08	Ge Infrastructure Technology Llc	Turbine blade and assembly with dovetail arrangement for enlarged rotor groove
EP4442964A1 (fr) *	2023-04-04	2024-10-09	General Electric Technology GmbH	Procédé d'assemblage d'une aube de turbine dans une rainure de rotor définie dans un rotor ayant un axe

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RU2476729C1 (ru) *	2011-07-29	2013-02-27	Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн")	Рабочее колесо осевого компрессора газотурбинного двигателя
JP5922370B2 (ja)	2011-10-20	2016-05-24	三菱日立パワーシステムズ株式会社	動翼支持構造
US9239062B2 (en) *	2012-09-10	2016-01-19	General Electric Company	Low radius ratio fan for a gas turbine engine
CN103850715A (zh) *	2012-11-30	2014-06-11	西门子公司	转子轮盘
RU2530198C1 (ru) *	2013-02-28	2014-10-10	Общество с ограниченной ответственностью "Владимирский инновационно-технологический центр"	Способ крепления лопастей к ступице колеса
RU168474U1 (ru) *	2016-01-11	2017-02-06	Владимир Семенович Мельников	Крепление лопасти динамической машины на укороченном хвостовике
US9682756B1 (en) *	2016-10-17	2017-06-20	General Electric Company	System for composite marine propellers
US11021972B2 (en)	2018-08-14	2021-06-01	Rolls-Royce North American Technologies Inc.	Variable pitch blade holder for gas turbine engine
CN112049686A (zh) *	2019-06-05	2020-12-08	中国航发商用航空发动机有限责任公司	燃气轮机转子和燃气轮机
CN114382552A (zh) *	2022-02-24	2022-04-22	杭州汽轮机股份有限公司	一种超高转速大负荷工业透平动叶片及动叶片组
US12055069B2 (en) *	2022-09-20	2024-08-06	Siemens Energy, Inc.	System and method for reducing blade hook stress in a turbine blade

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EP1253293A2 (fr) *	2001-04-26	2002-10-30	ALSTOM (Switzerland) Ltd	Fixation d'une aube rotorique au rotor d'une turbomachine
WO2005054682A1 (fr)	2003-12-06	2005-06-16	Alstom Technology Ltd	Rotor pour un compresseur
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2010
- 2010-11-03 EP EP10189854A patent/EP2320030B1/fr active Active
- 2010-11-09 US US12/942,565 patent/US8770938B2/en not_active Expired - Fee Related
- 2010-11-10 CN CN201010624485.3A patent/CN102121400B/zh active Active
- 2010-11-10 JP JP2010251639A patent/JP5765918B2/ja not_active Expired - Fee Related

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
GB614678A (en) *	1946-07-19	1948-12-20	Parsons C A & Co Ltd	Improvements in or relating to turbine blading or the like
GB674543A (en) *	1949-05-25	1952-06-25	Ag Fuer Technische Studien	Improvements in and relating to blade assemblies for turbines and rotary compressors
US4645425A (en) *	1984-12-19	1987-02-24	United Technologies Corporation	Turbine or compressor blade mounting
US5141401A (en)	1990-09-27	1992-08-25	General Electric Company	Stress-relieved rotor blade attachment slot
EP0707135A2 (fr) *	1994-10-14	1996-04-17	ABB Management AG	Rotor avec aubes
EP1130217A1 (fr) *	2000-03-01	2001-09-05	ABB Alstom Power N.V.	Fixation des aubes dans une turbomachine
EP1253293A2 (fr) *	2001-04-26	2002-10-30	ALSTOM (Switzerland) Ltd	Fixation d'une aube rotorique au rotor d'une turbomachine
WO2005054682A1 (fr)	2003-12-06	2005-06-16	Alstom Technology Ltd	Rotor pour un compresseur
JP2005220825A (ja) *	2004-02-06	2005-08-18	Mitsubishi Heavy Ind Ltd	タービン動翼
EP1703080A1 (fr)	2005-03-03	2006-09-20	ALSTOM Technology Ltd	Machine tournante

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
EP2956626B1 (fr) *	2013-02-12	2019-11-20	United Technologies Corporation	Aube de soufflante comprenant des cavités extérieures
EP2873808A1 (fr) *	2013-11-19	2015-05-20	MTU Aero Engines GmbH	Composé aubes-disques, procédé et turbomachine
US10041363B2 (en)	2013-11-19	2018-08-07	MTU Aero Engines AG	Blade-disk assembly, method and turbomachine
US12110809B1 (en)	2023-04-04	2024-10-08	Ge Infrastructure Technology Llc	Turbine blade and assembly with dovetail arrangement for enlarged rotor groove
EP4442963A1 (fr) *	2023-04-04	2024-10-09	General Electric Technology GmbH	Aube de turbine et agencement d'aube de turbine pour une rainure de rotor définie dans un rotor ayant un axe et systèmes de turbine
EP4442964A1 (fr) *	2023-04-04	2024-10-09	General Electric Technology GmbH	Procédé d'assemblage d'une aube de turbine dans une rainure de rotor définie dans un rotor ayant un axe
US12435637B2 (en)	2023-04-04	2025-10-07	Ge Infrastructure Technology Llc	Method for turbine blade and assembly with dovetail arrangement for enlarged rotor groove

Also Published As

Publication number	Publication date
US8770938B2 (en)	2014-07-08
CN102121400A (zh)	2011-07-13
JP2011102586A (ja)	2011-05-26
CN102121400B (zh)	2015-12-16
US20110110785A1 (en)	2011-05-12
JP5765918B2 (ja)	2015-08-19
EP2320030B1 (fr)	2012-12-19

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2012-03-14	RIC1	Information provided on ipc code assigned before grant	Ipc: F01D 5/30 20060101AFI20120209BHEP
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