EP1126136A2 - Aube de turbine avec carenage d'extremité refroidie - Google Patents

Aube de turbine avec carenage d'extremité refroidie Download PDF

Info

Publication number: EP1126136A2
Authority: EP; European Patent Office
Prior art keywords: turbine blade; cooling; blade according; bores; shroud element
Prior art date: 1999-12-28
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

EP00810966A

Other languages

German (de)

English (en)

Other versions

EP1126136A3 (fr

EP1126136B1 (fr

Inventor

Ibrahim Dr. El-Nashar

Hartmut Haehnle

Rudolf Kellerer

Beat Von Arx

Bernhard Prof.Dr. Weigand

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

Alstom Schweiz 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.)

1999-12-28

Filing date

2000-10-19

Publication date

2001-08-22

2000-10-19 Application filed by Alstom Technology AG, Alstom Schweiz AG filed Critical Alstom Technology AG

2001-08-22 Publication of EP1126136A2 publication Critical patent/EP1126136A2/fr

2004-05-19 Publication of EP1126136A3 publication Critical patent/EP1126136A3/fr

2006-06-14 Application granted granted Critical

2006-06-14 Publication of EP1126136B1 publication Critical patent/EP1126136B1/fr

2020-10-19 Anticipated expiration legal-status Critical

Status Expired - Lifetime legal-status Critical Current

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
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
- 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
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
- 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
- F05D2240/81—Cooled platforms
- 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

Definitions

the present invention relates to the field of gas turbines. It affects an air-cooled turbine blade according to the preamble of claim 1.
Such a turbine blade is e.g. from US-A-5,482,435 or US-A-5,785,496.
the known cooling holes take up comparatively little space within the shroud element on. Because a certain minimum thickness is required to drill the holes in the shroud element of the shroud element is required, and this or an even larger one Thickness of the shroud element also in the area outside the holes is maintained, there is an unfavorably small ratio of the flow Shroud volume to shroud volume not flowed through. As a consequence, that the cooling of the shroud element is not optimal, and that the shroud element comparatively due to the large proportion of solid material is heavy and therefore high during operation due to the centrifugal forces is exposed to mechanical loads.
the object is achieved by the entirety of the features of claim 1.
the essence of the invention is that the cavities carrying the cooling fluid inside the Shroud element in coordination with the shroud element in shape and dimension To be designed so that the volume through which the cooling fluid flows occupies a high proportion of the total volume of the shroud element.
the weight of the shroud element be significantly reduced.
a first preferred embodiment of the turbine blade according to the invention is characterized in that the cavities include cooling holes, that the cooling holes are tunnel-shaped, the thickness of the Cover band element outside the cooling holes is reduced, and that the Cooling holes essentially parallel to the direction of movement of the blade tip run from the inside out and in front of the outer edge of the Open the cover band element upwards into the outside space.
the tunnel-shaped The formation of the cooling bores not only reduces the proportion of solid material in the Shroud element, but also mechanically stiffens the shroud element. The cooling air escaping upwards can also escape unhindered if the shroud elements of all blades of a turbine stage are lined up an annular shroud.
cooling holes open laterally into the recesses.
a part of Cooling holes can also be designed as a diffuser.
a second preferred embodiment of the invention is characterized in that that the cavities are designed as slits, which extend across the width of the shroud element extend that the slots substantially parallel to Direction of movement of the blade tip from the inside to the outside and each in front of the outer edge of the shroud element upwards into the outside space open into the cover band element from the top are embedded, and that the slots open laterally into the recesses.
the wide slots result in good cooling with a significant reduction in material.
Cooling is particularly effective if, according to a preferred further development this embodiment in the slots means for improving the heat transfer are provided between the cooling air and the shroud element.
the slots can be used as a means of improving heat transfer distributed arrangement of pins include, which flows around the cooling fluid turbulent and so the heat transfer between cooling fluid and shroud material continue to improve.
a third preferred embodiment of the turbine blade according to the invention is characterized in that the cavities are in the direction of movement of the blade tip extending cooling holes include that the cooling holes are crossed by a plurality of cross holes, and that the cross holes are blocked off from the outside by closed ends are.
This configuration of the intersecting cooling holes is of geometry comparable to the previously mentioned wide slots with distributed pin arrangement.
the solid material is used with greatly improved heat transfer of the shroud element significantly reduced and thus weight saved.
the intersecting cooling holes can be compared with conventional means insert easily into the shroud element. In terms of cooling technology in particular Favorable cooling holes can be achieved if the cooling holes and the cross holes are made using the so-called "STEM drilling" process are.
Fig. 1 is a first preferred embodiment in plan view from above the turbine blade according to the invention.
the turbine blade 10 comprises the actual blade profile (extending perpendicular to the plane of the drawing) 23 and a shroud element arranged transversely thereto at the tip of the blade 11, which together with the shroud elements of the other (not shown) Buckets a continuous, ring-shaped, mechanically stabilizing Cover band results.
the blade profile 23 is partially hollow inside and of one or several cooling air ducts 18 (indicated by dashed lines in FIG. 1), direct the cooling air from the blade root to the tip of the blade (see e.g. Fig. 2 of US-A-5,482,435).
the cover band element 11 has on its upper side (22 in Fig. 2) two ribs running parallel in the direction of movement of the blade tip 12 and 13, which together with the opposite housing wall 20 of the gas turbine form a cavity 21 connected to the surroundings by gaps (FIG. 2).
Cooling holes 16 'and 17, 17' Inside the shroud element 11 run between and essentially parallel to the ribs 12, 13 a plurality of cooling bores 16, 16 'and 17, 17' (in Fig. 1 and 2 shown in dashed lines) starting from the center outwards.
the Cooling holes can be of a uniform shape, but can also be different be designed. 1 and 2 are the Cooling holes 16, 17 as holes with a largely constant diameter designed, while the cooling bores 16 ', 17' as diffusers with themselves in the direction of flow expanding cross-section are formed.
the cooling bores 16, 16 'and 17, 17' are on the input side with the cooling air duct 18 in connection and are supplied by this with cooling air (or another Cooling fluid).
the cooling bores extend 16, 17 not all the way to the side end or edge of the shroud element 11, but each open from the side into an elongated, from the Indentation 14 or 15 recessed into the cover band element 11 from the top side. This ensures that the cooling air always passes through the cooling holes, even if two (adjacent) shroud elements in mechanical Are in contact.
each of the cooling bores 16, 16 'and 17, 17' taken for themselves can be connected to a separate depression. Still is it is also conceivable, the cooling holes 16, 16 'and 17, 17' slightly oblique and from one To allow parallelism to run differently when it comes to optimization cooling over the entire surface of the shroud element 11 is necessary is.
FIG. 3 and 4 An alternative form of weight reduction is in the exemplary embodiment in FIG. 3 and 4 reproduced.
11 inside the shroud element instead a plurality of cooling holes on both sides of the blade profile Wide slot 25 or 26 is provided, each of which is from the central cooling air duct 18 extends to the lateral recesses 14 and 15 and opens there.
the Slots 25, 26 lead to a considerable because of their continuous width Weight reduction and ensure a uniform over the entire width Distributed cooling Throttling points 19 and 19 'can also be used here for limitation of the cooling air mass flow may be provided, the throttling points in each case on the input side (throttling points 19) and / or the output side (throttling points 19 ') of the slots 25, 26 are positioned.
Cooling through the slots 25, 26 can be further increased in their effect if as a means of improvement the heat transfer in the slots a distributed arrangement (one "array") is provided by pins 27.
Pins 7 increase the turbulence of the Cooling air flow and represent additional areas for heat transfer. In addition, they have a mechanical stabilizing effect when they are in the slots range from wall to wall.
the number and arrangement of the pins in the "array" can be changed in the Be changed as part of an optimization of the cooling effect.
Cooling holes 16, 17 (drilling axis 29) and these intersecting cross holes 28 (drilling axis 30) produces the effect in terms of weight loss and cooling comparable to the pin-occupied slots of FIGS. 3 and 4 is.
Cooling bores 16, 17 and cross bores 28 with internal roughness such as To provide turbulators or fins. This leads to a significantly more efficient one Cooling because the shape of the cooling hole can be optimized.
the cooling holes 16, 17 and cross holes 28 are to the side by after drilling closed ends 31 and 32 blocked off.
the cooling bores 16, 17 have again preferably throttling points 19 and open into laterally arranged depressions 14, 15 open at the top

Landscapes

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

EP00810966A 1999-12-28 2000-10-19 Aube de turbine avec carenage d'extremité refroidie Expired - Lifetime EP1126136B1 (fr)

Applications Claiming Priority (2)

Application Number	Priority Date	Filing Date	Title
DE19963377A DE19963377A1 (de)	1999-12-28	1999-12-28	Turbinenschaufel mit aktiv gekühltem Deckbandelement
DE1996377		1999-12-28

Publications (3)

Publication Number	Publication Date
EP1126136A2 true EP1126136A2 (fr)	2001-08-22
EP1126136A3 EP1126136A3 (fr)	2004-05-19
EP1126136B1 EP1126136B1 (fr)	2006-06-14

Family

ID=7934748

Family Applications (1)

Application Number	Title	Priority Date	Filing Date
EP00810966A Expired - Lifetime EP1126136B1 (fr)	1999-12-28	2000-10-19	Aube de turbine avec carenage d'extremité refroidie

Country Status (4)

Country	Link
US (1)	US6464460B2 (fr)
EP (1)	EP1126136B1 (fr)
CN (1)	CN1278018C (fr)
DE (2)	DE19963377A1 (fr)

Families Citing this family (23)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
US6869270B2 (en) *	2002-06-06	2005-03-22	General Electric Company	Turbine blade cover cooling apparatus and method of fabrication
EP1508668B1 (fr)	2003-07-23	2006-12-20	Alstom Technology Ltd	Procédé pour le reconditionnement et procédé pour la fabrication d'une aube de turbine
EP1515000B1 (fr) *	2003-09-09	2016-03-09	Alstom Technology Ltd	Aubage d'une turbomachine avec un carenage contouré
US20060280610A1 (en) *	2005-06-13	2006-12-14	Heyward John P	Turbine blade and method of fabricating same
GB2430170B (en) *	2005-09-15	2008-05-07	Rolls Royce Plc	Method of forming a cast component
US20070201980A1 (en) *	2005-10-11	2007-08-30	Honeywell International, Inc.	Method to augment heat transfer using chamfered cylindrical depressions in cast internal cooling passages
US7686581B2 (en) *	2006-06-07	2010-03-30	General Electric Company	Serpentine cooling circuit and method for cooling tip shroud
US7762774B2 (en) *	2006-12-15	2010-07-27	Siemens Energy, Inc.	Cooling arrangement for a tapered turbine blade
US7568882B2 (en) *	2007-01-12	2009-08-04	General Electric Company	Impingement cooled bucket shroud, turbine rotor incorporating the same, and cooling method
US8057177B2 (en) *	2008-01-10	2011-11-15	General Electric Company	Turbine blade tip shroud
US20090180894A1 (en) *	2008-01-10	2009-07-16	General Electric Company	Turbine blade tip shroud
US7946817B2 (en) *	2008-01-10	2011-05-24	General Electric Company	Turbine blade tip shroud
US7946816B2 (en)	2008-01-10	2011-05-24	General Electric Company	Turbine blade tip shroud
US8322986B2 (en) *	2008-07-29	2012-12-04	General Electric Company	Rotor blade and method of fabricating the same
GB0901129D0 (en) *	2009-01-26	2009-03-11	Rolls Royce Plc	Rotor blade
CH700686A1 (de) *	2009-03-30	2010-09-30	Alstom Technology Ltd	Schaufel für eine gasturbine.
CN102069365B (zh) *	2009-11-25	2014-12-10	中国江南航天工业集团林泉电机厂	一种散热器的制造方法及散热器
US8444372B2 (en)	2011-02-07	2013-05-21	General Electric Company	Passive cooling system for a turbomachine
EP2713009B1 (fr) *	2012-09-26	2015-03-11	Alstom Technology Ltd	Procédé et système de refroidissement pour refroidir des aubes d'au moins une rangée d'aubes dans une turbomachine rotative
CN107438717B (zh) *	2015-04-15	2021-10-08	罗伯特·博世有限公司	自由梢端型轴流式风扇组件
US10947898B2 (en)	2017-02-14	2021-03-16	General Electric Company	Undulating tip shroud for use on a turbine blade
JP6636668B1 (ja) *	2019-03-29	2020-01-29	三菱重工業株式会社	高温部品、高温部品の製造方法及び流量調節方法
US11255198B1 (en) *	2021-06-10	2022-02-22	General Electric Company	Tip shroud with exit surface for cooling passages

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GB1605335A (en) *	1975-08-23	1991-12-18	Rolls Royce	A rotor blade for a gas turbine engine
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1999
- 1999-12-28 DE DE19963377A patent/DE19963377A1/de not_active Ceased
2000
- 2000-10-19 EP EP00810966A patent/EP1126136B1/fr not_active Expired - Lifetime
- 2000-10-19 DE DE50012982T patent/DE50012982D1/de not_active Expired - Lifetime
- 2000-11-30 US US09/725,722 patent/US6464460B2/en not_active Expired - Lifetime
- 2000-12-28 CN CN00137072.3A patent/CN1278018C/zh not_active Expired - Fee Related

Also Published As

Publication number	Publication date
US6464460B2 (en)	2002-10-15
EP1126136A3 (fr)	2004-05-19
DE19963377A1 (de)	2001-07-12
CN1301911A (zh)	2001-07-04
US20010006600A1 (en)	2001-07-05
EP1126136B1 (fr)	2006-06-14
DE50012982D1 (de)	2006-07-27
CN1278018C (zh)	2006-10-04

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Publication	Publication Date	Title
EP1126136A2 (fr)	2001-08-22	Aube de turbine avec carenage d'extremité refroidie
EP1270873B1 (fr)	2010-01-27	Aube de turbine à gaz
EP1267039B1 (fr)	2005-11-09	Configuration de refroidissement du bord de fuite d'une aube
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DE69823236T2 (de)	2005-04-28	Einrichtung zur kühlung von gasturbinenschaufeln und methode zu deren herstellung
DE69302614T2 (de)	1996-11-28	Gekühlte Schaufel für eine Turbomaschine
DE69714960T3 (de)	2008-07-17	Wirbelelementkonstruktion für Kühlkanäle eines Gasturbinenrotorschaufelblattes
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EP2384393B1 (fr)	2017-06-28	Aube refroidie pour turbine a gaz
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DE19634238A1 (de)	1998-02-26	Kühlbare Schaufel
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DE112019000898B4 (de)	2025-04-24	Turbinenschaufel und gasturbine
DE60019965T2 (de)	2006-02-23	Axialturbine für gase
EP1167689A1 (fr)	2002-01-02	Configuration d'une aube de turbine refroidissable
EP0892150B1 (fr)	2003-02-05	Système de refroidissement pour le bord de fuite des aubes creuses d'une turbine à gaz