EP1013884A2 - Aube de turbine avec plateforme refroidie - Google Patents

Aube de turbine avec plateforme refroidie Download PDF

Info

Publication number: EP1013884A2
Authority: EP; European Patent Office
Prior art keywords: turbine blade; cooling; blade according; shroud; open
Prior art date: 1998-12-24
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

EP99811187A

Other languages

German (de)

English (en)

Other versions

EP1013884A3 (fr

EP1013884B1 (fr

Inventor

Alexander Dr. Beeck

Ibrahim Dr. El-Nashar

Beat Von Arx

Bernhard 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.)

General Electric Technology GmbH

Original Assignee

ABB Alstom Power Switzerland Ltd

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.)

1998-12-24

Filing date

1999-12-21

Publication date

2000-06-28

1998-12-24 Priority claimed from DE19860244A external-priority patent/DE19860244B4/de

1998-12-24 Priority claimed from DE19860245A external-priority patent/DE19860245A1/de

1999-12-21 Application filed by ABB Alstom Power Switzerland Ltd, Alstom Technology AG filed Critical ABB Alstom Power Switzerland Ltd

2000-06-28 Publication of EP1013884A2 publication Critical patent/EP1013884A2/fr

2003-11-05 Publication of EP1013884A3 publication Critical patent/EP1013884A3/fr

2005-07-27 Application granted granted Critical

2005-07-27 Publication of EP1013884B1 publication Critical patent/EP1013884B1/fr

2019-12-21 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
- F01D5/22—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
- 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
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2240/00—Components
- F05B2240/80—Platforms for stationary or moving blades
- F05B2240/801—Platforms for stationary or moving blades 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
- F05D2240/00—Components
- F05D2240/80—Platforms for stationary or moving blades
- F05D2240/81—Cooled platforms

Definitions

the present invention relates to the field of gas turbines. It affects an air-cooled turbine blade, which is vertical at the tip of the blade to the blade longitudinal axis extending shroud element, wherein the shroud element for the purpose of cooling a plurality of cooling holes is crossed, which on the input side with at least one through the Turbine blade in connection with the cooling air duct running at the tip of the blade stand and on the output side in the outside space surrounding the turbine blade flow out.
Generic turbine blades are from DE 198 13 173 A1 or from US 5,785,496.
the basic idea of the invention is, on the one hand, to guide the cooling bores through the shroud element in such a way that a high heat transfer between the shroud element and cooling air is ensured and, on the other hand, to allow these bores to open into the outside space in such a way that the exposed regions of the shroud reliably depend on Cooling air is applied and additionally cooled. This is achieved by proceeding from the cooling channel of the blade in the area of the shroud element, the cooling holes running essentially parallel to the direction of movement of the shovel tip from the inside to the outside and each opening in front of the outer edge of the shroud element in a recess in the surface open to the outside.
recesses are made in the cover band element near the outer edge from the top, into which the cooling holes open laterally.
the outlet of the cooling air on the top of the shroud element is particularly effective if, according to a preferred development, mutually spaced sealing ribs are provided on the top of the shroud element, which form a cavity in cooperation with the opposite housing wall of the gas turbine, and the cooling holes in open this cavity.
the escaping cooling air leads to a pressure build-up in the cavity, as a result of which the penetration of hot gases is reduced.
the side edges of the Shroud elements recesses into which the cooling holes open.
the recesses Opposing shroud elements form a gap.
the cooling air is divided into two partial flows. A part flows to the top and feeds the cavity mentioned between the spaced Sealing ribs with the above-mentioned effect.
the other part flows to Underside of the cover tape and mixes there with the hot gases under setting a mixing temperature that reduces the thermal load in this area. Due to the gap geometry, the ratio of those flowing up and down can Partial quantities are influenced.
the holes can be created using the so-called "STEM drilling” process.
STEM drilling which has been described, for example, in US Pat. No. 5,306,401 in connection with the production of cooling holes in turbine blades, can be used to produce cooling bores with improved heat transfer properties simply and reliably.
the turbine blade 10 comprises the actual one Blade profile 23 and one arranged transversely thereto at the tip of the blade Shroud element 11, which together with the shroud elements of the other Buckets (not shown) a continuous, mechanically stabilizing Cover band results.
the blade profile 23 is partially hollow inside and of one or several cooling air channels 18, the cooling air from the blade root to the tip of the blade.
the shroud element 11 has on its top 22 two sealing 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.
cooling bores 17 are on the input side with the cooling air duct 18 in connection and are supplied by this with cooling air.
the cooling bores 17 do not extend all the way to the side End or edge of the shroud element 11, but each open from the side into an elongated, on the top 22 in the shroud element 11 recessed recess 14.
each of the cooling holes 17 taken for themselves can be connected to a separate depression.
the cooling holes 17 slightly oblique and parallel to each other to be different if it is to optimize cooling over the entire area of the shroud element 11 is necessary.
the cooling bores 17 in the cooling arrangement shown are preferably produced using the so-called "STEM drilling" method, which is described in detail in US Pat. No. 5,306,401. This makes it possible (by changing the feed) to equip the surface of the cooling bores 17 with roughness, ribs or turbulators. This leads to significantly more efficient cooling because the shape of the cooling hole can be optimized. Furthermore, it is advantageous to provide the cooling bores 17, preferably on the inlet side, ie in the area of the cooling air supply on the profile 23, with a throttle point 19. This makes it possible to limit the cooling air mass flow in a targeted manner and to obtain significantly more efficient cooling.
the embodiment according to FIG. 2 differs from that according to FIG.
cooling bores 17 are designed as a diffuser or similar to a diffuser from the throttle point 19, which is arranged on the input side of each cooling bore.
the cooling holes have an oval configuration. This, like the provision of internal roughness or the diffuser-like enlargement, increases the effective surface available for heat transfer.
the cooling bores 17 can have different configurations than those described above. As such, regular or irregular depressions or corrugations are conceivable.
the cooling bores 17 emerge on the side edge 25 of the shroud element 11.
the side edges 25 of the shroud elements 11 are, however, designed such that adjacent elements 11 are only in contact in some areas, but the area of the emerging cooling bores is in contrast recessed in a recess 15. Between the adjacent elements, the opposite depressions 15 form gaps 26 into which the cooling air enters.
This design reliably prevents the mouths from being closed by adjacent shroud elements. It ensures that the cooling air can always pass through the cooling bores 17, even if two adjacent cover band elements 11 are in mechanical contact.
the cooling air entering the gap 26 from the two adjacent elements 11 is divided into two partial flows.
the ratio of the two partial flows can be influenced by the design of the gap.
the top and bottom sides can have a different gap width or the boundary walls can be inclined or differently designed in terms of flow technology.
FIG 8 shows an embodiment with a coolant outlet on the underside of the Shroud element.
the cooling bores 17 open laterally into the recess 16. According to this variant, the mixing temperature in the area of the bottom of the Cover band lowered and thus the thermal load is reduced.

Landscapes

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

EP99811187A 1998-12-24 1999-12-21 Aube de turbine avec plateforme refroidie Expired - Lifetime EP1013884B1 (fr)

Applications Claiming Priority (4)

Application Number	Priority Date	Filing Date	Title
DE19860244A DE19860244B4 (de)	1998-12-24	1998-12-24	Turbinenschaufel mit aktiv gekühltem Deckbandelement
DE19860245		1998-12-24
DE19860245A DE19860245A1 (de)	1998-12-24	1998-12-24	Turbinenschaufel mit aktiv gekühltem Deckbandelement
DE19860244		1998-12-24

Publications (3)

Publication Number	Publication Date
EP1013884A2 true EP1013884A2 (fr)	2000-06-28
EP1013884A3 EP1013884A3 (fr)	2003-11-05
EP1013884B1 EP1013884B1 (fr)	2005-07-27

Family

ID=26051058

Family Applications (1)

Application Number	Title	Priority Date	Filing Date
EP99811187A Expired - Lifetime EP1013884B1 (fr)	1998-12-24	1999-12-21	Aube de turbine avec plateforme refroidie

Country Status (4)

Country	Link
US (1)	US6340284B1 (fr)
EP (1)	EP1013884B1 (fr)
CN (1)	CN1260442A (fr)
DE (1)	DE59912323D1 (fr)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
EP1126136A2 (fr) *	1999-12-28	2001-08-22	ALSTOM (Schweiz) AG	Aube de turbine avec carenage d'extremité refroidie
EP1267042A2 (fr) *	2001-06-14	2002-12-18	Mitsubishi Heavy Industries, Ltd.	Aube de turbine à gaz avec bande de recouvrement
US7273347B2 (en)	2004-04-30	2007-09-25	Alstom Technology Ltd.	Blade for a gas turbine
CH700686A1 (de) *	2009-03-30	2010-09-30	Alstom Technology Ltd	Schaufel für eine gasturbine.
WO2011045346A1 (fr) *	2009-10-15	2011-04-21	Abb Turbo Systems Ag	Roue de turbine
EP2657452A1 (fr) *	2010-12-22	2013-10-30	Mitsubishi Heavy Industries, Ltd.	Turbine
EP2290193A3 (fr) *	2009-08-18	2014-07-16	United Technologies Corporation	Trous de refroidissement pour le bord d'attaque de la plateforme d'une aube statorique
EP3550111A1 (fr) *	2018-04-06	2019-10-09	United Technologies Corporation	Carénage d'aube de turbine pour moteur à turbine à gaz comportant une turbine de puissance et son procédé de fabrication

Families Citing this family (31)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
EP1041247B1 (fr)	1999-04-01	2012-08-01	General Electric Company	Aube de turbineà gaz comprenant un circuit de refroidissement ouvert
US6761534B1 (en)	1999-04-05	2004-07-13	General Electric Company	Cooling circuit for a gas turbine bucket and tip shroud
US6254345B1 (en) *	1999-09-07	2001-07-03	General Electric Company	Internally cooled blade tip shroud
US6471480B1 (en) *	2001-04-16	2002-10-29	United Technologies Corporation	Thin walled cooled hollow tip shroud
US6632069B1 (en) *	2001-10-02	2003-10-14	Oleg Naljotov	Step of pressure of the steam and gas turbine with universal belt
US20040101410A1 (en) *	2001-10-02	2004-05-27	Oleg Naljotov	Axial flow fluid machine
US6491498B1 (en) *	2001-10-04	2002-12-10	Power Systems Mfg, Llc.	Turbine blade pocket shroud
US7074006B1 (en)	2002-10-08	2006-07-11	The United States Of America As Represented By The Administrator Of National Aeronautics And Space Administration	Endwall treatment and method for gas turbine
JP4195882B2 (ja) *	2003-04-18	2008-12-17	オレグナリオトフ	軸流フロー流体機械
US7066714B2 (en) *	2004-03-26	2006-06-27	United Technologies Corporation	High speed rotor assembly shroud
KR100758725B1 (ko)	2005-10-17	2007-09-14	올레지 날조토브	유니버설 쉬라우드를 구비한 증기/가스 터빈 압력 단
US7568882B2 (en) *	2007-01-12	2009-08-04	General Electric Company	Impingement cooled bucket shroud, turbine rotor incorporating the same, and cooling method
US7938951B2 (en) *	2007-03-22	2011-05-10	General Electric Company	Methods and systems for forming tapered cooling holes
US7964087B2 (en) *	2007-03-22	2011-06-21	General Electric Company	Methods and systems for forming cooling holes having circular inlets and non-circular outlets
US20080230396A1 (en) *	2007-03-22	2008-09-25	General Electric Company	Methods and systems for forming turbulated cooling holes
US20090180894A1 (en) *	2008-01-10	2009-07-16	General Electric Company	Turbine blade tip shroud
US7946816B2 (en) *	2008-01-10	2011-05-24	General Electric Company	Turbine blade tip shroud
US7946817B2 (en) *	2008-01-10	2011-05-24	General Electric Company	Turbine blade tip shroud
US8057177B2 (en) *	2008-01-10	2011-11-15	General Electric Company	Turbine blade tip shroud
US8317461B2 (en) *	2008-08-27	2012-11-27	United Technologies Corporation	Gas turbine engine component having dual flow passage cooling chamber formed by single core
GB0901129D0 (en) *	2009-01-26	2009-03-11	Rolls Royce Plc	Rotor blade
GB0910177D0 (en) *	2009-06-15	2009-07-29	Rolls Royce Plc	A cooled component for a gas turbine engine
US20140064984A1 (en) *	2012-08-31	2014-03-06	General Electric Company	Cooling arrangement for platform region of turbine rotor blade
JP5612136B2 (ja)	2013-01-09	2014-10-22	ファナック株式会社	複数の直線により形状が定義されるインペラの形成方法およびインペラ
US9759070B2 (en) *	2013-08-28	2017-09-12	General Electric Company	Turbine bucket tip shroud
US20160169001A1 (en) *	2013-09-26	2016-06-16	United Technologies Corporation	Diffused platform cooling holes
EP3060763B1 (fr) *	2013-10-21	2020-04-15	United Technologies Corporation	Découragement d'écoulement dans un écart d'aubes de turbine tolérant aux incidents
US10539026B2 (en)	2017-09-21	2020-01-21	United Technologies Corporation	Gas turbine engine component with cooling holes having variable roughness
JP7477284B2 (ja) *	2019-11-14	2024-05-01	三菱重工業株式会社	タービン翼及びガスタービン
US11255198B1 (en) *	2021-06-10	2022-02-22	General Electric Company	Tip shroud with exit surface for cooling passages
CN115324657A (zh) *	2022-10-12	2022-11-11	中国航发四川燃气涡轮研究院	涡轮工作叶片叶冠冷却结构

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Publication number	Priority date	Publication date	Assignee	Title
US5306401A (en)	1993-03-15	1994-04-26	Fierkens Richard H J	Method for drilling cooling holes in turbine blades
US5460486A (en)	1992-11-19	1995-10-24	Bmw Rolls-Royce Gmbh	Gas turbine blade having improved thermal stress cooling ducts
US5482435A (en)	1994-10-26	1996-01-09	Westinghouse Electric Corporation	Gas turbine blade having a cooled shroud
US5785496A (en)	1997-02-24	1998-07-28	Mitsubishi Heavy Industries, Ltd.	Gas turbine rotor
DE19813173A1 (de)	1997-03-25	1998-10-01	Mitsubishi Heavy Ind Ltd	Gekühlte Gasturbinen-Laufschaufel

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1999
- 1999-12-21 DE DE59912323T patent/DE59912323D1/de not_active Expired - Lifetime
- 1999-12-21 EP EP99811187A patent/EP1013884B1/fr not_active Expired - Lifetime
- 1999-12-23 US US09/471,410 patent/US6340284B1/en not_active Expired - Lifetime
- 1999-12-24 CN CN99124987A patent/CN1260442A/zh active Pending

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US5460486A (en)	1992-11-19	1995-10-24	Bmw Rolls-Royce Gmbh	Gas turbine blade having improved thermal stress cooling ducts
US5306401A (en)	1993-03-15	1994-04-26	Fierkens Richard H J	Method for drilling cooling holes in turbine blades
US5482435A (en)	1994-10-26	1996-01-09	Westinghouse Electric Corporation	Gas turbine blade having a cooled shroud
US5785496A (en)	1997-02-24	1998-07-28	Mitsubishi Heavy Industries, Ltd.	Gas turbine rotor
DE19813173A1 (de)	1997-03-25	1998-10-01	Mitsubishi Heavy Ind Ltd	Gekühlte Gasturbinen-Laufschaufel

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
EP1126136A2 (fr) *	1999-12-28	2001-08-22	ALSTOM (Schweiz) AG	Aube de turbine avec carenage d'extremité refroidie
EP1126136A3 (fr) *	1999-12-28	2004-05-19	ALSTOM Technology Ltd	Aube de turbine avec carenage d'extremité refroidie
EP1267042A2 (fr) *	2001-06-14	2002-12-18	Mitsubishi Heavy Industries, Ltd.	Aube de turbine à gaz avec bande de recouvrement
EP1267042A3 (fr) *	2001-06-14	2009-06-17	Mitsubishi Heavy Industries, Ltd.	Aube de turbine à gaz avec bande de recouvrement
US7273347B2 (en)	2004-04-30	2007-09-25	Alstom Technology Ltd.	Blade for a gas turbine
WO2010112299A1 (fr) *	2009-03-30	2010-10-07	Alstom Technology Ltd.	Aube pour une turbine à gaz
CH700686A1 (de) *	2009-03-30	2010-09-30	Alstom Technology Ltd	Schaufel für eine gasturbine.
US9464529B2 (en)	2009-03-30	2016-10-11	General Electric Technology Gmbh	Blade for a gas turbine
EP2290193A3 (fr) *	2009-08-18	2014-07-16	United Technologies Corporation	Trous de refroidissement pour le bord d'attaque de la plateforme d'une aube statorique
WO2011045346A1 (fr) *	2009-10-15	2011-04-21	Abb Turbo Systems Ag	Roue de turbine
EP2657452A1 (fr) *	2010-12-22	2013-10-30	Mitsubishi Heavy Industries, Ltd.	Turbine
EP2657452A4 (fr) *	2010-12-22	2014-06-11	Mitsubishi Heavy Ind Ltd	Turbine
US9353640B2 (en)	2010-12-22	2016-05-31	Mitsubishi Hitachi Power Systems, Ltd.	Turbine
EP3550111A1 (fr) *	2018-04-06	2019-10-09	United Technologies Corporation	Carénage d'aube de turbine pour moteur à turbine à gaz comportant une turbine de puissance et son procédé de fabrication

Also Published As

Publication number	Publication date
US6340284B1 (en)	2002-01-22
DE59912323D1 (de)	2005-09-01
CN1260442A (zh)	2000-07-19
EP1013884A3 (fr)	2003-11-05
EP1013884B1 (fr)	2005-07-27

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