EP1138878A2 - Elément saillant, plat pour turbine à gaz - Google Patents

Elément saillant, plat pour turbine à gaz Download PDF

Info

Publication number: EP1138878A2
Authority: EP; European Patent Office
Prior art keywords: plenum; component section; cooling; section according; hot gas
Prior art date: 2000-03-31
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

EP01108008A

Other languages

German (de)

English (en)

Other versions

EP1138878B1 (fr

EP1138878A3 (fr

Inventor

Alexander Dr. Beeck

Christoph Nagler

Mark Richter

Klaus Semmler

Lothar Schneider

Joerg Dr. Stengele

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

Alstom Technology AG

Alstom Power NV

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.)

2000-03-31

Filing date

2001-03-29

Publication date

2001-10-04

2001-03-29 Application filed by Alstom Technology AG, Alstom Power NV filed Critical Alstom Technology AG

2001-10-04 Publication of EP1138878A2 publication Critical patent/EP1138878A2/fr

2003-10-01 Publication of EP1138878A3 publication Critical patent/EP1138878A3/fr

2008-05-14 Application granted granted Critical

2008-05-14 Publication of EP1138878B1 publication Critical patent/EP1138878B1/fr

2021-03-29 Anticipated expiration legal-status Critical

Status Expired - Lifetime legal-status Critical Current

Images

Classifications

- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/10—Cores; Manufacture or installation of cores
- B22C9/103—Multipart cores
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—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
- F01D5/14—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
- 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
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
- 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
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/202—Heat transfer, e.g. cooling by film cooling

Definitions

the invention relates to a plate-shaped, projecting component section of a Gas turbine or the like according to the preamble of claim 1.
Such component sections can often be found where constructive Overhanging areas on main components, such as on Buckets, fasteners are provided or sealing elements, too between two neighboring components. Problematic are such overhanging component sections especially in thermally highly stressed Areas where hot gas is applied to the surface. It is often essential to provide cooling there.
EP 0 911 486 A2 describes a cooled one Known blade of a gas turbine, in which overhanging areas in the form of plate-shaped, cantilevered component sections are formed in the axial direction are attached in front of and behind the blade root to cover the hub area with the adjacent blade root areas of rotor blades to ensure.
To cool this plate-shaped, cantilevered Component sections are provided cooling bores that are purely convective from cooling air be flowed through.
the cooling holes run for example in the front overhanging component section in the circumferential direction and are from the main cooling air supply fed. Due to the high thermal load in this Area there are additional turbulence generators in the cooling holes, to improve heat transfer.
the rear, overhanging component section has a plurality of axially extending Cooling holes, which are also fed by the main cooling air supply.
the cooling bores open axially at the end of the component section, so that the cooling medium escapes into the hot gas stream after flowing through the cooling channels.
the invention tries to avoid the disadvantages described. You are the Task based on a plate-shaped, projecting component section of a Specify gas turbine or the like of the type mentioned, the one allows more effective cooling of the surface exposed to hot gas and thus has an increased service life with a reduced cooling air requirement.
a plenum is provided, which is assigned exclusively to the component section, so that enables optimal cooling of the surface exposed to hot gas becomes.
the plenum is immediately adjacent to the surface to be cooled arranged and is flowed through by the cooling medium convectively.
the cooling bores are designed as blow-out openings which emanate from the plenum and open on the surface exposed to hot gas. So it is possible, a highly effective film cooling on the hot gas Realize surface, while the coolant consumption is kept extremely low can be. The reason is that the cooling air is initially convective flows through the cooling area and then by blowing out train highly effective cooling film.
a number of preferred versions are based on the simple and inexpensive Realization of this cooling concept directed.
the choice of the optimal shaping process for the plenary mainly depends on the manufacturing process from the actual component on which the plate-shaped, projecting section is to be provided. Other important aspects are those to be realized Geometry, as well as the manufacturing specifications.
a multi-part core is used to create the desired geometry of the plenary. If necessary, side openings for Positioning of the core will be required afterwards, ie afterwards can be concluded from the shaping process.
the plenum through a recess in the component section to form, for example opposite to the one to be cooled Surface is open and therefore by a cover to be retrofitted can be locked.
the advantage of this variant lies in the possibility of making the geometry of the plenary largely revealing.
the cover can be attached using cost-effective connection methods, such as soldering or welding.
both the plenum and the blow-out openings using the EDM process.
the shape, size and arrangement of the blow-out openings in particular can be freely selected and implemented with the highest precision.
the plenum as such can also be implemented exactly with this procedure. Lateral outlet openings, as required for the production of the plenum, can remain completely or partially open as additional outlet openings, depending on the design of the cooling concept. Otherwise, they are closed after the molding process.
the plenum is preferably connected via feed channels to a main plenum, which supplies the blade with cooling air. In this way, no direct connection to the cooling medium supply is required, which means that the design effort can be reduced.
cooling concept described above is suitable for use with it is preferred that any thermally highly stressed components can be realized used on overhangs of turbine blades.
thermal loads particularly high on the other hand is in the immediate vicinity of the overhang mostly provided for a coolant supply anyway, whereby the cooling concept according to the invention is particularly easy to implement leaves.
the concept according to the invention is based on a plate-shaped, cantilevered Component section explained in the form of an overhang 1, which is a component a platform 3 carrying a turbine blade 4 is formed.
a surface 2 is thermally highly stressed, namely by one not shown here Hot gas jet.
FIGS. 1 and 2 are on the overhang 1 four essentially parallel and spaced apart Pleni 10 available, which consistently enforce the overhang 1. You run immediately adjacent to the surface 2 and cool it in this area through a cooling medium, which is not shown in more detail and is passed through convectively. Blow-out openings 12 are also present, preferably in rows and arranged in association with the Pleni 10. They are based on Pleni 10 and open on the surface 2. In this way, the cooling medium from the Pleni 10 blown out through the blow-out openings 12 such that a coherent Forms cooling film. The surface 2 is thus optimally cooled.
the plenums 10 can be operated using EDM tools 19 are formed, drill the through holes in the overhang 1. This creates a connection to a main plenum 5 below the platform 3 manufactured, whereby the pleni 10 are fed with cooling air from this area.
the plenums 10 can open on the side on the overhang 1, as shown in Fig. 1. In this case, cooling air is also discharged from the side blown out the overhang 1. However, it is equally possible to use Pleni 10 in to partially or completely close this area.
the cross-section of the individual plenums 10 can vary to match the local one To achieve a coordinated cooling effect when exposed to heat. This also applies to their number and distribution of their arrangement along the overhang 1. The same applies analogously for the cooling bores or blow-out openings 12, which for training of the cooling film are responsible.
Fig. 3 shows a plenum 30, the overhang 1 largely complete with regard to its longitudinal and transverse extension interspersed throughout. This enables a largely ideally evened out convective cooling of the surface 2 and also offers the possibility of the film cooling air bores (not shown here in detail) are distributed as desired to arrange.
the plenum 30 is again supplied by the main plenum 5. For this there are feed channels 6 provided that the connection between the main plenum 5 and the Establish plenum 30.
the plenum 30 and the feed channels 6 are in this case directly during the Casting process formed.
a core 39 shown in FIG. 4 is used for this purpose, which specifies the shape of the plenum 30.
FIG. 5 shows a recess 50 cast in the overhang 1, from which the cooling bores 52 depart.
the actual plenum is then formed when the recess 50 is closed by a cover, not shown here becomes.
the cover can consist of a simple plate that is on the overhang 1 is placed and soldered or welded there. So you can even complicated geometries due to a corresponding design of the recess 50 are implemented. Such geometries can, for example, on the Surface 2 arranged pins, ribs or turbulence generators (not shown).

Landscapes

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

EP01108008A 2000-03-31 2001-03-29 Composant de turbine à gaz Expired - Lifetime EP1138878B1 (fr)

Applications Claiming Priority (2)

Application Number	Priority Date	Filing Date	Title
DE10016081A DE10016081A1 (de)	2000-03-31	2000-03-31	Plattenförmiger, auskragender Bauteilabschnitt einer Gasturbine
DE10016081		2000-03-31

Publications (3)

Publication Number	Publication Date
EP1138878A2 true EP1138878A2 (fr)	2001-10-04
EP1138878A3 EP1138878A3 (fr)	2003-10-01
EP1138878B1 EP1138878B1 (fr)	2008-05-14

Family

ID=7637140

Family Applications (1)

Application Number	Title	Priority Date	Filing Date
EP01108008A Expired - Lifetime EP1138878B1 (fr)	2000-03-31	2001-03-29	Composant de turbine à gaz

Country Status (3)

Country	Link
US (1)	US6565317B2 (fr)
EP (1)	EP1138878B1 (fr)
DE (2)	DE10016081A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
CH700320A1 (de) *	2009-01-30	2010-07-30	Alstom Technology Ltd	Verfahren zum herstellen eines bauteils einer gasturbine.
EP3467257A1 (fr) *	2017-10-09	2019-04-10	United Technologies Corporation	Structures de refroidissement des platformes des aubes statorique

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
US6887033B1 (en) *	2003-11-10	2005-05-03	General Electric Company	Cooling system for nozzle segment platform edges
US7004720B2 (en) *	2003-12-17	2006-02-28	Pratt & Whitney Canada Corp.	Cooled turbine vane platform
US7625172B2 (en) *	2006-04-26	2009-12-01	United Technologies Corporation	Vane platform cooling
US10189100B2 (en)	2008-07-29	2019-01-29	Pratt & Whitney Canada Corp.	Method for wire electro-discharge machining a part
US8925201B2 (en) *	2009-06-29	2015-01-06	Pratt & Whitney Canada Corp.	Method and apparatus for providing rotor discs
US20130094971A1 (en) *	2011-10-12	2013-04-18	General Electric Company	Hot gas path component for turbine system
CA2898822A1 (fr)	2013-03-13	2014-10-09	Rolls-Royce Corporation	Agencement de trou de refroidissement a tranchee pour une ailette composite a matrice ceramique

Citations (1)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
EP0911486A2 (fr)	1997-10-28	1999-04-28	Mitsubishi Heavy Industries, Ltd.	Refroidissement d'une aube de guidage pour une turbine à gaz

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IT1079131B (it) *	1975-06-30	1985-05-08	Gen Electric	Perfezionato raffreddamento applicabile particolarmente a elementi di turbomotori a gas
DE2643049A1 (de) *	1975-10-14	1977-04-21	United Technologies Corp	Schaufel mit gekuehlter plattform fuer eine stroemungsmaschine
US4017213A (en) *	1975-10-14	1977-04-12	United Technologies Corporation	Turbomachinery vane or blade with cooled platforms
US4353679A (en) *	1976-07-29	1982-10-12	General Electric Company	Fluid-cooled element
GB2163218B (en) *	1981-07-07	1986-07-16	Rolls Royce	Cooled vane or blade for a gas turbine engine
JPH03213602A (ja) *	1990-01-08	1991-09-19	General Electric Co <Ge>	ガスタービンエンジンの当接セグメントを連結する自己冷却式ジョイント連結構造
US5197852A (en) *	1990-05-31	1993-03-30	General Electric Company	Nozzle band overhang cooling
GB9224241D0 (en) *	1992-11-19	1993-01-06	Bmw Rolls Royce Gmbh	A turbine blade arrangement
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US5823741A (en) *	1996-09-25	1998-10-20	General Electric Co.	Cooling joint connection for abutting segments in a gas turbine engine

2000
- 2000-03-31 DE DE10016081A patent/DE10016081A1/de not_active Withdrawn
2001
- 2001-03-29 DE DE50113955T patent/DE50113955D1/de not_active Expired - Lifetime
- 2001-03-29 EP EP01108008A patent/EP1138878B1/fr not_active Expired - Lifetime
- 2001-03-30 US US09/820,679 patent/US6565317B2/en not_active Expired - Lifetime

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
EP0911486A2 (fr)	1997-10-28	1999-04-28	Mitsubishi Heavy Industries, Ltd.	Refroidissement d'une aube de guidage pour une turbine à gaz

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
CH700320A1 (de) *	2009-01-30	2010-07-30	Alstom Technology Ltd	Verfahren zum herstellen eines bauteils einer gasturbine.
WO2010086402A2 (fr)	2009-01-30	2010-08-05	Alstom Technology Ltd.	Procédé de production d'un élément de turbine à gaz
WO2010086402A3 (fr) *	2009-01-30	2010-10-21	Alstom Technology Ltd.	Procédé de production d'un élément de turbine à gaz
EP3467257A1 (fr) *	2017-10-09	2019-04-10	United Technologies Corporation	Structures de refroidissement des platformes des aubes statorique
US11118474B2 (en)	2017-10-09	2021-09-14	Raytheon Technologies Corporation	Vane cooling structures

Also Published As

Publication number	Publication date
US6565317B2 (en)	2003-05-20
EP1138878B1 (fr)	2008-05-14
US20010036407A1 (en)	2001-11-01
EP1138878A3 (fr)	2003-10-01
DE10016081A1 (de)	2001-10-04
DE50113955D1 (de)	2008-06-26

Publication	Publication Date	Title
DE3211139C1 (de)	1983-08-11	Axialturbinenschaufel,insbesondere Axialturbinenlaufschaufel fuer Gasturbinentriebwerke
EP1013884B1 (fr)	2005-07-27	Aube de turbine avec plateforme refroidie
DE60018817T2 (de)	2005-08-11	Gekühlte Gasturbinenschaufel
DE60017166T2 (de)	2005-05-25	Gusskern für eine innengekühlte turbinenschaufel, deren speiseröffnung nicht verschlossen werden muss
DE69011005T2 (de)	1994-12-22	Keramischer Gasbrenner für Heisslufterhitzer und Steine dafür.
EP1113145B1 (fr)	2006-04-05	Aube pour turbine a gaz avec section de mesure sur le bord de fuite
DE69823236T2 (de)	2005-04-28	Einrichtung zur kühlung von gasturbinenschaufeln und methode zu deren herstellung
DE19944923B4 (de)	2007-07-19	Turbinenschaufel für den Rotor einer Gasturbine
DE19810066C2 (de)	2001-03-01	Gasturbinenlaufschaufel
DE60128319T2 (de)	2008-01-10	Mantelringsegment für eine Turbine
DE60223115T2 (de)	2008-08-07	Kühlfluidführung bei einem Gasturbinenschaufelblatt
DE69919298T2 (de)	2005-08-04	Kühlstruktur für eine Gasturbinenbrennkammer
DE102009026052B4 (de)	2022-11-17	Kühleinrichtung für das hintere Ende eines Brennkammerübergangstücks und zugehöriges Verfahren
DE60221284T2 (de)	2008-04-10	Bauteil zur beaufschlagung mit hoher thermischer belastung beim betrieb und verfahren zur herstellung eines solchen bauteils
DE69914509T2 (de)	2004-06-24	Verfahren zur Herstellung einer dreiteiligen Spritzgiessdüse und eines Spritzgiesshohlraumeinsatzes und zum Kühlen eines Formhohlraumes
DE69908603T2 (de)	2004-05-13	Dampfgekühlte statorschaufel einer gasturbine
DE10001109A1 (de)	2001-07-19	Gekühlte Schaufel für eine Gasturbine
CH628397A5 (de)	1982-02-26	Luftgekuehlte turbinenschaufel.
EP2304185A1 (fr)	2011-04-06	Aube de turbine pour une turbine à gaz et noyau de coulée pour sa fabrication
DE4323038A1 (de)	1994-01-20	Spritzdüse mit abnehmbarem vorderen Teil
EP1247602B1 (fr)	2008-02-20	Procédé pour la fabrication d'une aube de turbine
EP2611990A1 (fr)	2013-07-10	Aube de turbine pour une turbine à gaz
EP1201879A2 (fr)	2002-05-02	Composant refroidi, noyau de coulage et procédé pour la fabrication dudit composant
EP2300178A1 (fr)	2011-03-30	Aube pour une turbine à gaz et procédé de fabrication par technique de coulée d une telle aube
EP1431662B1 (fr)	2008-09-17	Chambre de combustion de turbine avec système de refroidissement à circuit fermé

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