EP1138878B1 - Composant de turbine à gaz - Google Patents

Composant de turbine à gaz Download PDF

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Publication number
EP1138878B1
EP1138878B1 EP01108008A EP01108008A EP1138878B1 EP 1138878 B1 EP1138878 B1 EP 1138878B1 EP 01108008 A EP01108008 A EP 01108008A EP 01108008 A EP01108008 A EP 01108008A EP 1138878 B1 EP1138878 B1 EP 1138878B1
Authority
EP
European Patent Office
Prior art keywords
plenum
cooling
component
component according
hot gas
Prior art date
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.)
Expired - Lifetime
Application number
EP01108008A
Other languages
German (de)
English (en)
Other versions
EP1138878A2 (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
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.)
Filing date
Publication date
Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP1138878A2 publication Critical patent/EP1138878A2/fr
Publication of EP1138878A3 publication Critical patent/EP1138878A3/fr
Application granted granted Critical
Publication of EP1138878B1 publication Critical patent/EP1138878B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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 component of a gas turbine with a plate-shaped, projecting component section according to the preamble of claim 1.
  • Plate-shaped projecting component sections are often found in gas turbines where, for structural reasons, overhanging areas of main components, such as blades, fasteners are provided or sealing elements, even between two adjacent components, must be attached. Such overhanging component sections are problematic, especially in areas subject to high thermal stress, in which hot gas is applied to the surface. There it is often necessary to provide cooling.
  • a cooled turbine gas turbine blade in which overhanging regions are formed in the form of plate-shaped cantilevered component sections which are mounted in the axial direction in front of and behind the blade root to ensure coverage in the hub region with the adjacently arranged blade root regions of rotor blades.
  • cooling holes are provided, which are flowed through by convection cooling air.
  • the cooling holes extend, for example, in the front overhanging component portion in the circumferential direction and are fed by the main cooling air supply. Due to the high thermal load in this area, turbulence generators are additionally present in the cooling bores in order to improve the heat transfer.
  • the rear, overhanging component portion has a plurality of axially extending cooling holes, which are also fed by the main cooling air supply.
  • the cooling holes open axially at the downstream end of the component section, so that the cooling medium emerges into the hot gas stream after flowing through the cooling channels.
  • the trailing edge cavity of the blade platform has a plurality of film cooling passages which ensure film cooling of the blade trailing edge.
  • the trailing edge cavity is produced in a casting process using a ceramic core.
  • the concerns US 5460486 A a turbine blade of a gas turbine with at least one extending in the blade cooling air duct, and arranged at the blade tip shroud segment, which forms a blade reinforcing band together with other segments of adjacent blades, and with a in the shroud segment substantially vertical to the blade axis and running with the cooling air passage channel connected to the blade cooling air channel located in the blade inflow region, from which cooling air holes lead to the surface of the shroud segment.
  • a film cooling is provided in this solution, wherein the film cooling holes are arranged downstream of the component edge (sealing edge) of the shroud segment relative to the flow direction of the hot gas.
  • the invention seeks to avoid the disadvantages described. It is the object of the invention to provide a component of a gas turbine with a plate-shaped, projecting component portion of the type mentioned, which allows more effective cooling of the surface acted upon by hot gas and thus has an increased life with reduced cooling air requirement.
  • the plenum in the form of at least one first cooling hole opens at the axial downstream end of the component portion.
  • a number of preferred embodiments is directed to the simple and cost-effective implementation of this cooling concept.
  • the choice of the optimum shaping process for the plenum depends mainly on the manufacturing process of the actual component, on which the plate-shaped projecting portion is provided. Other important aspects are the geometry to be realized, as well as the manufacturing specifications.
  • a multi-part core is used to realize the desired geometry of the plenum.
  • lateral openings for positioning the core may be required, which can be closed subsequently, that is, following the molding process.
  • the plenum is connected via feed channels with a Weinplenum, which supplies the blade with cooling air.
  • a Weinplenum which supplies the blade with cooling air.
  • the above-described cooling concept can be implemented for use in any desired, thermally highly stressed components of a gas turbine, it is preferably used on overhangs of turbine blades.
  • the thermal loads are particularly high, on the other hand, in the immediate vicinity of the overhang usually provided a coolant supply anyway, which can be particularly easy to implement the cooling concept of the invention.
  • plenum 10 In the in the Fig. 1 and Fig. 2 illustrated embodiment, four substantially parallel and spaced apart plenum 10 are provided on the overhang 1, which consistently pass through the overhang 1 and open in the form of first cooling holes at the axial downstream end of the component section.
  • the plenums run directly adjacent to the surface 2 and cool them in this area by a not shown in detail, convective pass cooling medium.
  • second cooling bores 12 are provided, preferably arranged in rows and in association with the plenums 10. They emanate from the plenum 10 and open into vent openings 13 at the surface 2, upstream of the axial downstream end of the overhang. In this way, cooling medium is blown out of the plenum 10 through the blow-out openings 13 in such a way that a coherent cooling film is formed.
  • the surface 2 is optimally cooled.
  • the plenums 10 may be formed by EDM tools 19 which drill through holes in the overhang 1. It is thus made a connection to a Hauptplenum 5 below the platform 3, whereby the Pleni 10 are fed with cooling air from this area.
  • the cross section of the individual plenums 10 may vary to achieve a cooling effect tailored to the local heat load. This also applies with regard to their number and distribution of their arrangement along the overhang 1. The same applies mutatis mutandis to the cooling holes or outlet openings 12, which are responsible for the formation of the cooling film.
  • Fig. 3 illustrated embodiment shows a plenum 30, which passes through the overhang 1 with respect to its longitudinal and transverse extent largely completely. This allows a largely ideal uniformed convective cooling of the surface 2 and also offers the possibility to arrange the (not shown here) film cooling air holes in any distributed.
  • Feed channels 6 are provided for this purpose, which establish the connection between the main plenum 5 and the plenum 30.
  • the plenum 30 and the feed channels 6 are in this case formed directly during the casting process.
  • a in Fig. 4 shown core 39, which dictates the shape of the plenum 30.
  • two feed channel sections 38 are provided to form the feed channels 6.
  • 39 can be formed in a simple manner, the plenum 30 including the feed channels 6.
  • the above-described concept is not limited to the application to overhangs of turbine blades, but an application is possible wherever plate-shaped cantilevered component sections are exposed to high thermal loads and therefore must be effectively cooled.

Landscapes

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

Claims (7)

  1. Composant d'une turbine à gaz comprenant une portion de composant en forme de plaque, en saillie, comprenant :
    - une surface (2) sollicitée par du gaz chaud,
    - au moins une chambre (10 ; 30) associée exclusivement à la portion de composant (1), laquelle est disposée directement à côté de la surface (2) sollicitée par le gaz chaud et peut être parcourue par un fluide de refroidissement de manière convective,
    caractérisé en ce que
    - la chambre (10 ; 30) débouche, sous forme d'au moins un alésage de refroidissement, à l'extrémité aval axiale de la portion de composant,
    - des deuxièmes alésages de refroidissement (12) partent de la chambre (10 ; 30) et les alésages de refroidissement (12) présentent des ouvertures de soufflage (13) qui débouchent, en amont de l'extrémité aval axiale de la portion de composant (1), au niveau de la surface (2) sollicitée par le gaz chaud, de sorte qu'un film de refroidissement puisse être produit.
  2. Composant selon la revendication 1, caractérisé en ce que la chambre (30, 50) traverse substantiellement complètement la portion de composant (1).
  3. Composant selon la revendication 1 ou 2, caractérisé en ce que la chambre (30, 50) est moulée dans un procédé de coulée.
  4. Composant selon la revendication 3, caractérisé en ce que la chambre (30 ; 50) est formée au moyen d'un noyau en plusieurs parties (38 ; 39).
  5. Composant selon la revendication 1 ou 2, caractérisé en ce que la chambre (10) et/ou les ouvertures de soufflage (13) sont fabriquées par un procédé EDM.
  6. Composant selon l'une quelconque des revendications précédentes, caractérisé en ce que la chambre (10 ; 30) est connectée par le biais de canaux d'alimentation (6) à une chambre principale (5).
  7. Composant selon l'une quelconque des revendications précédentes, caractérisé en ce que la portion de composant est réalisée sous forme d'un porte-à-faux (1) formé sur une aube de turbine (4).
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
DE10016081 2000-03-31
DE10016081A DE10016081A1 (de) 2000-03-31 2000-03-31 Plattenförmiger, auskragender Bauteilabschnitt einer Gasturbine

Publications (3)

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

Families Citing this family (9)

* 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
CH700320A1 (de) * 2009-01-30 2010-07-30 Alstom Technology Ltd Verfahren zum herstellen eines bauteils einer gasturbine.
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
WO2014163694A2 (fr) 2013-03-13 2014-10-09 Moody Jack K Agencement de trou de refroidissement à tranchée pour une ailette composite à matrice céramique
US11118474B2 (en) * 2017-10-09 2021-09-14 Raytheon Technologies Corporation Vane cooling structures

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
US5344283A (en) * 1993-01-21 1994-09-06 United Technologies Corporation Turbine vane having dedicated inner platform cooling
US5413458A (en) * 1994-03-29 1995-05-09 United Technologies Corporation Turbine vane with a platform cavity having a double feed for cooling fluid
US5823741A (en) * 1996-09-25 1998-10-20 General Electric Co. Cooling joint connection for abutting segments in a gas turbine engine
JP3495579B2 (ja) 1997-10-28 2004-02-09 三菱重工業株式会社 ガスタービン静翼

Also Published As

Publication number Publication date
EP1138878A2 (fr) 2001-10-04
US20010036407A1 (en) 2001-11-01
DE50113955D1 (de) 2008-06-26
EP1138878A3 (fr) 2003-10-01
DE10016081A1 (de) 2001-10-04
US6565317B2 (en) 2003-05-20

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