EP1717416A1 - Aube de turbine, utilisation et méthode de fabrication de l'aube de turbine - Google Patents

Aube de turbine, utilisation et méthode de fabrication de l'aube de turbine Download PDF

Info

Publication number
EP1717416A1
EP1717416A1 EP05009054A EP05009054A EP1717416A1 EP 1717416 A1 EP1717416 A1 EP 1717416A1 EP 05009054 A EP05009054 A EP 05009054A EP 05009054 A EP05009054 A EP 05009054A EP 1717416 A1 EP1717416 A1 EP 1717416A1
Authority
EP
European Patent Office
Prior art keywords
turbine blade
throttle
blade
cavity
insert
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.)
Withdrawn
Application number
EP05009054A
Other languages
German (de)
English (en)
Inventor
Malte Dr. Blomeyer
Karsten Klein
Christian Lerner
Jan Münzer
Uwe Dr. Paul
Olaf Schmidt
Oliver Schneider
Silke Settegast
Rostislav Dr. Teteruk
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP05009054A priority Critical patent/EP1717416A1/fr
Publication of EP1717416A1 publication Critical patent/EP1717416A1/fr
Withdrawn legal-status Critical Current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
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • 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
    • 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
    • F05D2230/237—Brazing
    • 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
    • F05D2250/30—Arrangement of components
    • F05D2250/32—Arrangement of components according to their shape
    • F05D2250/323—Arrangement of components according to their shape convergent
    • 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 cast, cooled turbine blade with a wing-shaped blade profile, which is formed by a concave pressure side wall and a convex suction side wall and which has at least one cavity for guiding a coolant between the two side walls. Furthermore, the invention relates to the use and manufacture of such a turbine blade.
  • a generic turbine blade for a gas turbine is from the US 5,243,759 known.
  • the turbine blade has seen in cross-section in the flow direction of the hot gas, a plurality of successive cavities, which cooling air can be supplied by two arranged in the blade root supply channels.
  • a first, arranged immediately behind the leading edge cavity is separated by a barrier rib from a second cavity.
  • One of the two supply channels merges into the second cavity, which is in fluid communication with the first cavity via connecting channels provided in the barrier rib.
  • Film cooling holes extend from the first cavity through the outer wall of the turbine blade, through which cooling air blown from the supply channel via the second cooling air fed into the first cavity is blown during operation of the gas turbine.
  • the amount of blown cooling air depends on the one hand on the pressure of the provided cooling air and on the other hand on the number and size of the cavities and the connecting channels in the partition wall.
  • connection channels are made by spacers, which connect the casting cores together and support each other. After casting the turbine blade, both the casting cores and the spacers are purged and removed from the turbine blade so that voids and connection channels remain within the turbine blade.
  • the connecting channels in the interior of the turbine blade, the cavities interconnected subject to the manufacturing tolerances.
  • these connecting channels are dimensioned so that at least the turbine blade during operation undergoes at least sufficient cooling.
  • the object of the present invention is to provide a generic turbine blade, which, used in a gas turbine, results in increased efficiency of the gas turbine during operation.
  • the task directed towards the turbine blade is achieved by the features of claim 1, the use directed object by the features of claim 7 and the manufacturing process directed by the features of claim 8.
  • the invention is based on the knowledge to provide in a cast turbine blade at least one separately manufactured throttle insert, which is equipped with at least one throttle opening, whose cross-section adjusts the flow of coolant targeted.
  • a molded cavity boundary or wall having communication passages for passing coolant is partially replaced by a throttle insert with prefabricated throttle openings.
  • the flow of coolant defining opening of the compound of two rooms is no longer determined by the highly tolerance-prone casting, but by the provided in the throttle insert and prefabricated throttle openings. These can be manufactured with a much greater accuracy than the cast connection channels, for example by machining such as drilling or milling. A needs-based, economical dosage of coolant is achieved.
  • the coolant can be forwarded both from a first cavity into a second cavity or throttled outward.
  • the casting cores used to make the turbine blade can be increased, which promotes core stability and also simplifies the interior design of the turbine blade. This leads in total to a reduction of development costs.
  • the invention does not require any spacers arranged between the casting cores of the casting mold, to be produced to the desired degree, which later leave the connecting channels provided between the cavities.
  • the flowable through the throttle opening portion of the coolant is used in the turbine blade only for convective cooling, for effusion and / or film cooling of the turbine blade.
  • the proportion of the coolant flowing through the throttle openings is not immediately used for impingement cooling, i. the throttle insert is not an impingement cooling element or sheet.
  • the two cavities are separated by a common, cast wall of the turbine blade, in which connection channels are provided.
  • the production of the cavities, the wall and the connecting channels takes place with a casting mold, in which two casting cores are connected by means of spacers.
  • the spacers are manufactured with comparatively large cross-sections, so that in the manufactured turbine blade more coolant would flow through the remaining connecting channel than required at least. Due to the additional introduction of a throttle insert in the turbine blade - in the flow direction of the coolant immediately before or after the connecting channels - in which throttle openings are already provided, which flows through the connecting channel Coolant dosed because the throttle opening has a smaller, transverse to the flow of coolant flow area than the connecting channel. The throttle opening and the connecting channel are thus connected in series.
  • the throttle insert is disposed in the interior of the turbine blade so as to abut against a cast support rib substantially separating two cavities, or arranged comparatively close, preferably parallel. To keep the flow losses in the coolant low, the throttle opening and the connecting channel are aligned.
  • the throttle insert extends in the direction of the blade longitudinal axis approximately over the entire height of the blade profile.
  • the throttle insert (s) may be part of the casting mold so as to be cast during casting of the turbine blade.
  • the throttle openings are then filled with the core material and are opened with removal of the casting core.
  • the throttle insert may be incorporated into the cast turbine blade such that it forms the common wall separating the part cavities.
  • the throttle openings incorporated in the throttle insert continue to operate according to the invention.
  • the prefabricated, provided with at least one throttle opening Throttle insert is inserted into the mold and is then cast together with the turbine blade.
  • the throttle insert is thus a part of the casting core that remains in the turbine blade after casting, whereas the remaining casting core is dissolved out of the interior.
  • the turbine blade can be particularly inexpensive to produce without finishing and bring the throttle insert effectively and firmly with the turbine blade. This is particularly advantageous in the case of rotor blades, since they are exposed to enormous centrifugal forces during operation.
  • FIG. 1 shows a gas turbine 1 in a longitudinal partial section. It has inside a rotatably mounted about a rotation axis 2 rotor 3, which is also referred to as a turbine runner. Along the rotor 3 successively follow an intake 4, a compressor 5, a toroidal annular combustion chamber 6 with several Coaxially arranged burners 7, a turbine unit 8 and the exhaust housing 9.
  • the annular combustion chamber 6 forms a combustion chamber 17 which communicates with an annular flow channel 18.
  • There four successive turbine stages 10 form the turbine unit 8. Each turbine stage 10 and each compressor stage is formed of two blade rings.
  • the turbine blades 21 in this case have a blade root 25, a platform region 27 and a wing-shaped airfoil profile 29 in succession along a blade longitudinal axis 23.
  • At least the turbine blades 21 of the front turbine stages, based on the flow direction of the hot gas 11, are cast. They are hollow in their interior for the guidance of coolant, preferably cooling air, so that they can withstand the occurring in the front region of the turbine unit 8, particularly high temperatures.
  • a blade profile 29 of a turbine blade 21 according to the invention is shown in perspective in FIG.
  • the blade profile 29 has a leading edge 31 for the inflowing hot gas 11 and a trailing edge 33, at which the hot gas 11 flowing around the blade profile 29 leaves the turbine blade 21.
  • a support rib 38 is provided between the pressure side wall 37 and the suction side wall 35, which connects and supports the two walls.
  • a plate-shaped throttle insert 39 is provided over approximately the complete height of the blade profile 29, in which a plurality of throttle openings 41 in the form of bores 43 are introduced.
  • the throttle insert 39 is close to the two blade walls 35, 37 and supports the two side walls 35, 37 additionally in the region of the trailing edge 33 from each other.
  • the throttle insert 39 may be part of the casting mold for casting the turbine blade 21 remaining in the casting after casting, or it has been retrofitted into the casting and tightly secured between the pressure sidewall 37 and the suction sidewall 35 by welding, brazing or other suitable method .
  • the throttle openings 41 were made as bores. Since the bores can be made mechanically simple and comparatively precise with respect to a casting process, they are not subject to such great tolerance variations as the connecting ducts of the prior art remaining after casting by removal of the spacers.
  • the support rib 38 includes with the pressure side wall 37 and the suction side wall 35 a first cavity 45 a.
  • a second cavity 47 which is partially bounded by the throttle insert 39, follows downstream of the hot gas flow direction.
  • Both cavities 45, 47 each have a feed channel 49 for supplying coolant 51.
  • the turbine blade 21 according to the invention is used in a gas turbine 1 to save the operation of this machine coolant 51, preferably cooling air, since only the proportion of coolant 51 is blown through the throttle openings 41, which is required to cool the trailing edge 33 as needed. Compared with a turbine blade known from the prior art, the turbine blade 21 according to the invention can be manufactured more cheaply.
  • FIG. 1 A further embodiment of a blade profile 129 with a support rib 138 and a throttle insert 139 is shown partially in perspective in FIG.
  • the throttle insert 139 provided in the first cavity 145 bears against a support rib 138 parallel thereto and has at least one throttle opening 141 whose minimum cross section d 2 is smaller than the minimum cross section d 1 of a connecting channel 140 located in the support rib 138.
  • the side of the throttle opening 141 facing the connecting channel 140 is approximately the same size, ie it has substantially the same flow cross-section d 1 as the connecting channel 140.
  • the side of the throttle opening 141 facing the first cavity 145 represents the flow-limiting cross-section d 2 .
  • the guided through the throttle insert 139 proportion of coolant 51 by the simple, inexpensive and comparatively exactly established throttle opening 141 set so that due to the low manufacturing tolerances When drilling or milling no excessive cooling of the leading edge 31 takes place. Coolant 51 can accordingly be saved, which has an efficiency-increasing effect on a gas turbine 1 equipped with this turbine blade 21.
  • the coolant 51 passing from the second cavity 147 into the first cavity 145 also experiences a flow acceleration.
  • FIG. 4 shows a further variant of a throttle insert 239, in which this is mounted in a located in the support rib 238 connecting channel 240.
  • a throttle insert 239 with a throttle opening 241 can be arranged in each connecting channel 240 in each case.
  • the connecting channel 240 has the shape of an opening or a bore, the throttle insert 239 can also be inserted in the form of a sleeve therein
  • the coolant 51 which is supplied as required to a cavity 45, 145 is then used for convective cooling, for effusion and / or film cooling, and discharged accordingly.
  • the invention thus provides a cast, low-cost turbine blade with improved coolant consumption by providing the throttle openings inside the turbine blade in a throttle insert which is not cast with the turbine blade but is prefabricated with, for example, mechanically machined throttle openings.
  • the throttle insert may also be manufactured by a precision casting process to achieve the required throttle opening accuracy.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP05009054A 2005-04-25 2005-04-25 Aube de turbine, utilisation et méthode de fabrication de l'aube de turbine Withdrawn EP1717416A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP05009054A EP1717416A1 (fr) 2005-04-25 2005-04-25 Aube de turbine, utilisation et méthode de fabrication de l'aube de turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP05009054A EP1717416A1 (fr) 2005-04-25 2005-04-25 Aube de turbine, utilisation et méthode de fabrication de l'aube de turbine

Publications (1)

Publication Number Publication Date
EP1717416A1 true EP1717416A1 (fr) 2006-11-02

Family

ID=35677477

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05009054A Withdrawn EP1717416A1 (fr) 2005-04-25 2005-04-25 Aube de turbine, utilisation et méthode de fabrication de l'aube de turbine

Country Status (1)

Country Link
EP (1) EP1717416A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2489837A1 (fr) 2011-02-18 2012-08-22 Siemens Aktiengesellschaft Insert de dosage pour aube de turbine et aube de turbine associée
EP3306036A1 (fr) * 2016-10-04 2018-04-11 Honeywell International Inc. Aube de turbine avec un passage de refroidissement et un régulation de débit
EP3396108A1 (fr) * 2017-04-26 2018-10-31 General Electric Company Procédé permettant de fournir une structure de refroidissement pour un composant
EP3315228B1 (fr) * 2016-10-27 2020-10-07 United Technologies Corporation Composant provenant de la fabrication additive pour une turbine a gaz

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4437810A (en) * 1981-04-24 1984-03-20 Rolls-Royce Limited Cooled vane for a gas turbine engine
US5511937A (en) * 1994-09-30 1996-04-30 Westinghouse Electric Corporation Gas turbine airfoil with a cooling air regulating seal
DE19961565A1 (de) * 1999-12-20 2001-06-21 Abb Alstom Power Ch Ag Verfahren zur Einstellung des Durchflussvolumens eines Kühlmediums durch eine Turbinenkomponente

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4437810A (en) * 1981-04-24 1984-03-20 Rolls-Royce Limited Cooled vane for a gas turbine engine
US5511937A (en) * 1994-09-30 1996-04-30 Westinghouse Electric Corporation Gas turbine airfoil with a cooling air regulating seal
DE19961565A1 (de) * 1999-12-20 2001-06-21 Abb Alstom Power Ch Ag Verfahren zur Einstellung des Durchflussvolumens eines Kühlmediums durch eine Turbinenkomponente

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2489837A1 (fr) 2011-02-18 2012-08-22 Siemens Aktiengesellschaft Insert de dosage pour aube de turbine et aube de turbine associée
EP3306036A1 (fr) * 2016-10-04 2018-04-11 Honeywell International Inc. Aube de turbine avec un passage de refroidissement et un régulation de débit
US10683763B2 (en) 2016-10-04 2020-06-16 Honeywell International Inc. Turbine blade with integral flow meter
EP3315228B1 (fr) * 2016-10-27 2020-10-07 United Technologies Corporation Composant provenant de la fabrication additive pour une turbine a gaz
US10975703B2 (en) 2016-10-27 2021-04-13 Raytheon Technologies Corporation Additively manufactured component for a gas powered turbine
EP3396108A1 (fr) * 2017-04-26 2018-10-31 General Electric Company Procédé permettant de fournir une structure de refroidissement pour un composant
US10583489B2 (en) 2017-04-26 2020-03-10 General Electric Company Method of providing cooling structure for a component

Similar Documents

Publication Publication Date Title
EP1113145B1 (fr) Aube pour turbine a gaz avec section de mesure sur le bord de fuite
EP3182011B1 (fr) Paroi d'un composant à refroidir à l'aide d'air de refroidissement, en particulier paroi de chambre de combustion de turbine à gaz
EP2304185B1 (fr) Aube de turbine pour une turbine à gaz et noyau de coulée pour sa fabrication
EP1201879B1 (fr) Composant refroidi, noyau de coulage et procédé pour la fabrication dudit composant
EP1914036B1 (fr) Aube de turbine pour une turbine avec un canal de refroidissement
EP2639411B1 (fr) Boîtier de turbomachine avec un système de recirculation de fluide
WO2007012590A1 (fr) Aube de turbine refroidie pour turbine a gaz et utilisation d'une aube de turbine de ce type
EP3093447B1 (fr) Rotor d'une turbine a gaz ayant un guidage d'air de refroidissement ameliore
EP1757773A1 (fr) Aube creuse de turbine
DE10355738A1 (de) Rotor für eine Turbine
EP3658751B1 (fr) Aubage d'aube de turbine
EP1895096A1 (fr) Aube mobile de turbine refroidie
EP2818724B1 (fr) Turbomachine et procédé
EP3473808B1 (fr) Pale d'aube pour une aube mobile de turbine à refroidissement intérieur ainsi que procédé de fabrication d'une telle pale
EP1717416A1 (fr) Aube de turbine, utilisation et méthode de fabrication de l'aube de turbine
EP1431662A1 (fr) Chambre de combustion de turbine avec système de refroidissement à circuit fermé
EP1207269B1 (fr) Aube de turbine à gaz
WO2019086065A1 (fr) Conduit intermédiaire produit par fabrication additive et destiné à être agencé entre un compresseur basse pression et un compresseur haute pression, ainsi que procédé de fabrication dudit conduit
EP2161411A1 (fr) Aube de turbine dotée d'une fréquence propre adaptée à l'aide d'un élément d'insertion
EP3112593A1 (fr) Aube de turbine a refroidissement interieur
EP1138878B1 (fr) Composant de turbine à gaz
DE102010049541B4 (de) Laufschaufel für eine Strömungsmaschine
DE102004011151B4 (de) Turbinenschaufel
EP2095894A1 (fr) Procédé destiné à la fabrication d'une aube de turbine refroidie à l'intérieur
EP3464825B1 (fr) Aube de turbine dotée de canaux de refrigerant et orifices d'evacuation

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR LV MK YU

AKX Designation fees paid
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20070503

REG Reference to a national code

Ref country code: DE

Ref legal event code: 8566