EP1041246A1 - Aube de turbine à gaz coulée avec refroidissement interne, procédé et dispositif de fabrication d'un collecteur dans l'aube de turbine à gaz - Google Patents

Aube de turbine à gaz coulée avec refroidissement interne, procédé et dispositif de fabrication d'un collecteur dans l'aube de turbine à gaz Download PDF

Info

Publication number
EP1041246A1
EP1041246A1 EP99106454A EP99106454A EP1041246A1 EP 1041246 A1 EP1041246 A1 EP 1041246A1 EP 99106454 A EP99106454 A EP 99106454A EP 99106454 A EP99106454 A EP 99106454A EP 1041246 A1 EP1041246 A1 EP 1041246A1
Authority
EP
European Patent Office
Prior art keywords
gas turbine
turbine blade
core
supply channels
casting
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Withdrawn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
EP99106454A
Other languages
German (de)
English (en)
Inventor
Peter Dipl.-Ing. Tiemann
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 EP99106454A priority Critical patent/EP1041246A1/fr
Priority to DE50003266T priority patent/DE50003266D1/de
Priority to PCT/EP2000/002606 priority patent/WO2000058606A1/fr
Priority to EP00920564A priority patent/EP1165939B1/fr
Priority to US09/937,829 priority patent/US6565318B1/en
Priority to JP2000608077A priority patent/JP4567206B2/ja
Publication of EP1041246A1 publication Critical patent/EP1041246A1/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Withdrawn legal-status Critical Current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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • F01D5/087—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor in the radial passages of the rotor disc

Definitions

  • the invention relates to a coolant-flowed, cast Gas turbine blade, in particular gas turbine blade with a blade root, which is in a rotating disc of the gas turbine is used and the multiple supply channels for one Internal cooling system and having a distribution space, wherein the supply channels coolant by means of a supply channel the disc can be supplied with the supply channels communicated via the distribution room.
  • the invention further relates to a device for casting a Gas turbine blade with a casting core, the supply channels has forming core ribs, as well as a method of manufacture a cast gas turbine blade.
  • a gas turbine blade is known from US Pat. No. 4,344,738, the one with a blade root in a disc transverse groove of a rotatable Disk of the gas turbine is used, the Washer a supply duct for supplying the gas turbine with coolant.
  • the supply duct opens below of the blade root in the for receiving the blade root certain disc transverse groove.
  • Supply channels go from the blade root through which the coolant enters the internal cooling system is directed.
  • the supply channels predominantly point edged entry openings.
  • U.S. Patent 4,992,026 discloses a coolant flow Gas turbine blade with an internal cooling system, the Coolant is introduced into the blade root through supply channels and through supply channels into the internal cooling system initiated.
  • the supply channels point at their transitions edges set at right angles from the blade root.
  • the internal cooling of the gas turbine blade is said to be high Operating temperatures, strong heating of the Avoid blade material that can cause serious damage can lead.
  • the cooling medium especially those far from its inflow area Parts of the gas turbine blades that have the greatest loads are easily reached.
  • the cooling medium can only be increased Pressure through the supply lines what is often not possible to a sufficient extent.
  • the Distribution room is said to be essentially a reliable and even distribution of the coolant to the supply channels serve, with only small losses of the coolant may occur.
  • This distribution room is the usual one Casting process generally rectangular and shows in particular right-angled transitions of the supply channels to the distribution room. Due to the edged structure strong flow vortices arise at the entrances of the supply channels, which basically good cooling of the flow Ensure areas.
  • the distribution room is in the Blade root, it is not a strong heat load subject and thus has only a low cooling requirement on.
  • This condition can be improved by the inputs the supply channels in the distribution room after the casting process mechanically reworked.
  • this must be because of the geometry of the blade root and the properties of the Scoop material is mainly made by hand and is therefore very labor intensive.
  • this one Procedure does not ensure that all supply channels the desired shape or all of a gas turbine blade Gas turbine blades of one type have the same flow resistance have what a high quality requirements sufficient calculation of the flow properties and however, optimal use of the cooling medium is necessary would.
  • the object of the invention is therefore to provide a coolant through which cast gas turbine blade, in particular gas turbine blade specify the flow optimized Has transitions from the distribution room to the supply channels, that is, low flow resistances at the outlet openings of the distribution room.
  • Distribution room and internal cooling system are said to be in a single manufacturing process, the Casting process, can be produced.
  • Another object of the invention consists of an apparatus and a method for Production of such a coolant-flowed, cast Gas turbine blade with a corresponding distribution space specify.
  • the medium fed through the supply channel of the disc no longer has to go through two 90 ° angles in the internal cooling system be introduced, but is in a flowing, continuous flow movement directly to the internal cooling system headed. It arises with the flow around Cooling medium no cavities in which the cooling medium as in Dead zones stands.
  • the cooling medium supplied is due to the Rounding or flattening of the inlet openings very little swirled.
  • the inlet openings of the supply channels close directly to the distribution room and are in a manufacturing process generated with it.
  • the roundings or flattenings are designed to be reproducible through the casting process.
  • a series of gas turbine blades the same, predetermined sizes or dimensions for the inlet openings and the distribution space.
  • This becomes the basis for reliable prediction the coolant requirement or the coolant function delivered. This is particularly important to ensure that even remote parts of the gas turbine blades be reliably cooled and thus wear is minimized by overheating.
  • the coolant is already at a low pressure due to the low flow resistance through the distribution room into the supply channels introduced and thus escapes only slightly Dimensions by the space between the blade root and rotating Disk of the gas turbine. This will reduce the losses of the coolant is minimized and the coolant is used optimally.
  • the distribution room is preferably in the form of a semi-ellipsoid. Its base area also corresponds to the largest cross section of the ellipsoid and is inserted into a disk groove Gas turbine blade limited by the disc. The side faces of the semi-ellipsoid and also the transitions between the side surfaces are rounded.
  • This simple one Geometry is easy to manufacture and reliably prevents the formation of dead zones in which the introduced coolant stands. Due to the missing edges only arise low turbulence on the walls of the distribution room, the lead to negligible flow losses. Through the ellipsoidal shape, it is possible to the coolant inflow the supply channels adjacent to different areas of the ellipsoid to steer specifically.
  • a predetermined coolant supply can thus be easily set be that the cross section of the supply channel and the local changes in the cross-sections of the distribution room on the cross sections of the inlet openings downstream are coordinated.
  • the cross-sectional changes of the Distribution room correspond for example in height and width in the shape of a semi-ellipsoid.
  • the transitions between the Inlet openings or around the inlet openings are called transition cross-sections. Due to the rounding or flattening of the inlet openings a larger cross-section of the inlet opening directly at the distributor space, which is then at the transition to the supply channel reduced.
  • the feed channel essentially has one constant cross section, but there may also be a rounding or a flattening of a supply channel available to improve the flow properties be, which increases the cross section to the distribution room.
  • the cross sections described are on top of each other coordinated, i.e. there are predetermined cross-sectional ratios taken into account to coordinate the coolant supply. This is necessary if, for example, an increased coolant requirement due to a high operating temperature respectively special training of the internal cooling system in one Gas turbine blade consists of the high pressures of the coolant need or have a high leakage rate.
  • the lowest longitudinal rib of the Blade root closest to the axis of rotation of the gas turbine, extended along a major axis of the gas turbine blade is.
  • the blade root With its longitudinal ribs, the blade root is at undercuts the washer groove in which it is inserted is.
  • the distribution space for is in the lowest longitudinal rib the cooling medium housed.
  • the blade root is in the range the lowest longitudinal rib extended. This extension takes place along the major axis of the gas turbine blade, the means when the gas turbine blade is inserted perpendicular to the circumference the disc. Due to the extended training of the lower Longitudinal rib is the stability of the holding device in the Blade root still guaranteed and the extension leaves become easy in the manufacturing process of the gas turbine blade accomplish this by thickening the core base of the casting core is trained.
  • the inlet openings of the supply channels on the Height of the transition flank between the lowest longitudinal rib and the overlying longitudinal rib. In this way ensures that the area of the distribution room is only is covered by the lowest longitudinal rib. Between two Longitudinal ribs each have a transition flank, the slope ensures that the blade root is held securely the gas turbine blade in the undercut of the disc given is.
  • the proposed arrangement of the inlet openings of the supply channels ensures that a subsequent Machining of the blade root after the casting process in one defined area can take place without the shovel is damaged, the area of the distribution room itself each located within the lowest longitudinal rib. The extension the longitudinal rib can thus be adjusted almost as desired.
  • the on a casting device for producing a gas turbine blade with a distribution room task by a device for casting a gas turbine blade with a casting core the core ribs forming the supply channels has solved, the casting core forming a distribution space Has core base with which the core ribs are integrally formed are and a smooth transition from the core to the Core ribs is present.
  • the casting device has one inner core.
  • the casting core becomes when the gas turbine blade is cast used to a predetermined inner area to keep the gas turbine blade free of casting material.
  • This free area includes the internal cooling system, the supply channels and the distribution room.
  • the supply channels through elongated approaches of the casting core kept free, the so-called core ribs.
  • the distribution room is widened compared to the core ribs and formed a certain thickness and height area, the so-called core foot.
  • the core base is with the core ribs integrally formed.
  • the rounded design of the transition between the supply channels and the distribution room always takes place in the same Way according to the shape of the casting core. This enables exact adherence to predetermined dimensions. It is possible desired dimensions of the internal cooling system of the gas turbine blade so ensure they are reproducible for a whole series of gas turbine blades can be set can. This provides a basis for an inexpensive and reliable manufacture of internally cooled gas turbine blades.
  • the casting core is formed in one piece, it is against the deformation forces caused by the solidification of the Melt occur, very stable.
  • the transition from the core foot to the core ribs is like this in each case designed to be fluent by changing the cross section preferably continuously from the core ribs to the core foot enlarged. After the casting process is due to the smooth transition of the core ribs into the core foot none Post-processing of the inlet openings of the supply channels Ensuring a low flow resistance is necessary. Accordingly, one step in the production of the Gas turbine blade.
  • the core ribs with increasing Cross section into the core foot which has a thickness, which is larger than the thickness of the core ribs. On this is a further reduction in flow resistance of the coolant flow possible.
  • a further improvement in the flow properties of the This creates a transition from the distribution room to the supply channels delivered that the rounded core ribs into a curved Expire surface that ends in the core base.
  • This The area forms one of the actual entrances to the supply channels imagined narrowing that is a continuous and low turbulence redirection of the coolant flow in the Supply channels supported.
  • Casting core easier to manufacture and also in terms of to better calculate its flow properties.
  • the on a method of manufacturing a gas turbine blade using a described device for casting directed problem is solved in that the distribution room and the supply channels by using the one-piece Pouring core.
  • the casting process is one-piece through the use of the Casting core more accurate and at the same time less time-consuming because the individual parts of the casting core set up together can be.
  • the distribution room must use this procedure can no longer be incorporated mechanically.
  • This complex essentially to be carried out by hand Measure, represents a time-consuming and costly step in the manufacture of a gas turbine blade with a distributor space
  • This process is through the proposed use of the one-piece casting core is now superfluous. Furthermore are the dimensions and thus the coolant flow through the Inlet openings of the supply channels and the distribution room reproducibly adjustable.
  • the distribution room can be necessary or desired can also be mechanically reworked. This is opposite simplifies the usual mechanical processing, that through the casting process most of the material to be worked out is missing. So it's just make minor corrections that require less manufacturing require.
  • Fig.1 is a schematic and not to scale a principle Construction of the base area of a gas turbine blade 1, shown inserted in a disk 3 of a gas turbine.
  • the disk 3 is rotatable about the axis of rotation 14 of the gas turbine.
  • the gas turbine blade 1 is with your blade root 2, which has two longitudinal ribs 13, 13 ', in a disk transverse groove 60 of the disc 3 held.
  • the blade root 2 supports undercuts 12 of the disc 3 with its longitudinal ribs 13,13 'against the parallel to the longitudinal direction 15 of the Gas turbine blade 15 acting centrifugal forces around the axis of rotation 14 rotating disc 3.
  • the disc 3 has a supply channel 6 and the blade root 2 several supply channels 4 through a distribution room 5 are in fluid communication with each other.
  • This line system allows coolant 80 from the Disk 3 in the internal cooling system of the gas turbine blade 1 be directed.
  • the coolant 80 is preferably cooling air.
  • the distribution space 5 has rounded or flattened Inlet openings 7 of the supply channels 4. To this Way, the coolant 80 passed through the distribution space 5 and in the supply channels 4 to the internal cooling system headed with minimal flow losses.
  • the distribution space 5 is on its base side 70 to the supply duct 6 open. On this base page 70 arise so almost no flow losses.
  • the distribution room 5 is rounded like an ellipsoid. It shows in its cross-sectional shape parallel to its base side 70 a shape of itself shrinking ellipse. In the perpendicular cross-sectional area 9, shown in Fig. 4b, it has the cross-sectional shape half an ellipse with itself continuously changing cross section. This semi-elliptical shape will through the rounded inlet openings 7 of the supply channels 4 interrupted. The transitions between the inlet openings 7 of the supply channels 4 and half the ellipse of the distribution room 5 are rounded, so that they do not form appreciable flow resistance.
  • the Inlet openings 7 are both directly next to each other, that is bump or be adjacent to each other.
  • the areas between the inlet openings 7 of the supply channels 4 are rounded in terms of flow, i.e. it there are no edges.
  • the cross section 8 of the feed channel 6 is preferred to the local changes in cross-sections 9 of the Distribution space 5 aligned perpendicular to its base plane 70, just as with the cross sections 10 of the flow downstream inlet openings 7. In this way one for cooling the most distant areas of the gas turbine blade 1 necessary coolant flow 80 safely set become.
  • the supply channels 4 limit with different Cross sections 10 and transition cross-sections adapted to them 11, which merge into the distribution room 5 to the Distribution room 5. This way one can be different strong coolant flow 80, each of the cross section 10 of the supply channel 4 depends on a predetermined Area of the internal cooling system. this makes possible an individual adjustment of the cooling.
  • the gas turbine blade 1 which is shown in Fig.1, is Made in a single casting process, with the distribution space 5 by a casting core 18 with the core ribs 19, the keep the supply channels 4 free of casting material, formed becomes.
  • the distribution space 5 has a height 90, which with the Height 16 of the distance of the lower part of the lower longitudinal rib 13 for the transition into the subsequent longitudinal rib 13 'of Blade base 2 approximately matches.
  • FIG. 2 shows a plan view of the base side 70 of the blade root 2 in a perspective view. From the distribution room 5 rounded or flattened inlet openings 7 of the supply channels 4. The longitudinal ribs 13, 13 'are with Undercuts 12 formed.
  • the supply channels 4 have an oval or elliptical shape, which is particularly streamlined is.
  • the inlet openings are correspondingly elliptical 7 adapted, the cross section of the elliptical Inlet openings 7 from the distribution space 5 to the Supply channels 4 continuously reduced.
  • the coolant flow 80 runs from the supply duct 6 with diameter 8 in the distribution space 5 and through the inlet openings 7 in the supply channels 4. Through the rounded inlet openings 7 and the rounded distribution space 5 as well as the rounded opening 110 of the feed channel 6, the coolant flow 80 is unhindered in the Internal cooling system of the gas turbine blade 1 introduced.
  • the distribution space 5 has a maximum height 90.
  • FIG. 4b shows a cross section through the view of Fig.3.
  • the blade root 2 of the gas turbine blade is shown, which is cut through the distribution space 5.
  • the distribution room has an elliptical cross-section with the cross-sectional area 9.
  • the casting core 18 shows a casting core 18, which is the essential component the device for casting a gas turbine blade 1 represents.
  • the casting core 18 has core ribs 19 and one Core foot 20 on.
  • the core ribs 19 with the thickness 21 form the Supply channels 4 of the gas turbine blade 1 when casting.
  • the Core foot 20 and core ribs 19 are integrally formed and the core rib 19 go with an increasing cross section 21 in the core foot 20 over. This transition takes place in a continuously increasing cross section 21, so that none abrupt changes in thickness occur.
  • the core ribs 19 are rounded and preferably run into a curved one Surface 24, which ends in the core base 20. In this way is the distribution space 5 after the casting particularly streamlined shaped.
  • 6 shows a longitudinal section through the Core foot 20 and a core rib 19 the continuous transition the thickness 23 of the core rib 19 in the thickness 22 of the core base 20th
  • a casting core 18 described above is used in the manufacture the gas turbine blade 1 described above. He enables easy manufacture of both a large distribution space 5 as well as a continuous transition from Distribution space 5 to the supply ducts 4 of the gas turbine blade, without reworking the gas turbine blade 1 would be necessary in this area. However it is easily possible, such a cast gas turbine blade 1 mechanically rework in their distribution room 5, For example, changed around the gas turbine blade 1 Adjust the requirements later or the same Casting core 18 to use for different models. By the Core foot 20 becomes an essential part of what is to be worked out Materials kept free. The subsequent mechanical Editing is therefore just a correction can be carried out quickly and inexpensively.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Molds, Cores, And Manufacturing Methods Thereof (AREA)
EP99106454A 1999-03-29 1999-03-29 Aube de turbine à gaz coulée avec refroidissement interne, procédé et dispositif de fabrication d'un collecteur dans l'aube de turbine à gaz Withdrawn EP1041246A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP99106454A EP1041246A1 (fr) 1999-03-29 1999-03-29 Aube de turbine à gaz coulée avec refroidissement interne, procédé et dispositif de fabrication d'un collecteur dans l'aube de turbine à gaz
DE50003266T DE50003266D1 (de) 1999-03-29 2000-03-23 Kühlmitteldurchströmte, gegossene gasturbinenschaufel sowie vorrichtung und verfahren zur herstellung eines verteilerraums der gasturbinenschaufel
PCT/EP2000/002606 WO2000058606A1 (fr) 1999-03-29 2000-03-23 Aube de turbine a gaz moulee parcourue par un refrigerant, et dispositif et procede de production d'une chambre distributrice pour l'aube de turbine
EP00920564A EP1165939B1 (fr) 1999-03-29 2000-03-23 Aube de turbine a gaz moulee parcourue par un refrigerant, et dispositif et procede de production d'une chambre distributrice pour l'aube de turbine
US09/937,829 US6565318B1 (en) 1999-03-29 2000-03-23 Cast gas turbine blade through which coolant flows, together with appliance and method for manufacturing a distribution space of the gas turbine blade
JP2000608077A JP4567206B2 (ja) 1999-03-29 2000-03-23 冷却材の貫流する鋳造ガスタービン翼

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP99106454A EP1041246A1 (fr) 1999-03-29 1999-03-29 Aube de turbine à gaz coulée avec refroidissement interne, procédé et dispositif de fabrication d'un collecteur dans l'aube de turbine à gaz

Publications (1)

Publication Number Publication Date
EP1041246A1 true EP1041246A1 (fr) 2000-10-04

Family

ID=8237884

Family Applications (2)

Application Number Title Priority Date Filing Date
EP99106454A Withdrawn EP1041246A1 (fr) 1999-03-29 1999-03-29 Aube de turbine à gaz coulée avec refroidissement interne, procédé et dispositif de fabrication d'un collecteur dans l'aube de turbine à gaz
EP00920564A Expired - Lifetime EP1165939B1 (fr) 1999-03-29 2000-03-23 Aube de turbine a gaz moulee parcourue par un refrigerant, et dispositif et procede de production d'une chambre distributrice pour l'aube de turbine

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP00920564A Expired - Lifetime EP1165939B1 (fr) 1999-03-29 2000-03-23 Aube de turbine a gaz moulee parcourue par un refrigerant, et dispositif et procede de production d'une chambre distributrice pour l'aube de turbine

Country Status (5)

Country Link
US (1) US6565318B1 (fr)
EP (2) EP1041246A1 (fr)
JP (1) JP4567206B2 (fr)
DE (1) DE50003266D1 (fr)
WO (1) WO2000058606A1 (fr)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1234949A2 (fr) * 2001-02-26 2002-08-28 United Technologies Corporation Configuration des entrées d'air de refroidissement dans le pied d'une aube
WO2010108879A1 (fr) * 2009-03-23 2010-09-30 Alstom Technology Ltd Turbine à gaz
EP2243574A1 (fr) * 2009-04-20 2010-10-27 Siemens Aktiengesellschaft Dispositif de coulée destiné à la fabrication d'une aube directrice de turbine d'une turbine à gaz et aube directrice de turbine
EP2639407A1 (fr) * 2012-03-13 2013-09-18 Siemens Aktiengesellschaft Agencement de turbine à gaz pour diminuer les contraintes sur des disques de turbine et turbine à gaz associée
EP2896786A1 (fr) * 2014-01-20 2015-07-22 Honeywell International Inc. Ensembles de rotor de turbine avec des cavités de fente améliorées
CN106687232A (zh) * 2014-09-04 2017-05-17 赛峰航空器发动机 用于制造陶瓷芯的方法
CN106890945A (zh) * 2015-12-17 2017-06-27 通用电气公司 模芯组件及熔模铸造方法
EP3336313A1 (fr) * 2016-12-19 2018-06-20 Rolls-Royce Deutschland Ltd & Co KG Ensemble d'aube mobile pour turbines d'une turbine turbine à gaz et procédé de fourniture d'air sceau dans un ensemble d'aube mobile pour turbines
EP2956626B1 (fr) * 2013-02-12 2019-11-20 United Technologies Corporation Aube de soufflante comprenant des cavités extérieures
FR3087479A1 (fr) * 2018-10-23 2020-04-24 Safran Aircraft Engines Aube de turbomachine

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7216694B2 (en) * 2004-01-23 2007-05-15 United Technologies Corporation Apparatus and method for reducing operating stress in a turbine blade and the like
US7059825B2 (en) * 2004-05-27 2006-06-13 United Technologies Corporation Cooled rotor blade
US20060222587A1 (en) * 2005-03-29 2006-10-05 Paras Prasad Hybrid inorganic nanoparticles, methods of using and methods of making
US7357623B2 (en) * 2005-05-23 2008-04-15 Pratt & Whitney Canada Corp. Angled cooling divider wall in blade attachment
US7690896B2 (en) * 2005-05-27 2010-04-06 United Technologies Corporation Gas turbine disk slots and gas turbine engine using same
US7632071B2 (en) * 2005-12-15 2009-12-15 United Technologies Corporation Cooled turbine blade
EP1806426A1 (fr) * 2006-01-09 2007-07-11 Siemens Aktiengesellschaft Dispositf de fixation pour composants métalliques d'une turbine
CH699996A1 (de) * 2008-11-19 2010-05-31 Alstom Technology Ltd Verfahren zum bearbeiten eines gasturbinenläufers.
US8622702B1 (en) * 2010-04-21 2014-01-07 Florida Turbine Technologies, Inc. Turbine blade with cooling air inlet holes
US20140208771A1 (en) * 2012-12-28 2014-07-31 United Technologies Corporation Gas turbine engine component cooling arrangement
US20170234447A1 (en) * 2016-02-12 2017-08-17 United Technologies Corporation Methods and systems for modulating airflow
WO2019008656A1 (fr) * 2017-07-04 2019-01-10 東芝エネルギーシステムズ株式会社 Aube de turbine et turbine
KR102028804B1 (ko) * 2017-10-19 2019-10-04 두산중공업 주식회사 가스 터빈 디스크
CN110043328B (zh) * 2018-12-17 2021-10-22 中国航发沈阳发动机研究所 一种冷却式变几何低压涡轮导向叶片

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3582230A (en) * 1969-02-26 1971-06-01 Bbc Sulzer Turbomaschinen Turbomachine with cooled rotor
US3918835A (en) * 1974-12-19 1975-11-11 United Technologies Corp Centrifugal cooling air filter
US4203705A (en) * 1975-12-22 1980-05-20 United Technologies Corporation Bonded turbine disk for improved low cycle fatigue life
US4344738A (en) 1979-12-17 1982-08-17 United Technologies Corporation Rotor disk structure
GB2224082A (en) * 1988-10-19 1990-04-25 Rolls Royce Plc Turbine disc having cooling and sealing arrangements
US4992026A (en) 1986-03-31 1991-02-12 Kabushiki Kaisha Toshiba Gas turbine blade
EP0894941A1 (fr) * 1997-07-28 1999-02-03 Asea Brown Boveri AG Rotor d'une turbomachine

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3540752A1 (de) 1985-11-16 1987-05-21 Blaupunkt Werke Gmbh Schaltungsanordnung mit steuerbarem verstaerkungsfaktor
JPS62203902A (ja) * 1986-03-04 1987-09-08 Toshiba Corp ガスタ−ビンホイ−ル
JPH0231355U (fr) * 1988-08-19 1990-02-27
DE3835932A1 (de) * 1988-10-21 1990-04-26 Mtu Muenchen Gmbh Vorrichtung zur kuehlluftzufuehrung fuer gasturbinen-rotorschaufeln
US5117626A (en) * 1990-09-04 1992-06-02 Westinghouse Electric Corp. Apparatus for cooling rotating blades in a gas turbine
US5403156A (en) * 1993-10-26 1995-04-04 United Technologies Corporation Integral meter plate for turbine blade and method
DE4422965A1 (de) * 1994-06-30 1996-01-04 Mtu Muenchen Gmbh Einrichtung zur Abscheidung von Fremdpartikeln aus der den Laufschaufeln einer Turbine zuzuführenden Kühlluft
JPH0828297A (ja) * 1994-07-28 1996-01-30 Hitachi Ltd 高温ガスタービン及び複合発電プラント
JPH0970642A (ja) * 1995-09-05 1997-03-18 Mitsubishi Materials Corp 鋳型の製造方法及びこの鋳型を用いた精密鋳造品の製造方法

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3582230A (en) * 1969-02-26 1971-06-01 Bbc Sulzer Turbomaschinen Turbomachine with cooled rotor
US3918835A (en) * 1974-12-19 1975-11-11 United Technologies Corp Centrifugal cooling air filter
US4203705A (en) * 1975-12-22 1980-05-20 United Technologies Corporation Bonded turbine disk for improved low cycle fatigue life
US4344738A (en) 1979-12-17 1982-08-17 United Technologies Corporation Rotor disk structure
US4992026A (en) 1986-03-31 1991-02-12 Kabushiki Kaisha Toshiba Gas turbine blade
GB2224082A (en) * 1988-10-19 1990-04-25 Rolls Royce Plc Turbine disc having cooling and sealing arrangements
EP0894941A1 (fr) * 1997-07-28 1999-02-03 Asea Brown Boveri AG Rotor d'une turbomachine

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1234949A2 (fr) * 2001-02-26 2002-08-28 United Technologies Corporation Configuration des entrées d'air de refroidissement dans le pied d'une aube
EP1234949A3 (fr) * 2001-02-26 2004-01-14 United Technologies Corporation Configuration des entrées d'air de refroidissement dans le pied d'une aube
WO2010108879A1 (fr) * 2009-03-23 2010-09-30 Alstom Technology Ltd Turbine à gaz
EP2236746A1 (fr) * 2009-03-23 2010-10-06 Alstom Technology Ltd Turbine à gaz
US9341069B2 (en) 2009-03-23 2016-05-17 General Electric Technologyy Gmbh Gas turbine
WO2010121939A1 (fr) * 2009-04-20 2010-10-28 Siemens Aktiengesellschaft Dispositif de coulée pour la production d'une aube de turbine d'une turbine à gaz, et aube de turbine correspondante
CN102458715A (zh) * 2009-04-20 2012-05-16 西门子公司 用于制造燃气轮机的涡轮动叶片的浇铸装置和涡轮动叶片
EP2243574A1 (fr) * 2009-04-20 2010-10-27 Siemens Aktiengesellschaft Dispositif de coulée destiné à la fabrication d'une aube directrice de turbine d'une turbine à gaz et aube directrice de turbine
US9759075B2 (en) 2012-03-13 2017-09-12 Siemens Aktiengesellschaft Turbomachine assembly alleviating stresses at turbine discs
EP2639407A1 (fr) * 2012-03-13 2013-09-18 Siemens Aktiengesellschaft Agencement de turbine à gaz pour diminuer les contraintes sur des disques de turbine et turbine à gaz associée
WO2013135319A1 (fr) * 2012-03-13 2013-09-19 Siemens Aktiengesellschaft Configuration de turbine à gaz réduisant les tensions sur les disques de turbine et turbine à gaz correspondante
EP2956626B1 (fr) * 2013-02-12 2019-11-20 United Technologies Corporation Aube de soufflante comprenant des cavités extérieures
US9777575B2 (en) 2014-01-20 2017-10-03 Honeywell International Inc. Turbine rotor assemblies with improved slot cavities
EP2896786A1 (fr) * 2014-01-20 2015-07-22 Honeywell International Inc. Ensembles de rotor de turbine avec des cavités de fente améliorées
CN106687232A (zh) * 2014-09-04 2017-05-17 赛峰航空器发动机 用于制造陶瓷芯的方法
CN106687232B (zh) * 2014-09-04 2019-04-05 赛峰航空器发动机 用于制造陶瓷芯的方法
US10328485B2 (en) 2014-09-04 2019-06-25 Safran Aircraft Engines Method for producing a ceramic core
CN106890945A (zh) * 2015-12-17 2017-06-27 通用电气公司 模芯组件及熔模铸造方法
EP3336313A1 (fr) * 2016-12-19 2018-06-20 Rolls-Royce Deutschland Ltd & Co KG Ensemble d'aube mobile pour turbines d'une turbine turbine à gaz et procédé de fourniture d'air sceau dans un ensemble d'aube mobile pour turbines
US10619490B2 (en) 2016-12-19 2020-04-14 Rolls-Royce Deutschland Ltd & Co Kg Turbine rotor blade arrangement for a gas turbine and method for the provision of sealing air in a turbine rotor blade arrangement
FR3087479A1 (fr) * 2018-10-23 2020-04-24 Safran Aircraft Engines Aube de turbomachine
US11156107B2 (en) 2018-10-23 2021-10-26 Safran Aircraft Engines Turbomachine blade
GB2578833B (en) * 2018-10-23 2023-02-15 Safran Aircraft Engines Turbomachine blade

Also Published As

Publication number Publication date
EP1165939B1 (fr) 2003-08-13
JP4567206B2 (ja) 2010-10-20
WO2000058606A1 (fr) 2000-10-05
JP2002540347A (ja) 2002-11-26
DE50003266D1 (de) 2003-09-18
US6565318B1 (en) 2003-05-20
EP1165939A1 (fr) 2002-01-02

Similar Documents

Publication Publication Date Title
EP1165939B1 (fr) Aube de turbine a gaz moulee parcourue par un refrigerant, et dispositif et procede de production d'une chambre distributrice pour l'aube de turbine
DE69823236T2 (de) Einrichtung zur kühlung von gasturbinenschaufeln und methode zu deren herstellung
DE3789514T2 (de) Gekühlte Gasturbinenschaufel.
EP1113145B1 (fr) Aube pour turbine a gaz avec section de mesure sur le bord de fuite
EP1223308B1 (fr) Composante d'une turbomachine
DE60035757T2 (de) Turbolader mit variablem förderrahmen
CH697919A2 (de) Turbinenblatt mit konkavem Kühlkanal und darin angeordneten, entgegengesetzte Drallströme bewirkende Turbulatoren.
EP0964981B1 (fr) Aube de turbine et son utilisation dans un systeme de turbine a gaz
EP0892149B1 (fr) Système de refroidissement pour le bord d'attac d'une aube creuse pour turbine à gaz
EP1668236B1 (fr) Chambre de combustion comprenant un dispositif de refroidissement, et procede de production de cette chambre de combustion
DE3840448C2 (de) Stranggießkokille
EP1292760B1 (fr) Configuration d'une aube de turbine pouvant etre refroidie
DE10160135A1 (de) Kokillenrohr zum Stranggießen von Metallen
DE10345761B4 (de) Spritzgießvorrichtung mit einer Mischungseinheit
DE10033271A1 (de) Wassermantelkern
DE69625360T2 (de) Herstellung von strangpressmatrizen
EP1499462A1 (fr) Adaptation du transfert de chaleur sur des coquilles pour coulee continue, en particulier au niveau de la surface du bain
EP1136621A2 (fr) Rouleau rotative
EP0892150B1 (fr) Système de refroidissement pour le bord de fuite des aubes creuses d'une turbine à gaz
DE2127454A1 (de) Gasturbine
WO2001000965A1 (fr) Composant, notamment aube de turbine, pouvant etre expose a un gaz chaud
EP1506826B1 (fr) Lingotière pour la coulée continue
EP1795281A2 (fr) Lingotière
WO2005005785A1 (fr) Aube refroidie pour une turbine a gaz
EP1247937A1 (fr) Aube de turbine à gaz et turbine à gaz

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 CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE

AX Request for extension of the european patent

Free format text: AL;LT;LV;MK;RO;SI

AKX Designation fees paid
REG Reference to a national code

Ref country code: DE

Ref legal event code: 8566

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: 20010405