EP1621730A1 - Element refroidi d'une turbomachine et procédé pour le moulage de cet élement - Google Patents
Element refroidi d'une turbomachine et procédé pour le moulage de cet élement Download PDFInfo
- Publication number
- EP1621730A1 EP1621730A1 EP04017673A EP04017673A EP1621730A1 EP 1621730 A1 EP1621730 A1 EP 1621730A1 EP 04017673 A EP04017673 A EP 04017673A EP 04017673 A EP04017673 A EP 04017673A EP 1621730 A1 EP1621730 A1 EP 1621730A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- component
- cooling channel
- cooling
- turbulator
- guide
- 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.)
- Granted
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Classifications
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- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/20—Actively adjusting tip-clearance
- F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
-
- 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
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
- F23M5/00—Casings; Linings; Walls
- F23M5/08—Cooling thereof; Tube walls
- F23M5/085—Cooling thereof; Tube walls using air or other gas as the cooling medium
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/005—Combined with pressure or heat exchangers
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- 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
- F05D2230/21—Manufacture essentially without removing material by casting
-
- 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
- F05D2250/20—Three-dimensional
- F05D2250/25—Three-dimensional helical
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- 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
- F05D2260/221—Improvement of heat transfer
- F05D2260/2212—Improvement of heat transfer by creating turbulence
Definitions
- the invention relates to a cooled component of a turbomachine through which a hot working fluid flows, in particular a turbine blade of a gas turbine, in whose outer surface can be acted upon by the working medium, a cooling channel is provided, which is flowed through along its longitudinal axis by a cooling fluid. Furthermore, the invention relates to a gas turbine with a cooled component and a method for casting a cooled component.
- a heat exchanger tube which has along its longitudinal axis, extending inside and twisted around the main flow direction ribs.
- the ribs serve to enlarge the inner surface of the tube and to generate a twist in the medium flowing through the tube. This is intended to increase the heat transfer compared to a smooth tube.
- a turbine blade is known as a cooled component of a gas turbine.
- the hot working fluid generated in a gas turbine by the combustion of a fuel flows along the blades of the rotor to generate rotational energy.
- they are cooled by means of air or steam.
- the blades of the gas turbine have a channel extending in the interior of the blade in the region of a leading edge and extending in the radial direction of the rotor. A cooling fluid flowing in this channel cools the particularly thermally stressed leading edge.
- a blade is known for example from DE 197 38 065 A1.
- the object of the invention is to provide a cooled component for a gas turbine, which can be cooled more efficiently to increase efficiency. It is another object of the invention to provide a gas turbine and a method for casting a cooled component for this purpose.
- the object directed to the cooled component is solved by the features of claim 1, the object directed to the gas turbine by the features of claim 15 and that of the method of casting the component by the features of claim 16.
- Advantageous embodiments are specified in the subclaims.
- a means be provided in the cooling channel, which impart a twist to the flowing cooling fluid.
- the swirl in the cooling fluid increases the heat transfer. Consequently, the component can be cooled more efficiently, which can be used either to a cooling fluid savings or to a greater heat dissipation. In both cases, the cooling effect is increased, which leads either by an increased hot gas temperature to an improved efficiency or by a lowered thermal component load to improve the economy.
- An angular momentum on the cooling fluid may be generated if the means for imparting the twist is formed as at least one guide element arranged on the inner surface of the cooling channel, which extends along a helix having a pitch angle of 45 ° or greater. Accordingly, in the cooling fluid flow locally another component in the circumferential direction of the cooling channel is impressed, which represents the twist around the main flow direction.
- the cooling channel in the manner of a multi-start screw on several guide elements with identical pitch angles. This results in a core flow flowing in the center of the cooling channel, from which partial flows directed transversely to the main flow direction form as continuous branches. Therefore, all flow channel segments existing between the vanes can communicate with each other.
- the formation of a controlled and effective core flow over the vane tips in the longitudinal axis leads to increased power values with respect to the heat transfer.
- the central core flow can form centrally in the interior of the cooling channel if each guide element projects into the cooling channel with a radial extent which is less than half the diameter of the cooling channel.
- the cooling channel does not have a massive core in the center.
- each guide element is approximately 0.2 times the diameter of the cooling channel.
- the guide element protrudes into the cooling channel with a radial extent, which is different along the helical profile of the guide element.
- a further increase in the heat transfer can be achieved if the cooling channel has at least one turbulator element on its inner surface.
- the turbulator element is designed as a transversely to the helical line of the guide element extending rib or aligned or staggered portions of a rib or nubs leaves to achieve an increase in heat transfer.
- the turbulence in the cooling fluid caused by the turbulator element can also be used for local adaptation and for increasing the heat transfer.
- Particularly advantageous is the embodiment in which the turbulator elements protrude with a radial extent in the cooling channel, which is less than the radial extent of the guide elements.
- the radial extent of each turbulator element is approximately 0.1 times the diameter of the cooling channel.
- An adaptation to the local requirements with respect to the cooling can be achieved if the pitch angle of the guide elements along the cooling channel is different.
- a partial flow is generated more or less transverse to the main flow direction of the cooling fluid.
- this enables an acceleration or a deceleration of the cooling fluid, so that the heat transfer from the outer wall into the cooling fluid can be advantageously influenced as a result.
- the cross section of the means for impressing the twist in the manner of a pointed thread shaped like a trapezoidal thread, in the manner of a saw thread or in the manner of a round thread.
- the cooled component may be a turbine vane, a turbine blade, a guide ring, or a combustor heat shield.
- the component is a turbine vane or a turbine blade and the cooling channel extends in the region of a leading edge in the blade longitudinal direction.
- the turbulators arranged in a turbine blade with a cooling channel are provided only in the region or part of the cooling channel circumference, which faces the suction-side outer wall.
- secondary flows occur in the cooling fluid flowing in the cooling channel, which cause a different channel-side heat transfer from the blade material into the cooling fluid along the circumference of the cooling channel.
- the suction-side outer wall of a turbine blade due to the flow around hot gas is exposed to higher temperatures than the pressure-side outer wall. Therefore, a different degrees of cooling the suction-side outer wall against the pressure-side outer wall in turbine blades is desirable.
- This is advantageously taken into account by the turbulators are arranged only in the region of the circumference of the channel, which faces the suction-side outer wall of the turbine blade. As a result, at this point a higher channel-side heat transfer can be achieved than before.
- the invention for producing a component in a casting method with a casting mold proposes that the means for imparting a twist during casting be prepared by inserting into a casting core to be inserted in the casting mold for forming a cooling channel in the casting mold the corresponding guide element structure and / or the the Turbulatorelement Modell is incorporated.
- FIG. 6 shows a gas turbine 11 with a compressor 13, a combustion chamber 15 and a turbine unit 17, which follow one another along a rotor 19 of the gas turbine 11.
- a working machine for. B. a generator (not shown) coupled.
- Both in the compressor 13 and in the turbine unit 17 are consecutively provided in blade rings 21, 25 vanes 23 and blades 27.
- the guide vanes 23 and rotor blades 27 of the turbine unit 17 are cooled with a cooling fluid KF, for example air or steam, so that they are at the temperatures prevailing there of the hot working medium A can withstand.
- a cooling fluid KF for example air or steam
- Such a vane 23 is shown as a cooled component 28 in FIG.
- the guide blade 23 has a blade root 31, a platform region 33 and an airfoil 35 successively along the blade axis 29.
- the airfoil 35 extends with a pressure-side outer wall 36 and suction-side outer wall 38 of a leading edge 37 to a trailing edge 39.
- cooling channel 41 is arranged, on the inner surface of a guide member 43 is arranged, the protrudes into the cooling channel 41.
- FIG. 2 shows a section through the blade airfoil 35 of a turbine blade, which may be designed as a guide blade 23 or as a rotor blade 27.
- a diameter D projecting into the four guide elements 43 in the manner of a four-speed screw.
- the diameter D is described by a dividable in sections boundary of the cooling channel cross-section, which belongs to an area equal to the cooling channel cross-section circle.
- the guide elements 43 run in the direction of a center 49 of the cooling channel 41 analogous to a saw thread pointed.
- the cross section of the guide elements could also be trapezoidal triangular.
- FIG. 3 shows the cooling channel 41 with a guide element 43 lying on a helix 44.
- the main flow direction of the cooling fluid KF runs along the longitudinal axis 45 of the cooling channel 41.
- the helix 44 of the guide element 43 has, with respect to each plane perpendicular to the longitudinal axis 45, a pitch angle S, which is 45 ° or greater.
- the guide element 43 protrudes with a radial extent h 1 in the circular cross-section in the cooling channel 41, which is on the order of 0.2 times the diameter D.
- FIG. 3 shows transversely to the helix 44 the guide elements 43 extending rib or knob-shaped Turbulator institute 47, the radial extent h 2 is smaller than that of the guide elements 43, in particular of the order of 0.1 times the diameter D.
- the airfoil 35 of the turbine blade is flowed around by the working medium A.
- the cooling fluid KF for example, compressor air
- the cooling channel 41 in the direction of the longitudinal axis 45.
- the guide elements 43 imprint the cooling fluid KF a transverse to the main flow direction, in particular in the circumferential direction, directed flow component.
- a swirling core flow flowing in the center 49 is generated, which rotates about the longitudinal axis 45 of the cooling channel 41.
- the angular momentum exerted on the cooling fluid KF allows the core flow to flow to the outer edge of the cooling passage 41 into the pocket-shaped flow passage segments 50.
- the radial extent h 1 of the guide elements 43 can extend over the circumference and / or length of the cooling channel 41 rising and decreasing, so that a different sized transverse partial flow can be achieved.
- the turbulator elements 47 are to be arranged in the flow channel sectors 50 at the parts of the circumference of the cooling channel 41 of the blades 27, which are to be designated in the direction of rotation of the rotor 19 as a leading part of the circumference of the cooling channel 41 with locally lower pressure in the cooling fluid flow, ie the turbulator elements 47th are arranged on the side of the cooling channel 41, which faces the suction-side outer wall 38 (see Fig. 2).
- the volume flow rate of the cooling fluid flow decreases, and at the same time, the cooling fluid flow rate and the local heat transfer inducing turbulence increase.
- the turbulent amplification of the cooling effect is locally supported by the flow guidance in the region of the rib structure via the specifically placed turbulator elements 47 on the leading side in the rotating system channel side, so that the adverse effect of the centrifugal force field on the heat transfer of the cooling fluid flow is reduced and a smoothing of local temperature gradients and a Improvement of the low-cycle fatigue behavior is brought about.
- FIG. 4 shows a combustor heat shield 55 as a cooled component 28 of a gas turbine engine.
- the combustion chamber heat shield 55 has an outer wall 36a which can be acted upon by a hot working medium and in which a plurality of cooling channels 41 are provided for cooling the same.
- the channels 41 are each formed with four guide elements 43 in the manner of a four-speed screw.
- Fig. 5 shows the rotor 19 of a gas turbine 11 with a blade attached thereto 27.
- a guide vane 23 is disposed adjacent.
- a guide ring 61 of the blade tip 52 is opposite.
- the guide ring 61 limits the flow channel of the turbine unit 17 radially outward.
- a plurality of cooling channels 41 are arranged, in which the cooling fluid KF can flow, wherein a plurality of guide elements 43 impose an angular momentum or a twist on the cooling fluid KF.
- turbulators 47 are applicable in the areas of the cooling passage circumference of combustion heat shields 55 and / or guide rings 61, which is closest to the hot gas loaded outer wall.
- the cooling channel 41 is provided in the rotor blade 27 in the area of the leading edge 37, in which the guide element 43 imparts a twist to the cooling fluid KF.
- the pitch angle S of the helix 44 is increased in comparison to the radially inner region 67, which leads to an acceleration of the cooling fluid KF. It can thus be a targeted influencing the flow velocity of the cooling fluid KF and the heat transfer.
- the cooled component 28, in particular a moving blade 27, is known to be produced in the casting process.
- the means for impressing a swirl ie the guide elements 43 and possibly the turbulator elements, are already taken into account during casting by incorporating the corresponding guide element structure and / or the turbulator element structure before a casting core to be used for forming a cooling channel in a casting mold becomes.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
AT04017673T ATE410586T1 (de) | 2004-07-26 | 2004-07-26 | Gekühltes bauteil einer strömungsmaschine und verfahren zum giessen dieses gekühlten bauteils |
ES04017673T ES2312890T3 (es) | 2004-07-26 | 2004-07-26 | Elemento enfriado de una turbomaquina y procedimiento de moldeo de este elemento enfriado. |
DE502004008210T DE502004008210D1 (de) | 2004-07-26 | 2004-07-26 | Gekühltes Bauteil einer Strömungsmaschine und Verfahren zum Giessen dieses gekühlten Bauteils |
EP04017673A EP1621730B1 (fr) | 2004-07-26 | 2004-07-26 | Element refroidi d'une turbomachine et procédé pour le moulage de cet élement |
CN200510084761.0A CN1727643B (zh) | 2004-07-26 | 2005-07-20 | 流体机械的冷却构件及其铸造方法和有该构件的燃气轮机 |
US11/189,409 US7824156B2 (en) | 2004-07-26 | 2005-07-26 | Cooled component of a fluid-flow machine, method of casting a cooled component, and a gas turbine |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP04017673A EP1621730B1 (fr) | 2004-07-26 | 2004-07-26 | Element refroidi d'une turbomachine et procédé pour le moulage de cet élement |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1621730A1 true EP1621730A1 (fr) | 2006-02-01 |
EP1621730B1 EP1621730B1 (fr) | 2008-10-08 |
Family
ID=34925939
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP04017673A Expired - Lifetime EP1621730B1 (fr) | 2004-07-26 | 2004-07-26 | Element refroidi d'une turbomachine et procédé pour le moulage de cet élement |
Country Status (6)
Country | Link |
---|---|
US (1) | US7824156B2 (fr) |
EP (1) | EP1621730B1 (fr) |
CN (1) | CN1727643B (fr) |
AT (1) | ATE410586T1 (fr) |
DE (1) | DE502004008210D1 (fr) |
ES (1) | ES2312890T3 (fr) |
Cited By (5)
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EP2703603A2 (fr) | 2012-09-04 | 2014-03-05 | Rolls-Royce Deutschland Ltd & Co KG | Aube de turbine à gaz dotée d'un élément générateur de tourbillon et son procédé de fabrication |
WO2015032936A1 (fr) * | 2013-09-09 | 2015-03-12 | Siemens Aktiengesellschaft | Chambre de combustion d'une turbine à gaz et outil et procédé permettant de produire des canaux de refroidissement dans un composant d'une turbine à gaz |
WO2016014056A1 (fr) * | 2014-07-24 | 2016-01-28 | Siemens Aktiengesellschaft | Système de refroidissement d'un profil d'une turbine comprenant des bloqueurs d'écoulement s'étendant dans le sens de l'envergure |
EP3009605A4 (fr) * | 2014-08-04 | 2016-08-31 | Mitsubishi Hitachi Power Sys | Élément à haute température de turbine à gaz, turbine à gaz équipée de celui-ci, et procédé de fabrication de élément à haute température de turbine à gaz |
DE102016221566A1 (de) * | 2016-11-03 | 2018-05-03 | Bayerische Motoren Werke Aktiengesellschaft | Wasserabscheider zum Abscheiden von Wasser in einem Fahrzeug |
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US7665955B2 (en) * | 2006-08-17 | 2010-02-23 | Siemens Energy, Inc. | Vortex cooled turbine blade outer air seal for a turbine engine |
US7665965B1 (en) * | 2007-01-17 | 2010-02-23 | Florida Turbine Technologies, Inc. | Turbine rotor disk with dirt particle separator |
GB2498551B (en) * | 2012-01-20 | 2015-07-08 | Rolls Royce Plc | Aerofoil cooling |
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US9995148B2 (en) | 2012-10-04 | 2018-06-12 | General Electric Company | Method and apparatus for cooling gas turbine and rotor blades |
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EP3039340B1 (fr) * | 2013-08-30 | 2018-11-28 | United Technologies Corporation | Passages de dilution à tourbillonnement à section contractée pour chambre de combustion de moteur à turbine à gaz |
EP3084182B8 (fr) * | 2013-12-20 | 2021-04-07 | Raytheon Technologies Corporation | Cavite de refroidissement de composants de turbine a gaz avec elements favorisant la generation de tourbillons |
KR101509385B1 (ko) * | 2014-01-16 | 2015-04-07 | 두산중공업 주식회사 | 스월링 냉각 채널을 구비한 터빈 블레이드 및 그 냉각 방법 |
US20150204197A1 (en) * | 2014-01-23 | 2015-07-23 | Siemens Aktiengesellschaft | Airfoil leading edge chamber cooling with angled impingement |
EP2918782A1 (fr) * | 2014-03-11 | 2015-09-16 | United Technologies Corporation | Composant avec trou de refroidissement ayant une rainure hélicoïdale et moteur à turbine à gaz associé |
US9932835B2 (en) * | 2014-05-23 | 2018-04-03 | United Technologies Corporation | Airfoil cooling device and method of manufacture |
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US10690055B2 (en) | 2014-05-29 | 2020-06-23 | General Electric Company | Engine components with impingement cooling features |
US9957816B2 (en) | 2014-05-29 | 2018-05-01 | General Electric Company | Angled impingement insert |
US10563514B2 (en) | 2014-05-29 | 2020-02-18 | General Electric Company | Fastback turbulator |
US10012090B2 (en) * | 2014-07-25 | 2018-07-03 | United Technologies Corporation | Airfoil cooling apparatus |
EP3186559B1 (fr) * | 2014-08-26 | 2020-10-14 | Siemens Energy, Inc. | Système de refroidissement pour injecteurs de carburant à l'intérieur d'une chambre de combustion dans un moteur à turbine |
US10697306B2 (en) | 2014-09-18 | 2020-06-30 | Siemens Aktiengesellschaft | Gas turbine airfoil including integrated leading edge and tip cooling fluid passage and core structure used for forming such an airfoil |
US10280785B2 (en) | 2014-10-31 | 2019-05-07 | General Electric Company | Shroud assembly for a turbine engine |
US10233775B2 (en) | 2014-10-31 | 2019-03-19 | General Electric Company | Engine component for a gas turbine engine |
KR101609562B1 (ko) | 2014-11-27 | 2016-04-06 | 한국항공우주연구원 | 유동 안내부를 갖는 터빈 블레이드 |
CN107429569B (zh) | 2015-04-03 | 2019-09-24 | 西门子公司 | 具有低流动框架式通道的涡轮动叶后缘 |
US10577947B2 (en) * | 2015-12-07 | 2020-03-03 | United Technologies Corporation | Baffle insert for a gas turbine engine component |
GB2574368A (en) * | 2018-04-09 | 2019-12-11 | Rolls Royce Plc | Coolant channel with interlaced ribs |
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CN110700896B (zh) * | 2019-11-29 | 2020-09-01 | 四川大学 | 具有旋流冲击冷却结构的燃气轮机涡轮转子叶片 |
US11441778B2 (en) * | 2019-12-20 | 2022-09-13 | Raytheon Technologies Corporation | Article with cooling holes and method of forming the same |
CN115247575B (zh) * | 2022-05-12 | 2024-05-03 | 中国航发四川燃气涡轮研究院 | 一种螺旋状涡轮叶片冷却单元及冷却结构 |
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EP1283326B1 (fr) * | 2001-08-09 | 2005-12-21 | Siemens Aktiengesellschaft | Refroidissement d'une aube de turbine |
GB0222352D0 (en) * | 2002-09-26 | 2002-11-06 | Dorling Kevin | Turbine blade turbulator cooling design |
FR2858352B1 (fr) * | 2003-08-01 | 2006-01-20 | Snecma Moteurs | Circuit de refroidissement pour aube de turbine |
-
2004
- 2004-07-26 DE DE502004008210T patent/DE502004008210D1/de not_active Expired - Lifetime
- 2004-07-26 EP EP04017673A patent/EP1621730B1/fr not_active Expired - Lifetime
- 2004-07-26 ES ES04017673T patent/ES2312890T3/es not_active Expired - Lifetime
- 2004-07-26 AT AT04017673T patent/ATE410586T1/de not_active IP Right Cessation
-
2005
- 2005-07-20 CN CN200510084761.0A patent/CN1727643B/zh not_active Expired - Fee Related
- 2005-07-26 US US11/189,409 patent/US7824156B2/en not_active Expired - Fee Related
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DE3216960A1 (de) * | 1982-05-06 | 1983-11-10 | Kabel Metallwerke Ghh | Verfahren zur herstellung eines rohres mit an seiner oberflaeche schraubenlinienfoermig verlaufenden rippen |
WO2004035992A1 (fr) * | 2002-10-18 | 2004-04-29 | Alstom Technology Ltd. | Composant pouvant etre refroidi |
US20040096313A1 (en) * | 2002-11-12 | 2004-05-20 | Harvey Neil W. | Turbine components |
Cited By (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9506352B2 (en) | 2012-09-04 | 2016-11-29 | Rolls-Royce Deutschland Ltd & Co Kg | Turbine blade of a gas turbine with swirl-generating element and method for its manufacture |
DE102012017491A1 (de) | 2012-09-04 | 2014-03-06 | Rolls-Royce Deutschland Ltd & Co Kg | Turbinenschaufel einer Gasturbine mit Drallerzeugungselement |
EP2703603A2 (fr) | 2012-09-04 | 2014-03-05 | Rolls-Royce Deutschland Ltd & Co KG | Aube de turbine à gaz dotée d'un élément générateur de tourbillon et son procédé de fabrication |
EP2703603A3 (fr) * | 2012-09-04 | 2017-08-16 | Rolls-Royce Deutschland Ltd & Co KG | Aube de turbine à gaz dotée d'un élément générateur de tourbillon et son procédé de fabrication |
WO2015032936A1 (fr) * | 2013-09-09 | 2015-03-12 | Siemens Aktiengesellschaft | Chambre de combustion d'une turbine à gaz et outil et procédé permettant de produire des canaux de refroidissement dans un composant d'une turbine à gaz |
US9822646B2 (en) | 2014-07-24 | 2017-11-21 | Siemens Aktiengesellschaft | Turbine airfoil cooling system with spanwise extending fins |
CN106536858A (zh) * | 2014-07-24 | 2017-03-22 | 西门子公司 | 具有顺翼展延伸流阻断器的涡轮翼型件冷却系统 |
WO2016014056A1 (fr) * | 2014-07-24 | 2016-01-28 | Siemens Aktiengesellschaft | Système de refroidissement d'un profil d'une turbine comprenant des bloqueurs d'écoulement s'étendant dans le sens de l'envergure |
CN106536858B (zh) * | 2014-07-24 | 2019-01-01 | 西门子公司 | 具有顺翼展延伸流阻断器的涡轮翼型件冷却系统 |
US9540934B2 (en) | 2014-08-04 | 2017-01-10 | Mitsubishi Hitachi Power Systems, Ltd. | Hot part of gas turbine, gas turbine including the same, and manufacturing method of hot part of gas turbine |
EP3009605A4 (fr) * | 2014-08-04 | 2016-08-31 | Mitsubishi Hitachi Power Sys | Élément à haute température de turbine à gaz, turbine à gaz équipée de celui-ci, et procédé de fabrication de élément à haute température de turbine à gaz |
TWI609128B (zh) * | 2014-08-04 | 2017-12-21 | 三菱日立電力系統股份有限公司 | 燃氣渦輪機的高溫零件、具備該高溫零件的燃氣渦輪機、及燃氣渦輪機之高溫零件的製造方法 |
DE102016221566A1 (de) * | 2016-11-03 | 2018-05-03 | Bayerische Motoren Werke Aktiengesellschaft | Wasserabscheider zum Abscheiden von Wasser in einem Fahrzeug |
Also Published As
Publication number | Publication date |
---|---|
DE502004008210D1 (de) | 2008-11-20 |
US7824156B2 (en) | 2010-11-02 |
US20070014664A1 (en) | 2007-01-18 |
EP1621730B1 (fr) | 2008-10-08 |
ATE410586T1 (de) | 2008-10-15 |
CN1727643B (zh) | 2010-12-15 |
CN1727643A (zh) | 2006-02-01 |
ES2312890T3 (es) | 2009-03-01 |
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