EP1882818A1 - Générateurs de tourbillons dans microcircuits en serpentins pour refroidissement d'aube - Google Patents
Générateurs de tourbillons dans microcircuits en serpentins pour refroidissement d'aube Download PDFInfo
- Publication number
- EP1882818A1 EP1882818A1 EP07252837A EP07252837A EP1882818A1 EP 1882818 A1 EP1882818 A1 EP 1882818A1 EP 07252837 A EP07252837 A EP 07252837A EP 07252837 A EP07252837 A EP 07252837A EP 1882818 A1 EP1882818 A1 EP 1882818A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- cooling
- vortex generators
- cooling microcircuit
- microcircuit
- refractory metal
- 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
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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/02—Sand moulds or like moulds for shaped castings
- B22C9/04—Use of lost patterns
-
- 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
-
- 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
- F05D2230/211—Manufacture essentially without removing material by casting by precision casting, e.g. microfusing or investment 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
- F05D2250/10—Two-dimensional
- F05D2250/11—Two-dimensional triangular
-
- 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
- F05D2250/10—Two-dimensional
- F05D2250/18—Two-dimensional patterned
- F05D2250/185—Two-dimensional patterned serpentine-like
-
- 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
-
- 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
- F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
- F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs
Definitions
- the present invention relates to a cooling microcircuit for use in turbine engine components, such as turbine blades, that has a plurality of vortex generators within the legs through which a cooling fluid flows to improve cooling effectiveness.
- a typical gas turbine engine arrangement includes at plurality of high pressure turbine blades.
- cooling flow passes through these blades by means of internal cooling channels that are turbulated with trip strips for enhancing heat transfer inside the blade.
- the cooling effectiveness of these blades is around 0.50 with a convective efficiency of around 0.40.
- cooling effectiveness is a dimensionless ratio of metal temperature ranging from zero to unity as the minimum and maximum values.
- the convective efficiency is also a dimensionless ratio and denotes the ability for heat pick-up by the coolant, with zero and unity denoting no heat pick-up and maximum heat pick-up respectively. The higher these two dimensionless parameters become, the lower the parasitic coolant flow required to cool the high-pressure blade.
- the blade cooling flow should not increase and if possible, even decrease for turbine efficiency improvements. That objective is extremely difficult to achieve with current cooling technology. In general, for such an increase in gas temperature, the cooling flow would have to increase more than 5% of the engine core flow.
- the present invention relates to a turbine engine component, such as a turbine blade, which has one or more vortex generators within the cooling microcircuits used to cool the component.
- a cooling microcircuit for use in a turbine engine component.
- the cooling microcircuit broadly comprises at least one leg through which a cooling fluid flows and a plurality of cast vortex generators positioned within the at least one leg.
- a process for forming a refractory metal core for use in forming a cooling microcircuit having vortex generators broadly comprises the steps of providing a refractory metal core material and forming a refractory metal core having a plurality of indentations in the form of the vortex generators.
- FIGS. 1 - 3 illustrate a serpentine microcircuit cooling arrangement for a turbine engine component, such as a turbine blade.
- a turbine engine component 90 such as a high pressure turbine blade, may be cooled using the cooling design scheme shown in FIGS. 1 - 3.
- the cooling design scheme as shown in FIG. 1, encompasses two serpentine microcircuits 100 and 102 located peripherally in the airfoil walls 104 and 106 respectively for cooling the main body 108 of the airfoil portion 110 of the turbine engine component.
- Separate cooling microcircuits 96 and 98 may be used to cool the leading and trailing edges 112 and 114 respectively of the airfoil main body 108.
- the coolant inside the turbine engine component may be used to feed the leading and trailing edge regions 112 and 114. This is preferably done by isolating the microcircuits 96 and 98 from the external thermal load from either the suction side 116 or the pressure side 118 of the airfoil portion 110. In this way, both impingement jets before the leading and trailing edges become very effective.
- the coolant may be ejected out of the turbine engine component by means of film cooling.
- the microcircuit 102 has a fluid inlet 126 for supplying cooling fluid to a first leg 128.
- the inlet 126 receives the cooling fluid from one of the feed cavities 142 in the turbine engine component. Fluid flowing through the first leg 128 travels to an intermediate leg 130 and from there to an outlet leg 132. Fluid supplied by one of the feed cavities 142 may also be introduced into the cooling microcircuit 96 and used to cool the leading edge 112 of the airfoil portion 110.
- the cooling circuit 102 may include fluid passageway 131 having fluid outlets 133.
- the thermal load to the turbine engine component may not require film cooling from each of the legs that form the serpentine peripheral cooling microcircuit 102.
- the flow of cooling fluid may be allowed to exit from the outlet leg 132 at the tip 134 by means of film blowing from the pressure side 116 to the suction side 118 of the turbine engine component.
- the outlet leg 132 may communicate with a passageway 136 in the tip 134 having fluid outlets 138.
- the serpentine cooling microcircuit 100 for the pressure side 116 of the airfoil portion 110.
- the microcircuit 100 has an inlet 141 which communicates with one of the feed cavities 142 and a first leg 144 which receives cooling fluid from the inlet 141.
- the cooling fluid in the first leg 144 flows through the intermediate leg 146 and through the outlet leg 148.
- fluid from the feed cavity 142 may also be supplied to the trailing edge cooling microcircuit 98.
- the cooling microcircuit 98 may have a plurality of fluid passageways 150 which have outlets 152 for distributing cooling fluid over the trailing edge 114 of the airfoil portion 110.
- the outlet leg 148 may have one or more fluid outlets 153 for supplying a film of cooling fluid over the pressure side 116 of the airfoil portion 110 in the region of the trailing edge 114.
- FIGS. 5 - 7 illustrate a photo-lithography method of forming these features onto a refractory metal core material 200.
- the machining process may be done through a chemical etching process.
- Sufficient material may be taken out of the refractory metal core 200 to form the desired vortex generators/turbulators 180.
- these machined indentations are filled with superalloy material to form the vortex generators 180 within the legs of the cooling microcircuits.
- the overall process is referred to as a photo-etch process prior to investment casting.
- the process consists of using the refractory metal core as the core material in an investment casting technique to form the cooling passages with vortex generators in the blade cooling passage.
- the photo-etch process consists of two sub-processes: (1) the preparation of mask material through the process of photo-lithography; and (2) a subsequent process of chemically attacking the refractory metal core material by etching away as small surface indentions.
- a layer of polymer film mask material 202 is placed over the refractory metal core 200 and is subjected to UV light 204.
- the ultraviolet light 204 is programmed to impinge onto the polymer film mask material 202 for curing purposes. As certain designated parts of the polymer film mask material 202 are cured by light, the other surface areas of the polymer film mask material 202 are not affected by the light.
- non-cured polymer film material is chemically removed from the area 210, while the cured polymer film material 202 is maintained so as to form a mask.
- areas of the refractory metal core material 200 not protected by the mask are attacked by an etching chemical solution through acid dip or spray.
- the etching process leaves an indentation 212 in the refractory metal core 200 to form a turbulator, such as a trip strip or a vortex generator.
- a laser beam can be used to outline the vortex generators in the refractory metal core material 200 with beams that penetrate the refractory metal core substrate 200 to form the desired features shown in FIGS. 4A - 4D.
- FIG. 8 illustrates how the photo-etch process leads to the legs 128, 130, 132, 144, 146, and 148 in the turbine engine component 90 after the casting process.
- a wax pattern leads to the solidification of the superalloy, and the refractory metal core 200, as the core material, leads to the open spaces for the legs of the cooling microcircuits.
- the refractory metal core 200 is eventually removed through a leaching process.
- the series of vortex generators 180 are placed on the walls of the legs 128, 130, 132, 144, 146, and/or 148 as shown in FIG. 8.
- both the pressure side and the suction side peripheral serpentine cooling microcircuits may not include film cooling with the exception of the last leg/passage of the serpentine arrangement for the pressure side circuit and for the tip of the suction side serpentine arrangement. Therefore, film cooling may not protect upstream sections of the serpentine cooling design. This is particularly important from a performance standpoint which allows for no mixing of the coolant from film with external hot gases. Since the cooling circuits 100 and 102 are embedded in the walls, their cross sectional area is small and internal features, such as the vortex generators 180 shown in FIGS. 4A - 4D, are needed to increase the convective efficiency of the circuits 100 and 102, leading to an overall cooling effectiveness for the turbine engine component 90. Naturally, the cooling flow may be reduced from typical values of 5% core engine flow to about 3.5%.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP20100010854 EP2282009A1 (fr) | 2006-07-18 | 2007-07-18 | Générateurs de tourbillons dans microcircuits en serpentins pour refroidissement d'aube |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/489,155 US7513744B2 (en) | 2006-07-18 | 2006-07-18 | Microcircuit cooling and tip blowing |
US11/491,404 US7699583B2 (en) | 2006-07-21 | 2006-07-21 | Serpentine microcircuit vortex turbulatons for blade cooling |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP10010854.7 Division-Into | 2010-09-27 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1882818A1 true EP1882818A1 (fr) | 2008-01-30 |
EP1882818B1 EP1882818B1 (fr) | 2013-06-05 |
Family
ID=38657199
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP07252837.5A Active EP1882818B1 (fr) | 2006-07-18 | 2007-07-18 | Générateurs de tourbillons dans microcircuits en serpentins pour refroidissement d'aube |
EP20100010854 Withdrawn EP2282009A1 (fr) | 2006-07-18 | 2007-07-18 | Générateurs de tourbillons dans microcircuits en serpentins pour refroidissement d'aube |
Family Applications After (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP20100010854 Withdrawn EP2282009A1 (fr) | 2006-07-18 | 2007-07-18 | Générateurs de tourbillons dans microcircuits en serpentins pour refroidissement d'aube |
Country Status (1)
Country | Link |
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EP (2) | EP1882818B1 (fr) |
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2473949A (en) * | 2009-09-24 | 2011-03-30 | Gen Electric | Heat transfer apparatus with turbulators |
US8408872B2 (en) | 2009-09-24 | 2013-04-02 | General Electric Company | Fastback turbulator structure and turbine nozzle incorporating same |
CN108910019A (zh) * | 2018-07-05 | 2018-11-30 | 中国空气动力研究与发展中心高速空气动力研究所 | 一种采用热双金属微锯齿结构的空气流动控制系统 |
US10233775B2 (en) | 2014-10-31 | 2019-03-19 | General Electric Company | Engine component for a gas turbine engine |
US10280785B2 (en) | 2014-10-31 | 2019-05-07 | General Electric Company | Shroud assembly for a turbine engine |
US10364684B2 (en) | 2014-05-29 | 2019-07-30 | General Electric Company | Fastback vorticor pin |
US10465530B2 (en) | 2013-12-20 | 2019-11-05 | United Technologies Corporation | Gas turbine engine component cooling cavity with vortex promoting features |
US10563514B2 (en) | 2014-05-29 | 2020-02-18 | General Electric Company | Fastback turbulator |
EP3346096B1 (fr) * | 2017-01-10 | 2020-03-04 | Doosan Heavy Industries & Construction Co., Ltd. | Aube fixe ou pale d'une turbine á gaz |
US11136891B2 (en) * | 2017-01-31 | 2021-10-05 | Siemens Energy Global GmbH & Co. KG | Wall comprising a film cooling hole |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3068580B1 (fr) | 2013-11-15 | 2020-09-02 | United Technologies Corporation | Procédé et système d'usinage fluidique |
KR102138327B1 (ko) | 2013-11-15 | 2020-07-27 | 한화에어로스페이스 주식회사 | 터빈 |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5361828A (en) * | 1993-02-17 | 1994-11-08 | General Electric Company | Scaled heat transfer surface with protruding ramp surface turbulators |
EP0845580A2 (fr) * | 1993-12-28 | 1998-06-03 | Kabushiki Kaisha Toshiba | Dispositif pour accroitre la transmission de chaleur |
US6071363A (en) * | 1992-02-18 | 2000-06-06 | Allison Engine Company, Inc. | Single-cast, high-temperature, thin wall structures and methods of making the same |
EP1445424A2 (fr) * | 2003-02-05 | 2004-08-11 | United Technologies Corporation | Refroidissement avec microcanaux pour extrémité d'aube de turbine |
EP1659264A2 (fr) * | 2004-11-23 | 2006-05-24 | United Technologies Corporation | Aube de turbine avec un conduit de refroidissement additionnel au bord d'attaque |
Family Cites Families (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5896663A (en) * | 1995-04-04 | 1999-04-27 | Aurafin Corporation | Process for making jewelry utilizing a soft photopolymer |
US7134475B2 (en) * | 2004-10-29 | 2006-11-14 | United Technologies Corporation | Investment casting cores and methods |
-
2007
- 2007-07-18 EP EP07252837.5A patent/EP1882818B1/fr active Active
- 2007-07-18 EP EP20100010854 patent/EP2282009A1/fr not_active Withdrawn
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6071363A (en) * | 1992-02-18 | 2000-06-06 | Allison Engine Company, Inc. | Single-cast, high-temperature, thin wall structures and methods of making the same |
US5361828A (en) * | 1993-02-17 | 1994-11-08 | General Electric Company | Scaled heat transfer surface with protruding ramp surface turbulators |
EP0845580A2 (fr) * | 1993-12-28 | 1998-06-03 | Kabushiki Kaisha Toshiba | Dispositif pour accroitre la transmission de chaleur |
EP1445424A2 (fr) * | 2003-02-05 | 2004-08-11 | United Technologies Corporation | Refroidissement avec microcanaux pour extrémité d'aube de turbine |
EP1659264A2 (fr) * | 2004-11-23 | 2006-05-24 | United Technologies Corporation | Aube de turbine avec un conduit de refroidissement additionnel au bord d'attaque |
Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2473949A (en) * | 2009-09-24 | 2011-03-30 | Gen Electric | Heat transfer apparatus with turbulators |
US8408872B2 (en) | 2009-09-24 | 2013-04-02 | General Electric Company | Fastback turbulator structure and turbine nozzle incorporating same |
GB2473949B (en) * | 2009-09-24 | 2016-01-20 | Gen Electric | Fastback turbulator structure and turbine nozzle incorporating same |
US10465530B2 (en) | 2013-12-20 | 2019-11-05 | United Technologies Corporation | Gas turbine engine component cooling cavity with vortex promoting features |
US10364684B2 (en) | 2014-05-29 | 2019-07-30 | General Electric Company | Fastback vorticor pin |
US10563514B2 (en) | 2014-05-29 | 2020-02-18 | General Electric Company | Fastback turbulator |
US10233775B2 (en) | 2014-10-31 | 2019-03-19 | General Electric Company | Engine component for a gas turbine engine |
US10280785B2 (en) | 2014-10-31 | 2019-05-07 | General Electric Company | Shroud assembly for a turbine engine |
EP3346096B1 (fr) * | 2017-01-10 | 2020-03-04 | Doosan Heavy Industries & Construction Co., Ltd. | Aube fixe ou pale d'une turbine á gaz |
US11136891B2 (en) * | 2017-01-31 | 2021-10-05 | Siemens Energy Global GmbH & Co. KG | Wall comprising a film cooling hole |
CN108910019A (zh) * | 2018-07-05 | 2018-11-30 | 中国空气动力研究与发展中心高速空气动力研究所 | 一种采用热双金属微锯齿结构的空气流动控制系统 |
CN108910019B (zh) * | 2018-07-05 | 2020-03-31 | 中国空气动力研究与发展中心高速空气动力研究所 | 一种采用热双金属微锯齿结构的空气流动控制系统 |
Also Published As
Publication number | Publication date |
---|---|
EP2282009A1 (fr) | 2011-02-09 |
EP1882818B1 (fr) | 2013-06-05 |
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