WO2006047854A1 - Aspherical dimples for heat transfer surfaces and method - Google Patents
Aspherical dimples for heat transfer surfaces and method Download PDFInfo
- Publication number
- WO2006047854A1 WO2006047854A1 PCT/CA2005/001625 CA2005001625W WO2006047854A1 WO 2006047854 A1 WO2006047854 A1 WO 2006047854A1 CA 2005001625 W CA2005001625 W CA 2005001625W WO 2006047854 A1 WO2006047854 A1 WO 2006047854A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- dimples
- dimple
- rim
- heat transfer
- turbine engine
- Prior art date
Links
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
- F01D5/186—Film cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
- F28F13/00—Arrangements for modifying heat-transfer, e.g. increasing, decreasing
- F28F13/06—Arrangements for modifying heat-transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media
- F28F13/12—Arrangements for modifying heat-transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media by creating turbulence, e.g. by stirring, by increasing the force of circulation
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
- F28F3/00—Plate-like or laminated elements; Assemblies of plate-like or laminated elements
- F28F3/02—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations
- F28F3/04—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being integral with the element
- F28F3/042—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being integral with the element in the form of local deformations of the element
- F28F3/044—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being integral with the element in the form of local deformations of the element the deformations being pontual, e.g. dimples
-
- 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
- F05D2250/28—Three-dimensional patterned
-
- 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
- F05D2250/60—Structure; Surface texture
- F05D2250/61—Structure; Surface texture corrugated
-
- 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
-
- 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
-
- 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 invention relates generally to shaped dimples for use in heat transfer surfaces such as, for example, those employed in cooling gas turbine engines.
- dimples are small depressions provided on a heat transfer surface to create or amplify localised turbulences in the boundary layer of a gas flowing over the surface. Many dimples are generally provided on a same surface. One purpose of this turbulence is to increase the heat transfer between the gas and the surface on which the dimples are provided. This is often used, for example, in internal airfoil cooling or combustor cooling in gas turbine engines. Dimples can also be used for other purposes, however the purpose affects dimple placement, arrangement, etc.
- Fig. 3 illustrates a typical heat transfer dimple as found in the prior art.
- This dimple is semi-spherical, namely that its bottom surface is shaped as a segment of a sphere. It comprises a bottom surface having a radius of curvature r.
- the ratio between the maximum depth ( ⁇ ) and the maximum diameter (D) is generally 0.2 or more.
- the present invention provides a gas turbine engine component comprising a turbine portion exposed, in use, to a hot fluid flow; at least one cooling passage disposed within the turbine portion, the passage having a surface; and a plurality of aspherically-shaped dimple provided on the surface.
- the present invention provides an airfoil for use in a gas turbine engine, the airfoil having at least one internal cooling passage therein adapted to direct a cooling fluid flow therethrough, the airfoil comprising a plurality of aspherical dimples disposed on at least one internal surface of the passage.
- the present invention provides a heat transfer dimple for use on a surface exposed, in use, to a flowing gas, the dimple having an aspherical shape.
- the present invention provides a shaped surface for use in a gas turbine engine to create turbulences in a gas when the gas flows thereon, the surface comprising a plurality of aspherical dimples.
- the present invention provides a method of promoting heat transfer, the method comprising: providing a plurality of aspherical dimples on a surface; and directing a gas over the surface, the gas having a temperature being different than that of the surface.
- the present invention provides a method of inducing turbulence in a gas flowing inside a gas turbine engine, the method comprising: providing a plurality of aspherical dimples on a surface; and directing the gas over the surface.
- Fig. 1 shows a generic gas turbine engine to illustrate an example of a general environment in which the invention can be used.
- Fig. 2 is a schematic top plan view of a generic heat transfer surface on which dimples are provided.
- Fig. 3 is a cross-sectional view of a spherical dimple, as found in the prior art.
- Figs. 4a, 4b and 4c are schematic views of an aspherical dimple in accordance with one preferred embodiment of the present invention.
- Figs. 5a, 5b and 5c are schematic views of an aspherical dimple in accordance with another preferred embodiment of the present invention.
- Figs. 6a, 6b and 6c are schematic views of an aspherical dimple in accordance with yet another preferred embodiment of the present invention. DETAILED DESCRIPTION
- Fig. 1 illustrates an example of a gas turbine engine 10 of a type preferably provided for use in subsonic flight, generally comprising in serial flow communication a fan 12 through which ambient air is propelled, a multistage compressor 14 for pressurizing the air, a combustor 16 in which the compressed air is mixed with fuel and ignited for generating an annular stream of hot combustion gases, and a turbine section 18 for extracting energy from the combustion gases.
- a gas turbine engine 10 of a type preferably provided for use in subsonic flight, generally comprising in serial flow communication a fan 12 through which ambient air is propelled, a multistage compressor 14 for pressurizing the air, a combustor 16 in which the compressed air is mixed with fuel and ignited for generating an annular stream of hot combustion gases, and a turbine section 18 for extracting energy from the combustion gases.
- This figure illustrates an example of the environment in which the present invention can be used.
- Fig. 2 schematically illustrates a generic surface 20 in which a plurality of dimples 30 are provided.
- Such surface 20 can be present in various components of the gas turbine engine 10, for instance in the internal cooling paths of airfoils or in some areas of the combustor 16.
- dimples 30 can be provided on surfaces 20 of about any shape and configuration.
- Dimples 30 are small and usually shallow depressions. They are usually made directly within the material of the surface 20 in which they are located. Traditionally, the dimples 30 were shaped as segments of sphere. Fig. 3 shows an' example of a spherical dimple 30'.
- the gas flowing on the surface 20 has a boundary layer whose flow will be disrupted by the presence of the dimples 30.
- turbulences appear in the gas flow but without causing significant pressure losses. These turbulences increase the swirling of the gas molecules above the surface 20, thereby increasing the heat transfer efficiency between the gas and the surface 20.
- aspherically-shaped dimples 30 can be used to improve the efficiency of the turbulences compared to spherically-shaped dimples 30' (Fig. 3).
- These non-spherical dimples 30 can have many possible embodiments, some of which are shown in Figs. 4a through 6c. Each of these preferred embodiments have some specificities that may attract the attention of the engineers in the design of their components.
- Figs. 4a, 4b and 4c schematically illustrate a cross section of an aspherical dimple 30 in accordance with one preferred embodiment.
- Fig. 4a illustrates a "disproportional" dimple in which the shape has been exaggerated for illustration proposes only. The real preferred aspect is shown in Fig. 4b.
- Fig. 4c shows an upper view of the dimple 30, as shown in Fig. 4b.
- the dimple 30 preferably comprises acircular rim 32.
- the bottom surface 34 of the dimple is preferably flat and inclined. The inclination preferably begins at the leading side 36 with reference to the gas flow, although any desired orientation may be used.
- the bottom surface 34 intersects a corresponding inclined wall 38 at the trailing side 40 of the dimple 30.
- the ratio of the maximum depth ( ⁇ ) versus the maximum diameter (D) of the dimple is less than 0.2, and more preferably being about 0.1.
- Figs. 5a, 4b and 4c schematically illustrate a cross section of an aspherical dimple 30 in accordance with another embodiment.
- Fig. 5a illustrates a "disproportional" dimple 30 for illustration purposes. The real preferred aspect is shown in Fig. 5b.
- Fig. 5c shows an upper view of the dimple 30, as shown in Fig. 5b.
- the dimple 30 preferably comprises a circular rim 32 and a central circular raised portion 42 with a flat upper surface 44 which is at the same level than the main surface 20.
- the raised portion 42 has a diameter D' that is preferably about a quarter of the diameter D of the dimple 30.
- the bottom surface 34 of the dimple 30 is substantially shaped as a segment of torus (or donut).
- the ratio of the maximum depth ( ⁇ ) versus the maximum diameter (D) of the dimple is less than 0.2, and more preferably being about 0.1.
- Figs. 6a, 4b and 4c schematically illustrate a cross section of an aspherical dimple 30 in accordance with another embodiment.
- Fig. 6a illustrates a "disproportional" dimple 30 for illustration purposes. The real preferred aspect is shown in Fig. 6b.
- Fig. 6c shows an upper view of the dimple 30, as shown in Fig. 6b.
- the dimple 30 is preferably shaped as a double wedge with a substantially flat bottom surface 34.
- the double wedge forms an arrow-like shape which is preferably pointed towards the upstream side of the gas flow, although any desired orientation may be used.
- the bottom surface 34 of the dimple 30 is substantially flat and inclined, starting from the leading side 36 with reference to the gas flow and up to the trailing side 40.
- the ratio of the maximum depth ( ⁇ 5) versus the maximum diameter (D) of an imaginary circle 50, in which the arrow is positioned is less than 0.2, and more preferably being about 0.1.
- This dimple itself otherwise has an a circular rim.
- the aspherical dimples 30 will allow engineers designing devices in which it is possible to enhance heat transfer or induce more effective turbulences when exposed to a gas flowing on a surface having several of these dimples 30.
- aspherical dimples need not be employed exclusively, not one type of aspherical dimples employed, but rather a plurality of types and sizes may be employed, and can be used in conjunction with spherical dimples 30', if desired.
- the present invention has been described with respect to its application to gas turbine engines, the skilled reader will appreciate that the invention has board application to many different types of heat transfer environments and applications. Still other modifications which fall within the scope of the present invention will be apparent to those skilled in the art, in light of a review of this disclosure, and such modifications are intended to fall within the appended claims.
Abstract
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2007539432A JP2008519197A (en) | 2004-11-05 | 2005-10-20 | Non-spherical dimples and methods for heat transfer surfaces |
EP05797099A EP1812769A1 (en) | 2004-11-05 | 2005-10-20 | Aspherical dimples for heat transfer surfaces and method |
CA002583126A CA2583126A1 (en) | 2004-11-05 | 2005-10-20 | Aspherical dimples for heat transfer surfaces and method |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/981,466 US20060099073A1 (en) | 2004-11-05 | 2004-11-05 | Aspherical dimples for heat transfer surfaces and method |
US10/981,466 | 2004-11-05 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2006047854A1 true WO2006047854A1 (en) | 2006-05-11 |
Family
ID=36316505
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/CA2005/001625 WO2006047854A1 (en) | 2004-11-05 | 2005-10-20 | Aspherical dimples for heat transfer surfaces and method |
Country Status (5)
Country | Link |
---|---|
US (1) | US20060099073A1 (en) |
EP (1) | EP1812769A1 (en) |
JP (1) | JP2008519197A (en) |
CA (1) | CA2583126A1 (en) |
WO (1) | WO2006047854A1 (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2569540C1 (en) * | 2014-05-21 | 2015-11-27 | Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Казанский национальный исследовательский технический университет им. А.Н. Туполева-КАИ" (КНИТУ-КАИ) | Heat exchange surface (versions) |
US9771806B2 (en) | 2011-11-30 | 2017-09-26 | Ihi Corporation | Turbine blade |
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EP2143883A1 (en) * | 2008-07-10 | 2010-01-13 | Siemens Aktiengesellschaft | Turbine blade and corresponding casting core |
US9376960B2 (en) | 2010-07-23 | 2016-06-28 | University Of Central Florida Research Foundation, Inc. | Heat transfer augmented fluid flow surfaces |
EP2518429A1 (en) * | 2011-04-28 | 2012-10-31 | Siemens Aktiengesellschaft | An enhanced cooling surface |
EP2599957A1 (en) * | 2011-11-21 | 2013-06-05 | Siemens Aktiengesellschaft | Cooling fin system for a cooling channel and turbine blade |
US9255491B2 (en) | 2012-02-17 | 2016-02-09 | United Technologies Corporation | Surface area augmentation of hot-section turbomachine component |
EP2679793A1 (en) * | 2012-06-28 | 2014-01-01 | Alstom Technology Ltd | Flow channel for a gaseous medium and corresponding exhaust-gas liner of a gas turbine |
US9995148B2 (en) | 2012-10-04 | 2018-06-12 | General Electric Company | Method and apparatus for cooling gas turbine and rotor blades |
US9850762B2 (en) | 2013-03-13 | 2017-12-26 | General Electric Company | Dust mitigation for turbine blade tip turns |
CA2949539A1 (en) | 2014-05-29 | 2016-02-18 | General Electric Company | Engine components with impingement cooling features |
US10422235B2 (en) | 2014-05-29 | 2019-09-24 | General Electric Company | Angled impingement inserts with cooling features |
CA2950011C (en) | 2014-05-29 | 2020-01-28 | General Electric Company | Fastback turbulator |
US9957816B2 (en) | 2014-05-29 | 2018-05-01 | General Electric Company | Angled impingement insert |
US10364684B2 (en) | 2014-05-29 | 2019-07-30 | General Electric Company | Fastback vorticor pin |
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 |
FR3028883B1 (en) | 2014-11-25 | 2019-11-22 | Safran Aircraft Engines | TURBOMACHINE ROTOR SHAFT HAVING AN IMPROVED THERMAL EXCHANGE SURFACE |
US10808540B2 (en) * | 2018-03-22 | 2020-10-20 | Raytheon Technologies Corporation | Case for gas turbine engine |
CN109083689B (en) * | 2018-07-26 | 2021-01-12 | 中国科学院工程热物理研究所 | Recess, cooling structure, cooling assembly and method of forming recess |
CN110195615A (en) * | 2019-05-20 | 2019-09-03 | 沈阳航空航天大学 | A kind of impact overflow double-wall structure of target surface trough of belt |
FR3104691B1 (en) * | 2019-12-12 | 2022-08-12 | Safran Aircraft Engines | Heat exchanger comprising a disturbing wall with hollow turbulence generators |
DE102020202978A1 (en) | 2020-03-09 | 2021-09-09 | MTU Aero Engines AG | COMPONENT FOR A FLOW MACHINE |
CN112780354B (en) | 2021-02-03 | 2021-12-24 | 上海交通大学 | Tail edge crack-splitting cooling structure and method suitable for turbine blade and turbine blade |
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JP3909124B2 (en) * | 1997-07-31 | 2007-04-25 | Sriスポーツ株式会社 | Golf ball |
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US6142734A (en) * | 1999-04-06 | 2000-11-07 | General Electric Company | Internally grooved turbine wall |
US6390740B1 (en) * | 2000-10-03 | 2002-05-21 | Spalding Sports Worldwide, Inc. | Non-circular dimples formed via an orbital pantograph cutter |
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2004
- 2004-11-05 US US10/981,466 patent/US20060099073A1/en not_active Abandoned
-
2005
- 2005-10-20 JP JP2007539432A patent/JP2008519197A/en active Pending
- 2005-10-20 EP EP05797099A patent/EP1812769A1/en not_active Withdrawn
- 2005-10-20 CA CA002583126A patent/CA2583126A1/en not_active Abandoned
- 2005-10-20 WO PCT/CA2005/001625 patent/WO2006047854A1/en active Application Filing
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US3578264A (en) * | 1968-07-09 | 1971-05-11 | Battelle Development Corp | Boundary layer control of flow separation and heat exchange |
US3578264B1 (en) * | 1968-07-09 | 1991-11-19 | Univ Michigan | |
US5577555A (en) * | 1993-02-24 | 1996-11-26 | Hitachi, Ltd. | Heat exchanger |
US6183197B1 (en) * | 1999-02-22 | 2001-02-06 | General Electric Company | Airfoil with reduced heat load |
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Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9771806B2 (en) | 2011-11-30 | 2017-09-26 | Ihi Corporation | Turbine blade |
RU2569540C1 (en) * | 2014-05-21 | 2015-11-27 | Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Казанский национальный исследовательский технический университет им. А.Н. Туполева-КАИ" (КНИТУ-КАИ) | Heat exchange surface (versions) |
Also Published As
Publication number | Publication date |
---|---|
CA2583126A1 (en) | 2006-05-11 |
JP2008519197A (en) | 2008-06-05 |
US20060099073A1 (en) | 2006-05-11 |
EP1812769A1 (en) | 2007-08-01 |
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