US20060099073A1 - Aspherical dimples for heat transfer surfaces and method - Google Patents
Aspherical dimples for heat transfer surfaces and method Download PDFInfo
- Publication number
- US20060099073A1 US20060099073A1 US10/981,466 US98146604A US2006099073A1 US 20060099073 A1 US20060099073 A1 US 20060099073A1 US 98146604 A US98146604 A US 98146604A US 2006099073 A1 US2006099073 A1 US 2006099073A1
- Authority
- US
- United States
- Prior art keywords
- dimples
- dimple
- rim
- heat transfer
- turbine engine
- 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.)
- Abandoned
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
- F01D5/186—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. 4 a , 4 b and 4 c are schematic views of an aspherical dimple in accordance with one preferred embodiment of the present invention.
- FIGS. 5 a , 5 b and 5 c are schematic views of an aspherical dimple in accordance with another preferred embodiment of the present invention.
- FIGS. 6 a , 6 b and 6 c are schematic views of an aspherical dimple in accordance with yet another preferred embodiment of the present invention.
- 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. 4 a through 6 c. Each of these preferred embodiments have some specificities that may attract the attention of the engineers in the design of their components.
- FIGS. 4 a , 4 b and 4 c schematically illustrate a cross section of an aspherical dimple 30 in accordance with one preferred embodiment.
- FIG. 4 a illustrates a “disproportional” dimple in which the shape has been exaggerated for illustration proposes only. The real preferred aspect is shown in FIG. 4 b.
- FIG. 4 c shows an upper view of the dimple 30 , as shown in FIG. 4 b.
- the dimple 30 preferably comprises a circular 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. 5 a , 4 b and 4 c schematically illustrate a cross section of an aspherical dimple 30 in accordance with another embodiment.
- FIG. 5 a illustrates a “disproportional” dimple 30 for illustration purposes. The real preferred aspect is shown in FIG. 5 b.
- FIG. 5 c shows an upper view of the dimple 30 , as shown in FIG. 5 b .
- 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. 6 a , 4 b and 4 c schematically illustrate a cross section of an aspherical dimple 30 in accordance with another embodiment.
- FIG. 6 a illustrates a “disproportional” dimple 30 for illustration purposes. The real preferred aspect is shown in FIG. 6 b.
- FIG. 6 c shows an upper view of the dimple 30 , as shown in FIG. 6 b .
- 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 ( ⁇ ) 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 acircular 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
A dimple for use on a heat transfer surface exposed to a flowing gas, for use for example in a gas turbine engine, the dimple having an aspherical shape.
Description
- The invention relates generally to shaped dimples for use in heat transfer surfaces such as, for example, those employed in cooling gas turbine engines.
- In heat transfer technologies, 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 (δ) and the maximum diameter (D) is generally 0.2 or more. - As there is a constant need for more efficient and reliable gas turbine engines, there is consequently a constant need for new features and methods that allow reaching these goals, such as improvements in the field of heat transfer.
- In one aspect, 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.
- In another aspect, 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.
- In another aspect, 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.
- In another aspect, 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.
- In another aspect, 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.
- In another aspect, 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.
- Further details of these and other aspects of the present invention will be apparent from the detailed description and figures included below.
- Reference is now made to the accompanying figures depicting aspects of the present invention, in which:
-
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. 4 a, 4 b and 4 c are schematic views of an aspherical dimple in accordance with one preferred embodiment of the present invention. -
FIGS. 5 a, 5 b and 5 c are schematic views of an aspherical dimple in accordance with another preferred embodiment of the present invention. -
FIGS. 6 a, 6 b and 6 c are schematic views of an aspherical dimple in accordance with yet another preferred embodiment of the present invention. -
FIG. 1 illustrates an example of agas turbine engine 10 of a type preferably provided for use in subsonic flight, generally comprising in serial flow communication afan 12 through which ambient air is propelled, amultistage compressor 14 for pressurizing the air, acombustor 16 in which the compressed air is mixed with fuel and ignited for generating an annular stream of hot combustion gases, and aturbine 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 ageneric surface 20 in which a plurality ofdimples 30 are provided.Such surface 20 can be present in various components of thegas turbine engine 10, for instance in the internal cooling paths of airfoils or in some areas of thecombustor 16. Although the illustratedsurface 20 appears to be flat,dimples 30 can be provided onsurfaces 20 of about any shape and configuration. -
Dimples 30 are small and usually shallow depressions. They are usually made directly within the material of thesurface 20 in which they are located. Traditionally, thedimples 30 were shaped as segments of sphere.FIG. 3 shows an example of aspherical dimple 30′. - During operation of the
gas turbine engine 10, the gas flowing on thesurface 20 has a boundary layer whose flow will be disrupted by the presence of thedimples 30. As a result, turbulences appear in the gas flow but without causing significant pressure losses. These turbulences increase the swirling of the gas molecules above thesurface 20, thereby increasing the heat transfer efficiency between the gas and thesurface 20. - It was found by the inventors that aspherically-
shaped dimples 30 can be used to improve the efficiency of the turbulences compared to spherically-shaped dimples 30′ (FIG. 3 ). Thesenon-spherical dimples 30 can have many possible embodiments, some of which are shown inFIGS. 4 a through 6 c. Each of these preferred embodiments have some specificities that may attract the attention of the engineers in the design of their components. -
FIGS. 4 a, 4 b and 4 c schematically illustrate a cross section of anaspherical dimple 30 in accordance with one preferred embodiment.FIG. 4 a illustrates a “disproportional” dimple in which the shape has been exaggerated for illustration proposes only. The real preferred aspect is shown inFIG. 4 b.FIG. 4 c shows an upper view of the dimple 30, as shown inFIG. 4 b. The dimple 30 preferably comprises acircular rim 32. Thebottom surface 34 of the dimple is preferably flat and inclined. The inclination preferably begins at the leadingside 36 with reference to the gas flow, although any desired orientation may be used. Thebottom surface 34 intersects a correspondinginclined wall 38 at thetrailing side 40 of the dimple 30. Preferably, the ratio of the maximum depth (δ) versus the maximum diameter (D) of the dimple is less than 0.2, and more preferably being about 0.1. -
FIGS. 5 a, 4 b and 4 c schematically illustrate a cross section of anaspherical dimple 30 in accordance with another embodiment.FIG. 5 a illustrates a “disproportional” dimple 30 for illustration purposes. The real preferred aspect is shown inFIG. 5 b.FIG. 5 c shows an upper view of the dimple 30, as shown inFIG. 5 b. The dimple 30 preferably comprises acircular rim 32 and a central circular raisedportion 42 with a flatupper surface 44 which is at the same level than themain surface 20. The raisedportion 42 has a diameter D′ that is preferably about a quarter of the diameter D of the dimple 30. Thebottom surface 34 of thedimple 30 is substantially shaped as a segment of torus (or donut). Preferably, the ratio of the maximum depth (δ) versus the maximum diameter (D) of the dimple is less than 0.2, and more preferably being about 0.1. -
FIGS. 6 a, 4 b and 4 c schematically illustrate a cross section of anaspherical dimple 30 in accordance with another embodiment.FIG. 6 a illustrates a “disproportional” dimple 30 for illustration purposes. The real preferred aspect is shown inFIG. 6 b.FIG. 6 c shows an upper view of thedimple 30, as shown inFIG. 6 b. Thedimple 30 is preferably shaped as a double wedge with a substantiallyflat 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. Thebottom surface 34 of thedimple 30 is substantially flat and inclined, starting from the leadingside 36 with reference to the gas flow and up to the trailingside 40. Preferably, the ratio of the maximum depth (δ) versus the maximum diameter (D) of animaginary 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 acircular rim. - As can be appreciated, 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 thesedimples 30. - The above description is meant to be exemplary only, and one skilled in the art will recognize that changes may be made to the embodiments described without department from the scope of the invention disclosed. For example, other aspherical shapes can be used, and the ones disclosed herein are exemplary only. The orientations of the exemplary dimples relative to the direction of flow thereover may be any desired, and need not be as described. The ratio between the maximum depth and the maximum diameter of the dimples can be equal or more than 0.2, although a lesser value is believed to be more advantageous where pressure losses caused by the dimple are important, as they are in the filed of gas turbine cooling. Also, 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. Although 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.
Claims (35)
1. 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.
2. The gas turbine engine component of claim 1 , wherein at least some of the dimples have a generally circular rim, said rim being an interface between the dimples and the surface.
3. The gas turbine engine component of claim 1 , wherein at least some of the dimples have a generally acircular rim, said rim being an interface between the dimples and the surface.
4. The gas turbine engine component of claim 1 , wherein at least some of the dimples have a ratio between a maximum depth and a maximum diameter of less than 0.2.
5. The gas turbine engine component of claim 4 , wherein the ratio is substantially equal to 0.1.
6. The gas turbine engine component of claim 1 , wherein at least some of the dimples have a substantially flat bottom surface.
7. The gas turbine engine component of claim 1 , wherein at least some of the dimples have a bottom surface substantially shaped as a segment of torus.
8. The gas turbine engine component of claim 1 , wherein at least some of the dimples have a bottom surface shaped as a double wedge with a substantially flat bottom surface.
9. 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.
10. The airfoil of claim 9 , wherein at least some of the dimples have a generally circular rim, said rim being an interface between the dimples and the surface.
11. The airfoil of claim 9 , wherein at least some of the dimples have a generally acircular rim, said rim being an interface between the dimples and the surface.
12. The airfoil of claim 9 , wherein at least some of the dimples have a ratio between a maximum depth and a maximum diameter of less than 0.2.
13. The airfoil of claim 12 , wherein the ratio is substantially equal to 0.1.
14. The airfoil of claim 9 , wherein at least some of the dimples have a substantially flat bottom surface.
15. The airfoil of claim 9 , wherein at least some of the dimples have a bottom surface substantially shaped as a segment of torus.
16. The airfoil of claim 9 , wherein at least some of the dimples have a bottom surface shaped as a double wedge with a substantially flat bottom surface.
17. A heat transfer dimple for use on a surface exposed, in use, to a flowing gas, the dimple having an aspherical shape.
18. The heat transfer dimple of claim 17 , wherein the dimple has a generally circular rim, said rim being an interface between the dimple and the surface.
19. The heat transfer dimple of claim 17 , wherein the dimple has a generally acircular rim, said rim being an interface between the dimple and the surface.
20. The heat transfer dimple of claim 17 , wherein the dimple has a ratio between a maximum depth and a maximum diameter of less than 0.2.
21. The heat transfer dimple of claim 20 , wherein the ratio is substantially equal to 0.1.
22. The heat transfer dimple of claim 17 , wherein the dimple has a substantially flat bottom surface.
23. The heat transfer dimple of claim 17 , wherein the dimple has a bottom surface substantially shaped as a segment of torus.
24. The heat transfer dimple of claim 17 , wherein the dimple has a bottom surface shaped as a double wedge with a substantially flat bottom surface.
25. 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.
26. The surface of claim 25 , wherein at least some of the dimples have a generally circular rim, said rim being an interface between the dimples and the surface.
27. The surface of claim 25 , wherein at least some of the dimples have a generally acircular rim, said rim being an interface between the dimples and the surface.
28. The surface of claim 25 , wherein at least some of the dimples have a ratio between a maximum depth and a maximum diameter of less than 0.2.
29. The surface of claim 28 , wherein the ratio is substantially equal to 0.1.
30. The surface of claim 25 , wherein at least some of the dimples have a substantially flat bottom surface.
31. The surface of claim 25 , wherein at least some of the dimples have a bottom surface substantially shaped as a segment of torus.
32. The surface of claim 25 , wherein at least some of the dimples have a bottom surface shaped as a double wedge with a substantially flat bottom surface.
33. 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.
34. The method of claim 33 , wherein the dimples induce increased turbulence in the flow and thereby promote heat transfer.
35. 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.
Priority Applications (5)
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 |
JP2007539432A JP2008519197A (en) | 2004-11-05 | 2005-10-20 | Non-spherical dimples and methods for heat transfer surfaces |
PCT/CA2005/001625 WO2006047854A1 (en) | 2004-11-05 | 2005-10-20 | Aspherical dimples for heat transfer surfaces and method |
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 (1)
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 |
Publications (1)
Publication Number | Publication Date |
---|---|
US20060099073A1 true US20060099073A1 (en) | 2006-05-11 |
Family
ID=36316505
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US10/981,466 Abandoned US20060099073A1 (en) | 2004-11-05 | 2004-11-05 | 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 (22)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2143883A1 (en) * | 2008-07-10 | 2010-01-13 | Siemens Aktiengesellschaft | Turbine blade and corresponding casting core |
WO2012146480A1 (en) * | 2011-04-28 | 2012-11-01 | Siemens Aktiengesellschaft | An enhanced cooling surface |
WO2013076110A1 (en) * | 2011-11-21 | 2013-05-30 | Siemens Aktiengesellschaft | Cooling rib system for a cooling passage of a turbine blade |
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 |
US9255491B2 (en) | 2012-02-17 | 2016-02-09 | United Technologies Corporation | Surface area augmentation of hot-section turbomachine component |
FR3028883A1 (en) * | 2014-11-25 | 2016-05-27 | Snecma | TURBOMACHINE ROTOR SHAFT HAVING AN IMPROVED THERMAL EXCHANGE SURFACE |
US9376960B2 (en) | 2010-07-23 | 2016-06-28 | University Of Central Florida Research Foundation, Inc. | Heat transfer augmented fluid flow surfaces |
US9850762B2 (en) | 2013-03-13 | 2017-12-26 | General Electric Company | Dust mitigation for turbine blade tip turns |
US9957816B2 (en) | 2014-05-29 | 2018-05-01 | General Electric Company | Angled impingement insert |
US9995148B2 (en) | 2012-10-04 | 2018-06-12 | General Electric Company | Method and apparatus for cooling gas turbine and rotor blades |
CN109083689A (en) * | 2018-07-26 | 2018-12-25 | 中国科学院工程热物理研究所 | Recess portion, cooling structure, cooling component and the method for forming recess portion |
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 |
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 |
US10422235B2 (en) | 2014-05-29 | 2019-09-24 | General Electric Company | Angled impingement inserts with cooling features |
US20190292915A1 (en) * | 2018-03-22 | 2019-09-26 | United Technologies Corporation | Case for gas turbine engine |
US10563514B2 (en) | 2014-05-29 | 2020-02-18 | General Electric Company | Fastback turbulator |
US10690055B2 (en) | 2014-05-29 | 2020-06-23 | General Electric Company | Engine components with impingement cooling features |
CN112780354A (en) * | 2021-02-03 | 2021-05-11 | 上海交通大学 | Tail edge crack-splitting cooling structure and method suitable for turbine blade and turbine blade |
DE102020202978A1 (en) | 2020-03-09 | 2021-09-09 | MTU Aero Engines AG | COMPONENT FOR A FLOW MACHINE |
US20220412675A1 (en) * | 2019-12-12 | 2022-12-29 | Safran Aircraft Engines | Heat exchanger comprising a baffle wall with hollow turbulence generators |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP6025110B2 (en) * | 2011-11-30 | 2016-11-16 | 株式会社Ihi | 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) |
Citations (25)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1656408A (en) * | 1927-10-20 | 1928-01-17 | Leonard A Young | Golf ball |
US1666699A (en) * | 1927-12-16 | 1928-04-17 | L A Young Company | Golf ball |
US1716435A (en) * | 1928-05-29 | 1929-06-11 | Revere Rubber Co | Golf ball |
US3301527A (en) * | 1965-05-03 | 1967-01-31 | Gen Electric | Turbine diaphragm structure |
US3578264A (en) * | 1968-07-09 | 1971-05-11 | Battelle Development Corp | Boundary layer control of flow separation and heat exchange |
US3664928A (en) * | 1969-12-15 | 1972-05-23 | Aerojet General Co | Dimpled heat transfer walls for distillation apparatus |
US3684007A (en) * | 1970-12-29 | 1972-08-15 | Union Carbide Corp | Composite structure for boiling liquids and its formation |
US4420039A (en) * | 1980-02-07 | 1983-12-13 | Dubrovsky Evgeny V | Corrugated-surface heat exchange element |
US5005838A (en) * | 1989-05-09 | 1991-04-09 | Sumitomo Rubber Industries, Ltd. | Golf ball |
US5353865A (en) * | 1992-03-30 | 1994-10-11 | General Electric Company | Enhanced impingement cooled components |
US5468125A (en) * | 1994-12-20 | 1995-11-21 | Alliedsignal Inc. | Turbine blade with improved heat transfer surface |
US5577555A (en) * | 1993-02-24 | 1996-11-26 | Hitachi, Ltd. | Heat exchanger |
US5738493A (en) * | 1997-01-03 | 1998-04-14 | General Electric Company | Turbulator configuration for cooling passages of an airfoil in a gas turbine engine |
US5975850A (en) * | 1996-12-23 | 1999-11-02 | General Electric Company | Turbulated cooling passages for turbine blades |
US6006823A (en) * | 1992-03-31 | 1999-12-28 | Kiknadze; Gennady Iraklievich | Streamlined surface |
US6059671A (en) * | 1997-07-31 | 2000-05-09 | Sumitomo Rubber Industries, Ltd. | Golf ball |
US6098397A (en) * | 1998-06-08 | 2000-08-08 | Caterpillar Inc. | Combustor for a low-emissions gas turbine engine |
US6119987A (en) * | 1995-07-19 | 2000-09-19 | Nikolaus Vida | Method and apparatus for controlling the boundary or wall layer of a continuous medium |
US6142734A (en) * | 1999-04-06 | 2000-11-07 | General Electric Company | Internally grooved turbine wall |
US6183197B1 (en) * | 1999-02-22 | 2001-02-06 | General Electric Company | Airfoil with reduced heat load |
US6237344B1 (en) * | 1998-07-20 | 2001-05-29 | General Electric Company | Dimpled impingement baffle |
US6390740B1 (en) * | 2000-10-03 | 2002-05-21 | Spalding Sports Worldwide, Inc. | Non-circular dimples formed via an orbital pantograph cutter |
US20030068222A1 (en) * | 2001-10-09 | 2003-04-10 | Cunha Frank J. | Turbine airfoil with enhanced heat transfer |
US20030086785A1 (en) * | 2001-11-08 | 2003-05-08 | Genral Electric Company | Cooling passages and methods of fabrication |
US20040107718A1 (en) * | 2002-12-06 | 2004-06-10 | Michael Bowman | Method, system and apparatus for cooling high power density devices |
Family Cites Families (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1604122B1 (en) * | 2003-03-19 | 2008-11-05 | Vida, Nikolaus, Dr. | Three dimensional surface structure for reduced friction resistance and improved heat exchange |
-
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
Patent Citations (26)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1656408A (en) * | 1927-10-20 | 1928-01-17 | Leonard A Young | Golf ball |
US1666699A (en) * | 1927-12-16 | 1928-04-17 | L A Young Company | Golf ball |
US1716435A (en) * | 1928-05-29 | 1929-06-11 | Revere Rubber Co | Golf ball |
US3301527A (en) * | 1965-05-03 | 1967-01-31 | Gen Electric | Turbine diaphragm structure |
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 | |
US3664928A (en) * | 1969-12-15 | 1972-05-23 | Aerojet General Co | Dimpled heat transfer walls for distillation apparatus |
US3684007A (en) * | 1970-12-29 | 1972-08-15 | Union Carbide Corp | Composite structure for boiling liquids and its formation |
US4420039A (en) * | 1980-02-07 | 1983-12-13 | Dubrovsky Evgeny V | Corrugated-surface heat exchange element |
US5005838A (en) * | 1989-05-09 | 1991-04-09 | Sumitomo Rubber Industries, Ltd. | Golf ball |
US5353865A (en) * | 1992-03-30 | 1994-10-11 | General Electric Company | Enhanced impingement cooled components |
US6006823A (en) * | 1992-03-31 | 1999-12-28 | Kiknadze; Gennady Iraklievich | Streamlined surface |
US5577555A (en) * | 1993-02-24 | 1996-11-26 | Hitachi, Ltd. | Heat exchanger |
US5468125A (en) * | 1994-12-20 | 1995-11-21 | Alliedsignal Inc. | Turbine blade with improved heat transfer surface |
US6119987A (en) * | 1995-07-19 | 2000-09-19 | Nikolaus Vida | Method and apparatus for controlling the boundary or wall layer of a continuous medium |
US5975850A (en) * | 1996-12-23 | 1999-11-02 | General Electric Company | Turbulated cooling passages for turbine blades |
US5738493A (en) * | 1997-01-03 | 1998-04-14 | General Electric Company | Turbulator configuration for cooling passages of an airfoil in a gas turbine engine |
US6059671A (en) * | 1997-07-31 | 2000-05-09 | Sumitomo Rubber Industries, Ltd. | Golf ball |
US6098397A (en) * | 1998-06-08 | 2000-08-08 | Caterpillar Inc. | Combustor for a low-emissions gas turbine engine |
US6237344B1 (en) * | 1998-07-20 | 2001-05-29 | General Electric Company | Dimpled impingement baffle |
US6183197B1 (en) * | 1999-02-22 | 2001-02-06 | General Electric Company | Airfoil with reduced heat load |
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 |
US20030068222A1 (en) * | 2001-10-09 | 2003-04-10 | Cunha Frank J. | Turbine airfoil with enhanced heat transfer |
US20030086785A1 (en) * | 2001-11-08 | 2003-05-08 | Genral Electric Company | Cooling passages and methods of fabrication |
US20040107718A1 (en) * | 2002-12-06 | 2004-06-10 | Michael Bowman | Method, system and apparatus for cooling high power density devices |
Cited By (28)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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 |
WO2012146480A1 (en) * | 2011-04-28 | 2012-11-01 | Siemens Aktiengesellschaft | An enhanced cooling surface |
WO2013076110A1 (en) * | 2011-11-21 | 2013-05-30 | Siemens Aktiengesellschaft | Cooling rib system for a cooling passage of a turbine blade |
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 |
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 |
US10422235B2 (en) | 2014-05-29 | 2019-09-24 | General Electric Company | Angled impingement inserts with cooling features |
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 |
GB2534016B (en) * | 2014-11-25 | 2020-12-02 | Snecma | Turbine engine rotor shaft comprising an improved heat exchange surface |
US10287911B2 (en) | 2014-11-25 | 2019-05-14 | Safran Aircraft Engines | Turbine engine rotor shaft comprising an improved heat exchange surface |
GB2534016A (en) * | 2014-11-25 | 2016-07-13 | Snecma | Turbine engine rotor shaft comprising an improved heat exchange surface |
FR3028883A1 (en) * | 2014-11-25 | 2016-05-27 | Snecma | 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 |
US20190292915A1 (en) * | 2018-03-22 | 2019-09-26 | United Technologies Corporation | Case for gas turbine engine |
CN109083689A (en) * | 2018-07-26 | 2018-12-25 | 中国科学院工程热物理研究所 | Recess portion, cooling structure, cooling component and the method for forming recess portion |
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 |
US20220412675A1 (en) * | 2019-12-12 | 2022-12-29 | Safran Aircraft Engines | Heat exchanger comprising a baffle wall with hollow turbulence generators |
DE102020202978A1 (en) | 2020-03-09 | 2021-09-09 | MTU Aero Engines AG | COMPONENT FOR A FLOW MACHINE |
CN112780354A (en) * | 2021-02-03 | 2021-05-11 | 上海交通大学 | Tail edge crack-splitting cooling structure and method suitable for turbine blade and turbine blade |
US11401820B1 (en) | 2021-02-03 | 2022-08-02 | Shanghai Jiao Tong University | Cooling structure and method of trailing-edge cutback of turbine blade, and turbine blade |
Also Published As
Publication number | Publication date |
---|---|
WO2006047854A1 (en) | 2006-05-11 |
CA2583126A1 (en) | 2006-05-11 |
JP2008519197A (en) | 2008-06-05 |
EP1812769A1 (en) | 2007-08-01 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
CA2583126A1 (en) | Aspherical dimples for heat transfer surfaces and method | |
US20220170383A1 (en) | Engine component assembly | |
KR101410570B1 (en) | Turbine case impingement cooling for heavy duty gas turbines | |
US9638057B2 (en) | Augmented cooling system | |
CN104204413B (en) | Turbine airfoil trailing edge cooling slit | |
JP6356410B2 (en) | Fillet for use with turbine rotor blade tip shroud | |
US6932572B2 (en) | Film cooled article with improved temperature tolerance | |
US8201412B2 (en) | Apparatus and method for cooling a combustor | |
US8168912B1 (en) | Electrode for shaped film cooling hole | |
US20170191417A1 (en) | Engine component assembly | |
US6629817B2 (en) | System and method for airfoil film cooling | |
JP2016128687A (en) | Engine component | |
US20130039777A1 (en) | Airfoil including trench with contoured surface | |
US7156619B2 (en) | Internally cooled gas turbine airfoil and method | |
JP6824623B2 (en) | Rotor blade with flared tip | |
US10533749B2 (en) | Effusion cooling holes | |
EP2861909A2 (en) | Gas turbine engine wall | |
US6997675B2 (en) | Turbulated hole configurations for turbine blades | |
US9810071B2 (en) | Internally cooled airfoil | |
CA2910691A1 (en) | Airfoil for a turbine engine | |
EP3181821B1 (en) | Turbulators for improved cooling of gas turbine engine components | |
CN109348723A (en) | The component of cover plate with the impinging cooling vallecular cavity and diffusion bond formed by salient rib to salient rib | |
US20160177739A1 (en) | Turbine blade having heat sinks that have the shape of an aerofoil profile | |
US10830095B2 (en) | Impingement cooling features for gas turbines | |
US10280785B2 (en) | Shroud assembly for a turbine engine |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: PRATT & WHITNEY CANADA CORP., CANADA Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:DJERIDANE, TOUFIK;BLASKOVICH, TIMOTHY;SREEKANTH, SRI;AND OTHERS;REEL/FRAME:016990/0639;SIGNING DATES FROM 20041203 TO 20050127 |
|
STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |