US2006099073A1PendingUtilityA1

Aspherical dimples for heat transfer surfaces and method

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Assignee: DJERIDANE TOUFIKPriority: Nov 5, 2004Filed: Nov 5, 2004Published: May 11, 2006
Est. expiryNov 5, 2024(expired)· nominal 20-yr term from priority
Inventors:Toufik DjeridaneTimothy BlaskovichSri SreekanthRicardo TrindadeMichael Clyde PappleOlivier BiborLarry LebelPhillip Ligrani
F05D 2260/202F05D 2260/2214F05D 2250/61F01D 5/186F05D 2260/2212F05D 2260/22141F28F 3/044F28F 13/12F05D 2250/28
29
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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.

Claims

exact text as granted — not AI-modified
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.

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