System and method for adaptive impingement cooling

Abstract

An adaptive cooling structure comprises a mounting support, a liner, and a spacer. The mounting support has a coolant aperture for directing cooling air through the support. The liner has a first surface facing away from the mounting support and a second surface facing towards the support. The liner is coupled to the mounting support, and the spacer is positioned between the support and the liner. The positioning of the spacer creates a chamber between the mounting support and the liner, thus allowing the cooling air to impinge on the second surface of the liner. The liner wall is configured to deflect away from the mounting support to expand the chamber, thus allowing the cooling air to further impinge on the second surface of the liner.

1 . A structure for adaptive cooling comprising:
 a mounting support having a coolant aperture for directing cooling air through the mounting support;   a liner coupled to the mounting support, including a wall having a first surface facing away from the mounting support and a second surface facing toward the mounting support;   a spacer positioned between the mounting support and the liner, the spacer creating a chamber between the mounting support and the liner, thus allowing the cooling air to impinge on the second surface of the liner; and   wherein the liner wall is configured to deflect away when exposed to hot air from the mounting support to expand the chamber, thus allowing the cooling air to further impinge on the second surface of the liner.   
     
     
         2 . The structure of  claim 1 , wherein the spacer positions the liner a distance away from the mounting support to provide impingement cooling at a first rate, and wherein the liner is configured to deflect an amount to increase the distance such that impingement cooling is provided at a second, greater rate. 
     
     
         3 . The structure of  claim 1 , wherein the liner permits the cooling air to pass through and exit the first surface, forming a film. 
     
     
         4 . The structure of  claim 1 , wherein the coolant aperture has a diameter D, the chamber has a distance L between the liner and the support that is less than three times the value of D, and the liner wall deflects away from the mounting support when exposed to hot air, increasing L to approximately three times the value of D. 
     
     
         5 . The structure of  claim 1 , wherein a mounting post with a threaded stud extends from the second surface of the liner wall and through the support, the mounting post is surrounded by a washer acting as the spacer between the support and the liner, and a nut secures the mounting post to the support. 
     
     
         6 . The structure of  claim 1 , wherein the first surface is a hot surface with a hot spot location, and the hot spot location causes the liner wall to deflect away from the mounting support. 
     
     
         7 . The structure of  claim 1 , wherein the liner is an impingement film cooled panel acting as a heat shield in a gas turbine combustor. 
     
     
         8 . The structure of  claim 1 , wherein the liner is an impingement film cooled liner in a gas turbine augmenter. 
     
     
         9 . A method of adaptively cooling a liner coupled to a support with a spacer positioned between the liner and the support, the method comprising:
 introducing cooling air into a coolant aperture in the support;   directing the cooling air into a chamber between the support and the liner and impinging the cooling air against the liner at a first rate;   deflecting the liner away from the mounting support, expanding the chamber; and   directing the cooling air into the chamber and further impinging the cooling air against the liner at a second rate.   
     
     
         10 . The method of  claim 9 , wherein the spacer positions the liner a distance away from the mounting support to provide impingement cooling at the first rate, and wherein the liner is configured to deflect an amount to increase the distance such that impingement cooling is provided at the second rate. 
     
     
         11 . The method of  claim 10 , wherein the second rate is greater than the first rate. 
     
     
         12 . The method of  claim 9 , wherein the coolant aperture has a diameter D, the chamber has a distance L between the liner and support that is less than three times the value of D, and the deflecting step causes the liner to deflect away from the mounting support, increasing L to between approximately one to four times the value of D. 
     
     
         13 . The method of  claim 10 , wherein the deflecting step causes the liner to deflect away from the mounting support, increasing L to between approximately two to four times the value of D. 
     
     
         14 . The method of  claim 10 , wherein the deflecting step causes the liner to deflect away from the mounting support, increasing L to approximately three times the value of D. 
     
     
         15 . The method of  claim 10 , wherein the chamber has a distance L between the liner and support that is between approximately two to three times the value of D, and the deflecting step causes the liner to deflect away from the mounting support, increasing L to between approximately two to four times the value of D. 
     
     
         16 . The method of  claim 13 , wherein the deflecting step causes the liner to deflect away from the mounting support, increasing L to between approximately 2.5 to 3.5 times the value of D. 
     
     
         17 . The method of  claim 13 , wherein the deflecting step causes the liner to deflect away from the mounting support, increasing L to approximately three times the value of D. 
     
     
         18 . The method of  claim 9 , and further comprising:
 directing the cooling air to pass through the liner and exit the first surface, forming a film.   
     
     
         19 . The method of  claim 9 , wherein a hot spot location on the liner causes the deflecting step. 
     
     
         20 . The method of  claim 9 , wherein the liner is an impingement film cooled panel acting as a heat shield in a gas turbine combustor and the liner is exposed directly to hot air. 
     
     
         21 . The method of  claim 9 , wherein the liner is an impingement film cooled liner in a gas turbine augmenter and the liner is exposed directly to hot air.