Double-skin liner for a gas turbine

Abstract

A double-skin liner for a combustion chamber of a gas turbine. The double-skin liner includes an inner layer, an outer layer with an expansion gap provided on the outer layer, a gap covering element, a sealing element, a plurality of internal cooling holes provided on the inner layer, and a plurality of external cooling holes provided on the outer layer. When the inner layer expands due to temperature increase, a proximal section of the outer layer and a distal section of the outer layer distance from each other through lengthening the expansion gap.

What is claimed is: 
     
         1 - A double-skin liner for a combustion chamber of a gas turbine, the double-skin liner comprising:
 an inner layer, the inner layer being cylindrical;   an outer layer, the outer layer being cylindrical, a first end of the inner layer fixedly attached to a first end of the outer layer, a second end of the inner layer fixedly attached to a second end of the outer layer, the inner layer and the outer layer forming a cooling gap between the inner layer and the outer layer, the outer layer comprising:
 a proximal section; 
 a distal section; and 
 an expansion gap provided on the outer layer between the proximal section and the distal section, the expansion gap comprising a 360-degree cylindrical gap; 
   a gap covering element, the gap covering element being cylindrical, the gap covering element attached to an outer surface of the outer layer, a first end of the gap covering element fixedly attached to the distal section of the outer layer, a second end of the gap covering element movably attached to the proximal section of the outer layer, the gap covering element configured to prevent air flow between the cooling gap and an outer space of the outer layer through the expansion gap, the gap covering element comprising:
 a first flat section at the first end of the gap covering element, the first flat section fixedly attached to the distal section of the outer layer; 
 a second flat section at the second end of the gap covering element, the second section movably disposed onto the proximal section of the outer layer; and 
 a curved section attached between the first flat section and the second flat section; 
   a sealing element, the sealing element attached to the outer surface of the outer layer, the gap covering element disposed between the outer layer and the sealing element, the sealing element configured to form a seal between the double-skin liner and a transition piece when a distal end of the double-skin liner is inserted into the transition piece;   a plurality of internal cooling holes provided on the inner layer, the plurality of internal cooling holes configured to provide air communication between an inner space of the inner layer and the cooling gap; and   a plurality of external cooling holes provided on the outer layer, the plurality of external cooling holes configured to provide air communication between the cooling gap and an outer space of the outer layer,   wherein:
 the proximal section of the outer layer and the distal section of the outer layer are configured to extend a distance from each other by lengthening the expansion gap responsive to expansion of the inner layer; 
 the plurality of internal cooling holes, the cooling gap, and the plurality of external cooling holes are configured to provide cooling mechanism for the double-skin liner by (how); and 
 the second flat section is configured to move along the proximal section of the outer layer responsive to the proximal section of the outer layer and the distal section of the outer layer distancing from each other. 
   
     
     
         2 - A double-skin liner for a combustion chamber of a gas turbine, the double-skin liner comprising:
 an inner layer; and   an outer layer, a first end of the inner layer fixedly attached to a first end of the outer layer, a second end of the inner layer fixedly attached to a second end of the outer layer, the inner layer and the outer layer forming a cooling gap between the inner layer and the outer layer, the outer layer comprising:
 a proximal section; 
 a distal section; and 
 an expansion gap provided on the outer layer between the proximal section and the distal section, 
   wherein the proximal section of the outer layer and the distal section of the outer layer are configured to distance from each other through lengthening the expansion gap responsive to expansion of the inner layer.   
     
     
         3 - The double-skin liner of  claim 2 , further comprising a gap covering element, the gap covering element attached to an outer surface of the outer layer, a first end of the gap covering element fixedly attached to the distal section of the outer layer, a second end of the gap covering element movably attached to the proximal section of the outer layer, the gap covering element configured to prevent air communication between the cooling gap and an outer space of the outer layer through the expansion gap. 
     
     
         4 - The double-skin liner of  claim 3 , further comprising a sealing element, the sealing element attached to the outer surface of the outer layer, the gap covering element disposed between the outer layer and the sealing element, the sealing element configured to form a seal between the double-skin liner and a transition piece when a distal end of the double-skin liner is inserted into the transition piece. 
     
     
         5 - The double-skin liner of  claim 4 , further comprising:
 a plurality of internal cooling holes provided on the inner layer, the plurality of internal cooling holes configured to provide air communication between an inner space of the inner layer and the cooling gap; and   a plurality of external cooling holes provided on the outer layer, the plurality of external cooling holes configured to provide air communication between the cooling gap and the outer space of the outer layer,   wherein the plurality of internal cooling holes, the cooling gap, and the plurality of external cooling holes are configured to provide cooling mechanism for the double-skin liner.   
     
     
         6 - The double-skin liner of  claim 5 , wherein the gap covering element comprises:
 a first flat section at the first end of the gap covering element, the first flat section fixedly attached to the distal section of the outer layer;   a second flat section at the second end of the gap covering element, the second section movably disposed onto the proximal section of the outer layer; and   a curved section attached between the first flat section and the second flat section,   wherein the second flat section is configured to move along the proximal section of the outer layer responsive to the proximal section of the outer layer and the distal section of the outer layer distancing from each other.   
     
     
         7 - A turbine combustor comprising a combustor liner, the combustor liner having a hollow cylindrical shape, the combustor liner comprising:
 an inner layer comprising a hollow cylindrical shape disposed about a central axis of the combustor liner, the inner layer comprising an upstream end and a downstream end with respect to combustion gas flow during operation;   an outer layer with a hollow cylindrical shape, the outer layer disposed outside the inner layer in a radial direction surrounding the inner layer, the outer layer comprising a first section and a second section wherein the first section is upstream of the second section with respect to the combustion gas flow during operation, the first section of the outer layer comprising an upstream end and a downstream end with respect to the combustion gas flow during operation, the second section of the outer layer comprising an upstream end and a downstream end with respect to the combustion gas flow during operation, the upstream end of the first section of the outer layer attached to the upstream end of the inner layer, the downstream end of the second section of the outer layer attached to the downstream end of the inner layer;   wherein the downstream end of the first section of the outer layer is mounted adjacent the upstream end of the second section of the outer layer with a gap between the downstream end of the first section of the outer layer and the upstream end of the second section of the outer layer, the gap configured at least equivalent to distance that the first section of the outer layer and the second section of the outer layer are configured to expand due to the combustion gas; and   a gap sealing element with a hollow cylindrical shape disposed outside the gap in a radial direction surrounding the gap, the gap sealing element comprising an upstream end and a downstream end with respect to the combustion gas flow during operation, the upstream end of the gap sealing element configured in contact with the first section of the outer layer, the downstream end of the gap sealing element configured in contact with the second section of the outer layer, the gap sealing element configured to seal the gap and to disconnect air communication between the gap and an outside of the outer layer.   
     
     
         8 - The turbine combustor of  claim 7 , further comprising:
 a transition piece connected to the second section of the outer layer in a radial direction via a hula seal, the transition piece configured to bring out the combustion gas.   
     
     
         9 - The turbine combustor of  claim 7 , wherein the upstream end of the first section of the outer layer is welded to the upstream end of the inner layer. 
     
     
         10 - The turbine combustor of  claim 7 , wherein the downstream end of the second section of the outer layer is welded to the downstream end of the inner layer. 
     
     
         11 - The turbine combustor of  claim 7 , wherein the upstream end of the gap sealing element is attached to the first section of the outer layer, the downstream end of the gap sealing element configured in contact with the second section of the outer layer, the downstream end of the gap sealing element further configured to be slidable on the second section of the outer layer. 
     
     
         12 - The turbine combustor of  claim 11 , wherein the upstream end of the gap sealing element is welded to the first section of the outer layer. 
     
     
         13 - The turbine combustor of  claim 7 , wherein the downstream end of the gap sealing element is attached to the second section of the outer layer, the upstream end of the gap sealing element is configured to be in contact with the first section of the outer layer, the upstream end of the gap sealing element further configured to be slidable on the first section of the outer layer. 
     
     
         14 - The turbine combustor of  claim 13 , wherein the downstream end of the gap sealing element is welded to the second section of the outer layer.