Cooled turbine blade

Claim 2

A fluid cooled gas turbine blade having an airfoil portion and a root portion with at least one radially extending chamber within the airfoil portion of said blade, a first fluid channel providing a liquid coolant inlet to said chamber, a plurality of second fluid channels subadjacent the blade surface in said airfoil portion, each of said second channels having an inlet in fluid communication with said chamber subadjacent the top of said blade and an outlet in fluid communication with said chamber generally adjacent the root portion of said blade, a third fluid channel providing fluid communication from said chamber to exit the blade adjacent said tip, the entry to said third channel from within said chamber being disposed at an intermediate position in the radial extent of said chamber and generally radially inwardly of the desired depth of fluid accumulated therein to limit the depth of said fluid in said chamber from adjacent said tip to said entry position whereby any further fluid entering said chamber will exit via said third channel, and, an exhaust channel providing vapor flow communication from said chamber to exit said blade on the downstream face thereof adjacent said root portion whereby, liquid cooling fluid entering said blade is collected in said chamber and under the generally high centrifugal force field of said blade when rotating enters each of said plurality of second channels for flow therethrough promoting vaporization of the liquid to cool the blade, and wherein the flow of the fluid in said second channels and the flow of said vapor generated therein are in a common direction from said tip to said root portion to provide stability for the fluid flow through all said second channels.

Claim 3

Blade structure according to claim 1 wherein said chamber extends generally radially substantially across the airfoil portion of said blade and wherein the fluid exiting said second channels into said chamber is separated, under the influence of the centrifugal force field, into liquid for retention in said chamber for recirculation, and vapor exhausted through said exhaust channel.

Claim 4

Blade structure according to claim 2 wherein said blade defines more than one of said chambers, and wherein each of said chambers has a plurality of said second channels in flow communication therewith.

Claim 5

In a gas turbine engine having a rotor disc and a plurality of blades secured thereto through root portions engaging said disc, said blades also defining an airfoil portion in the path of hot motive gases and a root portion, and means for cooling said blades, said means comprising coolant fluid delivery means for directing said fluid to a circumferential gutter in said disc, a coolant fluid inlet passage in said disc subadjacent each cooled blade therein for directing said fluid to the root portion of said blade and wherein said blade defines a first internal channel providing a liquid coolant inlet in communication with a generally radially extending chamber within the airfoil portion of said blade, a plurality of second fluid channels subadjacent the blade surface in said airfoil portion, each of said second channels having an inlet in fluid communication with said chamber subadjacent the tip of said blade and an outlet in fluid communication with said chamber generally adjacent the root portion of said blade, a third channel providing fluid communication from said chamber to exit the blade adjacent said tip, the entry to said third channel from within said chamber being disposed at an intermediate position in the radial extent of said chamber and generally radially inwardly of the desired depth of fluid accumulated therein to limit the depth of said fluid in said chamber from adjacent said tip to said entry position whereby and further fluid entering said chamber will exit via said third channel, and, an exhaust channel providing vapor flow communication from said chamber to exit said blade on the downstream face thereof adjacent said root portion whereby, liquid cooling fluid entering said blade is collected in said chamber and under the generally high centrifugal force field of said blade when rotating enters each of said plurality of second channels for flow therethrough promoting vaporization of the liquid to cool the blade, and wherein the flow of the fluid in said second channels and the flow of said vapor generated therein are in a common direction from said tip to said root portion to provide stability for the fluid flow through all said second channels.

Claim 6

In a gas turbine engine having a rotor disc and a plurality of blades secured thereto through root portions engaging said disc, said blades also defining an airfoil portion in the path of hot motive gases and a root portion, and means for cooling said blades, said means comprising coolant fluid delivery means for directing said fluid to a circumferential gutter in said disc, a coolant fluid inlet passage in said disc subadjacent each cooled blade therein for directing said fluid to the root portion of said blade and wherein said blade defines a first internal channel providing a liquid coolant inlet in communication with a generally radially extending chamber within the airfoil portion of said blade, a plurality of second fluid channels subadjacent the blade surface in said airfoil portion, each of said second channels having an inlet in fluid communication with said chamber subadjacent the tip of said blade and an outlet in fluid communication with said chamber generally adjacent the root portion of said blade, a third channel providing fluid communication from said chamber to exit the blade adjacent said tip, the entry to said third channel from within said chamber being disposed at an intermediate position in the radial extent of said chamber and generally radially inwardly of the desired depth of fluid accumulated therein to limit the depth of said fluid in said chamber from adjacent said tip to said entry position whereby and further fluid entering said chamber will exit via said third channel, and, an exhaust channel providing vapor flow communication from said chamber to exit said blade on the downstream face thereof adjacent said root portion whereby, liquid cooling fluid entering said blade is collected in said chamber and under the generally high centrifugal force field of said blade when rotating enters each of said plurality of second channels for flow therethrough promoting vaporization of the liquid to cool the blade, and wherein the flow of the fluid in said second channels and the flow of said vapor generated therein are in a common direction from said tip to said root portion to provide stability for the fluid flow through all said second channels.

Claim 7

Structure according to claim 4 wherein said chamber extends generally radially substantially across the airfoil portion of said blade and wherein the fluid exiting said second channels into said chamber is separated, under the influence of the centrifugal force field, into liquid for retention in said chamber for recirculation, and vapor exhausted through said exhaust channel.

Claim 8

Structure according to claim 5 wherein said blade defines more than one of said chambers and wherein each of said chambers has a plurality of said second channels in flow communication therewith.