Zero-cross-flow impingement via an array of differing length, extended ports
AssigneeSolar Turbines Incorporated
InventorsSrinath Varadarajan Ekkad, Eric Ian Esposito, Yong Weon Kim
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Abstract
A jet impingement array design and method are disclosed for efficiently cooling the liner of a gas turbine combustion chamber, while eliminating almost all effects of coolant gas crossflow. The design includes an array of extended jet ports for which the distance between the ends of the jet ports and the surface to be cooled progressively decreases from upstream to downstream. Spent air from upstream jets is directed away from downstream jets, thereby reducing the detrimental effects of crossflow, and optimizing heat transfer.
Claims19
A gas turbine, comprising:
- a liner disposed around a combustion chamber of the turbine engine;
- a shell positioned radially outwards the liner to define an annular channel therebetween;
- and
- a plurality of ports extending through the shell to direct a coolant into the annular channel and direct the coolant from an upstream end to a downstream end of the annular channel, each port of the plurality of ports including a distal end that opens into the annular channel, the plurality of ports including a first end port proximate the upstream end and a second end port proximate the downstream end, wherein the distal end of the second end port is positioned closer to the liner than the distal end of the first end port.
A gas turbine, comprising:
- a liner disposed around a combustion chamber of the turbine engine;
- a shell positioned circumferentially around the liner to define an annular channel therebetween;
- and
- a plurality of ports extending through the shell into the annular channel, the plurality of ports having a distal end and being configured to deliver a coolant into the annular channel and direct the coolant from an upstream end to a downstream end of the annular channel, wherein the plurality of ports are arranged on the shell such that a radial distance between the distal end of a port of the plurality of ports and the liner decreases as an axial distance of the port from the upstream end increases, wherein the plurality of ports include at least three ports.
A method of impingement cooling a double walled liner of a gas turbine, the double walled liner including an inner liner surrounding a combustion chamber of the turbine engine and an outer liner positioned radially outwards the inner liner to define an annular channel, that extends from an upstream end to a downstream end, therebetween, comprising:
- delivering a coolant radially into the annular channel through a plurality of ports on the outer liner such that the coolant enters the annular channel closer to the inner liner at the downstream end than at the upstream end;
- directing the delivered coolant to impinge upon the inner liner;
- and
- directing the coolant to flow towards the downstream end after the impinging.
Dependencies are inferred from the claim text.