Duplex turbine shroud
AssigneeGeneral Electric Company
InventorsChing-Pang Lee, Geoffrey Douglas Robinson, Robert Joseph Orlando
Life of this patent
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Abstract
A gas turbine engine shroud includes a row of different first and second shroud segments alternating circumferentially therearound. The first segments have a first pattern of first cooling holes extending therethrough. The second segments have a second pattern of second cooling holes extending therethrough. The corresponding patterns have different collective flowrate capabilities.
Claims25
A gas turbine engine apparatus comprising:
- an annular combustor having a row of fuel injectors;
- an annular turbine nozzle following said combustor and having a row of vane doublets with axial splitlines therebetween;
- a row of turbine blades following said nozzle;
- a duplex turbine shroud surrounding said blades, and comprising a row of different first and second shroud segments alternating circumferentially around said blades;
- said first segments having a first pattern of first cooling holes clocked with said fuel injectors for receiving hot combustion streaks therefrom over said first holes;
- and
- said second segments having a second pattern of second cooling holes clocked offset with said injectors for receiving cold combustion streaks from the spaces therebetween over said second holes.
A duplex turbine shroud comprising:
- a row of different first and second shroud segments alternating circumferentially;
- said first segment having a first pattern of first cooling holes extending therethrough;
- and
- said second segment having a second pattern of second cooling holes extending therethrough.
A shroud in combination with an upstream turbine nozzle and annular combustor having a row of fuel injectors, and said first shroud segments are clocked with said injectors for receiving hot combustion streaks therefrom over said first holes thereof.
Dependencies are inferred from the claim text.