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US 2014/0271104 A1Published application
Turbine Shroud Cooling System
AssigneeGeneral Electric Company
InventorsCharles Lewis Davis, III, Terry Howard Strout, Pawel Piotr Kolniak
Life of this patent
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Abstract
The present application provides a turbine shroud cooling system for a gas turbine engine. The turbine shroud cooling system may include a number of variable area cooling shrouds with tuning pins and a number of fixed area cooling shrouds with anti-rotation pins. The variable area cooling shrouds may include modulated cooling shrouds. The fixed area shrouds may include non-modulated shrouds.
Claims20
A turbine shroud cooling system for a gas turbine engine, comprising:
- a plurality of variable area cooling shrouds;
- the plurality of variable area cooling shrouds comprising a tuning pin;
- and
- a plurality of fixed area cooling shrouds;
- the plurality of fixed area cooling shrouds comprising an anti-rotation pin.
2 more elements
A method of cooling a plurality of shrouds in a gas turbine engine, comprising:
- installing a plurality of variable area shrouds;
- installing a plurality of fixed area shrouds;
- flowing a cooling flow through the plurality of variable area shrouds;
- modulating the cooling flow through the plurality of variable area shrouds;
- and
- flowing the cooling flow through the plurality of fixed area shrouds.
3 more elements
A gas turbine engine, comprising:
- a plurality of variable area modulated cooling shrouds;
- the plurality of variable area modulated cooling shrouds comprising a tuning pin;
- and
- a plurality of fixed area non-modulated cooling shrouds;
- the plurality of fixed area non-modulated cooling shrouds comprising an anti-rotation pin.
2 more elements
Dependencies are inferred from the claim text.