Turbine shroud cooling
AssigneePratt & Whitney Canada Corp.
InventorsRemy Synnott, Mohammed Ennacer, Chris Pater, Denis Blouin, Kapila Jain, Farough Mohammadi
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Abstract
A turbine shroud segment has a body having a radially outer surface and a radially inner surface extending axially between a leading edge and a trailing edge and circumferentially between a first and a second lateral edge. A first serpentine channel is disposed axially along the first lateral edge. A second serpentine channel is disposed axially along the second lateral edge. The first and second serpentine channels each define a tortuous path including axially extending passages between a front inlet proximate the leading edge and a rear outlet at the trailing edge of the body.
Claims9
A turbine shroud segment for a gas turbine engine;
- the turbine shroud segment comprising:
- a body having a radially outer surface and a radially inner surface extending axially between a leading edge and a trailing edge and circumferentially between a first and a second lateral edge;
- a first serpentine channel disposed axially along the first lateral edge;
- and a second serpentine channel disposed axially along the second lateral edge, the first serpentine channel and the second serpentine channel each defining a tortuous path including axially extending passages between a front inlet adjacent to the leading edge and a rear outlet at the trailing edge of the body, wherein at least one of the first serpentine channel and the second serpentine channel has a crossover wall defining a series a crossover holes configured to accelerate a flow of coolant passing therethrough.
Dependencies are inferred from the claim text.