Gas turbine structure
AssigneeROLLS-ROYCE plc
InventorsDavid W Barrett, Philip D Robinson
Life of this patent
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Abstract
A stage of turbine blades (40) in a gas turbine engine (10) is surrounded by an array of shroud segments (42). The upstream ends of the segments (42) have plenum chambers (54) into which cooling air is fed from a compressor (12) via one hole (66) of a pair of holes, the other being numbered (68). Air from the plenum chambers (54) passes out to film cool the interior surface of each respective segment (42). Air from holes (68) passes out to convection cool the exterior surface of each segment (42), which effect is enhanced by the provision of ribs (80) and fences (82).
Claims8
A gas turbine engine including a stage of turbine blades and a plurality of arcuate segments, said arcuate segments surrounding said stage of turbine blades, the inner surfaces of said arcuate segments defining a part of a turbine gas annulus of said engine, wherein each said segment includes a plenum chamber at its upstream end connected in cooling air flow series with a cooling air supply via a cooling air distribution member, which member has cooling air inlets from said supply, and cooling air outlets, each cooling air inlet being in flow series with a respective pair of cooling air outlets, and wherein during operation of said engine, one outlet of each said pair of outlets passes cooling air to the radially inner surface of a respective segment via an associated plenum chamber, and the other outlet of said pair passes cooling air to the radially outer surface of the respective segment.
Dependencies are inferred from the claim text.