Gas turbine engine end-wall component

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United States of America Patent

PATENT NO 9915169
SERIAL NO

14810551

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Abstract

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An end-wall component of the mainstream gas annulus of a gas turbine engine having an annular arrangement of vanes, the component including a cooling arrangement having ballistic cooling holes (33) through which, in use, dilution cooling air is jetted into the mainstream gas upstream of the vanes to reduce the mainstream gas temperature adjacent the end-wall, wherein the cooling holes are arranged in one or more circumferentially extending rows and wherein the axial position of the cooling holes in the or each row varies.

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Patent Owner(s)

Patent OwnerAddress
ROLLS-ROYCE PLCKINGS PLACE 90 YORK WAY LONDON N1 9FX

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Inventor(s)

Inventor Name Address # of filed Patents Total Citations
Jackson, Dougal Richard Derby, GB 8 188
Tibbott, Ian Lichfield, GB 49 1126

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