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In a gas turbine engine including a compressor having a casing with a passage adapted to pass bleed air to a circumferentially extending bleed manifold surrounding the casing, the passage including a surface exposed to incendiary particles periodically entrained in the bleed air, an improvement is p

In a gas turbine engine including a compressor having a casing with a passage adapted to pass bleed air to a circumferentially extending bleed manifold surrounding the casing, the passage including a surface exposed to incendiary particles periodically entrained in the bleed air, an improvement is provided comprising means for preventing impingement of the particles upon the exposed surface. In one form the means is disposed between the exposed surface and the bleed air and is comprised of a material which, when reacted with the particles, produces a compound which is essentially nonpyrophoric in the environment of the passage.

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In a gas turbine engine including a compressor having a casing with a mounting slot adapted to receive a mounting tang of a stationary airfoil, a plurality of bleed apertures extending through said casing and communicating said slot with a bleed manifold extending about said casing radially outwardl

In a gas turbine engine including a compressor having a casing with a mounting slot adapted to receive a mounting tang of a stationary airfoil, a plurality of bleed apertures extending through said casing and communicating said slot with a bleed manifold extending about said casing radially outwardly thereof, each of said apertures having an aperture surface area, said slot having a first surface in engagement with said tang and a second surface spaced from said tang, the improvement comprising: first means for preventing incendiary particles entrained in a gas stream flowing through said slot from impinging upon said second surface, wherein said first means is comprised of coating means bonded to said second surface to isolate said second surface from impingement by said particles.