Compressor bleed manifold for a gas turbine engine

Means for protecting the bleed manifold formed from the outer case of a gas turbine engine, said engine having a compressor section including a drum rotor defining an inner boundary for the engine's gas path and for supporting a plurality of compressor stages each of which comprises a row of circumferentially spaced axial flow blades, stator means including wall means defining an inner case radially spaced and coaxially disposed relative to said drum rotor defining an outer boundary for said gas path, means for defining the bleed manifold consisting essentially of a bowed wall formed from a portion of the outer case of said gas turbine engine radially spaced and coaxially disposed relative to said inner case of said drum rotor, and an inner annular wall portion and said bowed wall both being concentrically disposed relative to said outer boundary defining an annular cavity, said inner annular wall portion creating a heat sink and being spaced from said inner case, means for leading a portion of said gas path out of said gas turbine engine through said annular cavity including a first opening in said inner case for flowing a continuous stream of fluid susceptible of including incendiary particles entrained therein, a second opening in said inner annular wall portion parallelly disposed relative to said first opening for leading said stream of fluid into said annular cavity, and a bleed port in said bowed wall, said first opening and said second opening being laterally spaced relative to each other so that said stream of fluid and said incendiary particles entrained therein ingested in said first opening impinges on said inner annular wall portion prior to being ingested into said annular cavity so that heat is dissipated from said incendiary particles by said inner wall for protecting said outer case.