Manifold protection system

Claim 2

A protection system for use in a bleed manifold associated with a gas turbine engine, said manifold including a wall partially defining a flow path for a fluid flowing in a stream through said manifold, a fluid inlet disposed upstream of said wall, said fluid flow stream periodically including incendiary particles entrained therein, said protection system comprising barrier means disposed within said manifold and within said flow stream upstream of said wall for preventing impingement of at least a portion of said particles upon said wall, said barrier means comprising fluid flow stream turning means for removing said portion of said particles from said fluid flow stream and pocket means disposed adjacent said fluid flow stream for receiving said particles removed from said flow stream by said stream turning means.

Claim 3

The invention as set forth in claim 1 wherein said stream turning means comprises fluid inlet and outlet means disposed in said barrier means for providing an abrupt change in direction of the fluid flow stream flowing within said barrier means whereby the inertia of said portion of particles carries said portion of particles out of said flow stream and into said pocket means.

Claim 4

The invention as set forth in claim 2 wherein said pocket means are formed by a double-walled portion having spaced apart inner and outer walls, said inner walls disposed so as to be impinged upon by said portion of particles removed from said flow stream.

Claim 5

The invention as set forth in claim 3 wherein said barrier means further includes a material having a low heat transfer coefficient and high sublimation temperature disposed between said inner and outer barrier walls.

Claim 6

A protection system for use in a bleed manifold associated with a gas turbine engine, said manifold including a wall partially defining a flow path for a fluid flowing in a stream through said manifold, a fluid inlet disposed upstream of said wall, said fluid flow stream periodically including incendiary particles entrained therein, said protection system comprising barrier means disposed within said manifold and within said flow stream upstream of said wall for preventing impingement of at least a portion of said particles upon said wall, wherein said barrier means is comprised of a circumferentially and axially extending base portion having a plurality of fluid inlet apertures disposed therein, said base portion disposed in abutting engagement with a casing portion of said engine such that said inlet apertures overlap bleed ports in said casing, a radially and circumferentially extending fluid exit wall depending radially from said base portion and having a plurality of fluid exit apertures disposed therein, a double-walled portion having spaced apart inner and outer walls, said double-walled portion having a generally curved configuration and connecting said base portion and said exit wall portion.

Claim 7

A protection system for use in a bleed manifold associated with a gas turbine engine, said manifold including a wall partially defining a flow path for a fluid flowing in a stream through said manifold, a fluid inlet disposed upstream of said wall, said fluid flow stream periodically including incendiary particles entrained therein, said protection system comprising barrier means disposed within said manifold and within said flow stream upstream of said wall for preventing impingement of at least a portion of said particles upon said wall, wherein said barrier means is comprised of a circumferentially and axially extending base portion having a plurality of fluid inlet apertures disposed therein, said base portion disposed in abutting engagement with a casing portion of said engine such that said inlet apertures overlap bleed ports in said casing, a radially and circumferentially extending fluid exit wall depending radially from said base portion and having a plurality of fluid exit apertures disposed therein, a double-walled portion having spaced apart inner and outer walls, said double-walled portion having a generally curved configuration and connecting said base portion and said exit wall portion.

Claim 8

A protection system for use in a bleed manifold associated with a gas turbine engine, said manifold including a wall partially defining a flow path for a fluid flowing in a stream through said manifold, a fluid inlet disposed upstream of said wall, said fluid flow stream periodically including incendiary particles entrained therein, said protection system comprising barrier means disposed within said manifold and within said flow stream upstream of said wall for preventing impingement of at least a portion of said particles upon said wall, said barrier means comprising protective liner means disposed between said manifold wall and said stream of fluid flowing within said manifold for receiving impingement by said particles, wherein said protective liner means includes inner and outer spaced apart walls, said outer wall being disposed between said inner wall and said manifold wall, and a material having a low heat transfer coefficient and a high sublimation temperature disposed in said space between said inner and outer walls.

Claim 9

A protection system for use in a bleed manifold associated with a gas turbine engine, said manifold including a wall partially defining a flow path for a fluid flowing in a stream through said manifold, a fluid inlet disposed upstream of said wall, said fluid flow stream periodically including incendiary particles entrained therein, said protection system comprising barrier means disposed within said manifold and within said flow stream upstream of said wall for preventing impingement of at least a portion of said particles upon said wall, said barrier means comprising protective liner means disposed between said manifold wall and said stream of fluid flowing within said manifold for receiving impingement by said particles, wherein said protective liner means includes inner and outer spaced apart walls, said outer wall being disposed between said inner wall and said manifold wall, and a material having a low heat transfer coefficient and a high sublimation temperature disposed in said space between said inner and outer walls.

Claim 10

The invention as set forth in claim 6 wherein said barrier means has the same general contour of said manifold wall.

Claim 11

The invention as set forth in claim 7 wherein said barrier means abuttingly engages said manifold wall.

Claim 12

The invention as set forth in claim 8 wherein said barrier means extends circumferentially about the axial centerline of said engine and is comprised of a plurality of circumferentially extending segments.