Gas turbine engine fuel manifold

Claim 2

For a gas turbine engine having a combustor disposed radially inside an annular casing, a fuel manifold for providing fuel to said combustor comprising: an arcuate manifold tube disposed radially inside said casing and subject to high temperature compressor discharge air during operation of said combustor; a thermal insulation layer disposed on and completely surrounding said tube; and a cover layer disposed on and completely surrounding said insulation layer and being substantially rigid for protecting said insulation layer from physical damage, wherein said tube has a thermal coefficient of expansion and said cover layer has a thermal coefficient of expansion less than said tube thermal coefficient of expansion.

Claim 3

A fuel manifold according to claim 1, wherein said tube is subject to a differential temperature, and said cover is subject to a different differential temperature, and said tube and cover layer coefficients of expansion are preselected so that the product of said tube thermal coefficient of expansion and said tube differential temperature is substantially equal to the product of said cover layer thermal coefficient of expansion and said cover layer differential temperature.

Claim 4

For a gas turbine engine having a combustor disposed radially inside an annular casing, a fuel manifold for providing fuel to said combustor comprising: an arcuate manifold tube disposed radially inside said casing and subject to high temperature compressor discharge air during operation of said combustor; a thermal insulation layer disposed on and completely surrounding said tube; and a cover layer disposed on and completely surrounding said insulation layer and being substantially rigid for protecting said insulation layer from physical damage, wherein said cover layer is a ceramic matrix composite.

Claim 5

For a gas turbine engine having a combustor disposed radially inside an annular casing, a fuel manifold for providing fuel to said combustor comprising: an arcuate manifold tube disposed radially inside said casing and subject to high temperature compressor discharge air during operation of said combustor; a thermal insulation layer disposed on and completely surrounding said tube; and a cover layer disposed on and completely surrounding said insulation layer and being substantially rigid for protecting said insulation layer from physical damage, wherein said cover layer is a ceramic matrix composite.

Claim 6

For a gas turbine engine having a combustor disposed radially inside an annular casing, a fuel manifold for providing fuel to said combustor comprising: an arcuate manifold tube disposed radially inside said casing and subject to high temperature compressor discharge air during operation of said combustor; a thermal insulation layer disposed on and completely surrounding said tube; and a cover layer disposed on and completely surrounding said insulation layer and being substantially rigid for protecting said insulation layer from physical damage, wherein said tube includes a plurality of manifold stems extending radially therefrom and in flow communication therewith for channeling fuel from said manifold tube to a respective plurality of fuel injectors joined to said manifold stems, and thermal insulation layer and said cover layer are disposed also on said manifold stems.

Claim 7

For a gas turbine engine having a combustor disposed radially inside an annular casing, a fuel manifold for providing fuel to said combustor comprising: an arcuate manifold tube disposed radially inside said casing and subject to high temperature compressor discharge air during operation of said combustor; a thermal insulation layer disposed on and completely surrounding said tube; and a cover layer disposed on and completely surrounding said insulation layer and being substantially rigid for protecting said insulation layer from physical damage, wherein said tube includes a plurality of manifold stems extending radially therefrom and in flow communication therewith for channeling fuel from said manifold tube to a respective plurality of fuel injectors joined to said manifold stems, and thermal insulation layer and said cover layer are disposed also on said manifold stems.

Claim 8

For a gas turbine engine having a combustor disposed radially inside an annular casing, a fuel manifold for providing fuel to said combustor comprising: an arcuate manifold tube; a thermal insulation layer disposed on and completely surrounding said tube; and a cover layer disposed on and completely surrounding said insulation layer and being substantially rigid for protecting said insulation layer from physical damage, wherein said manifold tube is disposed radially inside said casing and is subject to high temperature compressor discharge air during operation of said combustor, and both said thermal insulation layer and said cover layer have preselected thermal conductivities for providing thermal insulation of said tube for maintaining an internal wetted wall temperature of said tube below about 350° F. (177° C.).

Claim 9

For a gas turbine engine having a combustor disposed radially inside an annular casing, a fuel manifold for providing fuel to said combustor comprising: an arcuate manifold tube; a thermal insulation layer disposed on and completely surrounding said tube; and a cover layer disposed on and completely surrounding said insulation layer and being substantially rigid for protecting said insulation layer from physical damage, wherein said manifold tube is disposed radially inside said casing and is subject to high temperature compressor discharge air during operation of said combustor, and both said thermal insulation layer and said cover layer have preselected thermal conductivities for providing thermal insulation of said tube for maintaining an internal wetted wall temperature of said tube below about 350° F. (177° C.).

Claim 10

A fuel manifold according to claim 5, wherein said manifold comprises two of said arcuate manifold tubes disposed coaxially with each other and together extending circumferentially about 360°.

Claim 11

A fuel manifold according to claim 6 wherein each of said manifold tubes extends circumferentially about 180°.

Claim 12

A fuel manifold according to claim 7 wherein said manifold tubes are disposed radially inside said casing and further including respective fuel inlet conduits extending from outside and through said casing and joined in flow communication with said manifold tubes for providing fuel thereto.

Claim 13

A fuel manifold according to claim 8 further including two of said manifolds, in the form of a radially inner manifold and a radially outer manifold, with said two arcuate manifold tubes of respective ones thereof being disposed about 90° relative to the other two arcuate manifold tubes so that said fuel inlet conduits of said inner manifold pass between gaps formed between adjacent ones of said outer manifold tubes and extend to said casing.

Claim 14

A fuel manifold according to claim 9 wherein said combustor includes radially outer and inner liners joined at upstream ends to an annular dome, and said manifold tubes are disposed upstream of said dome and radially between said outer and inner liners.