Gas turbine engine construction and operation

Claim 2

Combustion apparatus comprising the combination of: a combustor in which liquid fuel can be burned and means for reducing the emission of nitrogen oxides from said combustor, said last-mentioned means comprising means for; introducing a liquid coolant and the liquid fuel into said combustor; there mixing said coolant with said fuel; atomizing the fuel and coolant and forming a uniform mixture of fuel, coolant, and combustion air as the mixture enters the primary combustion zone in said combustor, said means for introducing a liquid coolant and the liquid fuel into said combustor comprising at least one fuel injection nozzle for introducing the liquid fuel into the combustor and means for introducing said liquid coolant into said combustor through said fuel injection nozzle, said fuel injection nozzle comprising a body having a centrally disposed combustion air passage extending through and opening onto one end thereof and an annular liquid fuel passage concentrically surrounding said air passage and opening onto the same end of the nozzle as said combustion air passage; said combustor further comprising means for introducing the liquid fuel into said annular passage; means for introducing the liquid coolant into the combustion air passage, and means for forming said liquid coolant into a film on the wall of said combustion air passage comprising means for introducing air into said centrally disposed passage and means for imparting a swirl to the air in said centrally disposed passage, thereby promoting the uniform mixing of said coolant and said fuel as they are discharged from said one end of said fuel injection nozzle.

Claim 3

A gas turbine engine comprising: a compressor; turbine means for driving said compressor and for providing kinetic energy in useful form; a combustor in which the liquid fuel can be burned with air discharged from said compressor to provide hot gases for driving said turbine means; and means for reducing the emission of nitrogen oxides from said engine, said last-mentioned means comprising: means for introducing a liquid coolant and the liquid fuel into said combustor; there mixing said coolant with said fuel; atomizing the fuel; and forming a uniform mixture of air, liquid coolant, and fuel as said mixture enters the primary combustion zone in said combustor, said means for introducing a liquid coolant and the liquid fuel into said combustor comprising at least one fuel injection nozzle for introducing the liquid fuel into the gas turbine engine combustor and means for introducing the liquid coolant into said combustor through said fuel injection nozzle, said fuel injection nozzle comprising a body having a centrally disposed, combustion air passage extending through and opening onto one end thereof and an annular liquid fuel passage concentrically surrounding said combustion air passage and opening onto the same end of said body as the latter; said gas turbine engine further comprising means for introducing the liquid fuel into said annular passage; means for introducing the liquid coolant into the combustion air passage; and means for forming said liquid coolant into a film on the wall of said combustion air passage comprising means for introducing air into said centrally disposed passage and means for imparting a swirl to the air in said centrally disposed passage, thereby promoting the uniform mixing of said coolant and said fuel as they are discharged from said one end of said fuel injection nozzle.

Claim 4

A gas turbine engine comprising: a compressor; turbine means for driving said compressor and for providing kinetic energy in useful form; a combustor in which the liquid fuel can be burned with air discharged from said compressor to provide hot gases for driving said turbine means; and means for reducing the emission of nitrogen oxides from said engine, said last-mentioned means comprising: means for introducing a liquid coolant and the liquid fuel into said combustor; there mixing said coolant with said fuel; atomizing the fuel; and forming a uniform mixture of air, liquid coolant, and fuel as said mixture enters the primary combustion zone in said combustor, said means for introducing a liquid coolant and the liquid fuel into said combustor comprising at least one fuel injection nozzle for introducing the liquid fuel into the gas turbine engine combustor and means for introducing the liquid coolant into said combustor through said fuel injection nozzle, said fuel injection nozzle comprising a body having a centrally disposed, combustion air passage extending through and opening onto one end thereof and an annular liquid fuel passage concentrically surrounding said combustion air passage and opening onto the same end of said body as the latter; said gas turbine engine further comprising means for introducing the liquid fuel into said annular passage; means for introducing the liquid coolant into the combustion air passage; and means for forming said liquid coolant into a film on the wall of said combustion air passage comprising means for introducing air into said centrally disposed passage and means for imparting a swirl to the air in said centrally disposed passage, thereby promoting the uniform mixing of said coolant and said fuel as they are discharged from said one end of said fuel injection nozzle.

Claim 5

A gas turbine engine comprising: a compressor; turbine means for driving said compressor and for providing kinetic energy in useful form; a combustor in which the liquid fuel can be burned with air discharged from said compressor to provide hot gases for driving said turbine means; and means for reducing the emission of nitrogen oxides from said engine, said last-mentioned means for comprising means for: introducing a liquid coolant and the liquid fuel into said combustor; there mixing said coolant with said fuel; atomizing the fuel; and forming a uniform mixture of air, liquid coolant, and fuel as said mixture enters the primary combustion zone in said combustor, including means comprising a plurality of fuel injection nozzles for introducing the liquid fuel into the gas turbine engine combustor and means for introducing the liquid coolant into said combustor through said fuel injection nozzles, said fuel injection nozzles being equidistantly spaced in a circular array and the means for supplying the liquid fuel to the nozzles comprising upper and lower, arcuately shaped fuel manifolds having, together, an essentially circular configuration, the circular array of equiangularly spaced fuel injection nozzles being spaced concentrically within the circle formed by said manifolds; fuel lines connecting those fuel injectors girdled by each of the manifolds to that manifold at generally equidistantly spaced locations therealong; means for supplying fuel to the upper manifold at the opposite ends thereof; a fuel supply line connected between said fuel supplying means and said lower manifold approximately mid way between the ends of the latter; and means in said fuel supply line for creating a pressure drop that is effective to cause said fuel to be distributed at rates approaching equal through the upper and lower fuel manifolds.

Claim 6

A gas turbine engine comprising: a compressor; turbine means for driving said compressor and for providing kinetic energy in useful form; a combustor in which the liquid fuel can be burned with air discharged from said compressor to provide hot gases for driving said turbine means; and means for reducing the emission of nitrogen oxides from said engine, said last-mentioned means for comprising means for: introducing a liquid coolant and the liquid fuel into said combustor; there mixing said coolant with said fuel; atomizing the fuel; and forming a uniform mixture of air, liquid coolant, and fuel as said mixture enters the primary combustion zone in said combustor, including means comprising a plurality of fuel injection nozzles for introducing the liquid fuel into the gas turbine engine combustor and means for introducing the liquid coolant into said combustor through said fuel injection nozzles, said fuel injection nozzles being equidistantly spaced in a circular array and the means for supplying the liquid fuel to the nozzles comprising upper and lower, arcuately shaped fuel manifolds having, together, an essentially circular configuration, the circular array of equiangularly spaced fuel injection nozzles being spaced concentrically within the circle formed by said manifolds; fuel lines connecting those fuel injectors girdled by each of the manifolds to that manifold at generally equidistantly spaced locations therealong; means for supplying fuel to the upper manifold at the opposite ends thereof; a fuel supply line connected between said fuel supplying means and said lower manifold approximately mid way between the ends of the latter; and means in said fuel supply line for creating a pressure drop that is effective to cause said fuel to be distributed at rates approaching equal through the upper and lower fuel manifolds.

Claim 7

A gas turbine engine as defined in claim 1 wherein said fuel injection nozzle also comprises a gas fuel shroud forming an annular supply passage for a gaseous fuel around said liquid fuel passage and an annular array of communicating discharge ports at said one end of said nozzle, said discharge ports being inclined toward the axial centerline of said cylindrical nozzle body.

Claim 8

A gas turbine engine as defined in claim 4 wherein said fuel injection nozzle has an air shroud forming a secondary air passage, said passage being, at its discharge side, inclined toward the axial centerline of said nozzle at, and beyond, said one end thereof.

Claim 9

A gas turbine engine as defined in claim 5 wherein said fuel injection nozzle has means surrouding said secondary air passage forming means for imparting a swirl to air supplied to and flowing therethrough to stabilize the flame generated by the combustion of fuel discharged from said nozzle.

Claim 10

A gas turbine engine as defined in claim 2 wherein said fuel injection nozzle also comprises a shroud surrounding the nozzle body and forming therewith an annular supply passage for a gaseous fuel which concentrically surrounds said liquid fuel passage and an annular array of discharge ports at said one end of said nozzle body, said discharge ports communicating with said gaseous fuel passage and being inclined toward the axial centerline of said nozzle body.

Claim 11

A gas turbine engine as defined in claim 7 wherein said fuel injection nozzle has an air shroud forming a secondary air passage around the nozzle body, said passage being, at its discharge side, inclined toward the axial centerline of said nozzle body at, and beyond, said one end thereof.

Claim 12

A gas turbine engine as defined in claim 8 wherein said fuel injection nozzle has means surrounding said secondary air passage forming means for imparting a swirl to air supplied to and flowing therethrough to stabilize the flame generated by the combustion of fuel discharged from said nozzle.

Claim 13

A gas turbine engine as defined in any of the preceding claims 8 or 9 wherein the air introducing means includes the gas turbine engine compressor, whereby said air is compressor discharge air.

Claim 14

A gas turbine engine as defined in claim 2 which has a plurality of fuel injection nozzles as aforesaid and which includes means for supplying gaseous fuel to the fuel injection nozzles, said last-mentioned means comprising a circular manifold surrounding the turbine engine combustor and fuel lines connecting said manifold to said fuel injection nozzles.

Claim 15

A gas turbine engine as defined in claim 2 which has a vertically oriented, annular array of fuel injection nozzles as aforesaid and wherein the means for introducing coolant into the gas turbine engine combustor includes an annular coolant supply manifold and lines connecting said manifold to said nozzles, there being orifices in said lines for equalizing the flow of coolant to the several nozzles.

Claim 16

A gas turbine engine as defined in claim 3 wherein the means in the liquid fuel supply system for creating said pressure drop is a check valve oriented to allow fuel to flow from said fuel supplying means through said fuel supply line to said lower manifold.

Claim 17

A gas turbine engine as defined in either of the preceding claims 3 or 13 in which the liquid fuel supply system includes means for draining fuel from said lower manifold coincidentally with the shutdown of the engine, said means comprising a fuel return line connected between said fuel supplying means and said lower manifold adjacent said fuel supply line and a check valve in said fuel return line which is oriented to allow fuel to flow from said lower manifold into said fuel supplying means when the pressure in the latter falls below the pressure in the lower manifold.

Claim 18

A gas turbine engine as defined in either of the preceding claims 3 or 13 in which the supplying means of the liquid fuel supply system comprises a first, generally semicircular fuel line surrounding the lower manifold and connected at its opposite ends to the ends of the upper manifold, and a second fuel line communicating with the first fuel line approximately mid way between the ends of the latter.