Superalloy material components for turbine engines, including steam and combustion turbine engines are fabricated by superplastic formation of a laser-sintered preform. Superalloy material powder is sintered into a preform, such as by laser sintering. The preform is inserted within a pressurized forming furnace, containing a mold with a mold cavity defined by a mold cavity surface. The preform is heated in the forming furnace, and differential pressure is applied across the preform to deform it superplastically into abutting contact with the mold cavity surface, without fracturing the preform. Thereafter, the superalloy component is extracted from the forming furnace.

A combustor is configured such that an outer liner defines a combustion chamber configured such that fuel and air are supplied thereto from an upstream end side, the fuel is subjected to combustion, and a combustion gas flows out to a downstream end side, an inner liner extends to be concentric with the outer liner inside the outer liner, a sub burner is defined between the outer liner and the inner liner, a main burner is defined on the downstream end side, the fuel is supplied at an equivalence ratio and is subjected to combustion in the sub burner, and the fuel and the air are supplied to the main burner through a region provided radially inward of the inner liner and are subjected to combustion while being mixed with a burnt gas.

A combustor is configured such that an outer liner defines a combustion chamber configured such that fuel and air are supplied thereto from an upstream end side, the fuel is subjected to combustion, and a combustion gas flows out to a downstream end side, an inner liner extends to be concentric with the outer liner inside the outer liner, a sub burner is defined between the outer liner and the inner liner, a main burner is defined on the downstream end side, the fuel is supplied at an equivalence ratio and is subjected to combustion in the sub burner, and the fuel and the air are supplied to the main burner through a region provided radially inward of the inner liner and are subjected to combustion while being mixed with a burnt gas.

A cable assembly for a flame sensor apparatus includes an inner conductor electrically connected to a photodiode that generates a current. The inner conductor transmits the current from the photodiode. A first insulating layer circumferentially surrounds the inner conductor. The first insulating layer includes a mineral insulation material. An inner sheath circumferentially surrounds the first insulating layer. The inner sheath includes an electrically conductive material. A second insulating layer circumferentially surrounds the inner sheath. The second insulating layer includes a mineral insulation material. An outer sheath circumferentially surrounds the second insulating layer. The outer sheath includes an electrically conductive material. The cable assembly is for use in temperatures up to about 300 degrees Celsius or greater. A method of attaching a cable assembly for a flame sensor apparatus.

A cable assembly for a flame sensor apparatus includes an inner conductor electrically connected to a photodiode that generates a current. The inner conductor transmits the current from the photodiode. A first insulating layer circumferentially surrounds the inner conductor. The first insulating layer includes a mineral insulation material. An inner sheath circumferentially surrounds the first insulating layer. The inner sheath includes an electrically conductive material. A second insulating layer circumferentially surrounds the inner sheath. The second insulating layer includes a mineral insulation material. An outer sheath circumferentially surrounds the second insulating layer. The outer sheath includes an electrically conductive material. The cable assembly is for use in temperatures up to about 300 degrees Celsius or greater. A method of attaching a cable assembly for a flame sensor apparatus.

A finely distributed combustion system for a gas turbine engine is provided. A combustor body may extend along a longitudinal axis. A premixer space may be formed within the combustor body to premix air and fuel. The premixer space is in communication with an array of finely distributed perforations arranged in a wall of the combustor body to eject an array of premixed main flamelets throughout a contour of the combustor body between the upstream base of the combustor body and the downstream base of the combustor body. The array of finely distributed perforations—potentially comprising thousands or even hundreds of thousands of perforations spatially distributed on a miniaturized scale—for ejecting the premixed main flamelets is technically advantageous compared to conventional distributed combustion systems, where injection of relatively longer main flames occurs just at a few discrete axial locations.

A finely distributed combustion system for a gas turbine engine is provided. A combustor body may extend along a longitudinal axis. A premixer space may be formed within the combustor body to premix air and fuel. The premixer space is in communication with an array of finely distributed perforations arranged in a wall of the combustor body to eject an array of premixed main flamelets throughout a contour of the combustor body between the upstream base of the combustor body and the downstream base of the combustor body. The array of finely distributed perforations—potentially comprising thousands or even hundreds of thousands of perforations spatially distributed on a miniaturized scale—for ejecting the premixed main flamelets is technically advantageous compared to conventional distributed combustion systems, where injection of relatively longer main flames occurs just at a few discrete axial locations.

A combustor including: a transition piece having a cylindrical shape and including an inlet of combustion gas at one end and an outlet of the combustion gas at the other end and configured to allow the combustion gas flowing from the inlet to flow out from the outlet so as to introduce the combustion gas into a turbine; a cooling medium introduction unit introduced with the cooling medium and provided on an outer periphery portion in an outlet side of the transition piece; a cooling medium inlet configured to introduce the cooling medium into the cooling medium introduction unit; and a cooling portion, connected to the cooling medium introduction unit, provided on a portion from the outlet of the transition piece toward the inlet and configured to allow the cooling medium from the cooling medium introduction unit to pass through the outlet toward the inlet.

A combustor including: a transition piece having a cylindrical shape and including an inlet of combustion gas at one end and an outlet of the combustion gas at the other end and configured to allow the combustion gas flowing from the inlet to flow out from the outlet so as to introduce the combustion gas into a turbine; a cooling medium introduction unit introduced with the cooling medium and provided on an outer periphery portion in an outlet side of the transition piece; a cooling medium inlet configured to introduce the cooling medium into the cooling medium introduction unit; and a cooling portion, connected to the cooling medium introduction unit, provided on a portion from the outlet of the transition piece toward the inlet and configured to allow the cooling medium from the cooling medium introduction unit to pass through the outlet toward the inlet.

A tail pipe (50) comprises: a pipe (51); an acoustic attenuator (61) that forms an acoustic space (Ss) on the outer peripheral side of the pipe (51); and a cooling air jacket (65) that forms a cooling air space (Sa) isolated from the outer space (So), which is the space on the outer peripheral side of the pipe (51). The pipe (51) has: a first air flow path (56) that is formed between the outer peripheral surface (55o) and the inner peripheral surface (55i); and an acoustic hole (59) that penetrates from the acoustic space (Ss) to a combustion space (Sc), which is a space on the inner peripheral side of the pipe (51c). The first air flow path (56) has: an inlet (56i) that faces into the cooling air space (Sa) and guides the air in the cooling air space (Sa) into the first air flow path (56); and an outlet (56o) that faces into the acoustic space (Ss) and guides the air passing through the first air flow path (56) into the acoustic space (Ss).