Abstract: A gas turbine includes a compressor, a combustor, an air lead-out member, an outer peripheral cover portion, and an auxiliary device member. The outer peripheral cover portion includes outer peripheral concave portions and outer peripheral convex portions, and is formed in a manner so that the outer peripheral concave portions recessed radially inward of the combustor so as to enter between mutually-adjacent combustion cylinders among the plurality of combustion cylinders and the outer peripheral convex portions protruding radially outward of the combustor so as to extend along outer peripheral surfaces of the plurality of combustion cylinders are alternately and continuously arranged in a circumferential direction of the combustor. The auxiliary device member is attached to one of the outer peripheral concave portions.

Abstract: A gas turbine includes a combustor, an air lead-out member, an outer peripheral cover portion, an inner peripheral cover portion, and a fuel supply unit. A lead-out port of the air lead-out member is located radially outward of one end portion of the combustor. The combustor has a guide wall portion which is formed so as to connect mutually-adjacent combustion cylinders and guides air from an air flow path to an inner space via a communication path. Through holes are formed in the outer peripheral surface of each of the combustion cylinders and open to the inner space to allow air in the inner space to flow into the downstream side of a combustion chamber.

Abstract: The liner of a combustor (100) for a gas turbine engine is provided with a projection region (111) provided with a plurality of projections (110) each projecting toward the compressed air chamber (56) from the liner outer surface and having a vertical wall portion (114) extending substantially orthogonally to a flow direction of compressed air flowing in the compressed air chamber, and a plurality of cooling holes (118) passed through the liner from the liner outer surface to the liner inner surface such that an end of each cooling hole on a side of the compressed air chamber is more downstream than an end of the cooling hole on a side of the combustion chamber (52) with respect to the flow direction of the compressed air in the compressed air chamber, at least a part of the cooling holes being formed in the projection region.

Abstract: A fuel nozzle device (100) for injecting liquid fuel into a combustion chamber (52) of a gas turbine engine (10) includes an outer tube (101), a rear end wall (102) closing a base end of the outer tube, a tapered conical tube (104) defining a first air passage (112) therein, and a second air passage (114) having an annular cross section jointly with the outer tube, a fuel passage (108) axially passed through the rear end wall, and leading to a fuel ejection port (109) directed toward an inner circumferential surface of a base end of the conical tube, a first air introduction passage (111) passed through the outer tube to communicate with the first air passage, and a second air introduction passage (113) passed through the outer tube to communicate with the second air passage.

Abstract: A fuel nozzle device (100) for injecting liquid fuel into a combustion chamber (52) of a gas turbine engine (10) includes an outer tube (101), a rear end wall (102) closing a base end of the outer tube, a tapered conical tube (104) defining a first air passage (112) therein, and a second air passage (114) having an annular cross section jointly with the outer tube, a fuel passage (108) axially passed through the rear end wall, and leading to a fuel ejection port (109) directed toward an inner circumferential surface of a base end of the conical tube, a first air introduction passage (111) passed through the outer tube to communicate with the first air passage, and a second air introduction passage (113) passed through the outer tube to communicate with the second air passage.

Abstract: The liner of a combustor (100) for a gas turbine engine is provided with a projection region (111) provided with a plurality of projections (110) each projecting toward the compressed air chamber (56) from the liner outer surface and having a vertical wall portion (114) extending substantially orthogonally to a flow direction of compressed air flowing in the compressed air chamber, and a plurality of cooling holes (118) passed through the liner from the liner outer surface to the liner inner surface such that an end of each cooling hole on a side of the compressed air chamber is more downstream than an end of the cooling hole on a side of the combustion chamber (52) with respect to the flow direction of the compressed air in the compressed air chamber, at least a part of the cooling holes being formed in the projection region.

Abstract: Formed in a wall part of a dome part of an annular combustor encircling an axis of a gas turbine engine are multiple fuel supply holes spaced at predetermined intervals in circumferential direction around the axis and many cooling holes extending through the wall part in direction inclined to a normal thereof. When two adjacent fuel supply holes are defined as first and second fuel supply holes, a virtual boundary line contacting an outer semi-circular portion, far from the axis, of the first fuel supply hole and an inner semi-circular portion, close to the axis, of the second fuel supply hole is set. The first cooling holes in region radially outward, relative to the axis, of the line are inclined toward the second fuel supply hole, and the second cooling holes in region radially inward, relative to the axis, of the line are inclined toward the first fuel supply hole.

Abstract: In a combustor for a gas turbine engine, a radially outer end part of a dilution air introduction passage is radially slidably fitted into an inner periphery of an outer opening. A radially inner end part of the passage axially slidably abuts against an open edge of an inner opening. Therefore, even if outer and inner wall parts undergo relative movement in radial or axial direction due to difference in thermal expansion amount, it is possible to prevent occurrence of excessive stress and ensure airtightness for the outer and inner openings, stabilizing amount of dilution air introduced into a combustion chamber. Air does not leak into space between the outer and inner wall parts from the radially outer end part, therefore, air jet passing through an impingement cooling hole of the outer wall part collides with the inner wall part without disturbed, enhancing cooling effect of the inner wall part.

Abstract: A nozzle guide support device, that supports a nozzle guide of a fuel nozzle on an open flange part encircling a fuel supply hole of a combustor of a gas turbine engine, is formed by fixing a cap that supports the nozzle guide in a floating state to the open flange part by means of a rivet. Rotation of the nozzle guide relative to the open flange part is restricted by engagement between a recess portion of the nozzle guide and a spacer fitted to the rivet. Accordingly, not only is it possible to cut production time and production cost compared with a case in which the nozzle guide support device is fixed by welding or brazing, but it is also possible to suppress unlimited rotation of the fuel nozzle guide while enabling the fuel nozzle guide to float in a radial direction and a axial direction.

Abstract: In a structure for cooling a gas turbine engine, an open flange part encircling a fuel supply hole formed in a combustor includes a conical portion enlarging in a conical shape toward an outside of the combustor and a flat portion extending radially outward in a flat plate shape from an extremity of the conical portion, and a nozzle guide includes a cylindrical portion covering an outer periphery of a fuel nozzle for supplying fuel to the fuel supply hole and a bottom flange portion being bent radially outward from a corner portion at an extremity of the cylindrical portion and supported in a floating state on the flat portion. A cooling hole for supplying air that cools the open flange part and the nozzle is formed in the corner portion of the guide, and a direction of the cooling hole is inclined toward an axis of the nozzle.

Abstract: Formed in a wall part of a dome part of an annular combustor encircling an axis of a gas turbine engine are multiple fuel supply holes spaced at predetermined intervals in circumferential direction around the axis and many cooling holes extending through the wall part in direction inclined to a normal thereof. When two adjacent fuel supply holes are defined as first and second fuel supply holes, a virtual boundary line contacting an outer semi-circular portion, far from the axis, of the first fuel supply hole and an inner semi-circular portion, close to the axis, of the second fuel supply hole is set. The first cooling holes in region radially outward, relative to the axis, of the line are inclined toward the second fuel supply hole, and the second cooling holes in region radially inward, relative to the axis, of the line are inclined toward the first fuel supply hole.

Abstract: In a structure for cooling a gas turbine engine, an open flange part encircling a fuel supply hole formed in a combustor includes a conical portion enlarging in a conical shape toward an outside of the combustor and a flat portion extending radially outward in a flat plate shape from an extremity of the conical portion, and a nozzle guide includes a cylindrical portion covering an outer periphery of a fuel nozzle for supplying fuel to the fuel supply hole and a bottom flange portion being bent radially outward from a corner portion at an extremity of the cylindrical portion and supported in a floating state on the flat portion. A cooling hole for supplying air that cools the open flange part and the nozzle is formed in the corner portion of the guide, and a direction of the cooling hole is inclined toward an axis of the nozzle.

Abstract: Since a wall part of a combustor of a gas turbine engine includes a cylindrical flange projecting integrally from an outer periphery of a spark plug fitting hole, and a spark plug support device covering an extremity of a spark plug is welded or brazed to the flange, a welded or brazed site of the device is above the flange lower in temperature than the wall part, and it is possible to suppress decrease in strength at the welded or brazed site and to improve durability, and also to reduce cost since a shape of the device may be coincided with a simple shape of the flange and machining of the device becomes easy. Since the flange is formed integrally with the wall part, compared with a case where the flange is formed from a separate member, the number of components and machining steps is decreased, enabling further cost reduction.

Abstract: A nozzle guide support device, that supports a nozzle guide of a fuel nozzle on an open flange part encircling a fuel supply hole of a combustor of a gas turbine engine, is foamed by fixing a cap that supports the nozzle guide in a floating state to the open flange part by means of a rivet. Rotation of the nozzle guide relative to the open flange part is restricted by engagement between a recess portion of the nozzle guide and a spacer fitted to the rivet. Accordingly, not only is it possible to cut production time and production cost compared with a case in which the nozzle guide support device is fixed by welding or brazing, but it is also possible to suppress unlimited rotation of the fuel nozzle guide while enabling the fuel nozzle guide to float in a radial direction and a axial direction.

Abstract: To provide a diesel light oil composition having an excellent ignitability while containing butanol. The diesel light oil composition comprises a diesel light oil base material, butanol having a volume percentage in a range of 9% to 20% and butyl nitrate or butyl nitrite having a volume percentage in a range of 0.8% to 4%. It is preferable that the butanol is 20 v/v %, and the butyl nitrate or butyl nitrite is 4 v/v %. The butyl nitrite or butyl nitrate is derived from butanol as a material.

Abstract: A rotary fluid machine is provided in which, among first bearings (23f, 23r) and a second bearing (24) supporting in a casing (11) opposite ends of a rotor (22) that includes an axial piston cylinder group (56) for converting the pressure energy of a working medium into mechanical energy, only the first bearings (23f, 23r) are formed from combined angular bearings that can support an axial load, and the second bearing (24) is formed from a radial bearing that can support a radial load and is axially movable relative to the rotor (22). Since the rotor (22) is axially positioned relative to the casing (11) by only the first bearings (the combined angular bearings) (23f, 23r), a difference in the amount of axial thermal expansion between the casing (11) and the rotor (22) can be absorbed by the second bearing (radial bearing) (24) without any problem. This can solve effectively problems caused by a difference in the amount of thermal expansion between the casing and the rotor of the rotary fluid machine.