Abstract: A resin composition is provided which is improved in fluidability, stiffness and impact resistance and therefore can achieve the reduction in wall thickness of a resin product for automotive interior/exterior applications comprising a polypropylene resin; and a resin product produced from the resin composition. The resin composition comprises 30 to 65 mass % of an ethylene-propylene block copolymer having a melt flow rate of 60 to 120 g/10 minutes and a Charpy impact strength of 3 kJ/m2 or more; 0 to 25 mass % of a homopolypropylene resin having a melt flow rate of 10 g/10 minutes or more and a modulus of elasticity of 2000 MPa or more; 5 to 20 mass % of an ethylene-?-olefin copolymer rubber having a Mooney viscosity of 20 to 75 or a styrene-ethylene butylenes-styrene copolymer having a styrene component content of 15 to 30 mass %; and 23 to 37 mass % of talc having an average particle diameter of 8 ?m or less.

Abstract: While comprising filled minor compartments being filled with an inclusion in which a liquid makes the major component, and vacant minor compartments being filled with the air, at least one of the vacant minor compartments adjoins the filled minor compartments, and a fragile section is formed in at least one of ribs that demarcate the filled minor compartments and the adjoining vacant minor compartments. After the fragile section has fractured, shock energy can be absorbed furthermore by means of circulation resistance to the inclusion that flows from the filled minor compartments to the vacant minor compartments.

Abstract: A blade cooling structure of a gas turbine, which can reduce the pressure loss of a cooling medium without decreasing the heat transfer coefficient, is provided. The blade cooling structure comprises a cooling passage (15) for flowing cooling air (A) from a proximal end portion (12) toward a blade portion (14) of a moving blade (11), a plurality of turbulators (21) arranged, on both wall surfaces of the cooling passage (15) opposing each other, in such a manner as to be inclined with respect to the flowing direction of the cooling air (A), and a plurality of dimples (22) formed in a downstream region (N) downstream of a center position (O) in the flowing direction of the cooling air (A) on the wall surface of the cooling passage (15) between the adjacent turbulators (21).

Abstract: While comprising filled minor compartments being filled with an inclusion in which a liquid makes the major component, and vacant minor compartments being filled with the air, at least one of the vacant minor compartments adjoins the filled minor compartments, and a fragile section is formed in at least one of ribs that demarcate the filled minor compartments and the adjoining vacant minor compartments. After the fragile section has fractured, shock energy can be absorbed furthermore by means of circulation resistance to the inclusion that flows from the filled minor compartments to the vacant minor compartments.

Abstract: A blade cooling structure of a gas turbine, which can reduce the pressure loss of a cooling medium without decreasing the heat transfer coefficient, is provided. The blade cooling structure comprises a cooling passage (15) for flowing cooling air (A) from a proximal end portion (12) toward a blade portion (14) of a moving blade (11), a plurality of turbulators (21) arranged, on both wall surfaces of the cooling passage (15) opposing each other, in such a manner as to be inclined with respect to the flowing direction of the cooling air (A), and a plurality of dimples (22) formed in a downstream region (N) downstream of a center position (O) in the flowing direction of the cooling air (A) on the wall surface of the cooling passage (15) between the adjacent turbulators (21).

Abstract: A resin composition is provided which is improved in fluidability, stiffness and impact resistance and therefore can achieve the reduction in wall thickness of a resin product for automotive interior/exterior applications comprising a polypropylene resin; and a resin product produced from the resin composition. The resin composition comprises 30 to 65 mass % of an ethylene-propylene block copolymer having a melt flow rate of 60 to 120 g/10 minutes and a Charpy impact strength of 3 kJ/m2 or more; 0 to 25 mass % of a homopolypropylene resin having a melt flow rate of 10 g/10 minutes or more and a modulus of elasticity of 2000 MPa or more; 5 to 20 mass % of an ethylene-?-olefin copolymer rubber having a Mooney viscosity of 20 to 75 or a styrene-ethylene butylenes-styrene copolymer having a styrene component content of 15 to 30 mass %; and 23 to 37 mass % of talc having an average particle diameter of 8 ?m or less.

Abstract: A center cluster panel 2 is formed with a projected portion 20 including an upper panel 21 extended to a vehicle rear side and disposed at an uppermost portion thereof, a curved face panel 22 connected to a rear portion of the upper panel 21 and directed to a vehicle front side by being bent from the connected portion 24, and a lower panel 23 connected to the curved face panel 22, extended to a front side and disposed on a vehicle lower side of the upper panel 21. The upper panel 21 and the lower panel 23 are formed such that respective wall thicknesses t1 and t2 are uniform. The wall thickness t1 of the upper panel 21 is made to be thicker than the wall thickness t2 of the lower panel 23. The curved face panel 22 is formed such that a wall thickness t3 thereof is equal to the wall thickness t1 of the upper panel 21 at the portion 24 connected with the upper panel 21 and formed such that the more proximate to the lower panel 23 from the connected portion 24, the more thinned the wall thickness t3 gradually.

Abstract: In a clip attaching seat 1 integrally provided to a vehicular interior molded product and attached with a clip having a locking head portion of a bulged shape above a neck portion, on a face of a seating portion 11 in a plate-like shape formed with a clip locking hole 12, ribs (14 through 16) having widths the same as a plate thickness thereof are formed. Thereby, a rigidity of the thin-walled seating portion 11 is ensured while making a wall thickness of a total of the clip attaching seat 1 constant.

Abstract: A center cluster panel 2 is formed with a projected portion 20 including an upper panel 21 extended to a vehicle rear side and disposed at an uppermost portion thereof, a curved face panel 22 connected to a rear portion of the upper panel 21 and directed to a vehicle front side by being bent from the connected portion 24, and a lower panel 23 connected to the curved face panel 22, extended to a front side and disposed on a vehicle lower side of the upper panel 21. The upper panel 21 and the lower panel 23 are formed such that respective wall thicknesses t1 and t2 are uniform. The wall thickness t1 of the upper panel 21 is made to be thicker than the wall thickness t2 of the lower panel 23. The curved face panel 22 is formed such that a wall thickness t3 thereof is equal to the wall thickness t1 of the upper panel 21 at the portion 24 connected with the upper panel 21 and formed such that the more proximate to the lower panel 23 from the connected portion 24, the more thinned the wall thickness t3 gradually.

Abstract: For the purpose of reduced NOx gas emission, a gas turbine engine comprises a cylinder having a combustion region inside of the cylinder; a resonator having a cavity and provided around the surface of the cylinder and sound absorption holes formed on the cylinder and having opening ends on the cylinder.

Abstract: There is provided a combustor to burn fuel, comprising a bypass passage connected to one side of the combustor to supply air into the combustor; and an annular passage provided around the combustor and connected to the bypass passage, wherein air supplied through the bypass passage passes in the annular passage in the circumferential direction, and is uniformly supplied into the combustor in the circumferential direction thereof through an opening which connects the combustor and the annular passage. Accordingly, compressed air passing through the bypass passage can be supplied uniformly into a tail portion of the combustor, and unevenness of temperature distribution in a cross section of the combustor tail portion can be reduced.

Abstract: A gas turbine combustor includes a side wall, for defining a combustion volume, having upstream and downstream ends, a pilot nozzle, disposed adjacent the upstream end of the side wall, for discharging a pilot fuel to form a diffusion flame in the combustion volume, and a plurality of main nozzles, provided around the pilot nozzles, for discharging a fuel-air mixture to form premixed flames in the combustion volume. Film air is supplied into the combustion volume downstream of the main nozzles along the inner surface of the side wall to reduce the fuel-air ratio in a region adjacent the inner surface of the side wall and to restrain a combustion-driven oscillation in the combustion volume.

Abstract: A gas turbine combustor includes a side wall, for defining a combustion volume, having upstream and downstream ends, a pilot nozzle, disposed adjacent the upstream end of the side wall, for discharging a pilot fuel to form a diffusion flame in the combustion volume, and a plurality of main nozzles, provided around the pilot nozzles, for discharging a fuel-air mixture to form premixed flames in the combustion volume. Film air is supplied into the combustion volume downstream of the main nozzles along the inner surface of the side wall to reduce the fuel-air ratio in a region adjacent the inner surface of the side wall and to restrain a combustion-driven oscillation in the combustion volume.

Abstract: In a tail tube seal structure of gas turbine, a U-shaped groove is provided at one side of a tail tube seal where a flange of a tail tube outlet is fitted, and a pi-shaped groove is provided at other side of the tail tube seal where a gas pass side flange end is fitted, thereby composing the seal of the connection area. Inclined cooling holes are drilled in the tail tube seal in addition to the cooling holes existing conventionally. The cooling air flows in from the inclined holes and cools the gas pass side of the groove due to the film effect. Therefore, the difference in thermal expansion between the groove and flange end is decreased, the wear of this area is decreased, and the reliability of the seal is enhanced.

Abstract: A gas turbine combustor includes a side wall, for defining a combustion volume, having upstream and downstream ends, a pilot nozzle, disposed adjacent the upstream end of the side wall, for discharging a pilot fuel to form a diffusion flame in the combustion volume, and a plurality of main nozzles, provided around the pilot nozzles, for discharging a fuel-air mixture to form premixed flames in the combustion volume. Film air is supplied into the combustion volume downstream of the main nozzles along the inner surface of the side wall to reduce the fuel-air ratio in a region adjacent the inner surface of the side wall and to restrain a combustion-driven oscillation in the combustion volume.

Abstract: For the purpose of reduced NOx gas emission, a gas turbine engine comprises a cylinder having a combustion region inside of the cylinder; a resonator having a cavity and provided around the surface of the cylinder and sound absorption holes formed on the cylinder and having opening ends on the cylinder.

Abstract: For the purpose of reduced NOx gas emission, a gas turbine engine comprises a cylinder having a combustion region inside of the cylinder; a resonator having a cavity and provided around the surface of the cylinder and sound absorption holes formed on the cylinder and having opening ends on the cylinder.

Abstract: A gas turbine moving blade is provided which prevents occurrence of cracks caused by thermal stresses due to temperature differences between a blade and a platform while the gas turbine is being stopped. During steady operation time of the moving blade, cooling air enters cooling passages to flow through other cooling passages for cooling the blade, and then to flow out of the blade. A recessed portion having a smooth curved surface is provided in the platform near a blade fitting portion on the blade trailing edge side. A fillet of the blade fitting portion on the blade trailing edge side has a curved surface with curvature larger than that of a conventional blade fitting portion. A hub slot below the fillet, for blowing air, has a cross sectional area larger than other slots of the blade trailing edge. A thermal barrier coating is applied to the blade surface.

Abstract: A gas turbine combustor includes a side wall, for defining a combustion volume, having upstream and downstream ends, a pilot nozzle, disposed adjacent the upstream end of the side wall, for discharging a pilot fuel to form a diffusion flame in the combustion volume, and a plurality of main nozzles, provided around the pilot nozzles, for discharging a fuel-air mixture to form premixed flames in the combustion volume. Film air is supplied into the combustion volume downstream of the main nozzles along the inner surface of the side wall to reduce the fuel-air ratio in a region adjacent the inner surface of the side wall and to restrain a combustion-driven oscillation in the combustion volume.

Abstract: There is provided a combustor to burn fuel, comprising a bypass passage connected to one side of the combustor to supply air into the combustor; and an annular passage provided around the combustor and connected to the bypass passage, wherein air supplied through the bypass passage passes in the annular passage in the circumferential direction, and is uniformly supplied into the combustor in the circumferential direction thereof through an opening which connects the combustor and the annular passage. Accordingly, compressed air passing through the bypass passage can be supplied uniformly into a tail portion of the combustor, and unevenness of temperature distribution in a cross section of the combustor tail portion can be reduced.