Patent application number | Description | Published |
20090016870 | TURBOFAN ENGINE - A turbofan engine of the invention is provided with a fan first-stage moving blade for taking an air therein, and a spinner rotationally driving the fan first-stage moving blade, the spinner has a spiral blade extending spirally to an outer side in a radial direction, sucking the air from a front face of the spinner and supplying the air to the fan first-stage moving blade. Further, the fan first-stage moving blade and the spinner are integrally coupled, and the spiral blade and the fan first-stage moving blade are formed such that blade surfaces are smoothly connected. | 01-15-2009 |
20090304518 | TURBOFAN ENGINE - A hub-side leading edge part of a fan first-stage rotating blade | 12-10-2009 |
20100135781 | BLADE ROW OF AXIAL FLOW TYPE COMPRESSOR - In a blade row of an axial flow type compressor in which a rotor blade row and a stator blade row are alternately arranged in an axial direction, the stator blade row | 06-03-2010 |
20100143105 | COMPRESSOR STATOR BLADE AND COMPRESSOR ROTOR BLADE - A compressor stator blade | 06-10-2010 |
20100232970 | FAN ROTATING BLADE FOR TURBOFAN ENGINE | 09-16-2010 |
20130111908 | FAN ROTOR BLADE AND FAN - A fan rotor blade includes a blade body constructed of a composite material, a blade root constructed of the composite material, and a sheath attached to a leading edge of the blade body. The sheath includes a sheath main body and a pair of joint flanges, and is segmented into a sheath base segment and a sheath top segment. The sheath top segment has a longer length than a length of the sheath base segment along a span direction. A sheath length of the sheath main body at an assumed impact position with an obstacle is not shorter than 10% chord and not longer than 60% chord. A sheath length of the sheath along an end edge of the fan rotor blade is not shorter than 40% chord. The fan rotor blade possesses sufficient impact resistance and can be simplified and light-weighted. | 05-09-2013 |
20130323065 | FAN ROTOR BLADE AND FAN - A fan rotor blade has a rotor blade leading edge. On a hub side of the rotor blade leading edge, a vertical hub section is formed. From a top end of the vertical hub section to a mid-span side of the rotor blade leading edge, a backward tilt mid-span section is formed. From a top end of the backward tilt mid-span section to a tip end of the rotor blade leading edge, a forward tilt tip section is formed. From a hub end of the rotor blade leading edge to a base end of the vertical hub section, a backward tilt hub section is formed. The backward tilt hub section is backwardly tilted so that a top end thereof is positioned behind a base end thereof. | 12-05-2013 |
20140363304 | ROTOR BLADE AND FAN - A rotor blade main body includes multiple first composite sheet groups and multiple second composite sheet groups which are provided in a blade thickness direction. Each first composite sheet group includes multiple composite sheets which are stacked one on another from a blade thickness center side toward a dorsal surface. Each second composite sheet group includes multiple composite sheets which are stacked one on another from the blade thickness center side toward a ventral surface. A composite direction of orientation directions of fibers in the multiple composite sheets in each of the sheet groups inclines by 20 degrees to 45 degrees from a span direction. | 12-11-2014 |
20150064000 | COUPLING PART STRUCTURE FOR VANE AND JET ENGINE INCLUDING THE SAME - A coupling support member including a pair of divided pieces is placed in a coupling part between a vane proximal end portion of a guide vane and an attachment flange, and the pair of divided pieces are joined to the vane proximal end portion from both the sides in the vane thickness direction. A linear protrusion is formed on one of joint surfaces of the vane proximal end portion to the pair of divided pieces. A groove engaged with the linear protrusion formed in the vane proximal end portion is formed on one of respective joint surfaces of the pair of divided pieces of the coupling support member. The vane proximal end portion is held between the pair of divided pieces of the coupling support member, by the fastening force that is applied to the pair of divided pieces of the coupling support member from both the sides in the vane thickness direction. It is possible to obtain a high structural strength while contributing to a reduction in weight of a jet engine. | 03-05-2015 |