A motor casing of cast metal used for a vehicle drive device, comprising an equipment mounting seat provided on a top part, an oil cooler connection seat, and a longitudinal hole opened in the oil cooler connection seat, wherein a seat surface of the equipment mounting seat is inclined to get higher from one side to the other, and the longitudinal hole is inclined to get higher from one side to the other in parallel to the seat surface.

A core structure for a providing a cooling passage in a gas turbine engine includes a core body that has a first cooling passage core. The first cooling passage core has a first width in a chord-wise direction near a first wall. A second width in the chord-wise direction near a second wall. A third width in the chord-wise direction between the first and second walls. The third width being smaller than the first and second widths to form an hourglass shape.

A core structure for a providing a cooling passage in a gas turbine engine includes a core body that has a first cooling passage core. The first cooling passage core has a first width in a chord-wise direction near a first wall. A second width in the chord-wise direction near a second wall. A third width in the chord-wise direction between the first and second walls. The third width being smaller than the first and second widths to form an hourglass shape.

A blade preform includes a strut connecting a plat-form to a blade root portion extending longitudinally in an upstream-downstream direction, an upstream web and a downstream web, which each extend in a direction substantially perpendicular to the longitudinal direction of the blade root and are formed at the upstream and downstream ends of the strut. The upstream and downstream webs connect the upstream and downstream ends of the plat-form to the upstream and downstream ends of the blade root. The blade root extends in a direction perpendicular to the longitudinal direction of the blade root over a distance smaller than that of the upstream and downstream webs and the side edges of each web are extended by walls that converge at the flanks of the blade root.

A blade preform includes a strut connecting a plat-form to a blade root portion extending longitudinally in an upstream-downstream direction, an upstream web and a downstream web, which each extend in a direction substantially perpendicular to the longitudinal direction of the blade root and are formed at the upstream and downstream ends of the strut. The upstream and downstream webs connect the upstream and downstream ends of the plat-form to the upstream and downstream ends of the blade root. The blade root extends in a direction perpendicular to the longitudinal direction of the blade root over a distance smaller than that of the upstream and downstream webs and the side edges of each web are extended by walls that converge at the flanks of the blade root.

The device according to any of the preceding claims 13 to 19, characterized in that the device is further configured to carry out a method comprising the step of positioning the green sand mold (3), wherein the device is provided with levelling means configured to hold an upper side of the green sand mold (3) during step c in a parallel position in relation to a gravitationally horizontal plane.

The device according to any of the preceding claims 13 to 19, characterized in that the device is further configured to carry out a method comprising the step of positioning the green sand mold (3), wherein the device is provided with levelling means configured to hold an upper side of the green sand mold (3) during step c in a parallel position in relation to a gravitationally horizontal plane.

A method for producing a rotor vane (10) for a turbomachine, including producing a rough casting, the heel of which has a downstream lip (121) with a transverse increased thickness (130) such that the lip has an upstream surface (134) substantially parallel to an axis The method further includes machining said increased thickness so that the downstream lip has an upstream surface (138) inclined in relation to the axis.

A method for producing a rotor vane (10) for a turbomachine, including producing a rough casting, the heel of which has a downstream lip (121) with a transverse increased thickness (130) such that the lip has an upstream surface (134) substantially parallel to an axis The method further includes machining said increased thickness so that the downstream lip has an upstream surface (138) inclined in relation to the axis.

A decorative emblem comprises a plurality of unit emblem bodies; a plurality of fastening legs connected correspondingly to the plurality of unit emblem bodies and having a reduced diameter portion formed on the center thereof in such a manner as to be easily bent and broken; and leg fixing bars adapted to fix the ends of the fastening legs thereto.