초록 ▼

A blade part in a turbofan includes a hub coupled with a rotating axis of a driving part, a plurality of blades arranged radially at a circumferential part of the hub, and a shroud coupled with a plurality of the blades and arranged so as to confront the hub wherein the blades lie between the hub an

A blade part in a turbofan includes a hub coupled with a rotating axis of a driving part, a plurality of blades arranged radially at a circumferential part of the hub, and a shroud coupled with a plurality of the blades and arranged so as to confront the hub wherein the blades lie between the hub and the shroud, and wherein each of the blades form an airfoil constructed with a top camber line defined by an NACA 4-digit airfoil and a bottom camber line lying closer to the top camber line than a bottom camber line defined by the NACA 4-digit airfoil.

대표청구항 ▼

1. A blade part in a turbofan, comprising: a hub coupled with a rotating axis of a driving part; a plurality of blades arranged radially at a circumferential part of the hub; and a shroud coupled with a plurality of the blades and arranged so as to confront the hub wherein the blades lie bet

1. A blade part in a turbofan, comprising: a hub coupled with a rotating axis of a driving part; a plurality of blades arranged radially at a circumferential part of the hub; and a shroud coupled with a plurality of the blades and arranged so as to confront the hub wherein the blades lie between the hub and the shroud, and wherein each cross-section of the blades is defined by NACA four digits, so as to form an airfoil wherein, if a chord line is an X-axis and a leading edge in an origin, and a chord c is 1, x is a chordwise, X-axis direction, relative coordinate and y t(x) is a thickness function so as to satisfy wherein Y c(x) is a Y-axis relative coordinate of a mean camber line and &thgr; is a slope of the mean camber line so as to satisfywhere M is a % value of a relative y coordinate of a maximum camber and P is a 10% value of a relative x coordinate of the maximum camber and wherein a coordinate (x u,yu) of the top camber line of the blade is defined by xu=x−yt(x)sin &thgr;, yu=yc(x) +yt(x)cos &thgr; and a coordinate (xl,yl) of the bottom camber line satisfies xl=x+yt(x)sin &thgr;, yc(x)−yt(x)cos &thgr;