Patent ID: 8177496
Filing Date: 2012-05-15
Classification: F01D,F02K,F04D,F05D,Y02T

Abstract:
1. A blade for a turbomachine, the blade extending, in use, in a radial direction relative to the axis of the turbomachine, and the turbomachine having at least one operating condition which generates supersonic fluid flow at the blade, wherein the blade is adapted to provide, at the supersonic operating condition, a leading edge sweep angle which varies such that successive radial positions (i) to (iii) along the leading edge are at respective sweep angle turning points, position (i) being the radially inner and position (iii) the radially outer of the positions, and position (i) being at or radially outward of the 30% span position, where 0% span is the radially innermost point of the leading edge and 100% span is the radially outermost point of the leading edge.