High-turning and high-transonic blade

Details High-turning and high-transonic blade High-turning and high-transonic blade

2006-06-06

2006-06-06

Look, Edward K. (Department: 3745)

Rotary kinetic fluid motors or pumps

Means, disposition or arrangement for causing supersonic...

C416S243000, C416SDIG004

Reexamination Certificate

active

07056089

ABSTRACT:
A high-turning and high-transonic blade for use in a blade cascade of an axial-flow compressor, wherein a distribution of flow speed on an extrados at a leading edge of the blade has a supersonic region of a substantially constant flow speed in the rear of a first large value of the flow speed and inside a position corresponding to 15% of a chord length from the leading edge. The supersonic region is established so that a value obtained by the division of a difference between Mach numbers at front and rear ends of the supersonic region by a chord-wise length of the supersonic region is smaller than 1, and the maximum Mach number in the supersonic region is smaller than 1.4. A first large shock wave is positively generated at a position where the flow speed assumes a first maximum value, whereby a second shock wave generated in the supersonic region of the substantially constant flow speed in the rear of such a position can be weakened. Thus, boundary layer separation due to the second shock wave can be suppressed, to thereby remarkably reduce the pressure loss of a following flow on the blade.

REFERENCES:
patent: 4655412 (1987-04-01), Hinkleman
patent: 5554000 (1996-09-01), Katoh et al.
patent: 07-083196 (1995-03-01), None
patent: 09-256998 (1997-09-01), None

Affiliated with

Also associated with

Rating

High-turning and high-transonic blade does not yet have a rating. At this time, there are no reviews or comments for this patent.

If you have personal experience with High-turning and high-transonic blade, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and High-turning and high-transonic blade will most certainly appreciate the feedback.

Rate now

Comments { 0 }

Profile ID: LFUS-PAI-O-3666887