Cooling structure of stationary blade, and gas turbine

F - Mech Eng,Light,Heat,Weapons – 01 – D

Patent

Rate now

  [ 0.00 ] – not rated yet Voters 0   Comments 0

Details

F01D 5/18 (2006.01)

Patent

CA 2435444

A collision plate having plural small holes is provided at an interval from a bottom surface of an inner shroud to form a chamber and guides cooking air from the small holes into the chamber. A leading edge flow path is provided at a leading edge side along a width direction and introduces the cooling air. A side flow path is provided along both sides of the inner shroud and guides the cooling air to a trailing edge side. A header is formed along the width direction near the trailing edge and guides the cooling air from the side flow path. Plural trailing edge flow paths are formed at the trailing edge side at intervals along a width direction, in which one end of each flow path is connected to the header and the other end is open at the trailing edge, and the cooling air in the header is ejected from the trailing edge.

LandOfFree

Say what you really think

Search LandOfFree.com for Canadian inventors and patents. Rate them and share your experience with other people.

Rating

Cooling structure of stationary blade, and gas turbine does not yet have a rating. At this time, there are no reviews or comments for this patent.

If you have personal experience with Cooling structure of stationary blade, and gas turbine, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Cooling structure of stationary blade, and gas turbine will most certainly appreciate the feedback.

Rate now

     

Profile ID: LFCA-PAI-O-1983443

  Search
All data on this website is collected from public sources. Our data reflects the most accurate information available at the time of publication.