Airfoil cooling with staggered refractory metal core...

Fluid reaction surfaces (i.e. – impellers) – With heating – cooling or thermal insulation means – Changing state mass within or fluid flow through working...

Reexamination Certificate

Rate now

  [ 0.00 ] – not rated yet Voters 0   Comments 0

Details

C415S115000, C029S889721

Reexamination Certificate

active

07731481

ABSTRACT:
A turbine engine component has an airfoil portion with a pressure side wall and a suction side wall and a cooling system. The cooling system has at least one cooling circuit disposed longitudinally along the airfoil portion. Each cooling circuit has a plurality of staggered internal pedestals for increasing heat pick-up.

REFERENCES:
patent: 5370499 (1994-12-01), Lee
patent: 5383766 (1995-01-01), Przirembel et al.
patent: 5392515 (1995-02-01), Auxier et al.
patent: 5690472 (1997-11-01), Lee
patent: 6514042 (2003-02-01), Kvasnak et al.
patent: 6832889 (2004-12-01), Lee et al.
patent: 6981840 (2006-01-01), Lee et al.
patent: 7011502 (2006-03-01), Lee et al.
patent: 7131818 (2006-11-01), Cunha et al.

LandOfFree

Say what you really think

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

Rating

Airfoil cooling with staggered refractory metal core... does not yet have a rating. At this time, there are no reviews or comments for this patent.

If you have personal experience with Airfoil cooling with staggered refractory metal core..., we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Airfoil cooling with staggered refractory metal core... will most certainly appreciate the feedback.

Rate now

     

Profile ID: LFUS-PAI-O-4214029

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