Invention Grant
- Patent Title: Cooling circuit flow path for a turbine section airfoil
- Patent Title (中): 涡轮机翼型的冷却回路流路
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Application No.: US11622060Application Date: 2007-01-11
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Publication No.: US08757974B2Publication Date: 2014-06-24
- Inventor: Tracy A. Propheter-Hinckley , Young H. Chon , Joseph W. Bridges, Jr.
- Applicant: Tracy A. Propheter-Hinckley , Young H. Chon , Joseph W. Bridges, Jr.
- Applicant Address: US CT Hartford
- Assignee: United Technologies Corporation
- Current Assignee: United Technologies Corporation
- Current Assignee Address: US CT Hartford
- Agency: Carlson, Gaskey & Olds P.C.
- Main IPC: F01D5/18
- IPC: F01D5/18

Abstract:
A cooled airfoil includes an impingement rib having a multiple of openings which supply a cooling airflow from a cooling circuit flow path toward an airfoil leading edge. The multiple of openings are offset in the impingement rib opposite an outer airfoil wall which includes gill holes. Offsetting the multiple of openings opposite an outer airfoil wall which includes the gill holes focuses the cooling airflow across turbulators to increase the cooling airflow dwell time to increase the thermal transfer therefrom in higher temperature airfoil areas.
Public/Granted literature
- US20090074575A1 COOLING CIRCUIT FLOW PATH FOR A TURBINE SECTION AIRFOIL Public/Granted day:2009-03-19
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