| Patent Number |
Title Of Patent |
Date Issued |
| 7607891 |
Turbine component with tip flagged pedestal cooling |
October 27, 2009 |
| A turbine blade for a gas turbine engine is provided with improved cooling at a radially outer portion of the trailing edge. A tip flag path is provided with a first pedestal array to increase the heat transfer at the area. In addition, a second pedestal array replaces the metering holes |
| 7553131 |
Integrated platform, tip, and main body microcircuits for turbine blades |
June 30, 2009 |
| A turbine engine component has an airfoil portion with a pressure side and a suction side. The turbine engine component further has a first cooling microcircuit for cooling the suction side of the airfoil portion. The first cooling microcircuit is embedded within a first wall forming the |
| 7553128 |
Blade outer air seals |
June 30, 2009 |
| A blade outer air seal (BOAS) has a body having an inner (ID) face and an outer (OD) face, first and second circumferential ends, and fore and aft longitudinal ends. The BOAS has one or more mounting hooks extending from the body. The OD face comprises a plurality of transversely elongat |
| 7513745 |
Advanced turbulator arrangements for microcircuits |
April 7, 2009 |
| A passageway is provided through which a cooling fluid flows in a first direction. The passageway has a plurality of trip strips positioned within the passageway. Adjacent one of the trip strips are oriented to converge towards each other at a first end to form an apex portion and to |
| 7445432 |
Enhanced serpentine cooling with U-shaped divider rib |
November 4, 2008 |
| A cooling passageway for use in an airfoil prtrion of a turbine engine component having a pressure side wall and a suction side wall is provided. The cooling passsageway comprises a serpentine flow passageway through which a cooling fluid flows. The passageway has an inlet through wh |
| 7311498 |
Microcircuit cooling for blades |
December 25, 2007 |
| A turbine engine component such as a turbine blade includes an airfoil portion formed by a suction side wall and a pressure side wall, and a cooling microcircuit incorporated in at least one of the suction side wall and the pressure side wall. The cooling microcircuit comprises a cha |
| 7303375 |
Refractory metal core cooling technologies for curved leading edge slots |
December 4, 2007 |
| A turbine engine component has an airfoil portion with a leading edge portion. The leading edge portion includes a plurality of staggered holes for causing fluid to flow over a surface of the airfoil portion. A method for forming the leading edge portion using refractory metal core t |
| 7114916 |
Tailored turbulation for turbine blades |
October 3, 2006 |
| A turbine blade having improved cooling characteristics is provided. The turbine blade has an airfoil portion having a span, and at least one cooling passageway in the airfoil portion extending from a root portion of the airfoil portion to a tip portion of the airfoil portion. A plur |
| 6997675 |
Turbulated hole configurations for turbine blades |
February 14, 2006 |
| A turbine blade having improved cooling has an airfoil with a root end and a tip end and at least one cooling passageway in the airfoil. Each cooling passageway extends from the root end to the tip end and has a circular cross-section. A plurality of turbulation promotion devices are |
| 6508620 |
Inner platform impingement cooling by supply air from outside |
January 21, 2003 |
| A stator blade assembly for a gas turbine engine has a leading edge portion with a passage communicating between a plenum and an air supply port of the outer shroud and an internal blade cooling channel communicating between passages and apertures adjacent the trailing edge of the blade. |
