公开(公告)号：SG132581A1

公开(公告)日：2007-06-28

申请号：SG2006063416

申请日：2006-09-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANCISCO J ,  MESSEH WILLIAM ABDEL

Abstract: 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 channel through which a cooling fluid flows, at least one exit hole for distributing cooling fluid over a surface of ':the turbine blade, and internal features within the channel for accelerating the flow of cooling fluid prior to the cooling fluid flowing through the at least one exit hole.

公开(公告)号：SG134214A1

公开(公告)日：2007-08-29

申请号：SG2006086714

申请日：2006-12-12

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANCISCO J ,  MESSEH WILLIAM ABDEL

Abstract: A turbine engine component for use in a small engine application has an airfoil portion having a root portion, a tip portion, a suction side wall, and a pressure side wall. The suction side wall and the pressure side wall have the same thickness. Still further, the turbine engine component has a platform with an internal cooling circuit.

公开(公告)号：SG132580A1

公开(公告)日：2007-06-28

申请号：SG2006063408

申请日：2006-09-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANCISCO J ,  MESSEH WILLIAM ABDEL

Abstract: 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 technology is described.

公开(公告)号：SG134213A1

公开(公告)日：2007-08-29

申请号：SG2006086706

申请日：2006-12-12

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANCISCO J ,  MESSEH WILLIAM ABDEL

Abstract: A turbine engine component having improved cooling is provided. The turbine engine component includes an airfoil portion having a leading edge, a trailing edge, a pressure side, a suction side, a root, and a tip, and at least one cooling circuit in a wall of the airfoil portion. The at least one cooling circuit has at least one passageway extending between the root and the tip. The at least one passageway has an aspect ratio of no greater than 2:1, and preferably substantially unity.

公开(公告)号：SG132578A1

公开(公告)日：2007-06-28

申请号：SG2006063382

申请日：2006-09-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANCISCO J ,  MESSEH WILLIAM ABDEL

Abstract: A turbine component has an airfoil portion with at least one central core element, a pressure side wall, and a suction side wall. The airfoil portion also has a serpentine cooling passageway in at least one of the walls. In a preferred embodiment, the airfoil portion has a serpentine cooling passageway in both of the pressure and suction side walls. A refractory metal core for forming the serpentine cooling passageway(s) is also described.