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：DE602006004827D1

公开(公告)日：2009-03-05

申请号：DE602006004827

申请日：2006-11-22

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANCISCO J ,  ABDEL-MESSEH WILLIAM

IPC: F01D5/18 ,  B22C9/12

Abstract: A turbine engine component has an airfoil portion (12) with a leading edge portion (10). The leading edge portion (10) includes a plurality of staggered holes (14) for causing fluid to flow over a surface of the airfoil portion (10). A method for forming the leading edge portion (10) 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：DE602007013150D1

公开(公告)日：2011-04-28

申请号：DE602007013150

申请日：2007-07-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANCISCO J ,  ALBERT JASON E

IPC: F01D5/18

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：GB2461367B

公开(公告)日：2011-01-05

申请号：GB0908102

申请日：2009-05-11

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SNYDER TIMOTHY S ,  CUNHA FRANCISCO J

IPC: F01D25/12 ,  F01D25/14 ,  F01D25/30 ,  F02K1/82

Abstract: A system comprises a bypass duct, a turbine case, a turbine exhaust ring and a splash plate. The turbine case is formed along a radially inner margin of the bypass duct, and the turbine exhaust ring is coaxially disposed within the turbine case. The splash plate extends axially along the turbine exhaust ring, radially spaced between the turbine exhaust ring and the turbine case. There are cooling fluid apertures in the turbine case to provide cooling fluid flow from the bypass duct onto the splash plate, and impingement holes in the splash plate to provide impingement flow onto the turbine exhaust ring.

公开(公告)号：DE602007008996D1

公开(公告)日：2010-10-21

申请号：DE602007008996

申请日：2007-07-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANCISCO J ,  ABDEL-MESSEH WILLIAM

IPC: F01D5/18 ,  F01D5/20

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：SG132579A1

公开(公告)日：2007-06-28

申请号：SG2006063390

申请日：2006-09-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANCISCO J ,  DAHMER MATTHEW T

Abstract: A turbine engine component has an airfoil portion with a suction side. The component includes a cooling microcircuit embedded within a wall Structure forming the suction side. The cooling microcircuit has at least one cooling film hole positioned ahead of a gage point for creating a flow of cooling fluid over an exterior surface of the suction side which travels past the gage point. The cooling microcircuit is formed using refractory metal core technology. A method for forming the cooling microcircuit is described.

公开(公告)号：GB2461367A

公开(公告)日：2010-01-06

申请号：GB0908102

申请日：2009-05-11

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SYNDER TIMOTHY S ,  CUNHA FRANCISCO J

IPC: F01D25/12 ,  F01D25/14 ,  F01D25/30 ,  F02K1/82

Abstract: A cooling system for a turbine exhaust assembly 10 comprises an annular case 20, 21, a flow-path ring 12 and a splash plate or baffle 32. The flow-path ring 12 is coaxially disposed within the annular case 20, 21, and the splash plate or baffle 32 extends axially between the annular case 20, 21 and the flow-path ring 12. A plurality of cooling fluid apertures 31 are formed in the annular case 20, 21 in order to provide cooling fluid flow onto the splash plate or baffle 32. A plurality of impingement holes 33 are formed in the splash plate or baffle 32 in order to provide impingement cooling flow onto the flow-path ring 12. The flow-path ring may be provided with film cooling apertures 41 along the aft portion and/or the full axial length thereof. A blocker door 28 may be provided outside of the annular case 20, 21, downstream of the apertures 31, to increase a relative pressure of the cooling fluid flow. The annular case 20, 21 may comprise an inner turbine exhaust case or an outer turbine case.