公开(公告)号：SG122040A1

公开(公告)日：2006-05-26

申请号：SG200508439

申请日：2005-10-27

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANK J ,  TELLER BRET ,  CHON YOUNG ,  MONGILLO DOMINIC ,  PIETRASZKIEWICZ EDWARD F

Abstract: An airfoil (34), and in a disclosed embodiment a rotor blade, has a serpentine cooling path. To best account for the Coriolis effect, the paths of the serpentine cooling channel have trapezoidal cross-sections. An area of the rotor blade between a smaller side (43) of the trapezoidal-shaped paths, and a facing wall (46) of the rotor blade has high thermal and mechanical stresses, and is a challenge to adequately cool. A microcircuit (50), which is a very thin cooling circuit having crossing pedestals (112), is embedded into the blade in this area. The microcircuit provides additional cooling, and addresses the challenges with regard to cooling these areas.

公开(公告)号：PL367008A1

公开(公告)日：2004-10-18

申请号：PL36700804

申请日：2004-04-06

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANK J ,  DAHMER MATTHEW T

IPC: B22C9/10 ,  F01D5/18 ,  B23P15/04 ,  F02C7/00 ,  F01D5/00

Abstract: A turbine element airfoil (22) has a cooling passageway network with a slot extending from a trailing passageway toward the trailing edge (32). A number of discrete posts arranged in rows (130-146) span the slot between pressure and suction sidewall portions.

公开(公告)号：CA2463390A1

公开(公告)日：2004-10-08

申请号：CA2463390

申请日：2004-04-02

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DAHMER MATTHEW T ,  CUNHA FRANK J

IPC: B23P15/04 ,  B22C9/10 ,  F01D5/18 ,  F02C7/00

Abstract: A turbine element airfoil has a cooling passageway network with a slot extending from a trailing passageway toward the trailing edge. A number of discrete posts span the slot between pressure and suction sidewall portions.

公开(公告)号：SG136063A1

公开(公告)日：2007-10-29

申请号：SG2007017270

申请日：2007-03-08

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ABDEL-MESSEH WILLIAM ,  CUNHA FRANK J

Abstract: 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 form a region in which turbulence is created. The apex portion is oriented at an angle with respect to the first direction.

公开(公告)号：SG127789A1

公开(公告)日：2006-12-29

申请号：SG200601656

申请日：2006-03-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANK J ,  COUCH ERIC ,  SANTELER KEITH A ,  GAYMAN SCOTT W ,  HUDSON ERIC A ,  JOE CHRISTOPHER ,  LETIZIA ERIC

Abstract: An airfoil assembly includes an airfoil extending away from a platform. One or more cooling circuits are formed through the platform in order to provide cooling of the platform. The cooling circuit may include a downwardly directed inlet receiving cooling air from below the platform. The cooling air is then directed in a direction generally parallel to the outer surface of the platform and through exits formed through the outer surface of the platform. The cooling circuit may optionally include a plurality of pedestals extending from an outer wall to an inner wall of the cooling circuit to increase the rigidity and the cooling function of the cooling circuit.

公开(公告)号：SG122911A1

公开(公告)日：2006-06-29

申请号：SG200507274

申请日：2005-11-22

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANK J ,  PIETRASZKIEWICZ EDWARD F ,  KONTROVITZ DAVID M ,  LEVINE JEFFREY R ,  CHON YOUNG ,  MONGILLO DOMINIC ,  TELLER BRET

Abstract: An airfoil (59), and in a disclosed embodiment a rotor blade, has film cooling holes (48) formed at a leading edge (41). A supplemental film cooling channel (60) is positioned near the leading edge (41), but spaced toward the trailing edge from the leading edge. The supplemental film cooling channel (60) directs film cooling air onto a suction wall (38). The supplemental film cooling channel air is generally directed to a location on the suction wall (38) that has raised some challenges in the past. In a disclosed embodiment, the airfoil is provided with a thermal barrier coating, and the supplemental film cooling air protects this thermal barrier coating.

公开(公告)号：PL367009A1

公开(公告)日：2004-10-18

申请号：PL36700904

申请日：2004-04-06

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANK J ,  PALUMBO MICHAEL A

IPC: F01D5/18 ,  F02C7/12

Abstract: An improved cooling design and method for cooling airfoils within a gas turbine engine is provided includes a plenum (80) longitudinally located within the leading edge (46) of the airfoils. Within the plenum (80) are positioned a plurality of turbulence promoters (86) to provide enhanced heat transfer within the leading edge. Also, the cooling design includes a plurality of inlets (72,76) to receive cooling air from an internal cavity (36) of the airfoil as well as a plurality of outlets (64,66) located within a trench (52) on the exterior surface of the leading edge (46) through which the cooling air exits to film cool the leading edge.

公开(公告)号：PL364838A1

公开(公告)日：2004-08-09

申请号：PL36483804

申请日：2004-02-05

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANK J ,  DUBE BRYAN P

IPC: F01D5/18 ,  F01D5/08 ,  F01D5/30 ,  F02C7/18 ,  F01D5/02

Abstract: An improved cooling design and method for cooling airfoils within a gas turbine engine is provided which includes an embedded microcircuit that traverses a tip (36) between a suction sidewall (44) and a pressure sidewall (42) of the airfoil (54). The microcircuit includes at least one inlet (70) disposed proximate to the tip (36) and one of the sidewalls (44) for receiving cooling air from an internal cooling cavity of the airfoil and at least outlet (72) disposed proximate to the tip (36) through which the cooling air ejects into a region outside the airfoil.

公开(公告)号：DE602005020229D1

公开(公告)日：2010-05-12

申请号：DE602005020229

申请日：2005-10-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANK J ,  ALBERT JASON E ,  PIETRASZKIEWICZ EDWARD F

IPC: F01D5/18 ,  F01D5/08 ,  F01D5/14

Abstract: A gas turbine engine blade (11) has a relatively large fillet (18) to improve the characteristics of the air flow thereover. The fillet (18) has a thin wall which, together with an impingement rib (35), defines a fillet cavity (24) therebetween, and cooling air is provided to flow through impingement holes (26) in the impingement rib (3 5) and impinge on the rear surface (27) of the fillet (18). The impingement holes (26) are elongated in cross sectional shape with their elongations being oriented in a direction generally transverse to a radial direction.

公开(公告)号：DE602007005411D1

公开(公告)日：2010-05-06

申请号：DE602007005411

申请日：2007-03-26

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ABDEL-MESSEH WILLIAM ,  CUNHA FRANK J

IPC: F01D5/18

Abstract: A passageway (102) is provided through which a cooling fluid flows in a first direction (104). The passageway (102) has a plurality of trip strips (106) positioned within the passageway (102). Adjacent one of the trip strips (106) are oriented to converge towards each other at a first end to form an apex portion (108) and to form a region (112) in which turbulence is created. The apex portion (108) is oriented at an angle with respect to the first direction (104).