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：AU2005201194A1

公开(公告)日：2005-11-24

申请号：AU2005201194

申请日：2005-03-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MONGILLO DOMINIC ,  MERCADANTE RUTHANN ,  GREGG SHAWN

IPC: F01D20060101 ,  F01D5/00 ,  F01D5/12 ,  F01D5/14 ,  F01D5/18 ,  F01D9/02 ,  F01D25/12 ,  F02C7/00 ,  F02C7/16

Abstract: A hollow airfoil (22) comprises a leading edge wall portion (42), a plurality of cavities (48,50,52), one or more crossover ribs (46), a plurality of cooling apertures (54), and a plurality of impingement apertures (56). The cavities are disposed adjacent the leading edge wall portion (42), between the leading edge wall portion (42) and a first rib (44). The crossover ribs (46) extend between the leading edge wall portion (42) and the first rib (44), and at least one crossover rib (46) is disposed between a pair of the cavities (48,50,52). The cooling apertures (54) are disposed in the leading edge wall portion (42), providing a passage through which cooling air can exit the cavities. The impingement apertures (56) are disposed in the first rib (44), providing a passage through which cooling air can enter the cavities. At least one of the impingement apertures (56) is contiguous with one of the crossover ribs (46).

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.