公开(公告)号：EP3967929A1

公开(公告)日：2022-03-16

申请号：EP21196928.2

申请日：2021-09-15

申请人： Raytheon Technologies Corporation

发明人： JUSTICE, Andrew W ,  BUNCE, Nicholas A ,  SEN, Baris A

IPC分类号： F23R3/14 ,  F23R3/28

摘要： A guide plate (204) for a swirler assembly (200) is disclosed. In various embodiments, the guide plate (204) includes a guide plate flange (224) configured for engagement with a swirler body (202) having a plurality of primary swirler inlets (212); and a first plurality of purge holes (450) extending through the guide plate flange (224) and configured to introduce a first vectored purge flow into the swirler body (202).

公开(公告)号：EP3783262A1

公开(公告)日：2021-02-24

申请号：EP20191789.5

申请日：2020-08-19

申请人： Raytheon Technologies Corporation

发明人： ICHIHASHI, Fumitaka ,  SNYDER, Timothy S ,  LIENAU, Jeffrey J ,  SEN, Baris A

IPC分类号： F23R3/00 ,  F23R3/04 ,  F23R3/10

摘要： A combustor (50) for a gas turbine engine includes an annular shell (52; 54), an annular bulkhead (60) connected to the shell (52; 54), and a heat shield panel (74). The heat shield panel (74) has a first surface (76) facing a combustion chamber (56) and a second surface (78) opposite the first surface (76). The heat shield panel (74) is mounted to the bulkhead (60) and defines a cooling chamber (98) between the bulkhead (60) and the heat shield panel (74). The heat shield panel (74) has a wall extending from the heat shield panel (74) toward the bulkhead (60) around at least a portion of a periphery of the heat shield panel (74). The wall includes a circumferential wall portion including at least one cooling air passage (136; 140) extending between the cooling chamber (98) and a cavity (132; 134) defined between the circumferential wall portion and the shell (52; 54). The at least one cooling air passage (136; 140)is configured to purge the cavity (132; 134) by directing a first cooling air stream (138; 142) from the cooling chamber (98) into the cavity (132; 134).