公开(公告)号：EP3862539A1

公开(公告)日：2021-08-11

申请号：EP21155059.5

申请日：2021-02-03

申请人： Raytheon Technologies Corporation

发明人： TU, John S. ,  NEWMAN, Robert ,  SANCHEZ, Paul K. ,  LIENAU, Jeffrey J. ,  OLS, John T. ,  MANOHARAN, Prabaharan ,  SAMBARAPU, Venu ,  ALLABANDA, Rajendra Prasad Uppara

IPC分类号： F01D9/06 ,  F01D25/12 ,  F01D25/14 ,  F01D25/26 ,  F02C7/18

摘要： Flow diverters (318; 400; 902) for installation in mid-turbine frame systems (304; 910) at a conduit outlet (314) of gas turbine engines are described. The flow diverters include a diverter body (406) having a connector portion (408; 912) defining a diverter inlet (402; 916), a diverter extension (410; 920) at least partially defining a diverter outlet (404; 918), and a curved portion (418; 922) arranged between the connector portion (408; 912) and the diverter extension (410; 920), the curved portion configured to change a direction of flow from a first direction to a second direction that is about 90° from the first direction as the flow passes from the diverter inlet (402; 916) to the diverter outlet (404; 918).

公开(公告)号：EP3854995A1

公开(公告)日：2021-07-28

申请号：EP21153834.3

申请日：2021-01-27

申请人： Raytheon Technologies Corporation

发明人： LIENAU, Jeffrey J. ,  NEWMAN, Robert ,  CHUONG, Conway ,  KOPP-VAUGHAN, Kristin ,  MATHIYALAGAN, Senthil Prasad ,  NELANTI, Krishna ,  UPPARA ALLABANDA, Rajendra Prasad

IPC分类号： F01D11/00 ,  F01D25/24 ,  F02C7/28

摘要： An air seal assembly (76) for a gas turbine includes a flow path platform (66). The air seal assembly (76) further includes a casing (60) disposed radially outside the flow path platform (66). The air seal assembly (76) further includes an annular finger seal (74) mounted to the casing (60) and disposed between the flow path platform (66) and the casing (60). The annular finger seal (74) includes a first circumferential portion (80) mounted to the casing (60), a second circumferential portion (86) extending from the first circumferential portion (80), and a third circumferential portion (88) extending from the second circumferential portion (86) and contacting an outer surface (90) of the flow path platform (66). The third circumferential portion (88) includes a plurality of air cooling holes (98) configured to direct a cooling air stream (100) onto the flow path platform (66).

公开(公告)号：EP3851744A1

公开(公告)日：2021-07-21

申请号：EP21152121.6

申请日：2021-01-18

申请人： Raytheon Technologies Corporation

发明人： ICHIHASHI, Fumitaka ,  LIENAU, Jeffrey J.

IPC分类号： F23R3/00 ,  F23R3/06

摘要： A combustor for a gas turbine engine includes a combustion chamber defined between an inner shell and an outer shell. The combustor further includes a bulkhead extending between the inner shell and the outer shell. The combustor further includes a liner panel mounted to one of the inner shell and the outer shell aft of the bulkhead. The liner panel includes a first section including a first plurality of effusion holes. A first portion of the first plurality of effusion holes extends in a substantially circumferential direction. A second portion of the first plurality of effusion holes, disposed forward of the first portion, transitions from the substantially circumferential direction toward a substantially forward direction. A third portion of the first plurality of effusion holes, disposed aft of the first portion, transitions from the substantially circumferential direction to a substantially aft direction.