-
公开(公告)号:EP3851642A1
公开(公告)日:2021-07-21
申请号:EP21152146.3
申请日:2021-01-18
摘要: A gas turbine engine (10) includes a turbine section (18) including a first vane stage (74). The gas turbine engine (10) further includes a combustor (50) disposed forward of the first vane stage (74). The combustor (50) includes a combustion chamber (56) in fluid communication with the first vane stage (74). The combustion chamber (56) is radially defined between a first shell (52) and a second shell (54). The first shell (52) includes a first seal assembly (88) at an aft end (60) of the first shell (52). The first seal assembly (88) includes a conformal seal (90) forming a first seal between the first shell (52) and a forward face (78) of the first vane stage (74). The second shell (52) includes a second seal assembly (104) at an aft end (68) of the second shell (54). The second seal assembly (104) includes a brush seal (110) forming a second seal between the second shell (54) and the forward face (82) of the first vane stage (74).
-
公开(公告)号:EP3865668A1
公开(公告)日:2021-08-18
申请号:EP21157203.7
申请日:2021-02-15
IPC分类号: F01D9/02 , F01D11/00 , F16J15/3288 , F01D9/04
摘要: A brush seal system includes a component including a first mating surface (136). The brush seal system further includes a brush seal (110) including a brush seal backing plate (112), a retaining ring (114), and a plurality of bristles (116) retained between the brush seal backing plate (112) and the retaining ring (114). The brush seal backing plate (112) includes a second mating surface (138) mounted to the first mating surface (136). The brush seal system further includes at least one cooling channel (128) extending from an exterior side (130) of the component to an interior side (132) of the component so as to bypass the brush seal (110).
-
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
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
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).
-
-