COMBUSTOR TO VANE SEALING ASSEMBLY AND METHOD OF FORMING SAME

    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

    IPC分类号: F01D9/02 F01D11/00

    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).

    COMBUSTOR TO VANE SEALING ASSEMBLY AND METHOD OF FORMING SAME

    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

    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).