| 发明名称 |
COMBUSTOR ASSEMBLY FOR A GAS TURBINE ENGINE |
| 摘要 |
A combustor assembly for a gas turbine engine includes a hanger and a combustor liner fixed to the hanger such as, for example, by an annular weld joint. The combustor liner has an inner surface extending along an axis and is operable to define either a radial outer boundary or a radial inner boundary of the combustion chamber. The combustor assembly also includes a heat shield at least partially overlapping and confronting the inner surface of the combustor liner along the axis, with the heat shield releasably engaged with the hanger. |
| 申请公布号 |
US2014311153(A1) |
申请公布日期 |
2014.10.23 |
| 申请号 |
US201314102929 |
申请日期 |
2013.12.11 |
| 申请人 |
Rolls-Royce Corporation ;Rolls-Royce North America Technologies, Inc. |
发明人 |
Smallwood Michel S.;Wigal Mindi D. |
| 分类号 |
F23R3/00 |
主分类号 |
F23R3/00 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A combustor assembly for a gas turbine engine, comprising:
a hanger; a combustor liner fixed to said hanger at an attachment location, said combustor liner having an inner surface extending along an axis and operable to define one of a radial outer boundary and a radial inner boundary of a combustion chamber; and a heat shield at least partially overlapping and confronting said inner surface of said combustor liner along said axis, said heat shield releasably engaged with said hanger. |
| 地址 |
Indianapolis IN US |
