| 摘要 |
<p>A gas turbine (400) includes a liner (410, 820, 920, 1020, 1120), a casing (810 ,910,1010,1110) surrounding the liner, a hula seal (420) flexibly connected to an aft end of the liner (445) and a liner aft support mechanism (440). The liner is configured to receive compressed gas and fuel at an upstream end, the mixture of the compressed gas and the fuel being burned in a combustion core area of the liner to yield hot exhaust gasses. The liner aft end support mechanism is located downstream from an area (513) where a highest temperature on an outer surface of the liner is attained, and upstream to a portion (516) where the hula seal is connected to the liner, and is configured to movably support the liner inside the casing. The liner aft end support mechanism (440) includes at least three individual support elements (800, 900, 1000, 1100,1200) configured to allow a part of the individual support elements to move in the flow direction relative to at least one of the liner or the casing.</p> |
