| 摘要 |
A transition ( 200 ) for a gas turbine engine ( 100 ) comprises a transition wall ( 201 ) comprising cooling channels ( 213 L, 213 R, 223 L, 223 R) that are adapted to pass a cooling fluid, such as compressed air from a compressor ( 102 ) during operation of the gas turbine engine ( 100 ) so as to cool combusted hot gases passing through the transition ( 200 ). For each cooling channel ( 213 L, 213 R, 223 L, 223 R), respective entry ports ( 212 L, 212 L, 222 L, 222 R) and exit ports ( 214 L, 214 R, 224 L, 224 R) are arranged so as to obtain a performance improvement based upon pressure differentials between the respective entry and exit ports. In various embodiments, a scoop ( 220 ) is associated with an entry port ( 222 L, 222 R) so as to establish a more elevated pressure differential in the respective cooling channel ( 223 L, 223 R). An entry port ( 330 a-h ) may be positioned offset relative to a lower-positioned exit port ( 340 a-h ) so as to so minimize or eliminate intake of heated airflow from a respective nearby exit port ( 340 a-h ). Such offset positioning may be based on the airflow paths and cooling requirements at selected high-temperature operating conditions.
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