| 摘要 |
A component of a gas turbine engine (eg., turbine blade) comprises a coolant passage 2 which extends between an entry 6 and an exit 10, the surface roughness 24, 26 and/or the flow cross-section area (note steps 22) of the passage being configured such that, in at least one region along the passage, the heat transfer coefficient between coolant flowing through the passage and the wall of the passage increases in the downstream direction. The surface roughness 24,26 may vary along the length of the passage and/or the flow cross-sectional area may converge in a stepwise 22 manner. The surface roughness may be provided by circumferential ribs. The component may be a turbine blade, nozzle guide vane, or a liner of the turbine annulus, and may be manufactured by a stereo lithographic process. Also note the graph which shows the heat transfer rate 20 increasing downstream along the passage.
|
