| 摘要 |
<P>PROBLEM TO BE SOLVED: To provide an inlet diffuser of a gas turbine combustor of small volume and low pressure loss, capable of stably splitting a flow rate. Ž<P>SOLUTION: This inlet diffuser comprises a flow contracting section 14 in which a flow channel area from an inlet 11 of the airflow 1 to a throat section 13 is gradually reduced, a splitter 14 for dividing the airflow of the throat section into a plurality of flow channels 15a, 15b, and a plurality of flow expanding sections 16 for gradually increasing the flow channel area from the plurality of flow channels to the combustor 2 at a downstream side. An spread angle of the flow expanding section 16 is set to an angle free from generation of swirl. Ž<P>COPYRIGHT: (C)2010,JPO&INPIT Ž
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