| 摘要 |
In various embodiments, the present invention provides a means for improving gas turbine engine performance by applying fluid flow control to the inter-turbi ne duct (20) joining a high-pressure turbine spool (17) and an associated low-pressu re turbine spool (15), allowing the low-pressure turbine spool (15) to have a relativel y larger diameter than the high-pressure turbine spool (17). One or more unobstructed fluid flow paths (27) between one or more boundary layer suction ports (44) dispos ed within the upstream end (22) of the outer-body surface (32) of the inter- turbine duct (20) and the suction side of the associated low-pressure turbine nozzle (12) are provided. Advantageously, the natural static pressure difference between the se points results in a self aspirating assembly (10). The fluid flow control provided by the respective suction and blowing forces generated allows for a relatively larg er diameter low-pressure turbine spool (15) and/or relatively fewer low-pressure turbine nozzles (12) to be used than is possible with conventional systems, assemblies, and methods. Thus, a gas turbine engine weight savings and optimized performance may be achieved.
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