A disclosed gas turbine engine includes a fan including a plurality of fan blades rotatable about an engine axis and core engine disposed within a core nacelle for driving the fan. A bypass passage is defined between the core nacelle and an outer or fan nacelle. A duct mounted within the core nacelle defines a bleed air flow path for directing bleed air from the core engine into the bypass passage. The bleed air duct includes a plurality of airfoils disposed at a defined chord angle for directing bleed airflow into the bypass passage to minimize disruption to bypass airflow.
申请公布号
WO2014051673(A1)
申请公布日期
2014.04.03
申请号
WO2013US29052
申请日期
2013.03.05
申请人
UNITED TECHNOLOGIES CORPORATION
发明人
TURNER, MATTHEW, A.;SALAMON, KEITH, T.;FORD, BARRY, M.