초록 ▼

An engine shroud with integral honeycomb panel corners for use in the thrust reverser region of ducted fan gas turbine engines. The integral shroud is useful in a turbine engine having a core engine surrounded by an engine casing and nacelle, with a fan at the inlet directing air flow into the bypas

An engine shroud with integral honeycomb panel corners for use in the thrust reverser region of ducted fan gas turbine engines. The integral shroud is useful in a turbine engine having a core engine surrounded by an engine casing and nacelle, with a fan at the inlet directing air flow into the bypass duct between core engine and engine nacelle. The shroud basically consists of right and left ducts each having an approximately semicircular cross-section with radial flanges extending from the duct edges. The flanges permit the halves to be fastened together to produce a tubular shroud adapted to surround a gas turbine engine and form the inner wall of a bypass duct. The disclosed shroud eliminates the prior complex corner fittings connecting the semicircular center portion of the shroud to the extending flanges and provides simple, integral corners.

대표청구항 ▼

In a gas turbine engine of the type having a core engine, a shroud surrounding the core engine, a tubular outer nacelle defining an annular bypass duct therebetween and a fan disposed in the nacelle inlet for directing compressed gas flow into and through said bypass duct, said shroud formed in two.

In a gas turbine engine of the type having a core engine, a shroud surrounding the core engine, a tubular outer nacelle defining an annular bypass duct therebetween and a fan disposed in the nacelle inlet for directing compressed gas flow into and through said bypass duct, said shroud formed in two. axially divided halves, each having a generally semicircular cross-section center portion with radially extending flanges secured to the axial edges of said center section; the improvement wherein: each shroud half comprises an integral panel having a honeycomb core of substantially uniform thickness and continuous facesheets bonded to both core surfaces, the honeycomb core in corner regions having lower density and greater flexibility than the honeycomb core in the balance of the shroud.