Integrated engine shroud for gas turbine engines

Patent · Tue Jan 28 00:00:00 EST 1992

OSTI ID:5327528

Layland, M J

This patent describes improvement 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 the bypass duct, the shroud formed in two axially divided halves, each having a generally C shaped center cross section with radially extending flanges secured to the axial edges of the center section. The improvement comprises: each shroud comprises an integral panel having a honeycomb core and continuous facesheets bonded to both surfaces, wherein corner regions between the center section and the flanges are comprised of a honeycomb core having a higher density than the honeycomb core in the center section and flanges.

• Assignee: Rohr Industries, Inc., Chula Vista, CA (United States)
• Patent Number(s): US 5083426; A
• Application Number: PPN: US 7-415788
• OSTI ID: 5327528
• Resource Relation: Patent File Date: 2 Oct 1989
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
GAS TURBINE ENGINES
SHROUDS
ANNULAR SPACE
COMPRESSIBLE FLOW
DUCTS
GAS FLOW
HONEYCOMB STRUCTURES
CONFIGURATION
COOLING SYSTEMS
ENGINES
FLUID FLOW
HEAT ENGINES
INTERNAL COMBUSTION ENGINES
MECHANICAL STRUCTURES
REACTOR COMPONENTS
REACTOR COOLING SYSTEMS
SPACE
330103* - Internal Combustion Engines- Turbine