Gas turbine engine case with integral shroud support ribs

Patent · Tue May 26 04:00:00 EDT 1992

OSTI ID:7238372

Cvelbar, D A; Rubino, A

This patent describes a gas turbine engine case. It comprises an inner circumferential case including an inner case shroud portion at the upstream end; a conical case portion secured to the downstream end of the shroud portion; a support ring at an upstream end of the shroud portion; and an intermediate shroud portion between the support ring and the conical case portion; an outer circumferential case including an outer case shroud portion at the upstream end; a conical outer casing portion secured to the downstream end of the inner case shroud portion; a diffuser formed of downstream extensions of the shroud portion; a plurality of cambered vanes joining the shroud portions axially coextensive with the support ring; characterized by; the thickness of the intermediate shroud portion not exceeding the maximum thickness of the vanes; and integral ribs on the side of each intermediate side of each shroud portion away from the vanes, coincident with the radial extension of the vanes.

• Assignee: United Technologies Corp., Hartford, CT (United States)
• Patent Number(s): US 5115642; A
• Application Number: PPN: US 7-637904
• OSTI ID: 7238372
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
330103* -- Internal Combustion Engines-- Turbine
330603 -- Vehicle Design Factors-- Engine System
COOLING SYSTEMS
DESIGN
ENGINES
GAS TURBINE ENGINES
HEAT ENGINES
INTERNAL COMBUSTION ENGINES
REACTOR COMPONENTS
REACTOR COOLING SYSTEMS
SHROUDS