Gas turbine engine case with integral shroud support ribs
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
- Resource Relation:
- Patent File Date: 7 Jan 1991
- Country of Publication:
- United States
- Language:
- English
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