Intermediate casing for a gas-turbine engine
US8857193B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Jan 19, 2011 |
| Grant date | Oct 14, 2014 |
| Priority date | — |
| Expiry date | Jun 17, 2033 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An intermediate casing for a gas-turbine engine has an outer ring (3), an inner ring (1) and an intermediate ring (2) mutually supported by mutually aligned outer and inner supporting struts (4, 5). A radial drive shaft (6), positioned through inner and outer supporting struts (4.1, 5.1) aligned at a 6-o′ clock position, connects to an auxiliary gear drive (7). Four additional outer supporting struts (5.2, 5.3, 5.4, 5.5) are spaced apart 72°. A mounting bracket connects to the outer ring at a side facing an aircraft fuselage in areas of two of the additional outer supporting struts. The arrangement of supporting struts and type of mounting bracket attachment, saves weight, improves flow in the bypass duct and increase maintenance and installation access at the bottom side of the engine to nearly 144°.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.