SYSTEMS FOR STIFFENING CASES ON GAS-TURBINE ENGINES

An engine case (200) may include a first half (202) and a second half (206). The first half (202) may have a semiannular geometry with a first flange (204) located at a circumferential edge of the first half (202). The second half (206) may also have a semiannular geometry. The second half (206) may...

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Bibliographic Details
Main Author WEBB, Scot A
Format Patent
LanguageEnglish
French
German
Published 01.01.2020
Subjects
AIRCRAFT
ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT
AVIATION
BLASTING
COSMONAUTICS
ENGINE PLANTS IN GENERAL
EQUIPMENT FOR FITTING IN OR TO AIRCRAFT
FLYING SUITS
HEATING
LIGHTING
MACHINES OR ENGINES IN GENERAL
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES
PARACHUTES
PERFORMING OPERATIONS
STEAM ENGINES
TRANSPORTING
WEAPONS
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Summary:An engine case (200) may include a first half (202) and a second half (206). The first half (202) may have a semiannular geometry with a first flange (204) located at a circumferential edge of the first half (202). The second half (206) may also have a semiannular geometry. The second half (206) may further include a flange (208) located at a circumferential edge of the first half (202). The second flange (208) may be aligned with the first flange (204) and mechanically coupled to the first flange (204). The first flange (204) and the second flange (208) may be configured to substantially align with an engine mounting point (212). The engine case (200) may also have an annular geometry.
Bibliography:Application Number: EP20170157479