SYSTEMS AND METHODS FOR STIFFENING CASES ON GAS-TURBINE ENGINES

An engine case may include a first half and a second half. The first half may have a semiannular geometry with a first flange located at a circumferential edge of the first half. The second half may also have a semiannular geometry. The second half may further include a flange located at a circumfer...

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Bibliographic Details
Main Author Webb Scot A
Format Patent
LanguageEnglish
Published 24.08.2017
Subjects
AIR INTAKES FOR JET-PROPULSION PLANTS
AIRCRAFT
ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT
AVIATION
BLASTING
COMBUSTION ENGINES
CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
COSMONAUTICS
EQUIPMENT FOR FITTING IN OR TO AIRCRAFT
FLYING SUITS
GAS-TURBINE PLANTS
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
LIGHTING
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT PUMPS
PARACHUTES
PERFORMING OPERATIONS
POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS
PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
TRANSPORTING
WEAPONS
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Summary:An engine case may include a first half and a second half. The first half may have a semiannular geometry with a first flange located at a circumferential edge of the first half. The second half may also have a semiannular geometry. The second half may further include a flange located at a circumferential edge of the first half. The second flange may be aligned with the first flange and mechanically coupled to the first flange. The first flange and the second flange may be configured to substantially align with an engine mounting point. The engine case may also have an annular geometry.
Bibliography:Application Number: US201615051377