Gas turbine engine comprising three rotary bodies

A gas turbine engine for propelling an aircraft, including a low pressure rotary body including low pressure turbine rotor blades, an intermediate rotary body including intermediate turbine rotor blades, a high pressure rotary body including high pressure turbine rotor blades, an air flow flowing th...

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Bibliographic Details
Main Authors Chanez Philippe Gérard, M'Bengue Lamine
Format Patent
LanguageEnglish
Published 15.11.2016
Subjects
AIR INTAKES FOR JET-PROPULSION PLANTS
BLASTING
COMBUSTION ENGINES
CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
GAS-TURBINE PLANTS
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
JET-PROPULSION PLANTS
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
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Summary:A gas turbine engine for propelling an aircraft, including a low pressure rotary body including low pressure turbine rotor blades, an intermediate rotary body including intermediate turbine rotor blades, a high pressure rotary body including high pressure turbine rotor blades, an air flow flowing through the engine from upstream to downstream. The at least one intermediate turbine rotor blade is followed directly downstream by a low pressure turbine rotor blade so as to straighten air flow deflected by the intermediate turbine rotor blade.
Bibliography:Application Number: US201214122777