GAS TURBINE ENGINE HAVING AN AIR BLEED SYSTEM

A gas turbine engine is provided having a compressor section, a combustion section located downstream of the compressor section, and a turbine section located downstream of the combustion section. A structural member (94) extends from the compressor section to the turbine section for strengthening o...

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Bibliographic Details
Main Author BECKER JR., Thomas Lee
Format Patent
LanguageEnglish
French
German
Published 22.02.2017
Subjects
AIR INTAKES FOR JET-PROPULSION PLANTS
BLASTING
COMBUSTION ENGINES
CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
ENGINE PLANTS IN GENERAL
GAS-TURBINE PLANTS
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
LIGHTING
MACHINES OR ENGINES IN GENERAL
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES
STEAM ENGINES
WEAPONS
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Summary:A gas turbine engine is provided having a compressor section, a combustion section located downstream of the compressor section, and a turbine section located downstream of the combustion section. A structural member (94) extends from the compressor section to the turbine section for strengthening one or more components of the gas turbine engine. The structural member (94) also defines a flowpath (96) extending between an inlet in airflow communication with the compressor section and an outlet in airflow communication with the turbine section. The flowpath (96) is configured to provide bleed air from the compressor section to the turbine section to capture at least a portion of the energy in such bleed air.
Bibliography:Application Number: EP20160184516