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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Bibliographische Detailangaben
1. Verfasser:	BECKER JR., Thomas Lee
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	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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Beschreibung
Zusammenfassung:	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.