GAS TURBINE ENGINE

A gas turbine engine, and arrangements of turbine blades around an exhaust nozzle of an engine core. Example embodiments include a gas turbine engine for an aircraft comprising: an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor, the engine c...

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Bibliographische Detailangaben
1. Verfasser:	HARVEY, Giles E
Format:	Patent
Sprache:	eng
Schlagworte:	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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Beschreibung
Zusammenfassung:	A gas turbine engine, and arrangements of turbine blades around an exhaust nozzle of an engine core. Example embodiments include a gas turbine engine for an aircraft comprising: an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor, the engine core comprising an inlet upstream of the compressor and an exhaust nozzle at a downstream outlet of the turbine; a fan located upstream of the engine core inlet; and a set of exhaust nozzle vanes spanning the exhaust nozzle, the turbine comprising a first row of turbine blades upstream of the exhaust nozzle vanes and a second row of turbine blades downstream of the exhaust nozzle guide vanes, one or more of the exhaust nozzle guide vanes comprising a passage configured to direct airflow downstream from the first row of turbine blades towards the second row of turbine blades.