GAS TURBINE ENGINE WITH INTERCOOLED COOLING AIR AND CONTROLLED BOOST COMPRESSOR

A gas turbine engine (100) comprises a compressor section having a downstream most end (113) and a cooling air tap (120) at a location spaced upstream from the downstream most end (113). The cooling air tap (120) is passed through at least one boost compressor (118) and at least one heat exchanger (...

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Bibliographische Detailangaben
Hauptverfasser:	SNAPE, Nathan, STAUBACH, Joseph Brent
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 GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine engine (100) comprises a compressor section having a downstream most end (113) and a cooling air tap (120) at a location spaced upstream from the downstream most end (113). The cooling air tap (120) is passed through at least one boost compressor (118) and at least one heat exchanger (124, 130), and then passed to a turbine section to cool the turbine section, the boost compressor (118) being controlled to provide a desired pressure to the turbine section.