HIGH PRESSURE RATIO GAS TURBINE ENGINE

A gas turbine engine (10) comprising:a high pressure turbine (17);a low pressure turbine (19);a high pressure compressor (15) coupled to the high pressure turbine (17) by a high pressure shaft (27);a propulsor (23) and a low pressure compressor (14) coupled to the low pressure turbine (19) via a low...

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Bibliographische Detailangaben
Hauptverfasser:	Bousfield, Ian, Hales, Michael
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 (10) comprising:a high pressure turbine (17);a low pressure turbine (19);a high pressure compressor (15) coupled to the high pressure turbine (17) by a high pressure shaft (27);a propulsor (23) and a low pressure compressor (14) coupled to the low pressure turbine (19) via a low pressure shaft (26) and a reduction gearbox (30); whereinthe low pressure compressor (14) consists of four or five compressor stages (14);the high pressure compressor (15) consists of eight or nine compressor stages;the low pressure turbine (19) comprises four or more stages; andthe high pressure compressor (15) and low pressure compressor (14) together define a core overall pressure ratio of greater than 36:1.