TURBINE SHAFT POWER TAKE-OFF

A multi-spool gas turbine engine (10) comprises a low pressure (LP) spool (20) and a high pressure (HP) spool (40) independently rotatable of one another about an engine axis (17). The LP spool (20) comprises an LP turbine (21), an LP compressor (22) and an LP shaft (23). The HP pressure spool (40)...

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Bibliographic Details
Main Author LEFEBVRE, Guy
Format Patent
LanguageEnglish
French
German
Published 24.01.2018
Subjects
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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Summary:A multi-spool gas turbine engine (10) comprises a low pressure (LP) spool (20) and a high pressure (HP) spool (40) independently rotatable of one another about an engine axis (17). The LP spool (20) comprises an LP turbine (21), an LP compressor (22) and an LP shaft (23). The HP pressure spool (40) comprises an HP turbine (41), an HP compressor (42) and an HP shaft (43). The LP shaft (23) has an upstream shaft portion (23b) extending upstream of the LP turbine (21) to a location upstream of the LP compressor (22) to provide a first power take-off at an upstream end (E 2 ) of the engine (10) and a downstream shaft portion (23a) extending downstream of the LP turbine (21) to provide a second power take-off at a downstream end (E 1 ) of the engine (10).
Bibliography:Application Number: EP20170182096