TURBINE SHAFT POWER TAKE-OFF

• Main Author: LEFEBVRE, Guy
• Format: Patent
• Language: English; 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

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).