SWITCHING BLEED VALVE FOR A GAS TURBINE ENGINE

• Main Author: DiBENEDETTO, Enzo
• Format: Patent
• Language: English; French; German
• Published: 03.04.2019
• Subjects: AIR INTAKES FOR JET-PROPULSION PLANTS; BLASTING; COMBUSTION ENGINES; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS; ENGINE PLANTS IN GENERAL; GAS-TURBINE PLANTS; HEATING; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS; LIGHTING; MACHINES OR ENGINES IN GENERAL; MECHANICAL ENGINEERING; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES; NON-POSITIVE DISPLACEMENT PUMPS; POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS; STEAM ENGINES; WEAPONS

A gas turbine engine (20) includes a compressor section (24) having multiple stages, a combustor section (26) fluidly connected to the compressor section (24), a turbine section (28) fluidly connected to the combustor section (26), and a bleed structure (200) radially outward of the stages. The bleed structure (200) includes a body structure (214) having a first set of openings (216) radially outward of a first stage and a second set of openings (218) radially outward of a second stage. The bleed structure (200) further includes a circumferential sleeve (214) configured to cover the first set of openings (216) in a first position and configured to cover the second set of openings (218) in a second position. An actuator (230) is coupled to the circumferential sleeve (214) and is configured to articulate the circumferential sleeve (214) between the first and second positions.