BLEED HOLE FLOW DISCOURAGER

• Main Author: GRIFFIN, David R
• Format: Patent
• Language: English; French; German
• Published: 31.01.2024
• 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 (92), a turbine section (28) and an intermediate combustor (56). The compressor section (92) has a plurality of rotating compressor blades (101, 103) rotating about an axis of rotation, and static stator vanes (100) positioned axially intermediate the rotating compressor blades (101, 103). There are a plurality of bleed holes (118) extending through a compressor outer housing (111) positioned radially outwardly of the rotating compressor blades (101, 103), and allowing air compressed by the compressor blades (101, 103) to move into a bleed chamber (90). There is a bleed chamber outer housing (108) positioned radially outwardly of the compressor outer housing (111), and defining the bleed chamber (90) in part in combination with the compressor outer housing (111). A flow discourager (116) is positioned radially intermediate the bleed holes (118) and the bleed outer housing (108), such that air leaving the bleed hole (118) impacts upon the flow discourager (116) before reaching the bleed chamber outer housing (108).