INTERNAL HEAT EXCHANGER SYSTEM TO COOL GAS TURBINE ENGINE COMPONENTS

• Main Authors: BINTZ, Matthew E, DIBENEDETTO, Enzo
• Format: Patent
• Language: English; French; German
• Published: 29.06.2022
• 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 high pressure compressor section (152) of a gas turbine engine (20) including: an inner case (114) separating a core flow path (C) of the gas turbine engine and a plenum (144) formed between the inner case and an outer case (112); a bleed port (245) located on an inner surface (114A) of the inner case, the inner surface being proximate the core flow path; an outlet (247) located on an outer surface (114B) of the inner case, the outer surface being proximate the plenum; and a bleed air passageway (200) passing through the inner case to fluidly connect the bleed port to the outlet, wherein the bleed air passageway is fluidly connected to the core flow path through the bleed port and the bleed air passageway is fluidly connected to the plenum through the outlet.