PRESSURE SENSOR ASSEMBLY FOR A TURBINE ENGINE

• Main Authors: FRIEDMAN, Joshua, CLARK, Robert Arthur, BEATTY, Keith F, ROSENZWEIG, Mark, CAMACHO, Jorge, LI, Hejie, JAMES, Kehleyr
• Format: Patent
• Language: English; French; German
• Published: 14.10.2020
• Subjects: AIR INTAKES FOR JET-PROPULSION PLANTS; BLASTING; COMBUSTION APPARATUS; COMBUSTION ENGINES; COMBUSTION PROCESSES; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS; ENGINE PLANTS IN GENERAL; GAS-TURBINE PLANTS; GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS; HEATING; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS; LIGHTING; MACHINES OR ENGINES IN GENERAL; MEASURING; MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER,MECHANICAL EFFICIENCY, OR FLUID PRESSURE; MECHANICAL ENGINEERING; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES; PHYSICS; STEAM ENGINES; TESTING; WEAPONS

A gas turbine engine includes a liner positioned within a compressor section or a turbine section of the gas turbine engine and at least partially defining a core air flowpath through the gas turbine engine. The gas turbine engine also includes a casing at least partially enclosing the liner. Additionally, the gas turbine engine includes a pressure sensor assembly having a body, an extension member, and a pressure sensor. The pressure sensor is positioned at least partially within the body and the body is positioned at least partially on an outer side of the casing, the extension member extending from the body through a casing opening in the casing and towards a liner opening in the liner. The extension member defines a continuous sense cavity exposing the pressure sensor to the core air flowpath.