There is provided a blower system 400 for a gas turbine engine 10. The blower system 400 comprises: a rotor assembly 420, an airframe port 452 and a routing-control valve 46. The rotor assembly 420 is configured to be mechanically coupled to a spool 440 of the gas turbine engine 10. The airframe port 452 is configured to receive and discharge air to an airframe system 450. The routing-control valve 46 comprises: a primary channel 460 for bidirectional flow between the rotor assembly 420 and the airframe port 452; a primary valve member 480 configured to open and close the primary channel 460; and an auxiliary channel 461 branched from the primary channel 460. The auxiliary channel 461, 462 is configured to bypass the primary valve member 480 for: a first auxiliary flow from the airframe port 452 to the rotor assembly 420; or a second auxiliary flow for purging air from the rotor assembly 420 to a discharge port 422. The blower system 400 is configured to operate in an engine drive mode in which air received from the airframe port 452 drives a rotor 410 of the rotor assembly 420 to rotate the spool 440, and in a blower mode in which the spool 440 drives the rotor 410 to discharge air to the airframe port 452.
BLOWER SYSTEM
GEBLÄSESYSTEM
SYSTÈME DE SOUFFLANTE
21.08.2024
Patent
Elektronische Ressource
Englisch
IPC: | F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F04D Strömungsarbeitsmaschinen , NON-POSITIVE-DISPLACEMENT PUMPS |