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
2024-08-21
Patent
Electronic Resource
English
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 |