US 11,808,216 B1
Air-provisioning system with ejectors
Paul K. Johnson, Ft. Wayne, IN (US); Andrew J. Eifert, Indianapolis, IN (US); Richard Peace, London (GB); Richard Young, London (GB); and Robert T. Duge, Indianapolis, IN (US)
Assigned to Rolls-Royce North American Technologies Inc., Indianapolis, IN (US); Rolls-Royce Corporation, Indianapolis, IN (US); and Rolls-Royce plc
Filed by Rolls-Royce North American Technologies Inc., Indianapolis, IN (US); Rolls-Royce Corporation, Indianapolis, IN (US); and Rolls-Royce plc, London (GB)
Filed on Jun. 10, 2022, as Appl. No. 17/837,749.
Int. Cl. F02C 9/18 (2006.01); F02C 6/08 (2006.01)
CPC F02C 9/18 (2013.01) [F02C 6/08 (2013.01); F05D 2220/323 (2013.01); F05D 2260/605 (2013.01); F05D 2260/606 (2013.01); F05D 2270/3061 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A propulsion system, comprising
a first gas turbine engine including a first propulsive fan, a first engine core including a first compressor, a first combustor, and a first turbine configured to drive the first propulsive fan, and a first bypass duct surrounding the first engine core,
a second gas turbine engine including a second propulsive fan, a second engine core including a second compressor, a second combustor, and a second turbine configured to drive the second propulsive fan, and a second bypass duct surrounding the second engine core, and
an air-provisioning system including a first ejector, a second ejector, a plenum that is fluidically connected with the first ejector and the second ejector, and a first propulsor, the air-provisioning system configured to bleed and mix air from the first gas turbine engine and the second gas turbine engine to provide selectively a flow of plenum air from the plenum to the first propulsor at a desired pressure and a desired flow rate to power the first propulsor,
wherein the first ejector is fluidically connected to the first compressor and the first bypass duct of the first gas turbine engine such that first compressor bleed air from the first compressor and first bypass bleed air from the first bypass duct is conducted to the first ejector and the first ejector outputs a first mixed bleed air to the plenum having a pressure that is higher than a pressure of the first bypass bleed air,
wherein the second ejector is fluidically connected to the second compressor and the second bypass duct of the second gas turbine engine such that second compressor bleed air from the second compressor and second bypass bleed air from the second bypass duct is conducted to the second ejector and the second ejector outputs a second mixed bleed air to the plenum having a pressure higher than a pressure of the second bypass bleed air, and
wherein the first mixed bleed air and the second mixed bleed air are combined in the plenum to provide the plenum air having the desired pressure and the desired flow rate, and the plenum is configured to conduct selectively the flow of plenum air to the first propulsor at the desired flow rate and the desired pressure to drive rotation of the first propulsor.