Thrust recovery in airplanes

Abstract

Several embodiments include a system and method for providing thrust recovery in an aircraft engine. The system and method enables a wider range of safe operation for aircraft where the aircraft engine is rapidly reactivated from a substantially deactivated state. The method thereby reduces noise output and fuel usage during descent and shortens runway lengths and occupancy time required for landing. Thrust recovery is provided via the use of stored bleed air being re-injected back into the aircraft engine. An onboard air storage tank and a system of valves facilitating this method are disclosed.

1 . A method for thrust recovery in a jet engine, comprising:
 storing pressurized gas including at least a portion of a pressurized bleed air from a compressor on the jet engine in at least an onboard tank;   substantially deactivating a combustor of the jet engine during flight; and   operating a valve to feed the pressurized gas from the onboard tank through the jet engine thereby reactivating the combustor.   
     
     
         2 . The method of  claim 1 , wherein said storing the pressurized gas occurs after a cruise phase of flight operation has ended. 
     
     
         3 . The method of  claim 1 , wherein operating the valve includes injecting the pressurized gas into the jet engine at a compressor intake. 
     
     
         4 . The method of  claim 1 , wherein operating the valve includes injecting the pressurized gas into the jet engine at a high-pressure compressor. 
     
     
         5 . The method of  claim 1 , wherein the pressurized gas is entirely the pressurized bleed air. 
     
     
         6 . The method of  claim 1 , further comprising:
 substantially separating one or more non-oxygen components of the pressurized bleed air; and   directing the one or more non-oxygen components of the pressurized bleed air to customer air; and   wherein the portion of the pressurized bleed air is oxygen-rich bleed air and the pressurized gas comprises the oxygen-rich bleed air.   
     
     
         7 . The method of  claim 1 , wherein said operating the valve is responsive to a throttle adjustment for the jet engine. 
     
     
         8 . The method of  claim 1 , further comprising:
 reconnecting the combustor to a turbofan by gradually reducing the feed of the pressurized gas from the onboard tank to ensure maximum spin rates of a combustor turbine while airflow is increased through the turbofan to support sustained operation from ambient air.   
     
     
         9 . The method of  claim 1 , further comprising:
 opening a set of reverse thrust doors on the jet engine during landing of an associated aircraft.   
     
     
         10 . The method of  claim 1 , wherein the onboard tank is a fuel tank. 
     
     
         11 . The method of  claim 1 , wherein the pressurized gas is 275 kPa. 
     
     
         12 . A method for piloting an aircraft during an aborted landing sequence, comprising:
 storing a combustible gas in an onboard tank;   in preparation for landing, substantially deactivating a combustor of a jet engine during flight;   configuring the aircraft for a glided landing; and   operating a valve to feed the combustible gas from the onboard tank through the jet engine thereby reactivating the combustor.   
     
     
         13 . A method for emergency thrust recovery in a jet engine, comprising:
 storing a combustible gas in an onboard tank;   in preparation for landing, substantially deactivating a combustor of the jet engine during flight; and   operating a valve to feed the combustible gas from the onboard tank through the jet engine thereby reactivating the combustor.   
     
     
         14 . The method of  claim 13 , wherein said storing the gas occurs after a cruise phase of flight operation has ended. 
     
     
         15 . The method of  claim 13 , wherein operating the valve includes injecting the combustible gas into the jet engine at a compressor intake. 
     
     
         16 . The method of  claim 13 , wherein operating the valve includes injecting the combustible gas into the jet engine at a high-pressure compressor. 
     
     
         17 . The method of  claim 13 , wherein the stored combustible gas is bleed air, the method further comprising:
 substantially separating one or more non-oxygen components of the bleed air; and   directing the one or more non-oxygen components of the bleed air to customer air; and   wherein the combustible gas fed through the jet engine comprises oxygen-rich bleed air.   
     
     
         18 . The method of  claim 13 , wherein said operating the valve is responsive to a throttle adjustment for the jet engine. 
     
     
         19 . The method of  claim 13 , further comprising:
 reconnecting the combustor to a turbofan by gradually reducing the feed of the gas from the onboard tank to ensure maximum spin rates of a combustor turbine while airflow is increased through the turbofan to support sustained operation from ambient air.   
     
     
         20 . The method of  claim 13 , further comprising:
 opening a set of reverse thrust doors on the jet engine during landing of an associated aircraft.