Thrust augmentation via partial core exhaust reheat

An aircraft engine, comprising:

• a fan;
• an engine core downstream of the fan;
• a bypass airflow duct downstream of the fan and positioned externally of the engine core, wherein the fan accelerates airflow through the bypass airflow duct to produce a first thrust;
• a core airflow duct downstream of the fan and extending through the engine core, the core airflow duct including a core combustion chamber, wherein airflow through the core airflow duct is combusted within the core combustion chamber to produce a second thrust;
• an augmented thrust airflow duct in communication with the core airflow duct, the augmented thrust airflow duct including an augmenter combustion chamber, wherein airflow diverted from the core airflow duct through the augmented thrust airflow duct is combusted within the augmenter combustion chamber to produce an augmented thrust;
• a variable exhaust nozzle (VEN) movable to at least a first position, wherein the VEN is closed a first amount, and a second position, wherein the VEN is closed a second amount greater than the first amount, the VEN configured to divert airflow from the core airflow duct to the augmented thrust airflow duct in each of the first position and the second position, the first position of the VEN corresponding to a first amount of diverted airflow and the second position of the VEN corresponding to a second amount of diverted airflow greater than the first amount of diverted airflow;
• and
• a controller configured to control an amount of fuel supplied to the augmenter combustion chamber based on the position of the VEN such that, in the first position of the VEN, a first amount of fuel corresponding to the first amount of airflow is supplied to the augmenter combustion chamber and such that, in the second position of the VEN, a second amount of fuel corresponding to the second amount of airflow is supplied to the augmenter combustion chamber, the second amount of fuel greater than the first amount of fuel.

An aircraft engine, comprising:

• a fan;
• an engine core downstream of the fan;
• a bypass airflow duct downstream of the fan and positioned externally of the engine core, wherein the fan accelerates airflow through the bypass airflow duct to produce a first thrust;
• a core airflow duct downstream of the fan and extending through the engine core, the core airflow duct including a core combustion chamber, wherein airflow through the core airflow duct is combusted within the core combustion chamber to produce a second thrust;
• an augmented thrust airflow duct in communication with the core airflow duct, the augmented thrust airflow duct including an augmenter combustion chamber, wherein airflow diverted from the core airflow duct through the augmented thrust airflow duct is combusted within the augmenter combustion chamber to produce an augmented thrust;
• a door movable to at least a first position, wherein the door is open a first amount, and a second position, wherein the door is open a second amount greater than the first amount, the door configured to divert airflow from the core airflow duct to the augmented thrust airflow duct in each of the first position and the second position, the first position of the door corresponding to a first amount of diverted airflow and the second position of the door corresponding to a second amount of diverted airflow greater than the first amount of diverted airflow;
• and
• a controller configured to control an amount of fuel supplied to the augmenter combustion chamber based on the position of the door such that, in the first position of the door, a first amount of fuel corresponding to the first amount of airflow is supplied to the augmenter combustion chamber and such that, in the second position of the door, a second amount of fuel corresponding to the second amount of airflow is supplied to the augmenter combustion chamber, the second amount of fuel greater than the first amount of fuel.