Transmission and method for control of boost spool
A gas turbine engine includes a first spool, a second spool, a third spool, and a epicyclic differential. The epicyclic differential includes a sun gear, planet gears supported from a planet carrier, a ring gear, and a locking member, each housed within an accessory gearbox. The planet carrier couples to the second spool. The sun gear couples to the third spool, and the ring gear couples to engine accessories. A method of operating the gas turbine engine includes supplying a first fuel flow rate to a primary combustor associated with the first and third spools and supplying a second fuel flow rate to a secondary combustor associated with the second spool based on a power lever angle within an intermediate power level range.
1. A method of operating a gas turbine engine having an operational power range that includes an intermediate power range comprising a first power subrange and a second power subrange that is less than a maximum continuous power and greater than a minimum continuous power, the method comprising:
providing the gas turbine engine having a primary combustor rotationally coupled to epicyclic differential and a boost spool having a secondary combustor rotationally coupled to the epicyclic differential wherein the epicyclic differential includes a locking member that is disengaged based on the power lever angle less than the second power subrange and engaged based on the power lever angle greater than the first power subrange;
supplying a first fuel flow rate to the primary combustor of the gas turbine engine contemporaneously with supplying a second fuel flow rate to the secondary combustor of the boost spool based on the power lever angle indicative of the first power subrange of the intermediate power range, wherein: the first fuel rate varies based on the power lever angle; and the second fuel flow rate varies based on a rotational speed of an accessory gearbox including the epicyclic differential; and
engaging the locking member based on a power lever angle greater than the first power subrange.
2. The method of claim 1 , further comprising: engaging the locking member to rotationally couple a planet carrier to a ring gear or sun gear of the epicyclic differential based on the power lever angle greater than the first power subrange, wherein rotationally coupling the planet carrier to the ring gear or the sun gear prevents rotation of the planet carrier relative to the ring gear or the sun gear.
3. The method of claim 2 , further comprising:
supplying a third fuel flow rate to the primary combustor of the gas turbine engine contemporaneously with supplying a fourth fuel flow rate to the secondary combustor of the gas turbine engine based on the power lever angle indicative of the second power subrange of the intermediate power range, wherein:
the third fuel rate varies to maintain a minimum exhaust pressure ratio of the gas turbine engine; and
the fourth fuel flow rate varies based on the power lever angle indicative of the second power subrange of the intermediate power range.
4. The method of claim 3 , further comprising: disengaging a clutch based on the power lever angle greater than the second subrange and less than or equal to the maximum continuous power, wherein disengaging the clutch uncouples a shaft from the accessory gearbox.
5. The method of claim 4 , further comprising:
supplying the first fuel flow rate to the primary combustor of the gas turbine engine contemporaneously with stopping fuel flow to the secondary combustor based on the power lever angle greater than the second subrange and less than or equal to the maximum continuous power, wherein
the first fuel rate varies based on the power lever angle.
6. The method of claim 5 , further comprising: supplying the second fuel flow rate to the secondary combustor contemporaneously with supplying the third fuel flow rate to the primary combustor based on the power lever angle less than the first sub range and greater than or equal to the minimum continuous power, wherein: the second fuel flow rate varies based on a rotational speed of the accessory gearbox; and the third fuel flow rate varies to maintain the minimum exhaust pressure ratio of the gas turbine engine.
7. The method of claim 2 , further comprising:
disengaging the locking member to rotationally uncouple the planet carrier from the ring gear and sun gear of the epicyclic differential based on the power lever angle less than the second power subrange, wherein rotationally uncoupling the planet carrier from the ring gear or the sun gear permits rotation of the planet carrier relative to the ring gear or the sun gear.