Three-stream gas turbine engine control
A control system and schemes for controlling a three-stream gas turbine engine are disclosed. In one aspect, a three-stream engine is architecturally arranged so as to define a primary bypass flowpath, a secondary bypass flowpath, and a core flowpath that may each output propulsive thrust. The three-stream engine includes one or more effectors that can be controlled to adjust a thrust contribution provided by the secondary bypass flowpath to the net propulsive thrust as well as a thermal contribution provided by the secondary bypass flowpath to an associated thermal management system. Competing demands, limits, and priorities can be considered in controlling the effector. In some embodiments, a secondary effector can be ganged or controlled in conjunction with the effector to assist with adjustment of the contributions provided by the secondary bypass flowpath.
1. A three-stream gas turbine engine for an aircraft, comprising:
a shaft;
a primary fan mechanically coupled with the shaft;
a mid-fan positioned downstream of the primary fan and mechanically coupled with the shaft;
an engine core;
a core cowl surrounding at least a portion of the engine core, a core flowpath being defined between the engine core and the core cowl;
an outer cowl surrounding at least a portion of the core cowl, a secondary bypass flowpath being defined between the core cowl and the outer cowl;
an effector, wherein the effector is an array of inlet guide vanes positioned upstream of the mid-fan;
a thermal management system having one or more heat exchangers disposed in the secondary bypass flowpath; and
one or more processors configured to:
determine an effector demand based on an effector schedule and a thermal demand associated with the thermal management system; and
cause the effector to adjust an airflow through the secondary bypass flowpath based at least in part on the effector demand, wherein causing the effector to adjust the airflow through the secondary bypass flowpath based at least in part on the effector demand includes:
setting the array of inlet guide vanes to a first position in accordance with the effector schedule when the thermal demand is at a first level; and
adjusting the array of inlet guide vanes to a second position when the thermal demand is at a second level that is greater than the first level, the second position being more closed than the first position in order to reduce temperature and mass flow of airflow through the secondary bypass flowpath and increase a rate of thermal exchange between the one or more heat exchangers and the airflow.
2. The three-stream gas turbine engine of claim 1 , further comprising:
a secondary effector positioned along the core flowpath; and
a compressor having one or more stages of compressors rotor blades and compressor stator vanes, wherein at least one stage of compressor stator vanes are variable stator vanes, and
wherein the secondary effector is the variable stator vanes.
3. The three-stream gas turbine engine of claim 1 , further comprising:
a low pressure compressor positioned along the core flowpath downstream of the mid-fan;
a high pressure compressor positioned along the core flowpath downstream of the low pressure compressor; and
a variable bleed valve positioned downstream of the low pressure compressor and upstream of the high pressure compressor, and
wherein a secondary effector is the variable bleed valve, and
wherein in causing the secondary effector to assist with adjustment of the airflow through the secondary bypass flowpath, the one or more processors are configured to:
cause adjustment of a position of the variable bleed valve.
4. The three-stream gas turbine engine of claim 1 , wherein the three-stream gas turbine engine defines a primary fan radius to mid-fan radius ratio as being equal to or greater than 2.0 and less than or equal to 6.5, the primary fan radius to mid-fan radius ratio being defined by a radius spanning between a longitudinal axis defined by the three-stream gas turbine engine and a leading edge tip of one primary fan blade of the primary fan to a radius spanning between the longitudinal axis and a leading edge tip of one mid-fan blade of the mid-fan.
5. The three-stream gas turbine engine of claim 1 , wherein the one or more processors are further configured to:
receive a temperature at the one or more heat exchangers from an associated temperature sensor operable to sense the temperature at the one or more heat exchangers; and
cause the effector to adjust an airflow through the secondary bypass flowpath based at least in part on the temperature at the one or more heat exchangers.
6. The three-stream gas turbine engine of claim 1 , wherein causing the effector to adjust the airflow through the secondary bypass flowpath based at least in part on the effector demand includes: holding a position of the array of inlet guide vanes for a period of time to avoid exceeding a thrust limit.
7. A non-transitory computer readable medium comprising computer-executable instructions, which, when executed by one or more processors associated with a three-stream gas turbine engine having a primary fan and a mid-fan and defining a core flowpath, a primary bypass flowpath, and a secondary bypass flowpath, cause the one or more processors to:
determine an effector demand associated with an effector of the three-stream gas turbine engine based on an effector schedule and a thermal demand associated with a thermal management system having one or more heat exchangers disposed in the secondary bypass flowpath, wherein the effector is an array of inlet guide vanes positioned upstream of the mid-fan; and
cause the effector to adjust an airflow through the secondary bypass flowpath based at least in part on the effector demand, wherein causing the effector to adjust the airflow through the secondary bypass flowpath based at least in part on the effector demand includes:
setting the array of inlet guide vanes to a first position in accordance with the effector schedule when the thermal demand is at a first level; and
adjusting the array of inlet guide vanes to a second position when the thermal demand is at a second level that is greater than the first level, the second position being more closed than the first position in order to reduce temperature and mass flow of airflow through the secondary bypass flowpath and increase a rate of thermal exchange at the thermal management system.
8. An aircraft, comprising:
a three-stream gas turbine engine defining a core flowpath, a primary bypass flowpath, and a secondary bypass flowpath; and
a thermal management system having one or more heat exchangers disposed in the secondary bypass flowpath, the three-stream gas turbine engine comprising:
a shaft;
a primary fan mechanically coupled with the shaft;
a mid-fan positioned downstream of the primary fan and mechanically coupled with the shaft;
an engine core;
a core cowl surrounding at least a portion of the engine core, the core flowpath being defined between the engine core and the core cowl;
an outer cowl surrounding at least a portion of the core cowl, the secondary bypass flowpath being defined between the core cowl and the outer cowl;
an effector, wherein the effector is an array of inlet guide vanes positioned upstream of the mid-fan; and
one or more processors configured to:
determine an effector demand based on an effector schedule and a thermal demand associated with the thermal management system; and
cause the effector to adjust an airflow through the secondary bypass flowpath based at least in part on the effector demand, wherein causing the effector to adjust the airflow through the secondary bypass flowpath based at least in part on the effector demand includes:
setting the array of inlet guide vanes to a first position in accordance with the effector schedule when the thermal demand is at a first level; and
adjusting the array of inlet guide vanes to a second position when the thermal demand is at a second level that is greater than the first level, the second position being more closed than the first position in order to reduce temperature and mass flow of airflow through the secondary bypass flowpath and increase a rate of thermal exchange between the one or more heat exchangers and the airflow.
9. The aircraft of claim 8 , wherein the three-stream gas turbine engine further comprises:
a secondary effector positioned along the core flowpath; and
a compressor having one or more stages of compressors rotor blades and compressor stator vanes, wherein at least one stage of compressor stator vanes are variable stator vanes, and
wherein the secondary effector is the variable stator vanes.