Engine with rotating detonation combustion system
A Brayton cycle engine and method for operation. The engine includes an inner wall assembly and an upstream wall assembly each extended from a longitudinal wall into a gas flowpath. An actuator adjusts a depth of the detonation combustion region into the gas flowpath between the inner wall assembly and the upstream wall assembly. The engine flows an oxidizer through the gas flowpath and the inner wall captures a portion of the oxidizer. The engine further adjusts the captured flow of oxidizer via the upstream wall and flows a first flow of fuel to the captured flow of oxidizer to produce rotating detonation gases. The engine flows the detonation gases downstream and to mix with the flow of oxidizer, and flows and burns a second flow of fuel to the detonation gases/oxidizer mixture to produce thrust.
1. A method for operating an engine, the engine comprising (a) a longitudinal wall extended along a lengthwise direction, wherein the longitudinal wall defines a gas flowpath of the engine and a combustion section, the gas flowpath having a depth perpendicular to the longitudinal wall, (b) an inner wall assembly extendable from the longitudinal wall into the gas flowpath, wherein the inner wall assembly includes a concave upstream face that defines a rotating detonation combustion region at an upstream side of the inner wall assembly and adjacent to the longitudinal wall, and (c) an upstream wall assembly coupled to the longitudinal wall upstream of the inner wall assembly, wherein an actuator is coupled to the upstream wall assembly and is configured to actuate the upstream wall assembly to extend the upstream wall assembly into the gas flowpath a depth, the method comprising:
flowing an oxidizer through the gas flowpath into the combustion section, wherein the flow of oxidizer includes a first portion and a second portion;
capturing the first portion of the flow of oxidizer at the rotating detonation combustion region via the concave upstream face of the inner wall assembly being extended into the gas flowpath a depth;
adjusting an amount of the first portion of the flow of oxidizer provided to the concave upstream face of the inner wall assembly via actuating the upstream wall assembly to adjust the depth of the upstream wall assembly extended into the gas flowpath;
flowing a first flow of fuel to the first portion of the flow of oxidizer at the rotating detonation combustion region;
producing a rotating detonation wave of detonation gases at the rotating detonation combustion region via a first mixture of the first flow of fuel and the first portion of the flow of oxidizer;
adjusting a size of the rotation detonation wave at the rotating detonation combustion region by adjusting a depth of the inner wall assembly extended into the gas flowpath;
mixing at least a portion of the detonation gases from the rotating detonation combustion region with a second flow of fuel and the second portion of the flow of oxidizer in the gas flowpath; and
burning a second mixture including the second flow of fuel, at least the portion of the detonation gases, and the second portion of the flow of oxidizer, wherein burning the second mixture is downstream of the rotating detonation wave of detonation gases relative to the gas flowpath.
2. The method of claim 1 , wherein the adjusting the amount of the first portion of the flow of oxidizer provided to the inner wall assembly is based at least on an operating condition of the engine.
3. The method of claim 2 , wherein the operating condition of the engine is based at least on pressure, temperature, or flow rate of the flow of oxidizer at the combustion section.
4. The method of claim 1 , wherein the adjusting the amount of the first portion of the flow of oxidizer is based at least on a desired minimum number of detonation cells to produce the rotating detonation wave.
5. The method of claim 1 , wherein the adjusting the amount of the first portion of the flow of oxidizer comprises:
adjusting a cross sectional area of the gas flowpath based on an operating condition of the engine.
6. The method of claim 5 , wherein the adjusting the cross sectional area of the gas flowpath comprises:
adjusting the depth the upstream wall assembly extended into the gas flowpath based at least on the operating condition of the engine.
7. The method of claim 1 , wherein the burning the second mixture comprises a deflagrative combustion process.
8. The method of claim 1 , wherein the flowing the oxidizer to the combustion section comprises a supersonic axial velocity through the gas flowpath producing an oblique shockwave in the gas flowpath.
9. The method of claim 8 , comprising:
adjusting a profile of the oblique shockwave based on an operating condition of the engine.
10. The method of claim 9 , wherein the adjusting the profile of the oblique shockwave comprises:
adjusting the depth of the upstream wall extended into the gas flowpath.