A Brayton cycle engine including a longitudinal wall extended along a lengthwise direction. The longitudinal wall defines a gas flowpath of the engine. An inner wall assembly is extended from the longitudinal wall into the gas flowpath. The inner wall assembly defines a detonation combustion region in the gas flowpath upstream of the inner wall assembly.

A method of reducing low-energy flow in a flight vehicle engine includes an isolator of the engine having a swept-back wedge to improve flow mixing. The wedge includes forward shock-anchoring locations, such as edges or rapidly-curved portions, that anchor oblique shocks in situations where the isolator has sufficient back pressure. The swept-back wedge may also create swept oblique shocks along its length. Boundary layer flow streamlines are diverted running parallel to or parallel but moving outward conically to the swept-wedge leading edge moving outboard and upward. The non-viscous flow outside the boundary layer is processed through the swept-back ramp shock and diverted outboard and upward as well. The outboard aft portion of the wedge at the sidewall intersection may also induce shocks and divert flow near the walls closer toward the walls and upward, and/or improve flow mixing.

A method of reducing low-energy flow in a flight vehicle engine includes an isolator of the engine having a swept-back wedge to improve flow mixing. The wedge includes forward shock-anchoring locations, such as edges or rapidly-curved portions, that anchor oblique shocks in situations where the isolator has sufficient back pressure. The swept-back wedge may also create swept oblique shocks along its length. Boundary layer flow streamlines are diverted running parallel to or parallel but moving outward conically to the swept-wedge leading edge moving outboard and upward. The non-viscous flow outside the boundary layer is processed through the swept-back ramp shock and diverted outboard and upward as well. The outboard aft portion of the wedge at the sidewall intersection may also induce shocks and divert flow near the walls closer toward the walls and upward, and/or improve flow mixing.

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.

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.

The present disclosure is directed to a rotating detonation combustion system for a propulsion system including a plurality of combustors in adjacent arrangement along the circumferential direction. Each combustor defines a combustor centerline extended through each combustor, and each combustor comprises an outer wall defining a combustion chamber and a combustion inlet. Each combustion chamber is defined by an annular gap and a combustion chamber length together defining a volume of each combustion chamber. Each combustor defines a plurality of nozzle assemblies each disposed at the combustion inlet in adjacent arrangement around each combustor centerline. Each nozzle assembly defines a nozzle wall extended along a lengthwise direction, a nozzle inlet, a nozzle outlet, and a throat therebetween, and each nozzle assembly defines a converging-diverging nozzle. A first array of combustors defines a first volume and a second array of combustors defines a second volume different from the first volume.

The present disclosure is directed to a rotating detonation combustion system for a propulsion system including a plurality of combustors in adjacent arrangement along the circumferential direction. Each combustor defines a combustor centerline extended through each combustor, and each combustor comprises an outer wall defining a combustion chamber and a combustion inlet. Each combustion chamber is defined by an annular gap and a combustion chamber length together defining a volume of each combustion chamber. Each combustor defines a plurality of nozzle assemblies each disposed at the combustion inlet in adjacent arrangement around each combustor centerline. Each nozzle assembly defines a nozzle wall extended along a lengthwise direction, a nozzle inlet, a nozzle outlet, and a throat therebetween, and each nozzle assembly defines a converging-diverging nozzle. A first array of combustors defines a first volume and a second array of combustors defines a second volume different from the first volume.

Provided herein are various new or improved airbreathing and non-airbreathing engines. In another example, a new type of rotary engine is provided and is assembled into a single body from manufactured parts and comprising front and rear non-vented case plates, a detonation channel, a center case plate, a rotary gate valve spacer plate, front and rear bearing cover plates, front and rear centrifugal fan bearings and a non-vented centrifugal flywheel fan. The front non-vented case plate and the detonation channel includes an air intake port. The center case plate comprises an adjustable fuel aerosolizing combustor - detonator. The non-vented centrifugal flywheel fan comprises a plurality of rotary gate valves, a plurality of radial fan blades and a splined drive shaft. The rotary engine also comprises a plurality of case plate bolts, case plate post spacers, case plate nuts and bearing cover plate bolts.

Provided herein are various new or improved airbreathing and non-airbreathing engines. In another example, a new type of rotary engine is provided and is assembled into a single body from manufactured parts and comprising front and rear non-vented case plates, a detonation channel, a center case plate, a rotary gate valve spacer plate, front and rear bearing cover plates, front and rear centrifugal fan bearings and a non-vented centrifugal flywheel fan. The front non-vented case plate and the detonation channel includes an air intake port. The center case plate comprises an adjustable fuel aerosolizing combustor - detonator. The non-vented centrifugal flywheel fan comprises a plurality of rotary gate valves, a plurality of radial fan blades and a splined drive shaft. The rotary engine also comprises a plurality of case plate bolts, case plate post spacers, case plate nuts and bearing cover plate bolts.

A ram air fan assembly includes a motor/bearing housing that extends along a horizontal length of the ram air fan assembly. An inner housing assembly is in fluid communication with the motor/bearing housing to define a joint. The inner housing assembly includes first and second ellipse-shaped slots. The first slot is positioned at a first angle with respect to a radial axis of the inner housing assembly that is perpendicular to the horizontal length, and the second slot is positioned at a second angle with respect to the radial axis, the second angle being different from the first angle, and each slot extending along a first direction parallel to the horizontal length to define an axial width and extending along a radial axis to define a radial width being greater than the axial width.