Abstract: A wave rotor combustor for use in a gas turbine engine includes an inlet assembly, a rotor drum, and an outlet assembly. The inlet assembly is arranged to direct a flow of gasses into rotor passages formed in the rotor drum. The rotor drum is arranged to receive the gasses. The outlet assembly is arranged to direct the gasses out of the rotor drum.

Abstract: A wave rotor combustor includes an inlet plate, an outlet plate, and a rotor drum assembly positioned therebetween. The inlet plate is formed to include an inlet port arranged to receive a mixture of fuel and air. The outlet plate is formed to include an outlet port arranged to receive combusted gasses flowing out of the wave rotor combustor. The rotor drum assembly is arranged to rotate relative to the inlet and outlet plates and to combust the fuel and air mixture as part of a combustion process. Conditioned air is passed through the wave rotor combustor to regulate a temperature distribution of the wave rotor combustor.

Abstract: A wave rotor includes an inlet plate, an outlet plate, and a rotor drum positioned therebetween. The inlet plate is formed to include an inlet port arranged to receive gasses. The outlet plate is formed to include an outlet port arranged to receive the gasses flowing out of the wave rotor. The rotor drum is arranged to rotate relative to the inlet and outlet plates. A piston assembly is used to counteract forces from pressure built up in the rotor drum.

Abstract: A wave rotor assembly includes a wave rotor combustor and an exit duct. The wave rotor combustor includes an aft plate formed to include an exit port and a rotor drum mounted for rotation relative to the aft plate. The rotor drum is formed to include a plurality of rotor passages arranged to align with the exit port during rotation of the rotor drum. The exit duct is coupled to the aft plate and defines a passage arranged to receive exhaust gasses flowing through the exit port.

Abstract: One embodiment of the present disclosure is a gas turbine engine. Another embodiment is a unique combustion system. Another embodiment is a unique engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for employing continuous detonation combustion processes. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: One embodiment of the present invention is an engine. Another embodiment is a unique combustion system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for engines and combustion systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: One embodiment of the present invention is a unique pulse detonation combustion system. Another embodiment is a unique gas turbine engine including a unique pulse detonation combustion system. In some embodiments, the pulse detonation combustion system includes an inlet section, a vortex generator and at least one flame accelerator. The inlet section, vortex generator and the at least one flame accelerator may be operative to initiate a deflagration to detonation transition. In some embodiments, the pulse detonation combustion system may include a flame accelerator configured with a directionally-dependent drag coefficient. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for pulse detonation combustion systems, gas turbine engines, and other machines and engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

Abstract: A constant volume combustor device includes, in one form, a detonative combustion. The apparatus includes inlet and outlet ports that interface with a plurality of fluid flow passageways on a rotor. A buffer gas is routed through some of the inlet and outlet ports and into and out of the plurality of fluid flow passageways. One of the inlet ports is a buffer gas inlet port that when placed in registry with a fluid flow passageway allows the flow of buffer gas into the respective passageway. Fuel is delivered into the buffer gas proximate the buffer gas inlet port so that only a portion of the buffer gas inlet port receives any fuel. In one form the wave rotor of the constant volume combustor is supported by magnetic bearings.

Abstract: One embodiment of the present invention is a unique pulse detonation combustion system. Another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for pulse detonation combustion systems, gas turbine engines, and other machines and engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

Abstract: A constant volume combustor device includes detonative combustion. In one form the wave rotor of the constant volume combustor is supported by magnetic bearings.

Abstract: One embodiment of the present invention is a unique engine. Another embodiment of the present invention is a unique combustion system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for engines and combustion systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: One embodiment of the present invention is an engine. Another embodiment is a unique combustion system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for engines and combustion systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: A pressure wave apparatus utilizing the principles of pulsed detonation and wave rotor technologies. The apparatus includes inlet and outlet ports that interface with a plurality of fluid flow passageways on a rotor. A buffer gas is routed through some of the inlet and outlet ports and into and out of the plurality of fluid flow passageways. One of the inlet ports is a buffer gas inlet port that when placed in registry with a fluid flow passageway allows the flow of buffer gas into the respective passageway. Fuel is delivered into the buffer gas proximate the buffer gas inlet port so that only a portion of the buffer gas inlet port receives any fuel.

Abstract: A constant volume combustor device includes detonative combustion. In one form the wave rotor of the constant volume combustor is supported by magnetic bearings.

Abstract: A constant volume combustor device includes, in one form, a detonative combustion. In one form the wave rotor of the constant volume combustor is supported by magnetic bearings. The constant volume combustor device includes a rotor having a number of fluid passageways that rotate about an axis. End plates having at least one inlet port and at least one outlet port are located on either end of the rotor. Relatively compressed air enters the rotor through the at least one inlet port, is burned with fuel in a pulsed combustion process, and exits at least one exit port. The pulsed combustion process can be a pulsed detonation combustion process or a pulsed deflagration combustion process.

Abstract: A pressure wave apparatus utilizing the principles of pulsed detonation and wave rotor technologies. The apparatus includes inlet and outlet ports that interface with a plurality of fluid flow passageways on a rotor. A buffer gas is routed through some of the inlet and outlet ports and into and out of the plurality of fluid flow passageways. One of the inlet ports is a buffer gas inlet port that when placed in registry with a fluid flow passageway allows the flow of buffer gas into the respective passageway. Fuel is delivered into the buffer gas proximate the buffer gas inlet port so that only a portion of the buffer gas inlet port receives any fuel.

Abstract: A constant volume combustor device includes detonative combustion. In one form the wave rotor of the constant volume combustor is supported by magnetic bearings.

Abstract: A particle separator for use with a turbine engine is arranged to divide a flow of air into a radially inner air flow and a radially outer air flow. The particle separator is further arranged to separate inner particles from the inner air flow to allow air from the inner air flow to enter the turbine engine without the inner particles and arranged to separate outer particles from the outer air flow to allow air from the outer air flow to enter the turbine engine without the outer particles.

Abstract: An attachment for the air intake of a gas turbine engine includes a plurality of particle separators. The particle separators cooperate to define an attachment axis and are spaced circumferentially about the attachment axis. Each particle separator includes a housing defining a separator axis, a first flow passage having at least a portion that is annular, an annular opening, and an annular second flow passage. The first and second flow passages are configured so that inertia of particles entrained in a stream of air flowing through the annular portion of the first flow passage tends to cause the particles to flow from the annular portion through the opening into the second flow passage to allow the stream of air to enter the engine flow passage free of the particles removed therefrom. The separator axes are parallel to and spaced apart from the attachment axis.

Abstract: A particle separator for use with a turbine engine is arranged to divide a flow of air into a radially inner air flow and a radially outer air flow. The particle separator is further arranged to separate inner particles from the inner air flow to allow air from the inner air flow to enter the turbine engine without the inner particles and arranged to separate outer particles from the outer air flow to allow air from the outer air flow to enter the turbine engine without the outer particles.