Abstract: A bleed plenum for a compressor section associated with a gas turbine engine includes a plenum chamber having a first wall spaced apart from a second wall to define a plenum slot configured to receive a flow of fluid from the compressor section. A slot angle of the plenum slot is defined between a centerline of the plenum slot and a longitudinal axis of the gas turbine engine and varies about a circumference of the bleed plenum. The second wall includes a bullnose having a wedge angle defined between the second wall and a surface associated with the compressor section. The bullnose faces into the flow of fluid through the plenum slot, and the wedge angle of the bullnose varies about the circumference of the bleed plenum.

Abstract: A bleed plenum for a compressor section associated with a gas turbine engine includes a plenum chamber having a first wall spaced apart from a second wall to define a plenum slot configured to receive a flow of fluid from the compressor section. A slot angle of the plenum slot is defined between a centerline of the plenum slot and a longitudinal axis of the gas turbine engine and varies about a circumference of the bleed plenum. The second wall includes a bullnose having a wedge angle defined between the second wall and a surface associated with the compressor section. The bullnose faces into the flow of fluid through the plenum slot, and the wedge angle of the bullnose varies about the circumference of the bleed plenum.

Abstract: The present invention provides a new filter cleaning method that has cleaning performance superior to that of ultrasonic cleaning. The method for cleaning a filter of the present invention includes the steps of: generating a shock wave; and bringing the shock wave into contact with a filter to which a filler adhered, wherein in the shock wave contacting step, a pressure applied to the filter by the shock wave is 0.07 MPa or more.

Abstract: The present invention provides a new filter cleaning method that has cleaning performance superior to that of ultrasonic cleaning. The method for cleaning a filter of the present invention includes the steps of: generating a shock wave; and bringing the shock wave into contact with a filter to which a filler adhered, wherein in the shock wave contacting step, a pressure applied to the filter by the shock wave is 0.07 MPa or more.

Abstract: A dynamic pressure exchanger configured for a combustion process includes a seal plate and a rotor assembly. The rotor assembly is mounted for rotation relative to the seal plate about a central axis of the dynamic pressure exchanger.

Abstract: An entrance stator in a turbofan has an airfoil shape with a leading edge and a trailing edge connected by surfaces which define a suction side and a pressure side. The entrance stator has a channel with an opening on the pressure side, extending to an exit on the suction side, having a pressure gradient between the opening and the exit. The channels are preceded with a ridge. The channels and the ridges control the boundary layer, enabling higher efficiencies. The channels and ridges add energy to the boundary layer to prevent separation.

Abstract: The present invention provides a novel cleaning device capable of removing deposits on an exposed surface of a cleaning object in a short time. The cleaning device (1) of the present invention, for removing deposits on an exposed surface of a cleaning object (3) includes: a shock-wave generation section (2) that generates a shock wave; and a cleaning object storage section (4) that adjoins the shock-wave generation section (2) or stores the shock-wave generation section (2) therein and stores the cleaning object (3).

Abstract: A dynamic pressure exchanger configured for a combustion process includes an inlet plate and a rotor assembly mounted for rotation relative to the inlet plate about a central axis of the dynamic pressure exchanger. The inlet plate is formed to include an inlet port configured to direct air into the rotor assembly. The rotor assembly includes an inner rotor and an outer rotor arranged around the inner rotor.

Abstract: An entrance stator in a turbofan has an airfoil shape with a leading edge and a trailing edge connected by surfaces which define a suction side and a pressure side. The entrance stator has a channel with an opening on the pressure side, extending to an exit on the suction side, having a pressure gradient between the opening and the exit. The channels are preceded with a ridge. The channels and the ridges control the boundary layer, enabling higher efficiencies. The channels and ridges add energy to the boundary layer to prevent separation.

Abstract: A dynamic pressure exchanger configured for a combustion process includes a seal plate and a rotor assembly. The rotor assembly is mounted for rotation relative to the seal plate about a central axis of the dynamic pressure exchanger.

Abstract: A dynamic pressure exchanger configured for a combustion process includes an inlet plate and a rotor assembly mounted for rotation relative to the inlet plate about a central axis of the dynamic pressure exchanger. The inlet plate is formed to include an inlet port configured to direct air into the rotor assembly. The rotor assembly includes an inner rotor and an outer rotor arranged around the inner rotor.

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: 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: Pulse detonation combustors of valveless construction. One valveless pulse detonation combustor, having a tube with a closed end and an open end, is constructed with a flame accelerator within the tube, adjacent the open end. A valveless, apertured flow restrictor is positioned between the flame accelerator and the closed end of the tube. A sparking device is positioned within the tube, between the flow restrictor and the flame accelerator. Valveless fuel and air ports are positioned between the flow restrictor and the closed end of the tube. Substantially right-angle manifold passageways are in communication with each of the ports.

Abstract: Pulse detonation combustors of valveless construction. One valveless pulse detonation combustor, having a tube with a closed end and an open end, is constructed with a flame accelerator within the tube, adjacent the open end. A valveless, apertured flow restrictor is positioned between the flame accelerator and the closed end of the tube. A sparking device is positioned within the tube, between the flow restrictor and the flame accelerator. Valveless fuel and air ports are positioned between the flow restrictor and the closed end of the tube. Substantially right-angle manifold passageways are in communication with each of the ports.