Abstract: A method for operating a pulse detonation engine, wherein the method includes channeling air flow from a pulse detonation combustor into a flow mixer having an inlet portion, an outlet portion, and a body portion extending therebetween. The method also includes channeling ambient air past the flow mixer and mixing the air flow discharged from the pulse detonation combustor with the ambient air flow such that a combined flow is generated from the flow mixer that has less flow variations than the air flow discharged from the pulse detonation combustor.

Abstract: A flow control device for use with a pulse detonation chamber including an inlet coupled in flow communication with a source of compressed air. The inlet extends at least partially into the chamber to facilitate controlling air flow into the chamber. The device also includes a body portion extending downstream from and circumferentially around the inlet, wherein the body portion is positioned in flow communication with the inlet.

Abstract: A pulse detonation combustor (PDC) assembly includes an upstream chamber forming an inlet plenum, a downstream chamber including a downstream portion of at least one PDC tube, and an integrated PDC head coupled to the upstream chamber and the downstream chamber. The integrated PDC head is configured to facilitate fuel injection and ignition within the PDC tube. The PDC tube includes an inner seal surface and an outer seal surface configured to mate with the inner seal surface, wherein the inner seal surface includes an elevated section thereon that engages with the outer seal surface such that the PDC tube is free to partially pivot about a longitudinal axis thereof.

Abstract: A turbine disk assembly including a rotatable cylindrical member rotatably coupled to a shaft and a plurality of turbine blades extend circumferentially outward from said cylindrical member. The turbine blades include at least two different geometrical shapes, a first of the geometrical shapes is configured to facilitate extracting power from a first pulsed detonation combustor product stream. A second of said geometrical shapes is configured to facilitate extracting power from a second pulsed detonation combustor product stream that is different from the first pulsed detonation combustor product stream.

Abstract: A detonation chamber for a pulse detonation combustor including: a plurality of dimples disposed on at least a portion of an inner surface of the detonation chamber wherein the plurality of dimples enhance a turbulence of a fluid flow through the detonation chamber

Abstract: An aircraft engine is provided with at least one pulse detonation device, and the operational frequency of the pulse detonation device is varied over an operational range of frequencies around a mean frequency value. The pulse detonation device can be positioned upstream, downstream or adjacent to a turbine section of the engine. An additional embodiment of the present invention is an aircraft engine provided with more than one pulse detonation device, and the operational frequency of one, or more, of the pulse detonation devices is varied over an operational range of frequencies around a mean frequency value.

Abstract: A pulse detonation combustor is provided with a fuel-air mixer located upstream from a detonation chamber. A fuel-air mixture exits the fuel-air mixer and enters the detonation chamber, where it is ignited by an ignition source. The flow from the fuel-air mixer passes over the surface of a center body, which extends downstream from the fuel-air mixer. The surface of the center body contains at least one turbulence generator, which imparts additional turbulence in the fuel-air mixture passing through the chamber. The turbulence generator aids in the mixing of the fuel and air of the fuel-air mixture to enhance the deflagration to detonation transition within the pulse detonation combustor.

Abstract: The present invention is a gas turbine engine system containing a compressor stage, a pulse detonation stage, and a turbine stage. During operation of the engine system, compressed flow from the compressor stage is directed to at least one off-axis pulse detonation tube in the pulse detonation stage. The off-axis pulse detonation tube detonates a mixture containing the compressed flow and a fuel to create a detonation wave, which is routed to an inlet portion of a reverse flow turbine. The exhaust flow from the reverse flow turbine is then directed away from the engine through ducting.

Abstract: A pulse detonation device for dividing a pulse detonation shock wave into an primary and control portion to reduce the strength of a propagating shock wave and/or change its direction. The device contains a flow separator which directs a portion of the shock wave into itself, thus reducing the shock wave's strength. In one configuration, the control region converges in cross-sectional area so as to accelerate the flow in the control region, while the primary region diverges to slow the flow in the primary region. The flow in the control region is directed, at an angle, into the flow of the primary region to impede and/or redirect the flow of the primary region.

Abstract: A pulse detonation (PD) assembly includes at least one PD chamber having a wall, which defines cooling holes arranged along at least a portion of the PD chamber. A manifold extends around the PD chamber. The manifold and PD chamber are separated by a bypass region. A PD assembly with reverse flow cooling includes at least one PD chamber. A sleeve extends around the PD chamber. The sleeve and PD chamber are separated by a reverse flow cooling passage configured to receive a flow of air and to flow the air in a reverse direction to supply the PD chamber. A PD assembly with bypass flow cooling includes at least one PD chamber and a manifold extending around the PD chamber(s), which are separated by a bypass region. The PD assembly further includes a mixing plenum configured to receive and mix the bypass flow from the bypass region and the detonation by-products from the PD chamber(s).

Abstract: A pulse detonation (PD) assembly includes a number of PD chambers adapted to expel respective detonation product streams and a number of barriers disposed between respective pairs of PD chambers. The barriers define, at least in part, a number of sectors that contain at least one PD chamber. A hybrid engine includes a number of PD chambers and barriers. The hybrid engine further includes a turbine assembly having at least one turbine stage, being in flow communication with the PD chambers and being configured to be at least partially driven by the detonation product streams. A segmented hybrid engine includes a number of PD chambers and segments configured to receive and direct the detonation product streams from respective PD chambers. The segmented hybrid engine further includes a turbine assembly configured to be at least partially driven by the detonation product streams.

Abstract: An engine includes at least one pulse detonation chamber configured to receive and detonate a fuel and an oxidizer. The pulse detonation chamber has an outlet end and includes a porous liner adapted to fit within an inner surface of the pulse detonation chamber within a vicinity of the outlet end. The engine also includes a casing housing the pulse detonation chamber.

Abstract: The present invention is a gas turbine engine system containing a compressor stage, a pulse detonation stage, and a turbine stage. During operation of the engine system, compressed flow from the compressor stage is directed to at least one off-axis pulse detonation tube in the pulse detonation stage. The off-axis pulse detonation tube detonates a mixture containing the compressed flow and a fuel to create a detonation wave, which is routed to an inlet portion of a reverse flow turbine. The exhaust flow from the reverse flow turbine is then directed away from the engine through ducting.

Abstract: An engine includes at least one pulse detonation chamber configured to receive and detonate a fuel and an oxidizer. The pulse detonation chamber has an outlet end and includes a porous liner adapted to fit within an inner surface of the pulse detonation chamber within a vicinity of the outlet end. The engine also includes a casing housing the pulse detonation chamber.