Abstract: A pulse detonation engine comprises a primary air inlet; a primary air plenum located in fluid communication with the primary air inlet; a secondary air inlet; a secondary air plenum located in fluid communication with the secondary air inlet, wherein the secondary air plenum is substantially isolated from the primary air plenum; a pulse detonation combustor comprising a pulse detonation chamber, wherein the pulse detonation chamber is located downstream of and in fluid communication with the primary air plenum; a coaxial liner surrounding the pulse detonation combustor defining a cooling plenum, wherein the cooling plenum is in fluid communication with the secondary air plenum; an axial turbine assembly located downstream of and in fluid communication with the pulse detonation combustor and the cooling plenum; and a housing encasing the primary air plenum, the secondary air plenum, the pulse detonation combustor, the coaxial liner, and the axial turbine assembly.

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 swirler having cross-sectional area comparable to the area of a detonation chamber is placed upstream of the detonation chamber to enhance the fuel-air mixing. The swirler has a first region and a second region, each of which induces swirl in the flow through the swirler. Each region induces a different direction of swirl in the flow. The residual net swirl present in the flow downstream of the swirler is controlled by the relative properties of each region of the swirler. The swirler also provides high optical blockage to inhibit the upstream propagation of flow due to the detonation shockwave.

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: A method and system for actively controlling thrust pressure in a steam turbine is disclosed. The method may comprise monitoring a thrust pressure affecting a thrust fitting in a steam turbine, and adjusting the thrust pressure to maintain a desired thrust pressure on the thrust fitting in the steam turbine.