Abstract: A turbine exhaust structure for an intermediate-pressure exhaust end of a high-and-intermediate-pressure (HIP) module.

Abstract: A fluid plenum including a body defining an internal cavity having an inlet and an outlet. The fluid plenum further includes at least one wall positioned in the internal cavity that divides the internal cavity into first and second passageways, and which also divides the inlet into first and second inlet portions, and divides the outlet into first and second outlet portions. The first passageway receives fluid through the first inlet portion and directs fluid to the first outlet portion, and the second passageway receives fluid through the second inlet portion and directs fluid to the second outlet portion. The first and second passageways extend first and second lengths that are different from one another, and also generate a substantially common back-pressure at the first and second inlet portions during flow of a fluid stream through the inlet, including a first sub-stream of the fluid stream through the first passageway and a second sub-stream of the fluid stream through the second passageway.

Abstract: The present invention features a flood damage prevention apparatus having a modular equilateral triangular prism enclosure with an interlocking system used to interlock and position additional modules of the apparatus during flood damage prevention deployment. The interlock system enables additional modules of the flood damage prevention apparatus to be locked in position. Each module may be protected from flood debris damage by way of a protective covering over each enclosure. The apparatus may be filled with fluid via a seal tight opening located on the surface of the enclosure which in turn may be closed using a seal tight apparatus.

Abstract: Disclosed are a casing arrangement and a method to reduce critical panel mode response in a gas turbine casing. The casing arrangement includes a turbine exhaust cylinder connected to a turbine exhaust manifold establishing a fluid flow path, the fluid flow path including an inner and an outer flow path. A plurality of stiffening ribs are coupled to a surface of the inner flow path which effectively increases the stiffness reducing the critical panel mode response.

Abstract: Systems and methods for operating a turbocharged engine are described. In one example, a turbocharger system, comprising: a bearing housing including a turbine and at least one compressor coupled to the turbine via a shaft; and wherein the turbine comprises a stator stage and a rotor stage mounted to the cylinder head by the bearing housing and positioned in an exhaust passage of a cylinder head. In this way, a more compact design is achieved which eliminates the cost and complexity of a turbine housing and improves turbine efficiency by positioning the turbine closer to the exhaust pulses.

Abstract: An apparatus (10) is presented for controlling a boundary layer (30) in a diffusing flow path (14) of a power generating machine (16). The apparatus includes a passage (18) in the power generating machine with an inlet (20) and an outlet (22). The apparatus also includes a fluid source (24) coupled to the inlet to transmit fluid into the passage. The apparatus also includes a vortex generator (26) within the passage effective to generate a vortex fluid (12) at the outlet. The outlet is positioned to inject the vortex fluid into the diffusing flow path of the power generating machine in order to control the boundary layer of the diffusing flow path. An apparatus is also provided to enhance the diffusion of a flow path within a power generating machine.

Abstract: In accordance with one embodiment, a system includes a turbine engine including an axial-radial diffuser section disposed about a first longitudinal axis downstream in an exhaust flow path from a turbine section. The system also includes an exhaust plenum including a first plenum portion disposed about the axial-radial diffuser section, wherein the first plenum portion includes a curved wall portion that diverges away from a circumference of the axial-radial diffuser section. The exhaust plenum also includes a second plenum portion extending away from the first plenum portion downstream along a second longitudinal axis of the exhaust plenum approximately crosswise to the first longitudinal axis.

Abstract: An exhaust collector having a radial inlet configured to receive exhaust gas in a radial direction, an outlet configured to deliver exhaust gas in and outlet direction, and an enclosure configured to collect the received exhaust gas into at least two circumferential counter flows, and route the collected exhaust gas to the outlet, wherein the enclosure includes a collected flow barrier configured to divide the collected exhaust gas from the exhaust gas received at the radial inlet, and a collected flow circumferential divider configured to form a physical barrier between at least a portion of the at least two circumferential counter flows.

Abstract: An exhaust system is provided for mitigating condensate formation in a common exhaust stack and for effecting improved heat transfer. Reduced condensate formation and improved heat transfer is achieved by inducing non-laminar flow through the common exhaust stack and a heat exchanger operatively coupled to the common exhaust stack. Heat transfer is further improved by dew point control. Non-laminar flow is induced by connecting more than one gas turbine to the common exhaust stack through non-laminar flow inducing arrangements. The various coupling arrangements also add structural rigidity to the common exhaust stack for increased stack height and improved plume dispersion.

Abstract: A gas turbine engine has an engine core and an annular by-pass duct, within a surrounding nacelle. An exhaust nozzle of the nacelle includes a selectively deployable noise-reduction section on an inner surface thereof. The noise-reduction section includes an inflatable envelope comprising a fixed outer wall and a displaceable inner wall. At least projections on the inner wall are inwardly displaced when the envelope is pressurized and retracted radially outwardly when the envelope is de-pressurized. When the envelope is pressurized, the inner wall includes portions that project to form a rough surface on the inner surface of the nacelle exhaust nozzle. This thickens the boundary layer and reduces the speed of the gas flow at the outer radius of the nozzle, thus reducing the differential velocity with the ambient air, which reduces the gradient throughout the shear layer thus reducing the noise level of the engine.

Abstract: A diffuser for a gas turbine includes an inlet adapted for coupling to the gas turbine. The diffuser also includes at least one outlet located proximate a diffuser end, wherein the diffuser end is located downstream of the inlet. The diffuser further includes an outer wall and an inner barrel that extends substantially to the diffuser end.

Abstract: A gas turbine is provided, including a turbine, an exhaust diffuser, and a plasma actuator. The turbine releases an exhaust gas. The exhaust diffuser receives the exhaust gas from the turbine. The exhaust diffuser has an inlet and an outlet, and at least one wall that is disposed between the inlet and the outlet. The plasma actuator produces a plasma along the at least one wall of the diffuser.

Abstract: A flow passage defined between an inner and an outer boundary for guiding a fluid flow in an axial direction. A flow control vane is supported at a radial location between the inner and outer boundaries. A fluid discharge opening is provided for discharging a flow of the compressed fluid from a trailing edge of the vane, and a fluid control surface is provided adjacent to the fluid discharge opening and extends in the axial direction at the trailing edge of the vane. The fluid control surface has a curved trailing edge forming a Coanda surface. The fluid discharge opening is selectively provided with a compressed fluid to produce a Coanda effect along the control surface. The Coanda effect has a component in the radial direction effecting a turning of the fluid flow in the flow path radially inward or outward toward one of the inner and outer boundaries.

Abstract: A turbine exhaust diffuser adjustment system for a gas turbine engine capable of altering the flow of turbine exhaust gases is disclosed. The turbine exhaust diffuser adjustment system may be formed from one or more flow ramps positioned in a flowpath. The flow ramp may include a downstream, radially outward point that extends radially outward further from the ID flowpath boundary than an upstream, radially outward point that is positioned upstream from the downstream, radially outward point. The flow ramp may be adjustable such that an angular position of a radially outer surface of the flow ramp may be adjusted relative to the ID flowpath boundary, thereby enabling the flowpath to be changed during turbine operation to enhance the efficiency of the turbine engine throughout its range of operation.

Abstract: An exhaust gas diffuser is provided and includes a peripheral body, a center body, formed to define an interior and disposed within the peripheral body to define an annulus between the peripheral body and the center body through which a first fluid flows along a main flow direction, a plurality of first members, each of which is respectively coupled to the peripheral body and the center body, to support the center body within the peripheral body and a plurality of second members, each of which extends across the annulus from the peripheral body to the center body downstream from the plurality of the first members relative to the main flow direction, to transport a second fluid to the center body interior. The plurality of the second members is circumferentially clocked relative to the plurality of the first members.

Abstract: An apparatus (10) is presented for controlling a boundary layer (30) in a diffusing flow path (14) of a power generating machine (16). The apparatus includes a passage (18) in the power generating machine with an inlet (20) and an outlet (22). The apparatus also includes a fluid source (24) coupled to the inlet to transmit fluid into the passage. The apparatus also includes a vortex generator (26) within the passage effective to generate a vortex fluid (12) at the outlet. The outlet is positioned to inject the vortex fluid into the diffusing flow path of the power generating machine in order to control the boundary layer of the diffusing flow path. An apparatus is also provided to enhance the diffusion of a flow path within a power generating machine.

Abstract: An exhaust system for a double flow steam turbine providing a separate external exhaust path from an upper section of a turbine outlet of a first turbine section to a first condenser and a separate external exhaust path from a lower section the turbine outlet of the first turbine section to the first condenser. A separate external exhaust path from an upper section of a turbine outlet of a second turbine section and a separate external exhaust path from a lower section of the turbine outlet of the second turbine section is also provided.

Abstract: An exhaust system for a plurality of turbines. An exhaust gas outlet is positioned on each of the plurality of turbines. The exhaust gas outlet provides a way of discharging any exhaust gas produced by a turbine during operation of the turbine. A common exhaust is operatively connected to the exhaust gas outlet of each of the plurality of turbines. The common exhaust is disposed to receive any exhaust gas produced by the plurality of turbines during the operation of at least one of the turbines. A back flow damper is positioned on the exhaust gas outlet for each of the plurality of turbines. An isolation damper is disposed on the back flow damper. The isolation damper is in fluid communication with the common exhaust.

Abstract: An axial flow steam turbine flow path that includes a rotor and a casing defining the axial steam flow path; and a toroidal diffuser for diffusing the exhaust steam and turning the exhaust steam from a generally axial flow direction to a generally transverse or vertical and tangential direction; wherein the toroidal diffuser comprises a diffuser that, at least in part, incorporates the shape of a toroid or a section of a toroid; and wherein a toroid comprises the shape generated by revolving a circular or oval shape in three dimensional space about an axis coplanar with the circular or oval shape, which does not touch the circular or oval shape.

Abstract: A flow by-pass system is provided in a downward-discharging exhaust hood of a steam turbine to by-pass a small percentage of the total steam flow from the top portion of the exhaust hood to the vicinity of the condenser and in that way relieve excess pressure in the top portion incident to the more convoluted path of the main portion of steam passing from the top to the bottom and to decrease energy loss caused by friction and thus to improve turbine efficiency. The flow by-pass system includes by-pass conduits within the front portion of the exhaust hood extending from the top portion to the vicinity of the condenser.

Abstract: Steam exhaust outlets of a low pressure steam turbine are fitted with a divider plate to separate exhaust steam into isolated flow paths in fluid communication with a condenser. Separation of the flow paths is maintained through the condenser so that heat rate is improved by lower average back pressure and higher temperature condensate exiting the condenser. In a double flow turbine, a further divider plate separates steam from one exhaust outlet from that of the other exhaust outlet thereby creating four steam flow paths to the condenser.

Abstract: A method and apparatus is provided for improving the performance of vapor turbine diffusers by preventing flow separation from the diffuser walls. Such separation from the diffuser walls is decreased or eliminated herein by chilling the diffuser walls below the saturation temperature, causing some condensation to occur and insuring vapor flow toward the walls to eliminate the natural tendency toward separation in diffusing vapor passages.

Abstract: An exhaust device for a condensable-fluid axial-flow turbine, comprising an annular diffuser with an axial input situated at the output of the last stage of the turbine and a substantially radial output leading to a condenser which is divided into two zones, in one of which the pressure is lower than in the other, the outer wall of the diffuser with respect to the input flow into the duct having a circumferential suction slot which removes a fraction of the flow in the diffuser towards the lower-pressure part of the condenser, said wall further having a shape such that the pressure gradient measured at its surface in the flow direction is negative or zero at all points.

Abstract: A toroidal shaped collector with a radial inlet and a single discharge outlet includes a pair of substantially parallel spaced baffle plates extending from the inlet partway into the collector chamber, disposed in the plane of the collector and serves to receive and discharge the airflow from a gas generator such as a gas turbine engine particularly adapted for nonaircraft applications.