Abstract: A silencer apparatus for a gas turbine inlet system ducting is disclosed. The inlet ducting contains a main silencer and a pre-silencer, and Inlet Bleed Heat (“IBH”) located between the silencers. The pre-silencer decreases the noise level from the turbine compressor and makes the air flow/temperature profiles more uniform. The main silencer reduces noise from the IBH and the remaining noise from the compressor to an appropriate level. The main silencer is comprised of a first plurality of sound-absorbing splitters disposed along the gas flow direction in the gas turbine inlet ducting. The pre-silencer is comprised of a second plurality of sound-absorbing splitters disposed along the gas flow direction in the gas turbine inlet ducting, but staggered with respect to the first plurality of splitters to thereby block a direct line of travel for noise acoustical waves from the compressor travelling opposite the gas flow direction in the inlet ducting.

Abstract: A liquid injection apparatus for use with a compressor having a rotor shaft and a casing part is provided. The liquid injection apparatus includes at least one conduit and at least one nozzle coupled to the conduit(s). The liquid injection apparatus is panel-shaped and has a first panel segment, a second panel segment, and at least one of: a passage defined between the first panel segment and the second panel segment, the passage sized to receive at least one of the rotor shaft and the casing part; and a third panel segment positioned between the first panel segment and the second panel segment. The third panel segment is at least in part detachable from the first panel segment and/or the second panel segment for receiving at least one of the rotor shaft and the casing part between the first panel segment and the second panel segment.

Abstract: An inlet system for a gas turbine includes an integrated inlet bleed heat system, wherein the inlet bleed design is integrated in, e.g., a silencer or inlet.

Abstract: Synthetic media pads configured to be arranged in a stack of an evaporative cooler for a gas turbine, wherein the synthetic media pads include high density synthetic media pads and low density synthetic media pads. The sides of the pads may have surface patterns, such as grooves and ridges, to provide support for the pads.

Abstract: An inlet bleed heat (IBH) system manifold for a compressor inlet housing is provided. The manifold includes: a plurality of feed pipes for delivering a compressor discharge air, each feed pipe extending across a duct of the compressor inlet housing. Each feed pipe includes: an elongated inner feed pipe for delivering the compressor discharge air, the inner feed pipe including a plurality of orifices along at least a portion of a length of the inner feed pipe, each orifice extending through a wall of the inner feed pipe allowing the compressor discharge air to exit the inner feed pipe; and a noise attenuating material disposed about the inner feed pipe and the plurality of orifices, the noise attenuating material configured to attenuate noise created by the compressor discharge air exiting the plurality of orifices.

Abstract: A gas turbine system includes an exhaust processing system that may process exhaust gas generated by a gas turbine engine, the exhaust processing system includes an exhaust diffuser that may receive the exhaust gas from a turbine of the gas turbine engine and having an annular passage disposed between an inner annular wall and an outer annular wall, and an air injection assembly disposed within the exhaust diffuser. The air injection assembly includes one or more air injection conduits disposed within the annular passage of the exhaust diffuser and including fluid injection holes that may direct a cooling fluid into a first mixing region of the exhaust diffuser.

Abstract: A simple-cycle gas turbine system includes an injection system including a plurality of injection tubes that may inject a fluid into a duct of an exhaust processing system that may process exhaust gas generated by a gas turbine engine. The exhaust processing system includes a selective catalytic reduction (SCR) system that may reduce a level of nitrogen oxides (NOx) within the exhaust gas; and a mixing system positioned adjacent to the plurality of injection tubes and within the exhaust processing system. The mixing system includes a mixing module having a plurality of turbulators that may swirl the fluid, or the exhaust gas, or both, in a first swirl direction to encourage turbulent flow along an axis of the exhaust processing system and thereby facilitate mixing between the fluid and the exhaust gas.

Abstract: A baffle for an air intake section of a rotary machine includes a pair of oppositely disposed perforated walls that at least partially define an exterior of the baffle and an interior cavity of the baffle. The baffle also includes a pair of panels disposed within the interior cavity. Each of the panels is coupled proximate a respective one of the perforated walls, such that a chamber is defined between the panels. Each of the panels includes a first sound absorbing material that is substantially completely vaporizable at an operating temperature of the rotary machine.

Abstract: A baffle for an air intake section of a rotary machine includes a pair of oppositely disposed perforated walls that at least partially define an exterior of the baffle and an interior cavity of the baffle. The baffle also includes a pair of panels disposed within the interior cavity. Each of the panels is coupled proximate a respective one of the perforated walls, such that a chamber is defined between the panels. Each of the panels includes a first sound absorbing material that is substantially completely vaporizable at an operating temperature of the rotary machine.

Abstract: A silencer duct that may be part of, for example, a turbomachine inlet may include a duct body. A first perforated wall extends within the duct body and substantially parallel to an interior surface of the duct body. A first acoustic absorbing material may be positioned between the duct body and the first perforated wall. A silencer element may extend axially through the duct body, the silencer element including a second perforated wall having a second acoustic absorbing material adjacent thereto.

Abstract: A silencer duct includes at least one element including a three-dimensional (3D) chamber having a portion that is at least one of non-vertical or non-linear. An acoustic absorbing member is self-supporting such that is may be positioned within the portion to substantially fill the portion, but does not sag or droop over time.

Abstract: A silencer duct that may be part of, for example, a turbomachine inlet and may include a duct body, and a silencer element extending axially through the duct body. A first portion of a coupler may extend axially from a first side of the duct body. A second portion of a coupler may extend axially from a second side of the duct body. At least one of the first portion of the coupler and the second portion of the coupler are configured to couple to at least one of an adjacent silencer duct and an inlet.

Abstract: A power system is provided. The power system includes a gas turbine assembly having a compressor, a combustor, and a turbine coupled in serial flow arrangement. The compressor has a compressor inlet. The power system also includes an electrostatic precipitation system coupled to the gas turbine assembly upstream from the compressor inlet. The compressor is oriented to receive working gases discharged from the electrostatic precipitation system to facilitate removing entrained matter from the working gases flowing into the compressor inlet.

Abstract: An inlet system for a gas turbine includes an inlet duct, a silencer assembly disposed downstream from the inlet duct and an outlet duct disposed downstream from the silencer assembly. The silencer assembly may include a duct and a plurality of laterally spaced baffles disposed within the duct. The baffles may be arranged substantially parallel to a flow of air flowing through the inlet system. Each baffle includes a leading edge portion, a trailing edge portion that is longitudinally spaced from the leading edge portion and a pair of laterally opposing side walls that extend between the leading and trailing edges. Each baffle includes at least one acoustic panel that extends at least partially across one side wall of the pair of side walls.

Abstract: A silencer panel includes an acoustic absorbing material; and an enclosure surrounding the acoustic absorbing material. The enclosure includes at least one plastic, perforated side wall.

Abstract: A silencer panel section may include an acoustic absorbing material, a first enclosure surrounding the acoustic absorbing material, and a first coupler configured to couple the first enclosure to a second enclosure of an adjacent silencer panel section. A silencer panel may employ a plurality of the sections coupled together to form a single silencer panel. A silencer duct may include a frame forming a working fluid flow path, and a plurality of silencer panel mounts positioned within the frame, each silencer panel mount configured to slidingly receive a silencer panel, such as the silencer panel described herein.

Abstract: A silencer panel includes an acoustic absorbing material; and an enclosure surrounding the acoustic absorbing material. The enclosure includes at least one plastic, perforated side wall. A first electrostatic particle removing electrode may be associated with the enclosure to remove particles from a working fluid in conjunction with a second electrostatic particle removing electrode.

Abstract: A load coupling device includes a housing including an interior portion, an ambient air inlet provided in the housing, and a load coupling guard arranged in the housing. The load coupling guard includes a turbomachine end and a load end and a passage extending therebetween. A vent extends upwardly from the load coupling guard. The vent is fluidically exposed to the load end. An ambient air inlet passage is formed in the load coupling guard and fluidically connects the ambient air inlet and the vent. The load end is substantially fluidically isolated from the turbomachine end.

Abstract: A silencer apparatus for a gas turbine inlet system ducting is disclosed. The inlet ducting contains a main silencer and a pre-silencer, and Inlet Bleed Heat (“IBH”) located between the silencers. The pre-silencer decreases the noise level from the turbine compressor and makes the air flow/temperature profiles more uniform. The main silencer reduces noise from the IBH and the remaining noise from the compressor to an appropriate level. The main silencer is comprised of a first plurality of sound-absorbing splitters disposed along the gas flow direction in the gas turbine inlet ducting. The pre-silencer is comprised of a second plurality of sound-absorbing splitters disposed along the gas flow direction in the gas turbine inlet ducting, but staggered with respect to the first plurality of splitters to thereby block a direct line of travel for noise acoustical waves from the compressor travelling opposite the gas flow direction in the inlet ducting.

Abstract: Embodiments of the present disclosure provide an assembly including a fibrous medium having a plurality of substantially corrugated channels therein, the plurality of substantially corrugated channels being permeable to a flow of fluid therethrough; a distributor in contact with the fibrous medium, and including an aperture therein for transmitting a liquid coolant through the distributor; and at least two acoustic shields coupled to the fibrous medium and proximal to opposing sides of the distributor.