Abstract: An inlet filter housing includes a plurality of components that collectively form a complete filtering and conditioning system for filtering and conditioning a fluid along a housing flow path. Each component is fitted within an external structure of an International Organization of Standards (ISO) shipping container, which provides a rectangular cuboid enclosure. Each component includes operative structure of at least one of: a) only a portion of an axial extent of the filtering and conditioning system, and b) only a portion of a lateral cross-sectional area of the housing flow path.

Abstract: An inlet filter housing includes a plurality of components that collectively form a complete filtering and conditioning system for filtering and conditioning a fluid along a housing flow path. Each component is fitted within an external structure of an International Organization of Standards (ISO) shipping container, which provides a rectangular cuboid enclosure. Each component includes operative structure of at least one of: a) only a portion of an axial extent of the filtering and conditioning system, and b) only a portion of a lateral cross-sectional area of the housing flow path.

Abstract: A system includes an acoustic monitoring, analysis, and diagnostic system having a processor. The processor is configured to receive NF noise signals from a near field (NF) microphone array, the NF microphone array measures noises from a power generation system in a NF. The processor is configured to receive FF noise signals from a far field (FF) microphone array, the FF microphone array measures noises from a power generation system in a FF. The processor is configured to derive NF and FF noise measurements based on the signals and to synchronize the NF and FF noise measurements to create synchronized NF and FF noise data. The processor is configured to analyze the synchronized NF and FF noise data to create a NF and an FF noise signature. The processor is configured to diagnose root causes of noises generated from the power generation system and to report the root causes.

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 gas turbine system includes a load coupling connecting a gas turbine to a generator. A load coupling guard surrounds the load coupling to define an enclosed spaced around the load coupling. The load coupling guard includes a porous sleeve such that hydrogen coolant leaked into the load coupling guard from the generator is vented to ambient air.

Abstract: A progressive shipping stand includes a stage one assembly, and a stage two assembly. The stage one assembly and the stage two assembly together define a first profile, and the stage two assembly alone defines a second profile, smaller than the first profile. The stage two assembly may be attachable directly to a load. The stage two assembly is operable independently in a discrete support configuration and is selectively cooperable with the stage one assembly in a full support configuration. The shipping support allows for large machinery such as a turbine or the like to meet at least one shipping criteria that would not otherwise be feasible using a standard shipping support.

Abstract: A support assembly for supporting a gas turbine during a manufacturing configuration, a shipping configuration and an operating configuration. The support assembly includes a stand leg securable to a base, and the stand leg includes a turbine casing interface with a slot sized to receive a turbine casing pin. A support plate is attachable to the turbine casing interface. The support plate includes a closed pin aperture that is sized to fit over the turbine casing pin in the slot. The slot is a U-shaped slot in the turbine casing interface, and the U-shaped slot is open to receive the turbine casing pin from above.

Abstract: An assembly for securing machinery such as a gas turbine on a deck includes a first block unit configured to restrict vertical displacement of the machinery relative to the deck, and a second block unit configured to restrict axial and lateral displacement of the machinery. The first block unit includes a base block securable to the deck and an attachment block secured to the base block. The second block unit is engageable with the machinery base.

Abstract: A support assembly supports a gas turbine in a manufacturing configuration, a shipping configuration and an operating configuration. The support assembly includes a stand leg securable to a base, where the stand leg includes a turbine casing interface with a slot sized to receive a turbine casing pin. A support plate attachable to the turbine casing interface includes a pin aperture that is sized to fit over the turbine casing pin in the slot.

Abstract: The present disclosure is directed to a sound attenuation system for a gas turbine engine. The sound attenuation system includes a compressor inlet casing having a compressor inlet casing inner surface and defining a compressor inlet passage extending therethrough. An inlet plenum body couples to the compressor inlet casing. The inlet plenum body includes an inlet body inner surface and defines an inlet plenum therein. One or more sound attenuating panels couple to at least one of the compressor inlet casing inner surface and the inlet plenum body inner surface of the duct. Each sound attenuating panel includes a first sheet defining a first plurality of apertures extending therethrough and a solid second sheet spaced apart from the first sheet.

Abstract: An acoustic treatment assembly includes a fluid passage and a first panel disposed within the fluid passage. Additionally, at least a portion of a fluid flow through the acoustic treatment assembly is configured to flow across a first micro-perforated surface of the first panel. Further, the first panel includes at least one module, and each module of the at least one module includes the first micro-perforated surface and a respective back surface offset from the first micro-perforated surface opposite the fluid flow across the first micro-perforated surface. The first micro-perforated surface and the back surface form a first cavity configured to promote resonance within a first frequency range of the fluid flow.

Abstract: An assembly for securing machinery such as a gas turbine on a deck includes a first block unit configured to restrict vertical displacement of the machinery relative to the deck, and a second block unit configured to restrict axial and lateral displacement of the machinery. The first block unit includes a base block securable to the deck and an attachment block secured to the base block. The second block unit is engageable with the machinery base.

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 gas turbine system includes a load coupling connecting a gas turbine to a generator. A load coupling guard surrounds the load coupling to define an enclosed spaced around the load coupling. The load coupling guard includes a porous sleeve such that hydrogen coolant leaked into the load coupling guard from the generator is vented to ambient air.

Abstract: A progressive shipping stand includes a stage one assembly, and a stage two assembly. The stage one assembly and the stage two assembly together define a first profile, and the stage two assembly alone defines a second profile, smaller than the first profile. The stage two assembly may be attachable directly to a load. The stage two assembly is operable independently in a discrete support configuration and is selectively cooperable with the stage one assembly in a full support configuration. The shipping support allows for large machinery such as a turbine or the like to meet at least one shipping criteria that would not otherwise be feasible using a standard shipping support.

Abstract: A support assembly supports a gas turbine in a manufacturing configuration, a shipping configuration and an operating configuration. The support assembly includes a stand leg securable to a base, where the stand leg includes a turbine casing interface with a slot sized to receive a turbine casing pin. A support plate attachable to the turbine casing interface includes a pin aperture that is sized to fit over the turbine casing pin in the slot.

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: 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 hybrid turbomachine enclosure includes a plurality of walls interconnected to form an interior configured and disposed to receive a turbomachine, the plurality of walls including a first wall having a panel on frame construction and a hybrid wall including a first portion having a panel on frame structure and a second portion having a stiffened frame panel structure.

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.