Abstract: Systems and methods for utilizing gas turbine compartment ventilation discharge air. In one embodiment, a system may include a gas turbine engine having a compressor. The system also may include a gas turbine compartment disposed about the gas turbine engine. Moreover, the system may include an inlet bleed heat (IBH) manifold in fluid communication with the compressor. The gas turbine compartment may be in fluid communication with the IBH manifold for providing the IBH manifold with ventilation discharge air from the gas turbine compartment.

Abstract: Systems and methods for preheating fuel in a gas turbine engine are provided. In one embodiment, a system may include a gas turbine engine, a fuel line in fluid communication with the gas turbine engine, a gas turbine compartment disposed about the gas turbine engine, and a first conduit in fluid communication with the gas turbine compartment. The first conduit may include ventilation discharge air from the gas turbine compartment. The system also may include a first heat exchanger in communication with the fuel line and the first conduit. The first heat exchanger may be configured to exchange heat between the fuel and the ventilation discharge air from the gas turbine compartment.

Abstract: The present application provides a gas turbine engine for low turndown operations. The gas turbine engine may include a compressor with a compressor bleed air flow, an ambient air source with an ambient air flow, a turbine, and an eductor. The eductor blends the compressor bleed air flow and the ambient air flow into a blended air flow for use in cooling the turbine.

Abstract: The present application provides a gas turbine engine for low turndown operations. The gas turbine engine may include a compressor with a compressor bleed air flow, a turbine, and a compressor bleed air flow manifold. The compressor bleed air manifold directs a variable portion of the compressor bleed air flow to the turbine.

Abstract: The present application provides a gas turbine engine for low turndown operations. The gas turbine engine may include a compressor with a compressor bleed air flow, a turbine compartment with a turbine compartment air flow, a turbine, and an eductor. The eductor blends the compressor bleed air flow and the turbine compartment air flow into a blended air flow for use in cooling the turbine.

Abstract: A refurbishing method, refurbishing apparatus and refurbished article are provided. The refurbishing method includes accessing a plurality of rotatable components attached to a turbine assembly, the turbine assembly being a portion of a turbomachine, providing a predetermined volume of a buffered electrolytic solution in an electro-polishing tank, coupling the plurality of rotatable components to a power supply, immersing an immersion portion of at least one of the plurality of rotatable components in the buffered electrolytic solution, passing an electrical energy through the immersion portion of at least one of the plurality of rotatable components while the immersion portion is immersed in the buffered electrolytic solution, wherein an electrical flux to the immersion portion electro-polishes the immersion portion, separating the immersion portion from the buffered electrolytic solution, and applying a corrosion inhibitor to the plurality of rotatable components.

Abstract: A supercharging system includes a fan providing an air flow, and a prime mover that drives the fan. A duct directs a first portion of the air flow to a gas turbine system, a main bypass subsystem diverts a second portion of the air flow to a heat recovery steam generator; and a drive bypass subsystem that diverts a third portion of the air flow to the prime mover. The prime mover may be one of an aeroderivative gas turbine, a gas turbine, a reciprocating engine, a steam turbine and an induction motor and a variable frequency drive.

Abstract: A system for refurbishing at least one article attached to an assembly includes a refurbishing vessel that contains at least one wall and at least one open portion; means for providing an abrasive media to the vessel, wherein the abrasive media is caused to flow around the surfaces of the at least one article when the vessel is positioned on the at least one article; means for conformably sealing the at least one open portion against the flow of abrasive media, wherein a seal is created that conforms to the contours of the at least one article and prevents the abrasive media from escaping between the at least one article and the at least one wall; and means for removing the abrasive media from the vessel.

Abstract: A lubrication system for a heavy duty gas turbine includes a bearing lubrication assembly coupled to the bearing and an oil and vapor extraction assembly disposed in a cavity defined by a bell mouth hood in an air inlet duct. A high volume vacuum blower is coupled to the oil and vapor extraction assembly to provide a relative negative pressure. An oil and vapor separator is disposed downstream from the high volume vacuum blower. The lubrication system also includes a control subsystem that maintains a cavity pressure lower than an air inlet pressure.

Abstract: An air filter includes a filter material having a plurality of pleats, where each of the pleats includes a primary section and a folded section. The folded section is initially folded over at least a portion of the primary section such that the pleat has an initial pleat height. The folded section is configured to unfurl from being folded over the primary section based on a pressure differential between opposite sides of the filter material.

Abstract: A cleaning method and a cleaning fluid are provided. The cleaning method includes accessing a plurality of turbine components attached to a turbine assembly, the turbine assembly being a portion of a turbomachine, positioning at least one cleaning vessel over at least one of the turbine components, forming a liquid seal with a sealing bladder, providing a cleaning fluid to the cleaning vessel, and draining the cleaning fluid from the cleaning vessel. The cleaning fluid includes a carrier fluid and a solvent additive for removing fouling material from the turbine component. An alternative cleaning method is also provided.

Abstract: A gas turbine engine may be manually cleaned by removing a compressor casing and a turbine casing from the gas turbine engine, cleaning stator vanes of the gas turbine engine, and applying an organic acid solution to metallic surfaces of the gas turbine engine. The organic acid solution may be rinsed from the gas turbine engine and an anticorrosive solution may be applied to the metallic surfaces of the gas turbine engine.

Abstract: Methods and systems for imparting corrosion resistance to gas turbine engines are disclosed. Existing and/or supplemental piping is connected to existing compressor section air extraction and turbine section cooling air piping to supply water and anti-corrosion agents into areas of the gas turbine engine not ordinarily and/or directly accessible by injection of cleaning agents into the bellmouth of the turbine alone and/or repair methods. An anti-corrosion mixture is selectively supplied as a liquid-steam mixture to the compressor and/or the turbine sections of the gas turbine engine to coat the gas turbine engine components therein with a metal passivation coating which mitigates corrosion in the gas turbine engine.

Abstract: Methods and systems for dispersing an anticorrosion fluid to a turbine engine may be done while the turbine engine is online or offline. In an embodiment, a method may comprise selecting an anticorrosion fluid for a turbine engine and distributing the anticorrosion fluid into an air duct fluidly connected with the turbine engine.

Abstract: A gas turbine wash control system may perform a wash and a rinse of a gas turbine that is offline. An inter-rinse solution may be injected into the gas turbine. The gas turbine may be agitated and the inter-rinse solution drained. A second rinse of the gas turbine may be performed followed by the injection of an anticorrosive solution into the gas turbine.

Abstract: A gas turbine wash control system may perform a wash and a rinse of a gas turbine that is offline. An peracetic acid inter-rinse solution may be injected into the gas turbine. The gas turbine may be agitated and the peracetic acid inter-rinse solution drained. A second rinse of the gas turbine may be performed followed by the injection of an anticorrosive solution into the gas turbine.

Abstract: Methods and systems for imparting corrosion resistance to gas turbine engines are disclosed. Existing and/or supplemental piping is connected to existing compressor section air extraction piping and turbine section cooling air piping to supply water and anti-corrosion agents into areas of the gas turbine engine not ordinarily and/or directly accessible by injection of cleaning agents into the bellmouth of the turbine alone and/or repair methods. An anti-corrosion mixture is selectively supplied as an aqueous solution to the compressor and/or the turbine sections of the gas turbine engine to coat the gas turbine engine components therein with a metal passivation coating which mitigates corrosion in the gas turbine engine.

Abstract: Methods and systems for dispersing anticorrosive treatment for a turbine engine may incorporate an inlet bleed heat system. In an embodiment, a method may include selecting an anticorrosion fluid for a turbine engine and distributing the anticorrosion fluid via a vaporizing system fluidly connected with the turbine engine, wherein the vaporizing system is used to transform the anticorrosion fluid into a vapor.

Abstract: Disclosed herein are methods and systems for dispensing turbine engine anticorrosive protection. In an embodiment, a method may include selecting an anticorrosion fluid for a gas turbine engine and applying the anticorrosion fluid to the gas turbine engine.

Abstract: Methods and systems may dispense turbine engine anticorrosive protection. In an embodiment, a method may include determining a condition of a gas turbine engine while the gas turbine engine is online, wherein the condition includes the power output level of the gas turbine engine and applying, based on the condition, an anticorrosion fluid to the gas turbine engine while the gas turbine engine is online.