Abstract: A method for predicting the residual useful life of an air filter arrangement is described. The method includes the following steps: providing a plurality of predetermined reference degradation curves; measuring a degradation parameter of the filter arrangement; and estimating the residual useful life of the filter arrangement by comparing the predetermined reference degradation curves and an actual degradation curve defined by measured values of the degradation parameter.

Abstract: The present application provides a pulse filtration system for use with a compressor of a gas turbine engine. The pulse filtration system may include a pulse filter, a compressed air system in communication with the pulse filter, and a hydrophobic filter bag surrounding the pulse filter in whole or in part.

Abstract: A filter system for filtering intake air of a gas turbine is presented. The filter system includes a first filter arrangement. The filter system further includes a second filter arrangement located downstream from the first filter arrangement and having a collection efficiency higher than a collection efficiency the first filter arrangement. Furthermore, the filter system includes a guard filter arrangement located between the first filter arrangement and the second filter arrangement, where a collection efficiency of the guard filter arrangement is lower than the collection efficiency of the first filter arrangement.

Abstract: Aspects of the disclosure include methods and systems for the de-icing of pulse filters, such as those used in turbomachinery. A method according to the present disclosure can include: coupling a filter bag to the pulse filter such that the filter bag is in a contracted position, the filter bag having a complementary geometry relative to the pulse filter, such that the filter bag occupies an airflow cross-section of the pulse filter, and wherein the filter bag is composed of one of a hydrophilic material, a hydrophobic material, or an oleophobic material; and pulsing a compressed air through the pulse filter and the filter bag during operation of the gas turbine, such that the filter bag expands to dislodge ice from an outer surface of the filter bag.

Abstract: A filtering chamber for a gas turbine having a combustor, compressor and air inlet duct, and a corresponding maintenance method is described. The filtering chamber includes a first chamber in an inlet plenum; a second chamber in the inlet plenum; and an air bypass mechanism configured to reduce a pressure difference across a final filter that separates the first chamber from the second chamber.

Abstract: A method for predicting the residual useful life of an air filter arrangement is described. The method comprises the following steps: providing a plurality of predetermined reference degradation curves; measuring a degradation parameter of the filter arrangement; estimating the residual useful life of the filter arrangement by comparing the predetermined reference degradation curves and an actual degradation curve defined by measured values of the degradation parameter.

Abstract: An inlet air filter device including: at least one passage for delivering an air mass from an inlet section to an outlet section of the inlet air filter device, a water separator in the at least one passage for separating water in the air mass, the water separator positioned between the inlet section and the outlet section, a bypass element movable between a first open position in which the air mass is forced to cross the water separator and a second closed position in which the air mass flows from the inlet to the outlet section without crossing the water separator; a shutter element which is actuatable to co-operate with the bypass element for isolating the water separator from the air mass when the bypass element is in the second closed position.

Abstract: A system for testing at least one air filter element is provided. The system includes a test rig, wherein the test rig includes an elongated duct, and at least one measurement device coupled to the duct. The at least one measurement device is configured to measure at least one characteristic representative of a condition within the duct. At least one air filter element is coupled within the test rig. At least one first salt spray test is performed on the at least one air filter element. The collected salt spray water and equivalent amount of dry salt remaining in the test rig are quantified. At least one second salt spray test is performed on the at least one air filter element, wherein the at least one air filter element is dust loaded prior to the at least one second salt spray test.

Abstract: A filter system for filtering intake air of a gas turbine, comprising a first filter arrangement and a second filter arrangement, located downstream from the first filter arrangement and having a higher collection efficiency than the first filter arrangement. Furthermore, a guard filter arrangement, having a lower collection efficiency than the first filter arrangement, is located between the first filter arrangement and the second filter arrangement.

Abstract: The present application provides a pulse filtration system for use with a compressor of a gas turbine engine. The pulse filtration system may include a pulse filter, a compressed air system in communication with the pulse filter, and a hydrophobic filter bag surrounding the pulse filter in whole or in part.

Abstract: The present application provides a pulse filtration system for use with a compressor of a gas turbine engine. The pulse filtration system may include a pulse filter, a compressed air system in communication with the pulse filter, and a filter bag surrounding the pulse filter in whole or in part.

Abstract: A filtering chamber for a gas turbine having a combustor, compressor and air inlet duct, and a corresponding maintenance method is described. The filtering chamber includes a first chamber in an inlet plenum; a second chamber in the inlet plenum; and an air bypass mechanism configured to reduce a pressure difference across a final filter that separates the first chamber from the second chamber.

Abstract: Methods of testing gas turbine filter elements under high or low temperature operating environments are provided. In one aspect, the method includes performing a fractional efficiency test on a filter. The method also includes heating or cooling the filter to a temperature that is higher or lower than an ambient temperature. The method further includes performing a second fractional efficiency test on the filter after the filter has been heated or cooled for a period of time at the temperature.

Abstract: A system for testing at least one air filter element is provided. The system includes a test rig, wherein the test rig includes an elongated duct, and at least one measurement device coupled to the duct. The at least one measurement device is configured to measure at least one characteristic representative of a condition within the duct. At least one air filter element is coupled within the test rig. At least one first salt spray test is performed on the at least one air filter element. The collected salt spray water and equivalent amount of dry salt remaining in the test rig are quantified. At least one second salt spray test is performed on the at least one air filter element, wherein the at least one air filter element is dust loaded prior to the at least one second salt spray test.

Abstract: An inlet air filter device including: at least one passage for delivering an air mass from an inlet section to an outlet section of the inlet air filter device, a water separator in the at least one passage for separating water in the air mass, the water separator positioned between the inlet section and the outlet section, a bypass element movable between a first open position in which the air mass is forced to cross the water separator and a second closed position in which the air mass flows from the inlet to the outlet section without crossing the water separator; a shutter element which is actuatable to co-operate with the bypass element for isolating the water separator from the air mass when the bypass element is in the second closed position

Abstract: A power plant including a thermal machine, an inlet duct for delivering a combustive first fluid in said thermal machine, a ventilation circuit for delivering a cooling second fluid to said thermal machine, the first and/or the second fluid including water therein, and a water recovery device connected with the inlet duct and/or the ventilation circuit for condensing and collecting said water from the first and/or the second fluid, the water recovery device being associated with at least one heat exchanger thermally connected with the inlet duct and/or the ventilation circuit for cooling said first and/or said second fluid beyond the dew point thereof, the water recovery device further including connecting means for delivering the water condensed from the first and/or the second fluid to a water using device.

Abstract: A hull structure of nonmetallic material, in particular of a reinforced plastics material, for boats, ships, minesweepers and the like includes a preferably one-piece shell (1) and at least one deck (2, 2'). A plurality of ribs (3) are distributed along the length of the hull and extend across the corresponding transverse section of the shell (1). A plurality of transverse members (4, 4') (known as beams) extend directly underneath the deck (2, 2'). In order to give the hull greater structural strength and make it lighter, each transverse rib (3) joined to the shell (1) is connected (103, 203) to a corresponding transverse member (4, 4') joined to the deck (2, 2') and to continuous fore and aft members (15) (girders) passing in the manner of bulkheads, so as to form a single one-piece frame with the keel member.

Abstract: An induction conduit in an internal combustion engine cylinder head is formed with an appendage of rectangular section extending parallel to the axis of a valve stem at the end of the conduit adjacent the valve seat and disposed in a radial plane inclined to the transverse axis of the valve parallel to the engine shaft at an angle of between 0.degree. and 45.degree. to assist in reducing the turbulence in the inducted air due to centrifugal motion. The lower face of the appendage can be machined to regulate the degree of turbulence.