Abstract: An inlet duct for a gas turbine engine includes a particle separator, a scavenge duct, and a layer of material having a low coefficient of restitution. The particle separator including an outer wall spaced, an inner wall, and a splitter located radially between the outer wall and the inner wall. The scavenge duct is coupled with particle separator. The layer of material is located on at least one of the outer wall, the splitter, and the scavenge duct.

Abstract: An inlet duct for a gas turbine engine includes a particle separator, a scavenge duct, and a layer of material having a low coefficient of restitution. The particle separator including an outer wall spaced, an inner wall, and a splitter located radially between the outer wall and the inner wall. The scavenge duct is coupled with particle separator. The layer of material is located on at least one of the outer wall, the splitter, and the scavenge duct.

Abstract: A microchannel heat exchanger (MCHX) includes an air-passage layer including a plurality of air-passage microchannels, a working fluid layer including a plurality of working fluid microchannels, and a sealing layer coupled to the working fluid layer to provide a working/sealing layer set. The working/sealing layer set includes an arrangement of raised pedestals. The raised pedestals may extend from the working fluid layer to the sealing layer and contact the sealing layer.

Abstract: Devices, systems, and methods of a casing for a heat suppression system of a gas turbine engine exhaust include a heat shield and an insulation layer for arrangement between the heat shield and an outer skin.

Abstract: Devices, systems, and methods of a casing for a heat suppression system of a gas turbine engine exhaust include a heat shield and an insulation layer for arrangement between the heat shield and an outer skin.

Abstract: A microchannel heat exchanger (MCHX) includes an air-passage layer including a plurality of air-passage microchannels, a working fluid layer including a plurality of working fluid microchannels, and a sealing layer coupled to the working fluid layer to provide a working/sealing layer set. The working/sealing layer set includes an arrangement of raised pedestals. The raised pedestals may extend from the working fluid layer to the sealing layer and contact the sealing layer.

Abstract: Devices, systems, and methods of a casing for a heat suppression system of a gas turbine engine exhaust include a floating heat shield.

Abstract: A gas turbine engine heat exchange system includes a first microchannel heat exchanger (MCHX) configured to transfer heat between a first air stream and a working fluid. The first MCHX includes a plurality of air-passage layers. Each of the air-passage layers includes a plurality of etched air-passage microchannels that are configured to allow passage of the first air stream therethrough. The first MCHX also includes a plurality of working fluid layers. Each working fluid layer includes a plurality of etched working fluid microchannels that are configured to allow passage of the working fluid therethrough.

Abstract: A gas turbine engine heat exchange system including a first multi-width channel heat exchanger (MWCHX) configured to transfer heat between a first air stream and a heat transfer fluid. The first MWCHX includes a first plurality of air-passage mini-channels configured to allow passage of the first air stream therethrough, where each air-passage channel has an air-channel width and an air-channel length greater than the air-channel width. The MWCHX also includes a first plurality of heat transfer fluid channels configured to allow passage of the heat transfer fluid therethrough, where each heat transfer fluid channel has a heat transfer channel width and a heat transfer channel length greater than the heat transfer channel width. The heat transfer channel width is less than the air-channel width.

Abstract: Devices, systems, and methods of a casing for a heat suppression system of a gas turbine engine exhaust include a floating heat shield.

Abstract: An improved system, apparatus and method for intercooling a turbo fan engine, and more specifically, a system for intercooling a turbo fan engine employing a secondary bypass duct that minimizes pressure losses. The secondary bypass duct is radially inwardly disposed from a fan bypass duct and receives fan bypass air through an inlet. The portion of fan bypass air flows through one or more microchannel or minichannel heat exchangers. The secondary bypass duct has an outlet in communication with the bypass air stream downstream of the throat of a fan bypass nozzle. The secondary bypass air is accelerated at the exit to create thrust.

Abstract: A gas turbine engine variable porosity combustor liner has a laminated alloy structure. The laminated alloy structure has combustion chamber facing holes on one side and cooling plenum facing holes on a radially opposite side. The combustion chamber facing holes are in fluid communication with the cooling plenum facing holes via axially and circumferentially extending flow passages sandwiched between metal alloy sheets of the laminated alloy structure. Porous zones having respective different cooling flow amounts are formed in the laminated allow structure based on at least one of an arrangement of the combustion chamber facing holes, an arrangement of the cooling plenum facing holes, and an arrangement of the flow passages.

Abstract: A combustion chamber includes an inner wall, an outer wall surrounding the inner wall, and a flow passage between the inner wall and outer wall that permits forward flow and restricts reverse flow. The inner wall has a plurality of effusion holes in fluid communication with the inside of the combustion chamber. The outer wall has a plurality of cooling side holes in fluid communication with a cooling source. The inner wall and the outer wall define a flow passage therebetween that fluidly connects one or more of the cooling side holes with one or more of the effusion holes. The flow passage has a geometric configuration to permit forward flow of gases through the flow passage from the cooling source to the inside of the combustion chamber and to restrict reverse flow of gases through the flow passage from the inside of the combustion chamber to the cooling source. The permitted flow rate is greater than the restricted flow rate.

Abstract: A turbine engine includes a fan that provides an air flow to the turbine engine as compressor intake air and as compressor bypass air, a first stage compressor positioned to receive the compressor intake air and output a first stage compressed air, and a boiler positioned to cool the first stage compressed air using a fluid. A second stage compressor is positioned to receive the cooled first stage compressed air. A pump is configured to pump the fluid as a liquid into the boiler, extract energy from the first stage compressed air, and cause the cooling of the first stage compressed air.

Abstract: An improved system, apparatus and method for intercooling a turbo fan engine, and more specifically, a system for intercooling a turbo fan engine employing a secondary bypass duct that minimizes pressure losses. The secondary bypass duct is radially inwardly disposed from a fan bypass duct and receives fan bypass air through an inlet. The portion of fan bypass air flows through one or more microchannel or minichannel heat exchangers. The secondary bypass duct has an outlet in communication with the bypass air stream downstream of the throat of a fan bypass nozzle. The secondary bypass air is accelerated at the exit to create thrust.

Abstract: A gas turbine engine heat exchange system includes a first microchannel heat exchanger (MCHX) configured to transfer heat between a first air stream and a working fluid. The first MCHX includes a plurality of air-passage layers. Each of the air-passage layers includes a plurality of etched air-passage microchannels that are configured to allow passage of the first air stream therethrough. The first MCHX also includes a plurality of working fluid layers. Each working fluid layer includes a plurality of etched working fluid microchannels that are configured to allow passage of the working fluid therethrough.

Abstract: A gas turbine engine heat exchange system including a first multi-width channel heat exchanger (MWCHX) configured to transfer heat between a first air stream and a heat transfer fluid. The first MWCHX includes a first plurality of air-passage mini-channels configured to allow passage of the first air stream therethrough, where each air-passage channel has an air-channel width and an air-channel length greater than the air-channel width. The MWCHX also includes a first plurality of heat transfer fluid channels configured to allow passage of the heat transfer fluid therethrough, where each heat transfer fluid channel has a heat transfer channel width and a heat transfer channel length greater than the heat transfer channel width. The heat transfer channel width is less than the air-channel width.

Abstract: A gas turbine engine variable porosity combustor liner has a laminated alloy structure. The laminated alloy structure has combustion chamber facing holes on one side and cooling plenum facing holes on a radially opposite side. The combustion chamber facing holes are in fluid communication with the cooling plenum facing holes via axially and circumferentially extending flow passages sandwiched between metal alloy sheets of the laminated alloy structure. Porous zones having respective different cooling flow amounts are formed in the laminated allow structure based on at least one of an arrangement of the combustion chamber facing holes, an arrangement of the cooling plenum facing holes, and an arrangement of the flow passages.

Abstract: A turbine engine includes a fan that provides an air flow to the turbine engine as compressor intake air and as compressor bypass air, a first stage compressor positioned to receive the compressor intake air and output a first stage compressed air, and a boiler positioned to cool the first stage compressed air using a fluid. A second stage compressor is positioned to receive the cooled first stage compressed air. A pump is configured to pump the fluid as a liquid into the boiler, extract energy from the first stage compressed air, and cause the cooling of the first stage compressed air.

Abstract: A combustion chamber includes an inner wall, an outer wall surrounding the inner wall, and a flow passage between the inner wall and outer wall that permits forward flow and restricts reverse flow. The inner wall has a plurality of effusion holes in fluid communication with the inside of the combustion chamber. The outer wall has a plurality of cooling side holes in fluid communication with a cooling source. The inner wall and the outer wall define a flow passage therebetween that fluidly connects one or more of the cooling side holes with one or more of the effusion holes. The flow passage has a geometric configuration to permit forward flow of gases through the flow passage from the cooling source to the inside of the combustion chamber and to restrict reverse flow of gases through the flow passage from the inside of the combustion chamber to the cooling source. The permitted flow rate is greater than the restricted flow rate.