Abstract: A negative pressure wound dressing for use with breast incisions. The wound dressing includes a drape layer, a manifold layer, a base layer, and a reduced pressure interface. The drape layer has a first surface and a second, wound-facing, surface. The drape layer is substantially impermeable to liquid and substantially permeable to vapor. The manifold layer has a first surface and a second, wound-facing surface. The manifold layer has a perimeter defined by a first convex curved side surface defining a first lobe, a second convex curved side surface defining a second lobe, and a connecting portion between the first lobe and the second lobe. The base layer is configured to: (i) couple the drape layer to the manifold layer, and (ii) the dressing to a patient's tissue. The reduced pressure interface is integrated with the drape layer.

Abstract: A method for designing a system implementing model-based system engineering with maintenance forecasting may utilize a systems model and a maintenance forecast model. The systems model receives an initial systems design, generates an initial set of system design specifications based on the initial systems design, generates an initial concept of operations based on the initial systems design, and outputs the initial set of system design specifications and the initial concept of operations to the maintenance forecast model. The maintenance forecast model determines a first maintenance prediction for the initial systems design based on the initial set of system design specifications and the initial concept of operations received from the systems model. The systems model then receives the first maintenance prediction from the maintenance forecast model, and creates a first updated systems design based on the first maintenance prediction.

Abstract: A combustor wall assembly has a heat shield and a supporting shell with a cooling cavity defined therebetween. A grommet generally includes a wall defining a dilution hole isolated from the cooling cavity, and a flange projecting radially outward from the wall and into the cooling cavity. The flange is space from the heat shield and a cooling channel is defined between the wall and the heat shield that communicates with the cavity for cooling the wall proximate to a combustion chamber.

Abstract: A curvic seal for a gas turbine engine includes a cylindrical seal with a retention feature.

Abstract: A curvic seal for a gas turbine engine includes a cylindrical seal with a retention feature.

Abstract: A combustor wall assembly has a heat shield and a supporting shell with a cooling cavity defined therebetween. A grommet generally includes a wall defining a dilution hole isolated from the cooling cavity, and a flange projecting radially outward from the wall and into the cooling cavity. The flange is space from the heat shield and a cooling channel is defined between the wall and the heat shield that communicates with the cavity for cooling the wall proximate to a combustion chamber.

Abstract: A combustor component defining a dilution hole configuration for a combustor wall assembly of a gas turbine engine has first and second dilution holes that communicate radially with one-another and with respect to respective centerlines of each dilution hole. In operation, each dilution hole forms a respective jet stream along respective centerlines for flowing cooling air into a combustion chamber.

Abstract: A combustor wall assembly has a heat shield and a supporting shell with a cooling cavity defined therebetween. A grommet generally includes a wall defining a dilution hole isolated from the cooling cavity, and a flange projecting radially outward from the wall and into the cooling cavity. The flange is space from the heat shield and a cooling channel is defined between the wall and the heat shield that communicates with the cavity for cooling the wall proximate to a combustion chamber.

Abstract: A thermally compliant grommet assembly for a combustor includes first and second shells spaced apart from one another and a grommet having a tubular portion projecting into a hole in the second shell and defining a bore in fluid communication through the first and second shells. The grommet further has an oblong flange portion extending circumferentially around and projecting outward from the tubular portion. The oblong flange portion is located between and is in sealing contact with the first and second shells. At least one of the first and second shells is constructed and arranged to move between cold and hot states and generally along a thermal displacement path. The oblong flange portion is generally elongated along the path to maintain sealing contact with at least one of the shells as the shells move between the hot and cold states.

Abstract: A disk-seal arrangement for a gas turbine engine rotor includes a blade retention disk having a longitudinally opening slot therein and a seal disk juxtaposed to said blade retention disk and a single anti-rotation tab received within the blade retention disk slot. The seal disk also includes a pair of balance slots disposed immediately adjacent the antirotation tab to offset the weight thereof for preserving rotor balance. A split ring is disposed longitudinally between the blade retention and seal disks for reacting longitudinal loading therebetween. The ends of the split ring seat against side surfaces of the antirotation between the split ring and the blade retention and seal disks.

Abstract: A conjoined grommet assembly for a combustor wall assembly of a gas turbine engine has a first grommet defining at least in-part a first dilution hole, and a second grommet defining at least in-part a second dilution hole. The first and second dilution holes are spaced closely together such that the first grommet is in contact with the second grommet.

Abstract: A curvic seal for a gas turbine engine includes a cylindrical seal with a retention feature.

Abstract: A combustor component defining a dilution hole configuration for a combustor wall assembly of a gas turbine engine has first and second dilution holes that communicate radially with one-another and with respect to respective centerlines of each dilution hole. In operation, each dilution hole forms a respective jet stream along respective centerlines for flowing cooling air into a combustion chamber.

Abstract: A combustor wall assembly has a heat shield and a supporting shell with a cooling cavity defined therebetween. A grommet generally includes a wall defining a dilution hole isolated from the cooling cavity, and a flange projecting radially outward from the wall and into the cooling cavity. The flange is space from the heat shield and a cooling channel is defined between the wall and the heat shield that communicates with the cavity for cooling the wall proximate to a combustion chamber.

Abstract: A conjoined grommet assembly for a combustor wall assembly of a gas turbine engine has a first grommet defining at least in-part a first dilution hole, and a second grommet defining at least in-part a second dilution hole. The first and second dilution holes are spaced closely together such that the first grommet is in contact with the second grommet.

Abstract: A thermally compliant grommet assembly for a combustor includes first and second shells spaced apart from one another and a grommet having a tubular portion projecting into a hole in the second shell and defining a bore in fluid communication through the first and second shells. The grommet further has an oblong flange portion extending circumferentially around and projecting outward from the tubular portion. The oblong flange portion is located between and is in sealing contact with the first and second shells. At least one of the first and second shells is constructed and arranged to move between cold and hot states and generally along a thermal displacement path. The oblong flange portion is generally elongated along the path to maintain sealing contact with at least one of the shells as the shells move between the hot and cold states.