Abstract: Methods, devices and systems are disclosed for inter-app communications between software applications on a mobile communications device. In one aspect, a computer-readable medium on a mobile computing device comprising an inter-application communication data structure to facilitate transitioning and distributing data between software applications in a shared app group for an operating system of the mobile computing device includes a scheme field of the data structure providing a scheme id associated with a target software app to transition to from a source software app, wherein the scheme id is listed on a scheme list stored with the source software app; and a payload field of the data structure providing data and/or an identification where to access data in a shared file system accessible to the software applications in the shared app group, wherein the payload field is encrypted.

Abstract: Methods, devices and systems are disclosed for inter-app communications between software applications on a mobile communications device. In one aspect, a computer-readable medium on a mobile computing device comprising an inter-application communication data structure to facilitate transitioning and distributing data between software applications in a shared app group for an operating system of the mobile computing device includes a scheme field of the data structure providing a scheme id associated with a target software app to transition to from a source software app, wherein the scheme id is listed on a scheme list stored with the source software app; and a payload field of the data structure providing data and/or an identification where to access data in a shared file system accessible to the software applications in the shared app group, wherein the payload field is encrypted.

Abstract: An airfoil cooling system may be provided. An airfoil may have a pressure side and a suction side that are separated by a leading edge. The leading edge may pass through a stagnation point of the airfoil. A spar may have an outer surface comprising standoffs. The standoffs may define a cooling channel that extends across the leading edge on the outer surface of the spar, from the pressure side to the suction side. The cooling channel may have a first portion and a second portion defined by the standoffs. The first portion may be located closer to a base or a tip of the airfoil than the second portion. The spar may further comprise an inlet on the pressure side or the suction side. The inlet may be configured to convey a cooling fluid from a passageway located inside of the spar to the cooling channel.

Abstract: An airfoil cooling system may be provided. An airfoil may have a pressure side and a suction side that are separated by a leading edge. The leading edge may pass through a stagnation point of the airfoil. A spar may have an outer surface comprising standoffs. The standoffs may define a cooling channel that extends across the leading edge on the outer surface of the spar, from the pressure side to the suction side. The cooling channel may have a first portion and a second portion defined by the standoffs. The first portion may be located closer to a base or a tip of the airfoil than the second portion. The spar may further comprise an inlet on the pressure side or the suction side. The inlet may be configured to convey a cooling fluid from a passageway located inside of the spar to the cooling channel.

Abstract: An airfoil cooling system may be provided. An airfoil may have a pressure side and a suction side that are separated by a leading edge. The leading edge may pass through a stagnation point of the airfoil. A spar may have an outer surface comprising standoffs. The standoffs may define a cooling channel that extends across the leading edge on the outer surface of the spar, from the pressure side to the suction side. The cooling channel may have a first portion and a second portion defined by the standoffs. The first portion may be located closer to a base or a tip of the airfoil than the second portion. The spar may further comprise an inlet on the pressure side or the suction side. The inlet may be configured to convey a cooling fluid from a passageway located inside of the spar to the cooling channel.

Abstract: An airfoil with dual wall cooling for a gas turbine engine comprises a spar having pressure and suction side walls that meet at leading and trailing edges of the airfoil, with a tip extending therebetween. An interior of the spar includes a coolant cavity, and each of the pressure and suction side walls includes an arrangement of pedestals on an outer surface thereof and a plurality of cooling holes in fluid communication with the coolant cavity. A pressure side coversheet overlies the pressure side wall and terminates in a radial direction short of the tip of the spar to form a shelf extending along a chordal direction. Flow channels between the pressure side wall and coversheet are configured to direct coolant from the cooling holes to radial flow outlets adjacent to the shelf. A suction side coversheet overlies the suction side wall, and a coolant circuit between the suction side wall and coversheet does not include radial coolant outlets.

Abstract: An airfoil cooling system may be provided. An airfoil may have a pressure side and a suction side that are separated by a leading edge. The leading edge may pass through a stagnation point of the airfoil. A spar may have an outer surface comprising standoffs. The standoffs may define a cooling channel that extends across the leading edge on the outer surface of the spar, from the pressure side to the suction side. The cooling channel may have a first portion and a second portion defined by the standoffs. The first portion may be located closer to a base or a tip of the airfoil than the second portion. The spar may further comprise an inlet on the pressure side or the suction side. The inlet may be configured to convey a cooling fluid from a passageway located inside of the spar to the cooling channel.

Abstract: An airfoil with dual wall cooling for a gas turbine engine comprises a spar having pressure and suction side walls that meet at leading and trailing edges of the airfoil, with a tip extending therebetween. An interior of the spar includes a coolant cavity, and each of the pressure and suction side walls includes an arrangement of pedestals on an outer surface thereof and a plurality of cooling holes in fluid communication with the coolant cavity. A pressure side coversheet overlies the pressure side wall and terminates in a radial direction short of the tip of the spar to form a shelf extending along a chordal direction. Flow channels between the pressure side wall and coversheet are configured to direct coolant from the cooling holes to radial flow outlets adjacent to the shelf. A suction side coversheet overlies the suction side wall, and a coolant circuit between the suction side wall and coversheet does not include radial coolant outlets.

Abstract: A check valve assembly for the forced gas cooling system of a vacuum heat treating furnace is disclosed. The check valve assembly includes a check valve for installation on the exterior of a hot zone wall in a vacuum heat treating furnace. The check valve includes a valve body forming an inlet, an outlet, and a channel extending longitudinally through the valve body. The valve body has an inner wall that forms a recess near the inlet. The channel contains a flap pivotally supported on a shaft that extends through the recess. The flap pivots in and out of the channel to permit a cooling gas to flow through the valve body in one direction while substantially preventing the flow of gas through the valve body in the opposite direction. The flap is operable between a closed position in which the flap extends into the channel to obstruct the channel, and an open position in which the flap is pivoted out of the channel and into the recess.