Abstract: Aspects presented herein may enable a tracking device to disable its transmitter based on determining whether the wireless device is within the vicinity or a threshold distance of an airport and/or based on information or measurements obtained from its modem receiver. In one aspect, a wireless device detects whether the wireless device is within a threshold distance of a target location or whether the wireless device is airborne. The wireless device disables a transmitter of the wireless device based on detecting that the wireless device is within the threshold distance of the target location or that the wireless device is airborne.

Abstract: A probe cooling system for a gas turbine engine includes a probe housing and a bushing disposed between an end of the probe housing and a gas path, the bushing extending from the end of the probe housing to form a cavity. The system also includes a first plenum defined within the probe housing and configured to direct air from an internal cooling air supply towards the cavity. The system also includes a second plenum defined between the bushing and the probe housing and configured to direct air from the internal cooling air supply towards the cavity.

Abstract: A probe cooling system for a gas turbine engine includes a probe housing and a bushing disposed between an end of the probe housing and a gas path, the bushing extending from the end of the probe housing to form a cavity. The system also includes a first plenum defined within the probe housing and configured to direct air from an internal cooling air supply towards the cavity. The system also includes a second plenum defined between the bushing and the probe housing and configured to direct air from the internal cooling air supply towards the cavity.

Abstract: An assembly for preventing rotation of a damper in a stator system includes a slot in the damper and a block for engaging the slot to prevent rotation of the damper. The block is positioned within a groove located at a mid span portion of an inner air seal.

Abstract: A cast assembly for a gas turbine engine compressor, the compressor including a plurality of axial flow stators and a rotor having a plurality of axial flow blades, each of the blades having a tip section and a leading edge. The assembly comprises a stator outer platform, a boss, a passage, a blade outer shroud and a circumferential slot. A boss is formed in the platform and includes a passage. The passage includes an inlet and an outlet. The inlet is disposed in the circumferential slot. The outlet being disposed upstream of the leading edge of the blades. The passage circumferentially converges inward from the inlet to the outlet. The outer shroud joins with said outer platform during the assembly of the compressor such that the circumferential slot is formed downstream and proximate to the leading edge of the blades. The circumferential slot is in flow communication with the inlet and converges axially.

Abstract: The present invention relates to an assembly for preventing rotation of a damper in a stator system. The rotation preventing assembly comprises a slot in the damper and a block for engaging the slot to prevent rotation of the damper. The block is positioned within a groove located at a mid span portion of an inner air seal.

Abstract: A cast assembly for a gas turbine engine compressor, the compressor including a plurality of axial flow stators and a rotor having a plurality of axial flow blades, each of the blades having a tip section and a leading edge. The assembly comprises a stator outer platform, a boss, a passage, a blade outer shroud and a circumferential slot. A boss is formed in the platform and includes a passage. The passage includes an inlet and an outlet. The inlet is disposed in the circumferential slot. The outlet being disposed upstream of the leading edge of the blades. The passage circumferentially converges inward from the inlet to the outlet. The outer shroud joins with said outer platform during the assembly of the compressor such that the circumferential slot is formed downstream and proximate to the leading edge of the blades. The circumferential slot is in flow communication with the inlet and converges axially.