Abstract: The invention relates to a human mobility measuring method comprising a structuring step where CDR raw metadata is filtered so as to identify a device identification, a cell site identification, a date, and a time; a data frame generating and sorting step where the filtered CDR metadata is sorted and the filtered sorted CDR metadata are projected into an occupancy grid comprising a location vs. time-bin matrix, a probabilistic map generating step of a device's location in space and time, and a filtering step to accurately represent human mobility from patterns that reflect errors, uncertainties, or patterns not related with real human mobility. The method further comprises a gap filling process allowing for a continuous localization of the device by extrapolating any trajectory in space and time of any device and a projecting step comprising projecting the trajectories defined at a Voronoi grid defined by the sites and towers to the road and street grid.

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that has an internal wall and an external wall. The external wall defines pressure and suction sides that extends in a chordwise direction between a leading edge and a trailing edge, a first impingement cavity and a second impingement cavity bounded by the external wall at a leading edge region that defines the leading edge. A first crossover passage within the internal wall is connected to the first impingement. The first crossover passage defines a first passage axis that intersects a surface of the first impingement cavity. A second crossover passage within the internal wall is connected to the second impingement cavity. The second crossover passage defines a second passage axis that intersects a surface of the second impingement cavity.

Abstract: A balance bracket for a diffuser case of gas turbine engine is disclosed. In various embodiments, the balance bracket includes a first portion configured for mounting to a first boss on the diffuser case, a second portion configured for mounting to a second boss on the diffuser case, the second portion spaced a distance from the first portion, and a first undulating portion positioned intermediate the first portion and the second portion.

Abstract: A cooling structure for a gas turbine engine comprises a gas turbine engine structure defining a cooling cavity. A cooling component is configured to direct cooling flow in a desired direction into the cooling cavity. A bracket supports the cooling component and has an attachment interface to fix the bracket to the gas turbine engine structure. A first orientation feature associated with the bracket. A second orientation feature is associated with the gas turbine engine structure. The first and second orientation features cooperate with each other to ensure that the cooling component is only installed in one orientation relative to the gas turbine engine structure. A gas turbine engine and a method of installing a cooling structure are also disclosed.

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that has an internal wall and an external wall. The external wall defines pressure and suction sides that extends in a chordwise direction between a leading edge and a trailing edge, a first impingement cavity and a second impingement cavity bounded by the external wall at a leading edge region that defines the leading edge. A first crossover passage within the internal wall is connected to the first impingement. The first crossover passage defines a first passage axis that intersects a surface of the first impingement cavity. A second crossover passage within the internal wall is connected to the second impingement cavity. The second crossover passage defines a second passage axis that intersects a surface of the second impingement cavity.

Abstract: An airfoil according to an example of the present disclosure includes, among other things, an internal wall and an external wall. The external wall defines pressure and suction sides between a leading edge and a trailing edge, and the airfoil section defines a mean camber line that extends between the leading and trailing edges to bisect a thickness of the airfoil section. A first cavity and a second cavity are separated by the internal wall. The second cavity is bounded by the external wall at the leading edge. At least one crossover passage within the internal wall connects the first cavity to the second cavity. The crossover passage defines a passage axis. The passage axis defines a passage angle with respect to the mean camber line such that the passage axis extends transversely from the mean camber line to intersect a surface of the second cavity.

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that has an internal wall and an external wall. The external wall defines pressure and suction sides that extends in a chordwise direction between a leading edge and a trailing edge, a first impingement cavity and a second impingement cavity bounded by the external wall at a leading edge region that defines the leading edge, a first feeding cavity separated from the first impingement cavity and from the second impingement cavity by the internal wall, and a first crossover passage within the internal wall that connects the first impingement cavity and the first feeding cavity. The first crossover passage defines a first passage axis that intersects a surface of the first impingement cavity. A second crossover passage within the internal wall connects to the second impingement cavity.

Abstract: An airfoil according to an example of the present disclosure includes, among other things, an internal wall and an external wall. The external wall defines pressure and suction sides between a leading edge and a trailing edge, and the airfoil section defines a mean camber line that extends between the leading and trailing edges to bisect a thickness of the airfoil section. A first cavity and a second cavity are separated by the internal wall. The second cavity is bounded by the external wall at the leading edge. At least one crossover passage within the internal wall connects the first cavity to the second cavity. The crossover passage defines a passage axis. The passage axis defines a passage angle with respect to the mean camber line such that the passage axis extends transversely from the mean camber line to intersect a surface of the second cavity.

Abstract: A balance bracket for a diffuser case of gas turbine engine is disclosed. In various embodiments, the balance bracket includes a first portion configured for mounting to a first boss on the diffuser case, a second portion configured for mounting to a second boss on the diffuser case, the second portion spaced a distance from the first portion, and a first undulating portion positioned intermediate the first portion and the second portion.

Abstract: An airfoil according to an example of the present disclosure includes, among other things, an internal wall and an external wall. The external wall defines pressure and suction sides between a leading edge and a trailing edge, and the airfoil section defines a mean camber line that extends between the leading and trailing edges to bisect a thickness of the airfoil section. A first cavity and a second cavity are separated by the internal wall. The second cavity is bounded by the external wall at the leading edge. At least one crossover passage within the internal wall connects the first cavity to the second cavity. The crossover passage defines a passage axis. The passage axis defines a passage angle with respect to the mean camber line such that the passage axis extends transversely from the mean camber line to intersect a surface of the second cavity.

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that has an internal wall and an external wall. The external wall defines pressure and suction sides that extends in a chordwise direction between a leading edge and a trailing edge, a first impingement cavity and a second impingement cavity bounded by the external wall at a leading edge region that defines the leading edge, a first feeding cavity separated from the first impingement cavity and from the second impingement cavity by the internal wall, and a first crossover passage within the internal wall that connects the first impingement cavity and the first feeding cavity. The first crossover passage defines a first passage axis that intersects a surface of the first impingement cavity. A second crossover passage within the internal wall connects to the second impingement cavity.

Abstract: Combustor panel bodies with first and second sides, a pin array of cooling pins extending from the first side, with each pin extending a first height from the first side and having a pin diameter, each pin separated from adjacent pins by a pin array separation distance. A structural protrusion extending from the first side with no pins located at a position within a flashing distance that is equal to a protrusion separation distance plus one half of the pin diameter. A location of the pin is measured from a center point of the pin to a closest point on the exterior surface of the structural protrusion. A pin array scallop is integrally formed with the structural protrusion forming a reduction in material such that each pin of the array that is closest to the structural protrusion is positioned the pin array separation distance from the structural protrusion.

Abstract: An airfoil according to an example of the present disclosure includes, among other things, an internal wall and an external wall. The external wall defines pressure and suction sides between a leading edge and a trailing edge, and the airfoil section defines a mean camber line that extends between the leading and trailing edges to bisect a thickness of the airfoil section. A first cavity and a second cavity are separated by the internal wall. The second cavity is bounded by the external wall at the leading edge. At least one crossover passage within the internal wall connects the first cavity to the second cavity. The crossover passage defines a passage axis. The passage axis defines a passage angle with respect to the mean camber line such that the passage axis extends transversely from the mean camber line to intersect a surface of the second cavity.

Abstract: Combustor panel bodies with first and second sides, a pin array of cooling pins extending from the first side, with each pin extending a first height from the first side and having a pin diameter, each pin separated from adjacent pins by a pin array separation distance. A structural protrusion extending from the first side with no pins located at a position within a flashing distance that is equal to a protrusion separation distance plus one half of the pin diameter. A location of the pin is measured from a center point of the pin to a closest point on the exterior surface of the structural protrusion. A pin array scallop is integrally formed with the structural protrusion forming a reduction in material such that each pin of the array that is closest to the structural protrusion is positioned the pin array separation distance from the structural protrusion.

Abstract: A cooling structure for a gas turbine engine comprises a gas turbine engine structure defining a cooling cavity. A cooling component is configured to direct cooling flow in a desired direction into the cooling cavity. A bracket supports the cooling component and has an attachment interface to fix the bracket to the gas turbine engine structure. A first orientation feature associated with the bracket. A second orientation feature is associated with the gas turbine engine structure. The first and second orientation features cooperate with each other to ensure that the cooling component is only installed in one orientation relative to the gas turbine engine structure. A gas turbine engine and a method of installing a cooling structure are also disclosed.

Abstract: A tie rod assembly for a mid-turbine frame includes at least one tie rod for connecting an outer frame case to an inner frame case. At least one tie rod includes an inlet passage that branches into a first branch and a second branch. A plug is located in the first branch to block flow through a portion of the first branch.

Abstract: A cooling structure for a gas turbine engine comprises a gas turbine engine structure defining a cooling cavity. A cooling component is configured to direct cooling flow in a desired direction into the cooling cavity. A bracket supports the cooling component and has an attachment interface to fix the bracket to the gas turbine engine structure. A first orientation feature associated with the bracket. A second orientation feature is associated with the gas turbine engine structure. The first and second orientation features cooperate with each other to ensure that the cooling component is only installed in one orientation relative to the gas turbine engine structure. A gas turbine engine and a method of installing a cooling structure are also disclosed.

Abstract: A mid-turbine frame for a gas turbine engine includes an inner frame case that includes a fluid passage. At least one spoke includes an inlet passage with at least one branch extending in an axial direction in fluid communication with the fluid passage in the inner frame case. A fitting fluidly connects the at least one branch to the fluid passage in the inner frame case. The fitting also includes a transfer tube connecting the cooling airflow passage to a cup boss. The transfer tube is fixed relative to the cylindrical portion and moveable relative to the cup boss. A swirler tube is in fluid communication with the fluid passage and is configured to direct cooling airflow in a radial inward and downstream direction.

Abstract: A swirler tube is disclosed. A swirler is provided comprising a flange defining a first surface, a tube extending away from the first surface, a flow surface defined by a flange inner surface and a tube inner surface, the flange inner surface having an inlet diameter, and a metering feature disposed on the flow surface, wherein the metering feature is integral to the tube, the metering feature have a metering feature diameter that is less than the inlet diameter.

Abstract: A washer includes a hub and a first lobe connected to the hub. The first lobe includes a first hole. A second lobe is also connected to the hub and includes a second hole. A third lobe is also connected to the hub and includes a third hole. The first lobe extends from the hub at least partially in a first direction opposite the second lobe and the third lobe.