Abstract: Methods of treatment of pulmonary hypertension comprising dry powder inhalation administration of imatinib, a pharmaceutically acceptable salt, or a derivative thereof, are provided. Dry powder inhalable compositions comprising imatinib, a pharmaceutically acceptable salt, or a derivative thereof, are also provided as well as methods of making the same.

Abstract: Systems, program products, and methods for adjusting operating limit (OL) thresholds for compressors of gas turbine systems based on mass flow loss are disclosed herein. The systems may include at least one computing device in communication with the gas turbine system, sensor(s) measuring operational characteristic(s) of the gas turbine system, and a pressure sensor measuring an ambient fluid pressure surrounding the gas turbine system. The computing device(s) may be configured to adjust operational parameters of the gas turbine system by performing processes including determining a mass flow loss between an estimated, first mass flow rate and a calculated, second mass flow rate for the compressor of the gas turbine system, and adjusting an OL threshold for the compressor of the gas turbine system based on the mass flow loss. The OL threshold for the compressor may be below a predetermined surge threshold for the compressor.

Abstract: Systems, program products, and methods for adjusting operating limit (OL) thresholds for compressors of gas turbine systems based on mass flow loss are disclosed herein. The systems may include at least one computing device in communication with the gas turbine system, sensor(s) measuring operational characteristic(s) of the gas turbine system, and a pressure sensor measuring an ambient fluid pressure surrounding the gas turbine system. The computing device(s) may be configured to adjust operational parameters of the gas turbine system by performing processes including determining a mass flow loss between an estimated, first mass flow rate and a calculated, second mass flow rate for the compressor of the gas turbine system, and adjusting an OL threshold for the compressor of the gas turbine system based on the mass flow loss. The OL threshold for the compressor may be below a predetermined surge threshold for the compressor.

Abstract: A compressor assembly for a turbomachine includes a compressor wall including circumferentially spaced stator vanes defining at least one row of stator vanes. The at least one row of stator vanes defines at least one stator passage therein. Each stator vane includes a leading edge, an opposite trailing edge defining an axial chord distance, and a pressure side. The compressor assembly also includes, at least one bleed opening defined within the compressor wall and disposed adjacent the pressure side in the at least one stator passage within a range from approximately 20% the axial chord distance upstream of the leading edge to approximately 20% the axial chord distance downstream of the trailing edge. The compressor assembly further includes at least one bleed arm extending from the at least one bleed opening with at least a portion of compressor airflow extractable through the at least one bleed arm.

Abstract: A compressor for a gas turbine engine including one or more endwall treatments for controlling leakage flow and circumferential flow non-uniformities in the compressor. The compressor includes a casing, a hub, a flow path formed between the casing and the hub, a plurality of blades positioned in the flow path, and one or more circumferentially varying end-wall treatments formed in an interior surface of at least one of the casing or the hub. Each of the one or more circumferentially varying endwall treatments circumferentially varying based on their relative position to an immediately adjacent upstream bladerow. Each of the one or more endwall treatments is circumferentially varied in at least one of placement relative to the immediately adjacent upstream bladerow or in geometric parameters defining each of the plurality of circumferentially varying endwall treatments. Additionally disclosed is an engine including the compressor.

Abstract: An airfoil is disclosed herein. The airfoil may include a leading edge, a trailing edge, a suction side defined between the leading edge and the trailing edge, and a pressure side defined between the leading edge and the trailing edge opposite the suction side. The pressure side may include a concave profile about the trailing edge that varies from a profile of a remainder of the pressure side.

Abstract: A compressor assembly for a turbomachine includes a compressor wall including circumferentially spaced stator vanes defining at least one row of stator vanes. The at least one row of stator vanes defines at least one stator passage therein. Each stator vane includes a leading edge, an opposite trailing edge defining an axial chord distance, and a pressure side. The compressor assembly also includes, at least one bleed opening defined within the compressor wall and disposed adjacent the pressure side in the at least one stator passage within a range from approximately 20% the axial chord distance upstream of the leading edge to approximately 20% the axial chord distance downstream of the trailing edge. The compressor assembly further includes at least one bleed arm extending from the at least one bleed opening with at least a portion of compressor airflow extractable through the at least one bleed arm.

Abstract: A compressor for a gas turbine engine including one or more endwall treatments for controlling leakage flow and circumferential flow non-uniformities in the compressor. The compressor includes a casing, a hub, a flow path formed between the casing and the hub, a plurality of blades positioned in the flow path, and one or more circumferentially varying end-wall treatments formed in an interior surface of at least one of the casing or the hub. Each of the one or more circumferentially varying endwall treatments circumferentially varying based on their relative position to an immediately adjacent upstream bladerow. Each of the one or more endwall treatments is circumferentially varied in at least one of placement relative to the immediately adjacent upstream bladerow or in geometric parameters defining each of the plurality of circumferentially varying endwall treatments. Additionally disclosed is an engine including the compressor.

Abstract: An axial compressor for a gas turbine engine including one or more endwall treatments for controlling leakage flow in the compressor. The one or more endwall treatments having a height formed in an interior surface of a compressor casing or a compressor hub and configured to return a flow adjacent a plurality of rotor blade tips or a plurality of stator blade tips to a cylindrical flow passage upstream of a point of removal of the flow. Each of the endwall treatments defining a front wall, a rear wall, an outer wall extending between the front wall and the rear wall, an axial overhang, an axial overlap, an axial lean angle and a tangential lean angle. The axial overhang extending upstream to overhang at least one of the at least one set of rotor blades or the at least one set of stator blades. The axial overlap extending downstream to overlap at least one of the at least one set of rotor blades or the at least one set of stator blades.

Abstract: A sealing assembly for use with a rotating machine is described herein. The rotating machine includes a stator casing that includes a radially inner surface that defines a cavity therein, and a rotor positioned within the cavity and spaced inwardly from the stator inner surface. The sealing assembly includes a support ring coupled to the stator casing, and a plurality of plate members coupled to the support ring and oriented circumferentially about the rotor. A resistance member extends inwardly from the support ring towards the rotor outer surface. The resistance member is coupled to the support ring and extends through each plate member of the plurality of plate members. At least one rotor land is defined circumferentially about the rotor outer surface. Each plate member is oriented adjacent the at least one rotor land.

Abstract: An airfoil is disclosed herein. The airfoil may include a leading edge, a trailing edge, a suction side defined between the leading edge and the trailing edge, and a pressure side defined between the leading edge and the trailing edge opposite the suction side. The pressure side may include a concave profile about the trailing edge that varies from a profile of a remainder of the pressure side.

Abstract: A seal assembly for rotary machine is provided. The seal assembly includes multiple compliant plates disposed between a stationary component and a rotary component of the rotary machine, and coupled circumferentially along the stationary component. Each compliant plate comprises a tip configured to be disposed facing the rotary component, and at least one plate slot extending from the stationary component towards the rotary component. The seal assembly also includes at least one annular resistance member configured to be coupled to the stationary component and disposed in the at least one plate slot in the compliant plates and one or more rotor slots or grooves located circumferentially on a surface of the rotary component proximate the tip of each of the plurality of compliant plates.

Abstract: A sealing assembly for use with a rotating machine is described herein. The rotating machine includes a stator casing that includes a radially inner surface that defines a cavity therein, and a rotor positioned within the cavity and spaced inwardly from the stator inner surface. The sealing assembly includes a support ring coupled to the stator casing, and a plurality of plate members coupled to the support ring and oriented circumferentially about the rotor. A resistance member extends inwardly from the support ring towards the rotor outer surface. The resistance member is coupled to the support ring and extends through each plate member of the plurality of plate members. At least one rotor land is defined circumferentially about the rotor outer surface. Each plate member is oriented adjacent the at least one rotor land.

Abstract: A seal assembly for a turbo machine is provided. The turbo machine includes a rotary component and a stationary component. The seal assembly is disposed between the rotary component and the stationary component. The seal assembly is configured to provide a sealing between a high pressure area and a low pressure area of the turbo machine. The seal assembly includes a plurality of compliant plates coupled circumferentially along the stationary component. Each of the compliant plate includes a tip disposed facing the rotary component. A tip slot is provided on the tip of the compliant plates, wherein the tip slots is provided at the portion of the tip proximate the high pressure area. The compliant plates further include a plate slot extending from the stationary component towards the tip. An annular resistance member coupled to the stationary component is disposed in the plate slot in the compliant plates.