Abstract: A compressor operable in a heat pump mode of a refrigerant circuit includes a compression space in which a refrigerant is compressed. The compression space includes a discharge port and an injection port. A discharge chamber is fluidly coupled to the compression space by the discharge port. An injection chamber is fluidly coupled to the compression space by the injection port. A discharge recirculation pathway selectively provides fluid communication between the discharge chamber and the injection chamber. An injection of the recirculated refrigerant into the compression space through the injection port results in an increase in pressure, and hence temperature, of the refrigerant when discharged to the discharge chamber. The increased temperature of the discharged refrigerant increases a heating capacity of a condenser of the associated refrigerant circuit.

Abstract: An orbiting scroll of a scroll compressor includes a platter wall having a first face including a spiral structure projecting therefrom, a second face having a coupling structure configured to couple the orbiting scroll to a drive mechanism of the scroll compressor, and a circumferential surface connecting the first face to the second face in an axial direction of the platter wall. The orbiting scroll includes a mass reduction feature provided as an inwardly indented channel formed in the circumferential surface. The channel is further configured to form a retaining feature for retaining a rim of a mask during a process of coating the spiral structure of the first face with a surface coating.

Abstract: Embodiments herein include a kinetic response system for measuring analyte presence on a chemical sensor element. The chemical sensor element includes one or more discrete binding detectors, each discrete binding detector including a graphene varactor. The kinetic response system includes a measurement circuit having an excitation voltage generator for generating a series of excitation cycles over a time period. Each excitation cycle includes delivering a DC bias voltage to the discrete binding detectors at multiple discrete DC bias voltages across a range of DC bias voltages. The kinetic response system includes a capacitance sensor to measure capacitance of the discrete binding detectors resulting from the excitation cycles. The kinetic response system includes a controller circuit to determine the kinetics of change in at least one of a measured capacitance value and a calculated value based on the measured capacitance over the time period. Other embodiments are also included herein.

Abstract: A compressor operable in a heat pump mode of a refrigerant circuit includes a compression space in which a refrigerant is compressed. The compression space includes a discharge port and an injection port. A discharge chamber is fluidly coupled to the compression space by the discharge port. An injection chamber is fluidly coupled to the compression space by the injection port. A discharge recirculation pathway selectively provides fluid communication between the discharge chamber and the injection chamber. An injection of the recirculated refrigerant into the compression space through the injection port results in an increase in pressure, and hence temperature, of the refrigerant when discharged to the discharge chamber. The increased temperature of the discharged refrigerant increases a heating capacity of a condenser of the associated refrigerant circuit.

Abstract: Embodiments herein relate to systems and methods for utilizing hysteresis as a mechanism of analysis of a sample. A system for analyzing a fluid sample is included having a controller circuit and a chemical sensor element. The chemical sensor element can include one or more discrete binding detectors that can include one or more graphene varactors. The system can include measurement circuitry having an electrical voltage generator configured to generate an applied voltage at a plurality of voltage values to be applied to the one or more graphene varactors. The system can include a measurement circuit having a capacitance sensor configured to measure capacitance of the discrete binding detectors resulting from the applied voltage. The system for analyzing the fluid sample can be configured to measure hysteresis effects related to capacitance versus voltage values obtained from the one or more graphene varactors. Other embodiments are also included herein.

Abstract: Embodiments herein relate to chemical sensors based on the non-covalent surface modification of graphene with compounds containing hydrazine or hydroxylamine functional groups for the detection of aldehyde and ketone-bearing analytes. In an embodiment, a medical device is included having a graphene varactor included a graphene layer and a self-assembled monolayer disposed on an outer surface of the graphene layer through electrostatic interactions between a partial positive charge on hydrogen atoms of one or more hydrocarbons of the self-assembled monolayer and a ?-electron system of graphene. The self-assembled monolayer can include one or more compounds having one or more hydrazine groups or hydroxylamine groups, substituted hydrazine or hydroxylamine groups, or derivatives thereof. Other embodiments are also included herein.

Abstract: A turbine airfoil includes a trailing edge coolant cavity between a pressure sidewall and a suction sidewall. The trailing edge coolant cavity is positioned adjacent to and extending out to a trailing edge of the turbine airfoil. The interior includes an internal arrangement comprising an array of discrete fins formed aft of the trailing edge coolant cavity along the trailing edge.

Abstract: Embodiments herein relate to chemical sensors, devices and systems including the same, and related methods. In an embodiment, a medical device is included. The medical device can include a graphene varactor. The graphene varactor can include a graphene layer and a self-assembled monolayer disposed on an outer surface of the graphene layer through ?-? stacking interactions. The self-assembled monolayer can provide a Langmuir theta value of at least 0.9. The self-assembled monolayer can include polycyclic aromatic hydrocarbons, tetraphenylporphyrins or derivatives thereof, metallotetraphenylporphyrins, or aromatic cyclodextrins. Other embodiments are also included herein.

Abstract: A blade airfoil for a turbine engine that includes an internal multiple pass serpentine flow cooling circuits with a leading edge circuit and a trailing edge circuit. The entrance of a cavity in the leading edge circuit has a narrowing of a cavity width that expands further downstream to a consistent cavity width similar to the cavity width of the rest of the leading edge circuit.

Abstract: An integrated airfoil and platform cooling system (30) for a turbine rotor blade (10) includes an inlet (38, 48) located at the root (24) for receiving a supply of a coolant (K), and at least one cooling leg (32a, 32c, 42a, 42c) fluidly connected to the inlet (38, 48) and configured for conducting the coolant (K) in a radially outboard direction. The cooling leg (32a, 32c, 42a, 42c) is defined at least partially by a span-wise extending internal cavity (26) within a blade airfoil (12). An entrance of the cooling leg (32a, 32c, 42a, 42c) comprises a flow passage (92, 102) that extends radially outboard and laterally into a blade platform (50), so as to direct a radially outboard flowing coolant (K) to impinge on an inner side (60) of a radially outer surface (52) of the blade platform (50), before leading the coolant (K) into the cooling leg (32a, 32c, 42a, 42c).

Abstract: A turbine airfoil includes a trailing edge coolant cavity between a pressure sidewall and a suction sidewall. The trailing edge coolant cavity is positioned adjacent to and extending out to a trailing edge of the turbine airfoil. The interior includes an internal arrangement comprising an array of discrete fins formed aft of the trailing edge coolant cavity along the trailing edge.

Abstract: A blade airfoil for a turbine engine that includes an internal multiple pass serpentine flow cooling circuits with a leading edge circuit and a trailing edge circuit. The entrance of a cavity in the leading edge circuit has a narrowing of a cavity width that expands further downstream to a consistent cavity width similar to the cavity width of the rest of the leading edge circuit.

Abstract: An integrated airfoil and platform cooling system (30) for a turbine rotor blade (10) includes an inlet (38, 48) located at the root (24) for receiving a supply of a coolant (K), and at least one cooling leg (32a, 32c, 42a, 42c) fluidly connected to the inlet (38, 48) and configured for conducting the coolant (K) in a radially outboard direction. The cooling leg (32a, 32c, 42a, 42c) is defined at least partially by a span-wise extending internal cavity (26) within a blade airfoil (12). An entrance of the cooling leg (32a, 32c, 42a, 42c) comprises a flow passage (92, 102) that extends radially outboard and laterally into a blade platform (50), so as to direct a radially outboard flowing coolant (K) to impinge on an inner side (60) of a radially outer surface (52) of the blade platform (50), before leading the coolant (K) into the cooling leg (32a, 32c, 42a, 42c).

Abstract: A turbine component including a shrouded airfoil with a flow conditioner configured to direct leakage flow and coolant to be aligned with main hot gas flow is provided. The flow conditioner is positioned on a shroud base radially adjacent to the tip of the airfoil and includes a ramped radially outer surface positioned further radially inward than a radially outer surface of the shroud base. The ramped radially outer surface extends from a first edge to a second edge in a direction generally from the suction side to the pressure side of the airfoil, such that the first edge is positioned further radially inward than the second edge. Multiple coolant ejection holes are positioned on the ramped radially outer surface. The coolant ejection holes are connected fluidically to an interior of the airfoil.

Abstract: A turbine blade including a pressure sidewall (24) and a suction sidewall (26), and at least one partition rib (34) extends between the pressure and suction sidewalls (24, 26) to define a serpentine cooling path (35) having adjacent cooling channels (36a, 36b, 36c) extending in the spanwise direction (S) within the airfoil (12). A flow turning guide structure (50) extends around an end of the at least one partition rib (34) and includes a first element (52) extending from the pressure sidewall (24) to a lateral location in the cooling path between the pressure and suction sidewalls (24, 26), a second element (54) extending from the suction sidewall (26) to the lateral location in the cooling path between the pressure and suction sidewalls (24, 26). The first and second elements (52, 54) include respective distal edges (52d, 54d) that laterally overlap each other at the lateral location.

Abstract: An airfoil (10) is disclosed for a gas turbine engine in which the airfoil (10) includes an internal cooling system (14) with one or more converging-diverging exit slots (20) configured to increase the effectiveness of the cooling system (14) at the trailing edge (34) of the airfoil (10) by increasing the contact of cooling fluids with internal surfaces (24, 30) of the pressure and suction sides (36, 38) of the airfoil (10). In at least one embodiment, the trailing edge cooling channel (18) may include one or more converging-diverging exit slots (20) to further pressurize the trailing edge cooling channel (18) and may be formed by a first and second ribs (80, 82) extending between an outer walls (13, 12) forming the pressure and suction sides (36, 38).

Abstract: A turbine component (10) including a shrouded airfoil (32) with a flow conditioner (70, 70a, 70b) configured to direct leakage flow and coolant to be aligned with main hot gas flow is provided. The flow conditioner (70, 70a, 70b) is positioned on a shroud base (20) radially adjacent to the tip of the airfoil and includes a ramped radially outer surface (72) positioned further radially inward than a radially outer surface (25) of the shroud base (20). The ramped radially outer surface (72) extends from a first edge (74) to a second edge (76) in a direction generally from the suction side (40) to the pressure side (38) of the airfoil (32), such that the first edge (74) is positioned further radially inward than the second edge (76). Multiple coolant ejection holes (80) are positioned on the ramped radially outer surface (72). The coolant ejection holes (80) are connected fluidically to an interior (81) of the airfoil (32).

Abstract: A turbine blade including a pressure sidewall (24) and a suction sidewall (26), and at least one partition rib (34) extends between the pressure and suction sidewalls (24, 26) to define a serpentine cooling path (35) having adjacent cooling channels (36a, 36b, 36c) extending in the spanwise direction (S) within the airfoil (12). A flow turning guide structure (50) extends around an end of the at least one partition rib (34) and includes a first element (52) extending from the pressure sidewall (24) to a lateral location in the cooling path between the pressure and suction sidewalls (24, 26), a second element (54) extending from the suction sidewall (26) to the lateral location in the cooling path between the pressure and suction sidewalls (24, 26). The first and second elements (52, 54) include respective distal edges (52d, 54d) that laterally overlap each other at the lateral location.

Abstract: An airfoil (10) is disclosed for a gas turbine engine in which the airfoil (10) includes an internal cooling system (14) with one or more converging-diverging exit slots (20) configured to increase the effectiveness of the cooling system (14) at the trailing edge (34) of the airfoil (10) by increasing the contact of cooling fluids with internal surfaces (24, 30) of the pressure and suction sides (36, 38) of the airfoil (10). In at least one embodiment, the trailing edge cooling channel (18) may include one or more converging-diverging exit slots (20) to further pressurize the trailing edge cooling channel (18) and may be formed by a first and second ribs (80, 82) extending between an outer walls (13, 12) forming the pressure and suction sides (36, 38).

Abstract: A cooling system (10) for a turbine airfoil (12) of a turbine engine having one or more mid-chord cooling channels (16) that extend through both the airfoil (32) and a platform (18) of the airfoil (12) to provide adequate cooling the platform (18) while cooling the airfoil (32) is disclosed. The mid-chord cooling channel (16) may be formed from an airfoil portion (20) extending generally spanwise within the airfoil (32) and a platform portion (22) extending into a platform (18) of the airfoil (12) with a larger cross-sectional area than a cross-sectional area of the airfoil portion (20). The mid-chord cooling channel (16) may also extend into the platform (18) of the airfoil (12) a distance laterally outside of a silhouette (60) of the airfoil (32) defined by the leading edge (24), trailing edge (26), pressure side (28) and suction side (30) of the airfoil (32). Thus, the mid-chord cooling channel (16) extends laterally into the platform (18) to provide adequate cooling the platform (18).