Abstract: A method for controlling the temperature in a vehicle cabin, while the vehicle engine is turned off, includes the following steps: importing a State-of Charge information of a vehicle traction battery, an outside temperature, and inside temperature of the cabin into an electronic controller; calculating a normal electric power required for operating an HVAC system in a Normal mode; calculating a maximum operation time of the HVAC system in the Normal mode based on the State-of-Charge information; displaying the maximum operation time on a display; reading an operator input selecting one mode of at least the Normal mode and a first Eco mode of the HVAC system, wherein in the first Eco mode the HVAC system operates at a reduced electric power compared to the Normal mode; and operating the HVAC system in accordance with the operator input. A suitable HVAC system includes an appropriate user interface.

Abstract: An evaporator for an air conditioning system includes a plurality of clamshell plates stacked in series along a longitudinal axis and a plurality of core tubes coupled with the stacked clamshell plates. In an upper region of the evaporator, the stacked clamshell plates form an inlet tank and an outlet tank hydraulically communicated with the core tubes for a refrigerant flow. Each of the clamshell plates includes a pooling ridge on a first surface of the clamshell plate for pooling a liquid refrigerant by gravity such that the liquid refrigerant is evenly distributed to inlet core tubes disposed along the longitudinal axis.

Abstract: An assembly for a turbomachine and a method for assembling a plurality of flow path components are presented. The assembly includes a plurality of flow path components disposed adjacent to one another, each flow path component having a forward surface, an aft surface, a pressure side surface, and a suction side surface. A seal channel is defined by the pressure side surface and the suction side surface of adjacent flow path components. The seal channel has an open forward end proximate to the forward surfaces and at least two rear ends proximate to the aft surfaces. The assembly includes a plurality of seal layers disposed within the seal channel such that one or more seal layers extend from the open forward end to a rear end and one or more other seal layers extend from the open forward end to another rear end.

Abstract: A seal assembly that includes a rotatable seal component, a non-rotatable seal component, and a plurality of pairs of flexures. The non-rotatable seal component is disposed facing the rotatable seal component. The plurality of pairs of flexures is spaced apart from each other along a circumferential direction of the seal assembly. Each pair of the plurality of pairs of flexures has a center line and includes a first flexure and a second flexure disposed in a stressed condition such that a portion of the first flexure and a portion of the second flexure are in contact with each other. Further, the first end of the first flexure is inclined at a first angle relative to the center line and a first end of the second flexure is inclined at a second angle relative to the center line. Also, first end of the first flexure and a first end of the second flexure are coupled to each other and to the non-rotatable seal component.

Abstract: A turbine shroud is disposed about a row of rotating turbine blades. The turbine shroud includes arcuate shroud segments sealingly engaged with one another. Each shroud segment includes a bottom panel with a radially inner surface and a radially outer surface, a first end, and a second end. The first end includes a first end face, a first end cutback face spaced from the first end face, and an intermediate surface extending between the first end face and the end cutback face to define a recess. The second end includes a second end face, a second end cutback face spaced from the second end face, and a projecting surface extending between the second end face and the second end cutback face. The projecting surface of each shroud segment overlaps the recess of a circumferentially adjacent shroud segment to produce a sealed joint.

Abstract: A turbine shroud is disposed between stages of stationary turbine nozzles. The turbine shroud includes arcuate shroud segments sealingly engaged with one another. Each shroud segment includes a bottom panel with a radially inner surface and a radially outer surface and opposite ends. Each end includes an end face, an end cutback face spaced from the end face, and an intermediate surface extending between the end face and the end cutback face to define a recess. One or more seals overlap the recess of a circumferentially adjacent pair of shroud segments to produce a sealed joint.

Abstract: A seal assembly, for example, a face seal assembly for a machine such as a turbomachine, and an associated method of operating the seal assembly in the machine are disclosed. The seal assembly includes a rotatable seal component, a non-rotatable seal component, and a plurality of pairs of flexures. The non-rotatable seal component is disposed facing the rotatable seal component. The plurality of pairs of flexures is spaced apart from each other along a circumferential direction of the seal assembly. Each pair of the plurality of pairs of flexures includes a first flexure and a second flexure disposed in a stressed condition such that a portion of the first flexure and a portion of the second flexure are in contact with each other. Further, an end of the first flexure and an end of the second flexure are coupled to each other and to the non-rotatable seal component.

Abstract: The subject matter described herein relate to a segmented piston seal system. The segmented piston seal includes a first semi-circular section (FSCS) that includes a first locking structure at opposite ends of the FSCS. The segmented piston seal includes a second semi-circular section (SSCS) that includes a second locking structure at opposite ends of the SSCS. The first and second locking structures are configured to lock the FSCS and the SSCS together to form a piston seal.

Abstract: A thrust bearing assembly for a machine includes a stator housing, a fluid film thrust bearing, and a ring bearing. The stator housing surrounds at least a segment of a rotor shaft and one or more runners on the rotor shaft that include a first runner surface and a second runner surface facing in opposite axial directions along the rotor shaft. The fluid film thrust bearing is axially held between a first stator surface of the stator housing and the first runner surface. The fluid film thrust bearing is configured to generate a fluid cushion that blocks the first runner surface from engaging the fluid film thrust bearing. The ring bearing is axially held between a second stator surface of the stator housing and the second runner surface. The ring bearing has an annular contact surface that engages the second runner surface to axially support the rotor shaft.

Abstract: A thrust bearing assembly for a machine includes a stator housing, a fluid film thrust bearing, and a ring bearing. The stator housing surrounds at least a segment of a rotor shaft and one or more runners on the rotor shaft that include a first runner surface and a second runner surface facing in opposite axial directions along the rotor shaft. The fluid film thrust bearing is axially held between a first stator surface of the stator housing and the first runner surface. The fluid film thrust bearing is configured to generate a fluid cushion that blocks the first runner surface from engaging the fluid film thrust bearing. The ring bearing is axially held between a second stator surface of the stator housing and the second runner surface. The ring bearing has an annular contact surface that engages the second runner surface to axially support the rotor shaft.

Abstract: A seal for a blind shear ram is configured to extend between a first carrier and a second carrier of the blind shear ram. The seal includes an outer layer configured to contact at least one of the first carrier and the second carrier to seal a wellbore when the blind shear ram is in a closed position. The outer layer has a first stiffness. The seal also includes an inner layer spaced from the outer layer. The inner layer has a second stiffness. The seal further includes an anti-extrusion structure extending between the inner layer and the outer layer. The anti-extrusion structure has a third stiffness greater than the first stiffness and the second stiffness. The outer layer covers the anti-extrusion structure.

Abstract: A heating system for an automotive passenger cabin includes a blower fan generating an air flow; a first heater core downstream of the blower fan; a second heater core downstream of the first heater core; a coolant loop with a first branch and a second branch, wherein the first heater core is disposed in the first branch and the second heater core is disposed in the second branch; a change-over valve arrangement having a first setting establishing fluid communication between the first and second heater cores by connecting the first and second branches in two locations on opposite sides of the first and second heater cores. The change-over valve arrangement has a second setting separating the fluid communication between the first and second heater cores by disconnecting the first and second branches. The second branch or both the first and the second branch are connectable to a PCM heater.

Abstract: An assembly for a turbomachine and a method for assembling a plurality of flow path components are presented. The assembly includes a plurality of flow path components disposed adjacent to one another, each flow path component having a forward surface, an aft surface, a pressure side surface, and a suction side surface. A seal channel is defined by the pressure side surface and the suction side surface of adjacent flow path components. The seal channel has an open forward end proximate to the forward surfaces and at least two rear ends proximate to the aft surfaces. The assembly includes a plurality of seal layers disposed within the seal channel such that one or more seal layers extend from the open forward end to a rear end and one or more other seal layers extend from the open forward end to another rear end.

Abstract: A seal assembly, for example, a face seal assembly for a machine such as a turbomachine, and an associated method of operating the seal assembly in the machine are disclosed. The seal assembly includes a rotatable seal component, a non-rotatable seal component, and a plurality of pairs of flexures. The non-rotatable seal component is disposed facing the rotatable seal component. The plurality of pairs of flexures is spaced apart from each other along a circumferential direction of the seal assembly. Each pair of the plurality of pairs of flexures includes a first flexure and a second flexure disposed in a stressed condition such that a portion of the first flexure and a portion of the second flexure are in contact with each other. Further, an end of the first flexure and an end of the second flexure are coupled to each other and to the non-rotatable seal component.

Abstract: A method and system including a circumferential seal assembly for sealing between components within a turbine is provided. A circumferential seal assembly is disposed in a slot extending circumferentially about an inner barrel. The seal assembly includes a first shim layer and at least one additional shim layer configured in an overlapping stacked configuration so as to stagger the end portions of each of the shim segments defined by the shim layers, relative to one another and circumferentially about the seal assembly. One or more cloth layers are configured wrapping about the first shim layer and the at least one additional shim layer to define a sealing member having a first sealing surface and a second sealing surface. The assembly further including a base plate, wherein the sealing member is disposed on an upper surface of the base plate to provide for sealing engagement between the components of the turbine.

Abstract: Coating systems for a cooled turbine blade tip, such as a metal turbine blade tip, are provided. The coating system includes an abrasive layer overlying the surface of the turbine blade tip. One or more buffer layers may additionally be disposed between an outer surface of the blade tip and the abrasive layer. The coated blade tip can be used with a ceramic matrix composite (CMC) shroud coated with an environmental barrier coating (EBC) to provide improved cooling to the tip so as to lengthen oxidation time of the abrasive layer and reduce blade tip wear. Methods are also provided for forming the cooled blade tip and applying the coating system onto the cooled turbine blade tip.

Abstract: A seal assembly for a rotary machine is provided. The seal assembly includes a plurality of seal segments disposed circumferentially intermediate to a stationary housing and a rotor, where each of the plurality of seal segments includes a stator interface element and a shoe plate movably supported by the stator interface element. The shoe plate includes one or more labyrinth teeth, a load-bearing surface, and one or more supply ports for facilitating supply of high pressure fluid toward the rotor. In one embodiment, the shoe plate also includes a radially extending portion that is in contact with a portion of the ring movably supported into the stator interface element. In another embodiment, each of the plurality of seal segments includes a plurality of overlapping spring-loaded leaf seal plates in contact with the stator interface element and the radially extending portion. Method of operating the seal segment is also disclosed.

Abstract: A seal assembly for a rotary machine is provided. The seal assembly includes a plurality of seal segments disposed circumferentially intermediate to a stationary housing and a rotor, where each of the plurality of seal segments includes a stator interface element and a shoe plate movably supported by the stator interface element. The shoe plate includes one or more labyrinth teeth, a load-bearing surface, and one or more supply ports for facilitating supply of high pressure fluid toward the rotor. In one embodiment, the shoe plate also includes a radially extending portion that is in contact with a portion of the ring movably supported into the stator interface element. In another embodiment, each of the plurality of seal segments includes a plurality of overlapping spring-loaded leaf seal plates in contact with the stator interface element and the radially extending portion. Method of operating the seal segment is also disclosed.

Abstract: A kick detection system for drilling a well including an ultrasonic module for transmitting signals to a returning drilling fluid from the well, and receiving corresponding backscatter signals; and a process apparatus for obtaining a flow characteristic of the returning drilling fluid based on the backscatter signals, and detecting a kick based on the flow characteristic of the returning drilling fluid and drilling related data. A well drilling system including a drilling string for guiding a drilling bit and a drilling fluid to a well; a conduit defining a channel for accommodating the drilling string and a returning drilling fluid from the well; and the kick detection system. A kick detection method is also described.

Abstract: A seal assembly to seal a gas turbine hot gas path flow at an interface of a combustor liner and a downstream component, such as a stage one turbine nozzle, in a gas turbine. The seal assembly including a piston ring seal housing, defining a cavity, and a piston ring disposed within the cavity. The piston ring disposed circumferentially about the combustor liner. The piston ring is responsive to a regulated pressure to secure sealing engagement of the piston ring and outer surface of the combustor liner. The seal assembly includes at least one of one or more sectional through-slots, bumps or channel features to provide for a flow therethrough of a high-pressure (Phigh) bypass airflow exiting a compressor to the cavity. The high-pressure (Phigh) bypass airflow exerting a radial force on the piston ring.