Abstract: Optimizing power generation from waste heat in large industrial facilities such as petroleum refineries by utilizing a subset of all available hot source streams selected based, in part, on considerations for example, capital cost, ease of operation, economics of scale power generation, a number of ORC machines to be operated, operating conditions of each ORC machine, combinations of them, or other considerations are described. Subsets of hot sources that are optimized to provide waste heat to one or more ORC machines for power generation are also described. Further, recognizing that the utilization of waste heat from all available hot sources in a mega-site such as a petroleum refinery and aromatics complex is not necessarily or not always the best option, hot source units in petroleum refineries from which waste heat can be consolidated to power the one or more ORC machines are identified.

Abstract: A mixer (19), for an exhaust system (7) for mixing and/or evaporating a liquid (13) in an exhaust gas flow (8), especially for an SCR system (9), includes a plurality of guide blades (21) arranged in a star-shaped pattern. Simplified manufacturability of the mixer (19) is achieved if the guide blades (21) are connected each with a centrally arranged core (23) radially on the inside and if the guide blades (21). The guide blades (21) and the core (23) are formed by an integral cast part (24).

Abstract: A turbocharger system for simultaneously improving a fuel efficiency and obtaining a satisfactory hill start performance due to a downsized engine. The system includes an electric assist turbocharger which includes a turbine disposed in an exhaust passage of an engine and driven by exhaust gas, a compressor disposed in an intake passage and driven by a rotational torque of the turbine, and an electric motor assisting a driving force of the compressor and an electric motor control unit which drives the electric motor when detecting a start operation at a sloping road.

Abstract: A compressor that includes an impeller, a diffuser and a shroud. The diffuser includes vanes and one or more projections, each of which extends from a top of a vane. The shroud includes one or more holes. The shroud covers the impeller and the diffuser such that each projection protrudes through one of the holes. The shroud is then secured to the projections by an adhesive.

Abstract: The turbine rotor blade includes a platform with a first side and a second side; an airfoil extending from the first side of the platform; and an attachment portion extending from the second side of the platform. The attachment portion includes first and second side surfaces and a base surface on an underside of the attachment portion between the first and second side surface. The base surface includes at least one curved segment or angled segment.

Abstract: A method and a system for a heat exchanger assembly are provided. The heat exchanger assembly includes one or more arcuate heat exchanger segments each including an inlet header configured to extend circumferentially about a circumference of an inner surface of a fluid flow duct, and an outlet header configured to extend circumferentially about the fluid flow duct. The heat exchanger assembly also includes a first serpentine heat exchanger tube extending between the inlet header and the outlet header and including a series of flow path segments having a gradually changing direction defined by a bend radius of the tube such that a direction of flow through the serpentine heat exchanger tube reverses between the inlet and the outlet headers and a second serpentine heat exchanger tube extending between the inlet header and the outlet header, the second serpentine heat exchanger tube co-planar with the first serpentine heat exchanger tube.

Abstract: A housing section of a turbine engine compressor stage or a turbine engine turbine stage that, in particular, has a closed and annular-shaped, radially outer casing. The radially outer casing has radially inwardly extending webs that are angled at a slant relative to the radius.

Abstract: A system for controlling aircraft boundary layer airflow comprising a frame structure configured to be coupled or integral to an inner surface of an aircraft nacelle, the frame configured to support to the nacelle, and/or a modular plenum configured to be received by the frame structure, the modular plenum comprising a truncated tetrahedron intersected at its apex by a duct. The frame may comprise a plurality of sub-frames. The system may further comprise a plurality of modular plenums, each configured to fit within a sub-frame. The system may further comprise a flexible material configured to couple a first duct to a second duct. The system may further comprise a nacelle configured to receive the system.

Abstract: A screw spindle pump constituted by at least two parts is disclosed. The first part includes a housing and at least one spindle system disposed in the housing and capable of being driven in a rotational manner. Furthermore, a pressure region disposed downstream of the spindle system and at least one outlet opening which is connected to the pressure region, the outlet opening discharging the delivery medium out of the pressure region. The second part includes at least one low-pressure chamber disposed upstream of the spindle system and at least one inlet opening for the delivery medium into the low-pressure chamber. The first part and the second part are coupled together, preferably in a rotational manner, so that they can assume at least two different relative positions.

Abstract: A unique engine system has an engine with a dedicated exhaust gas recirculation cylinder, an EGR system that receives exhaust gas from the dedicated cylinder, and a turbocharger having turbine inlet ports in fluid communication with other engine cylinders via a plurality of exhaust passages. At least two of the exhaust passages are substantially isolated from each other. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for engines and engine systems.

Abstract: An apparatus has a base and a flow path assembly movably supported by the base and defining a serpentine flow path having an entry opening and an exit opening. An actuator is coupled with the flow path assembly and the base and is configured to rotate the flow path assembly between a vertical and an angled position relative to the base. The flow path is configured to allow a column of a first fluid with a first density to be trapped between columns of a second fluid with a second density higher than the first density. The first fluid column has a first height and the second fluid columns have second heights, so that a volume of the first fluid and a volume of the second fluid flow through the flow path and through the exit opening as the flow path assembly is rotated between the vertical and angled positions.

Abstract: An exhaust gas energy recovery system includes a power plant and a volumetric fluid expander. The power plant has an exhaust gas outlet for conveying an exhaust gas stream at a first pressure. The volumetric fluid expander includes a housing and an output shaft. The housing has an inlet and an outlet, and the housing inlet is in fluid communication with the exhaust gas outlet. The volumetric fluid expander generates useful work at the output shaft by expanding the exhaust gas stream to a second pressure lower than the first pressure generally without reducing the volume of the exhaust stream as the exhaust stream moves from the housing inlet to the outlet.

Abstract: Methods are disclosed for determining an oxidation state of a catalyst using RF signals. The method may include introducing radio-frequency signals into a resonant chamber including a catalyst, modulating an air-fuel ratio of an engine upstream of the catalyst to generate a sequence of uniform pulses and at least one altered pulse that differs from the uniform pulses, and comparing a frequency response of two or more resonant modes of the radio-frequency signals during the sequence to determine an oxidation state of the catalyst. The method may further include adjusting the air-fuel ratio based on the comparing step. Two or more altered pulses may be inserted into the air-fuel ratio sequence. The altered pulse may have a pulse width and/or amplitude that differs from the uniform pulses. The methods may be used to adjust an air-fuel ratio to correct or impart a bias.

Abstract: Embodiments of the present invention may include a variable nozzle turbocharger having a variable nozzle mechanism for controlling a flow velocity of exhaust gas to a turbine wheel. The variable nozzle mechanism includes a plurality of variable nozzles, a unison ring and a biasing member. The variable nozzles each have a nozzle vane. The unison ring is configured to adjust a degree of opening of the variable nozzles through rotation of the unison ring. The biasing member biases the unison ring so as to open the variable nozzles.

Abstract: A fuel nozzle for use in a gas turbine engine is provided. The fuel nozzle has a fuel nozzle tip with an outer tip housing. The tip housing has a recess formed at an inner surface of the tip housing. A shim is disposed within the recess and a surface of the shim contacts a diaphragm of the fuel nozzle tip. A thermal adjustment member is disposed within the recess against the shim. The tip housing, diaphragm and shim are formed of a base material having a coefficient of thermal expansion (?1) and the thermal adjustment member is formed of a different material having a coefficient of thermal expansion (?2) higher than the coefficient of thermal expansion (?1) of the base material.

Abstract: The present application relates to the compressor stator of an axial turbomachine. The stator comprises an annular row of main stator blades and auxiliary blades each of which are associated with a main blade. The auxiliary blades are located at the trailing edges of the main blades and are in the vicinity of the pressure faces of the main blades. The auxiliary blades are aligned to generate a low-pressure area at the trailing edges of the main blades. Thus, a flow bypassing a main blade by its suction face is sucked in by the low-pressure area when it approaches the trailing edge of the main blade. Stalling is thus avoided and the efficiency of the machine is improved.

Abstract: A removing poison apparatus of a lambda sensor includes: a lambda sensor detecting an oxygen concentration included in an exhaust gas; and a control unit differentiating a heating temperature and a heating time to remove poison of the lambda sensor depending on a lambda signal output from the lambda sensor in an overrun condition of the engine. By heating the lambda sensor depending on the magnitude of the lambda signal output from the lambda sensor, the lambda sensor may be inhibited from being degraded by combusting the material poisoned to the electrode of the lambda sensor and the failure of the lambda sensor may be correctly determined.

Abstract: An apparatus, system, and method for raising water is provided. The apparatus includes at least one container movable between at least a descended position and a ascended position within a body of water. A non-water-permeable membrane is positioned within the at least one container, wherein the membrane is movable within an interior compartment of the at least one container to separate the interior compartment into at least a first and a second portion. At least one vent structure is within a wall of the at least one container, wherein movement of the membrane controls a flow of water through the at least one vent structure and into at least one of the first and second portions.

Abstract: A method for enhanced cold (or warm) steam turbine start in a supplementary fired multi-gas turbine combined cycle plant is disclosed. Boiler supplementary firing, which is normally used to increase steam flow when the plant gas turbine is at maximum load, is used to augment steam production with a partly loaded, temperature matched gas turbine. This is done to satisfy minimum required steam flow for a cold (or warm) steam turbine start. Lighting the supplementary firing burners in the heat recovery steam generator/boiler and setting them at a minimum or low heat load serves to add enough steam, at the proper temperature, to insure a successful cold or warm steam turbine start when the gas turbine load and related steam production capacity from the gas turbine exhaust flow are limited by the need to match the required steam temperature and/or maintain low gas turbine exhaust emissions.

Abstract: A scroll compressor is disclosed which prevents leakage of refrigerant from a compression chamber and abrasion of bearings between a rotating shaft and an orbiting scroll by reducing the tilting angle of the orbiting scroll, because the allowable bearing angle is equal to or larger than the tilting angle, where the allowable bearing angle ? refers to the maximum angle at which the orbiting scroll is tilted with respect to the rotating shaft, and the tilting angle ? refers to the angle at which the orbiting scroll is tilted with respect to the plate.