Abstract: A system and method of controlling a turbocharged engine system includes receiving a boost mode selection signal and controlling the turbocharged engine system in response to the boost mode selection signal.

Abstract: A seal system includes a ceramic component that has a non-core-gaspath surface region that defines a first surface roughness and a core gaspath surface region. A metallic component is situated adjacent the non-core-gaspath surface region. A coating system is disposed on the ceramic component. The coating system includes a silicon-containing layer on the non-core-gaspath surface region and a barrier layer that has a first section on the silicon-containing layer and a second section on the core-gaspath region and that is connected to the first section. The surface of the barrier layer has a second surface roughness that is less than the first surface roughness. The first section is in contact with the metallic component and the second section serves as an environmental barrier on the core-gaspath region.

Abstract: A ram air turbine rotor comprises at least one intra-flow path shroud structure coupled between rotor blades, along a radial position between a support disc and an outer rim. The shroud structure includes shroud sectors each coupled between a respective pair of blades. The sectors each include a first edge adjacent to leading edges of the respective pair of blades, the first edge including a first curved segment, and a second edge adjacent to trailing edges of the respective pair of blades, the second edge including a second curved segment. The curved segments are each partially defined by a respective ellipse having a semi-major axis and a semi-minor axis. The semi-major axis is a portion of a spanwise distance between the respective pair of blades. The semi-minor axis is a portion of an axial distance between the leading edge of one blade and the trailing edge of an adjacent blade.

Abstract: A general mounting method for ducted fan propulsors is disclosed. This mounting method uses extremely slender stators that connect the duct ring to the propulsor which is mounted in the middle and drives the rotor, fan or propeller. The slender stators take the form of spokes and as such are so slender that the midspan stresses within the spokes are dominated by axial tension loads rather than the shear loads experienced by conventional stators. The spokes may have an aerodynamic shape and damping methods may be used to retard spoke vibrations and transmission of engine vibrations to the duct and force. The duct itself is also stiffened by the spoke arrangement, thereby reducing low frequency vibration modes.

Abstract: There is provided a load transfer interface in an aircraft engine for transferring a load from a bearing housing to an engine casing. The load transfer interface comprises a first component operatively coupled to and receiving the load from the bearing housing. The first component has a first annular body with a spigot extending axially from the first annular body. The interface comprises a second component operatively coupled to the first component and to the engine casing. The second component has a second annular body with a spigot-receiving cavity disposed therein. The spigot-receiving cavity is shaped and positioned to receive the spigot of the first component. The second component receives the load from the first component and transfers the load to the engine casing.

Abstract: A spray/gas mixer includes a main body having a circumferential wall defining an inlet opening at one end and an outlet opening at another end; a divider baffle within the main body; a swirl duct having a first end adjacent to the wall and a second end extending to the divider baffle; an injector orifice at the first end of the swirl duct; a swirl promoting means; and a restrictor. The swirl promoting means is arranged between the divider baffle and the restrictor. Gas passing through the swirl promoting means is swirled around the first longitudinal axis (A) before passing through the restrictor. The restrictor is disposed between the swirl promoting means and the second end, forcing gas reaching it from an upstream side away from a peripheral region of the interior towards a center axis of the main body.

Abstract: The present application provides an exhaust frame differential cooling system of a gas turbine engine to mitigate a temperature differential along a compressor and/or a turbine to minimize centerline eccentricity of a shaft. The exhaust frame differential cooling system may include a number of compressor temperature sensors positioned about the compressor and/or a number of turbine temperature sensors positioned about the turbine, an exhaust frame including an inner barrel with a bearing tunnel for the shaft, an outer barrel, and a number of struts extending from the inner barrel to the outer barrel, a blower, and a cooling air metering system that provides cooling air from the blower to the bearing tunnel and through the inner barrel, the struts, and the outer barrel in response to the temperature differential being determined along the compressor and/or the turbine.

Abstract: A method is provided for operating a thermal management system of a gas turbine engine. The method includes: operating the gas turbine engine to start-up the gas turbine engine; receiving data indicative of a state of a thermal transport bus of the thermal management system using a sensor, the state of the thermal transport bus including a phase of a thermal fluid within the thermal transport bus; and starting a pump of a pump assembly in response to receiving data indicative of the state of the thermal transport bus of the thermal management system, the pump in fluid communication with the thermal transport bus.

Abstract: A gas turbine engine includes: a fan that is in front of a compressor and rotates in association with a rotating shaft; a casing including an inner shell and an outer shell and a bypass passage; bearings inside the inner shell; an oil mist generator that is outside the outer shell and generates oil mist by mixing oil with compressed air extracted through an extraction port of the compressor; an air pipe through which the compressed air extracted from the compressor is guided to the oil mist generator; and an oil mist pipe through which the oil mist generated by the oil mist generator is guided to the bearings. At least one of the air pipe and the oil mist pipe includes a heat exchanger that is in the bypass passage and is cooled by the air flowing through the bypass passage.

Abstract: A mixer arrangement for aftertreatment of exhaust gas including a housing configured to form a cavity including a center flow channel in which the exhaust gas flows; and at least one side inlet arrangement configured to allow the exhaust gas to enter the center flow channel from the sides thereof and configured to cause an advancing center flow in the center flow channel and a rotating flow around or on the edges of the center flow in the center flow channel; wherein the at least one side inlet arrangement contains at least a pair of side inlet pipes on the side of the center flow channel.

Abstract: A vibrational dampening element is attached to a component and configured to adjust the amplitude of oscillations of the component. The vibrational dampening element includes a mass. The mass includes a main body and a member extending from the main body. A casing that encapsulates the mass. A fluidic chamber defined between the mass and the casing. A first fluidic portion is disposed between a first side of the mass and the casing. The first fluidic portion includes a first accumulator portion directly neighboring the member. A second fluidic portion is disposed between a second side of the mass and the casing. The second fluidic portion includes a second accumulator portion directly neighboring the member. The first accumulator portion is in fluid communication with the second accumulator portion. The vibrational dampening element further includes a primary passage that extends between the first fluidic portion and the second fluidic portion.

Abstract: A method and a system for synthesizing output power provided by an engine are provided. The engine comprising a compressor section, a combustor, and a turbine section in serial fluid flow communication. The engine is operated and, during the operating of the engine, a pressure of fluid at an exit of the compressor section, a temperature upstream of the exit of the compressor section, and a fuel flow rate to the engine are determined. A synthesized value of output power provided by the engine is determined based on a product of at least a first factor, a second factor, and a third factor, the first factor being a function of the pressure, the second factor being a function of the temperature, and the third factor being a function of the fuel flow rate. The synthesized value of output power provided by the engine is output.

Abstract: An aircraft auxiliary power unit is equipped with a charging compressor. A method determines a surge parameter indicative of a risk that the charging compressor will display the phenomenon known as surge. A method and a system control a relief valve of this charging compressor. The method for determining the surge parameter includes calculating this surge parameter Ppomp as being the sum of a first term T1 and of a second term T2, the first term T1 being calculated on the basis of a first pressure P1 measured downstream of a diffuser of the charging compressor, and of a second pressure P2 measured upstream of the diffuser, the second term T2 being calculated on the basis of a third pressure P3 measured upstream of the diffuser and of an ambient pressure Psamb indicative of a pressure of an ambient environment.

Abstract: A waste heat recovery (WHR) system that can be utilized in internal combustion engine systems includes at least two circuits, one having a low pressure working fluid and another having a high pressure working fluid. Each circuit can include heat exchangers to allow the working fluid to absorb heat form one or more heat source fluids associated with the engine. The system can also include an expander configured to receive the working fluid from the at least two circuits, and generating mechanical power. The system also can include a condenser, a sub cooler, and at least one working fluid pump to pump the working fluid in the at least two circuits. The cooling system also includes a controller that can receive temperature and pressure values from various locations in the WHR system and control at least the flow rates of the working fluids in the at least two circuits.

Abstract: This invention relates to a multi-stage rotor (10). More specifically, the invention relates to a multistage rotor (10) for the compressor stage of a machine that, through a concentric configuration of its innermost (12), outermost (24) and intermediary (16) blade sets co-operative with a reverse flow convoluting ducting arrangement, provides an axially compact, lighter and more easily maintainable compressor rotor for such machine. The multi-stage rotor (10) includes innermost (30), outermost (34) and intermediary (32) duct ports comprising a radial duct spans, as measured between respective diametrically inner and outer duct walls of the duct port, being greater than respective innermost (48), outermost (54) and intermediary (50, 52) radial blade spans of the respective blade sets rotatable at least partially within such duct port.

Abstract: Provided is a bearing structure that can support a rotary shaft with a small number of components. The bearing structure includes: a cylindrical sleeve (32) provided so as to surround the outer circumference of a rotary shaft (4) that rotates about a center axis line (CL) and configured to rotate together with the rotary shaft (4); thrust collars (34a, 34b) provided so as to abut against both ends in the center axis line (CL) direction of the cylindrical sleeve (32), respectively, having a larger diameter than the cylindrical sleeve (32), and configured to rotate together with the rotary shaft (4); and a compressor-side journal bearing (12) arranged on the outer circumference side of the cylindrical sleeve (32) and between the thrust collars (34a, 34b).

Abstract: A system comprising an aftertreatment system comprising: a catalyst member, and a first exhaust conduit upstream of the catalyst member; a first temperature sensor operatively coupled to the catalyst member; a flow sensor coupled to the first exhaust conduit; and a controller. The controller determines a temperature of the catalyst member, a flow rate of exhaust within the first exhaust conduit, and a space velocity of the exhaust within the catalyst member. The controller determines a first degradation value indicative of a degradation of the catalyst member. The controller determines a first difference between the first degradation value and a first degradation reference value and a second difference between the first degradation value and a second degradation reference value. After determining that the first difference is less than the second difference, the controller selects a first calibration metric. The controller determines a first efficiency value associated with the catalyst member.

Abstract: A method of fabricating an airfoil fairing for a vane arc segment includes providing a mandrel that necks down through a mandrel neck portion, providing fiber plies around the mandrel to form a tube that defines at least a portion of an airfoil profile of an airfoil section of an airfoil fairing, the fiber plies following the mandrel neck portion such that the tube has a corresponding tube neck portion that necks down to a collar, and removing the mandrel from the tube.

Abstract: A powerplant is provided that includes an engine and a water recovery system. The engine includes an engine combustor, an engine turbine, a flowpath and a fluid delivery system. The flowpath extends out of the engine combustor and through the engine turbine. The fluid delivery system includes a hydrogen reservoir and an oxygen reservoir. The hydrogen reservoir is configured to store fluid hydrogen as liquid hydrogen. The oxygen reservoir is configured to store fluid oxygen as liquid oxygen. The fluid delivery system is configured to provide the fluid hydrogen and the fluid oxygen for combustion within the engine combustor to produce combustion products within the flowpath. The water recovery system is configured to extract water from the combustion products. The water recovery system is configured to provide the water to a component of the powerplant.

Abstract: A mixer, an exhaust aftertreatment component, an exhaust aftertreatment system and a vehicle in which the mixer comprises: an inlet cover, providing an inlet space; an outlet cover, providing an outlet space; and a connecting pipe part, comprising a gas inlet inside the inlet space, a gas outlet inside the outlet space, and an injection inlet; wherein the connecting pipe part comprises a conical section and a pipe section connected downstream to the conical section, the conical section is located inside the inlet space, a side wall of the conical section comprises a plurality of openings distributed along a circumferential direction, the gas inlet comprises the plurality of openings, and a swirling structure is provided on the plurality of openings.