Abstract: A system is provided, including an airfoil. The an airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.

Abstract: A method detects a failure in a fuel return valve of an aircraft engine fuel circuit. A fuel system is connected to a fuel tank of the circuit and includes a high-pressure pump delivering a flow rate to an actuating cylinder, a cutoff valve capable of feeding the actuating cylinder disposed in a feed pipe of the engine; a fuel return pipe; a fuel return valve arranged to switch between an open position and a closed position. The method includes starting the engine at an engine speed; increasing the engine speed until a flow rate reaches a predefined value sufficient for opening the cutoff valve; measuring the position of the actuating cylinder and an engine speed corresponding to the opening of said cutoff valve.

Abstract: A blade outer air seal for a gas turbine engine includes a gas path surface exposed to exhaust gas flow, a first side extending radially outward from the gas path surface, a second side extending radially outward from the gas path surface, and a plurality of film cooling holes disposed on at least one of the gas path surface. The first side and the second side, the film cooling holes are disposed at locations described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate and a radial coordinate relative to a defined point of origin. A gas turbine engine is also disclosed.

Abstract: Aircraft turbomachine comprising at least one heat exchanger (40) and a gearbox (10) in a V-shaped overall configuration and comprising two lateral arms (20) joined together by a central joining piece, the heat exchanger being mounted between the arms of the gearbox.

Abstract: A variable displacement vane pump has a pressure controlled valve moveable between first and at least second valve positions based on an output pressure of the pressurized lubricant delivered through the outlet. The pressure controlled valve provides an integrated fail safe function to the pump when an electrical valve fails. The pressure controlled valve is inactive in the first position for an output pressure below a threshold level, allowing an electrical valve (current, solenoid, pulse width modulation (PWM) valve) to selectively control pressure in the control chamber under normal operation of the pump. In fail safe regulation mode, the electrical valve function is disabled and the pressure controlled valve is active in its second position, controlling pressure in the control chamber. Channels and vents in the pump can be opened and closed based on selective movement of the valve when the outlet pressure is at or above a threshold level.

Abstract: A cooling system for a turbine bucket including a multi-wall blade and a platform. A cooling circuit for the multi-wall blade includes: an outer cavity circuit and a central cavity for collecting cooling air from the outer cavity circuit; a platform core air feed for receiving the cooling air from the central cavity; and an air passage for fluidly connecting the platform core air feed to a platform core of the platform.

Abstract: An airflow system for a gas turbine system according to an embodiment includes: a compressor component of a gas turbine system; an airflow generation system for attachment to a rotatable shaft of the gas turbine system, the airflow generation system and the compressor component drawing in an excess flow of air through an air intake section; a mixing area for receiving an exhaust gas stream produced by the gas turbine system; an air extraction system for: extracting at least a portion of the excess flow of air generated by the airflow generation system and the compressor component to provide bypass air; and diverting the bypass air into the mixing area to reduce a temperature of the exhaust gas stream; and an exhaust processing system for processing the reduced temperature exhaust gas stream.

Abstract: A method of determining a duration of a movement of a starter air valve of a turbine engine, the valve for regulating the passage of a flow of pressurized air from upstream to the downstream of pipework, where the downstream side is connected to a pneumatic starter of the turbine engine, the method including determining an instant of initiation and an instant of completion of a movement of the valve during a movement phase of the valve, determining the duration of the movement of the valve, by subtracting the instant of initiation from the instant of completion, calculating a difference between the determined duration of the movement and a theoretical value of the duration.

Abstract: A system and a method for controlling operation of a power plant system. The system has at least a gasifier, a boiler, an induced draft fan, and a baghouse. A controller in communication with the system is configured to implement a first stage and/or a second stage sequences after detecting loss of flame in the boiler using a temperature measurement device. The method includes automatically bypassing the baghouse and controlled (e.g., decreasing) the speed of the induced draft fan in the system to relight the boiler. The input feed to the gasifier can be limited and devices operated for a predetermined amount of time before reigniting the boiler.

Abstract: An example airfoil includes an airfoil body with a leading edge and a trailing edge joined by a pressure side and a suction side to provide an external airfoil surface extending in a radial direction from at least one platform. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location. The local axial chord corresponds to a width of the airfoil between the leading edge and the trailing edge at the span location, and the Cartesian coordinates in Table 1 have a tolerance relative to the specified coordinates of up to +0.050 inches (+1.27 mm).

Abstract: A vane assembly includes a plurality of airfoils that extend from a first end to a second, opposed end. A first platform is at the first end and is joined to the plurality of airfoils. A second platform is at the second end and is joined to the plurality of airfoils. At least one of the first platform, the second platform and the plurality of airfoils include a three-dimensional arrangement of continuous fibers and at least one different one of the first platform, the second platform and the plurality of airfoils include a two-dimensional arrangement of continuous fibers.

Abstract: The epicyclic reduction gear comprises a planetary input shaft, planet gears meshing around said shaft and supported by a planet carrier, and two transverse sides. According to the invention, the reduction gear comprises at least one fluid transfer pipe suitable for being connected to a fluid supply source and passing through the planet carrier, being linked in rotation to same, from a first of said transverse sides of the reduction gear to a second of said transverse sides of the latter in order to open on the outside of the reduction gear and dispense the fluid.

Abstract: A method and system for a heat exchanger are provided. The heat exchanger includes a plurality of arcuate heat exchanger segments, each including a first header configured to extend circumferentially about at least a portion of a circumference of an internal surface of a fluid duct. The heat exchanger also includes a second header configured to extend circumferentially about the portion spaced axially apart from the first header in a direction opposite of fluid flow through the fluid duct and a first plurality of heat exchanger tubes extending generally axially between the first header and the second header, the first plurality of heat exchanger tubes each including a first flow path separate from a second flow path of any other of the first plurality of heat exchanger tubes, the first flow path changing direction along the flow path from the first header to the second header.

Abstract: A compressor that includes a frame, a rotor assembly, and a heat sink assembly. The rotor assembly includes a bearing assembly to which the heat sink assembly is secured. The compressor is configured such that, during use, air is drawn through the interior of the frame. The heat sink assembly then extends radially from the bearing assembly into the air path through the frame such that the air flows over the heat sink assembly.

Abstract: A system for recycling heat or energy of a working medium of a heat engine for producing mechanical work is described. The system may comprise a first heat exchanger (204) for transferring heat from a working medium output from an energy extraction device (202) to a heating agent to vaporize the heating agent; a second heat exchanger (240) for transferring further heat to the vaporized heating agent; a compressor (231) coupled to the second heat exchanger (240) arranged to compress the further-heated heating agent; and a third heat exchanger (211) for transferring heat from the compressed heating agent to the working medium. A heat pump is also described.

Abstract: An oil lubrication system is provided. The oil lubrication system may comprise an oil pump, a conduit fluidly coupled to the oil pump, and a damper fluidly coupled to the conduit. The damper may further comprise a volume configured to receive oil in response to a pulse event. A heat exchanger may also be fluidly coupled to the conduit. In various embodiments, the damper may comprise a spherical volume. The damper may be fluidly coupled to the conduit between the oil pump and the heat exchanger. An adapter may be mechanically coupled between the conduit and the damper. The adapter may comprise a passage in fluid communication with the conduit and the damper. The damper may further comprise a membrane. A gas or compressible fluid may be disposed in the damper on a first side of the membrane. The membrane may be configured to separate the gas from the oil.

Abstract: A method is disclosed for evaluating a soot quantity accumulated in a Selective Catalytic Reduction wash-coated particulate filter of an internal combustion engine. The internal combustion engine is equipped with an exhaust gas aftertreatment system including an urea injector. Using a map correlating a urea quantity value, a NOx quantity value, a temperature value and a mass flow value to a correction value of a soot quantity is used to correct an estimated value of the soot quantity in order to obtain an evaluated value of the soot quantity.

Abstract: A scroll compressor includes scroll compressor bodies, which, in turn, include a fixed scroll compressor body and a moveable scroll compressor body. The scroll compressor bodies have respective bases and respective scroll ribs that project from the respective bases, and which mutually engage about an axis for compressing fluid. The scroll compressor also includes a housing to house the scroll compressor bodies. A separator plate is configured to separate a high-pressure gas chamber from a low-pressure gas chamber within the housing. The separator plate has no machined surfaces, and has an outer perimeter portion which is attached to an unmachined inner surface of the housing. Having no machined surfaces indicates that no material is removed from the separator plate during its manufacture apart from operations to form initial inner and outer diameters of the separator plate.

Abstract: A piece of electronic equipment of a turbomachine, including a wall of which the inner surface defines at least one channel for the passage of a ventilating air stream of which the outlet opens on an outer surface of the wall with a view to discharging the ventilating air stream towards the outside of the equipment, wherein, at the outlet, a mechanism for diverting and/or guiding at least a portion of the discharged air stream, over at least a part of the outer surface of the wall.

Abstract: A method for operating a gas turbine engine is disclosed. The method includes detecting an off-load transient of the gas turbine engine. The method includes reducing a total flow of fuel to a combustor section of the gas turbine engine to a first reduced flow in response to detecting the off-load transient. The method includes adjusting a position of an inlet guide vane in response to detecting the off-load transient until either an on-load transient is detected or until an amount of time elapsed since detection of the off-load transient exceeds a maximum override time.