The gas turbine engine assembly can include a first component having a male fit perimeter, a second component having a female fit perimeter forming an interference fit with the male fit perimeter, one of the first component and the second component having a pulling lip spanning transversally and further spanning peripherally, and a structure holding the pulling lip transversally offset from the interference fit, the structure having a bending portion extending at least partially transversally.

Method for monitoring the operation of a pair of turboprop engines of an aircraft comprising the steps of: detecting the sound pressure generated by the first or second turboprop engine generating a respective first or second signal x(t); iteratively calculating by means of a function Rx/Ry the similarity between the first/second signal x(t)/y(t) at a time T1 and at a time T2 subsequent to time T1; and storing the degrees of similarity calculated in successive iterations in order to detect situations of normal operation of the engines when the degrees of similarity fall in successive iterations within the interval of a first value and to detect a potential fault situation in the engines when the degrees of similarity depart from this interval.

A device is provided comprising an expansion machine for generating mechanical energy by expanding vapor of a working medium; a generator connected to a shaft of the expansion machine and used for generating electric energy from mechanical energy of the expansion machine; wherein the expansion machine and the generator form a structural unit with an exhaust vapor chamber between the expansion machine and the generator, and wherein, when the expansion machine is in operation, working medium expanded into the exhaust vapor chamber contacts the generator; and means for feeding, in particular injecting, a liquid working medium into the exhaust vapor chamber. Also provided is an ORC device comprising the device and a method for operating the device.

A device is provided comprising an expansion machine for generating mechanical energy by expanding vapor of a working medium; a generator connected to a shaft of the expansion machine and used for generating electric energy from mechanical energy of the expansion machine; wherein the expansion machine and the generator form a structural unit with an exhaust vapor chamber between the expansion machine and the generator, and wherein, when the expansion machine is in operation, working medium expanded into the exhaust vapor chamber contacts the generator; and means for feeding, in particular injecting, a liquid working medium into the exhaust vapor chamber. Also provided is an ORC device comprising the device and a method for operating the device.

A bypass valve assembly for a turbine generator includes a valve body, bypass seats, valve stem, valve cap, bypass valve disc, bypass valves, and pressure seal head. The valve body defines a central bore and a plurality of passageways. Each passageway has an inlet smaller than its outlet. Each bypass seat is within the inlet of a corresponding passageway. The bypass seats have a higher wear resistance than the valve body. The valve stem is within the central bore. The valve cap is secured to the valve body. The bypass valve disc is secured to the valve stem. Each bypass valve has a base portion and a nose portion. Each nose portion defines a contoured surface area with a wear coating and extends into a corresponding passageway. The pressure seal head is disposed around the valve stem and defines steps having a wear coating.

A bypass valve assembly for a turbine generator includes a valve body, bypass seats, valve stem, valve cap, bypass valve disc, bypass valves, and pressure seal head. The valve body defines a central bore and a plurality of passageways. Each passageway has an inlet smaller than its outlet. Each bypass seat is within the inlet of a corresponding passageway. The bypass seats have a higher wear resistance than the valve body. The valve stem is within the central bore. The valve cap is secured to the valve body. The bypass valve disc is secured to the valve stem. Each bypass valve has a base portion and a nose portion. Each nose portion defines a contoured surface area with a wear coating and extends into a corresponding passageway. The pressure seal head is disposed around the valve stem and defines steps having a wear coating.

A turbocharger includes a three-way rotary turbine bypass valve (TBV) operable to selectively supply exhaust gases to a turbine feed passage leading to a turbine wheel, and/or to a bypass passage that bypasses the turbine wheel. The TBV is structured and arranged to close the bypass outlet of the valve when the turbine outlet is fully open, to partially open the bypass passage while the turbine outlet remains fully open, to fully open the bypass passage when the turbine outlet is partially closed, and to fully open the bypass passage when the turbine passage is fully closed. The TBV turns the exhaust gas flows through acute angles between inlet and outlets, mitigating pressure losses through the valve. Leakage to bypass is minimized by a labyrinth seal formed when the valve member closes the bypass outlet.

A turbocharger includes a three-way rotary turbine bypass valve (TBV) operable to selectively supply exhaust gases to a turbine feed passage leading to a turbine wheel, and/or to a bypass passage that bypasses the turbine wheel. The TBV is structured and arranged to close the bypass outlet of the valve when the turbine outlet is fully open, to partially open the bypass passage while the turbine outlet remains fully open, to fully open the bypass passage when the turbine outlet is partially closed, and to fully open the bypass passage when the turbine passage is fully closed. The TBV turns the exhaust gas flows through acute angles between inlet and outlets, mitigating pressure losses through the valve. Leakage to bypass is minimized by a labyrinth seal formed when the valve member closes the bypass outlet.

A variable geometry turbine comprising: a wheel supported for rotation about an axis; a housing comprising a first volute for receiving gas from a first source and a second volute for receiving gas from a second source; the first and second volutes being separated by a dividing wall; and an inlet passageway surrounding the wheel and fluidly connected to the volutes; the inlet passageway at least partially defined between a first wall and an opposite second wall, the first wall being moveable along the axis to vary the size of the inlet passageway; wherein a tip of the dividing wall defines a first radius relative to the axis, and a radially outermost part of the first wall positioned within the inlet passageway defines a second radius relative to the axis, and wherein the first radius is at least around 1% larger than the second radius.

The invention relates to a bypass turbomachine (2) for an aircraft, comprising a gas generator (5) and a ducted fan (4) comprising variable pitch blades (18) configured to take a reverse thrust position driving a reverse flow (24) of air within a secondary duct (16), the gas generator (5) being connected to a fan casing (3) by a stator blade assembly (40) that passes through the secondary duct, first openings (28) for letting in air from the reverse flow being located on an outer casing (17) at least partially internally delimiting the outer duct, and second openings (29) for letting said air out being located on an inner casing (14) at least partially externally delimiting an inner duct (12). The first openings are located within a plane that is perpendicular to a longitudinal axis (C) of the turbomachine and passes substantially through the middle of the blade assembly.