Abstract: A gas turbine engine comprises, in axial flow sequence, a fan assembly, a compressor module, a turbine module, and an exhaust module. The gas turbine engine comprises first and second engine mount planes. The first and second engine mount planes are configured to support gas turbine engine in machine body. The gas turbine engine has axial length L, with axial length extending from inlet face of engine to exhaust face of engine. The first engine mount plane is positioned axially along gas turbine engine at first engine mount plane position, with first engine mount plane position within a range of between 0.24*L to 0.32*L from the inlet face of the engine. The second engine mount plane is positioned axially along gas turbine engine at second engine mount plane position, with second engine mount plane position within a range of between 0.73*L to 0.79*L from the inlet face of the engine.

Abstract: A gas turbine engine comprises, in axial flow sequence, a fan assembly, a compressor module, a turbine module, and an exhaust module. The gas turbine engine comprises first and second engine mount planes. The first and second engine mount planes are configured to support gas turbine engine in machine body. The gas turbine engine has axial length L, with axial length extending from inlet face of engine to exhaust face of engine. The first engine mount plane is positioned axially along gas turbine engine at first engine mount plane position, with first engine mount plane position within a range of between 0.24*L to 0.32*L from the inlet face of the engine. The second engine mount plane is positioned axially along gas turbine engine at second engine mount plane position, with second engine mount plane position within a range of between 0.73*L to 0.79*L from the inlet face of the engine.

Abstract: A turbomachine assembly is provided. The assembly includes: a first rotor module including a first blade, a second rotor module, connected to the first rotor module, and including a second blade of smaller length than the first blade, and a damping device including a plurality of first radial external surfaces supported with friction against the first module. The damping device is stepped, and includes a second radial external surface supported with friction against the second module, so as to couple the modules for the purpose of damping their respective vibrational movements during operation.

Abstract: A turbomachine assembly is provided. The assembly includes: a first rotor module including a first blade, a second rotor module, connected to the first rotor module, and including a second blade of smaller length than the first blade, and a damping device including a plurality of first radial external surfaces supported with friction against the first module. The damping device is stepped, and includes a second radial external surface supported with friction against the second module, so as to couple the modules for the purpose of damping their respective vibrational movements during operation.

Abstract: Provided are automated cell culture systems and related in vitro cell culture methods, including for a co-culture of different cell populations having different cell culture conditions. For example, the system may comprise a bioreactor having a plurality of cell culture compartments, the bioreactor having a fluid port fluidly connected to the plurality of cell culture compartments. A pump fluidly connected to the fluid port can provide a cell culture medium to the plurality of culture compartments. A sensor is operably connected to at least one of the plurality of cell culture compartments for measuring at least one cell culture parameter. In this manner, a controller electronically connected the pump and sensor, is configured to automatically adjust a pump flow rate and/or a cell culture gas content to provide a desired steady-state cell culture parameter for facilitating cells interactions and collection of products representative of said interactions.

Abstract: The present invention relates to a method for dimensioning a turbomachine comprising a casing and a disc to which at least one blade is secured, said disc being rotationally driven by a shaft about a turbomachine axis (z), comprising: —acquisition (E1) of the coordinates (P) of the ends of the leading edge and of the trailing edge of the blade in a frame of reference connected with the disc; —expression (E2) of the coordinates (P?) of the ends of the leading edge and of the trailing edge of the blade in a frame of reference connected with the casing; —calculation (E3) of the distance (g) between the casing and the ends of the leading edge and trailing edge of the blade from the coordinates (P?) expressed in the frame of reference connected with the casing; —calculation (E4) of the contact pressures between the blade and the casing along the end of the blade from the calculated distance (g); —calculation (E5) of the reaction forces and moments resulting from contact between the blade and the casing from the ca

Abstract: The present invention relates to a method for dimensioning a turbomachine comprising a casing and a disc to which at least one blade is secured, said disc being rotationally driven by a shaft about a turbomachine axis (z), comprising:—acquisition (E1) of the coordinates (P) of the ends of the leading edge and of the trailing edge of the blade in a frame of reference connected with the disc;—expression (E2) of the coordinates (P?) of the ends of the leading edge and of the trailing edge of the blade in a frame of reference connected with the casing;—calculation (E3) of the distance (g) between the casing and the ends of the leading edge and trailing edge of the blade from the coordinates (P?) expressed in the frame of reference connected with the casing;—calculation (E4) of the contact pressures between the blade and the casing along the end of the blade from the calculated distance (g);—calculation (E5) of the reaction forces and moments resulting from contact between the blade and the casing from the calcula