A turbocharger includes a turbine housing that is a cast component, a turbine scroll passage, a discharge port, and a discharge port defining member. The turbine scroll passage surrounds the circumference of a turbine chamber defined in the turbine housing and the circumference of the turbine chamber. Exhaust gas that has passed through the turbine chamber is conducted to the discharge port. The discharge port defining member constitutes a wall surface of the discharge port. The discharge port defining member includes a tubular main body wall and an outer circumferential edge. The main body wall constitutes a wall surface of the discharge port. The outer circumferential edge extends from the distal end of the main body wall and outward in the radial direction of the impeller shaft. The outer circumferential edge is fixed between the turbine housing and a downstream exhaust pipe, which is connected to the discharge port.

A dual wall liner for a gas turbine engine may comprise a shell having a first side and a second side, a panel contacting the shell, the panel at least partially defining a hot gas path through which a hot gas flows, wherein the first side of the shell faces the panel, wherein the shell includes a thermal barrier coating (TBC) disposed on the first side of the shell. The TBC may thermally protect the shell from heat from a hot gas path.

The thermal blanket can be used for shielding an engine component. The thermal blanket has a window providing visual access to the engine component. The thermal blanket can have a non-transparent portion having an opening extending across the thickness of the non-transparent portion, the opening delimited by an internal edge of the non-transparent portion, and a transparent portion of transparent material in the opening, the transparent portion secured to the internal edge of the non-transparent portion.

An airfoil includes an airfoil section that has a ceramic airfoil wall that defines a suction side and a pressure side. There is an interior cavity in the airfoil section. A rib spans across the interior cavity and connects the suction side and the pressure side. The rib has a thermal conductance element that is configured to conduct heat away from the suction side and the pressure side.

A securing tool for a heat retention block covering a turbine casing main body includes: a securing rod, one end of which has an engaging portion with a protrusion; and a socket. The socket includes a guide groove, into which the protrusion of the securing rod is inserted, and a recessed groove. The guide groove includes a first guide groove, which extends in the socket axis direction from a starting end to a terminal end, and a second guide groove, the starting end of which is connected to the terminal end, and which extends from the starting end to a terminal end in a circumferential direction relative to the socket axis. The second guide groove is connected to the recessed groove.

A system and method for determining the condition of a thermal barrier coating on a base metal component, comprising the use of an induction coil to input into the metallic base layer through the coating layer, a temporally varying heat waveform, and measuring the temperature of the coating surface layer resulting from the input of the heat waveform using a temperature sensor disposed close to the surface of the coating layer. A controller correlates a signal from the temporally varying output of the temperature sensor with a signal corresponding to the temporally varying heat waveform, to determine the phase angle between the signals. The controller uses a mathematical relationship between the phase angle and the frequency of the heat waveform to determine the thermal properties of the non-metallic coating. Both the thermal diffusivity and the barrier coating thickness can be accurately obtained by this method and apparatus.

A compressor wheel includes a compressor wheel body, and a thermal insulating coating layer disposed so as to cover at least a part of a back surface of the compressor wheel body.

A combustion section for a gas turbine engine including an inner casing comprising a first material defining an inner diameter of a pressure vessel and a first heat transfer coefficient. A second material is extended at least partially over an outer diameter of the first material. The second material is disposed radially between the first material and a combustor liner. The second material defines a second heat transfer coefficient less than the first heat transfer coefficient.

A housing structure for a rotary machine includes a main body and a heat transfer member. The heat transfer member includes a material having higher thermal conductivity than that of the main body. In addition, the heat transfer member is sandwiched between a first surface and a second surface of the main body while receiving a compressive load from the first surface and the second surface, thereby alleviating temperature distribution that may occur in the main body and reducing thermal deformation.

A variable geometry turbocharger (100) includes a bearing housing (10) including a bearing-housing side support portion (40) configured to support a radially outer portion (38) of a nozzle mount (16) from a side opposite to a scroll flow passage (4) in an axial direction of a turbine rotor (2), and wherein at least one of the following condition (a) or (b) is satisfied: (a) the bearing-housing side support portion (40) includes at least one bearing-housing side recess portion (46) formed so as to be recessed in the axial direction so as not to be in contact with the radially outer portion (38); (b) the radially outer portion (38) of the nozzle mount (16) includes at least one nozzle-mount side recess portion (62) formed so as to be recessed in the axial direction so as not to be in contact with the bearing-housing side support portion (40).