The invention relates to a fuel system (1) for a turbine engine, adapted for injecting fuel in a combustion chamber (5) of the turbine engine, comprising: a pilot circuit (10), adapted for injecting fuel in the combustion chamber (5) by means of a pilot pipe (14), a main circuit (20), adapted for injecting fuel in the combustion chamber (5) by means of a main pipe (24),
the fuel system (1) being characterized in that it also comprises a thermal conductor (30) confined between the pilot pipe (14) and the main pipe (24) and configured to direct the thermal flow from the main pipe (24) to the pilot pipe (14).

A heat exchanger (2) comprising a duct (4) through which a first fluid (e.g. a coolant such as ram air) may flow, and one or more vanes (18) disposed within the duct (4) and configured to disrupt the flow of the first fluid through the duct (4). Each vane (18) comprises one or more flow channels (24) through which a second fluid (e.g. a fluid to be cooled, such as engine coolant) may flow so as to transfer heat between the first fluid flowing through the duct (4) and the second fluid flowing through the one or more flow channels (24). The flow channels (24) within the vanes (18) are separated from the duct (4) by a channel wall such that fluid cannot flow between the duct (4) and the flow channels (24).

An air turbine starter having a housing that includes an inlet and an outlet to define an air flow path from the inlet to the outlet. A stator includes a plurality of circumferentially spaced vanes extending into the air flow path and defined a stator core. A coating surrounds one or more portions of the housing, defining the housing core, or the stator, defining the stator core. The housing core or the stator core includes a first material having a first hardness and the coating comprises a second material having a second hardness.

An air-moving device may include an aerodynamic stator. The aerodynamic stator may be positioned forward of a motor of the air-moving device and aftward of an aerodynamic rotor of the air-moving device. A control unit may be integrated in and in thermal communication with the aerodynamic stator. The aerodynamic stator may transfer heat from the control unit to thermally conductive stator vanes of the aerodynamic stator. An airflow generated by the aerodynamic rotor may facilitate heat dissipation from the thermally conductive stator vanes. The aerodynamic stator may include electrically conductive stator vanes. The electrically conductive stator vanes may provide at least one of power or control signaling to the control unit.

An aerodynamic stator for an air-moving device is provided. The aerodynamic stator may receive a motor or a control unit of the air-moving device in a central cavity. The aerodynamic stator may include conductive stator vanes. The conductive stator vanes may be in conductive communication with the motor or control unit. An airflow generated by the aerodynamic rotor may facilitate heat dissipation from the thermally conductive stator vanes. The conductive stator vanes may include thermally conductive stator vanes. The conductive stator vanes may include electrically conductive stator vanes. The electrically conductive stator vanes may provide at least one of power or control signaling to the control unit.

An air-moving device may include an aerodynamic stator. The aerodynamic stator may be positioned forward of a motor of the air-moving device and aftward of an aerodynamic rotor of the air-moving device. A control unit may be integrated in and in thermal communication with the aerodynamic stator. The aerodynamic stator may transfer heat from the control unit to thermally conductive stator vanes of the aerodynamic stator. An airflow generated by the aerodynamic rotor may facilitate heat dissipation from the thermally conductive stator vanes. The aerodynamic stator may include electrically conductive stator vanes. The electrically conductive stator vanes may provide at least one of power or control signaling to the control unit.

Clearance control systems with thermal actuators are disclosed. An example thermally-actuated clearance control system for a gas turbine engine includes a compliant material; a high-conductive material coupled to a first surface of the compliant material, the high-conductive material thermally coupling the compliant material to a heated substance, the compliant material to expand radially-inward toward a fan blade when the high-conductive material provides heat; and an abradable material coupled to a second surface of the compliant material facing the fan blade.