摘要:
A gas turbine engine according to an exemplary aspect of the present disclosure includes a windmill pump driven by a spool. A first pump driven by said spool with an air-oil cooler is located downstream of the first pump. A second pump is also driven the spool with an air-air precooler located downstream of the second pump. A method of operating a gas turbine engine during a “windmilling” condition includes driving a windmill pump with a spool during a “windmilling ” condition. A lubricant is communicated to a geared architecture with the windmill pump. A first pump is driven by the spool and an air-oil cooler is located downstream of the first pump.
摘要:
A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan, a geared architecture, a spool which drives the fan through the geared architecture, and at least one component geared to the spool and being operable to control a speed of the spool during a “windmilling” condition. A method of gas turbine engine operations during a “windmilling” condition is also disclosed.
摘要:
Accessory gearboxes and related gas turbine engine systems are provided. In this regard, a representative accessory gearbox for a gas turbine engine is operative to be driven by rotational energy extracted from the gas turbine engine and imparted to the gearbox by multiple tower shafts.
摘要:
A gas turbine engine includes, among other things, a fan section including a fan rotor, a gear train defined about an engine axis of rotation, a high spool, and a low spool including a low pressure turbine that drives the fan rotor through the gear train. A static structure includes a first engine mount location and a second engine mount location.
摘要:
A buffer air pump provides pressurized cooling air for cooling components of the gas turbine engine. The buffer air pump is supported on and/or within an accessory gearbox and draws bypass air in through an inlet manifold. An impeller supported within a scroll housing pressurizes the incoming bypass air and directs the pressurized air through passages to a component requiring cooling. The buffer air pump draws in relatively cool air from the bypass flow, pressurizes the air with the impeller and sends the air through conduits and passages within the gas turbine engine to the component that requires cooling such as a bearing assembly.
摘要:
A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk and at least one spacer adjacent to the plurality of blades. A flow passage is defined between the rotor disk and the blades and spacer. A plurality of inlets are formed within the spacer to pump air into the flow passage.
摘要:
A rotor disk for a gas turbine engine includes a CMC hub and a rail integrated with the CMC hub opposite the multiple of CMC airfoils, the rail defines a rail platform section that tapers to a rail inner bore.