IMPROVED GAS TURBINE ENGINE
IMPROVED GAS TURBINE ENGINE
- New search for: GALLAGHER JAMIE W
- New search for: BLACKER DANIEL
- New search for: BLAKEMORE HUGH J
- New search for: MANSER ADRIAN M
- New search for: WATSON JONATHAN V
- New search for: FRY ALEXANDER L
- New search for: BARKER ROBERT A
- New search for: THORP JAMES
- New search for: PARENT MARIE-OCÉANE
- New search for: GALLAGHER JAMIE W
- New search for: BLACKER DANIEL
- New search for: BLAKEMORE HUGH J
- New search for: MANSER ADRIAN M
- New search for: WATSON JONATHAN V
- New search for: FRY ALEXANDER L
- New search for: BARKER ROBERT A
- New search for: THORP JAMES
- New search for: PARENT MARIE-OCÉANE
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.
Document information
IMPROVED GAS TURBINE ENGINE
2023-06-01
Patent
Electronic Resource
English