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: This invention relates to reloading devices for muzzle loading rifles or muskets in general, and more specifically to a construction, wherein a frangible sheet of material is used to maintain the powder and ball in their proper orientation, due to the frictional engagement between two cooperating elements, one of which houses a plunger that can be actuated to tear the sheet of material, and introduce the charge and projectile into the barrel of a firearm.