Abstract:
A variable area turbine arrangement according to an exemplary aspect of the present disclosure includes, among other things, a variable vane assembly and a secondary flow system associated with the variable vane assembly. Flow modulation of a cooling fluid through the secondary flow system is changed simultaneously with actuation of the variable vane assembly.
Abstract:
A hybrid sacrificial core for forming an impingement space and an internal cooling passageway network separate from the impingement space of a part may comprise a ceramic core having a first surface portion for forming the impingement space, and a refractory metal core that forms a plurality of passages of the internal cooling passageway network.
Abstract:
A method of manufacturing a military engine includes the steps of designing a commercial engine core, including a combustor, a high pressure compressor driven by a high pressure turbine, and a low pressure turbine designed to drive a low pressure compressor, and a fan through a gear reduction. A high speed fan is attached to the low pressure turbine, such that the combustor, high pressure compressor, low and high pressure turbines from an engine designed for commercial purposes is utilized for military purposes. A gas turbine engine is also disclosed.