A turbomachine assembly includes a first combustor (30) configured to combust fuel and compressed air and a second combustor (32) configured to combust fuel and compressed air. Flow moves through the first combustor (30) in a first direction and flow moves...

A gas turbine engine system (10) includes a fan assembly (12), a low pressure compressor (14), a low pressure turbine (16), a plurality of engine cores (30-1 to 30-n) including a first engine core and a second engine core, and a control assembly (36). A pr...