GAS TURBINE ENGINE WITH SHORT TRANSITION DUCT

摘要

A turbine section for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan drive turbine including a fan drive duct, the fan drive turbine being configured to drive a fan section through a geared architecture at a speed that is less than an input speed to the geared architecture. A fan drive turbine includes a fan drive duct, the fan drive turbine being configured to drive a fan section through a geared architecture at a speed that is less than an input speed to the geared architecture. At least one upstream turbine is configured to drive at least one compressor. The at least one upstream turbine includes a turbine duct defining a conical flow path having a conical inlet defined by a first diameter and a conical outlet defined by a second diameter greater than the first diameter. The conical outlet is in fluid communication with the fan drive duct downstream of the conical outlet. At least one row of shrouded rotor blades defines at least a portion of the conical flow path. A method of designing a gas turbine engine is also disclosed.

主权项

1. A turbine section for a gas turbine engine comprising:
a fan drive turbine including a fan drive duct, the fan drive turbine being configured to drive a fan section through a geared architecture at a speed that is less than an input speed to the geared architecture; at least one upstream turbine configured to drive at least one compressor, the at least one upstream turbine including a turbine duct defining a conical flow path having a conical inlet defined by a first diameter and a conical outlet defined by a second diameter greater than the first diameter, the conical outlet being in fluid communication with the fan drive duct downstream of the conical outlet; and at least one row of shrouded rotor blades defining at least a portion of the conical flow path.