公开(公告)号：US20240141837A1

公开(公告)日：2024-05-02

申请号：US18311460

申请日：2023-05-03

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jesse M Chandler ,  Marc J. Muldoon ,  Jon E. Sobanski ,  Neil J. Terwilliger ,  Joseph B. Staubach

IPC: F02C7/22 ,  F02C7/18

CPC classification number: F02C7/22 ,  F02C7/18 ,  F05D2260/211

Abstract: A propulsion system for an aircraft includes a gas generating core engine generates an exhaust gas flow that is expanded through a turbine section, a power turbine driven by the exhaust gas flow, a propulsor coupled to the power turbine, a hydrogen fuel system configured to supply hydrogen fuel to the combustor through a fuel flow path, a condenser arranged along the core flow path and configured to extract water from the exhaust gas flow, and an evaporator arranged along the core flow path receiving a portion of the water extracted by the condenser to generate a steam flow that is injected into the core flow path upstream of the turbine section.