| 摘要 |
Heat recuperation system for the family of shaft powered aircraft gas turbine engines, comprise of a shaft powered gas turbine engine with air inlet system, compressor, combustor, exhaust turbines, engine shaft(s) and exhaust system, where the shaft powered aircraft gas turbine engine has an Annular Finned-Tube Heat Exchanger (AFTHE) located in the exhaust system and a heat recovery apparatus functionally coupled to the AFTHE. The AFTHE with working fluid recovers heat from the exhaust gas. The recovered heat vaporizes the working fluid which drives a turbo-expander. The mechanical work developed by the turbo-expander can be used for driving the propulsion systems, compressor or an electric generator. The thermal energy available after expansion work can be used to heat the inlet air into the engine to prevent ice ingestion during icing conditions. This system increases performance and life of the engine, and reduces emissions, heat released to the environment, fuel consumption and fuel cost. |
