The cooling system may include a compressor bleed conduit extending from a compressor to the turbine blade cooling fluid supply that provides cooling fluid to at least one turbine blade.
The.Ĭooling system with compressor bleed and ambient air for gas turbine engineĪ cooling system for a turbine engine for directing cooling fluids from a compressor to a turbine blade cooling fluid supply and from an ambient air source to the turbine blade cooling fluid supply to supply cooling fluids to one or more airfoils of a rotor assembly is disclosed. 33.66 Section 33.66 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT AIRWORTHINESS STANDARDS: AIRCRAFT ENGINES Design and Construction Turbine Aircraft Engines § 33.66 Bleed air system. 14 Aeronautics and Space 1 false Bleed air system. The engine must supply bleed air without adverse effect on the engine, excluding reduced thrust or power. Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT AIRWORTHINESS STANDARDS: AIRCRAFT ENGINES Design and Construction Turbine Aircraft Engines § 33.66 Bleed air system. STANDARDS: AIRCRAFT ENGINES Design and Construction Turbine Aircraft Engines § 33.66 Bleed air system. For turbine engine bleed air systems, the. Induction System § 23.1111 Turbine engine bleed air system. 23.1111 Section 23.1111 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION.
14 Aeronautics and Space 1 false Turbine engine bleed air system.
Flight test verified the predicted fuel saving of 0.8 percent.ġ4 CFR 23.1111 - Turbine engine bleed air system. The cabin remained comfortable with reductions in cabin fresh air ( engine bleed air) as much as 50 percent. The recirculation system was evaluated in revenue service on a DC-10. An 0.8 percent fuel savings was achieved by a reduction in engine bleed air through the use of cabin air recirculation.
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