Gas turbine outer case active ambient cooling including air exhaust into a sub-ambient region of exhaust flow

Abstract

A gas turbine engine including an outer case extending circumferentially around the central longitudinal axis. A cooling channel is associated with the outer surface of the outer case, the cooling channel having a channel inlet and a channel outlet. An air duct is provided including an inlet end in fluid communication with the channel outlet and an outlet end in fluid communication with an exhaust gas flow from a turbine section of the gas turbine engine. An exit structure is located at the air duct outlet end, and the exit structure provides a sub-ambient pressure at the air duct outlet end to induce a flow from the air duct inlet end to the air duct outlet end.

Description

CROSS-REFERENCE TO RELATED APPLICATIONS[0001]This application is a continuation-in-part of and claims priority to U.S. patent application Ser. No. 13 / 314,311, filed Dec. 8, 2011, which application is herein incorporated by reference in its entirety as if fully set forth herein.FIELD OF THE INVENTION[0002]The present invention relates to gas turbine engines and, more particularly, to structures for providing thermal protection to limit heating of the outer case of a gas turbine engine.BACKGROUND OF THE INVENTION[0003]A gas turbine engine generally includes a compressor section, a combustor section, a turbine section and an exhaust section. In operation, the compressor section may induct ambient air and compress it. The compressed air from the compressor section enters one or more combustors in the combustor section. The compressed air is mixed with the fuel in the combustors, and the air-fuel mixture can be burned in the combustors to form a hot working gas. The hot working gas is ro...

AI Technical Summary

Benefits of technology

The patent text describes a system that reduces the pressure at the end of an air duct and draws heated air from a cooling channel into the duct, creating a jet pump effect. This occurs through an exit shield that diverts exhaust gas away from the manifold and affects the reduced pressure at the outlet end of the duct. The technical effect of this system is improved cooling efficiency and pressure reduction for better performance.

Problems solved by technology

Advancements in gas turbine engine technology have resulted in increasing temperatures, and associated outer case deformation due to thermal expansion.

Case deformation may increase stresses in the case and in components supported on the case within the engine, such as bearing support struts.

The additional stress, which may operate in combination with low cycle fatigue, may contribute to cracks, fractures or failures of the bearing support struts that are mounted to the casing for supporting an exhaust end bearing housing.

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