Heat Exchanger Mounting Assembly

Abstract

A mounting assembly for a heat exchanger for a gas turbine engine. The heat exchanger assembly includes a plurality of arcuate manifolds each supporting an array of fins extending from a radial inner surface. A plurality of circumferentially extending spaced weld tabs is integrally formed on the radial outer surface. A bracket assembly is utilized to attach the heat exchanger to a structural member of a gas turbine engine assembly, e.g., a fan case, in such a manner as to maximize the surface area available for fin placement, and to not interfere with the cooling circuits within the manifold. The mounting system provides adequate stiffness for high cycle fatigue loads (i.e., vibrations) and allows relative slippage between the heat exchanger and the fan case to accommodate thermal expansion and contraction to address low cycle fatigue loads.

Description

CROSS REFERENCE TO RELATED APPLICATIONS[0001]This Application claims priority and benefit of U.S. Provisional Patent Application Ser. No. 61 / 289,334 filed Dec. 22, 2009, the disclosure of which is incorporated herein by reference in its entirety.BACKGROUND OF THE INVENTION[0002]The field of this disclosure relates generally to a mounting assembly for mounting a heat exchanger in a gas turbine engine assembly, and more particularly to a mounting assembly including a slip joint to allow relative movement between a heat exchanger and a structural body of the gas turbine engine.[0003]Many known gas turbine engines have engine subsystems that should be cooled to facilitate improving the life span and / or reliability of the engine. To facilitate cooling the engine subsystems, at least some known gas turbine engine assemblies include radiators that are exposed to air flowing through the engine assembly to facilitate cooling a working fluid (e.g., an oil and / or a fuel) flowing through the ra...

AI Technical Summary

Benefits of technology

[0005]Exemplary embodiments disclosed herein provide a mounting system for a heat exchanger that provides sufficient stiffness for vibrational high cycle fatigue mediation while relieving low cycle fatigue stress caused by thermal expansion.

Problems solved by technology

However, many gas turbine engine radiators have been known to obstruct airflow through the engine assembly, causing turbulence and / or pressure drops within the engine assembly, which could adversely affect engine performance.

Additionally, interruption of the radiator with joint assemblies reduces the area available for cooling.

Moreover, at least some known gas turbine engine radiators are susceptible to high cycle fatigue (e.g., fatigue resulting from vibrations caused by rotor imbalance) and / or low cycle fatigue (e.g., fatigue resulting from thermal growth of the radiator caused by a temperature differential between the radiator and the supporting structure).

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