Gas turbine engine heat exchangers and methods of assembling the same

Abstract

A heat exchanger assembly for use in a gas turbine engine includes a bypass valve and at least one body portion. The body portion includes at least one de-congealing inlet channel in flow communication with the bypass valve, a plurality of cooling channels in flow communication with the bypass valve and the at least one de-congealing inlet channel, and at least one de-congealing outlet channel in flow communication with the bypass valve and the at least one de-congealing inlet channel. The bypass valve is configured to deliver a fluid between the at least one de-congealing inlet channel and the plurality of cooling channels during a first mode of operation to facilitate reducing a temperature of the fluid. The bypass valve is further configured to deliver the fluid between the at least one de-congealing inlet channel and the at least one de-congealing outlet channel during a second mode of operation.

Description

CROSS-REFERENCE TO RELATED APPLICATIONS[0001]This application is a non-provisional application and claims priority to U.S. Provisional Patent Application Ser. No. 61 / 680,323 filed Aug. 7, 2012 for “METHODS AND ASSEMBLY FOR OPERATING GAS TURBINE HEAT EXCHANGERS”, which is hereby incorporated by reference in its entirety.BACKGROUND OF THE INVENTION[0002]The application described herein relates generally to gas turbine engines, and more specifically to methods and apparatus for operating gas turbine engines.[0003]Gas turbine engines typically include an inlet, a fan, low and high pressure compressors, a combustor, and at least one turbine. The compressors compress air which is channeled to the combustor where it is mixed with fuel. The mixture is then ignited for generating hot combustion gases. The combustion gases are channeled to the turbine(s) which extracts energy from the combustion gases for powering the compressor(s), as well as producing useful work to propel an aircraft in fl...

AI Technical Summary

Benefits of technology

This patent describes a heat exchanger assembly for a gas turbine engine. The assembly includes a bypass valve and at least one body portion with cooling channels and a de-congealing inlet and outlet channels. The bypass valve delivers fluid to the cooling channels during different modes of operation to reduce the temperature of the fluid. The gas turbine engine assembly includes the heat exchanger assembly within a fan casing. The technical effect of this patent is to provide a more efficient and effective heat exchanger assembly for gas turbine engines that helps to reduce the temperature of fluid during operation.

Problems solved by technology

During engine operation, significant heat is produced which raises the temperature of engine systems to unacceptable levels.

Furthermore, when the bypass valve is disengaged to allow flow of lubricating fluid through the exchanger, the low temperature of the exchanger causes the flow of fluid to congeal before the fluid can warm the exchanger to allow the fluid to flow.

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