DYNAMIC THERMAL LOAD MONITORING AND MITIGATION FOR AIRCRAFT SYSTEMS
A thermal management system (68) for a gas turbine engine (20) includes a cooler (70) including a first portion (72) and a second portion (74), the first portion (72) for cooling a hot flow (80) with a coolant (78) and the second portion (74) for cooling the coolant with a refrigerant (82). A vapor...
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Main Author | |
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Format | Patent |
Language | English French German |
Published |
28.10.2020
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Subjects | |
Online Access | Get full text |
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Summary: | A thermal management system (68) for a gas turbine engine (20) includes a cooler (70) including a first portion (72) and a second portion (74), the first portion (72) for cooling a hot flow (80) with a coolant (78) and the second portion (74) for cooling the coolant with a refrigerant (82). A vapor compression system (66) circulates the refrigerant (82) through the second portion of the cooler (70). The vapor compression system (66) is a closed system in communication with at least one heat load (76A-D) in addition to the second portion (74) of the cooler (70). |
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Bibliography: | Application Number: EP20200167931 |