High reliability avionic cooling system

Refrigeration – With vehicle feature

Patent

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Details

454 76, 62DIG5, 622592, B60H 306

Patent

active

052534847

ABSTRACT:
A high reliability cooling system for avionics provides a low-weight tertiary backup. A first source of cooling airflow (20) is directed through a first duct (28) to a first compartment (30, 32). A second source of cooling airflow (58) is directed through a second duct (68) to a second compartment (70, 74, 76, 78). A check valve (104) is located in the first duct (28) and permits airflow from said first source (20) to said first compartment (30, 32) and prevents a back-flow of air therethrough. An interconnecting duct (84) is provided between the first and second ducts (28, 68). The interconnecting duct (84) connects to the first duct (28) at a location between the check valve (104) and the first compartment (30). A shutoff valve (86) is located in the interconnecting duct (84) and is operable to open or close airflow therethrough. The invention provides three modes of operation. First, with the shutoff valve (86) closed, there are two separated avionic cooling systems. Second, in the event of failure of the second source cooling airflow (58), the shutoff valve (86) can be opened to allow the first source (20) to provide cooling airflow to all avionics. Third, in the event of failure of the first source of cooling airflow (20), the shutoff valve (86) can be opened and the second source (58) can supply cooling airflow to all critical avionics. The check valve (104) segregates airflow in this mode between critical and non-critical avionics.

REFERENCES:
patent: 2336671 (1943-12-01), Chambers
patent: 2963879 (1960-12-01), de Paravicini
patent: 2966047 (1960-12-01), de Paravicini
patent: 3711044 (1973-01-01), Matulich
patent: 4484449 (1984-11-01), Muench
patent: 4653532 (1987-03-01), Powers
patent: 4741255 (1988-05-01), Lancaster
patent: 4966005 (1990-10-01), Cowell et al.

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