Hydraulic fluid heat dissipation control assembly and method

A hydraulic fluid heat dissipation control assembly for an aircraft hydraulic system, the hydraulic fluid heat dissipation control assembly comprising:

• two or more heat exchangers with at least two of the two or more heat exchangers positioned in parallel to each other;
• at least one fluid flow line coupled to the two or more heat exchangers;
• a filter coupled to the at least one fluid flow line;
• and,
• a pressure control valve positioned in line with one of the two or more heat exchangers, the pressure control valve configured to sense a pressure differential across the filter and the one of the two or more heat exchangers to control flow of a hydraulic fluid through the two or more heat exchangers, so as to control heat dissipation from the aircraft hydraulic system.

An aircraft having an aircraft hydraulic system with a hydraulic fluid heat dissipation control assembly, the aircraft comprising:

• a fuselage;
• a pair of wings operatively coupled to the fuselage;
• one or more aircraft hydraulic systems disposed within at least one of the fuselage and the pair of wings, each aircraft hydraulic system comprising:
• a hydraulic fluid heat dissipation control assembly comprising:
• at least one fluid flow line;
• a filter coupled to the at least one fluid flow line;
• one or more pump devices coupled to the at least one fluid flow line;
• two heat exchangers positioned in parallel to each other and coupled to the at least one fluid flow line;
• and,
• a pressure control valve positioned in line with one of the two heat exchangers, the pressure control valve configured to sense a pressure differential across the filter and the two heat exchangers to control flow of a hydraulic fluid from the one or more pump devices through the at least one fluid flow line and through the two heat exchangers in order to control heat dissipation from the aircraft hydraulic system and to obtain a heat dissipation controlled hydraulic fluid, which then flows to a return flow line or to a hydraulic fluid reservoir both located in the aircraft hydraulic system.

An aircraft having an aircraft hydraulic system with a hydraulic fluid heat dissipation control assembly, the aircraft comprising:

• a fuselage;
• a pair of wings operatively coupled to the fuselage;
• one or more aircraft hydraulic systems disposed within at least one of the fuselage and the pair of wings, each aircraft hydraulic system comprising:
• a hydraulic fluid heat dissipation control assembly comprising:
• at least one fluid flow line;
• a filter coupled to the at least one fluid flow line;
• one or more pump devices coupled to the at least one fluid flow line;
• two or more heat exchangers with at least two of the two more heat exchangers positioned in parallel to each other, and coupled to the at least one fluid flow line;
• and,
• a pressure control valve positioned in line with one of the two heat exchangers, the pressure control valve configured to sense a pressure differential across the filter and the one of the two or more heat exchangers to control flow of a hydraulic fluid from the one or more pump devices through the at least one fluid flow line and through the two or more heat exchangers in order to control heat dissipation from the aircraft hydraulic system and to obtain a heat dissipation controlled hydraulic fluid, which then flows to a return flow line or to a hydraulic fluid reservoir both located in the aircraft hydraulic system.

A method of controlling heat dissipation of a hydraulic fluid in an aircraft hydraulic system, the method comprising:

• installing a hydraulic fluid heat dissipation control assembly in an aircraft hydraulic system, the hydraulic fluid heat dissipation control assembly comprising:
• at least one fluid flow line;
• a filter coupled to the at least one fluid flow line;
• one or more pump devices coupled to the at least one fluid flow line;
• two heat exchangers positioned in parallel to each other and coupled to the at least one fluid flow line;
• and,
• a pressure control valve positioned in line with one of the two heat exchangers;
• sensing with the pressure control valve a pressure differential across the filter and the two heat exchangers;
• controlling with the pressure control valve, the flow of the hydraulic fluid through the two heat exchangers, so as to vary heat dissipation from the aircraft hydraulic system and so as to obtain a heat dissipation controlled hydraulic fluid;
• and,
• flowing the heat dissipation controlled hydraulic fluid to one of at least a return flow line or to a hydraulic fluid reservoir both in the aircraft hydraulic system.

A hydraulic fluid heat dissipation control assembly for an aircraft hydraulic system, the hydraulic fluid heat dissipation control assembly comprising:

• two heat exchangers;
• a fluid flow line coupled to one of the two heat exchangers;
• a filter coupled to the fluid flow line:
• one or more pumps devices coupled to the fluid flow line;
• and,
• a pressure control valve positioned in a bypass path;
• the pressure control valve configured to sense a pressure differential across the filter and the one of the two heat exchangers, to selectively bypass the other of the two heat exchangers, so as to control heat dissipation from the aircraft hydraulic system.

An aircraft having an aircraft hydraulic system with a hydraulic fluid heat dissipation control assembly, the aircraft comprising

• a fuselage:
• a pair of wings operatively coupled to the fuselage:
• one or more aircraft hydraulic systems disposed within at least one of the fuselage and the pair of wings, each aircraft hydraulic system comprising:
• a hydraulic fluid heat dissipation control assembly comprising:
• a fluid flow line;
• a filter coupled to the fluid flow line:
• one or more pumps devices coupled to the fluid flow line;
• two heat exchangers, with one of the two heat exchangers coupled to the fluid flow line;
• and,
• a pressure control valve positioned in a bypass path;
• the pressure control valve configured to sense a pressure differential across the filter and the one of the two heat exchangers, to selectively bypass the other of the two heat exchangers, in order to control heat dissipation from the aircraft hydraulic system and to obtain a heat dissipation controlled hydraulic fluid, which then flows to a return flow line or to a hydraulic fluid reservoir, both located in the aircraft hydraulic system.

A method of controlling heat dissipation of a hydraulic fluid in an aircraft hydraulic system, the method comprising:

• installing a hydraulic fluid heat dissipation control assembly in an aircraft hydraulic system, the hydraulic fluid heat dissipation control assembly comprising:
• a fluid flow line;
• a filter coupled to the fluid flow line:
• one or more pump devices coupled to the fluid flow line;
• two heat exchangers, with one of the two heat exchangers coupled to the fluid flow line;
• and,
• a pressure control valve positioned in a bypass line;
• sensing with the pressure control valve a pressure differential across the filter and the one of the two heat exchangers, to selectively bypass the other of the two heat exchangers, so as to control heat dissipation from the aircraft hydraulic system and so as to obtain a heat dissipation controlled hydraulic fluid;
• and,
• flowing the heat dissipation controlled hydraulic fluid to one of at least a return flow line or to a hydraulic fluid reservoir, both in the aircraft hydraulic system.