Patent Application
20230331390
Exemplary embodiments pertain to the art of aircraft and, more particularly, to a cabin air cooler system for an aircraft.
Most aircraft include control systems that control various environmental parameters in occupied and unoccupied aircraft spaces. For example, a cabin air cooling system (CAC) may be employed to direct a flow of conditioned air into aircraft spaces. CAC systems typically include a fan coupled to a rotor that is positioned within a stator. Electrically exciting the stator results in rotation of the rotor and, by extension, the fan. Typically, the stator operates at temperatures that warrant cooling. To cool the stator, air may be passed between the stator and the rotor or between the stator and a housing of the CAC. In some cases, a sleeve is positioned between the stator and the housing. The sleeve may pass a heat exchange medium in a thermal exchange relationship with the stator.
Disclosed in accordance with a non-limiting example is an aircraft system including a housing having an outer surface and an inner surface defining a cavity. A motor is arranged in the cavity. The motor includes a heat producing component mounted to the inner surface. A first cooling system is configured to direct a first heat exchange fluid in a first thermal exchange relationship with the heat producing component and a second cooling system is configured to direct a second heat exchange fluid in a second thermal exchange relationship with the heat producing component. The second heat exchange fluid is distinct from the first heat exchange fluid and the second thermal exchange relationship is distinct from the first thermal exchange relationship.
Additionally, or alternatively, in this or other non-limiting examples, the motor comprises an electric motor having a shaft, a rotor mounted to the shaft, and a stator defining the heat generating component disposed about the rotor.
Additionally, or alternatively, in this or other non-limiting examples, the first heat exchange fluid is a liquid and the second heat exchange fluid is a gas.
Additionally, or alternatively, in this or other non-limiting examples, the first cooling system includes a cooling jacket disposed between the outer surface and the inner surface, the cooling jacket extending about the housing.
Additionally, or alternatively, in this or other non-limiting examples, the stator includes a back iron mounted to the inner surface at the cooling jacket.
Additionally, or alternatively, in this or other non-limiting examples, the first heat exchange relationship is an indirect relationship with the back iron of the stator exchanging heat with the first heat exchange medium through the inner surface of the housing.
Additionally, or alternatively, in this or other non-limiting examples, a plurality of fins extend between the back iron and the inner surface of the housing, the plurality of fins transferring heat from the stator through the inner surface into the first heat exchange medium in the cooling jacket.
Additionally, or alternatively, in this or other non-limiting examples, the housing includes an inlet fluidically connected to the cooling jacket through the outer surface and an outlet fluidically connected to the cooling jacket through the outer surface, the inlet including a first quick connect and the outlet including a second quick connect.
Additionally, or alternatively, in this or other non-limiting examples, the second cooling system includes a flow path that extends along the shaft, the second heat exchange medium is air that passes along the flow path between the stator and the rotor.
Additionally, or alternatively, in this or other non-limiting examples, the second heat exchange relationship is a direct relationship with the air passing in direct contact with the stator.
Also disclosed, in accordance with a non-limiting example, is an aircraft including a fuselage having a passenger cabin, a wing mounted to the fuselage, an engine mounted to the wing and a cabin air mounted in the fuselage. The cabin air system including a compressor having a compressor housing having an inlet and an outlet and a cabin air cooling (CAC) system including a housing mounted to the compressor housing. The CAC housing having an outer surface and an inner surface defining a cavity that is fluidically connected to the compressor inlet. A motor is arranged in the cavity. The motor includes a heat producing component mounted to the inner surface. A first cooling system is configured to direct a first heat exchange fluid in a first thermal exchange relationship with the heat producing component and a second cooling system is configured to direct a second heat exchange fluid in a second thermal exchange relationship with the heat producing component. The second heat exchange fluid is distinct from the first heat exchange fluid and the second thermal exchange relationship is distinct from the first thermal exchange relationship.
Additionally, or alternatively, in this or other non-limiting examples, the motor comprises an electric motor having a shaft, a rotor mounted to the shaft, and a stator defining the heat generating component disposed about the rotor, the shaft being connected to the compressor.
Additionally, or alternatively, in this or other non-limiting examples, the first heat exchange fluid is a liquid and the second heat exchange fluid is a gas flowing through the compressor inlet.
Additionally, or alternatively, in this or other non-limiting examples, the first cooling system includes a cooling jacket disposed between the outer surface and the inner surface, the cooling jacket extending about the housing.
Additionally, or alternatively, in this or other non-limiting examples, the stator includes a back iron mounted to the inner surface at the cooling jacket.
Additionally, or alternatively, in this or other non-limiting examples, the first heat exchange relationship is an indirect relationship with the back iron of the stator exchanging heat with the first heat exchange medium through the inner surface of the housing.
Additionally, or alternatively, in this or other non-limiting examples, a plurality of fins extend between the back iron and the inner surface of the housing, the plurality of fins transferring heat from the stator through the inner surface into the first heat exchange medium in the cooling jacket.
Additionally, or alternatively, in this or other non-limiting examples, the housing includes an inlet fluidically connected to the cooling jacket through the outer surface and an outlet fluidically connected to the cooling jacket through the outer surface, the inlet including a first quick connect and the outlet including a second quick connect.
Additionally, or alternatively, in this or other non-limiting examples, the second cooling system includes a flow path that extends along the shaft and fluidically connected to the compressor inlet, the second heat exchange medium is air passing through the compressor inlet along the flow path between the stator and the rotor.
Additionally, or alternatively, in this or other non-limiting examples, the second heat exchange relationship is a direct relationship with the air passing in direct contact with the stator.
The following descriptions should not be considered limiting in any way. With reference to the accompanying drawings, like elements are numbered alike:
A detailed description of one or more embodiments of the disclosed apparatus and method are presented herein by way of exemplification and not limitation with reference to the Figures.
An aircraft in accordance with a non-limiting example is indicated generally at 10 in
In a non-limiting example, cabin air system 30 includes an air intake 34 at first engine 24, a cabin air cooling (CAC) system 36, and an air mixing unit 38. An air filter 40 filters air passing through an air circulation circuit 42. An exhaust 44 discharges air from air circulation circuit 42 adjacent to tail 18. A bleed air valve 46 provides an interface between first engine 24 and CAC system 36. Referring to
Referring to
In a non-limiting example, CAC system 36 includes a first cooling system 102 and a second cooling system 104 (
In a non-limiting example, first cooling system 102 includes a cooling jacket 106 integrated into in CAC housing 80. More specifically, cooling jacket 106 is defined between outer surface 83 and inner surface 85 and is designed to contain the first heat exchange medium. In a non-limiting example, the first heat exchange medium is a liquid. In a non-limiting example, the liquid comprises water. However, it should be understood that various fluids both liquids and non-liquids may be employed as the first heat exchange medium.
In a non-limiting example, cooling jacket 106 includes an inlet 110 and an outlet 112. Inlet 110 includes a first quick connect 114 and outlet 112 includes a second quick connect 116. First and second quick connects 114 and 116 project outwardly from outer surface 83 of CAC housing 80. In a non-limiting example, inlet 110 and outlet 112 are fluidically connected to a reservoir 118 that contains an amount of the first heat exchange medium. Reservoir 118 includes a reservoir inlet 120 fluidically coupled to outlet 112 and a reservoir outlet 121 fluidically coupled to inlet 110. Reservoir 118 includes a pump 123 that provides a motive force to the first heat exchange medium. More specifically, the first heat exchange fluid circulates through a closed loop system (not separately labeled) including a delivery conduit 125 that extends between reservoir outlet 121 and inlet 110, and a return conduit 128 that extends between outlet 112 and reservoir inlet 120. The first heat exchange medium circulates through cooling jacket 106 absorbing heat from heat producing component 93 through inner surface 85. In a non-limiting example, delivery conduit 125, return conduit 128 and reservoir 118 may form part of another system in aircraft 10.
In a non-limiting example, second cooling system 104 includes a coolant passage 135 (
Reference will now follow to
At this point, it should be understood that the non-limiting examples shown and described herein represent systems for increasing cooling efficiency of a heat producing component in an aircraft system. Multiple cooling systems relying on existing heat exchange mediums may be directed in indirect and direct contact with the heat producing component in order to reduce operating temperatures. Further, while the heat producing component is described as a motor stator, the cooling systems described herein may be employed in connection with a wide array of aircraft systems.
The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the present disclosure. As used herein, the singular forms “a”, “an” and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms “comprises” and/or “comprising,” when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, element components, and/or groups thereof.
While the present disclosure has been described with reference to an exemplary embodiment or embodiments, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the scope of the present disclosure. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the present disclosure without departing from the essential scope thereof. Therefore, it is intended that the present disclosure not be limited to the particular embodiment disclosed as the best mode contemplated for carrying out this present disclosure, but that the present disclosure will include all embodiments falling within the scope of the claims.
