Patent Application
20230080053
Exemplary embodiments pertain to the art of aircraft and, more particularly, to a cryogenic fluid heat exchange system for an aircraft environmental control system (ECS).
Aircraft include environmental control systems (ECS) that are operated to condition and pressurize cabin air. In many cases, the aircraft includes a RAM air system that forms part of an air-conditioning pack. The air-conditioning pack conditions and introduces ambient air into an ECS. In the ECS, the ambient air is pressurized and then cooled before being introduced into passenger spaces. In addition to cooling cabin air, other systems are employed to capture water or condensation from the cooling system for use in still other aircraft systems.
Disclosed is an environmental control system (ECS) for an aircraft including a primary heat exchanger, a compressor including an inlet fluidically connected to the primary heat exchanger, a turbine operatively connected to the compressor, and a cryogenic fluid heat exchanger fluidically connected to the primary heat exchanger.
Additionally, or alternatively, in this or other non-limiting examples, a water separator fluidically connected between the cryogenic fluid heat exchanger and the turbine.
Additionally, or alternatively, in this or other non-limiting examples, the cryogenic fluid heat exchanger is connected between an outlet of the compressor and the turbine.
Additionally, or alternatively, in this or other non-limiting examples, a secondary heat exchanger arranged adjacent the primary heat exchanger, the secondary heat exchanger including an inlet portion fluidically connected to the outlet of the compressor, and an outlet portion fluidically connected to the cryogenic fluid heat exchanger.
Additionally, or alternatively, in this or other non-limiting examples, a condensing heat exchanger fluidically connected between the cryogenic fluid heat exchanger and the water separator.
Additionally, or alternatively, in this or other non-limiting examples, another turbine mechanically connected to the turbine, the another turbine having an inlet portion fluidically connected to the condensing heat exchanger and an outlet portion.
Additionally, or alternatively, in this or other non-limiting examples, a source of cryogenic fluid operatively connected to the secondary heat exchanger.
Additionally, or alternatively, in this or other non-limiting examples, a RAM air system operatively connected to the primary heat exchanger and the secondary heat exchanger.
Additionally, or alternatively, in this or other non-limiting examples, the cryogenic fluid heat exchanger is fluidically connected to an inlet of the primary heat exchanger.
Additionally, or alternatively, in this or other non-limiting examples, a source of cryogenic fluid is fluidically connected to the cryogenic fluid heat exchanger, and a fuel cell is operatively connected to the source of cryogenic fluid.
Also disclosed is an aircraft including a fuselage having a tail and a cabin. A first wing is supported by the fuselage. A second wing is supported by the fuselage. A stabilizer is arranged at the tail. An environmental control system (ECS) is mounted in the fuselage. The ECS includes a primary heat exchanger, a compressor including an inlet fluidically connected to the primary heat exchanger, a turbine operatively connected to the compressor. A cryogenic fluid heat exchanger is fluidically connected to the primary heat exchanger.
Additionally, or alternatively, in this or other non-limiting examples, a water separator fluidically connected between the cryogenic fluid heat exchanger and the turbine.
Additionally, or alternatively, in this or other non-limiting examples, the cryogenic fluid heat exchanger is connected between an outlet of the compressor and the turbine.
Additionally, or alternatively, in this or other non-limiting examples, a secondary heat exchanger arranged adjacent the primary heat exchanger, the secondary heat exchanger including an inlet portion fluidically connected to the outlet of the compressor, and an outlet portion fluidically connected to the cryogenic fluid heat exchanger.
Additionally, or alternatively, in this or other non-limiting examples, a condensing heat exchanger fluidically connected between the cryogenic fluid heat exchanger and the water separator.
Additionally, or alternatively, in this or other non-limiting examples, another turbine mechanically connected to the turbine, the another turbine having an inlet portion fluidically connected to the condensing heat exchanger and an outlet portion.
Additionally, or alternatively, in this or other non-limiting examples, a source of cryogenic fluid operatively connected to the secondary heat exchanger.
Additionally, or alternatively, in this or other non-limiting examples, a RAM air system operatively connected to the primary heat exchanger and the secondary heat exchanger.
Additionally, or alternatively, in this or other non-limiting examples, the cryogenic fluid heat exchanger is fluidically connected to an inlet of the primary heat exchanger.
Additionally, or alternatively, in this or other non-limiting examples, a source of cryogenic fluid is fluidically connected to the cryogenic fluid heat exchanger, and a fuel cell is operatively connected to the source of cryogenic fluid.
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
Reference will now follow to
In a non-limiting example, ECS 30 includes a cryogenic fluid heat exchanger 65 connected to outlet 45 of compressor 42. Cryogenic fluid heat exchanger 65 is also connected to a source of cryogenic fluid 67. In a non-limiting example, source of cryogenic fluid 67 takes the form of a tank 68 of liquid hydrogen. Source of cryogenic fluid 67 may also be connected to a fuel cell 70 and/or consumed in an engine in aircraft 10. A water separator 74 may be connected between cryogenic fluid heat exchanger 65 and turbine 50. With this arrangement, in addition to providing fuel to fuel cell 70, cryogenic fluid passing through cryogenic fluid heat exchanger 65 may also condition air passing from compressor 42 into turbine 50 in order to achieve a desired cooling in cabin 16. Cryogenic fluid heat exchanger 65 reduces component number and weight as compared to a conventional air-cycle air conditioning system.
Referring to
At this point, it should be understood that the non-limiting examples described herein disclose an environmental control system that employs cryogenic fluid to condition air passing to a cabin in an aircraft. The cryogenic fluid is sourced from a fuel cell supply and routed through the ECS to condition air passing through a RAM air system. The cryogenic fluid may be used to cool air passing into the RAM air system or to condition air passing from a compressor to a turbine. Combining fuel supply with the ECS reduces components that take up space in the aircraft, add weight, and require maintenance.
An intermediate secondary non-flammable or inert fluid loop (not shown) may be employed to remove heat from ECS air, (RAM air or compressed air, e.g., from engine bleed or an air compressor driven by a motor into the cryogenic liquid. This secondary fluid system, that employs cryogenic liquid as a heat sink, may be deployed in various heat exchanger embodiments discussed herein.
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.
