An aircraft comprising a heat exchanging pack comprising an energy recovering module with a hot and a cold side, the hot side thermally contacting the cold side, providing a heat exchange. The heat exchanging pack also comprises a secondary heat exchanger and a compressor coupled with a turbine. The
An aircraft comprising a heat exchanging pack comprising an energy recovering module with a hot and a cold side, the hot side thermally contacting the cold side, providing a heat exchange. The heat exchanging pack also comprises a secondary heat exchanger and a compressor coupled with a turbine. The hot side module inlet fluidly communicates with the bleed air duct, the cold side module inlet fluidly communicates with the ram air duct, the hot side module outlet fluidly communicates with the compressor inlet, the compressor outlet fluidly communicates with the hot side secondary inlet, the hot side secondary outlet fluidly communicates with the turbine inlet, and the cold side secondary inlet fluidly communicates with the ram air duct. The energy recovering module comprises a conversion apparatus, configured to generate energy out from the heat exchange taking place in the energy recovering module between the hot and cold sides.
대표청구항▼
1. An aircraft comprising: an engine with a bleed air port configured to let air from the engine flow into a bleed air duct,a ram air inlet flap, configured to let air from the outside of the aircraft flow into a ram air duct,a heat exchanging pack comprising: an energy recovering module with a hot
1. An aircraft comprising: an engine with a bleed air port configured to let air from the engine flow into a bleed air duct,a ram air inlet flap, configured to let air from the outside of the aircraft flow into a ram air duct,a heat exchanging pack comprising: an energy recovering module with a hot side comprising a hot side inlet and a hot side outlet, and a cold side comprising a cold side inlet and a cold side outlet, the hot side being in thermal contact with the cold side via a conversion apparatus, thus causing a heat exchange,a secondary heat exchanger with a hot side inlet, a hot side outlet, a cold side inlet and a cold side outlet, anda compressor coupled with a turbine, the compressor and turbine having an inlet and an outlet,such that the hot side inlet of the energy recovering module is in fluid communication with the bleed air duct,the cold side inlet of the energy recovering module is in fluid communication with the ram air duct,the hot side outlet of the energy recovering module is in fluid communication with the compressor inlet,the compressor outlet is in fluid communication with the hot side inlet of the secondary heat exchanger,the hot side outlet of the secondary heat exchanger is in fluid communication with the turbine inlet,the cold side inlet of the secondary heat exchanger is in fluid communication with the ram air duct,wherein the conversion apparatus is configured to generate electrical energy out from the heat exchange that takes place in the energy recovering module between the hot side and the cold side, and wherein the conversion apparatus comprises:at least four piston assemblies, each one having a cold side and a hot side,at least four regenerators, each one having a cold side and a hot side,wherein the piston assemblies and the regenerators are arranged in a closed circuit containing a work fluid that runs inside the piston assemblies and inside the regenerators, such that each regenerator is in fluid connection with two piston assemblies, the preceding one and the subsequent one, and each piston assembly is in fluid connection with two regenerators, the preceding one and the subsequent one,wherein between each piston assembly and the subsequent regenerator there is a heat exchanger from a first plurality of heat exchangers, the heat exchangers from the first plurality of heat exchangers different from the at least four regenerators, and configured to exchange heat between the work fluid and the bleed air from the hot side of the energy recovering module, andwherein between each regenerator and the subsequent piston assembly there is also a heat exchanger from a second plurality of heat exchangers, the heat exchangers from the second plurality of heat exchangers different from the at least four regenerators and different from the heat exchangers from the first plurality of heat exchangers, and the heat exchangers from the second plurality of heat exchangers configured to exchange heat between the work fluid and the air from the ram air duct of the cold side of the energy recovering module. 2. The aircraft according to claim 1, wherein the conversion apparatus further comprises an electrical generator configured to transform work by the at least four piston assemblies into electrical energy. 3. The aircraft according to claim 1, wherein the secondary heat exchanger also comprises a bypass valve placed in a secondary channel, which secondary channel is suitable for bypassing the compressor and turbine by creating a fluid contact between the inlet of the compressor and the outlet of the turbine. 4. The aircraft according to claim 1, wherein the working fluid comprises a gas. 5. The aircraft according to claim 1, wherein the working fluid comprises helium.
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이 특허에 인용된 특허 (2)
Masanao Ando JP; Osamu Satoh JP; Shoji Uryu JP; Koichi Ohara JP, Air cycle machine and air conditioning system using the same.
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