A thermoelectric power generation system for a vehicle is provided. The system includes an air compressor that is configured to compress and discharge air and a vortex tube that is configured to receive the compressed air discharged from the air compressor and separate and discharge the compressed air into two groups of air having a temperature difference. In addition, a thermoelectric module is provided that includes a thermoelectric element having a channel formed at a first side thereof introduced with any one of the two groups of air and a channel formed at a second side thereof introduced with the other of the two groups of air to generate an electromotive force due to a temperature difference of the two groups of air.

A temperature control system in an aircraft passenger service unit is disclosed. In embodiments, the system includes a swirl chamber configured to receive an inlet air stream, and a vortex tube configured to receive the inlet air stream from the swirl chamber and separate the inlet air stream into a warmer air stream and a cooler air stream. In embodiments, the system further includes a nozzle configured to direct a temperature-controlled air stream into a passenger space of an aircraft; wherein the nozzle is configured to be selectably adjusted in order to selectively blend the warmer air stream and the cooler air stream in order to generate the temperature-controlled air stream.

A temperature control system in an aircraft passenger service unit is disclosed. In embodiments, the system includes a swirl chamber configured to receive an inlet air stream, and a vortex tube configured to receive the inlet air stream from the swirl chamber and separate the inlet air stream into a warmer air stream and a cooler air stream. In embodiments, the system further includes a nozzle configured to direct a temperature-controlled air stream into a passenger space of an aircraft; wherein the nozzle is configured to be selectably adjusted in order to selectively blend the warmer air stream and the cooler air stream in order to generate the temperature-controlled air stream.

A deicing apparatus for aircraft comprises a passive vortex tube adapted to be mounted at a location at or adjacent a component of an aircraft and adapted to heat the component. A deicing method is also disclosed.

A spot cooling device which separates injected compressed air into hot air and cold air to discharge the hot air and eject the cold air to a space or subject includes: a main body including: an injection port through which compressed air is injected; a cold air nozzle through which cold air separated from the injected compressed air is ejected; and a passage part connected to the cold air nozzle and the injection port; and a temperature control unit installed through the passage part so as to control an opening degree of the passage part according to temperature change.

A spot cooling device which separates injected compressed air into hot air and cold air to discharge the hot air and eject the cold air to a space or subject includes: a main body including: an injection port through which compressed air is injected; a cold air nozzle through which cold air separated from the injected compressed air is ejected; and a passage part connected to the cold air nozzle and the injection port; and a temperature control unit installed through the passage part so as to control an opening degree of the passage part according to temperature change.

Systems, apparatuses, and methods are provided herein for providing temperature control. An apparatus for temperature control comprises a portable housing configured for delivery of items, an insulated storage compartment in the portable housing and configured to hold a plurality of items during a transport of the portable housing, a temperature control device configured to affect the temperature inside the insulated storage compartment, and a host coupler configured to couple with a host temperature control system to allow the host temperature control system to affect the temperature inside the insulated storage compartment. Wherein the temperature control device is configured to affect the temperature inside the insulated storage compartment without the host coupler being coupled to the host temperature control system.

Systems, apparatuses, and methods are provided herein for providing temperature control. An apparatus for temperature control comprises a portable housing configured for delivery of items, an insulated storage compartment in the portable housing and configured to hold a plurality of items during a transport of the portable housing, a temperature control device configured to affect the temperature inside the insulated storage compartment, and a host coupler configured to couple with a host temperature control system to allow the host temperature control system to affect the temperature inside the insulated storage compartment. Wherein the temperature control device is configured to affect the temperature inside the insulated storage compartment without the host coupler being coupled to the host temperature control system.

A deicing apparatus for aircraft comprises a passive vortex tube adapted to be mounted at a location at or adjacent a component of an aircraft and adapted to heat the component. A deicing method is also disclosed.

A medium conveying and heat exchange device and a vortex flow separator for an iron core of an electromagnetic device is provided. The vortex flow separator includes a jet pipe and a vortex flow separation pipe, the vortex flow separation pipe includes a vortex flow chamber, a cold end pipe section and a hot end pipe section. Compressed airflow flows through the jet pipe to form spiral airflow and flow into the vortex flow chamber in a tangential direction thereof. A valve having a cone-shaped surface is arranged inside the hot end pipe section, central airflow of the spiral airflow passes by the cone-shaped surface of the valve and flows back, and is cooled to become cold airflow, and then flows out from the cold end pipe section, to serve as cooling and drying airflow of the input electromagnetic device.