Temperature Control Equipment for Inside Aircraft or Similar Object

Abstract

Temperature control equipment for inside aircraft or similar, comprises a closed-cycle cooling circuit, including compression means, a condensation/evaporation exchanger, an expansion valve and an evaporation/condensation exchanger, and further comprises an open-cycle air circuit arranged such that the air from the air circuit crosses through the condensation/evaporation exchanger. The air circuit incorporates an additional heat exchanger which, in heat pump mode operation, is positioned in the air flow path prior to the passage of the air through the condensation/evaporation exchanger, and, in turn, a pressurised and heated coolant flows through the additional heat exchanger from the closed-cycle cooling circuit.

Claims

1. Temperature control equipment for inside aircraft or similar, which comprises and is based on a closed-cycle cooling circuit through which a coolant fluid circulates, the circuit comprising compression means, a condensation/evaporation exchanger, an expansion valve and an evaporation/condensation exchanger, and which also comprises an open-cycle air circuit equipped with supply means and arranged such that the air from said air circuit crosses through the condensation/evaporation exchanger, wherein the air circuit incorporates an additional heat exchanger that, in the heat pump-type operations, is interposed in the path of the air and positioned prior to the passage of the air through the condensation/evaporation exchanger, and said additional heat exchanger in turn has coolant fluid flowing through it which exits pressurised and heated from the compression means.

2. The temperature control equipment for the inside of aircraft or similar according to claim 1, wherein the compression means comprise at least one inverter compressor.

3. The temperature control equipment for the inside of aircraft or similar according to claim 1, wherein the compression means comprise at least one on-off compressor.

4. The temperature control equipment for the inside of aircraft or similar according to claim 1, wherein the compression means comprise a plurality of inverter and/or on/off compressors arranged in series.

5. The temperature control equipment for the inside of aircraft or similar according to claim 1, wherein the air supply means comprise at least one centrifugal fan.

6. The temperature control equipment for the inside of aircraft or similar according to according to claim 1 installed in an air conditioning system for airport use.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0016] FIG. 1 is a schematic view of a preferred embodiment of the temperature control equipment for the inside of aircraft or similar of the present invention.

[0017] FIG. 2 is a schematic plan view of a specific arrangement for the use thereof of a preferred embodiment of the temperature control equipment for the inside of aircraft or similar of the invention.

[0018] FIG. 3 is a schematic perspective view of a specific arrangement for the use thereof of a preferred embodiment of the temperature control equipment for the inside of aircraft or similar of the invention shown in FIG. 2.

DESCRIPTION OF A PREFERRED EMBODIMENT

[0019] As shown schematically in FIG. 1, the temperature control equipment for the inside of aircraft or similar of the invention comprises and is based on a closed-cycle cooling circuit 1 through which a coolant fluid known in the state of the art circulates.

[0020] Said circuit 1 comprises compression means 11, a condensation/evaporation exchanger 12, an expansion valve 13 and an evaporation/condensation exchanger 14.

[0021] The coolant fluid of the closed-cycle cooling circuit 1 follows the path indicated by the arrows in said circuit 1.

[0022] The temperature control equipment for the inside of aircraft or similar of the invention further comprises an open-cycle air circuit 2, as indicated by the dotted rectangle in FIG. 1. Said air circuit 2 is equipped with supply means 21 to move the air and arranged such that the air from said air circuit 2 crosses through the condensation/evaporation exchanger 12 of the closed-cycle cooling circuit 1, as indicated by the arrows.

[0023] The air circuit 2 further incorporates an additional heat exchanger 22, which is interposed in the path of the air, and positioned prior to the passage of the air through the condensation/evaporation exchanger 12 of the closed-cycle cooling circuit 1, in the case of heat pump-type operations of said closed-cycle cooling circuit 1 and therefore, of the temperature control equipment for the inside of aircraft or similar of the invention.

[0024] Said additional heat exchanger 22 in turn has pressurised and heated coolant fluid flowing through it which works in the closed-cycle cooling circuit 1 and comes from the compression means 11.

[0025] The described arrangement of the temperature control equipment for the inside of aircraft or similar of the invention implies that the air that circulates through the air circuit 2 and is supplied by the supply means 21, passes through the heat exchanger 22 before passing through the condensation/evaporation exchanger 12 of the closed-cycle cooling circuit 1.

[0026] According to the thermodynamic operation of the circuit 1, the coolant fluid leaves the compression means 11 in a pressurised and heated gas phase. The heat exchanger 22, according to the arrangement described and indicated in FIG. 1, upon receiving the passage of said coolant fluid, thus transfers heat to the air that passes through it, as indicated by FIG. 1, which implies that said air is heated and that upon arriving at the condensation/evaporation exchanger 12 of the circuit 1 it raises the temperature thereof to thus adequately perform the condensation thereof.

[0027] In different preferred embodiments of the temperature control equipment for the inside of aircraft or similar of the invention, the compression means 11 can comprise one or more inverter and/or on-off compressors, also arranged in series according to the operational needs.

[0028] Also in different preferred embodiments, the air supply means 21 can comprise a centrifugal fan.

[0029] FIG. 2 show a schematic plan representation of the temperature control equipment for the inside of aircraft or similar of the invention, in a specific arrangement for the use thereof, wherein the compression means 11, the condensation/evaporation exchanger 12, the air supply means 21 and the additional heat exchanger 22 can be seen, as well as the position of the air inlet 23 and the air outlet 24 and open-cycle air circuit 2 can be seen.

[0030] FIG. 3 shows a schematic perspective view of a specific arrangement for the use thereof of the temperature control equipment for the inside of aircraft or similar of the invention shown in FIG. 2.

[0031] The temperature control equipment for the inside of aircraft or similar of the present invention provides great advantages which are very useful when the condensation/evaporation exchanger 12 is at an initial temperature lower than the temperature necessary for starting the condensation of the coolant fluid in gas phase.

[0032] In the current state of the art, when the initial temperature for the condensation is lower than the temperature necessary for the condensation, electrical batteries are used, thus preheating the air until the minimum condensation temperature is reached. Such a technical solution implies elevated energy consumption, in addition to being expensive.

[0033] The technical solution described in the temperature control equipment for the inside of aircraft or similar of the present invention is an eminently thermodynamic solution, and is therefore more advantageous than the use of electrical batteries in the current state of the art, further extending the temperature range of the use thereof.

[0034] A very useful application and use of temperature control equipment for the inside of aircraft or similar of the present invention is, for example, in airport installations, and specifically in equipment external to an aircraft in order to be able to supply air conditioning inside of it when said aircraft is already in the stopped position. Said equipment can be mounted in the boarding bridges or near them (islands), or also be mobile and mounted in trucks or trailers.

[0035] In such circumstances, it can be common that said external equipment is at a temperature lower than the limit for starting condensation. As mentioned above, in the current state of the art, in the heat pump-type operations, when the temperatures are lower than the condensation limit, batteries with electrical resistors are used to preheat the air and reach the minimum condensation temperature.

[0036] The temperature control equipment for the inside of aircraft or similar of the present invention thus implies a considerable advantage in the preheating of the exterior air that is necessary for supplying the air conditioning of an aircraft when stopped, since it substitutes the batteries with electrical resistors with a thermodynamic solution.

[0037] The details, shapes, dimensions and other accessory elements, as well as the materials used to manufacture the temperature control equipment for the inside of aircraft or similar of the invention, may be suitably substituted for others which are technically equivalent, and do not diverge from the essential nature of the invention, nor the scope defined by the claims included below.