CN112429244B - Heat comprehensive utilization system - Google Patents
Heat comprehensive utilization system Download PDFInfo
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- CN112429244B CN112429244B CN202011210602.1A CN202011210602A CN112429244B CN 112429244 B CN112429244 B CN 112429244B CN 202011210602 A CN202011210602 A CN 202011210602A CN 112429244 B CN112429244 B CN 112429244B
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D13/08—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned the air being heated or cooled
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/0614—Environmental Control Systems with subsystems for cooling avionics
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/0659—Environmental Control Systems comprising provisions for cooling fuel systems
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/50—On board measures aiming to increase energy efficiency
Abstract
The application belongs to the technical field of heat utilization design of aircraft cabins and airborne equipment, and particularly relates to a heat comprehensive utilization system, which comprises the following components: a compressor; the hot edge inlet of the heat regenerator is communicated with the outlet of the air compressor; the hot side inlet of the condenser is communicated with the hot side outlet of the heat regenerator; the gas phase inlet of the dehydrator is communicated with the hot side outlet of the condenser, and the gas phase outlet of the dehydrator is communicated with the cold side inlet of the heat regenerator; the turbine cooler is coaxial with the compressor, and the inlet of the turbine cooler is communicated with the cold edge outlet of the heat regenerator; the outlet of the condenser is communicated with the cold side inlet of the condenser; the gas-liquid cooler is characterized in that a gas phase inlet of the gas-liquid cooler is communicated with a cold side outlet of the condenser; the air inlet of the cabin is communicated with the gas phase outlet of the gas-liquid cooler; and the cold edge inlet of the medium cooler is communicated with the liquid phase outlet of the gas-liquid cooler, and the cold edge outlet of the medium cooler is communicated with the liquid phase inlet of the gas-liquid cooler.
Description
Technical Field
The application belongs to the technical field of heat utilization design of aircraft cabins and airborne equipment, and particularly relates to a heat comprehensive utilization system.
Background
At present, control corresponding to the temperature of an aircraft cabin is realized by mixing cold air and hot air from an aircraft engine, larger power of the aircraft engine is required to be occupied, and in addition, a large amount of high-heat-flux airborne equipment exists on the aircraft.
The present application has been made in view of the above-described technical drawbacks.
It should be noted that the above disclosure of the background art is only for aiding in understanding the inventive concept and technical solution of the present application, which is not necessarily prior art to the present patent application, and should not be used for evaluating the novelty and creativity of the present application in the case where no clear evidence indicates that the above content has been disclosed at the filing date of the present application.
Disclosure of Invention
It is an object of the present application to provide a heat integrated utilization system that overcomes or mitigates at least one of the technical drawbacks of the known art.
The technical scheme of the application is as follows:
a heat integrated utilization system, comprising:
a compressor;
the hot edge inlet of the heat regenerator is communicated with the outlet of the air compressor;
the hot side inlet of the condenser is communicated with the hot side outlet of the heat regenerator;
the gas phase inlet of the dehydrator is communicated with the hot side outlet of the condenser, and the gas phase outlet of the dehydrator is communicated with the cold side inlet of the heat regenerator;
the turbine cooler is coaxial with the compressor, and the inlet of the turbine cooler is communicated with the cold edge outlet of the heat regenerator; the outlet of the condenser is communicated with the cold side inlet of the condenser;
the gas-liquid cooler is characterized in that a gas phase inlet of the gas-liquid cooler is communicated with a cold side outlet of the condenser;
the air inlet of the cabin is communicated with the gas phase outlet of the gas-liquid cooler;
and the hot side inlet of the medium cooler is communicated with the liquid phase outlet of the gas-liquid cooler, and the hot side outlet of the medium cooler is communicated with the liquid phase inlet of the gas-liquid cooler.
According to at least one embodiment of the present application, the above-mentioned heat integrated utilization system further includes:
and the inlet of the air-cooled radiator is communicated with the air outlet of the cabin.
According to at least one embodiment of the present application, the above-mentioned heat integrated utilization system further includes:
and the inlet of the three-way valve is communicated with the cold edge outlet of the condenser, one outlet of the three-way valve is communicated with the gas phase inlet of the gas-liquid cooler, and the other outlet of the three-way valve is communicated with the gas inlet of the cabin.
According to at least one embodiment of the present application, the above-mentioned heat integrated utilization system further includes:
the temperature sensor is arranged in the cabin and used for measuring the temperature in the cabin and generating a corresponding temperature signal;
and the controller is electrically connected with the three-way valve and the temperature sensor so as to be capable of adjusting the opening degrees of two outlets of the three-way valve according to temperature signals and controlling the temperature in the cabin to be at a temperature set value.
According to at least one embodiment of the present application, in the above heat comprehensive utilization system, the controller adjusts the opening degrees of two outlets of the three-way valve according to the temperature signal, and controls the temperature in the cabin to be at a temperature set value, specifically:
if the temperature value corresponding to the temperature signal is smaller than the temperature set value, the controller controls the opening degree of the communication outlet of the three-way valve and the gas phase inlet of the gas-liquid cooler to be increased, and/or controls the opening degree of the communication outlet of the three-way valve and the gas phase inlet of the cabin to be reduced;
if the temperature value corresponding to the temperature signal is larger than the temperature set value, the controller controls the opening degree of the communication outlet of the three-way valve and the gas phase inlet of the gas-liquid cooler to be reduced, and/or controls the opening degree of the communication outlet of the three-way valve and the gas phase inlet of the cabin to be increased.
According to at least one embodiment of the present application, the above-mentioned heat integrated utilization system further includes:
the hot side inlet of the gas-gas cooler is communicated with the outlet of the gas compressor, and the hot side outlet of the gas-gas cooler is communicated with the hot side inlet of the heat regenerator.
According to at least one embodiment of the present application, the above-mentioned heat integrated utilization system further includes:
and the atomizing nozzle is communicated with the free water outlet of the dehydrator so as to atomize the free water flowing out of the free water outlet and spray the atomized free water to the cold edge inlet of the gas-gas cooler.
Drawings
FIG. 1 is a schematic diagram of a heat integrated utilization system provided by an embodiment of the present application;
wherein:
1-a compressor; 2-a heat regenerator; a 3-cooler; 4-a dehydrator; 5-a turbine cooler; 6-gas-liquid cooler; 7-cabin; 8-a media cooler; 9-an air-cooled radiator; 10-a three-way valve; 11-a temperature sensor; 12-a controller; 13-gas cooler; 14-atomizing nozzle.
For the purpose of better illustrating the embodiments, certain elements of the drawings may be omitted, enlarged or reduced and do not represent the actual product dimensions; further, the drawings are for illustrative purposes, wherein the terms describing the positional relationship are limited to the illustrative description only and are not to be construed as limiting the present patent.
Detailed Description
In order to make the technical solution of the present application and its advantages more clear, the technical solution of the present application will be further and completely described in detail with reference to the accompanying drawings, it being understood that the specific embodiments described herein are only some of the embodiments of the present application, which are for explanation of the present application and not for limitation of the present application. It should be noted that, for convenience of description, only the part related to the present application is shown in the drawings, and other related parts may refer to the general design, and the embodiments of the present application and the technical features of the embodiments may be combined with each other to obtain new embodiments without conflict.
Furthermore, unless defined otherwise, technical or scientific terms used in the description of the application should be given the ordinary meaning as understood by one of ordinary skill in the art to which the application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," "outer," and the like as used in the description of the present application are merely used for indicating relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and that the relative positional relationships may be changed when the absolute position of the object to be described is changed, thus not being construed as limiting the application. The terms "first," "second," "third," and the like, as used in the description of the present application, are used for descriptive purposes only and are not to be construed as indicating or implying any particular importance to the various components. The use of the terms "a," "an," or "the" and similar referents in the description of the application are not to be construed as limiting the amount absolutely, but rather as existence of at least one. As used in this description of the application, the terms "comprises," "comprising," or the like are intended to cover an element or article that appears before the term as such, but does not exclude other elements or articles from the list of elements or articles that appear after the term.
Furthermore, unless specifically stated and limited otherwise, the terms "mounted," "connected," and the like in the description of the present application are used in a broad sense, and for example, the connection may be a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can also be communicated with the inside of two elements, and the specific meaning of the two elements can be understood by a person skilled in the art according to specific situations.
The application is described in further detail below with reference to fig. 1.
A heat integrated utilization system, comprising:
a compressor 1;
the hot side inlet of the regenerator 2 is communicated with the outlet of the compressor 1;
the hot side inlet of the condenser 3 is communicated with the hot side outlet of the heat regenerator 2;
the gas phase inlet of the dehydrator 4 is communicated with the hot side outlet of the condenser 3, and the gas phase outlet of the dehydrator is communicated with the cold side inlet of the heat regenerator 2;
the turbine cooler 5 is coaxial with the compressor 1, and the inlet of the turbine cooler is communicated with the cold edge outlet of the heat regenerator 2; the outlet of the condenser is communicated with the cold side inlet of the condenser 3;
a gas-liquid cooler 6, the gas phase inlet of which is communicated with the cold side outlet of the condenser 3;
a cabin 7, the air inlet of which is communicated with the gas phase outlet of the gas-liquid cooler 6;
and the cold side inlet of the medium cooler 8 is communicated with the liquid phase outlet of the gas-liquid cooler 6, and the cold side outlet of the medium cooler is communicated with the liquid phase inlet of the gas-liquid cooler 6.
For the heat comprehensive utilization system disclosed in the above embodiment, it can be understood by those skilled in the art that the heat comprehensive utilization system can be applied to comprehensive heat utilization of an aircraft cabin and on-board equipment, and when the heat comprehensive utilization system is used for comprehensive heat utilization of the aircraft cabin and on-board equipment, the inlet of the air compressor 1 can be connected with bleed air from an aircraft engine, the bleed air temperature and the pressure are relatively low, the cabin 7 is the aircraft cabin, and the medium cooler 8 is the medium cooler of the on-board equipment, in particular to the medium cooler of the high heat flux on-board equipment.
As for the heat comprehensive utilization system disclosed in the above embodiment, it may be further understood by those skilled in the art that when the heat comprehensive utilization system is used for comprehensively utilizing the cabin of an aircraft and the on-board device, the inlet of the air compressor 1 may be connected to the bleed air from the engine of the aircraft, the bleed air may be heated and boosted, the free water removed from the water remover 4 after further cooling and condensation by the regenerator 2, the cooled side of the regenerator 2 may be heated, and then the cooled side of the turbine cooler 5 may be cooled and depressurized, the cooled side of the condenser 3 may be heated, and the cooled medium flows into the cabin 7 after exchanging heat with the cooling medium in the air-liquid cooler 6, adjusts the temperature in the cabin 7, and at the same time the cooling medium in the air-liquid cooler 6 may be cooled, flows into the medium cooler 8, and may be further cooled by the aircraft fuel in the medium cooler 8, that is, the cooled side inlet of the medium cooler 8 may be communicated with the aircraft fuel tank, the cooled side outlet may be communicated with the fuel inlet of the aircraft engine, the cooled side outlet may be cooled medium may be cooled by the heat dissipated in the on-board device, and the heat dissipated by the on-board device, and the heat may be recycled to the on-board device through the heat exchanger.
As for the heat comprehensive utilization system disclosed in the above embodiment, it can be further understood by those skilled in the art that when the heat comprehensive utilization system is used for comprehensive utilization of an aircraft cabin and an on-board device, the aircraft engine is not required to provide hot air to regulate the temperature in the cabin 7, only bleed air with lower temperature and pressure from the aircraft engine is required, the power of the aircraft engine is relatively small, in addition, the temperature of the bleed air from the aircraft engine is raised by using cooling medium circulated between the air-liquid cooler 6 and the medium cooler 8, namely, the temperature of the bleed air from the aircraft engine is raised by using heat emitted by the on-board device, the heat emitted by the on-board device is effectively utilized, and the cooling medium circulated between the air-liquid cooler 6 and the medium cooler 8 is cooled in the air-liquid cooler 6 first, and then the aircraft fuel is cooled further in the medium cooler 8, so that the temperature rise of the fuel can be correspondingly reduced, namely, the temperature of the fuel flowing out from the cold side outlet of the medium cooler 8 is correspondingly reduced, and the fuel inlet oil temperature of the aircraft is prevented from being too high.
For the heat comprehensive utilization system disclosed in the above embodiment, it can be further understood by those skilled in the art that when the heat comprehensive utilization system is used for comprehensively utilizing heat of an aircraft cabin and on-board equipment, the inlet of the compressor 1 is designed to be connected with bleed air from an aircraft engine, and the bleed air is heated and boosted, so that the system can work stably.
It will also be appreciated by those skilled in the art that the heat integrated utilization system disclosed in the above embodiment is designed to remove free water from the water trap 4 to avoid moisture in the gas entering the turbine cooler 5.
As for the heat comprehensive utilization system disclosed in the above embodiment, it can be further understood by those skilled in the art that the turbine cooler 5 is designed to be coaxial with the compressor 1, so that the compressor 1 can be driven to work by expanding output shaft work while cooling and compressing gas.
For the heat comprehensive utilization system disclosed in the above embodiment, those skilled in the art can also understand that the design of the heat comprehensive utilization system is that the compressor 1, the regenerator 2, the condenser 3, the dehydrator 4 and the turbine cooler 5 are matched, and the gas is cooled in a high-pressure circulation regenerative condensation dehydration mode, so that the heat comprehensive utilization system has better refrigeration capability.
In some alternative embodiments, the heat integrated utilization system described above further comprises:
and the inlet of the air-cooled radiator 9 is communicated with the air outlet of the cabin 7.
For the heat comprehensive utilization system disclosed in the above embodiment, it can be understood by those skilled in the art that when the heat comprehensive utilization system is used for comprehensively utilizing heat of an aircraft cabin and airborne equipment, the air-cooled radiator 9 is an air-cooled radiator arranged on the aircraft, especially an air-cooled radiator of low heat flux airborne equipment, and the air outlet of the cabin 7 is designed to be communicated with the inlet of the air-cooled radiator 9, so that the air exhausted from the cabin 7 can be utilized to cool the airborne equipment.
In some alternative embodiments, the heat integrated utilization system described above further comprises:
the inlet of the three-way valve 10 is communicated with the outlet of the cold side of the condenser 3, one outlet of the three-way valve is communicated with the gas phase inlet of the gas-liquid cooler 6, the other outlet of the three-way valve is communicated with the gas inlet of the cabin 7, namely, the gas flowing out of the outlet of the cold side of the condenser 3 directly flows into the cabin 7 through a part of the three-way valve 10, and flows into the cabin 7 after being partially heated by the gas-liquid cooler 6, and the proportion of the two parts of gas can be adjusted as required to control the proper temperature in the cabin 7.
In some alternative embodiments, the heat integrated utilization system described above further comprises:
a temperature sensor 11, which is arranged in the cabin 7 and is used for measuring the temperature in the cabin 7 and generating a corresponding temperature signal;
the controller 12 is electrically connected to the three-way valve 10 and the temperature sensor 11, and is configured to adjust the opening degrees of the two outlets of the three-way valve 10 according to the temperature signal, and to control the temperature in the cabin 7 to be at a temperature set value.
In some alternative embodiments, in the above-mentioned heat comprehensive utilization system, the controller 12 adjusts the opening degrees of the two outlets of the three-way valve 10 according to the temperature signal, so as to control the temperature in the cabin 7 to be at a temperature set value, specifically:
if the temperature value corresponding to the temperature signal is smaller than the temperature set value, the controller 12 controls the opening degree of the three-way valve 10 communicated with the gas phase inlet and the gas phase outlet of the gas-liquid cooler 6 to be increased, and/or controls the opening degree of the three-way valve 10 communicated with the gas phase inlet and the gas phase outlet of the cabin 7 to be reduced, so that the temperature in the cabin 7 gradually approaches the temperature set value;
if the temperature signal corresponds to a temperature value greater than the temperature set value, the controller 12 controls the opening degree of the three-way valve 10 communicated with the gas inlet of the gas-liquid cooler 6 to be reduced, and/or controls the opening degree of the three-way valve 10 communicated with the gas inlet of the cabin 7 to be increased, so that the temperature in the cabin 7 gradually approaches the temperature set value.
In some alternative embodiments, the heat integrated utilization system described above further comprises:
and the hot side inlet of the gas-gas cooler 13 is communicated with the outlet of the gas compressor 1, and the hot side outlet of the gas-gas cooler is communicated with the hot side inlet of the heat regenerator 2 so as to primarily cool the gas before the gas enters the heat regenerator 2.
In some alternative embodiments, the heat integrated utilization system described above further comprises:
the atomizing nozzle 14 is communicated with the free water outlet of the dehydrator 4, so as to atomize the free water flowing out of the free water outlet and spray the atomized free water to the cold side inlet of the air-air cooler 13.
As can be appreciated by those skilled in the art, the heat comprehensive utilization system disclosed in the above embodiment is designed such that the vaporization latent heat of the free water is very high, the atomizing nozzle 14 is connected to the free water outlet of the water remover 4, atomizes the free water flowing out from the free water outlet, sprays the atomized free water to the cold side inlet of the air-air cooler 13, mixes the atomized free water with cooling air to cool the air flowing through the air-air cooler 13, and utilizes the free water removed from the water remover 4, thereby having higher cooling efficiency.
In the description, each embodiment is described in a progressive manner, and each embodiment is mainly described by the differences from other embodiments, so that the same similar parts among the embodiments are mutually referred.
Having thus described the technical aspects of the present application with reference to the preferred embodiments shown in the drawings, it should be understood by those skilled in the art that the scope of the present application is not limited to the specific embodiments, and those skilled in the art may make equivalent changes or substitutions to the related technical features without departing from the principle of the present application, and those changes or substitutions will fall within the scope of the present application.
Claims (4)
1. A heat integrated utilization system, comprising:
a compressor (1);
the hot edge inlet of the heat regenerator (2) is communicated with the outlet of the compressor (1);
the hot side inlet of the condenser (3) is communicated with the hot side outlet of the heat regenerator (2);
the gas phase inlet of the dehydrator (4) is communicated with the hot side outlet of the condenser (3), and the gas phase outlet of the dehydrator is communicated with the cold side inlet of the heat regenerator (2);
a turbine cooler (5) coaxial with the compressor (1), and the inlet of the turbine cooler is communicated with the cold edge outlet of the heat regenerator (2); the outlet of the condenser is communicated with the cold side inlet of the condenser (3);
a gas-liquid cooler (6) with a gas phase inlet communicated with a cold side outlet of the condenser (3);
-a compartment (7) with an inlet communicating with the gas phase outlet of the gas-liquid cooler (6);
a medium cooler (8) with a hot side inlet communicated with the liquid phase outlet of the gas-liquid cooler (6) and a hot side outlet communicated with the liquid phase inlet of the gas-liquid cooler (6);
a three-way valve (10) with an inlet communicated with the cold-side outlet of the condenser (3), one outlet communicated with the gas-phase inlet of the gas-liquid cooler (6), and the other outlet communicated with the gas inlet of the cabin (7);
a temperature sensor (11) arranged in the cabin (7) and used for measuring the temperature in the cabin (7) and generating a corresponding temperature signal;
the controller (12) is electrically connected with the three-way valve (10) and the temperature sensor (11) so as to be capable of adjusting the opening degrees of two outlets of the three-way valve (10) according to the temperature signal and controlling the temperature in the cabin (7) to be at a temperature set value;
the controller (12) adjusts the opening degrees of two outlets of the three-way valve (10) according to the temperature signal, and controls the temperature in the cabin (7) to be at a temperature set value, specifically:
if the temperature value corresponding to the temperature signal is smaller than a temperature set value, the controller (12) controls the opening degree of the three-way valve (10) communicated with the gas phase inlet and the gas phase outlet of the gas-liquid cooler (6) to be increased, and/or controls the opening degree of the three-way valve (10) communicated with the gas phase inlet and the gas phase outlet of the cabin (7) to be reduced;
and if the temperature value corresponding to the temperature signal is larger than a temperature set value, the controller (12) controls the opening degree of the three-way valve (10) communicated with the gas phase inlet and the gas phase outlet of the gas-liquid cooler (6) to be reduced, and/or controls the opening degree of the three-way valve (10) communicated with the gas phase inlet and the gas phase outlet of the cabin (7) to be increased.
2. The heat integrated utilization system according to claim 1, wherein,
further comprises:
and the inlet of the air-cooled radiator (9) is communicated with the air outlet of the cabin (7).
3. The heat integrated utilization system according to claim 1, wherein,
further comprises:
and the hot side inlet of the gas-gas cooler (13) is communicated with the outlet of the gas compressor (1), and the hot side outlet of the gas-gas cooler is communicated with the hot side inlet of the heat regenerator (2).
4. The heat integrated utilization system according to claim 3, wherein,
further comprises:
and an atomization nozzle (14) which is communicated with the free water outlet of the dehydrator (4) so as to atomize the free water flowing out of the free water outlet and spray the atomized free water to the cold edge inlet of the gas-gas cooler (13).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011210602.1A CN112429244B (en) | 2020-11-03 | 2020-11-03 | Heat comprehensive utilization system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011210602.1A CN112429244B (en) | 2020-11-03 | 2020-11-03 | Heat comprehensive utilization system |
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| CN112429244A CN112429244A (en) | 2021-03-02 |
| CN112429244B true CN112429244B (en) | 2023-08-22 |
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| CN202011210602.1A Active CN112429244B (en) | 2020-11-03 | 2020-11-03 | Heat comprehensive utilization system |
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| CN106428572A (en) * | 2016-10-10 | 2017-02-22 | 中国商用飞机有限责任公司 | Ventilating and cooling system and cooling method for airplane air-conditioner assembly cabin |
| EP3187418A1 (en) * | 2015-12-30 | 2017-07-05 | Airbus Operations S.L. | Air conditioning system |
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| JP2018053856A (en) * | 2016-09-30 | 2018-04-05 | 株式会社神戸製鋼所 | Thermal energy recovery system |
| CN111017235A (en) * | 2019-12-25 | 2020-04-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Energy-optimized aircraft electromechanical system thermal management method |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6848261B2 (en) * | 2003-04-03 | 2005-02-01 | Honeywell International Inc. | Condensing cycle with energy recovery augmentation |
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2020
- 2020-11-03 CN CN202011210602.1A patent/CN112429244B/en active Active
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3187418A1 (en) * | 2015-12-30 | 2017-07-05 | Airbus Operations S.L. | Air conditioning system |
| JP2018053856A (en) * | 2016-09-30 | 2018-04-05 | 株式会社神戸製鋼所 | Thermal energy recovery system |
| CN106428572A (en) * | 2016-10-10 | 2017-02-22 | 中国商用飞机有限责任公司 | Ventilating and cooling system and cooling method for airplane air-conditioner assembly cabin |
| CN107521698A (en) * | 2017-07-28 | 2017-12-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of environmental control system heat refrigeration apparatus |
| CN111017235A (en) * | 2019-12-25 | 2020-04-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Energy-optimized aircraft electromechanical system thermal management method |
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| CN112429244A (en) | 2021-03-02 |
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