CN202770042U - Whole sealing air circulation refrigerating system driven by power turbine - Google Patents
Whole sealing air circulation refrigerating system driven by power turbine Download PDFInfo
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- CN202770042U CN202770042U CN 201220352925 CN201220352925U CN202770042U CN 202770042 U CN202770042 U CN 202770042U CN 201220352925 CN201220352925 CN 201220352925 CN 201220352925 U CN201220352925 U CN 201220352925U CN 202770042 U CN202770042 U CN 202770042U
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Abstract
The utility model belongs to the field of plane environment control system construction and model design, and relates to a large-scale military and civilian use environment control system or an electronic equipment refrigerating system. A whole sealing air circulation refrigerating system driven by a power turbine comprises a pressure regulation turn-off valve 1, a speed regulation valve 2, a power turbine 3, a gas compressor 4, a heat exchanger 5, a cooling turbine 6, a water separator 7, a turn-off valve 8 and a bypass valve 9. The whole sealing air circulation refrigerating system driven by the power turbine is characterized in that the lower course of the pressure regulation turn-off valve 1 is connected with the speed regulation valve 2 and the turn-off valve 8. The power turbine 3, the gas compressor 4 and the cooling turbine 6 are installed coaxially. The heat exchanger 5 is arranged between the outlet of the gas compressor 4 and the inlet of the cooling turbine 6. The lower course of the cooling turbine 6 is connected with the water separator 7. The bypass valve 9 is arranged between the heat exchanger 5 and the water separator 7. The whole sealing air circulation refrigerating system driven by the power turbine can adapt to refrigeration needs of electronic equipment with different power requirements and cabins, thereby having generality.
Description
Affiliated technical field
The utility model belongs to plane environmental control system Configuration Design field, relates to the improvement of environmental control system or the electronic equipment refrigeration system of large-scale military-civil aircraft.
Background technology
The cooling assembly of most of aircrafts adopts the boost type air circulation refrigeration system, and this system passes into passenger cabin directly from engine bleed through primary heat exchanger, compressor, secondary heat exchanger, turbine and separator, discharges outside the machine at last.This System Assurance cabin pressurization increases expansion ratio of turbine, makes turbo driving steady, increases turbine service life.
This system is that open circulation needs larger engine bleed, has increased the compensatory loss of systematic function; Adopt primary heat exchanger as forecooler, lost the energy in most bleed; In addition, need ram-air as the air in the low-temperature receiver cooling heat exchanger, also have the compensatory loss of large systematic function.
The utility model content
The purpose of this utility model is: for the environmental control system of the large-scale military-civil aircraft that satisfies development, propose a kind of lightweight, little to the carrier aircraft performance impact, the totally-enclosed air circulation refrigeration system that the power turbine that the compensatory loss of energy is little drives.
The technical solution of the utility model is: system is comprised of Pressure Regulating Shutoff Valve 1, speed governing valve 2, power turbine 3, compressor 4, heat exchanger 5, cooling turbine 6, separator 7, shutoff valve 8 and bypass valve 9.Wherein connect speed governing valve 2 and turn-off valve 8 in the downstream of Pressure Regulating Shutoff Valve 1; Speed governing valve 2 downstreams connect power turbine 3, turn-off valve 8 downstreams and connect compressor 4, between compressor 4 outlets and cooling turbine 6 entrances, a heat exchanger 5 is installed, is connected a separator 7 in cooling turbine 6 downstreams, be provided with a bypass valve 9 between heat exchanger 5 and the separator 7.
The utility model has the advantages that: directly quote engine bleed drives coaxial work by power turbine compressor, take full advantage of the engine bleed energy, avoid relying on the carrier aircraft power supply, increase cooling turbine temperature drop and cooling system amount, increase the degree of admission of cooling turbine, reduce the cooling turbine size, and then reduce system weight; The totally enclosed type air circulation refrigeration system can reduce the engine bleed amount, cancels ram-air, thereby reduces the compensatory loss of energy of system.
Description of drawings
Fig. 1 is configuration schematic diagram of the present utility model;
Wherein, the 1st, Pressure Regulating Shutoff Valve, the 2nd, the speed governing valve, the 3rd, power turbine, the 4th, compressor, the 5th, heat exchanger, the 6th, cooling turbine, the 7th, separator, the 8th, turn-off valve, the 9th, bypass valve.
The specific embodiment
The below is described in further details the utility model.The technical problems to be solved in the utility model is: overcome existing system and rely on the carrier aircraft power supply, the problem such as compensatory resistance is large, and weight is large has designed the totally-enclosed air circulation refrigeration system that power turbine drives.
Referring to Fig. 1.The utility model system is comprised of Pressure Regulating Shutoff Valve 1, speed governing valve 2, power turbine 3, compressor 4, heat exchanger 5, cooling turbine 6, separator 7, shutoff valve 8 and bypass valve 9.Wherein connect speed governing valve 2 and turn-off valve 8 in the downstream of Pressure Regulating Shutoff Valve 1; Speed governing valve 2 downstreams connect power turbine 3, turn-off valve 8 downstreams and connect compressor 4, between compressor 4 outlets and cooling turbine 6 entrances, a heat exchanger 5 is installed, is connected a separator 7 in cooling turbine 6 downstreams, be provided with a bypass valve 9 between heat exchanger 5 and the separator 7.Power turbine (3), compressor (4) and the coaxial installation of cooling turbine (6).
By the source of the gas bleed, be divided into two branch roads through behind the Pressure Regulating Shutoff Valve 1.One the tunnel through speed governing valve 2, and the part air enters power turbine 3 expansion output mechanical powers, and the gas after the cooling of expanding is as the low-temperature receiver of heat exchanger 5 and the high temperature and high pressure gas heat exchange behind the compressor 4; The air of another branch road is through turn-offing valve 8, after compressed by compressor 4, enter heat exchanger 5 and reduce temperature, enter further expansion cooling of cooling turbine 6, air after the cooling is by separator 7, and the moisture that separator 7 gets off condensation in the cooled air is removed, and the Cryogenic air after dewatering enters passenger cabin or electronics bay, a part of hot-air of heat exchanger 5 outlets can be used to regulate the air themperature of cooling turbine 6 outlets by bypass valve 9.Again enter compressor 4 from passenger cabin or electronics bay air out, constantly circulate.
The utility model can be applicable to independently air circulation refrigeration system of large aircraft passenger cabin or electronic equipment, guarantees the amenity of passenger cabin, equipment reliably working in dry, cleaning and temperature adapt circumstance in it.Power turbine has controllable-area nozzle, by regulating the air intake duct nozzle area bleed pressure and required refrigerating capacity is complementary.For the air circulation system that is applied to passenger cabin, the pipeline that also needs to enter compressor in the passenger cabin outlet arranges efficient filtering and purifying, with the air quality that guarantees to enter passenger cabin.
Claims (2)
1. the totally-enclosed air circulation refrigeration system that drives of a power turbine, the totally enclosed type air circulation refrigeration system that described power turbine drives is comprised of Pressure Regulating Shutoff Valve (1), speed governing valve (2), power turbine (3), compressor (4), heat exchanger (5), cooling turbine (6), separator (7), shutoff valve (8) and bypass valve (9), it is characterized in that: connect speed governing valve (2) and turn-off valve (8) in the downstream of Pressure Regulating Shutoff Valve (1); Speed governing valve (2) downstream connects power turbine (3), turn-off valve (8) downstream and connect compressor (4), between compressor (4) outlet and cooling turbine (6) entrance, a heat exchanger (5) is installed, connect a separator (7) in cooling turbine (6) downstream, be provided with a bypass valve (9) between heat exchanger (5) and the separator (7).
2. the totally-enclosed air circulation refrigeration system of a kind of power turbine driving as claimed in claim 1 is characterized in that: power turbine (3), compressor (4) and the coaxial installation of cooling turbine (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220352925 CN202770042U (en) | 2012-07-20 | 2012-07-20 | Whole sealing air circulation refrigerating system driven by power turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220352925 CN202770042U (en) | 2012-07-20 | 2012-07-20 | Whole sealing air circulation refrigerating system driven by power turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202770042U true CN202770042U (en) | 2013-03-06 |
Family
ID=47776608
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220352925 Expired - Lifetime CN202770042U (en) | 2012-07-20 | 2012-07-20 | Whole sealing air circulation refrigerating system driven by power turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202770042U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN111547251A (en) * | 2020-04-13 | 2020-08-18 | 西安交通大学 | Turbine cooler |
| CN113353268A (en) * | 2021-06-18 | 2021-09-07 | 南京航空航天大学 | Semi-closed air circulation system for supplementing pressurized ram air by adopting centrifugal compressor |
-
2012
- 2012-07-20 CN CN 201220352925 patent/CN202770042U/en not_active Expired - Lifetime
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN111017235B (en) * | 2019-12-25 | 2021-09-03 | 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 |
| CN111547251A (en) * | 2020-04-13 | 2020-08-18 | 西安交通大学 | Turbine cooler |
| CN113353268A (en) * | 2021-06-18 | 2021-09-07 | 南京航空航天大学 | Semi-closed air circulation system for supplementing pressurized ram air by adopting centrifugal compressor |
| CN113353268B (en) * | 2021-06-18 | 2022-05-03 | 南京航空航天大学 | Semi-closed air circulation system for supplementing pressurized ram air by adopting centrifugal compressor |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130306 |