CN116517850A - Refrigerating and pressurizing system of two-stage four-wheel turbine cooler - Google Patents

Refrigerating and pressurizing system of two-stage four-wheel turbine cooler Download PDF

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Publication number
CN116517850A
CN116517850A CN202310340047.1A CN202310340047A CN116517850A CN 116517850 A CN116517850 A CN 116517850A CN 202310340047 A CN202310340047 A CN 202310340047A CN 116517850 A CN116517850 A CN 116517850A
Authority
CN
China
Prior art keywords
turbine
refrigeration
compressor
air
shell
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN202310340047.1A
Other languages
Chinese (zh)
Inventor
张志莲
邓瑞洋
肖云峰
孔祥雨
张樱瀚
孙鑫悦
王云燕
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Beijing Institute of Petrochemical Technology
Original Assignee
Beijing Institute of Petrochemical Technology
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Beijing Institute of Petrochemical Technology filed Critical Beijing Institute of Petrochemical Technology
Priority to CN202310340047.1A priority Critical patent/CN116517850A/en
Publication of CN116517850A publication Critical patent/CN116517850A/en
Pending legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/10—Centrifugal pumps for compressing or evacuating
    • F04D17/12—Multi-stage pumps
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT 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
    • B64D13/02—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being pressurised
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
    • F04D29/051—Axial thrust balancing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
    • F25B—REFRIGERATION MACHINES, PLANTS OR SYSTEMS; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS
    • F25B11/00—Compression machines, plants or systems, using turbines, e.g. gas turbines
    • F25B11/02—Compression machines, plants or systems, using turbines, e.g. gas turbines as expanders
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT 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

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Health & Medical Sciences (AREA)
  • General Health & Medical Sciences (AREA)
  • Pulmonology (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The invention discloses a refrigerating and pressurizing system of a two-stage four-wheel type turbine cooler, and relates to the technical field of turbine coolers. The air compressor comprises a first air compressor and a second air compressor, the refrigeration turbine comprises a first refrigeration turbine and a second refrigeration turbine, the air compressor and the refrigeration turbine are coaxially arranged on the surface of a transmission shaft, a thrust bearing baffle is arranged between the first refrigeration turbine and the second air compressor, the thrust bearing baffle is fixedly arranged on the surface of an intermediate baffle through a pin, a circulation shell is fixedly arranged on the outer side of the intermediate baffle, an air flow reversing shell is fixedly arranged on the outer side of the circulation shell, two ends of the transmission shaft are screwed up and limited through fastening nuts, a turbine shell and an air compressor shell are fixedly arranged at the end part of the air flow reversing shell, and different split air inflow amounts can be respectively adjusted according to requirements, so that low-temperature air or high-pressure air with different amounts can be obtained, unnecessary waste can be avoided, the cost is obviously reduced, and the efficiency is better.

Description

Refrigerating and pressurizing system of two-stage four-wheel turbine cooler
Technical Field
The invention relates to the technical field of turbine coolers, in particular to a refrigerating and pressurizing system of a two-stage four-wheel turbine cooler.
Background
The turbine cooler is an important refrigeration technology in the environmental control system of the current civil aviation aircraft and fighter aircraft, and has the function of converting high-temperature high-pressure air of turbine air into low-temperature air through the turbine cooler so as to dissipate heat of a cabin and electronic nacelle equipment. With the development of electronic equipment and the improvement of integration level, the requirements on the refrigeration and pressurization technology of the turbine cooler are also higher and higher.
In the traditional refrigeration mode, the turbine refrigeration air outlet and the compressor boosting air outlet are the same air flow, and have some defects such as poor refrigeration effect, unbalanced axial force and the like in low-speed flight. Therefore, in order to cope with the increasingly severe environmental demands, various refrigeration modes such as TC, TMC, TTC, TTCF are sequentially generated, and the refrigeration efficiency and stability are improved by changing the flow direction of the air flow and adding some intermediate processes.
However, with the continuous improvement of the integration level of electronic equipment, the heat flux density and the heat dissipation power of the equipment are larger and larger, the load of the electronic heat dissipation equipment is further increased, and higher requirements are put on the performance and the stability of the turbine refrigerator.
Disclosure of Invention
The invention aims to provide a refrigerating and pressurizing system of a two-stage four-wheel type turbine cooler, which solves the technical problems.
In order to achieve the above purpose, the present invention provides the following technical solutions: the utility model provides a doublestage four-wheel turbine cooler refrigeration pressurization system, includes the compressor, the refrigeration turbine, the compressor includes first compressor, second compressor, the refrigeration turbine includes first refrigeration turbine, second refrigeration turbine, compressor and refrigeration turbine coaxial arrangement are at the transmission shaft surface, be provided with thrust bearing between first refrigeration turbine and the second compressor, thrust bearing surface is provided with thrust bearing baffle, thrust bearing baffle passes through pin fixed mounting at the middle baffle surface, middle baffle outside fixed mounting has the circulation casing, circulation casing outside fixed mounting has the air current switching-over casing, the both ends of transmission shaft are through tightening the nut tightening spacing, the tip fixed mounting of air current switching-over casing has turbine shell, air compressor casing.
Preferably, the two ends of the transmission shaft are connected with bearing bases through dynamic pressure air bearing, and a foil and a gear seal groove are arranged in a gap between the transmission shaft and the dynamic pressure air bearing.
Preferably, the air flow reversing shell is internally provided with an air compressing volume cavity and a turbine cold air volume cavity, an air compressing flow passage, a second limiting column and an air floating bearing baffle are arranged between the outer side of the turbine cold air volume cavity and a bearing base close to one end of the second refrigeration turbine, and a cold air flow passage and a first limiting column are arranged between the outer side of the air compressing volume cavity and the bearing base close to one end of the first compressor.
Preferably, the airflow reversing shell and the circulation shell are both provided with three hundred and sixty-degree annular staggered holes for air intake, and the two flow channels of the circulation shell are respectively used for circulating the pressure boosting gas and the turbine gas; the flow direction of the pressure-increasing gas is as follows: the gas from the second compressor flows radially to the circulation shell, enters the compressed gas volume cavity through a longitudinal perforation flow direction method, and is then discharged; turbine cold air flow direction: the other air which is shunted from the air source flows into the cold air volume cavity of the turbine through the cold air inlet of the turbine, enters the first refrigeration turbine through the circulation shell, enters the second refrigeration turbine through the roundabout of the airflow reversing shell, is discharged and enters relevant electronic equipment to absorb heat.
Preferably, the outer side of the airflow reversing shell is fixedly penetrated by a turbine cold air inlet and a compressor hot air outlet respectively, the turbine cold air inlet is communicated with the turbine cold air volume cavity, and the compressor hot air outlet is communicated with the compressor hot air volume cavity.
Preferably, the transmission shaft is respectively a first compressor, a first refrigeration turbine, a second compressor and a second refrigeration turbine from right to left, wherein the first refrigeration turbine and the second compressor are arranged at two sides of the thrust bearing in a back-to-back way.
Compared with the related art, the refrigerating and pressurizing system of the two-stage four-wheel type turbine cooler has the following beneficial effects:
1. the first compressor, the first refrigeration turbine, the second compressor and the second refrigeration turbine are coaxially connected to rotate at a high speed, one gas of gas source split flow enters the first compressor to boost pressure, flows into the second compressor through the gas compressing flow passage to boost pressure again, is discharged through the hot gas outlet of the compressor, and the other gas of gas source split flow flows into the second refrigeration turbine to expand and refrigerate again through the first refrigeration turbine to be discharged through the cold gas flow passage and then is discharged through the turbine outlet, and the refrigeration turbines and the compressors work simultaneously, so that different split flow air inflow amounts can be adjusted respectively according to requirements, low-temperature gas or high-pressure gas with different amounts can be obtained, unnecessary waste can be avoided, cost is obviously reduced, and efficiency is better.
2. The novel design air inlet circulation method is adopted, the three hundred sixty-degree annular punching channels are used for air inlet circulation, the air inlet circulation pipe is staggered, the space of the whole machine is reasonably utilized, the occupied area is reduced, compared with the traditional balance between axial forces of a single whole machine, the novel air inlet circulation type air inlet circulation device is more excellent in performance, the novel double-refrigeration turbine and double-compressor installation mode is adopted, the first refrigeration turbine and the second compressor which are positioned in the middle of the transmission shaft are in a back-to-back mode, self-balancing is easy, damage is avoided, the service life is long, the economical efficiency is higher, the refrigerating efficiency of an aircraft environmental control system is greatly improved, and the air inlet circulation type air inlet circulation device can work under design working conditions and non-design working conditions.
Drawings
FIG. 1 is a plan cross-sectional view of the overall structure of the present invention;
FIG. 2 is a perspective cross-sectional view of the overall structure of the present invention;
FIG. 3 is a schematic diagram of the overall structure of the present invention;
FIG. 4 is a schematic diagram of the flow of the air source according to the present invention;
FIG. 5 is a schematic view of the hot gas flow of a compressor in a flow-through housing configuration of the present invention;
fig. 6 is a schematic diagram showing the cooling direction of the refrigeration turbine in the flow-through housing structure of the present invention.
In the figure: 1. the second refrigerating turbine, 2, a transmission shaft, 3, a turbine shell, 4, a turbine cold air inlet, 5, an air bearing baffle, 6, a second limit column, 7, an air compressing runner, 8, a turbine cold air volume cavity, 9, an air flow reversing shell, 10, a circulation shell, 11, an intermediate baffle, 12, a thrust bearing baffle, 13, an air compressing volume cavity, 14, a cold air flow channel, 15, a compressor shell, 16, a first limit column, 17, a first compressor, 18, a dynamic pressure air bearing, 19, a gear seal groove, 20, a compressor hot air outlet, 21, a first refrigerating turbine, 22, a thrust bearing, 23 and a second compressor.
Detailed Description
Examples:
referring to fig. 1-6, the present invention provides a technical solution, including a compressor and a refrigeration turbine, the compressor includes a first compressor 17 and a second compressor 23, the refrigeration turbine includes a first refrigeration turbine 21 and a second refrigeration turbine 1, the compressor and the refrigeration turbine are coaxially installed on the surface of a transmission shaft 2, a thrust bearing 22 is disposed between the first refrigeration turbine 21 and the second compressor 23, a thrust bearing baffle 12 is disposed on the surface of the thrust bearing 22, the thrust bearing baffle 12 is fixedly installed on the surface of an intermediate baffle 11 through a pin, a circulation shell 10 is fixedly installed on the outer side of the intermediate baffle 11, an airflow reversing shell 9 is fixedly installed on the outer side of the circulation shell 10, two ends of the transmission shaft are screwed and limited through fastening nuts, and a turbine shell 3 and an air compressor shell 15 are fixedly installed at the end of the airflow reversing shell 9.
The two ends of the transmission shaft 2 are connected with bearing bases through dynamic pressure air bearing 18, and a foil and gear seal groove 19 is arranged in the gap between the transmission shaft 2 and the dynamic pressure air bearing 18.
The inside of the airflow reversing shell 9 is provided with an air compressing volume cavity 13 and a turbine cold air volume cavity 8, an air compressing flow passage 7, a second limit post 6 and an air bearing baffle 5 are arranged between the outer side of the turbine cold air volume cavity 8 and a bearing base close to one end of the second refrigeration turbine 1, and a cold airflow passage 14 and a first limit post 16 are arranged between the outer side of the air compressing volume cavity 13 and the bearing base close to one end of the first compressor 17.
The airflow reversing shell 9 and the circulation shell 10 are respectively provided with three hundred and sixty-degree annular staggered holes for air intake, and two flow passages of the circulation shell 10 are respectively used for circulating the pressure boosting gas and the turbine gas; the flow direction of the pressure-increasing gas is as follows: the gas from the second compressor 23 flows radially to the flow-through housing 10, enters the compressed gas volume chamber 13 by a longitudinal perforation flow method, and is then discharged; turbine cold air flow direction: the other air from the air source flows into the turbine cold air volume cavity 8 through the turbine cold air inlet 4, enters the first refrigeration turbine 21 through the circulation shell 10, bypasses through the airflow reversing shell 9 and enters the second refrigeration turbine 1, and then is discharged and enters relevant electronic equipment to absorb heat.
The outside of the airflow reversing shell 9 is respectively penetrated and fixed with a turbine cold air inlet 4 and a compressor hot air outlet 20, the turbine cold air inlet 4 is communicated with the turbine cold air volume cavity 8, and the compressor hot air outlet 20 is communicated with the compressor volume cavity 13.
The transmission shaft 2 is respectively provided with a first compressor 17, a first refrigeration turbine 21, a second compressor 23 and a second refrigeration turbine 1 from right to left, wherein the first refrigeration turbine 21 and the second compressor 23 are arranged on two sides of the thrust bearing 22 in a back-to-back way.
In this embodiment: the first compressor 17, the first refrigeration turbine 21, the second compressor 23 and the second refrigeration turbine 1 are coaxially connected for high-speed rotation, one gas of gas source split flow enters the first compressor 17 for boosting, flows into the second compressor 23 for boosting again through the gas compressing flow passage 7 and then is discharged through the gas compressor hot gas outlet 20, the other gas of gas source split flow flows into the second refrigeration turbine for expansion refrigeration through the first refrigeration turbine 21 and then is discharged through the turbine outlet after expansion refrigeration through the cold gas flow passage 14, the refrigeration turbines and the gas compressors work simultaneously, different split flow air inflow amounts can be respectively adjusted according to requirements, thus different low-temperature gas or high-temperature gas with different amounts can be obtained, unnecessary waste can be avoided, the device has the advantages that the device is remarkably reduced in cost and better in efficiency, adopts a brand new design air inlet circulation method, adopts a three hundred sixty-degree annular punching channel for air inlet circulation, adopts a staggered air inlet circulation pipe, reasonably utilizes the whole machine space, reduces the occupied area, is more excellent in performance compared with the traditional balance between axial forces of a single whole machine, adopts a brand new double-refrigeration turbine and double-compressor installation mode, adopts a back-to-back mode for the first refrigeration turbine 21 and the second compressor 23 which are positioned in the middle of the transmission shaft 2, is easy to balance, is not easy to damage, has long service life and higher economy, simultaneously greatly improves the refrigeration efficiency of an aircraft ring control system, and can work and operate under design working conditions and non-design working conditions.
The basic principle of refrigeration is as follows: after the gas split-flow of the gas source is expanded and refrigerated by the first refrigeration turbine 21, the gas enters the second refrigeration turbine 1 to be refrigerated by a turbine cold air flow channel, namely a cold air flow channel 14, the low-temperature gas coming out of the second refrigeration turbine 1 directly enters an air-liquid heat exchanger to exchange heat with high-temperature liquid heated by electronic equipment, high-temperature air coming out of the air-liquid heat exchanger and the like is directly discharged out of the cabin, and the high-temperature air coming out of the air-liquid heat exchanger does not enter a compressor coaxial with the refrigeration turbine any more; the low-temperature liquid from the air-liquid heat exchanger is pumped into the electronic equipment through a liquid supply pump, so that heat generated by the electronic equipment is taken away. The other gas of the gas source split flow is boosted by the first compressor 17, enters the second compressor 23 through the gas compressing flow passage 7 and is boosted again to obtain high-pressure gas, and is discharged into a undetermined area for use.
When the heat load is smaller, the refrigerating capacity provided by the refrigerating system can meet the requirement, and the air inflow of the refrigerating turbine does not need to be increased; when the heat load is large, the expansion outputs mechanical work, the air inflow of a refrigerating turbine is increased, the temperature drop of the cooling turbine and the refrigerating capacity of the system are increased, meanwhile, the pressure is increased, the air inflow of a single refrigerating mode is small for most of the time, and when the refrigerating system works under a non-design working condition, the efficiency is reduced to influence the refrigerating performance; the double-refrigeration turbine driving refrigeration system is adopted, the refrigeration turbine can be designed under the condition of small pod heat load, the air inlet degree is increased, most of the working works under the design working condition, the dynamic balance in a range is maintained, and the refrigeration performance is good. Based on the two-refrigerating turbine driven refrigerating system, the requirements of all aspects of the electronic equipment nacelle can be met, the boosted gas pressure also meets the requirements, the two gas flows can be independently controlled, and the two-refrigerating turbine driven refrigerating system is an effective system suitable for cooling and boosting the nacelle and the electronic equipment nacelle.

Claims (6)

1. The utility model provides a doublestage four-wheel formula turbine cooler refrigeration pressurization system, includes compressor, refrigeration turbine, its characterized in that: the compressor comprises a first compressor (17) and a second compressor (23), the refrigeration turbine comprises a first refrigeration turbine (21) and a second refrigeration turbine (1), the compressor and the refrigeration turbine are coaxially arranged on the surface of a transmission shaft (2), a thrust bearing (22) is arranged between the first refrigeration turbine (21) and the second compressor (23), a thrust bearing baffle (12) is arranged on the surface of the thrust bearing (22), the thrust bearing baffle (12) is fixedly arranged on the surface of an intermediate baffle (11) through a pin, a circulation shell (10) is fixedly arranged on the outer side of the intermediate baffle (11), an airflow reversing shell (9) is fixedly arranged on the outer side of the circulation shell (10), two ends of the transmission shaft are tightly limited through fastening nuts, and a turbine shell (3) and an air compressor shell (15) are fixedly arranged at the end part of the airflow reversing shell (9).
2. The two-stage four-wheel turbine cooler refrigeration and pressurization system according to claim 1, wherein: the two ends of the transmission shaft (2) are connected with bearing bases through dynamic pressure air bearing (18), and a foil and a gear seal groove (19) are arranged in a gap between the transmission shaft (2) and the dynamic pressure air bearing (18).
3. The two-stage four-wheel turbine cooler refrigeration and pressurization system according to claim 2, wherein: the air flow reversing device is characterized in that an air compressing volume cavity (13) and a turbine cold air volume cavity (8) are arranged in the air flow reversing shell (9), an air compressing flow passage (7), a second limiting column (6) and an air floating bearing baffle (5) are arranged between the outer side of the turbine cold air volume cavity (8) and a bearing base close to one end of the second refrigeration turbine (1), and a cold air flow passage (14) and a first limiting column (16) are arranged between the outer side of the air compressing volume cavity (13) and the bearing base close to one end of the first air compressor (17).
4. A two-stage four-wheel turbo chiller refrigeration and pressurization system according to claim 3 wherein: the air flow reversing shell (9) and the circulating shell (10) are both provided with three hundred and sixty-degree annular staggered holes for air inlet, and the two flow channels of the circulating shell (10) are respectively used for circulating the pressure boosting gas and the turbine gas.
5. The two-stage four-wheel turbine cooler refrigeration and pressurization system according to claim 4, wherein: the outside of the airflow reversing shell (9) is fixedly penetrated by a turbine cold air inlet (4) and a compressor hot air outlet (20) respectively, the turbine cold air inlet (4) is communicated with the turbine cold air volume cavity (8), and the compressor hot air outlet (20) is communicated with the compressor volume cavity (13).
6. The two-stage four-wheel turbine cooler refrigeration and pressurization system according to claim 5, wherein: the transmission shaft (2) is respectively provided with a first compressor (17), a first refrigeration turbine (21), a second compressor (23) and a second refrigeration turbine (1) from right to left, wherein the first refrigeration turbine (21) and the second compressor (23) are arranged on two sides of the thrust bearing (22) in a back-to-back mode.
CN202310340047.1A 2023-03-31 2023-03-31 Refrigerating and pressurizing system of two-stage four-wheel turbine cooler Pending CN116517850A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202310340047.1A CN116517850A (en) 2023-03-31 2023-03-31 Refrigerating and pressurizing system of two-stage four-wheel turbine cooler

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202310340047.1A CN116517850A (en) 2023-03-31 2023-03-31 Refrigerating and pressurizing system of two-stage four-wheel turbine cooler

Publications (1)

Publication Number Publication Date
CN116517850A true CN116517850A (en) 2023-08-01

Family

ID=87402070

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202310340047.1A Pending CN116517850A (en) 2023-03-31 2023-03-31 Refrigerating and pressurizing system of two-stage four-wheel turbine cooler

Country Status (1)

Country Link
CN (1) CN116517850A (en)

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