KR101781833B1 - Fuel cooling and heating system for propellant rocket engine - Google Patents

Fuel cooling and heating system for propellant rocket engine Download PDF

Info

Publication number
KR101781833B1
KR101781833B1 KR1020150190799A KR20150190799A KR101781833B1 KR 101781833 B1 KR101781833 B1 KR 101781833B1 KR 1020150190799 A KR1020150190799 A KR 1020150190799A KR 20150190799 A KR20150190799 A KR 20150190799A KR 101781833 B1 KR101781833 B1 KR 101781833B1
Authority
KR
South Korea
Prior art keywords
refrigerant
fuel
heating
cooling
supply line
Prior art date
Application number
KR1020150190799A
Other languages
Korean (ko)
Other versions
KR20170079821A (en
Inventor
전준수
유병일
이정호
서대반
한영민
정용갑
Original Assignee
한국항공우주연구원
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 한국항공우주연구원 filed Critical 한국항공우주연구원
Priority to KR1020150190799A priority Critical patent/KR101781833B1/en
Publication of KR20170079821A publication Critical patent/KR20170079821A/en
Application granted granted Critical
Publication of KR101781833B1 publication Critical patent/KR101781833B1/en

Links

Images

Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M15/00—Testing of engines
    • G01M15/14—Testing gas-turbine engines or jet-propulsion engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/44—Feeding propellants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
    • 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
    • F25B29/00—Combined heating and refrigeration systems, e.g. operating alternately or simultaneously
    • F25B41/003—
    • F25B41/04—
    • 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
    • F25B45/00—Arrangements for charging or discharging refrigerant
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
    • G01K13/00—Thermometers specially adapted for specific purposes
    • 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
    • F25B2700/00—Sensing or detecting of parameters; Sensors therefor
    • F25B2700/21—Temperatures

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Thermal Sciences (AREA)
  • General Physics & Mathematics (AREA)
  • Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
  • Feeding And Controlling Fuel (AREA)

Abstract

A fuel cooling and heating device for a rocket engine propellant is disclosed.
A fuel cooling and heating apparatus for a rocket engine propellant for simulating various atmospheric conditions of a fuel, the fuel cooling and heating apparatus for a rocket engine propellant comprising: an enclosed case filled with a cooling or heating refrigerant; A heat exchanger disposed within said enclosure for exchanging kerosene as a propellant fuel with a cooling refrigerant or a heating refrigerant; And a heating heater disposed in the hermetically sealed case and heating the heated refrigerant, the fuel supply line for supplying kerosene to the heat exchanger; A fuel discharge line for discharging kerosene from the heat exchanger; A supply pump for supplying kerosene to the fuel supply line; a cooling refrigerant supply line connected to a lower portion of the closed case; A heated refrigerant supply line connected to a lower portion of the closed case; And a discharge line connected to a lower portion of the closed case to discharge the cooling refrigerant and the heating refrigerant, the first temperature measuring device being supported by the closed case and measuring the temperature of the upper side of the heating refrigerant; And a second temperature meter for measuring a temperature of the lower side of the heated refrigerant while being supported by the closed case, wherein each of the temperature gauges senses the temperature of the heated refrigerant by position, And the filling amount can be confirmed.

Description

[0001] Fuel cooling and heating system for propellant rocket engines [

The present invention relates to a fuel cooling and heating apparatus for a rocket engine propellant.

More specifically, it is possible to separately cool and heat the fuel for the rocket engine propellant, thereby simulating various atmospheric conditions of the fuel, and to improve the efficiency of the engine in consideration of the physical change amount of the fuel obtained by this condition. To a fuel cooling and heating device for a propellant.

The rocket engine uses two propellants, oxidizer and fuel, to generate thrust through the chemical reaction. Liquid oxygen is generally used as the oxidizing agent, and hydrocarbon as a fuel is generally used, and kerosene is most widely used.

On the other hand, the kerosene may change its physical properties depending on the external atmospheric conditions, particularly the temperature change, thereby affecting the efficiency of the engine. Therefore, it is necessary to analyze in advance how the kerosene changes according to the temperature change and to improve the efficiency of the engine in advance. In the past, it was not possible to test the kerosene because there was no separate equipment for testing the kerosene.

Prior Art Document 1: Laid-open Patent Publication No. 10-2012-0075944 (Publication date: July 9, 2012)

It is an object of the present invention to provide a rocket engine capable of separately cooling and heating a fuel for a rocket engine propellant so as to simulate various atmospheric conditions of the fuel and to improve the efficiency of the engine, And a fuel cooling and heating device for an engine propellant.

According to an object of the present invention, there is provided a fuel cooling and heating simulation apparatus for a rocket engine propellant for simulating various atmospheric conditions of a fuel,
A sealed case filled with a cooling refrigerant or a heating refrigerant;
A heat exchanger disposed within said enclosure for exchanging kerosene as a propellant fuel with a cooling refrigerant or a heating refrigerant; And
And a heater for heating the heated refrigerant while being disposed in the hermetically sealed case,
A fuel supply line for supplying kerosene to the heat exchanger;
A fuel discharge line for discharging kerosene from the heat exchanger;
And a supply pump for supplying kerosene to the fuel supply line,
A cooling refrigerant supply line connected to a lower portion of the sealed case;
A heated refrigerant supply line connected to a lower portion of the closed case;
And a discharge line connected to a lower portion of the closed case to discharge the refrigerant and the heating refrigerant,
A first temperature meter for measuring an upper temperature of the heated refrigerant while being supported by the closed case;
And a second temperature meter for measuring a temperature of the lower side of the heated refrigerant while being supported by the closed case, wherein each of the temperature gauges senses the temperature of the heated refrigerant by position, A fuel cooling and heating device for a rocket engine propellant is provided which can confirm the filling amount.
Preferably, the present invention may further include an opening / closing valve and a bellows pipe provided on the supply line.

delete

delete

delete

delete

The present invention is preferably such that the cooling refrigerant supply line, the heating refrigerant supply line and the discharge line are branched from one pipe.

The present invention is preferably such that each of the lines is individually opened and closed by an on-off valve.

In the present invention, preferably, the cooling refrigerant filled in the sealed case is liquid nitrogen, and the heating refrigerant is water.

The present invention preferably further comprises a gasification gas line installed on the upper portion of the closed case.

delete

The present invention is capable of cooling and heating the fuel for rocket engine propellant separately so that various atmospheric conditions of the fuel can be simulated and the efficiency of the engine can be improved in consideration of the physical change amount of the fuel obtained by this condition have.

1 is a configuration diagram of a fuel cooling and heating apparatus for a rocket engine propellant according to the present invention.

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings.

The terms used in the present invention are defined in consideration of the functions of the present invention and may vary depending on the intention or custom of the user or the operator. Therefore, the definitions of these terms are meant to be in accordance with the technical aspects of the present invention As well as the other.

In addition, optional terms in the following embodiments are used to distinguish one element from another element, and the element is not limited by the terms. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS In the following description of the present invention, detailed description of related arts which may unnecessarily obscure the gist of the present invention will be omitted.

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a block diagram of a fuel cooling and heating apparatus for a rocket engine propellant according to the present invention; FIG.

Referring to FIG. 1, the fuel cooling and heating apparatus for a rocket engine propellant according to the present invention is capable of separately cooling and heating a fuel for a rocket engine propellant to simulate various atmospheric conditions of fuel, A heat exchanger (200) and a heater (300).

The sealed case 100 is for filling a coolant or a heated coolant, and may include an upper case 110 and a lower case 120.

The upper case 110 and the lower case 120 have flanges 111 and 121 formed therein and have a structure in which the flanges 111 and 121 are fastened together. At this time, a gasket (not shown) is preferably interposed between the upper case 110 and the flange portions 111 and 121 of the lower case 120 to maintain airtightness.

Here, the cooling refrigerant filled in the closed casing 100 may be liquid nitrogen, and the heating refrigerant may be water.

For reference, the liquid nitrogen is a liquefied nitrogen and exists as a liquid at -196 캜 under atmospheric pressure. The critical temperature is -147.21 캜, and the critical pressure is 33.5 atm. The boiling point is -196 ° C under latm. Nitrogen is a gaseous element which occupies 80% of the air volume as a two-atom molecule. It can be industrially obtained by liquid fractionation (fractional liquefaction) of air. Chemically, a mixture of ammonium chloride and sodium nitrite is heated Obtained by distillation. The nitrogen thus obtained is cooled to -196 캜 to produce liquid nitrogen. Liquid nitrogen is colorless and transparent and has great fluidity. In addition to the basic raw materials for synthesis of ammonia, their properties such as inertness and low temperature are attracting attention. Such liquid nitrogen maintains a cryogenic temperature of -196 캜 at atmospheric pressure, and thus can be effectively used for quenching kerosene.

A coolant supply line 131 for injecting the coolant into the sealed case 100 may be connected to the lower portion of the lower case 120. A heated coolant supply line 132 for injecting the heated coolant may be connected to the coolant supply line 131, And a discharge line 133 for discharging the cooling refrigerant and the heating refrigerant may be connected.

Here, the cooling refrigerant supply line 131, the heating refrigerant supply line 132, and the discharge line 133 may be branched from one pipe 130, but the present invention is not limited thereto.

Further, the respective lines 131, 132, and 133 may be provided with open / close valves 131a, 132a, and 133a, respectively, so that each line can be individually opened and closed as needed.

For example, when the refrigerant is injected into the enclosed case 100, the opening / closing valve 131a of the refrigerant supply line 131 is opened while the heating refrigerant supply line 132 and the discharge line 133 are opened Closing valves 132a and 133a are closed,

Closing valve 132a of the heating and refrigerant supply line 132 is opened while the refrigerant supply line 131 and the discharge line 133 are opened and closed by the respective opening and closing valves 131a , 133a are closed,

Closing valve 133a of the discharge line 133 is open while the cooling refrigerant supply line 131 and the heating and refrigerant supply line 132 are opened and closed respectively when the cooling refrigerant or the heating refrigerant of the closed casing 100 is discharged, The valves 131a and 132a are closed.

The heat exchanger 200 exchanges kerosene, which is the propellant fuel, with the cooling or heating coolant. The heat exchanger 200 has a tubular shape to allow kerosene to flow therethrough and is disposed inside the closed casing 100.

Here, it is preferable that the heat exchanger 200 is a serpentine tube to increase heat exchange efficiency.

A fuel supply line 210 for supplying kerosene to the inside of the heat exchanger 200 is connected to the inlet side of the heat exchanger 200. A fuel discharge line 210 for discharging kerosene from the heat exchanger 200 is connected to the outlet side of the heat exchanger 200, And a supply pump P for supplying fuel from the fuel tank T to the supply line 210 may be connected to the supply line 210. [

An opening and closing valve 211 for opening and closing the fuel supply line 210 may be provided on the fuel supply line 210. In addition, (Not shown).

The heating heater 300 is for heating the heated refrigerant and is fitted into the fitting portion 112 provided at the center of the upper case 110 of the closed casing 100.

It is preferable that the heating heater 300 has a stick shape and its length is designed to be such that the lower end thereof is located at the bottom portion of the closed casing 100. This is to allow the heating refrigerant filled in the lower case 120 to be heated as a whole regardless of its level. That is, to improve the speed and efficiency of heating.

Meanwhile, the present invention may further include a gasification gas line 140 installed on the upper portion of the closed casing 100. The gasification gas vent line 140 is provided to prevent the inner pressure of the case from excessively rising due to vaporization of liquid nitrogen when the liquid nitrogen is filled into the closed casing 100, The vaporized gas is discharged through the vaporized gas vent line 140 when the inside of the chamber is above a certain pressure.

The present invention also includes a first temperature meter 141 for measuring the temperature of the upper side of the heated refrigerant while being supported by the closed case 100 and a second temperature meter for measuring the lower temperature of the heated refrigerant, (142).

The first and second temperature gauges 141 and 142 can detect the temperature of the heated coolant by position, and can check the amount of the heated coolant and the coolant.

When the propellant fuel is to be heated, water is injected into the sealed case 100 through the heated refrigerant supply line 132 and filled therein until the heat exchanger 200 is locked.

Thereafter, power is applied to the heating heater 300 to heat water to a predetermined temperature, and the supply pump P is operated to pump the fuel from the fuel tank T and supply the fuel to the heat exchanger 200. As a result, the fuel flowing inside the heat exchanger 200 is heated while being heat-exchanged by the heated coolant.

Conversely, when the propellant fuel is to be cooled, liquid nitrogen is injected into the closed casing 100 through the cooling refrigerant supply line 131, and the liquid is filled until the heat exchanger 200 is locked.

Thereafter, the supply pump P is operated to pump the fuel from the fuel tank T and supply the fuel to the heat exchanger 200. As a result, the fuel flowing inside the heat exchanger 200 is cooled while being heat-exchanged by the cooling coolant.

It will be apparent to those skilled in the art that various modifications, substitutions and substitutions are possible, without departing from the scope and spirit of the invention as disclosed in the accompanying claims. will be. Therefore, the embodiments disclosed in the present invention and the accompanying drawings are intended to illustrate and not to limit the technical spirit of the present invention, and the scope of the technical idea of the present invention is not limited by these embodiments and the accompanying drawings . The scope of protection of the present invention should be construed according to the following claims, and all technical ideas within the scope of equivalents should be construed as falling within the scope of the present invention.

100: sealed case 110: upper case
120: lower case 200: heat exchanger
210: fuel supply line 220: fuel discharge line
300: Heating heater

Claims (9)

A fuel cooling and heating simulator for a rocket engine propellant for simulating various atmospheric conditions of fuel,
A sealed case filled with a cooling refrigerant or a heating refrigerant;
A heat exchanger disposed within said enclosure for exchanging kerosene as a propellant fuel with a cooling refrigerant or a heating refrigerant; And
And a heater for heating the heated refrigerant while being disposed in the hermetically sealed case,
A fuel supply line for supplying kerosene to the heat exchanger;
A fuel discharge line for discharging kerosene from the heat exchanger;
And a supply pump for supplying kerosene to the fuel supply line,
A cooling refrigerant supply line connected to a lower portion of the sealed case;
A heated refrigerant supply line connected to a lower portion of the closed case;
And a discharge line connected to a lower portion of the closed case to discharge the refrigerant and the heating refrigerant,
A first temperature meter for measuring an upper temperature of the heated refrigerant while being supported by the closed case;
And a second temperature meter for measuring a temperature of the lower side of the heated refrigerant while being supported by the closed case, wherein each of the temperature gauges senses the temperature of the heated refrigerant by position, Fuel cooling and heating device for rocket engine propellant that can check filling amount.
delete The method according to claim 1,
Further comprising an on-off valve and a bellows pipe installed on the supply line.
delete The method according to claim 1,
Wherein the cooling refrigerant supply line, the heating refrigerant supply line, and the discharge line are branched from one pipe.
The method of claim 5,
Wherein each of the lines is individually opened and closed by an on-off valve.
The method according to claim 1,
Wherein the cooled refrigerant filled in the sealed case is liquid nitrogen and the heated refrigerant is water.
The method of claim 7,
Further comprising a vaporizing gas vat line disposed on the upper portion of the closed casing.
delete
KR1020150190799A 2015-12-31 2015-12-31 Fuel cooling and heating system for propellant rocket engine KR101781833B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
KR1020150190799A KR101781833B1 (en) 2015-12-31 2015-12-31 Fuel cooling and heating system for propellant rocket engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
KR1020150190799A KR101781833B1 (en) 2015-12-31 2015-12-31 Fuel cooling and heating system for propellant rocket engine

Publications (2)

Publication Number Publication Date
KR20170079821A KR20170079821A (en) 2017-07-10
KR101781833B1 true KR101781833B1 (en) 2017-09-26

Family

ID=59356368

Family Applications (1)

Application Number Title Priority Date Filing Date
KR1020150190799A KR101781833B1 (en) 2015-12-31 2015-12-31 Fuel cooling and heating system for propellant rocket engine

Country Status (1)

Country Link
KR (1) KR101781833B1 (en)

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP3133845B2 (en) * 1991-11-28 2001-02-13 シュルンベルジェ オーバーシーズ エス．エイ． Logging method and apparatus using annular electrode and azimuthal electrode

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP3133845B2 (en) * 1991-11-28 2001-02-13 シュルンベルジェ オーバーシーズ エス．エイ． Logging method and apparatus using annular electrode and azimuthal electrode

Also Published As

Publication number Publication date
KR20170079821A (en) 2017-07-10

Similar Documents

Publication Publication Date Title
RU2018129582A (en) LPG Distribution Kit
CN102435632A (en) Testing system for researching flow boiling heat transfer character and pressure drop character of cryogenic fluid
KR20100015831A (en) Hydrogen gas-cooling device
CN103674516A (en) Low temperature stiffness measuring device and method of diaphragm capsule assembly for carrier rocket
CN109073147A (en) It is applicable in the hydrogen filling station of liquid hydrogen
LeClair et al. Modeling cryogenic chilldown of a transfer line with GFSSP
KR101781833B1 (en) Fuel cooling and heating system for propellant rocket engine
KR20180136486A (en) Gas filling device
CN101008470A (en) Process and arrangement for filling high pressure gas containers using a filling tube
CN104819889B (en) Diamond anvil cell press minimum gas liquefying plant
CN109655131B (en) Visual experiment system for liquid phase pipeline of differential pressure type liquid level meter of low-temperature container
KR20150146203A (en) Measurement Apparatus of the Insulation to Measure Thermal Insulation Performance
CN109342496B (en) Low-temperature heat insulation performance measurement test method for vacuum conveying pipe
Cao et al. Experimental investigation of the characteristics of supercritical CO2 during the venting process
CN103344487B (en) Device for low-temperature stretching test of metal material
Lee et al. In-tube convective heat transfer characteristics of CO2 mixtures in a pipeline
Lee et al. Operational strategy to minimize operating costs in liquefied natural gas receiving terminals using dynamic simulation
CN114824356A (en) Aircraft with fuel cell and structure having tank containing heat transfer fluid ensuring cooling of fuel cell
Ebrahiminejadhasanabadi Solubility studies of carbon dioxide in novel hybrid solvents using a new static synthetic apparatus.
CN116066722A (en) Integrated modular system for transfer, storage and delivery of Liquefied Natural Gas (LNG)
RU2347134C1 (en) Device for thermocycling of cylinders-compressors
Jin et al. Experimental investigation of line chill-down process with liquid oxygen
Townsend et al. Design and development of a helium injection system to improve external leakage detection during liquid nitrogen immersion tests
Travis et al. GASFLOW Simulations for Cryogenic Tank Loss of Vacuum Scenarios
CN208169994U (en) A kind of LNG vaporization device

Legal Events

Date Code Title Description
A201 Request for examination
E902 Notification of reason for refusal
E90F Notification of reason for final refusal
E701 Decision to grant or registration of patent right
GRNT Written decision to grant