KR101220698B1 - Cooling device for high altitude test of gas turbine engine - Google Patents

Cooling device for high altitude test of gas turbine engine Download PDF

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Publication number
KR101220698B1
KR101220698B1 KR20100123506A KR20100123506A KR101220698B1 KR 101220698 B1 KR101220698 B1 KR 101220698B1 KR 20100123506 A KR20100123506 A KR 20100123506A KR 20100123506 A KR20100123506 A KR 20100123506A KR 101220698 B1 KR101220698 B1 KR 101220698B1
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South Korea
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fuel
unit
cooling
air
cooling unit
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KR20100123506A
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Korean (ko)
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KR20120062300A (en
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전용민
안이기
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한국항공우주연구원
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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Testing Of Engines (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)

Abstract

Disclosed is a cooling system for high-environmental testing of gas turbine engines that can cool fuel at low temperatures using cooling air without the need for a separate storage chiller. The cooling apparatus for the high-environmental test of the gas turbine engine according to an embodiment of the present invention is provided on the air guide unit for guiding low-temperature air, the air flow of the air guide unit, the heat transfer with the low-temperature air A fuel cooling unit cooling the accommodated fuel through the fuel supply unit, a fuel supply unit supplying the fuel to the fuel cooling unit, and one end of the fuel supply unit and the fuel cooling unit to communicate the fuel to the fuel cooling unit. Spray injection unit that can be provided by spraying, and a fuel discharge unit for discharging the cooled fuel. According to this configuration, it is possible to maximize the cooling efficiency of the fuel by spraying the fuel to expose as much surface area as possible to the outside.

Description

COOLING DEVICE FOR HIGH ALTITUDE TEST OF GAS TURBINE ENGINE}

A cooling device for testing the high environment of a gas turbine engine is disclosed. More specifically, a cooling apparatus for a high-environment test of a gas turbine engine capable of cooling fuel to low temperature using cooling air without using a separate storage cooling apparatus is disclosed.

Aircraft engines usually operate at high altitudes, so smooth operation at high altitudes must be ensured. On the other hand, the temperature, pressure, and density at high altitudes are very low compared to the ground, and at high altitudes, the aerodynamic and thermodynamic characteristics of the engine vary according to pressure and temperature changes, so the engines for aircrafts under such high altitude environments Should be tested to ensure that the

Ground-based high simulated test equipment is generally used for tests such as air force. The high-air simulation test facility makes the operating conditions of the engine similar to the actual high-air environment, and measures the aerodynamic, thermodynamic, and structural dynamics of the engine by measuring and analyzing the force, pressure, temperature, vibration, and flow rate from various sensors mounted thereon. As a test facility used to analyze and grasp operability, durability, safety, etc., it is widely used than actual flight test because it has various advantages such as saving test time and cost.

In order to perform the high simulation test as described above, the gas turbine engine combustor should be supplied with low temperature fuel and low temperature air similarly to the high environment.

In the conventional case, a device for cooling air used in a gas turbine engine is provided, and a fuel is cooled using a storage cooling device separately. That is, there is a problem that the efficiency is low and costly in terms of the structure using a dual cooling system.

In addition, since the fuel is mostly made of flammable materials, the storage, supply, and temperature control facilities of the fuel are separately installed in the outdoors, and thus there is a problem in that the temperature is changed to room temperature in the process of supplying the fuel to the test unit.

Therefore, in addition to the outdoor fuel equipment, a separate temperature controller was operated near the test unit, and a method of cooling the fuel through the temperature controller was used. However, this method has to be installed additional equipment for cooling the fuel, due to the large size of the cooling equipment has had a problem that it takes a lot of cost and unnecessary space to configure the fuel cooling equipment. As a result, energy consumption or space was inefficient due to double energy consumption.

In order to solve this problem, it is necessary to cool the fuel near the test section where the high-environmental test of the gas turbine engine takes place, but to find a more energy efficient method.

According to an embodiment of the present invention, there is provided a cooling apparatus for a high-environmental test of a gas turbine engine which is exposed to pre-cooled low temperature air and continuously cools fuel through heat transfer with the low temperature air.

In addition, even when the tube for cooling the fuel is exposed to low temperature air, it is designed not to obstruct the flow of low temperature air in one direction as much as possible for the high environment test of the gas turbine engine that can increase the efficiency of the overall system A cooling device is provided.

In addition, a cooling device is provided for the high-environmental test of the gas turbine engine that can maximize the cooling efficiency of the fuel by spraying the fuel to expose as much surface area to the outside.

The cooling apparatus for the high-environmental test of the gas turbine engine according to an embodiment of the present invention is provided on the air guide unit for guiding low-temperature air, the air flow of the air guide unit, the heat transfer with the low-temperature air A fuel cooling unit cooling the accommodated fuel through the fuel supply unit, a fuel supply unit supplying the fuel to the fuel cooling unit, and one end of the fuel supply unit and the fuel cooling unit to communicate the fuel to the fuel cooling unit. Spray injection unit that can be provided by spraying, and a fuel discharge unit for discharging the cooled fuel.

According to one side, the spray injection unit may include at least one nozzle.

According to one side, the fuel cooling unit is formed in a columnar shape, the thickness of the fuel cooling unit may become thinner toward the direction facing the flow of the guided air, so as not to interfere with the guide of the air.

According to one side, the shape of the cross section parallel to the air guide direction of the fuel cooling unit is preferably the shape of an airfoil (airfoil).

According to one side, the fuel cooling unit may be provided in plurality in the guide direction of the air sequentially.

According to one side, it is preferable that the fuel located at the top of the fuel cooling unit has a larger surface area exposed to the outside than the fuel located at the bottom.

The cooling tube according to an embodiment of the present invention is supplied with fuel and cooled after the fuel is discharged, exposed to low temperature air guided in one direction, and horizontal to the guide direction of the air so as not to interfere with the guidance of the air. The thickness of the cross section becomes thinner in the direction facing the air flow, and includes a spray injection unit on one side so that the fuel can be sprayed and supplied therein.

According to an embodiment of the present invention, a cooling tube for cooling the fuel is exposed to the pre-cooled low temperature air to continuously cool the fuel through heat transfer with the low temperature air.

In addition, even while the tube for cooling the fuel is exposed to low temperature air, the overall system efficiency can be improved by being designed so as not to disturb the flow of the low temperature air flowing in one direction as much as possible.

In addition, it is possible to maximize the cooling efficiency of the fuel by spraying the fuel to expose as much surface area to the outside.

1 is a view for explaining a cooling device for testing the high environment of the gas turbine engine according to an embodiment of the present invention,
FIG. 2 is a perspective view illustrating a cooling device for testing a high environment of the gas turbine engine of FIG. 1;
3 is a schematic cross-sectional view of FIG. 2;
4 and 5 schematically show the IV-IV cross section of FIG. 3 to explain various shapes of the fuel cooling unit, and
6 is a view schematically showing a cooling apparatus for explaining a modification of the fuel cooling unit.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, embodiments of the present invention will be described in detail with reference to the accompanying drawings.

The cooling device and its cooling tube according to one embodiment of the present invention are used to cool fuel for high altitude testing of gas turbine engines. Such cooling devices and cooling tubes are not necessarily limited to devices for testing high environments of gas turbine engines. That is, it can be used in various fields, and can be used as an apparatus for cooling a second medium such as fuel by using a first low temperature medium such as low temperature air.

The cooling device 100 includes an air guide unit 110, a fuel cooling unit 120, a fuel supply unit 121, a fuel discharge unit 122, and a spray injection unit 130. 1 to 3 are presented for more detailed description.

1 is a view for explaining a cooling apparatus for a high-environmental test of the gas turbine engine according to an embodiment of the present invention, Figure 2 is a perspective view showing a cooling apparatus for a high-environmental test of the gas turbine engine of Figure 1 And FIG. 3 schematically illustrates the cross section of FIG. 2.

Air guide unit 110 is a component for guiding the low-temperature air (A) to the gas intake engine (not shown) of the gas turbine engine or gas turbine engine for testing the high environment. By adjusting the pressure and temperature of the air (A) supplied to the engine inlet through the air guide unit 110, it is possible to simulate the operating state of the engine under a high altitude environment. At this time, the temperature and pressure of the air (A) passing through the air guide unit 110 can be variously adjusted according to the test environment and needs.

The air guide unit 110 may have a cross section rectangular, circular or elliptical. In this embodiment, however, the cross section is illustrated as having a pipe shape having a circular shape.

On the other hand, in the process of passing the low-temperature air (A) through the air guide unit 110, the outside of the air guide unit 110 to prevent the temperature of the air (A) rise due to heat transfer with the outside Insulation (not shown) may be further provided. As a result, the temperature of the air A can be kept constant in a low temperature state.

The air guide unit 110 may be connected to a plurality of parts through the flange 111. Accordingly, the cooling device 100 according to the present embodiment can be easily installed and separated.

The fuel cooling unit 120 serves as a cooling tube for cooling the fuel F1 supplied through the fuel supply unit 121. Therefore, the fuel cooling unit 120 exemplified as the cooling tube has a predetermined space formed therein to receive the fuel. When the fuel is supplied to the fuel cooling unit 120 through the fuel supply unit 121 as described above, the temperature of the fuel may be lowered through heat transfer with the low temperature air (A). The fuel cooling unit 120 is provided on the flow of air A so that cooling of the fuel can occur through heat transfer with the low temperature air A. Therefore, the fuel cooling unit 120 is illustrated as being located inside the air guide unit 110.

The fuel cooling unit 120 located inside the air guide unit 110 should not disturb the flow of low temperature air A, in addition to cooling the fuel using low temperature air A. Therefore, the fuel cooling unit 120 has a columnar shape perpendicular to the flow direction of the low-temperature air A, and the thickness of the fuel cooling unit 120 becomes thinner toward the direction facing the flow of the air A. FIG. It is desirable to have a configuration.

4 and 5 are schematic views illustrating the IV-IV cross section of FIG. 3 to describe various shapes of the fuel cooling unit 120.

4 and 5, in the fuel cooling unit 120, the thickness W2 on the side facing the flow of the low-temperature air A is the thickness W1 of the center region of the fuel cooling unit 120. It can be seen that the thinner formed. With this principle, the cross section of the fuel cooling unit 120 in the direction parallel to the air A guide direction may take the shape of a rhombus, an airfoil or the like. Further, preferably, the thickness W1 of the center region of the fuel cooling unit 120 may be limited to a level of 1/10 to 1/5 of the diameter of the air guide unit 110.

Due to this shape, even if the fuel cooling unit 120 is located in the middle of the flow of air A, the flow of air may not be hindered as much as possible.

Additionally, in order to improve the degree of heat transfer between the fuel cooling unit 120 and the low temperature air A, the fuel cooling unit 120 may be formed of a material having a high heat transfer rate. For example, some or all of the fuel cooling unit 120 may be formed of a copper material having high heat transfer rate.

The fuel supply unit 121 may be configured such that one end is connected to the fuel cooling unit 120 and the other end is connected to an external fuel storage tank (not shown). In this case, the spray injection unit 130 is provided at one end of the fuel supply unit 121 and the portion communicating the fuel cooling unit 120.

The spray injection unit 130 functions to finally spray the fuel supplied from the fuel supply unit 121 to provide the fuel cooling unit 120. The spray injection unit 130 includes at least one nozzle. Therefore, the desired amount of fuel injection can be obtained through at least one nozzle having a predetermined injection performance.

The fuel is sprayed into the fuel cooling unit 120 through the spray injection unit 130. Therefore, the fuel supplied to the liquid is injected into very small particles, and the fuel thus injected increases the surface area exposed to the outside. Therefore, heat is more effectively transmitted from the low-temperature air A, and rapid cooling of the fuel becomes possible.

Due to the spray injection unit 130, when the fuel cooling unit 120 is provided in a columnar shape in the vertical direction of the air flow inside the air guide unit 110, on the upper portion of the fuel cooling unit 120 The located fuel is formed with a larger surface area exposed to the outside than the fuel located below. That is, the injected fuel having a large surface area present in the upper portion of the fuel cooling unit 120 is rapidly cooled and moved to the lower portion, and is merged into a large drop as the cooling proceeds.

As a result, it is possible to inject the fuel with the desired injection characteristics through the spray injection unit 130, it is possible to continuously inject the desired amount, to increase the surface area of the fuel to enable rapid cooling of the fuel. And, the injected fuel is sufficiently received heat transfer from the low-temperature air (A), the fuel in the fuel cooling unit 120 can be cooled rapidly to a temperature similar to the low-temperature air (A).

On the other hand, one end of the fuel discharge unit 122 is connected to the fuel cooling unit 120, the other end is connected to the combustor (not shown), the fuel (F2) cooled by the fuel cooling unit 122 to the combustor Can supply In this case, the fuel supply unit 121, the fuel cooling unit 120, the spray injection unit 130, and the fuel discharge unit 122 may be integrally formed. Or it may be formed so that only the spray injection unit 130 can be replaced.

A modification of the cooling apparatus 100 will be described below in order to improve the heat transfer degree between the fuel cooling unit 120 and the low temperature air with reference to FIG. 6. 6 is a view schematically showing a cooling device 100 to explain a modification of the fuel cooling unit 120.

As shown in Figure 6, the fuel cooling unit 120 according to the present invention may be provided in plurality. That is, the fuel cooling unit 120 may be provided in plurality in the guide direction of the air sequentially. The number is not limited, but the following description will be given with three fuel cooling units.

The fuel F1 supplied through the fuel supply unit 121 may be supplied to the first fuel cooling unit 120a, the second fuel cooling unit 120b, and the third fuel cooling unit 120c. At this time, each may be connected to the first to third spray injection unit (130a, 130b, 130c). This configuration makes it possible to cool the fuel more quickly and effectively. And it is possible to adjust the injection degree of the fuel by adjusting the injection characteristics of each spray injection unit. Meanwhile, the number of fuel cooling units and the number of spray injection units may be selectively adjusted according to the degree of cooling required.

The fuel F1 supplied to the fuel supply unit 121 of the cooling apparatus 100 according to the embodiment of the present invention is the fuel cooling unit 120 through the sieve fuel supply unit 121 that is not cooled from a separate cooling unit. ) Can be supplied. However, not only that, it is also possible to supply the fuel cooling unit 120 in a state of cooling once through a temperature controller (not shown) installed separately in the outdoors, and to cool again from the low temperature air (A).

Through the configuration of the fuel cooling unit 120, which serves as the cooling device 100 or the cooling tube, it is possible to effectively supply the low-temperature fuel for testing the high environment of the gas turbine engine with a simple structure. At this time, the fuel can be rapidly cooled and continuously cooled by spraying the fuel, and the fuel can be cooled without limiting the shape of the fuel cooling unit 120 without disturbing the flow of low temperature air.

As described above, the present invention has been described by way of limited embodiments and drawings, but the present invention is not limited to the above embodiments, and those skilled in the art to which the present invention pertains various modifications and variations from such descriptions. This is possible.

Therefore, the scope of the present invention should not be limited to the described embodiments, but should be determined by the equivalents of the claims, as well as the claims.

100: cooling unit 110: air guide unit
120: fuel cooling unit 121: fuel supply unit
122: fuel discharge unit 130: spray injection unit
A: by air

Claims (8)

An air guide unit for guiding cold air;
A fuel cooling unit provided on a flow of air of the air guide unit to cool the fuel through heat transfer with the low temperature air;
A fuel supply unit supplying the fuel to the fuel cooling unit;
A spray injection unit which is formed to communicate one end of the fuel supply unit and the fuel cooling unit and sprays the fuel to the fuel cooling unit; And
And a fuel discharge unit for discharging the cooled fuel.
The fuel cooling unit is formed in a columnar shape, so that the thickness of the fuel cooling unit becomes thinner in a direction facing the flow of the guided air so as not to interfere with the guidance of the air. Cooling system. The method of claim 1,
The spray injection unit is a cooling device for testing the high environment of the gas turbine engine including at least one nozzle. delete The method of claim 1,
Cooling apparatus for a high-environmental test of a gas turbine engine having a shape of a cross section parallel to the air guide direction of the fuel cooling unit of the airfoil (airfoil). The method of claim 1,
The fuel cooling unit is a cooling device for a high-environmental test of the gas turbine engine is provided in plurality in the guide direction of the air sequentially. The method of claim 1,
Cooling apparatus for a high-environmental test of the gas turbine engine, characterized in that the fuel surface located on the upper portion of the fuel cooling unit has a larger surface area exposed to the outside than the fuel located on the bottom. delete delete
KR20100123506A 2010-12-06 2010-12-06 Cooling device for high altitude test of gas turbine engine KR101220698B1 (en)

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KR20100123506A KR101220698B1 (en) 2010-12-06 2010-12-06 Cooling device for high altitude test of gas turbine engine

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CN106441905A (en) * 2016-08-16 2017-02-22 中国航空工业集团公司沈阳发动机设计研究所 Signal transmission device with rotor acting as benchmark

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CN102980772B (en) * 2012-11-20 2015-06-17 凯迈(洛阳)机电有限公司 Pressure-maintaining fluid-infusion device of cooling fluid thermostatic device
CN104406794B (en) * 2014-12-01 2017-04-19 四川成发航空科技股份有限公司 Experimental device for detecting aeroengine guider
CN107588434A (en) * 2017-09-25 2018-01-16 上海泛智能源装备有限公司 A kind of spray cooling structure and combustor test device
CN110737292B (en) * 2019-09-20 2021-01-15 江苏大学 Wall surface temperature control system arranged in high-temperature and high-pressure container
CN115574348B (en) * 2021-07-05 2023-11-17 中国航发商用航空发动机有限责任公司 Gas spraying system, thermal shock fatigue tester and gas spraying cooling method

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KR20090066109A (en) * 2007-12-18 2009-06-23 한국항공우주연구원 Fuel cooler for low temperature gasturbine engine combustor performance test
KR20090006451U (en) * 2007-12-24 2009-06-29 한국동서발전(주) The Injection Test Device of Fuel Nozzle for Gas Turbine

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20090066109A (en) * 2007-12-18 2009-06-23 한국항공우주연구원 Fuel cooler for low temperature gasturbine engine combustor performance test
KR20090006451U (en) * 2007-12-24 2009-06-29 한국동서발전(주) The Injection Test Device of Fuel Nozzle for Gas Turbine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106441905A (en) * 2016-08-16 2017-02-22 中国航空工业集团公司沈阳发动机设计研究所 Signal transmission device with rotor acting as benchmark

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