KR20190001185U - Turbine engine test system - Google Patents

Abstract

The present invention relates to a gas turbine engine test system, an engine test case in which a coupling member is formed so that a small gas turbine engine module, a data module, and a detection module are respectively assembled and analyzed, and characteristics of the small gas turbine engine module A gas turbine engine test system is provided which includes a main control device for detecting the gas turbine engine and detecting the gas turbine engine, and it is possible to enhance intuitive assembling and easy mobility.

Description

Gas turbine engine test system {TURBINE ENGINE TEST SYSTEM}

The present invention relates to a gas turbine engine test system, and more particularly to a gas turbine engine test system capable of test operation on various types of micro gas turbine engines.

Generally, a thermal power plant is an energy conversion facility that converts the chemical energy of a fuel into electrical energy. It consists largely of a boiler, a turbine and a generator. The turbine is a device that obtains the rotational force by the impulsive force or reaction force by using the flow of the compressible fluid such as steam or gas, and it is classified into the steam turbine or the gas turbine depending on the fluid to be used.

In recent years, the utilization of these gas turbines has been widening, and it has been widely used not only for large-scale facilities such as thermal power plants, but also for micro-engines requiring power and components for general education materials.

Basically, a gas turbine engine is a rotary compressor that continuously sucks atmospheric air, compresses it, combusts it in a separate combustor, and then flows into the turbine and expands to generate power continuously. The turbojet, turbofans, turboprops, turbo-shafts, and ramjets.

First, the turbojet engine receives air from the front part, sucks it, compresses it with a turbocompressor, mixes it with fuel in the combustion chamber to produce high-temperature and high-pressure gas, and then turns the turbine to obtain the power of the compressor, Jet nozzle into the atmosphere and obtain the propulsive force by the reaction force of the jet.

The turbofan engine also adds a turbine back to the turbojet's turbine back to absorb the energy in the exhaust gas, driving the fan on the front of the compressor using that energy, An engine that is designed to increase the thrust further by ejecting it from the side (side) to the rear of the engine without being used for combustion.

The turboprop engine is designed to extract 90% of the engine output to the shaft output and to drive the propeller through the decelerator to obtain the propulsive force and at the same time to obtain the remaining 10% of the propulsion power from the exhaust jet.

The turboshaft engine is an engine that extracts 100% of the engine output from the shaft output and uses it to power the helicopter's rotor, the ship's power, and industrial power.

Finally, the ramjet engine uses Bernoulli's theorem, which sucks the air required for combustion by the forward movement of the engine, compressing it in a simple cylinder, injecting, igniting, and burning fuel to obtain propulsion Engine.

In order to easily understand the characteristics and performance of such a gas turbine engine in a laboratory, a small gas turbine engine such as a micro gas turbine engine has been developed and released. Small gas turbine engines are generally used for educational or laboratory purposes and are approximately 100 to 600 mm in diameter and weigh approximately 1 to 10 kg. In order to test the characteristics and performance of such a small gas turbine engine, a test system capable of fixing a small gas turbine engine and measuring temperature, pressure, and thrust is needed.

Accordingly, the present invention is directed to a gas turbine engine test system capable of precisely measuring the performance of a small gas turbine engine.

The present invention also has another purpose in providing a gas turbine engine test system in which each configuration is modularized to simplify disassembly and assembly.

It is another object of the present invention to provide a gas turbine engine test system including a guide sticker that can intuitively assemble each modularized configuration.

The solution of the present invention is not limited to those mentioned above, and other solutions not mentioned can be clearly understood by those skilled in the art from the following description.

According to an aspect of the present invention, there is provided a small gas turbine engine module, comprising: a data module for processing data signals and control signals input to and output from the small gas turbine engine module; An engine test case in which a coupling member is formed so that a detection module for detecting a state value according to an operation of the small gas turbine engine module in response to the control signal and outputting the data signal as the data signal is assembled; And a main control device separately configured from the engine test case, for generating the control signal and analyzing and detecting characteristics of the small gas turbine engine module in response to the data signal.

In the present invention, it is preferable to further include a fixing module for fixedly connecting the small gas turbine engine module and the coupling member.

The gas turbine engine module of the present invention further includes a supply device for supplying various fuels to the small gas turbine engine module.

The apparatus may further include an auxiliary control device configured to separate from the engine testing device and to select at least one of the various fuels and to control a supply amount of the fuel

The main control device controls the driving force of the small gas turbine engine module, controls the temperature resolution of the temperature sensor in the detection module, controls the thrust force value of the thrust sensor, And the value of the control signal is controlled.

In the present invention, the main control device includes: a control unit for controlling the small gas turbine engine module, the data module, and the detection module; And a storage unit for storing previously stored experimental results, wherein the controller compares the initial experimental result after the assembly with the pre-stored experimental result to detect a system error.

According to another aspect of the present invention, there is provided a compact gas turbine engine module, comprising: a data module for processing data signals and control signals input to and output from the small gas turbine engine module; A plurality of cases for packaging each of the detection modules for detecting a status value according to an operation of the small gas turbine engine module in response to the control signal and outputting the status value as the data signal; And a plurality of case-loaded carrying boxes, wherein each module and each of the plurality of cases is formed with a matching member of a color corresponding to each of the modules, and a module package of the gas turbine engine test system is provided .

In the present invention, the carrying box may include: a main body having a top opened and a space in which the plurality of cases are seated; A partition wall part for dividing the interior of the main body into a predetermined area; And a lid part coupled to one side of the body part to cover and seal the upper part of the body part.

The plurality of cases may include a first case for packing the small gas turbine engine module; A second case for packaging the data module; And a third case for packaging the detection module, wherein the small gas turbine engine module and the first case are formed of a matching member of a first color, and the data module and the second case are formed of a matching member of a second color And the detection module and the third case are formed of a matching member of a third color.

In the present invention, it is preferable that the first to third cases include different internal seating spaces.

The gas turbine engine test system according to the present invention provides the following effects.

Since the present invention can test the operation of a micro gas turbine engine according to various fuels, it is possible to provide an optimum operating environment according to the fuel used in the use of the gas turbine engine.

Since the present invention is easy to disassemble and assemble into a gas turbine engine test system, it is easy to move or ship, and the installation time can be minimized.

The effects of the present invention are not limited to those mentioned above, and other effects not mentioned may be clearly understood by those skilled in the art from the following description.

1 schematically illustrates a gas turbine engine test system according to an embodiment of the present invention;
Figures 2 and 3 are a perspective view and a front view of the securing module of Figure 1;
4 is a perspective view showing a state in which the small gas turbine engine module is fixed to the fixed module of FIG.
5A to 5C are diagrams for showing a state in which each module is packaged.
FIG. 6 is a view showing a state in which each of the modular cases of FIG. 5 is loaded on a carrying box; FIG.
7 is a block diagram for explaining a function according to an embodiment of the present invention;

The scope of the present invention should not be construed as being limited by the embodiments described herein, as the description of the present invention is merely an example for structural or functional explanation. That is, the embodiments are to be construed as being variously embodied and having various forms, so that the scope of the present invention should be understood to include equivalents capable of realizing technical ideas. Also, the purpose or effect of the present invention should not be construed as limiting the scope of the present invention, since it does not mean that a specific embodiment should include all such effects or merely include such effects.

Meanwhile, the meaning of the terms described in the present application should be understood as follows.

The terms " first ", " second ", and the like are intended to distinguish one element from another, and the scope of the right should not be limited by these terms. For example, the first component may be referred to as a second component, and similarly, the second component may also be referred to as a first component.

It is to be understood that when an element is referred to as being "connected" to another element, it may be directly connected to the other element, but there may be other elements in between. On the other hand, when an element is referred to as being "directly connected" to another element, it should be understood that there are no other elements in between. On the other hand, other expressions that describe the relationship between components, such as "between" and "between" or "neighboring to" and "directly adjacent to" should be interpreted as well.

It is to be understood that the singular " include " or " have ", as used herein, is intended to encompass a plurality of expressions, unless the context clearly dictates otherwise, It is to be understood that the combination is intended to specify that it does not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, or combinations thereof.

In each step, the identification code (e.g., a, b, c, etc.) is used for convenience of explanation, the identification code does not describe the order of each step, Unless otherwise stated, it may occur differently from the stated order. That is, each step may occur in the same order as described, may be performed substantially concurrently, or may be performed in reverse order.

All terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs, unless otherwise defined. Commonly used predefined terms should be interpreted to be consistent with the meanings in the context of the related art and can not be interpreted as having ideal or overly formal meaning unless explicitly defined in the present application.

Hereinafter, a gas turbine engine test system according to an embodiment of the present invention will be described with reference to the drawings.

FIG. 1 is a schematic view for explaining a gas turbine engine test system according to an embodiment of the present invention. FIGS. 2 and 3 are views showing a fixing module (see FIG. 1) FIG. 4 is a perspective view illustrating a state in which the small gas turbine engine module 110 is fixed to the fixing module 130 shown in FIG. 1; FIG.

Referring to FIG. 1, a gas turbine engine test system according to an embodiment of the present invention includes a small gas turbine engine module 110, a data module for processing data signals and control signals input to and output from the small gas turbine engine module And a detection module (not shown) for detecting a state value according to an operation of the small gas turbine engine module 110 in response to the control signal and outputting the detected state value as the data signal, An engine test case 200 in which a plurality of test tubes 200 are formed; And a main control unit 300 separately configured from the engine test case 200 and generating the control signal and analyzing and detecting characteristics of the small gas turbine engine module 110 in response to the data signal . The gas turbine engine module 110 further includes a fixing module 130 for fixing the coupling member to the small gas turbine engine module 110.

Hereinafter, a description will be given with reference to Figs. 1 to 4. Fig.

First, the engine test case 200 is formed with the upper section 210, the lower section 220, and the lower section 230 sequentially from above. The structures are divided into modules and have a structure that can be assembled with each other.

A small gas turbine engine module 110 is fixedly mounted on an upper section 210 of the engine test case 200 and a fixed module 130 which linearly moves by the thrust of the small gas turbine engine module 110 is mounted, (Not shown) mounted on the gas turbine engine module 110 for detecting a state value according to the operation of the small gas turbine engine module 110 is mounted. Here, the state value may be, for example, temperature or pressure. At this time, the detection module may be constituted by a temperature sensor or a pressure sensor for detecting temperature or pressure.

A data module 120 for processing data signals and control signals input to and output from the small gas turbine engine module 110 is mounted on the lower section 220 of the engine test case 200. In one embodiment, the data module 120 is mounted within the lower section 220.

Here, the control signal is a signal generated in the main control unit 300 to be described later, and is a signal for controlling driving of the small gas turbine engine module 110 and for controlling the temperature sensor or the pressure sensor, which is a detection module, A data value output from the small gas turbine engine module 110 or a data value output from a temperature sensor or a pressure sensor.

Hereinafter, a gas turbine engine test system according to an embodiment of the present invention will be described in more detail.

The engine test case 200 has a generally rectangular parallelepiped shape, and the upper section 210 and the lower section 220 are separated by a plate (not shown). The height of the engine test case 200 can be formed to a height enough for the user to easily carry out the operation of the small gas turbine engine module 110 mounted on the upper section 210.

The upper section 210 is open at its front and includes a fixed module 130 on which a small gas turbine engine module 110 is mounted and a temperature sensor and a pressure sensor inserted into the small gas turbine engine module 110, The thrust sensor 133 is located. A front cover 211 formed of transparent reinforced plastic or the like may be coupled to the open front of the upper section 210. Since the front cover 211 allows the user to directly confirm the driving operation of the small gas turbine engine module 110, it is possible to prevent the possibility that malfunctions may occur due to foreign substances entering the small gas turbine engine module 110 And the small gas turbine engine module 110 can be prevented from accessing the user, such as debris or gas, which is generated unintentionally when the engine module 110 is operated.

The upper section 210 has a rectangular parallelepiped shape, and a screen 212 may be formed on one side thereof and an exhaust duct 213 may be formed on the opposite side thereof.

The screen 212 is formed adjacent to the inlet of the small gas turbine engine module 110 and the exhaust duct 213 is formed adjacent to the exhaust of the small gas turbine engine module 110. The screen 212 serves to filter impurities mixed in the gas flowing into the intake port of the small gas turbine engine module 110. The exhaust duct 213 has a hollow cylindrical shape and one end thereof is located adjacent to the exhaust port of the small gas turbine engine module 110 and the other end is passed through the side of the upper section 210. The exhaust duct 213 allows gas ejected from the small gas turbine engine module 110 to be smoothly exhausted from the upper section 210.

The lower section 220 has a rectangular parallelepiped shape, and the holder 221 protrudes forward. The user can place a notebook or other item on the cradle 221 and use it. The shelf 221 has a mobile shelf 222. The mobile shelf 222 can be taken out of the shelf 221 if necessary, and can be stored by being pushed into the shelf 221 when not in use.

A fuel pump (not shown), an oil pump (not shown), and a power supply (not shown) necessary for driving the small gas turbine engine module 110 are installed in the lower section 220 in addition to the data module 120 Is located.

The fixed module 130 located in the upper section 210 of the engine test case 200 is used to fix the small gas turbine engine module 110 and to perform linear motion by the thrust of the small gas turbine engine module 110 Section. The fixed module 130 is brought into contact with the thrust sensor 133 due to the linear motion, whereby the thrust of the small gas turbine engine module 110 is measured.

The fixed module 130 includes a pair of engine stands 131 for fixing the small gas turbine engine module 110, a protrusion 132 projecting forward from the lower end of the engine stand 131, And a linear guide 133 that allows linear motion at the lower portion of the protrusion 132. [ The fixing module 130 includes a thrust sensor 133 positioned in front of the protrusion 132 and a supporting bar 134 supporting the thrust sensor 133.

The engine stand 131, the protrusion 132, the linear guide 133 and the thrust sensor 189 of the fixing module 130 are located on the plate 135. The plate 135 has a rectangular shape and is fixed to the upper section 210 by four fixing members 136. At this time, an engaging member (not shown) is formed inside the upper section 210 so as to be assembled with the fixing module 130. The user can fix the fixing member 136 and the engaging member to the upper section 210 It is possible to assemble the fixing module 130.

A linear guide 133 is fixed on the plate 135 and a supporting bar 134 supporting the thrust sensor 133 is assembled to the side surface of the plate 135. [

Meanwhile, a small gas turbine engine module 110 is fixed between the pair of engine stands 131. As a method of fixing the small gas turbine engine module 110, a metal strap (not shown) The small gas turbine engine module 110 may be mounted on the engine stand 131 by welding.

The gap between the engine stands 131 may be slightly larger than the width of the small gas turbine engine module 110. The height of the engine stand 131 may be greater than the height of the thrust sensor 133 because the gas introduced into the intake port of the small gas turbine engine module 110 is not disturbed by the thrust sensor 133 .

The protrusion 132 protruding forward from the lower end of the engine stand 131 has a "C" shape and is spaced apart from the plate 135 by a certain distance. The projecting portion 132 applies a compressive force to the thrust sensor 133 while linearly moving together with the engine stand 131 by the thrust of the small gas turbine engine module 110.

The linear guide 133 is engaged with the lower portion of the engine stand 131 to enable linear movement of the engine stand 131 and the protrusion 132. The linear guide 133 is advantageous in that frictional resistance is very small because rolling motion is performed by inserting a rolling member such as a ball or a roller between the rolling surfaces in order to minimize friction during sliding motion of the engine stand 131 and the protrusion 132 have.

The thrust sensor 133 measures the thrust of the small gas turbine engine module 110, and a load cell may be used. The load cell is a device for calculating a load by measuring a deformation of an elastic body generated by applying a load using a strain gauge (not shown). In the present embodiment, a strain gauge is attached to an elastic member of an " S " shape to constitute a thrust sensor 133. The elastic member is pressurized by a protrusion 132 which linearly moves by the small gas turbine engine module 110, Sexually transformed.

Strain gauges attached to the elastic body of the thrust sensor 133 are electrically connected to each other, and are particularly assembled in the form of a Wheatstone bridge to limit the influence of temperature changes. The Wheatstone bridge is excited by the reference voltage at two opposite ends. The deformation of the elastic body changes the electrical resistance value and the length of the strain gauge, and the thrust is measured by comparing the change value of such resistance or length with that before the small gas turbine engine module 110 is operated. The thrust sensor 133 is connected to the data module 120 to provide data on thrust of the small gas turbine engine module 110.

Although the present invention is not limited to the load cell as the thrust sensor 133, the present invention is not limited thereto. Anything that can measure the thrust of the engine in contact with the protrusion 132 of the fixed module 130 Do.

The back surface of the thrust sensor 133 is supported by a support bar 134. [ One end of the support bar 134 is assembled and fixed to the bottom surface of the upper section 210 so that even when a load acts on the thrust sensor 133, the support bar 134 does not deviate from the set position, It will be. Also, the support bar 134 serves to support the plate 135 while contacting the plate 135. This makes it possible to prevent the position of the plate 135, the engine stand 131, and the protrusion 132 from deviating from the originally set position due to the repetitive operation of the small gas turbine engine module 110.

Referring again to FIG. 1, a gas turbine engine test system according to an embodiment of the present invention includes a main control device 300. The main control device 300 is separately constructed from the engine test case 200 and is connected to the engine test case 200 through a control signal for controlling the configuration mounted on the engine test case 200 and a data signal transmitted from the engine test case 200 And a structure for analyzing and detecting the characteristics of the small gas turbine engine module 110.

As will be described later, the present invention has a modular structure as a whole and facilitates separation and coupling through an assembly structure. Therefore, the user can buy only the necessary configuration according to the economic situation when purchasing it. At this time, instead of purchasing the main control device 300 of FIG. 1, instead of the main control device 300, It is also possible to connect to the data module 120 and proceed with testing for the gas turbine engine.

The main control unit 300 is provided with a display 310 for analyzing the characteristics of the small gas turbine engine module 110 and displaying the characteristics thereof in real time and the display 310 displays the characteristics of the small gas turbine engine module 110 Operating conditions (temperature, pressure, fuel volume, thrust) can also be displayed in real time.

And an operation portion 320 for operating the operation of the small gas turbine engine module 110 is disposed at one side of the display 310. [ The operation unit 320 may include a data terminal for controlling an engine control unit (ECU), a throttle lever, and the like.

1 to 4, a gas turbine engine test system according to an embodiment of the present invention includes a small gas turbine engine module 110, a data module 120 and a detection module (not shown), and a fixed module 130 ). Therefore, each of these can be safely placed and carried in a case, etc., and it is easy to assemble and detach. In addition, since it is possible to select and purchase each module, the economic burden can be minimized.

5A to 5C are views for showing the packaged state of each module.

FIG. 5A shows a state in which the small gas turbine engine module 110 is seated on a foamed styrofoam or a sponge, FIG. 5B shows a state in which the data module 120 is seated, and FIG. 5C shows a state in which the temperature sensor and the pressure sensor are seated.

The gas turbine engine test system according to the embodiment of the present invention can be individually modularized and individually packaged as shown in FIG. 5, and the module configuration can be easily transported.

For reference, although not shown in the drawings, a gas turbine engine test system according to an embodiment of the present invention is configured separately from an engine test case 200, and various types of fuel are supplied to the small gas turbine engine module 110 And an auxiliary control device configured to separate from the engine test case 200 and to select at least one of the various fuels and to control a supply amount of the corresponding fuel.

Here, the supply device (not shown in the figure) is configured to store various liquid gas, gas, etc., and the auxiliary control device (not shown in the drawing) To provide the selected gas at a desired amount of gas at a predetermined time.

Subsequently, like the small gas turbine engine module 110 and the data module 120 shown in FIG. 1, and the detection module, the supply device and the auxiliary control device can also be configured in a modular fashion, It is easy to separate and assemble. 7) of the main control device 300 generates a fifth control signal C5 and supplies the fifth control signal C5 to the main control device 300. In this case, It is possible to control the fuel selection operation and the fuel amount control of the apparatus.

FIG. 6 is a view showing a state in which each of the modularized cases of FIG. 5 is loaded in a carrying box; FIG.

Referring to FIG. 6, a module package 400 of a gas turbine engine test system includes a small gas turbine engine module 110, data for inputting and outputting data signals to and from the small gas turbine engine module 110, And a plurality of cases (M1, M2, ...) for packaging each of the detection modules for detecting status values according to the operation of the small gas turbine engine module (110) in response to the control signals and outputting them as the data signals, M2, M3, M4, and M5, and a plurality of cases M1, M2, M3, M4, and M5.

First, the transport boxes 410, 420, and 430 include a plurality of cases M1, M2, M3, M4, and M5 in which modules such as a small gas turbine engine module 110, a data module 120, And a cover for covering and sealing the upper portion of the main body 410. The main body 410 includes a main body 410 having a space in which a profile P for fixing and supporting is seated, (420); And a partition wall 430 for dividing the inside of the main body 410 into a predetermined area.

As a result, since a plurality of modules are packed in respective cases and loaded in the corresponding positions, it is possible to easily move to a desired place.

Meanwhile, in the module package 400 of the gas turbine engine test system according to the embodiment of the present invention, each of the modules and the plurality of cases is formed of a matching member of hue corresponding to each other, It is possible to pack the desired module intuitively in the desired case if it is necessary to re-disassemble and package.

The small gas turbine engine module 110 is packaged in the first case M1 and the data module 120 is packaged in the second case M2 and the detecting module is housed in the third case M3 ). ≪ / RTI >

At this time, the small gas turbine engine module 110 and the first case Ml may be formed of, for example, a red color matching member, and the data module 120 and the second case Ml may be formed of a blue color matching member And the detection module and the third case M3 may be formed of a matching member of a yellow color. The fact that the small gas turbine engine module 110 and the first case M1 are formed of the red matching member means that the entirety or a part of the outer appearance of the small gas turbine engine module 110 and the first case M 1 is a red color ≪ / RTI > or in a red color.

Accordingly, if the user assembles the gas turbine engine test system and performs the test operation and then disassembles and packs the gas turbine engine test system, the small-sized gas turbine engine module 110 of red color is packed in the first case M1 of red color , It is possible to package the data module 120 of blue color in the second case M2 and the third color module M3 of the yellow color by packing the data module 120 of blue color in the second case M2 , And thus it is possible to carry out more intuitive and quick packaging through the matching member according to the color.

For reference, the first case M1, the second case M2, and the third case M3 have the same case size as shown in the figure, but since different modules are seated and packed, Respectively. The first to fourth cases M 1, M 2, M 3, and M 4 of FIG. 6 have the same appearance, but the fifth case M 5 includes the first to fourth cases M 1, It has a different appearance. However, since the fifth case M5 and the module packaged therein are also formed of a matching member of a specific color, even if the user does not know the wrapped state, the matching module is referred to the matching member, It is possible.

7 is a block diagram for explaining a function according to an embodiment of the present invention.

7, the small gas turbine engine module 110 includes a jet engine drive unit 111, a temperature sensor 112, a thrust sensor 113, and a pressure sensor 114, 300 under the control of the control unit 330.

The control unit 330 generates the first to fourth control signals C1, C2, C3 and C4. The jet engine driving unit 111 controls the driving force in response to the first control signal C1, 112 are controlled in temperature resolution in response to the second control signal C2 and the thrust sensor 113 is controlled in response to the third control signal C3 to limit thrust values, The limit pressure value is controlled in response to the control signal C4.

The temperature resolution, the limit thrust value, and the limit pressure value, which are controlled by the control unit 330, to be driven in a desired test environment of the small gas turbine engine module 110. [

The main control unit 300 includes a display 310, an operation unit 320, a control unit 330, and a storage unit 340.

The storage unit 340 stores the data detected by the jet engine driving unit 111, the temperature sensor 112, the thrust sensor 113, and the pressure sensor 114 and the first to fourth The control signals C1, C2, C3 and C4 are stored, and the experimental results are additionally stored. The reason for storing the experimental results in the storage unit 340 will be described below.

The gas turbine engine test system according to the embodiment of the present invention maximizes mobility because it can be disassembled and assembled. However, if disassembly and assembly are frequent, it may happen that the assembly is not performed properly due to the user's mistake. In this case, when the small gas turbine engine module 110 is driven, it is not detected as a predetermined result. If driving continues in a state where the assembly is not completed, another accident may occur. Accordingly, the controller 330 compares the existing experimental result stored in the storage unit 340 with the first experimental result after the assembly. When the result is out of the predetermined margin range, the controller 330 recognizes that an error has occurred in the gas turbine engine test system, It is possible to tell.

The embodiments and the accompanying drawings described in the present specification are merely illustrative of some of the technical ideas included in the present invention. Therefore, it is apparent that the embodiments disclosed in the present specification are not intended to limit the technical idea of the present invention but to illustrate it, and the scope of the technical idea of the present invention is not limited by these embodiments. It should be understood that variations and specific embodiments which can readily be devised by those skilled in the art within the scope of the technical idea included in the specification and drawings of the present invention are included in the scope of the present invention.

110: Small gas turbine engine module
120: Data module
130: Fixed module
200: Engine test case
300: main control device

Claims (10)

A small gas turbine engine module, a data module for processing data signals and control signals input to and output from the small gas turbine engine module, and a controller for detecting a state value according to the operation of the small gas turbine engine module in response to the control signal An engine test case in which a coupling member is formed such that detection modules outputting the data signals are respectively assembled; And
And a main control device separately configured from the engine test case for generating the control signal and analyzing and detecting characteristics of the small gas turbine engine module in response to the data signal
Gas turbine engine test system.
The method according to claim 1,
Further comprising a fixing module for fixedly connecting the small gas turbine engine module and the engaging member
Gas turbine engine test system.
The method according to claim 1,
Further comprising a supply device configured to separate from the engine test case and to supply various fuels to the small gas turbine engine module
Gas turbine engine test system.
The method of claim 3,
Further comprising an auxiliary control device detached from the engine testing device, for selecting at least one of the various fuels and controlling the supply amount of the fuel
Gas turbine engine test system.
The method according to claim 1,
The main control device
Controls the driving force of the small gas turbine engine module, controls the temperature resolution of the temperature sensor in the detection module, controls the limit thrust force value of the thrust sensor, and controls the limit pressure value of the pressure sensor.
Gas turbine engine test system.
The method according to claim 1,
The main control device includes a control unit for controlling the small gas turbine engine module, the data module, and the detection module; And
And a storage for storing pre-stored experimental results,
Wherein the control unit detects a system error by comparing the initial experimental result after the assembly with the pre-stored experimental result
Gas turbine engine test system.
A small gas turbine engine module, a data module for processing data signals and control signals input to and output from the small gas turbine engine module, and a controller for detecting a state value according to the operation of the small gas turbine engine module in response to the control signal A plurality of cases for packaging each of the detection modules outputting the data signal; And
And a plurality of case-loaded carrying boxes,
Characterized in that each module and each of the plurality of cases are formed with matching members of hues corresponding to each other
Modular package of gas turbine engine test system.
8. The method of claim 7,
The transport box includes:
A main body portion having a top opened and a space in which the plurality of cases are seated;
A partition wall part for dividing the interior of the main body into a predetermined area; And
And a lid part coupled to one side of the main body part and covering the upper part of the main body part to seal the main body part
Modular package of gas turbine engine test system.
8. The method of claim 7,
In the plurality of cases,
A first case for packaging the small gas turbine engine module;
A second case for packaging the data module; And
And a third case for packaging the detection module,
Wherein the small gas turbine engine module and the first case are formed of a matching member of a first color, the data module and the second case are formed of a matching member of a second color, And is formed of a matching member of a third color
Modular package of gas turbine engine test system.
8. The method of claim 7,
Characterized in that the first to third cases include different internal seating spaces
Modular package of gas turbine engine test system.

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