KR101501007B1 - Apparatus for testing self operating device - Google Patents

Apparatus for testing self operating device Download PDF

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Publication number
KR101501007B1
KR101501007B1 KR20140073451A KR20140073451A KR101501007B1 KR 101501007 B1 KR101501007 B1 KR 101501007B1 KR 20140073451 A KR20140073451 A KR 20140073451A KR 20140073451 A KR20140073451 A KR 20140073451A KR 101501007 B1 KR101501007 B1 KR 101501007B1
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KR
South Korea
Prior art keywords
casing
self
air
operating device
hole
Prior art date
Application number
KR20140073451A
Other languages
Korean (ko)
Inventor
서정민
황순찬
박준영
박무룡
윤의수
최범석
유일수
임형수
방제성
최원철
Original Assignee
한국기계연구원
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Publication date
Application filed by 한국기계연구원 filed Critical 한국기계연구원
Priority to KR20140073451A priority Critical patent/KR101501007B1/en
Application granted granted Critical
Publication of KR101501007B1 publication Critical patent/KR101501007B1/en

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • 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

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Testing Of Engines (AREA)

Abstract

The present invention relates to an apparatus for testing a self operating device which is initially driven with supplied air and fuel and then continuously driven only with fuel. The apparatus for testing a self operating device includes a casing and a rotating part. The casing is provided in a hollow cylindrical shape to have a predetermined inner diameter, has both ends open, has an injection hole formed on a side surface, through which the external air is injected, and has one end where one end portion of an air supply passage of the self operating device is inserted, wherein the one end portion has an outer diameter corresponding to the inner diameter. The rotary part is provided to have an outer diameter corresponding to the inner diameter of the casing, is inserted into the casing, has one end connected to one end portion of the self operating device, has a through hole formed in a side surface, and selectively connects the injection hole with the through hole by being rotated. Accordingly, the apparatus for testing a self operating device selectively determines whether to inject air without separating the apparatus from the self operating device, thereby measuring efficiently and accurately whether the self operating device is self-driven.

Description

[0001] APPARATUS FOR TESTING SELF OPERATING DEVICE [0002]

The present invention relates to a self-drive test apparatus, and more particularly, to a self-drive test apparatus for continuously driving fuel and air after initial drive by supplying air and fuel, And which can easily and precisely perform a self-driving test.

Recently, power generation systems using a fuel cell or a micro gas turbine as a distributed power source have attracted attention, unlike a large-scale large-scale power plant. A micro power supply (MPG) is a micro power supply that is designed to supply power independently to devices that require power, such as portable equipment or small unmanned self-powered equipment.

Lithium secondary batteries are mainly used in portable devices currently in use. However, typical commercial secondary batteries have a disadvantage in that they are short in continuous use time and take a long time to charge, and the energy density is close to the theoretical limit, so that the performance of portable electronic devices can not be solved by conventional secondary batteries . Recently, as the products requiring portable power source such as pet robots, humanoid robots, and military robots are in commercialization phase, the need and urgency of a new micro power feeder is increasing. The micro power generation system is basically required to have higher energy density than the existing power source, and it is assured that it is necessary to develop the power generation system. Ultra micro gas turbine (UMGT) is attracting attention as a power generation device with high output and energy density.

2. Description of the Related Art Generally, a micro gas turbine is a rotary internal combustion engine. The micro gas turbine is a rotary type internal combustion engine, which is composed of a compressor that receives air from outside and compresses it to a high pressure, a high pressure air supplied from a compressor, A combustor, and a turbine rotated by a high-temperature and high-pressure combustion gas discharged from the combustor.

Particularly, in the case of a self-driven micro gas turbine driven by fuel alone, the motor is initially driven by a motor to rotate the compressor so that the supplied air is converted into high temperature in the compressor and high temperature in the combustor. , The drive of the motor is stopped and driven only by the force of the fuel.

At this time, a test apparatus for measuring the performance of the self-driven micro gas turbine is required. In the conventional self-drive test apparatus, an air injection device is connected to a gas turbine, air is supplied during initial operation, and then air is injected by removing the air to measure self-drive smoothness. However, there is a problem that measurement is troublesome in the process of connecting and removing the air injecting device, and air is injected in the process of removing the air injecting device.

SUMMARY OF THE INVENTION Accordingly, it is an object of the present invention to provide a self-drive test apparatus for continuously driving fuel and air by supplying air and fuel, And it is an object of the present invention to provide a self-drive test apparatus capable of efficiently and precisely measuring whether self-drive is performed by selectively determining whether air is injected without separating the drive apparatus.

The above object of the present invention can be also achieved by a self-driving device testing apparatus for continuously driving fuel and air by supplying air and fuel, A casing having one end thereof inserted with one end of an air supply passage of the self-driving device having an outer diameter corresponding to the inner diameter; And a through hole is formed in a side surface of the casing so that the through hole can be rotated to selectively communicate the through hole and the through hole with each other. And a turning part.

Here, a latching groove is formed at the other end of the casing,

The casing being provided in a disc shape having a diameter larger than the outer diameter of the casing and being provided at the other end of the rotation portion and integrally rotating with the rotation portion, And a finishing cap for closing the casing and having an engaging member inserted into the engaging groove to limit rotation of the rotating portion.

Here, it is preferable that the finishing cap is provided with a receiving groove which is recessed to receive the engaging member, and the engaging member receives an elastic force toward the casing.

Here, it is preferable to further include a sealing member interposed between the self-driving device and the turning portion.

According to the present invention, there is provided a self-drive test apparatus capable of inserting air without removing the structure for injecting air into the self-driving apparatus to test whether the self-driving is performed more efficiently and precisely.

In addition, after a certain amount of air is injected, the communication between the injection hole and the through hole is blocked and fixed through the engagement member, thereby preventing the air from being re-introduced during the test.

Further, since the engaging member is provided so as to have an elastic force and is inserted into the engaging groove, it is possible to easily determine whether air is injected through a simple operation.

1 is a view illustrating a combined state of a self-drive test apparatus and an ultra-small gas turbine according to an embodiment of the present invention.
2 is a schematic perspective view of a self-drive test apparatus according to an embodiment of the present invention.
3 is a schematic exploded perspective view of the self-drive test apparatus of FIG.
4 is a schematic cross-sectional view of the self-drive test apparatus of FIG.
Fig. 5 is a view schematically showing the operation of the latching member of the self-drive testing device of Fig. 2;

Hereinafter, a self-drive test apparatus according to an embodiment of the present invention will be described in detail with reference to the accompanying drawings.

The self-drive test apparatus according to an embodiment of the present invention is a self-drive test apparatus capable of efficiently and precisely measuring whether self-drive is performed by selectively determining whether air is injected without separating the self- .

Before describing a self-drive test apparatus according to an embodiment of the present invention, a micro gas turbine connected to a self-driving device according to an embodiment of the present invention to supply external air will be briefly described.

1) is a rotary type internal combustion engine, which is composed of a compressor that receives air from outside and compresses it to a high pressure, a high-pressure air supplied from the compressor, and a fuel supplied from the fuel tank, A combustor for generating a combustion gas, and a turbine, a generator / motor, a recuperator and the like, which are rotated by a high-temperature high-pressure combustion gas discharged from the combustor.

In this case, the micro gas turbine 10 is initially driven by a motor to rotate the compressor to generate high-pressure air in the compressor, to supply high-temperature, high-pressure energy to the turbine, Driven self-powered gas turbine 10 that stops driving the motor and drives only the fuel.

However, the apparatus in which the self-drive test apparatus is used is not necessarily limited to the micro gas turbine 10, but may be applied to various self-drive apparatuses driven by similar principles.

2 is a schematic perspective view of a self-drive test apparatus according to an embodiment of the present invention. FIG. 2 is a schematic perspective view of a self- 3 is a schematic exploded perspective view of the self-drive test apparatus of FIG. 2, and FIG. 4 is a schematic cross-sectional view of the self-drive test apparatus of FIG.

1 to 4, a self-drive testing apparatus 100 according to an embodiment of the present invention includes a casing 110, a rotation unit 120 inserted into the casing 110, a rotation unit 120 And a seal member 150 interposed between the swivel unit 120 and the micro gas turbine 10 so as to prevent the gas turbine 10 from being caught by the sealing cap 130. [ do.

The casing 110 is configured to supply outside air to the micro gas turbine 10 side, and is provided in a hollow cylindrical shape. Inside the casing 110, one end portion of a pivoting portion 120 and a micro gas turbine 10 device described later is inserted. Specifically, since the outside air is supplied to the compressor side of the micro gas turbine 10, one end of the air supply passage close to the compressor is inserted into one end of the casing 110.

On the other hand, an injection hole 111 communicating with the inside of the casing 110 is formed on the side surface of the casing 110. An air injection pipe or the like may be connected to the injection hole 111 so that external air can be supplied. The size and the number of the injection holes 111 are preferably determined in consideration of the size of the apparatus, the amount of air to be injected, and the like.

In addition, the casing 110 is provided to have a predetermined thickness, and an engagement groove 112 is formed at the other end opposite to where the one end of the micro gas turbine 10 is inserted. An engaging member 140 installed in the finishing cap 130 is inserted into the engaging groove 112 to restrict the rotation of the rotating portion 120. At this time, after the engaging member 140 is inserted, the engaging groove 112 may be formed with a predetermined inclination so that the engaging member 140 can be easily detached when the user rotates the finishing cap 130.

The pivot portion 120 is configured to supply outside air injected through the injection hole 111 to the micro gas turbine 10 side, and is provided in a hollow cylindrical shape. One end of the rotation unit 120 is connected to one end of the micro gas turbine 10 inserted into the casing 110 and the other end of the micro turbine 10 is inserted into the casing 110. The diameter of the rotation unit 130 is smaller than the diameter of the casing 110, And a finishing cap 130 is installed at the other end of the swinging part 120.

A through hole 121 through which external air is injected is formed in a side surface of the swinging part 120. At this time, it is preferable that the through holes 121 and the injection holes 111 formed in the casing 110 are the same size. The external air injected through the injection hole 111 is moved through the through hole 121 into the swivel 120 and is then introduced into the micro gas turbine 10 through the injection hole 111 and the through hole 121, . The size and the number of the through holes 121 are preferably determined in consideration of the size of the device, the amount of air to be injected, and the like as well as the injection holes 111.

On the other hand, the turning unit 120 is rotatably provided in the casing 110. The rotation of the swinging part 120 determines whether or not the injection hole 111 and the through hole 121 are in communication with each other. The external air supplied to the micro gas turbine 10 through the injection hole 111 and the through hole 121 communicates with the injection hole 111 and the through hole 121 by the rotation of the rotary part 120. [ The supply to the micro gas turbine 10 side is cut off.

The finishing cap 130 rotates the rotary part 120 to determine whether external air is supplied or not, and prevents the external air injected into the rotary part 120 from flowing out.

The finishing cap 130 is provided in a disk shape larger than the diameter of the casing 110 and installed at the other end of the swivel portion 120 connected to the micro gas turbine 10. The casing 110 connected to the micro gas turbine 10 and the other end of the swinging part 120 are closed by the finishing cap 130. Since the diameter of the finishing cap 130 is larger than the diameter of the casing 110, the user can easily rotate the turning unit 120 to rotate the turning unit 120. In this embodiment, the finishing cap 130 is formed integrally with the pivoting portion 120 so that the pivoting portion 120 is easily pivotable and the inside is precisely closed. However, the present invention is not limited thereto.

A receiving recess 131 formed to be recessed is formed in a region of the finishing cap 130 in contact with the casing 110. When the receiving groove 131 and the engaging groove 112 are communicated with each other by the rotation of the finishing cap 130, the engaging member 140 is engaged with the engaging groove 112 So that rotation of the finishing cap 130 is restricted. When the receiving groove 131 and the engaging groove 112 are communicated with each other, it is preferable that the injection hole 111 and the through hole 121 are not communicated with each other. Since the micro gas turbine 10 requires air supply during the initial operation and no additional air supply is required when the micro gas turbine 10 is self-driven, the injection hole 111 and the through hole 121 are not connected It is preferable that the engaging member 140 is inserted into the engaging groove 112.

The latching member 140 includes a resilient member 141 and a latching jaw 142 for restricting rotation of the finishing cap 130. [ The elastic member 141 is installed in the receiving groove 131 to receive an elastic force toward the casing 110 and the latching jaw 142 is installed at one end of the elastic member 141. When the receiving groove 131 and the engaging groove 112 are not communicated with each other, the engaging member 140 receives elastic force toward the casing 110, but the extension of the engaging member 140 toward the casing 110 is restricted by the casing 110. However, when the receiving groove 131 and the engaging groove 112 are communicated by the rotation of the finishing cap 130, the elastic member 141 is extended toward the casing 110 by the elastic force, Is inserted into the latching groove 112. As a result, rotation of the finishing cap 130 is restricted.

On the other hand, it is preferable that the latching jaws 142 are provided so as to correspond to the inclination formed in the latching grooves 112. The user can rotate the finishing cap 130 so that the injection hole 111 and the through hole 121 are communicated with each other by the shape of the engaging jaw 142 and the engaging groove 112. [ That is, when the stopping jaw 142 is inserted into the stopping groove 112, the rotation is limited and fixed, and there is no possibility of rotating itself. However, when the user rotates the end cap 130, Can be pivoted by the shape of the base 112. Therefore, when the user judges that air is required to be injected in the state in which the engaging groove 142 is inserted into the engaging groove 112, or when the user tests the other apparatus, the user rotates the finishing cap 130 to rotate the injection hole 111 And the through hole 121 are communicated with each other so that air can be injected.

The sealing member (150) is interposed between one end of the micro gas turbine (10) and the turning portion (120). It is possible to prevent the air inside the swinging part 120 from flowing out to the outside by the sealing member 150.

Hereinafter, the operation of the self-drive test apparatus according to one embodiment of the present invention will be described.

First, one end of the micro gas turbine 10 and the pivot 120 are inserted into the casing 110 to interconnect the micro gas turbine 10 and the pivot 120. At this time, the seal member 150 is interposed between the micro gas turbine 10 and the swivel unit 120, thereby sealing the inside of the swivel unit 120 more accurately.

Thereafter, the finishing cap 130 is rotated so that the injection hole 111 and the through hole 121 are communicated with each other. Thereafter, external air is injected through an air injection pipe connected to the injection hole 111 or the like.

By driving the motor of the micro gas turbine 10 to rotate the compressor, the supplied external air is brought into a high-pressure state in the compressor, and the high-temperature state is established in the combustor so that high-temperature and high-pressure energy is transferred to the turbine.

After the micro gas turbine 10 is initially driven, the supply of the outside air is stopped to test whether the micro gas turbine 10 is self-driven. Thus, the finishing cap 130 is rotated until the engaging grooves 112 and the receiving grooves 131 communicate with each other. When the engaging groove 112 and the receiving groove 131 are communicated with each other, the engaging member 140 in the receiving groove 131 is inserted into the engaging groove 112 by the elastic force, do. At this time, since the injection hole 111 and the through hole 121 are not communicated with each other, external air is not injected. Since the engaging member 140 is inserted into the engaging groove 112, the outside air is not injected any more unless the user operates it separately, and it is determined whether the external air is injected only by rotating the finishing cap 130 have.

Therefore, according to the present invention, there is provided an apparatus for testing a self-driving apparatus which continuously drives fuel only after supplying air and fuel and performing initial driving, wherein the self-driving test apparatus and the self- And a self-drive test apparatus capable of efficiently and precisely measuring whether or not self-drive is performed is provided.

The scope of the present invention is not limited to the above-described embodiments, but may be embodied in various forms of embodiments within the scope of the appended claims. It will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the present invention as defined by the appended claims.

10: Micro gas turbine 100: Self-drive test device
110: casing 111: injection hole
112: engaging groove 120:
121: Through hole 130: Finishing cap
131: receiving groove 140: engaging member
150: sealing member

Claims (4)

A testing apparatus for a self-driving device (10) for initially driving a vehicle by supplying air and fuel, and continuously driving the vehicle by fuel only,
A self-driving device (10) having a hollow cylindrical shape with a predetermined inner diameter and having both ends opened, an injection hole (111) for injecting outside air into the side surface, and an outer diameter corresponding to the inner diameter at one end, A casing 110 into which the one end of the air supply passage of the casing 110 is inserted;
And has an outer diameter corresponding to the inner diameter of the casing 110 and is inserted into the casing 110 so that one end thereof is connected to one end of the self drive device 10 and the through hole 121 is formed in a side surface thereof, And a turning part (120) rotating to selectively communicate the injection hole (111) with the through hole (121). The method according to claim 1,
An engaging groove 112 is formed at the other end of the casing 110,
And is rotatable integrally with the rotation unit 120. The rotation unit 120 is installed at the other end of the casing 120, 110 are inserted into the coupling grooves 112 to restrict the rotation of the rotary part 120. The rotation of the rotary part 120 is restricted by the rotation of the rotary part 120, Further comprising a finishing cap (130) on which an engaging member (140) is provided. 3. The method of claim 2,
The finishing cap 130 is formed with a receiving groove 131 in which the engaging member 140 is received,
And the engaging member (140) receives an elastic force toward the casing (110). 3. The method of claim 2,
Further comprising a sealing member (150) interposed between the self-driving device (10) and the rotary part (120).
KR20140073451A 2014-06-17 2014-06-17 Apparatus for testing self operating device KR101501007B1 (en)

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Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR100857610B1 (en) 2007-11-05 2008-09-09 한국남부발전 주식회사 Apparatus for testing low-speed, high-speed and over-speed by using power generation turbine
KR100911310B1 (en) 2007-08-16 2009-08-11 한국항공우주연구원 Rake and performance measurement system for gas turbine combustors using the same
KR20120064281A (en) * 2010-12-09 2012-06-19 한국항공우주연구원 Sand and dust injection apparatus with air tube for gas turbine engine test

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR100911310B1 (en) 2007-08-16 2009-08-11 한국항공우주연구원 Rake and performance measurement system for gas turbine combustors using the same
KR100857610B1 (en) 2007-11-05 2008-09-09 한국남부발전 주식회사 Apparatus for testing low-speed, high-speed and over-speed by using power generation turbine
KR20120064281A (en) * 2010-12-09 2012-06-19 한국항공우주연구원 Sand and dust injection apparatus with air tube for gas turbine engine test

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
서정민, 박준영, 최범석, 박무룡, "500W급 초소형 가스터빈 개발을 위한 압축기 성능 평가", 한국유체기계학회 논문집 15(6), 2012.12, pp51-57 *

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