公开(公告)号：KR1020030074002A

公开(公告)日：2003-09-19

申请号：KR1020020014207

申请日：2002-03-15

Applicant: 한국항공우주연구원

Inventor： 전용민 ,  양인영 ,  김춘택 ,  남삼식 ,  양수석 ,  이대성

IPC: F16G11/12

CPC classification number: F16G11/12 ,  G01L1/2218

Abstract: PURPOSE: A turnbuckle having a load cell is provided to mount a mounting object to a specific site with a circular scale detecting plate and scale installed to a tip of a gap adjusting screw. CONSTITUTION: A gap adjusting screw(3,3') forming a ring(6,6') is assembled to a clamping nut(2,2') toward right and left directions. A circular scale indicating plate(4,4') is formed to an inner tip of the gap adjusting screw. Scale(5,5') is formed to a side of the clamping nut to indicate a gap. A tubular center portion(7) is formed to a middle portion of the clamping nut. A load cell(9) is composed of a strain gauge by processing an installing portion(8) from an upper side forming scale. The load cell is mounted to a turnbuckle(1). Therefore, a mounting object is mounted to a precise site by controlling a precise mounting site of the gap adjusting screw. Displacement of the gap adjusting screw and load on the clamping nut are measured by installing the load cell to the installing portion.

Abstract translation: 目的：提供一种具有称重传感器的螺丝扣，用于将安装对象安装到特定位置，并将圆形刻度检测板和刻度尺安装到间隙调节螺钉的尖端。 构成：形成环（6,6'）的间隙调节螺钉（3,3'）朝向左右方向组装到夹紧螺母（2,2'）。 在间隙调节螺钉的内端形成有圆周指示板（4,4'）。 刻度（5,5'）形成在夹紧螺母的一侧以指示间隙。 管状中心部分（7）形成在夹紧螺母的中间部分。 负载传感器（9）由应变计通过从上侧成形标尺处理安装部（8）构成。 称重传感器安装在螺丝扣（1）上。 因此，通过控制间隙调节螺钉的精确安装位置，将安装对象安装到精确位置。 通过将称重传感器安装到安装部分来测量间隙调节螺钉的位移和夹紧螺母上的负载。

公开(公告)号：KR101456990B1

公开(公告)日：2014-11-04

申请号：KR1020130070486

申请日：2013-06-19

Applicant: 한국항공우주연구원

Inventor： 전용민

IPC: F28F1/12 ,  F28F1/24

Abstract: 본 발명에 따른 유선형의 열교환 장치는 타원형 구조를 갖는 유선형 관, 및 유선형 관을 관통하여, 유선형 관의 내주면과 외주면에 동시에 형성되어, 유선형 관 내부로 이동중인 저온 또는 고온 유체의 온도대로 대기중의 온도를 저온 또는 고온화시키는 열교환 핀,을 포함하되, 열교환핀이 형성된 유선형 관이 대형 관에 설치되어 상기 대형 관내를 흐르는 유동(Duct flow)의 높거나 낮은 온도에너지를 상기 유선형 관 내부를 이동 중인 유체로 전달시켜, 공기의 흐름을 크게 방해하지 않고도 유질(FLOW QUALITY)을 최상으로 유지하면서 열효율을 극대화할 수 있는 효과가 있다.

Abstract translation: 根据本发明，流线型热交换器包括具有椭圆结构的流线型管道; 以及穿过流线型管道的热交换销，以同时形成内周面和外周面，以便随着在流线型管道内流动的低温或高温流体的温度而降低或增加大气温度。 具有形成热交换销的流线型管道被安装在大的管道上，以将在大管道内流动的流体的高或低热能传递到在流线型管道内移动的流体，从而最佳地保持流动质量而不严重扰乱空气 流量和最大化热效率。

公开(公告)号：KR101374356B1

公开(公告)日：2014-03-25

申请号：KR1020120157465

申请日：2012-12-28

Applicant: 한국항공우주연구원

Inventor： 전용민

IPC: B64D33/02 ,  G05B19/04 ,  B64D43/00

CPC classification number: B64D33/02 ,  B64D43/00 ,  B64D45/00 ,  B64D2045/0085 ,  F02M35/10

Abstract: The present invention relates to a method for controlling the distortion of an aircraft air scoop. By using a sensor including a pressure sensor, a temperature sensor, a velocity sensor, an acceleration sensor, and a posture sensor, the distortion of an inlet can be sensed, and the sensed information is provided, after being classified into one among normal, warning, and danger levels. When the distortion rate of the inlet reaches a limit value of a graph showing the planning margin of a compressor, a forced control is conducted, in order to reduce the distortion of the inlet. [Reference numerals] (AA) Normal, Warning; (BB) Danger; (S01) Measurement step; (S02) Operation step; (S03) Inlet distortion determination step; (S03a) First output step; (S03b) Second output step; (S03c) Third output step; (S04) Control range calculating step; (S05) Air suction hole control step

Abstract translation: 本发明涉及一种用于控制飞机空气勺的变形的方法。 通过使用包括压力传感器，温度传感器，速度传感器，加速度传感器和姿态传感器的传感器，可以感测入口的变形，并且在将感测信息分为正常的， 警告和危险等级。 当入口的失真率达到表示压缩机的规划余量的曲线图的极限值时，进行强制控制，以便减小入口的变形。 （附图标记）（AA）正常，警告; （BB）危险; （S01）测量步骤; （S02）操作步骤; （S03）入口失真确定步骤; （S03a）第一输出步骤; （S03b）第二输出步骤; （S03c）第三输出步骤; （S04）控制范围计算步骤; （S05）吸气孔控制步骤

公开(公告)号：KR101305776B1

公开(公告)日：2013-09-06

申请号：KR1020110141860

申请日：2011-12-26

Applicant: 한국항공우주연구원

Inventor： 전용민

IPC: F02C7/06 ,  F01M5/00 ,  F02C6/04

Abstract: 본 발명은 터빈엔진의 오일펌프 가열장치에 관한 것으로서, 더욱 상세하게는 시동기에 에너지를 공급하는 가스공급장치로부터 가스를 공급받아 터빈엔진의 오일펌프를 가열하여 저온상태에 의해 높아진 윤활오일의 점성을 낮춰 저온, 비정상 상태에서의 터빈엔진 구동시 소모되는 동력을 줄이기 위한 터빈엔진의 오일펌프 가열장치에 관한 것이다.

公开(公告)号：KR1020090067687A

公开(公告)日：2009-06-25

申请号：KR1020070135432

申请日：2007-12-21

Applicant: 한국항공우주연구원

Inventor： 전용민 ,  안이기

IPC: F02K1/30 ,  F02K1/06 ,  F02K1/15

Abstract: An engine nozzle opening device is provided to facilitate fabrication and to reduce expense because the configuration of the open member opening the engine nozzle closure is relatively simple. An engine nozzle opening device comprises an engine nozzle(10), an engine nozzle cap(20), an engine nozzle cap turning member, and an engine nozzle cap opening member. The engine nozzle generates thrust in a gas turbine engine. The engine nozzle closure is positioned in the exit of the engine nozzle. The engine nozzle cap opens and closes the engine nozzle. The engine nozzle closure turning member rotates the engine nozzle closure around the other end. The engine nozzle closure open member supports the upper end of the engine nozzle closure.

Abstract translation: 提供了一种发动机喷嘴打开装置，以便于制造和降低费用，因为打开发动机喷嘴盖的打开构件的构造相对简单。 发动机喷嘴打开装置包括发动机喷嘴（10），发动机喷嘴盖（20），发动机喷嘴盖转动构件和发动机喷嘴帽开口构件。 发动机喷嘴在燃气涡轮发动机中产生推力。 发动机喷嘴盖位于发动机喷嘴的出口处。 发动机喷嘴帽打开和关闭发动机喷嘴。 发动机喷嘴闭合转动构件围绕另一端旋转发动机喷嘴闭合。 发动机喷嘴闭合件打开构件支撑发动机喷嘴闭合件的上端。

公开(公告)号：KR1020080060029A

公开(公告)日：2008-07-01

申请号：KR1020060134087

申请日：2006-12-26

Applicant: 한국항공우주연구원

Inventor： 이경재 ,  이진근 ,  전용민 ,  고성희 ,  양수석 ,  이대성

IPC: G01M99/00

Abstract: A nozzle and an icing test simulation apparatus with the same are provided to increase reliability of a test result by making droplets having approximately same size and density as the actual droplets in the air. An icing test simulation system includes a liquid supply unit(110), a liquid pressure controller(120), a gas supply(130), a gas pressure controller(140), a spray(150), a cooling unit(160), and a controller(170). The liquid supply unit contains a liquid tank(112) and a gas tank(132). The liquid tank is connected to the spray through a first pipe(114). The liquid tank and the gas tank are connected to each other through a second pipe(116). The liquid pressure controller is installed on the second pipe and controls the amount of gas transmitted from the gas tank. The gas supply unit includes a third pipe(134). The third pipe connects the gas tank and the spray for transmitting the gas from the gas tank to the spray. The gas pressure controller controls pressure of the gas transmitted from the gas tank for changing the size of a droplet discharged from the spray. The spray is installed on a junction of the first and third pipes and mixes the gas and liquid supplied from the liquid tank to spray the mixture to the outside. The cooling unit provides conditions for icing the droplets discharged from the spray. The controller controls operations of the liquid controller and the gas controller.

Abstract translation: 提供了一种具有该喷嘴和一个结冰测试模拟装置，以通过使具有与空气中的实际液滴大致相同的尺寸和密度的液滴来提高测试结果的可靠性。 一种结冰测试模拟系统，包括液体供应单元（110），液体压力控制器（120），气体供应（130），气体压力控制器（140），喷雾器（150），冷却单元（160） 和控制器（170）。 液体供应单元包含液体罐（112）和气体罐（132）。 液体罐通过第一管（114）连接到喷雾器。 液罐和气罐通过第二管（116）相互连接。 液压控制器安装在第二管上，控制从气罐传出的气体量。 气体供给单元包括第三管道（134）。 第三条管道连接气罐和用于将气体从气罐传输到喷雾器的喷雾器。 气体压力控制器控制从气罐传递的气体的压力，用于改变从喷雾喷出的液滴的尺寸。 将喷雾器安装在第一和第三管道的接合处，并将从液体罐供应的气体和液体混合以将混合物喷射到外部。 冷却单元为从喷雾喷出的液滴进行结冰提供了条件。 控制器控制液体控制器和气体控制器的操作。

公开(公告)号：KR1020030076839A

公开(公告)日：2003-09-29

申请号：KR1020020015541

申请日：2002-03-22

Applicant: 한국항공우주연구원

Inventor： 양인영 ,  전용민 ,  김춘택 ,  양수석 ,  이대성

IPC: F02C9/28

Abstract: PURPOSE: A predicting method of a steady performance of a gas turbine engine is provided to reduce the test time. CONSTITUTION: The transient effect of an engine is quantificated mathematically. The change of the fuel consumption is predicted thereby. The test data of a transient status is compensated to the test data of a steady status. Thereby, the test time, the energy consumption, the waste of manpower, the development time of the engine are reduced and the life of the developed engine is extended.

Abstract translation: 目的：提供燃气轮机发动机稳定性能的预测方法，以减少测试时间。 构成：发动机的瞬态效应在数学上被量化。 从而预测燃料消耗的变化。 瞬态状态的测试数据被补偿到稳定状态的测试数据。 因此，测试时间，能源消耗，人力浪费，发动机开发时间减少，发动机发动机寿命延长。

公开(公告)号：KR1020030074001A

公开(公告)日：2003-09-19

申请号：KR1020020014205

申请日：2002-03-15

Applicant: 한국항공우주연구원

Inventor： 전용민 ,  양인영 ,  김춘택 ,  남삼식 ,  양수석 ,  이대성

IPC: F16B35/06

CPC classification number: F16B35/06

Abstract: PURPOSE: An eye bolt having a semicircular head section is provided to prevent the eye bolt from being broken or damaged due to vertical and horizontal loads applied thereto by forming the semicircular head section at an upper portion of the eye bolt. CONSTITUTION: An eye bolt(1) includes a semicircular head section(2) having a semicircular space section(3) therein. A lower planar head section(4) is formed at a lower portion of the semicircular head section(2) so as to horizontally make contact with an object. A screw section(5) is protruded from the lower planar head section(4). The lower planar head section(4) has a length longer than a diameter of the screw section(5) more than three times. At least one screw hole is formed in the object so as to receive the screw section(5) therein.

Abstract translation: 目的：提供具有半圆形头部的眼睛螺栓，以通过在眼螺栓的上部形成半圆形头部来防止眼螺栓由于施加于其上的垂直和水平负载而破损或损坏。 构成：眼睛螺栓（1）包括在其中具有半圆形空间部分（3）的半圆形头部（2）。 下平面头部（4）形成在半圆头部（2）的下部，从而水平地与物体接触。 螺钉部（5）从下平面头部（4）突出。 下平面头部部分（4）的长度大于螺杆部分（5）的直径大于三倍。 在物体中形成至少一个螺纹孔，以便在其中容纳螺钉部分（5）。

公开(公告)号：KR1020120062300A

公开(公告)日：2012-06-14

申请号：KR1020100123506

申请日：2010-12-06

Applicant: 한국항공우주연구원

Inventor： 전용민 ,  안이기

IPC: G01M15/14 ,  G01M15/02

Abstract: PURPOSE: A cooling device and cooling tube are provided to consecutively cool fuel through heat transmission with air of low temperatures because a cooling tube for cooling the fuel is exposed to the air of low temperature cooled in advance. CONSTITUTION: A cooling device for a high altitude test of a gas turbine engine comprises an air guiding unit(110), a fuel cooling unit(120), a fuel supply unit(121), spay unit(130), and a fuel discharging unit(122). The air guiding unit guides air of low temperatures. The fuel cooling unit is installed in an air flow path of the air guiding unit, thereby cooling fuel by heat transmission with the air of low temperatures. The fuel supply unit supplies the fuel to the fuel cooling unit. The spray unit connected to one end part of the fuel supply unit and fuel cooling unit sprays the fuel to the fuel cooling unit. The fuel discharging unit discharges the cooled fuel.

Abstract translation: 目的：提供一种冷却装置和冷却管，用于通过与低温空气的传热连续冷却燃料，因为用于冷却燃料的冷却管暴露于预先冷却的低温空气。 构成：用于燃气涡轮发动机的高空试验的冷却装置包括空气引导单元（110），燃料冷却单元（120），燃料供应单元（121），喷射单元（130）和排出燃料 单元（122）。 引导单元引导低温空气。 燃料冷却单元安装在空气引导单元的空气流动路径中，从而通过与低温空气的热传递来冷却燃料。 燃料供应单元将燃料供应到燃料冷却单元。 连接到燃料供应单元的一个端部的喷射单元和燃料冷却单元将燃料喷射到燃料冷却单元。 燃料排放单元排出冷却的燃料。

公开(公告)号：KR1020070066528A

公开(公告)日：2007-06-27

申请号：KR1020050127814

申请日：2005-12-22

Applicant: 한국항공우주연구원

Inventor： 전용민 ,  김춘택 ,  이진근 ,  양수석 ,  이대성

IPC: G01M15/02 ,  G01M15/00

Abstract: A nozzle opening device for an engine test is provided to instantaneously open an air supply nozzle while maintaining the sealing state of the air supply nozzle in a restricted space. A nozzle opening device for an engine test includes a frame(110), a nozzle cover(120), a fixing cylinder, a catching member(130), and a cover support bar(140). The frame is located on the upper and lower sides of the nozzle. The nozzle cover is provided on the outlet side of the nozzle to regulate the opening/closing operation of the outlet. The fixing cylinder is formed in the frame on the upper side of the nozzle. The catching member is hinge-coupled to one end of the fixing cylinder. The catching member regulates the opening/closing operation of the nozzle cover by selectively supporting one side of the nozzle cover. One end of the cover is engaged with a portion of the nozzle cover and the other end thereof is hinge-coupled to a portion of the frame.

Abstract translation: 提供用于发动机试验的喷嘴打开装置，以便在保持空气供应喷嘴的密封状态在受限空间的同时瞬时打开供气喷嘴。 用于发动机试验的喷嘴打开装置包括框架（110），喷嘴盖（120），固定筒，捕获构件（130）和盖支撑杆（140）。 框架位于喷嘴的上侧和下侧。 喷嘴盖设置在喷嘴的出口侧，以调节出口的打开/关闭操作。 固定筒形成在喷嘴上侧的框架中。 捕捉构件铰接于固定筒的一端。 捕捉构件通过选择性地支撑喷嘴盖的一侧来调节喷嘴盖的打开/关闭操作。 盖的一端与喷嘴盖的一部分接合，并且其另一端铰链连接到框架的一部分。