• Title/Summary/Keyword: engine facility

Search Result 263, Processing Time 0.028 seconds

Improving the Measurement Uncertainty of Altitude Test Facility for Gas Turbine Engines (가스터빈엔진 고공성능시험설비의 측정불확도 개선)

  • Lee, Dae-Sung;Yang, In-Young;Jun, Yong-Min;Kim, Chun-Taek;Yang, Soo-Seok
    • Transactions of the Korean Society of Mechanical Engineers B
    • /
    • v.26 no.11
    • /
    • pp.1496-1502
    • /
    • 2002
  • An Altitude Engine Test Facility(AETF) was built at the Korea Aerospace Research Institute in October 1999 and has been being operated for altitude testing of gas turbine engines of 3,000 Ibf class or less. The AETF has been calibrated using several engines such as J69 of Teledyne Co. as a facility checkout engine. Uncertainty analyses on the air flow rate and thrust were performed using the test results, according to ASME PTC 19.1-1998. Several modifications on the facility and test method were made in order to improve the measurement uncertainty to a satisfactory level over the whole operating envelop. Spatial distributions of pressure and temperature were measured, sensors were substituted by more accurate ones, inlet duct was modified to refine the flow quality, and pressure control logic was revised to remove the cell pressure fluctuation. As a result, the uncertainty of the air flow measurement was improved by 0.1% over all the test conditions, and the net thrust measurement by up to 3%. The improved measurement uncertainties of air flow and thrust are 0.68~O.73% and 0.4~1.3%, respectively.

Ground Firing Test Facility of Hybrid Rocket Engine (하이브리드로켓엔진 지상연소시험 설비)

  • Kim, Soo-Jong;Kim, Gi-Hun;Cho, Jung-Tae;Cho, Min-Kyoung;Do, Gyu-Sung;So, Jung-Soo;Heo, Jun-Young;Lee, Jung-Pyo;Park, Su-Hayng;Moon, Hee-Jang;Sung, Hong-Gye;Kim, Jin-Kon
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2008.11a
    • /
    • pp.251-254
    • /
    • 2008
  • Ground firing test facility and test field for firing test of hybrid rocket engine were constructed. Ground firing test facility were composed of hybrid rocket engine, thrust stand, oxidizer storage/supply system, control system and data acquisition system. Firing tests of thrust 50 kgf class were conducted. Stable performance data was obtained and operational reliability of ground firing test facility were found.

  • PDF

Internal Flow Aerodynamic Test of a Mach 5 Scramjet Engine (마하 5 스크램젯 엔진의 내부 유동 공력 시험)

  • Yang, In-Young;Lee, Yang-Ji;Kim, Young-Moon;Lee, Kyung-Jae;Kang, Sang-Hoon;Yang, Soo-Seok
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2011.11a
    • /
    • pp.584-587
    • /
    • 2011
  • An internal flow aerodynamic test was performed for a Mach 5 scramjet engine. The test was done without fuel injection, as a preliminary test for the combustion test. Test engine is an engineering model with intake cross-section of $70mm{\times}200mm$ and total length of 1.7m. Test facility is a blowdown-type, high enthalpy, hypersonic facility. 19 pressures were measured through the holes on the model surface along the engine internal flow passage. It was found that the facility start is possible, and also supersonic flow is maintained inside the engine.

  • PDF

An Analysis on Plume Behaviour of Rocket Engine with Ground Condition at High Altitude Engine Test Facility (고공시험설비에서 로켓엔진의 지상시험 플룸 거동 해석)

  • Kim, Seong-Lyong;Lee, SeungJae;Han, YoungMin
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2017.05a
    • /
    • pp.112-115
    • /
    • 2017
  • We analyzed the rocket engine flow to check whether the possibility of the ground test and the equipment safety problems in the high altitude engine test facility. The test condition is that the vacuum chamber is open and the coolant water is injected into the supersonic diffuser. The analysis uses two-dimensional axisymmetry with a mixture of plume, air, and cooling water. As a result, the ground test was possible up to the cooling water flow rate of 200 kg/sec. However, due to the back flow of the initial plume, the vacuum chamber is exposed to high temperature, and at the same time, the inside of the vacuum chamber is contaminated due to the reverse flow of the cooling water. Therefore, sufficient insulation measures and work for pollution avoidance should be preceded.

  • PDF

Methane Engine Combustion Test Facility Construction and Preliminary Tests (메탄엔진 연소시험설비 구축 및 예비 시험들)

  • Kang, Cheolwoong;Hwang, Donghyun;Ahn, Jonghyeon;Lee, Junseo;Lee, Dain;Ahn, Kyubok
    • Journal of the Korean Society of Propulsion Engineers
    • /
    • v.25 no.3
    • /
    • pp.89-100
    • /
    • 2021
  • This paper deals with the construction of a combustion test facility and preliminary tests for hot-firing tests of a methane engine. First, the combustion test facility for a 1 kN-class thrust chamber using liquid oxygen/gas methane as propellants was designed and built. Before hot-firing tests, the cold-flow tests of each propellant line and the ignition tests of torch igniter/afterburner were performed to verify propellant supply stability of the combustion test facility, operation of the control and measurement system, and successful ignition. Finally, a preliminary hot-firing test was conducted to measure the combustion efficiency, heat flux, and combustion stability of a thrust chamber prototype. The constructed combustion test facility will be helpfully used for basic research and development of methane engine thrust chambers.

Construction and Start-up Test of Hot-firing Test Facility for KSLV-II Combustion Chamber (한국형발사체 연소기 연소시험설비의 구축 및 시운전)

  • Lee, Kwang-Jin;Yi, Seung Jae;Seo, Daeban;Hwang, Chang Hwan;Woo, Seongphil;Im, Ji-Hyuk;Jeon, Junsu;So, Younseok;Kim, Chae-Hyoung;Kim, Sunghyuk;Kim, Seung-Han;Cho, Namkyung;Han, Yeoung Min
    • Journal of the Korean Society of Propulsion Engineers
    • /
    • v.20 no.1
    • /
    • pp.69-75
    • /
    • 2016
  • This paper covers the result of construction and start-up tests of the KSLV(Korea Space Launch Vehicle)-II combustion chamber hot-firing test facility. This facility was constructed from 2012 to 2014. Start-up test of this facility began in the second half of 2014. Oxidizer cold flow test, fuel cold flow test and cooling water cold flow test were carried out as start-up test. Afterward, ignition test of combustion chamber was accomplished. The result of ignition test is applied to set up start-up sequence of KSLV-II combustion chamber and utilized as base line data for hot-firing test of low and normal design point.

Study on the Humidity Effect on Gas turbine Engine Performances (습도가 엔진성능에 미치는 영향에 대한 실험적 고찰)

  • Lee, Bo-Hwa;Lee, Kyung-Jae;Yang, Soo-Seok;Kim, Chun-Taek
    • Aerospace Engineering and Technology
    • /
    • v.9 no.2
    • /
    • pp.98-104
    • /
    • 2010
  • The moisture in the atmosphere exerts a lot of influence upon Gas turbine engine performances. There is a noticeable influence of wet air at the summer sea level, high flight mach number and low engine rpm increasingly. An altitude Engine Test Facility is used to accomplish the engine performance tests at dry air condition and wet air condition, through which engine performance results is revealed. Also, Gas turbine Simulation Program is used to predict the variation of engine performance due to inlet humidity. In the result, net thrust and specific fuel consumption measured -2.826% and 1.325%, respectively at wet air condition compared to dry air condition.

The introduction of Engine Performance Test for Miniature Turbojet Engine considering humidity effects (습도 영향을 고려한 초소형 터보제트 엔진 성능시험 소개)

  • Lee, Bo-Hwa;Lee, Kyung-Jae;Yang, Soo-Seok;Kim, Yu-Il
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2010.11a
    • /
    • pp.335-338
    • /
    • 2010
  • The moisture in the atmosphere exerts a lot of influence upon Gas turbine engine performances. There is a noticeable influence of wet air at the summer sea level, high flight mach number and low engine rpm increasingly. An altitude Engine Test Facility is used to accomplish the engine performance tests at dry air condition and wet air condition, through which engine performance results is revealed. In the result, net thrust and specific fuel consumption measured -2.826% and 1.325%, respectively at wet air condition compared to dry air condition.

  • PDF

Development of a Hydrogen Peroxide Rocket Engine Facility

  • Ahn, Sang-Hee;S. Krishnan;Lee, Choong-Won
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2004.03a
    • /
    • pp.131-136
    • /
    • 2004
  • The ongoing developmental studies on the application of hydrogen peroxide for propulsion are briefly reviewed. A detailed design-study of a laboratory scale facility of a hydrogen peroxide mono-propellant engine of 100-N thrust is presented. For the preparation of concentrated hydrogen peroxide, a distillation facility has been realized. Results of water analogy tests are presented. Initial firings using the concentrated hydrogen peroxide were not successful. Low environmental temperature, low contact area of the catalyst pack, and contamination in the hydrogen peroxide were considered to be the reasons. Addressing the first two points resulted in successful firing of the rocket engine.

  • PDF

Aircraft Engine Performance Test Technologies by 150K lbf Thrust Test Cell (15만 파운드급 테스트 셀을 이용한 엔진성능 시험기술)

  • Kim, Woocheol;Kim, Chul;Kim, Sangbaek
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2017.05a
    • /
    • pp.180-187
    • /
    • 2017
  • Major design targets such as test cell type, cell flow, cell bypass ratio, approach velocity, cell depression, front cell distortion, noise level and vibration level to construct a new 150,000 lbf thrust aircraft engine test facility were established. Based on the final aerodynamic and acoustic performance tests conducted at the newly constructed test facility, it was found that the new test facility is judged to be excellent and meets design targets.

  • PDF