ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities最新文献_第5页

Techniques for using pressure-sensitive paint in shock tunnel facilities 在激波隧道设施中使用压敏涂料的技术

ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities Pub Date : 1997-09-29 DOI: 10.1109/ICIASF.1997.644650

J. Hubner, B. Carroll, K. Schanze, Hia Feng Ji

引用次数: 3

Methods and instrumentation for the investigation of nonstationary processes in liquid-propellant rocket engines 液体推进剂火箭发动机非平稳过程研究的方法和仪器

ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities Pub Date : 1997-09-29 DOI: 10.1109/ICIASF.1997.644762

Alexey Karpov

{"title":"Methods and instrumentation for the investigation of nonstationary processes in liquid-propellant rocket engines","authors":"Alexey Karpov","doi":"10.1109/ICIASF.1997.644762","DOIUrl":"https://doi.org/10.1109/ICIASF.1997.644762","url":null,"abstract":"At the nonstationary regimes of the liquid rocket engine operation essential fraction of the pulse duration relate to the transitional (preflame and postflame) processes which accompany the engine switching-on and switching-off. Some diagnostics methods and instrumentation have been developed for investigation of the processes in the combustion chambers, nozzles and jets of the spacecraft engines under nonstationary conditions. On the basis of experimentally obtained spatial, spectral and time characteristics of jet self-radiation in the visible and infrared spectral areas, the nonequilibrium degree of flow in the nozzle, the parameters distribution over a cross section, sizes and concentration of the carbon particles have been evaluated. Sizes, concentration and phase status of the propellant particles were determined by scattering characteristics of the laser light passing through the medium under test. A film thermometry was used for investigation of the engine thermal status at pulse modes of operation and for determination of heat fluxes on the surface of the chamber elements.","PeriodicalId":122871,"journal":{"name":"ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities","volume":"140 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1997-09-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134139980","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Experimental setup, measurement and analysis of the onset of compressor flow instabilities in an aeroengine 某型航空发动机压气机流动失稳起始的实验设置、测量与分析

ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities Pub Date : 1997-09-29 DOI: 10.1109/ICIASF.1997.644672

B. Hoss, L. Fottner

{"title":"Experimental setup, measurement and analysis of the onset of compressor flow instabilities in an aeroengine","authors":"B. Hoss, L. Fottner","doi":"10.1109/ICIASF.1997.644672","DOIUrl":"https://doi.org/10.1109/ICIASF.1997.644672","url":null,"abstract":"In the past decade great efforts have been undertaken to understand and control the flow structure in a compressor working close to its stability limit. Most of this research work was done at low-speed compressors in isolated test rig facilities. This paper presents the experimental setup, measurement and different analysing techniques of highly unsteady pressure signals during the onset process of compressor flow instabilities in the two-spool bypass aeroengine LARZAC 04 at various power settings. Several analysing techniques such as temporal low-pass and band-pass filtering, temporal and spatial Fourier transform and a wavelet analysing technique are applied. While filtering and the Fourier spectrum gives a good insight into the physical background of the stall inception process-but with very little warning time-the wavelet frequency spectrum indicates the approach of the stalling process a few hundred rotor revolutions (corresponding to 1-2 seconds in time) in advance independently of the type of precursor. Depending on the rotor speed three different types of stall inception processes were observed within the low pressure compressor. While a low-speed stall originates from spike-type precursors, long wavy pressure fluctuations corresponding to modal waves were observed prior to stall at mid-speed. At high-speed the rotor shaft unbalancing dominates the stall inception process as an external forcing function.","PeriodicalId":122871,"journal":{"name":"ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities","volume":"40 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1997-09-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114823478","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 7

Correcting luminescent paint measurements for self-illumination 校正自发光的发光涂料测量

ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities Pub Date : 1997-09-29 DOI: 10.1109/ICIASF.1997.644640

W. Ruyten

引用次数: 5

Visualization of the quiet test region in a supersonic wind tunnel using luminescent paint 利用发光涂料实现超音速风洞安静测试区的可视化

ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities Pub Date : 1997-09-29 DOI: 10.1109/ICIASF.1997.644667

K. Asai, T. Kunimasu, Y. Iijima

{"title":"Visualization of the quiet test region in a supersonic wind tunnel using luminescent paint","authors":"K. Asai, T. Kunimasu, Y. Iijima","doi":"10.1109/ICIASF.1997.644667","DOIUrl":"https://doi.org/10.1109/ICIASF.1997.644667","url":null,"abstract":"A temperature-sensitive luminescent paint technique has been used to visualize boundary-layer transition on a 10-degree cone model in the 0.2-m Supersonic Wind Tunnel at National Aerospace Laboratory. A luminescent paint based on EuTTA was applied on the model surface using airbrush. The paint coating was excited by a Xenon light and the luminescence image was acquired using a high resolution cooled-CCD camera. To enhance thermal signature across transition, tunnel flow was heated by a sudden shutdown of cooling water supply to heat exchanger. Two images were taken for each condition, one is transient image taken in heating process and the other is reference image taken in steady condition. By ratioing these two images, global transition patterns on the cone have been visualized as the edges of brightness. From transition images at various model locations in the test section, it was found that transition remains at a fixed spatial location with respect to the tunnel. This indicates that the cone transition is induced by radiated noise propagating from turbulent boundary layers on the tunnel walls. Effects of the stagnation pressure were also studied over the range from 55 to 150 kPa. The extent of quiet test region was found to be strongly sensitive to the pressure or unit Reynolds number. At the NAL 0.2-m SWT, natural transition did not occur on the cone at lower values of unit Reynolds number.","PeriodicalId":122871,"journal":{"name":"ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities","volume":"85 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1997-09-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123027216","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 5

Back step flow measurements using triple split film probe 用三分膜探头测量后台阶流量

ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities Pub Date : 1997-09-29 DOI: 10.1109/ICIASF.1997.644683

N. Alemdaroglu, O. Karatekin

引用次数: 1

Developing a stress wave thrust balance for a hypersonic shock tunnel 高超声速激波隧道应力波推力平衡的研究

ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities Pub Date : 1900-01-01 DOI: 10.1109/ICIASF.1997.644754

S. Tuttle, J. Simmons, D. Mee

引用次数: 1