[논문]Flow Visualization of Flowfield Structures around an Aerospike Nozzle using LIF and PSP

NIIMI, Tomohide; MORI, Hideo; TANIGUCHI, Mashio

[국내논문] Flow Visualization of Flowfield Structures around an Aerospike Nozzle using LIF and PSP 원문보기

NIIMI, Tomohide (Department of Micro-Nano Systems Engineering Nagoya University) , MORI, Hideo (Department of Micro-Nano Systems Engineering Nagoya University) , TANIGUCHI, Mashio (Department of Micro-Nano Systems Engineering Nagoya University)

Aerospike nozzles have been expected to be used for an engine of a reusable space shuttle to respond to growing demand for rocket-launching and its cost reduction. In this study, the flow field structures in any cross sections around clustered linear aerospike nozzles are visualized and analyzed, using laser induced fluorescence (LIF) of nitrogen monoxide seeded in the carrier gas of nitrogen. Since flow field structures are affected mainly by pressure ratio, the clustered linear aerospike nozzle is set inside a vacuum chamber to carry out the experiments in the wide range of pressure ratios from 75 to 200. Flow fields are visualized in several cross-sections, demonstrating the complicated three-dimensional flow field structures. Pressure sensitive paint (PSP) of PtTFPP bound by poly- IBM -co-TFEM is also applied to measurement of the complicated pressure distribution on the spike surface, and to verification of contribution of a truncation plane to the thrust. Finally, to examine the effect of the sidewalls attached to the aerospike nozzle, the flow fields around the nozzle with the sidewalls are compared with those without sidewalls.

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가설 설정

4(b) and it is also found from Fig. 2(b) that the barrel shock waves do not interact behind the base because the jets expand weakly. These mean that no back-flow is generated toward the base, resulting in no pressure increase on the base and no compensation for the thrust loss.
1. The complicated jet structures around the nozzle are clarified by using NO'LIF, such as the interactions of the jets issued from the adjacent nozzle orifices and of the jets from both side of the spike. For the relatively high pressure ratio (Ps/Pa =200), the barrel shock waves originating from the both spike edges interact with each other just behind the base surface, and the pressure on the base increases due to the back-flow from the interacting region, leading to the compensation for the thrust loss.

제안 방법

In this study, NO'LIF (Laser Induced Fluorescence), one of a non-intrusive measurement techniques, is used to visualize and analyze the flow field structures around clustered linear aerospike nozzles at any cross-sections. We also apply PSP (Pressure Sensitive Paint) to measure the complicated pressure distribution on the spike surface.
We also apply PSP (Pressure Sensitive Paint) to measure the complicated pressure distribution on the spike surface. Since the flow field structures are affected mainly by pressure ratios {Ps /Pa, R: the source pressure, & the ambient pressure), we set the nozzle into a vacuum chamber to carry out the experiments in the wide range of pressure ratios.
The linear aerospike nozzle used in this study is designed and developed assuming a two-dimensional flow. However, the undesirable lateral expansion out of the nozzle occurs actually, and it may cause a thrust loss.

대상 데이터

A gas mixture of NO2% + N2 98% expands through rectangular nozzle orifices into the vacuum chamber. A broadband ArF excimer laser (Lambda Physik LPX 105EJ wavelength 193 nm, FWHM 0.5 nm) is used as an excitation source, and the laser beam is focused on the flow field응 by a cylindrical lens (SIGMA Koki; f=400mm, size 30×30mm). The flow fields are imaged onto an image-intensified CCD camera (Hamamatsu C7300-10)with a camera lens (Nikon UV-NIKKOR; F(0.

성능/효과

2. It is clarified that the undesirable lateral expansions of linear aerospike nozzles can be suppressed by applying sidewalls, resulting in the probable increase in the thrust. Moreover, for the relatively high pressure ratio {Ps/Pa = 200), the pressure on the base surface of the nozzle with sidewalls is higher than that without sidewalls, causing the higher additional thrust.
From the results it is clarified that the lateral expansions of linear aerospike nozzles can be suppressed by applying sidewalls, resulting in the probable increase in the thrust. Moreover, the sidewalls also give rise to the higher thrust on the base surface for high pressure ratio, which causes the more effective compensation of the thrust loss caused by truncating the nozzle.

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[국내논문] Flow Visualization of Flowfield Structures around an Aerospike Nozzle using LIF and PSP 원문보기

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[국내논문] Flow Visualization of Flowfield Structures around an Aerospike Nozzle using LIF and PSP 원문보기

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가설 설정

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