Experimental Studies on Methane-Fuel Laboratory Scale Ram CombustorSource: Journal of Engineering for Gas Turbines and Power:;1995:;volume( 117 ):;issue: 003::page 394DOI: 10.1115/1.2814108Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: The laboratory scale ram combustor test program has been investigating fundamental combustion characteristics of a ram combustor, which operates from Mach 2.5 to 5 for the super/hypersonic transport propulsion system. In our previous study, combustion efficiency had been found poor, less than 70 percent, due to a low inlet air temperature and a high velocity at Mach 3 condition. To improve the low combustion efficiency, a fuel zoning combustion concept was investigated by using a subscale combustor model first. Combustion efficiency more than 90 percent was achieved and the concept was found very effective. Then a laboratory scale ram combustor was fabricated and combustion tests were carried out mainly at the simulated condition of Mach 5. A vitiation technique was used to simulate a high temperature of 1263 K. The test results indicate that ignition, flame stability, and combustion efficiency were not significant, but the NOx emissions are a critical problem for the ram combustor at Mach 5 condition.
keyword(s): Fuels , Combustion chambers , Methane , Combustion , Emissions , High temperature , Stability , Temperature , Propulsion systems , Flames AND Ignition ,
|
Show full item record
contributor author | Y. Kinoshita | |
contributor author | A. Tatara | |
contributor author | J. Kitajima | |
contributor author | Y. Seki | |
date accessioned | 2017-05-08T23:47:06Z | |
date available | 2017-05-08T23:47:06Z | |
date copyright | July, 1995 | |
date issued | 1995 | |
identifier issn | 1528-8919 | |
identifier other | JETPEZ-26741#394_1.pdf | |
identifier uri | http://yetl.yabesh.ir/yetl/handle/yetl/115268 | |
description abstract | The laboratory scale ram combustor test program has been investigating fundamental combustion characteristics of a ram combustor, which operates from Mach 2.5 to 5 for the super/hypersonic transport propulsion system. In our previous study, combustion efficiency had been found poor, less than 70 percent, due to a low inlet air temperature and a high velocity at Mach 3 condition. To improve the low combustion efficiency, a fuel zoning combustion concept was investigated by using a subscale combustor model first. Combustion efficiency more than 90 percent was achieved and the concept was found very effective. Then a laboratory scale ram combustor was fabricated and combustion tests were carried out mainly at the simulated condition of Mach 5. A vitiation technique was used to simulate a high temperature of 1263 K. The test results indicate that ignition, flame stability, and combustion efficiency were not significant, but the NOx emissions are a critical problem for the ram combustor at Mach 5 condition. | |
publisher | The American Society of Mechanical Engineers (ASME) | |
title | Experimental Studies on Methane-Fuel Laboratory Scale Ram Combustor | |
type | Journal Paper | |
journal volume | 117 | |
journal issue | 3 | |
journal title | Journal of Engineering for Gas Turbines and Power | |
identifier doi | 10.1115/1.2814108 | |
journal fristpage | 394 | |
journal lastpage | 400 | |
identifier eissn | 0742-4795 | |
keywords | Fuels | |
keywords | Combustion chambers | |
keywords | Methane | |
keywords | Combustion | |
keywords | Emissions | |
keywords | High temperature | |
keywords | Stability | |
keywords | Temperature | |
keywords | Propulsion systems | |
keywords | Flames AND Ignition | |
tree | Journal of Engineering for Gas Turbines and Power:;1995:;volume( 117 ):;issue: 003 | |
contenttype | Fulltext |