Imaging of laser-induced fluorescence in a high-pressure combustor

Abstract

Recently, we have completed the development of anThe ability to obtain quantitative planar laser-incorporates a production fuel injector and is capable of induced fluorescence (PLIF) measurements in a high-operating at pressures up to 50 atm with preheated air. pressure combustor would represent a significant This facility allows laser-based imaging techniques to be advance in the application of laser diagnostics to prac-performed at conditions that are representative of gastical combustion systems. To simulate the combustion turbine combustors. environment of a gas-turbine engine, an opticallyaccessible high-pressure combustor has been con-Planar laser-induced fluorescence (PLIF) is a widely structed. The combustor facility incorporates a pro-used diagnostic technique capable of providing instanduction liquid-fuel injector and a preheated air supply.taneous two-dimensional measurements in flames. In this paper, we demonstrate the feasibility of instan-However, the application of PLIF techniques to practical taneous OH PLIF measurements in spray flames of combustion devices operated at high pressure remains a heptane and Jet-A fuel at pressures up to 20 atm. Obser-challenge. Examples of such applications include PLIF vations of OH PLIF images at a range of pressures and imaging of fuel concentration in a flame-tube and a overall equivalence ratios are presented.spark-ignition engine. PLIF measurements of OH and

Simultaneous imaging of fuel, OH, and three component velocity fields in high pressure, liquid fueled, swirl stabilized flames at 5 kHz

“…The PAH levels increased with pressure, similar to soot production, as also noted in other studies [20,21]. Frank et al [22] presented 10 Hz OH fields at varying global fuel/air ratios and pressures up to 20 bar with liquid fuel. Locke et al performed 10 Hz OH-PLIF in a swirl-stabilized fuel tube combustor with JP-8 spray at pressures up to 18 bar [23,24].…”

Preliminary design of an optically accessible high-pressure combustor

“…Pressure drop is controlled using a variable are flow restrictor in the exit nozzle. Frank et al 6 The combustor has the capability of operating at pressures up to 5 MPa with a maximum flow rate of 0.4 kg/s…”

The Brief Introduction of Different Laser Diagnostics Methods Used in Aeroengine Combustion Research

“…In 1990, McMillin et al used PLIF technology to measure the structure of shock by heat flow imaging of NO in shock tube [8]. In 1999, Frank et al get the imagines of OH in the aeroengine combustor chamber under different pressure (maximum test pressure is 2026.5 kPa) by using PLIF technology [9]. In 2002, Hanson used PLIF technology to study the supersonic combustion [10].…”