The operating range of the flow rate or velocity for micro-jet flame is quite wide, which can be used as heat source. In order to optimize tube combustor in terms solid material, present paper numerically investigates impact thermal conductivity (λs) on limit flame. Unexpectedly, non-monotonic blow-off limits with increase λs found, and corresponding generation mechanisms are analyzed coupling ...

Soot concentration distribution is investigated both numerically and experimentally in methane-air diffusion flame. The experimental work is conducted with a cylindrical swirl stabilized combustor. Filter paper technique is used to measure soot volume fraction inside the combustor. The numerical simulation is based on the solution of the fully-coupled conservation equations for swirling turbule...

The following paper presents an overview of the Prometheus design system and its applications to gas turbine combustor design. Unlike a traditional “optimizer-centric” method, Prometheus aims to reduce both the level of workflow complexity and rework by taking a more “geometry-centric” approach to design optimization by shifting the control of script generation away from the optimization progra...

The length and volume requirements of small gas turbines for missiles or propelled targets lead to combustor designs with high combustion intensity and large value of the air loading parameterA. The conventional combustors have used conditions corresponding toll values in the 1 to 10 kg m -3s 1 range. The increase off?required for combustors in missiles conduces for existing liners to a decreas...

This paper presents analysis of the effect of actuation on combustion dynamics. Two different categories of actuators are examined: flow sources, e.g., acoustic speakers, and heat sources, e.g., fuel injectors. These sources are modeled in the conservation equations and a finite dimensional model is obtained. Two methods of analysis are used to gain insight into the physics of actuation, and it...

A scheme for identifying and visualizing the material properties that limit the performance of candidate materials for actively cooled aerospace propulsion components is presented and illustrated for combustor panels for Mach 7 hypersonic vehicles. The method provides a framework for exploring the nonlinear interactions between design and materials optimization. By probing the active constraint...

The following research paper presents an up-to-date status of the testing of a Dual-Mode Scramjet (DMSJ) model which is experimentally operated at UVa’s Aerospace Research Laboratory. The optical technique Stereoscopic Particle Image Velocimetry (SPIV) is applied to the combustor of the DMSJ with a ramp fuel injector configuration. SPIV is utilized to measure the three-dimensional, combusting, ...

Work to develop a practical, fast diagnostic technique to monitor the proximity of a combustor to blowout using measurements of the flame’s acoustic signature is described. The feasibility of this approach was demonstrated on three combustors with different flame holding mechanisms that are used in most practical combustion devices: pilot, swirl, and bluff-body stabilized flames. Extensive high...

Original scientific paper In the numerical simulation research of gas turbine combustor, there are plenty repetitive operations such as modelling and meshing. Parametric design idea is about simplifying it. This paper establishes a parametric modelling system of gas turbine combustor, mainly for the flame tube components, which includes parametric modelling and simple mesh generation. Taking a ...