Evaluation of Laminated Porous Wall Materials for Combustor Liner Cooling

Abstract

Some of the work at Detroit Diesel Allison (DDA) that has been aimed at the synthesis, characterization, and evaluation of a promising porous wall combustor-cooling concept featuring electrochemically etched, multilayer, diffusion-bonded sheet structures (Lamilloy) is briefly reviewed. The specific considerations of cooling effectiveness, design flexibility, fabrication complexity, and special operational and durability problems are considered in light of relevant engine and rig experience.

Full Coverage Discrete Hole Film Cooling: The Influence of the Number of Holes and Pressure Loss

“…The present results for wall D at low G compare very favourably with the Triply Lamilloy results of Nealy and Reider (1979). This was one of the best Lamilloy geometries and yet the present results achieve comparable results at low G without the need for complex internal flow within the wall thickness.…”

“…Transpiration cooling materials do not have the mechanical properties for high temperature gas turbine applications, although Wolf et al (1980) have successfully applied the technique to a high temperature turbine blade application. The materials Lamilloy (Nealy and Reider, 1979) and Transply (Wassel and Banghu, 1980) were developed to have transpiration type characteristics coupled with good high temperature mechanical properties. They were developed mainly to maximise the internal wall cooling, but involve full coverage discrete hole film cooling as well.…”

Elements of Propulsion: Gas Turbines and Rockets

“…Transpiration cooling, using advanced liner construction (e.g., Lamilloy, Ref. 75), can obtain a cooling effectiveness of about 0.8 with 17% cooling air, which can be used to obtain lower average metal temperatures (longer life) or higher gas temperatures (improved performance). As future combustor exit temperature requirements increase, the percentage of combustor air available for cooling decreases and increased cooling effectiveness will be required.…”

Numerical Investigation of Heat Transfer Characteristic on Scalelike Platelet Inner Duct

“…It has the advantages as better heat-proof ability, less cooling air need and higher cooling effectiveness, etc. Currently, Transpire [1][2][3], Lamilloy and Transply [4][5][6] laminated plates take the majority in the study. Transpire is mainly used in the cooling the liquid rocket engine thrust chamber.…”