PULSE DETONATION AS AN OPTION FOR FUTURE INNOVATIVE GAS TURBINE COMBUSTION TECHNOLOGIES: A CONCEPT ASSESSMENT

Övrigt konferensbidrag, 2010

A study on innovative combustion system for future aeroengine core concepts is done in the frame of the NEWAC project (EU FP6, AIP5-CT-2006-030876). A part of the high pressure core is replaced by a pulse detonation combustor. The ambition is to achieve a technical leap in TSFC reduction, or alternatively a lighter engine. In order to provide technical assessments on both the feasibility and performance of such a concept, specific tools were developed at TU Graz, Austria and Chalmers University, Sweden. The study emphasises the impact of flow intermittency on the direct environment of the pulse detonation combustor, and on the performance of a hybrid turbofan. A literature survey establishes the state of the art on pulse detonation technologies. Numerical tools for CFD calculation and performance analysis are presented. A concept assessment with a TSFC reduction by 5% in comparison to a conventional cycle is derived. 1 General Introduction The need for more efficient and environment friendly engines is tending towards new methods of combustion. Although new injections systems currently in development, like LPP (Lean Premixed Prevaporised), RQL (Rich burn Quick quench Lean burn) and LDI (Lean Direct Injection), are promising a reduction in pollutant emission there is also the trend to look for innovative combustion methods to lower in addition fuel consumption. One premising way to reduce thrust specific fuel consumption (TSFC) is to use pulse detonation [6]. A study on innovative combustion system for future aeroengine core concepts is done in the frame of the NEWAC project. A part of the high pressure core of a conventional aeroengine is replaced by a pulse detonation combustor. A medium-range two-spool turbofan is taken as a baseline for a back-to-back comparison. Pulse detonation (PD) is attractive because of its potential for higher thermal efficiency.