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Colorless distributed combustion (CDC) has been shown to provide significant improvement in gas turbine combustor performance.
The latter is related to combustor performance and fire safety issues in reduced gravity environments.
A full-pressure combustion test is planned to prove the combustor performance.
The design model could provide the combustor geometry and the combustor performance.
After conforming the feasibility of the combustor design code, we investigated the effects of steam addition on combustor performance.
Present investigations are focused on the effect of fuel injection scheme on a model scramjet combustor performance.
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As a further analysis, the effect of aging of catalytic coating on the overall combustor performances has been investigated.
The predicted lean flammability limit provides guidelines for the design of the combustor and some indications for further improving the combustor performances.
Distributed combustion has been shown to provide significant improvements of gas turbine combustors performance including uniform thermal field in the entire combustion chamber (improved pattern factor), ultra-low emission of NOx and CO, low noise, enhanced stability and higher efficiency.
In this context, common design tools and standard RANS predictive techniques are often not capable of properly characterizing combustors performances.
Due to the increasing need of minimizing energy loss or pollution of combustors, keeping good performance of combustion control is highly desired.
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Justyna Jupowicz-Kozak
CEO of Professional Science Editing for Scientists @ prosciediting.com