In Institute of Aviation from 2010 is realized a project POIG 2007-2014 "Turbine engine with detonation chamber." The main target is to develop a turbine engine using a rotating detonation effect in the process of combustion the fuel. This article presents the most important stages leading to achieve the goals. As a facility test, we have chosen a turbo shaft engine GTD-350 characterized by the location of combustion chamber, which is outside the engine. This feature has helped in modernization the combustion chamber to adjust it to the detonation combustion. Works over the project has been started from the attempts to obtain a rotating detonation in the combustion chamber with a diameter of 500 mm powered by hydrogen. These researches have allowed the team to master the method of detonation initiation and methods for identifying the process of spinning detonation. In the same time works over the kerosene injection on the visualization bench has been begun. On this bench, we have mainly evaluated the extent and location of the fuel stream and the quality of the spray. Simultaneously the program to simulate the injection and the process of spinning detonation in actual geometries of different combustion chambers has been created. The process of initiation the detonation is discussed in the article on the example of detonator using ammo tutorial. Researches about combustion detonation with simultaneously reinforcement the combustion chamber with hydrogen and liquid fuel JET-A1 has also been discussed in this article. Presented research results includes pressure fuel waveforms in supply manifold along with the measurements of combustion pressure correlated with Air-Fuel Equivalence Ratio-lambda. Currently we are working over the integration of the combustion chamber of the engine GTD-350.
This article contains a description of the work carried out under the UDA-POIG 01.03.01-14-071/09-10 project titled "A turbine engine with a detonation chamber". The work carried out during the project involved 14 construction, research and calculation tasks. Various research stands designed to analyse the process of mixture formation, initiation of detonation and research of rotating detonation in combustion chambers were constructed. Test stand for examining a turboshaft engine with detonation combustion chamber was built. Those test stands allowed powering the combustion chambers and the engine with both liquid and gaseous fuels, simultaneously or separately. At the same time, REFLOPS software, which could calculate the propagation of a detonation wave was created, and used in the design of further versions of combustion chambers. Data from the experiments was used to verify the calculations and models created in the mentioned software. GTD-350 engine was used as the base; the structure of which (combustion chamber situated outside the turbine-compressor unit) facilitated modifying the shape of the detonation combustion chamber. During the research, great emphasis was placed on the safety of researchers. Working with hydrogen in high temperatures and JET-A1 fuel, which was additionally heated, and the usage of the oxy-acetylene detonators forced extreme caution, and full compliance with developed procedures. The project was divided into 14 tasks that were often conducted simultaneously in a 20-person team implementing the project. The work was completed by performing comparative studies between conventional engine with deflagration combustion chamber, and modified engine with a detonation combustion chamber. During the completion of the project, it was the first working demonstrator engine with detonation combustion chamber in the world.
This article examines, based on the available information and authors’ self-assessments, the environmental impact of turbine engine exhaust gases effect on the environment in the airport space during engines flight phases in the landing and takeoff cycle (LTO). The attention of aviation professionals is drawn to the fact that the amount of exhaust from the turbine engine is so significant that it may adversely change the ambient air at the airport. Consequently, increased emission level of carbon monoxide (CO), hydrocarbons (HC) during engine start-up and idle may pose a threat to the health of ramp staff. Also, high emission levels of nitrogen oxides (NOx) during takeoff, climb, cruise and descent is not without importance for the environment around the airport space. The paper gives CO2, HC, CO and NOx emission estimations based on ICAO Engine Emission Data Bank and the number of passenger operations at a medium-sized airport. It also provides calculation results of aircraft CO2, HC, CO and NOx emission using average times of aircraft maneuvers taken from aircraft Flight Data Recorder (FDR) in the LTO cycle various aircraft types at the airport. The latter, based on actual maneuvering times, lead to significantly reduced estimates of toxic exhaust gas emission volumes.
scite is a Brooklyn-based organization that helps researchers better discover and understand research articles through Smart Citations–citations that display the context of the citation and describe whether the article provides supporting or contrasting evidence. scite is used by students and researchers from around the world and is funded in part by the National Science Foundation and the National Institute on Drug Abuse of the National Institutes of Health.
hi@scite.ai
10624 S. Eastern Ave., Ste. A-614
Henderson, NV 89052, USA
Copyright © 2024 scite LLC. All rights reserved.
Made with 💙 for researchers
Part of the Research Solutions Family.