Swirl trapped vortex type combustion chamber of micro-turbine engine

Abstract

The present invention solves the technical problem that a swirl trapped vortex type combustion chamber of micro-turbine engine is provided. A main combustion region of the head of the flame tube adopts the form of a trapped vortex, which is a protruding structure, and the position and size of the jet holes are reasonably arranged. In addition, a radial swirler is disposed on the inner and outer walls of the micro-combustor flame tube. The airflow action of the jet holes is stable between blades of the radial swirler and has a certain strength axial backflow region, so that the residence time of the head airflow in the head region of the flame barrel is increased, and the combustion time of the fuel oil in the head region is increased. Besides, in addition to the axial backflow region generated by the jet holes, the radial swirler generates a circumferential backflow region in the head region, so that heat and mass exchange of each axial backflow interval can be carried out, and the ignition reliability and stability of the combustion chamber are improved. The high-temperature region of the combustion chamber is close to the head region, the temperature distribution uniformity of the outlet of the combustion chamber is good, and the overall combustion chamber performance of the combustion chamber is greatly improved.

Description

technical field [0001] The invention belongs to the field of micro gas turbine engine combustors, in particular to a swirl vortex micro gas turbine engine combustor. Background technique [0002] In recent years, micro-power systems have become a research hotspot at home and abroad, and micro-engines have become one of the most promising power devices because of their advantages such as small size, light weight, large output energy, and high density. The United States is the first country in the world to carry out research on small and micro turbine engine technology, and it is also the country with the most types and the most advanced technologies. In 1960, Williams International Corporation of the United States developed the world's first miniature turbojet engine WR2-1 with a thrust of 265N. Outside of the United States, Japan is also developing a micro-turbine engine with a power of 100W; China Taiwan, Nanjing University of Aeronautics and Astronautics, Beijing Universi...

AI Technical Summary

Problems solved by technology

Due to the small geometric size of the combustion chamber, the residence time of the airflow in the combustion chamber is shortened, which reduces the combustion performance of the combustion chamber, and the gas has already flowed out of the combustion chamber when the fuel cannot be fully combusted.

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