Engineers from Rybinsk State Aviation Technical University (RSATU) named after P. A. Solovyov have developed a vortex ejector burner device, described in patent RU 2 869 465 C9. The design is intended for preparing and burning an air-fuel mixture and can be used in aircraft engines and thermal power plants. It provides for the adjustment of several elements that affect air movement and combustion conditions.

The device is based on a cylindrical ejector sleeve with a movable nozzle part. It can be moved along the axis of the combustion chamber, which, according to the patent, allows for additional changes in the conditions for preparing the air-fuel mixture.

At the outlet of the sleeve, there is an acceleration chamber, which participates in the preparation of the air-fuel mixture and increases the static pressure drop across the ejector sleeve.

Separate adjustment is provided for air swirl. The flame tube has at least two belts of tangential holes connecting the cooling channel with the combustion chamber. Their angle relative to the chamber axis can be changed, and the air supply through these holes should, according to the patent description, prevent the swirl from decaying as it moves.

Another adjustable section is located in the flame stabilizer zone. A stabilizer with adjustment screws and radial belts of holes in the end surface for secondary air supply is installed on the chamber axis.

A coaxial channel is formed between the stabilizer and the wall of the flame tube, and its flow area can also be changed. Thus, the design provides several adjustable elements that allow changing the parameters of the air flow in the combustion zone.

The adjustment of individual elements of the air path is claimed in the patent as a way to achieve a technical result. The document indicates an improvement in the preliminary preparation of the air-fuel mixture, a reduction in NOx nitrogen oxide concentration, an expansion of the stable combustion range by the excess air ratio, prevention of swirl decay, and a reduction in the likelihood of flame front detachment.

For an aircraft engine combustion chamber, the problem is not only to ensure the supply of fuel and air. As the mode changes, the air flow rate, pressure, mixture composition, and nature of the vortex motion change, so the conditions for a stable flame also constantly change.

The patent description specifically states that the adjustable nozzle part can move into the area of maximum rarefaction. According to the authors, this further increases the pressure drop and improves the preliminary preparation of the air-fuel mixture.

The scheme proposed by RSATU provides for the adjustment of several parameters: the position of the nozzle part, the angle of swirling air supply, and the flow area of the coaxial channel. Separate adjustment is provided for the supply of secondary air through the holes of the flame stabilizer.