Introduction to the problem of calculating the parameters of the mixing chamber of an afterburning bypass engine


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Abstract

The article considers the problem of calculation accuracy when using mathematical models of gas-turbine engines of the second level of complexity, using the example of a device for mixing the flows of the core engine and the bypass duct of a gas turbine engine, and suggests methods for solving it. The processes taking place in mixing chambers of air-breather engines are considered to be difficult for mathematical modeling since the exchange of kinetic and thermal energies of the flows characterized by different velocities, pressures, temperatures and chemical composition occurs in them simultaneously. The mixer does not only ensure mixing of flows from different engine ducts, but also acts as a kind of throttle. It regulates the pressure downstream of the fan and, consequently, air consumption in the bypass duct, thus affecting directly the fan characteristics and the distribution of flows over the engine ducts. The paper presents the dependencies of the workflow parameters that allow for more accurate verification of mixer models of the second level of complexity.

About the authors

O. D. Karev

United Engine Corporation

Author for correspondence.
Email: karev-od@uecrus.com
ORCID iD: 0000-0002-8976-1572

Design Engineer

Russian Federation

References

  1. Kudryavtsev A.V., Medvedev V.V. Ramjet engine afterburners and combustion chambers. Engineering practices of performance calculation. Trudy TsIAM. 2013. No. 1352. 137 p. (In Russ.)
  2. Kurzke J., Halliwell I. Propulsion and power: an exploration of gas turbine performance modeling. Cham, Switzerland: Springer International Publishing, 2018. 755 p. doi: 10.1007/978-3-319-75979-1
  3. Medvedev V.V. The principle of lobe number estimating and lobe mixer ducts profiling for bypass aviation engines. Scientific Bulletin of the Moscow State Technical University of Civil Aviation. 2005. No. 85. P. 7-12. (In Russ.)

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