Low-pressure nozzle with aerodynamic fuel atomization

A research was carried out with the construction of a model of a low-pressure nozzle with aerodynamic fuel atomization, which shows the advantages of nozzles of this type. In order to reduce the time at the stage of development and calculations, modern computer design systems were used. The research was carried out in the Flow Simulation module of the SolidWorks software package, which allows you to calculate and build a model of the internal flow around the nozzle using already known parameters. These parameters were set through the program conditions panel: fuel consumption per second; air flow rate at the inlet to the nozzle; static pressure in the combustion chamber. The calculations performed by the module made it possible to evaluate the manufacturability of the design, as well as the internal processes of mixing fuel with air. To determine the quality of fine dispersion of the fuel atomization, a model of the velocity field was calculated over the entire section of the nozzle, from which it can be seen that the maximum flow rate of the fuel is achieved in the outlet channels of the fuel atomizer of the nozzle. The results obtained indicate the operation of the low-pressure principle while maintaining high-quality fuel atomization. The use of low-pressure nozzle with aerodynamic fuel atomization is possible in modern gas turbine engines of civil aircraft, as well as in gas turbine.

engine, nozzle, fine dispersion, low pressure, velocity field, fuel mixing, manifold, flow rate, emission

1. Lefebvre A.H. Gas Turbine Combustion. CRC Press, 2010. 560 p.

2. Akhmedzyanov D. A., Akhmetov Yu. M., Mikhailov A.E. Investigation of the effect of dual-circuit fuel manifold on the efficiency of the power plant in the area of filling the main circuit. Vestnik UGATU = Vestnik USATU, 2010, vol. 14, no. 4, pp. 21−35 (in Russian).

3. Lozitsky L. P., Avdoshko M. D., Berezlev В. F., Gvozdetsky I. I., Ivanenko A. A., Molochnov M.A. Aircraft DualCircuit Engines D-30KU and D-30KP: Design, Reliability and Operating Experience. Moscow, Mashinostroenie Publ., 1988. 228 p. (in Russian).

4. Starcev N.I. Pipelines for Gas Turbine Engines. Moscow, Mashinostroenie Publ., 1976. 272 p. (in Russian).

5. Puchko N. I. (compiled). Theory of Aircraft Engines. Thermodynamic Analysis of the Gas Turbine Engine Direct Reaction. Minsk, Belarusian State Academy of Aviation, 2015. 55 p. (in Russian).

6. Inozemcev A. A., Sandratsky V.L. Gas Turbine Engines. Perm, Aviadvigatel Publ., 2006. 1204 p. (in Russian).

7. Nechaev U. N., Vedorev R. M., Kotovsky V. N., Polev A.S. Theory of Aircraft Engines: in 2 parts. Moscow, Air Force Academy named after Professor N.E. Zhukovsky, 2006. 366 p. (in Russian).

8. Skibin V. A., Solonin V.I. The Work of Leading Aircraft Engine Companies to Create Promising Aircraft Engines. Moscow, Central Institute of Aviation Motors, 2004. 424 p. (in Russian).

9. Wenger U. Rolls-Royce Technology for Future Aircraft Engines. Rolls-Royce, 2014. 40 p.

10. Storm R., Skor M., Koch L.D. A Guide for Educators and Students with Chemistry, Physics, and Math Activities. NASA, 2007. 114 p.