Determining the thrust of an aircraft gas turbine engine with flows mixing under condition of non-uniformity of total pressure at the engine inlet

Aeronautical and Space-Rocket Engineering

Thermal engines, electric propulsion and power plants for flying vehicles


Ezrokhi Y. A.*, Khoreva E. A.**, Kizeev I. S.**

Central Institute of Aviation Motors named after P.I. Baranov, CIAM, 2, Aviamotornaya str., Moscow, 111116, Russia



The article deals with the flight thrust determining method of a bypass engine with flows mixing in the presence of a non-uniform total pressure field at its inlet. The non-uniformity impact is taken into account for both air consumption due conventionally averaged total pressure at the inlet, and the specific thrust due to the overall pressure level reduction along the engine passage, and, respectively, the available differential pressure in the jet nozzle.

Earlier, the authors developed and patented the engine thrust determining method allowing evaluate its thrust while in flight under condition of the uniform flow at its inlet according to the measured operating conditions and external environment parameters. The presented work extends this simplified engineering method to the real case of a non-uniform total pressure field at the engine inlet. Moreover, it employs corrected values of the total pressure along the engine passage to compute the thrust.

Thus obtained, the value of the flight thrust can be used in both automated control system for its possible in-flight correction, such as partial or full flight thrust value restoration, and the complex engine diagnostics system to evaluate its deterioration rate and deterioration in performance of its separate parts and elements.

Calculated evaluations performed according the developed method with account for typical input total pressure non-uniformity revealed that the expected thrust fall will be of 8.9%, with about 8% herewith due to the air consumption reduction, and the rest is due to specific thrust decrease.


engine's flight thrust, bypass turboprop with mixing, total pressure non-uniformity at the inlet,engine measured parameters, total pressure averaging at the entrance


  1. Fokin D.B., Isyanov A.M. Vestnik Moskovskogo aviatsionnogo instituta, 2014, vol. 21, no. 4, pp. 132-143.

  2. Arkhipov D.V., Tumashev R.Z. Vestnik dvigatelestroeniya, 2013, no. 2, pp. 130-135.

  3. Greitzer E.M. Surge and rotating stall in axial flow compressors. Journal of Engineering for Power, 1976, vol. 98, no. 2, pp. 190-217.

  4. Krasnov D.S., Semernyak L.I. Tekhnika vozdushnogo flota, 1999, no. 1, pp. 36-54.

  5. Goryunov A.I., Goryunov I.M. Vestnik UGATU, 2010, no. 3, pp. 57-61.

  6. Kurzke J. Effects of Inlet Flow Distortion on the Performance of Aircraft Gas Turbines. Journal of Engineering for Gas Turbines and Power, 2008, vol. 130, no. 4, pp. 117-125.

  7. Pudovkin I.Yu., Kizeev I.S., Ezrokhi Yu.A. Svidetelstvo o gosudarstvennoi registratsii No. 2596413, 10.08.2016.

  8. Dvigateli aviatsionnye gasoturbinnye: metody i podprogrammy rascheta termodinamicheskikh parametrov vozdukha i productov sgoraniya uglevodorodnykh topliv. Rukovodyashiy tekhnicheskiy material aviatsionnoy teckhniki RTM 1677-83 (Aicraft gas turbine engines: methods and subroutines of air and hydrocarbon fuel combustion products thermodynamic parameters calculation. A guiding technical material of aviation technique, no. 1677-83), Moscow, TsIAM, 1983, 92 p.

  9. Abramovich G.N. Prikladnaya gasovaya dinamika (Applied gas dynamics), Moscow, Nauka, 1991, 600 p. — informational site of MAI

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