Choice of gas temperature at the turbopump turbine inlet

Cite item


The article considers some issues of choosing the gas temperature at the inlet of a liquid rocket engine turbopump turbine. The turbine is one of the key elements of the engine and its operability depends on the gas temperature. In addition, the turbine inlet gas temperature determines its power and main parameters of the engine – chamber pressure and thrust. The higher turbine inlet gas temperature, the higher the chamber pressure and the better engine performance. The permissible temperature of the turbine structure is determined by the required safety margins and durability of the turbine rotor blades. For expendable engines, the safety margin is determined by the material short-term strength at maximum gas temperature. For reusable engines with a long service life, the safety factor is determined by the material long-term strength. The article presents the main factors affecting the choice of the generator gas temperature. It shows that one of the main factors is the non-uniformity of the temperature field at the turbine inlet. The choice of maximum admissible temperature is determined not so much by the engine schematic – with the afterburning of oxidizing or reducing generator gas, but by the strength and durability of the structure with account of the influence of temperature factors.

About the authors

A. V. Ivanov

JSC NPO Energomash;
Moscow Aviation Institute (National Research University)

Author for correspondence.

Doctor of Science (Engineering), Associate Professor, Deputy Chief Designer for Science and New Technologies;


Russian Federation


  1. Dmitrenko A.I., Ivanov A.V., Kravchenko A.G., Momotov V.I., Savin A.A., Glebov V.A. Modern oxygen-kerosene oxidiser staged-combustion cycle engines turbopumps development. Kosmonavtika. 2012. No. 2. P. 42-49. (In Russ.)
  2. Chvanov V.K., Kashkarov A.M., Romasenko E.N., Tolstikov L.A. Turbo-driven pump sets of liquid-propellant rocket engines at NPO «Energomash». Conversion in Machine Bulding of Russia. 2006. No. 1. P. 15-21. (In Russ.)
  3. Sutton G.P. Turbopumps, a historical perspective. AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference (July, 9-12, 2006, Sacramento, California). V. 9. P. 6784-6824.
  4. Ivanov A.V., Belousov A.I., Dmitrenko A.I. Turbonasosnye agregaty kislorodno-vodorodnykh ZhRD [Turbopumps for oxygen-hydrogen rocket engines]. Voronezh: Voronezh State Technical University Publ., 2011. 283 p.
  5. Ivanov A.V., Rudis M.A. Durability assessment of turbopump turbine wheel blades with manufacturing feature defects. Aviation Engines. 2020. No. 2 (7). P. 7-14. (In Russ.). doi: 10.54349/26586061_2020_2_7
  6. Barsukov O.A., Strizhenko P.P. Results of hot tests of an oxygen preburner of a liquid-propellant engine 11D58MF. Vestnik of the Samara State Aerospace University. 2014. No. 5 (47), part 3. P. 167-175. (In Russ.). doi: 10.18287/1998-6629-2014-0-5-3(47)-167-175
  7. Yagodnikov D.A., Chertkov K.O., Antonov Yu.V., Novikov A. Numerical study of the working process in the reducing gas generator of the upper stage oxygen - methane engine. Aerospace Scientific Journal of the Bauman MSTU. 2015. No. 5. P. 12-25. (In Russ.). doi: 10.7463/aersp.0515.0821899
  8. Adzhjan A.P. Features of development of oxidizer-rich preburner for multimode single-chamber engine. Proceedings of NPO Energomash. 2010. No. 27. P. 200-216. (In Russ.)
  9. Katorgin B.I., Chvanov V.K., Fatuev I.Yu., Konovalov S.G. Features of RD-120 engine forcing investigation. Vestnik otdeleniya «Kosmicheskie Energeticheskie Sistemy Novogo Pokoleniya» Rossiyskoy akademii kosmonavtiki im. K.E. Tsiolkovskogo. 2004. Iss. 1. P. 11-16. (In Russ.)

Copyright (c) 2022 VESTNIK of Samara University. Aerospace and Mechanical Engineering

Creative Commons License
This work is licensed under a Creative Commons Attribution-ShareAlike 4.0 International License.

This website uses cookies

You consent to our cookies if you continue to use our website.

About Cookies