Skip to main content

Advertisement

Log in

Development turbine air-cooling system of GTE to increase its operating parameters

  • Original Paper
  • Published:
Aerospace Systems Aims and scope Submit manuscript

Abstract

The results researching of structural schemes cooling for turbines of aircraft bypass gas turbine engines are presented. A new scheme of supplying cooling air to the high-pressure turbine working blades is proposed. The front cavity of the nozzle and rotor blades is cooled continuously, regardless of the engine’s operating mode. The air for cooling the working blade of the high-pressure turbine is supplied by the transit tube through the vane from the cavity, which is located in front of the place where is supply locking, which ensures constant boost of the blade front cavity. To eliminate the heating from the turbine disk and centrifugal pumping, the swirling device is installed directly under the blade lock, where the supply of cooling air to the cavity is organized. The turbine disk is cooled by the second row of swirling device with air taken from the secondary zone of the combustion chamber. The swirling devices rows are separated by brush seal and labyrinth. The higher efficiency of the brushes, the location of the swirling device cooling the disk under the labyrinth in the upper part of the disk, the decrease in the number of labyrinth teeth and, as a result, the pressure drop across the labyrinth between the disk cooling cavity and the dummy cavity eliminates heating air cooling blade because the main part of the hotter air is to be directed down the disk and, further, along the shaft of the high-pressure rotor into the dummy cavity.

This is a preview of subscription content, log in via an institution to check access.

Access this article

Price excludes VAT (USA)
Tax calculation will be finalised during checkout.

Instant access to the full article PDF.

Institutional subscriptions

Fig. 1
Fig. 2
Fig. 3
Fig. 4
Fig. 5
Fig. 6

Similar content being viewed by others

Abbreviations

GTE:

Gas turbine engine

LPT, HPT:

Low-/high-pressure turbine

LPC, HPC:

Low-/high-pressure compressor

NB:

Nozzle blade

RB:

Rotor blade

AtA HE:

Air-to-air heat exchanger

ALV:

Auto-lock valve of cooling air

References

  1. Hronin D (1989) Design and design of aircraft gas turbine engines. M.: Mashinostroenie. 368 p.

  2. Kalinin E (1998) Effective heat exchange surfaces. M.: Energoatomizdat. pp 408

  3. Avgustinovich V, Smotin Y, Sipatov A, Rumyantsev D. et al. (2005) Numerical simulation of unsteady phenomena in gas turbine engines. M.: Mashinostroenie pp 523

  4. Revant Reddy A., Nesterenko V (2018) Constructive methods for improving the critical nodes of the cooling system of modern high-temperature theaters of aviation gas turbine engines. Scientific—Technical Bulletin of the Volga region, № 5. Pp 73–77.

  5. Nesterenko V., Nesterenko V. Jr., Asadollahi Gokhiekh A. et al. (2014) Research and analysis of the efficiency of air cooling systems for blades of high-pressure turbines of gas turbine engines. Aerospace Engineering and Technology. No. 7. P. 83–93.

  6. Minchenko A., Nesterenko V., Malinovsky I., Revanth Reddy A. Improving the Cooling Air Supply System for the HPT Blades of High-Temperature GTE. In: Proceedings of the international conference on aerospace system science and engineering 2019. Pp 55–65.

Download references

Author information

Authors and Affiliations

Authors

Corresponding author

Correspondence to Ivan Malinovskiy.

Rights and permissions

Reprints and permissions

About this article

Check for updates. Verify currency and authenticity via CrossMark

Cite this article

Malinovskiy, I., Nesterenko, V., Starodumov, A. et al. Development turbine air-cooling system of GTE to increase its operating parameters. AS 4, 239–246 (2021). https://doi.org/10.1007/s42401-021-00086-x

Download citation

  • Received:

  • Revised:

  • Accepted:

  • Published:

  • Issue Date:

  • DOI: https://doi.org/10.1007/s42401-021-00086-x

Keywords

Navigation