TY - JOUR

T1 - Low-Emission Combustion Chambers of GTU: Modern Trends, Diagnostics, and Optimization (Review)

AU - Chikishev, L. M.

AU - Markovich, D. M.

N1 - The study was supported by the Russian Science Foundation, grant no. 19-79-30075, https://rscf.ru/project/19-79-30075/ . The review of emission reduction technologies was carried out within the framework of the state assignment of the Kutateladze Institute of Thermophysics (Siberian Branch, Russian Academy of Sciences).

PY - 2024/1

Y1 - 2024/1

N2 - A brief overview of the designs of low-emission gas turbine-type combustion chambers is given using the example of aircraft propulsion systems. The most promising technology that helps reduce emissions of harmful substances is the combustion of a lean premixed fuel-air mixture, but its use is limited by nonstationary phenomena that have a significant impact on flame stabilization and lead to the occurrence of thermoacoustic resonance. Currently, this technology is implemented for high-power engines by only two companies: General Electric and Rolls-Royce. Work on creating a high-thrust engine in Russia is being carried out at AO UEC-Aviadvigatel within the framework of the PD-35 program. The problems of developing low-emission combustion chambers for gas pumping units are successfully solved at AO UEC-Aviadvigatel together with the Baranov Central Institute of Aviation Motor Development (GTU-16P). One of the key areas of energy development is also the development of high-power gas turbines of the classes GTE-65, GTE-170 (PAO Power Machines), GTD-110M (ODK Saturn), and here it is necessary to solve the same problems as for gas turbine engines. The most pressing problems are predicting the occurrence of thermoacoustic self-oscillations of gas in combustion chambers and controlling them using feedback both in nominal modes and in low-power modes. A review of technologies using low-emission combustion chambers is presented, and the current state of experimental studies of the flow structure and transfer processes in model combustion chambers is considered. Examples of advanced experimental stands that simulate flow and combustion in gas turbine-type combustion chambers are given and the necessary operating parameters and the technical solutions used are indicated that allow efficient measurements using modern optical diagnostic methods.

AB - A brief overview of the designs of low-emission gas turbine-type combustion chambers is given using the example of aircraft propulsion systems. The most promising technology that helps reduce emissions of harmful substances is the combustion of a lean premixed fuel-air mixture, but its use is limited by nonstationary phenomena that have a significant impact on flame stabilization and lead to the occurrence of thermoacoustic resonance. Currently, this technology is implemented for high-power engines by only two companies: General Electric and Rolls-Royce. Work on creating a high-thrust engine in Russia is being carried out at AO UEC-Aviadvigatel within the framework of the PD-35 program. The problems of developing low-emission combustion chambers for gas pumping units are successfully solved at AO UEC-Aviadvigatel together with the Baranov Central Institute of Aviation Motor Development (GTU-16P). One of the key areas of energy development is also the development of high-power gas turbines of the classes GTE-65, GTE-170 (PAO Power Machines), GTD-110M (ODK Saturn), and here it is necessary to solve the same problems as for gas turbine engines. The most pressing problems are predicting the occurrence of thermoacoustic self-oscillations of gas in combustion chambers and controlling them using feedback both in nominal modes and in low-power modes. A review of technologies using low-emission combustion chambers is presented, and the current state of experimental studies of the flow structure and transfer processes in model combustion chambers is considered. Examples of advanced experimental stands that simulate flow and combustion in gas turbine-type combustion chambers are given and the necessary operating parameters and the technical solutions used are indicated that allow efficient measurements using modern optical diagnostic methods.

KW - aircraft propulsion systems

KW - combustion

KW - combustion chamber

KW - gas turbine unit

KW - low-emission combustion chambers

KW - optical diagnostics of combustion processes

KW - panoramic methods

UR - https://www.scopus.com/record/display.uri?eid=2-s2.0-85186765189&origin=inward&txGid=58c83035eee04ac6dd6bf5521dacf160

UR - https://www.mendeley.com/catalogue/a4542f52-409c-33e9-bf02-b2a4a21702a9/

U2 - 10.1134/S0040601524010014

DO - 10.1134/S0040601524010014

M3 - Article

VL - 71

SP - 44

EP - 64

JO - Thermal Engineering (English translation of Teploenergetika)

JF - Thermal Engineering (English translation of Teploenergetika)

SN - 0040-6015

IS - 1

ER -