Air-to-air heat exchangers of the high-pressure turbine rotor cooling system in modern aviation turbojet

Nesterenko, V.G.; Аббаварам, Р.Р.

doi:10.18698/2308-6033-2018-11-1827

EJSI

2018

DOI: 10.18698/2308-6033-2018-11-1827

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Air-to-air heat exchangers of the high-pressure turbine rotor cooling system in modern aviation turbojet

V.G. Nesterenko¹,

Р.Р. Аббаварам²

Abstract: Analyzes the cooling system of hightemperature turbine gas generator GTE: shows the new design of tubular air-to-air heat exchangers with an effective convective cooling and optimized system regulation.

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Cited by 3 publications

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The problems of creating a propulsion system of a new generation supersonic passenger aircraft (review)

Alendar¹,

Lanshin²,

Evstigneev³

et al. 2023

VESTNIK of Samara University. Aerospace and Mechanical Engineer

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The problems of creating a propulsion system for a new generation supersonic passenger aircraft are considered on the basis of a review of the work on the supersonic transport being carried out in the world. It is shown that the desire to achieve high flight performance and commercial effectiveness of a supersonic passenger aircraft while meeting up-to-date environmental requirements leads to contradictory technical solutions regarding the propulsion system: the location and number of engines, the scheme of the air intake and nozzle, the choice of the scheme and design parameters of the engine, the use of new high-temperature materials in the engine hot section, etc. The features of the operating conditions of the engine components of a supersonic passenger aircraft in comparison with the engines of up-to-date subsonic civil aviation aircraft and supersonic military aircraft are indicated. The calculated estimates of the influence of various technical solutions on the parameters of the supersonic passenger aircraft engine are given. Due to the complexity and multi-criterion nature of the task of creating a supersonic passenger aircraft propulsion system, its solution requires an integrated approach based on close cooperation of specialists in airframe aerodynamics, engine, etc.

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The problems of creating a propulsion system of a new generation supersonic passenger aircraft (review)

Alendar¹,

Lanshin²,

Evstigneev³

et al. 2023

VESTNIK of Samara University. Aerospace and Mechanical Engineer

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Methods and techniques used in increasing gas temperature in front of the gas turbine engine turbine

Pismennyi¹

2023

PoHEI.MB

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The paper presents methods and techniques used in increasing gas temperature in front of the turbine blades of the gas turbine engine making it possible in the aggregate to reach the gas temperature of 2300 K. Gas turbine blades made on the basis of the best nickel alloys could operate for a long time without cooling at the temperature of not more than 1300 K. Convective-film cooling today appears to be the most effective method of air cooling the blades, due to which (in combination with the heat-shielding coatings) gas temperature of 2000 K is reached in the fifth-generation gas turbine engines. Significant increase in the efficiency of the turbine blades internal cooling (convective, convective-film, porous) is obtained with using the external cooling, i.e. decreasing the cooling air temperature by the cooling resource of the external environment: atmospheric air (secondary air), water and fuel. External cooling when using the convective-film cooling makes it possible to increase gas temperature in front of the turbine blades by 0.6 ... 1.5 K for each degree in the cooling air temperature decrease. A circulating heat exchanger is proposed, which lowers the cooling air temperature almost to the ambient temperature making it possible in combination with the known methods and techniques for increasing the gas temperature (heat-resistant materials, heat-shielding coatings, convective-film cooling) to increase gas temperature in front of the turbine blades by 300...400 K and bring it up to at least 2300 K. This would allow today to start creating stoichiometric and hyperforced gas turbine engines and to increase the bypass turbojet engines efficiency up to 45%. Air-liquid cooling is a variation of the turbine blades external cooling. The possibility (technical solutions were patented) of introducing the air-liquid cooling in gas turbine engines at the high flight speeds, including the turbojet engines, was studied.

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Air-to-Air Heat Exchanger in a Turbofan Ramjet Engine

2022

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Air-to-air heat exchangers of the high-pressure turbine rotor cooling system in modern aviation turbojet

Abstract: Analyzes the cooling system of hightemperature turbine gas generator GTE: shows the new design of tubular air-to-air heat exchangers with an effective convective cooling and optimized system regulation.

Cited by 3 publications

References 0 publications

The problems of creating a propulsion system of a new generation supersonic passenger aircraft (review)

The problems of creating a propulsion system of a new generation supersonic passenger aircraft (review)

Methods and techniques used in increasing gas temperature in front of the gas turbine engine turbine

Air-to-Air Heat Exchanger in a Turbofan Ramjet Engine

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