Анализ Характеристик Потока Между Двумя Вращающимися Дисками В Системе Подвода Воздуха К Рабочей Лопатке Турбины На Основе Адаптированных Критериев Подобия

Didenko, Roman; Piralishvili, Shota; Shahov, Valentin

doi:10.34759/tpt-2019-11-10-434-446

2019

DOI: 10.34759/tpt-2019-11-10-434-446

|View full text |Cite

Анализ Характеристик Потока Между Двумя Вращающимися Дисками В Системе Подвода Воздуха К Рабочей Лопатке Турбины На Основе Адаптированных Критериев Подобия

Roman Didenko¹,

Shota Piralishvili

Valentin Shahov

Help me understand this report

Search citation statements

Order By: Relevance

Paper Sections

Select...

Citation Types

Supporting

Mentioning

Contrasting

Year Published

2022

Publication Types

Select...

Article1

Relationship

Self Cite0

Independent1

Authors

Journals

Cited by 1 publication

References 0 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

Various cooling systems for advanced gas turbine jets: efficiency study

Malinovskiy¹,

Nesterenko

Starodumov³

et al. 2022

EJSI

View full text Add to dashboard Cite

The paper focuses on foreign and Russian aviation bypass turbojets with an afterburner, studies the design of their turbine cooling systems, and introduces the research findings. For computational research and comparative analysis, we used Russian and foreign samples of advanced bypass turbojets with an afterburner with the most optimal technical characteristics, made calculations of the gas-dynamic parameters of their cooling systems in four critical jet operating modes. In this paper, we introduce the results of hydraulic calculations of various schemes for supplying cooling air to the nozzle and working blades of a high-pressure turbine. Relying on the results of the calculation, we comparatively analyzed the foreign and Russian cooling systems design, in terms of power indicators and efficiency of a gas turbine jet. To do this, we used the following parameters: cooling air bleeding value at maximum jet speed and cruising mode, value of cooling air leakage through the axial gaps into the flow path, the change in the cooling air bleeding value as a percentage of the flow rate through the high-pressure compressor when switching from maximum to cruising mode, i.e. adaptability of the cooling system, the temperature of the cooling air at the point of supply to the cooling cavities of the blade of the nozzle apparatus or the working blade.

show abstract

Various cooling systems for advanced gas turbine jets: efficiency study

Malinovskiy¹,

Nesterenko

Starodumov³

et al. 2022

EJSI

View full text Add to dashboard Cite

show abstract

scite is a Brooklyn-based organization that helps researchers better discover and understand research articles through Smart Citations–citations that display the context of the citation and describe whether the article provides supporting or contrasting evidence. scite is used by students and researchers from around the world and is funded in part by the National Science Foundation and the National Institute on Drug Abuse of the National Institutes of Health.

Contact Info

customersupport@researchsolutions.com

10624 S. Eastern Ave., Ste. A-614

Henderson, NV 89052, USA

This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.

Blog Terms and Conditions API Terms Privacy Policy Contact Cookie Preferences Do Not Sell or Share My Personal Information

Made with 💙 for researchers

Part of the Research Solutions Family.

Анализ Характеристик Потока Между Двумя Вращающимися Дисками В Системе Подвода Воздуха К Рабочей Лопатке Турбины На Основе Адаптированных Критериев Подобия

Cited by 1 publication

References 0 publications

Various cooling systems for advanced gas turbine jets: efficiency study

Various cooling systems for advanced gas turbine jets: efficiency study

Contact Info

Product

Resources

About