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Ð”Ð²ÑƒÑ ÐºÐ¾Ð½Ñ‚ÑƒÑ€Ð½Ñ‹Ð¹ турбореактивный двигатель тягой 10000 кгс для истребителя

бакалаврская работа

Ð”Ð²ÑƒÑ ÐºÐ¾Ð½Ñ‚ÑƒÑ€Ð½Ñ‹Ð¹ турбореактивный двигатель тягой 10000 кгс для истребителя

Abstract

Представлены результаты расчета тепловой схемы паротурбинной установки. Приведены результаты приближенного расчета цилиндра высокого давления, а также проточной части этого цилиндра по среднему диаметру. Выполнен расчет параметров потока по радиусу одиннадцатой ступени цилиндра высокого давления паротурбинной установки. Показаны результаты выбора профилей пера рабочей лопатки и его прочностного расчета. Осуществлен прочностной расчет хвостовика рабочей лопатки и его сопряжения с ободом диска. Произведен расчет критического числа оборотов ротора цилиндра высокого давления. По результатам выполненных расчетов спроектированы рабочая лопатка одиннадцатой ступени цилиндра высокого давления и его проточная часть.

Keywords

камера сгорания, эмиссия, газотурбинный двигатель

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citations
This is an alternative to the "Influence" indicator, which also reflects the overall/total impact of an article in the research community at large, based on the underlying citation network (diachronically).
BIP!Citations provided by BIP!
popularity
This indicator reflects the "current" impact/attention (the "hype") of an article in the research community at large, based on the underlying citation network.
BIP!Popularity provided by BIP!
influence
This indicator reflects the overall/total impact of an article in the research community at large, based on the underlying citation network (diachronically).
BIP!Influence provided by BIP!
impulse
This indicator reflects the initial momentum of an article directly after its publication, based on the underlying citation network.
BIP!Impulse provided by BIP!
0
Average
Average
Average
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