Limit values of the Brayton cycle with the use of reduced fuel characteristics


Heat energy of fuels used in cycles is a source of reaching useful effect of the heat engine cycle. The maximum effect of using the fuels can be obtained in the cycles of rocket and aircraft engines since, due to their specific nature, they carry the fuel (as well as the oxidizer in rocket engines) during the whole period of performing the mission. The energy and transport power installations are to use the fuel available in the region and reasonably-priced. Taking the most common Brayton cycle as an example we considered factors that determine the maximum coefficient of heat consumption of fuel in the cycle. Two factors are considered restricting the efficiency of the Brayton cycle efficiency: the maximum permissible limit of the strength properties of materials and the maximum level of fuel combustion products. The values of the excess air ratios in the combustion of fuels and the limiting characteristics of heat engines according to the Brayton cycle are determined. The information on the generalized approach to the assessment of the energy properties of the fuels and the impact of this measure on the Brayton cycle is presented.

About the authors

E. L. Mikheenkov

Samara State Aerospace University

Author for correspondence.

Candidate of Technical Science

Associate Professor of the Department of Heat Engineering and Heat Engines

Russian Federation

S. O. Nekrasova

Samara State Aerospace University


Engineer of the Department of Heat Engineering and Heat Engines

Russian Federation


  1. Акимов, В. М. Теория и расчет ВРД. [Текст] / В.М. Акимов. – М.: Машиностроение, 1987. – 568 с.
  2. Болгарский, А. В. Расчёт процессов в камере сгорания ЖРД. [Текст] / А.В. Болгарский – М.: Оборонгиз, 1957. – 54 с.
  3. Термодинамические свойства индивидуальных веществ: справ. изд. в 4 т. [Текст] / Л. В. Гурвич, И. В. Вейц, В. А. Медведев [и др.]; редкол.: В. П. Глушко (отв. ред.); АН СССР, Ин-т высоких температур, Гос. ин-т прикл. химии. – 3-е изд., перераб. и расшир. –М.: Наука, 1981.
  4. Квасников, А. В. Теория жидкостных ракетных двигателей [Текст]: учеб. пособие для судостроит. машиностроит. и авиац. вузов / А. В. Квасников. – Л.: Судпромгиз, 1959. – 542 с.
  5. Пеккер, Я. Л. Теплотехнические расчёты по приведённым характеристикам топлива [Текст] / Я. Л. Пеккер. – М.: Энергия, 1977. – 256 с.



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